The Patriot Files

C Btry 2/56th ADA

denros — Tue, 15 Jul 2003 23:36:53 -0700

by: denros

Description: A view of the launcher site at Charlie Battery, 2/56th ADA near Salzwoog (Pirmasens), Germany. Taken early 1973

BGM-71 / M-220 Tube-launc

David — Fri, 21 Mar 2003 07:38:18 -0800

by: David

Description: The TOW anti-tank missile of Iran-Contra fame was introduced for service in the US Army in 1970. Current versions are capable of penetrating more than 30 inches of armor, or "any 1990s tank," at a maximum range of more than 3,000 meters. It can be fired by infantrymen using a tripod, as well from vehicles and helicopters, and can launch 3 missiles in 90 seconds. It is primarily used in antitank warfare, and is a command to line of sight, wire-guided weapon. TOW is used to engage and destroy enemy armored vehicles, primarily tanks. Secondary mission is to destroy other point targets such as non-armored vehicles, crew-served weapons and launchers. This system is designed to attack and defeat tanks and other armored vehicles. The system will operate in all weather conditions and on the "dirty" battlefield. In May 1972, U.S. soldiers initially used the TOW in combat during the Vietnam War. This was the very first time that American troops had ever fired an American-made missile under wartime conditions. The system has also seen action in various clashes between Israel and Syria as well as during the Iran/Iraq war. During the Gulf War, in Saudi Arabia the system was represented by the HMMWV with the light forces, the Bradley Fighting Vehicle with the heavy forces, Improved TOW Vehicle with some of the forces, and the Cobra-mounted version. The TOW was one of the earliest missile systems to arrive in SWA because of the large Iraqi armored threat it was deployed with some of the first units in Saudi: the 82nd Airborne Division, the 24th Mechanized Division and the101st Airborne Division. Thousands of missiles and hundreds of launchers were used during Operation Desert Storm. Forces of other countries, including Saudi Arabia, also had TOW at their disposal. Early reports focused on the problems being experienced by US Army and Marine Corps units in hitting targets during live-fire exercises because soldiers [lacked experience firing the weapon, as well as Iraqi use of "dazzlers" intended to interfere with the guidance of Army TOW missiles and other antitank missiles. But the TOW during ODS was a primary killer of Iraqi tanks, armored personnel carriers,and other vehicles. Before the start of the coalition air campaign in January 1991, Army and Marine Corps planners noted a trend of improvement as more and more units [had] the opportunity to practice firing the TOW. The Iraqi use of dazzlers also proved to be of little concern to coalition commanders. The purpose of the dazzler is to confuse the missile guidance system so it loses track of the missile. It did not work against the TOWs used in Southwest Asia. There were no reports since the war that any of these were effective in any way against TOWs. Before the start of the actual ground offensive, US Marine units successfully employed the TOW against various Iraqi targets. On 18 January 1991, newspapers reported that U.S. Marine Corps AH-1T Cobra helicopter gunships destroyed an Iraqi command post following Iraq's sporadic shelling of the Khafji area near the Saudi-Kuwaiti border. Four Cobra gunships destroyed a building used as an Iraqi command post with TOW missiles. Accounts told by Gulf War veterans who witnessed the TOW in action during the fighting revealed several instances where TOWs did things that surprised the engineers who designed them more than the soldiers who fired them. TOW missiles proved to be a determining factor in the first ground engagement of Operation Desert Storm. During the Battle of Khafji, which took place before the start of the actual ground offensive, the TOW demonstrated a pretty unique ability. The Saudis fought Iraqi tanks with TOW missiles and drove them out of the city. At one point in the battle, the Saudis saw Iraqi soldiers on top of a water tower. Not wishing to blow up the tower, the Saudis fired a TOW, blew the ladder off the tower and left the Iraqis stranded until the end of the battle." The lethality of the TOW missile was proven beyond doubt during the 100-hour ground campaign when one of the antitank munitions fired by US troops went right through the tank it was aimed at and penetrated another tank parked next to it. Another TOW went through a six foot dirt berm and knocked out an Iraqi armored personnel carrier on the otherside. In both instances, the TOW performed a feat which it supposedly was incapable of accomplishing. Even without these rather unusual and certainly unexpected displays of its effectiveness, the TOW did better than expected. The system's deadly accuracy proved to be unstoppable even out to its maximum effective range and under degraded visibility conditions. TOW was real powerful hitting because you could tell as soon as it hit, the vehicle was dead. TOW missiles were able to kill targets while the Bradley was on the move. The basic TOW Weapon System was fielded in 1970. Manufactured by Hughes Aircraft Company, the TOW is the most widely distributed anti-tank guided missile in the world with over 500,000 built and in service in the U.S. and 36 other countries. The TOW has extensive combat experience in Vietnam and the Middle East. Iran may have obtained 1,750 or more TOWs and used TOWs against Iraqi tanks in the 1980s. The TOW 2 launcher is the most recent launcher upgrade. It is compatible with all TOW missiles. The TOW 2 Weapon System is composed of a reusable launcher, a missile guidance set, and sight system. The system can be tripod mounted. However because it is heavy, it is generally employed from the HMMWV. The missile has a 20-year maintenance-free storage life. All versions of the TOW missile can be fired from the current launcher. The TOW is a crew portable, vehicle-mounted, heavy anitarmor weapon system consisting of a launcher and one of five versions of the TOW missile. It is designed to defeat armored vehicles and other targets such as field fortifications from ranges up to 3,750 meters. After firing the missile, the gunner must keep the cross hairs of the sight centered on the target to ensure a hit. The system will operate in all weather conditions in which the gunner can see a target throughout the missile flight by using either a day or night sight. The TOW Sight Improvement Program (TSIP) effort began in 199 However, on 15 October 1991 The Secretary of the Army cancelled the TSIP because of declining budget & funding issues. The Assistant Secretary of the Army for Research, Development and Acquisition directed the PEO, Tactical Missiles to coordinate the development of an affordable alternative. The latter effort subsequently became known as the Improved Target Acquisition System (ITAS) being developed for the Army's light forces. The TOW Improved Target Acquisition System (ITAS) is a materiel change to the The ITAS is a material change to the current TOW2 ground launcher and M966 HMMWV TOW2 acquisition and fire control subsystems for first-to-deploy light forces. ITAS aides in firing all versions of TOW and builds the bridge to TOW F&F. The TOW tripod and launch tube remain unchanged. ITAS significantly increases target acquisition and engagement ranges, while retaining the capability to fire all configurations of the TOW missile. ITAS uses a second-generation forward-looking infrared system, digital components, and an eyesafe laser range finder. ITAS has an improved design with BIT/ BITES for increased maintainability and reduced logistics requirements. It also features an improved man-machine interface that improves system engagement performance. The ITAS modification kit consists of an integrated (Day/ Night Sight with Laser Rangefinder) Target Acquisition Subsystem (TAS), Fire Control Subsystem (FCS), Battery Power Source (BPS), and Modified Traversing Unit (TU). The ITAS will operate from the High Mobility Multi- Purpose Wheeled Vehicle (HMMWV) and the dismount tripod platform. The ITAS will be fielded at battalion level, replacing TOW 2 in light infantry units. The TOW Improved Target Acquisition System low- rate initial production (LRIP) I contract was awarded September 30, 1996, with a production quantity of twenty- five units. LRIP II was awarded March 1998 for a quantity of seventy-three systems for the 1st BDE Fielding in September 1999. First unit equipped (FUE) was conducted in September 1998. Increased funding for Stryker and Future Combat Systems (FCS) came as a result of Army decisions in 2002 to terminate or restructure some 48 systems in the FY ?04-?09 Program Objective Memorandum (POM) long-term spending plan. Among the systems terminated were: United Defense?s Crusader self-propelled howitzer and the A3 upgrade for the Bradley Fighting vehicle, GD?s M1A2 Abrams System Enhancement Program, Lockheed Martin?s Army Tactical Missile System Block II and the associated pre-planned product improvement version of Northrop Grumman?s Brilliant Anti-armor (BAT) munition, Raytheon?s Stinger missile and Improved Target Acquisition System, and Textron?s Wide Area Mine. The TOW system is used on the HMMWV, the M151 jeep, the armored personnel carrier, the Bradley Fighting Vehicle (BFV) COBRA helicopters, the ITV, and the US Marine Corps light armored vehicle. Considerable improvements have been made to the missile since 1970. There are six missiles available for the TOW. Three of the five TOW missile versions--Basic TOW, Improved TOW and TOW 2--are no longer being produced for US forces. However, these versions are still used by 40 allied countries. In May 1972, US soldiers initially used the TOW in combat during the Vietnam War. This was the very first time that American troops had ever fired an American-made missile under wartime conditions. The system has also seen action in various clashes between Israel and Syria as well as during the Iran/Iraq war. In Saudi Arabia the system was represented by [the HMMWV] with the light forces, the Bradley Fighting Vehicle with the heavy forces, Improved TOW Vehicle with some of the forces, and the Cobra-mounted version. The TOW was one of the earliest missile systems to arrive in SWA because of the large Iraqi armored threat. It was deployed with some of the first units in Saudi: the 82nd Airborne Division, the 24th Mechanized Division and the 101st Airborne Division. Thousands of missiles and hundreds of launchers were used during Operation Desert Storm. Forces of other countries, including Saudi Arabia, also had TOW at their disposal. Despite early reports of the problems being experienced by U.S. Army and Marine Corps units in hitting targets during live-fire exercises because soldiers lacked experience firing the weapon as well as Iraqi use of 'dazzlers' intended to interfere with the guidance of Army TOW missiles and other antitank missiles," the TOW during Operation Desert Storm was a primary killer of Iraqi tanks, armored personnel carriers,and other vehicles. Before the start of the coalition air campaign in January 1991, Army and Marine Corps planners noted a trend of improvement as more and more units [had] the opportunity to practice firing the TOW. The Iraqi use of dazzlers also proved to be of little concern to coalition commanders. The purpose of the dazzler is to confuse the missile guidance system so it loses track of the missile. It's a well known technology that does not work against the TOWs used in Southwest Asia. There were no reports since the war that any of these were effective in any way against TOWs. Before the start of the actual ground offensive, US Marine units successfully employed the TOW against various Iraqi targets. On 18 January 1991, newspapers reported that US Marine Corps AH-1T Cobra helicopter gunships destroyed an Iraqi command post following Iraq's sporadic shelling of the Khafji area near the Saudi-Kuwaiti border. Four Cobra gunships destroyed a building used as an Iraqi command post with TOW missiles. Accounts told by Gulf War veterans who witnessed the TOW in action during the fighting revealed several instances where TOWs did things that surprised the engineers who designed them more than the soldiers who fired them. TOW missiles proved to be a determining factor in the first ground engagement of Operation Desert Storm. During the Battle of Khafji, which took place before the start of the actual ground offensive, the TOW demonstrated a pretty unique ability: the Saudis fought Iraqi tanks with TOW missiles and drove them out of the city. At one point in the battle, the Saudis saw Iraqi soldiers on top of a water tower. Not wishing to blow up the tower, the Saudis fired a TOW, blew the ladder off the tower and left the Iraqis stranded until the end of the battle." The lethality of the TOW missile was proven beyond doubt during the 100-hour ground campaign when one of the antitank munitions fired by US troops went right through the tank it was aimed at and penetrated another tank parked next to it. Another TOW went through a six foot dirt berm and knocked out an Iraqi armored personnel carrier on the otherside. In both instances, the TOW performed a feat which it supposedly was incapable of accomplishing. Primary function: Guided missile weapon system. Manufacturer: Hughes (missiles); Hughes and Kollsman (night sights); Electro Design Mfg. (launchers) Size: TOW 2A Missile: Diameter: 5.87 inches (14.91 cm) Length: 50.40 inches (128.02 cm) TOW 2B Missile: Diameter: 5.8 inches (14.9 centimeters) Length: 48.0 inches (121.9 centimeters) Warhead weight 12.4 kg Maximum effective range: 2.33 miles (3.75 kilometers) Armor penetration: T-80 + / 800+ mm [>700 mm] Time of flight to maximum effective range: 2A: 20 seconds 2B: 21 seconds Weight: Launcher w/TOW 2 Mods: 204.6 pounds (92.89 kilograms) Missile Guidance Set: 52.8 pounds (23.97 kilograms) TOW 2 Missile: 47.4 pounds (21.52 kilograms) TOW 2A Missile: 49.9 pounds (22.65 kilograms) TOW 2B Missile: 49.8 pounds (22.60 kilograms) Introduction date: 1970 Unit Replacement Cost: $180,000 Launching Platforms Man portable crew of 4 HMMWV M2/M3 Bradley Fighting Vehicle Marine Corps Inventory: TOW launchers - 1247 Characteristics of the TOW missile family CHARACTERISTICS BASIC TOW I-TOW TOW 2 TOW 2A TOW 2B Missile weight (lb) 41.5 42 47.3 49.9 49.8 Weight in container (lb) 56.3 56.5 61.8 64 64 Prelaunch length (in) 45.8 45.8 45.9 45.9 46 Standoff probe (in) NA 14.6 17.4 17.4 NA Max velocity (fps/mps) 981/299 970/296 1079/329 1079/ 329 1010/309 Warhead diameter (in) 5 5 6 5 5(2x) Explosive filler (lb) 5.4 4.6 6.9 6.9 - Max range (m) 3000 3750 3750 3750 3750

BGM-71 / M-220 Tube-launc

David — Fri, 21 Mar 2003 07:38:16 -0800

Patriot PAC-3 ERINT

David — Fri, 21 Mar 2003 06:49:58 -0800

by: David

Description: Patriot Advanced Capability-3 (PAC-3) is a high/medium advanced surface-to-air guided missile air defense system. PAC-3 is a major upgrade to the Patriot system. The PAC-3 Operational Requirements Document (ORD) represents the Army Air Defense need to buy back required battlespace lost against the current and evolving tactical missile and air breathing threat. PAC-3 is needed to ounter/defeat/destroy the 2008 threat and to extend Patriot's capabilities to accomplish new/revised missions. In tandem with the upgraded radar and ground control station, PAC-3 interceptors can protect an area about seven times greater than the original Patriot system. The PAC-3 Program consists of two interrelated acquisition programs - The PAC-3 Growth Program and the PAC-3 Missile Program. The Growth program consists of integrated, complementary improvements that will be implemented by a series of phased, incrementally fielded material changes. The PAC-3 Missile program is a key component of the overall improvements of the Patriot system, it will provide essential increases in battlespace, accuracy, and kill potential. PAC-3 is a much more capable derivative of the PAC-2/GEM system in terms of both coverage and lethality. The PAC-3 has a new interceptor missile with a different kill mechanism--rather than having an exploding warhead, it is a hit-to-kill system. The PAC-3 missile is a smaller and highly efficient missile. The canister is approximately the same size as a PAC-2 canister but contains four missiles and tubes instead of a single round. Selected Patriot launching stations will be modified to accept PAC-3 canisters. The Battalion Tactical Operations Center (BTOC) is an M900 series 5-ton expandable van that has been modified by the addition of data processing and display equipment, and utilized by the battalion staff to command and control the Patriot battalion. The BTOC allows the staff to perform automated tactical planning, communications link planning, and to display situational awareness information. In the 1997 budget DOD added about $230 million for the PAC-3 through the Future Years Defense Program (FYDP) and established a realistic schedule to lower the program execution risk by extending the engineering and manufacturing development (EMD) phase of the program by ten months. System performance will be improved by re-phasing the missile and radar procurements; upgrading three launchers per battery with Enhanced Launcher Electronics Systems; and extending the battery's remote launch capability. PAC-3 Low-Rate Initial Production (LRIP) will begin in the second quarter of fiscal year 1998, and the First Unit Equipped (FUE) date is planned for the fourth quarter of fiscal year 1999. The FUE capability will consist of 16 missiles and five radars which will be placed in one battalion. As of 1996, in addition to funds being programmed for the Ballistic Missile Defense Organization, the Army planned to spend $9.6 billion for all planned purchases of Patriot missiles, $490 million for modifications and $335 million for product improvements. The Patriot Advanced Capability 3 (PAC-3) Initial Operational Test and Evaluation (IOTE) began in 2002. The two major objectives of the Initial Operational Test and Evaluation (IOTE) are: (1) To assess the improvements in system performance provided by modifications in terms of operational effectiveness, suitability, and survivability; (2) to verify that modifications do not degrade the existing capabilities. The Initial Operational Test and Evaluation (IOTE) will be the first operational integration and assessment of the complete Patriot Advanced Capability 3 (PAC-3) Configuration 3 system. The 2nd Battalion 43rd Air Defense Artillery/108th Air Defense Artillery Brigade serves as the test unit for the Initial Operational Test and Evaluation (IOTE). The unit is equipped with the complete package of Patriot Advanced Capability 3 (PAC-3) Configuration 3 hardware, PDB-5+ software and the Patriot Advanced Capability 3 (PAC-3) missile. The Patriot Project Office has issued the upgraded equipment to 2-43 Air Defense Artillery. 2-43 has completed New Equipment Training (NET) and supports testing necessary to obtain material release of the Patriot Advanced Capability 3 (PAC-3) Missile equipment. The Initial Operational Test and Evaluation (IOTE) is conducted in four phases: (1) The Sustained Operations Phase is a five-day deployment to McGregor Range using approved tactics and doctrine. 2-43 Air Defense Artillery will defend against live aircraft in accordance with threat test support package in a simulated combat environment; (2) The Interoperability Phase is a six-day demonstration of the Patriot Advanced Capability 3 (PAC-3) interoperability with current Army and Joint Theater Missile Defense Systems. This phase is conducted using the Joint Common Simulated Missile Defense System Exerciser or actual tactical equipment; (3) The Flight Mission Simulator (FMS) Phase is a 22-day test of simulated air battles. The mobile Flight Mission Simulator (FMS) is a Patriot missile system simulation used to stimulate and evaluate radar performance, engagement decision and weapon assignment (EDWA) processing and test the Patriot Advanced Capability 3 (PAC-3)’s capabilities against a full spectrum of threat targets; (4) The Missile Flight Test Phase consists of four live missile tests conducted at White Sands Missile Range and Kwajalein Missile Range. The Air Defense Artillery Directorate of the Operational Test Command conducts the planning and execution of the Initial Operational Test and Evaluation (IOTE). Once Initial Operational Test and Evaluation (IOTE) is complete, the Army Evaluation Center prepares the system evaluation report. This report provides input for the Patriot Advanced Capability 3 (PAC-3) missile Milestone III decision (full rate production) and the materiel release for the complete Patriot Advanced Capability 3 (PAC-3) system. Four PAC-3 operational tests [some involving more than one interceptor launch] between February 2002 and May 2002 resulted in three launch failures, two misses and one hit that failed to destroy the incoming warhead. A malfunctioning radar and software problems led to the misses, and the launch failures resulted from electrical problems. The Army received the first 16 PAC-3s -- a full launcher load -- in September 2001. The Army is authorized to produce the missiles at a rate of 72 a year, and Congress authorize an increase to 96 per year in fiscal 2003. The plan is to eventually produce 144 a year, leading to a total inventory of 1,159 interceptors. Unable to certify that the PAC-3 interceptor was ready for stepped-up production, in mid-2002 Pentagon put off the decision for at least a year, and planned on further testing once fixes are in place. By early 2000 the cost of each PAC-3 missile had increased from $1.9 million to over $4 million, and the estimated total program cost had risen from $3.9 billion to $6.9 billion. After design and manufacturing modifications were initiated to control costs, the estimted cost per missile dropped to about $3 million, and as of mid-2002 program officials expected to reduce the unit cost to $2 million. Initial reports of a successful intercept of a Patriot missile-as-target by a Pac-3 missile on 25 April 2002 have sinced proven to be incorrect. A US Army statement said that subsequent analysis showed that the Pac-3 impacted the target missile but failed to destroy the warhead, so the intercept was unsuccessful. A second Pac-3 in the same test failed to launch. A PAC-3 missile successfully intercepted a target ballistic missile over Kwajalein Atoll on 30 May 2002. A second missile, however, failed to launch for unknown reasons. A failure to launch also occurred in the last test on 25 April. The target was a modified Minuteman missile with a separating reentry vehicle. This was the last test in the Initial Operational Test and Evaluation (IOT&E) program, prior to a Pentagon assessment of PAC-3’s readiness for full-rate production. As of late October 2002 the Army had taken delivery of 38 PAC-3 missiles, with another 15 due for delivery by December. The military is under contract to receive an additional 126 missiles over the 2003-2004 period. Congress increased the fiscal year 2003 budget request for PAC-3 of 72 missiles by an additional 48 missiles. In late November 2002, DOD approved plans to double PAC-3 monthly production rates, with the number of missiles increasing from four to eight per month after more manufacturing equipment and a second shift of personnel were added. DOD will acquire 108 PAC-3 missiles in FY 2004. The overall procurement objective of 1,159 PAC-3 missiles remains unchanged. The larger purchases in FY-03 and FY-04 may be offset by lower production in FY-08 and FY-09. Instead of buying 216 missiles in each of those years, DOD would receive 184 units annually.

Patriot PAC-3 ERINT

David — Fri, 21 Mar 2003 06:49:58 -0800

Patriot PAC-3 ERINT

David — Fri, 21 Mar 2003 06:49:57 -0800

Arrow TMD

David — Fri, 21 Mar 2003 06:41:56 -0800

by: David

Description: Israel began work on a potential theater missile defense (TMD) system in 1986, with the signing of a Memorandum of Understanding (MOU) with the United States. While the threat posed by ballistic missiles has been a concern for Israel since the mid-1980s, Iraqi ballistic missile attacks during the Gulf War underscored the danger posed by the buildup of missile technology in the region. Given the lack of available Israeli resources for TMD development, the United States agreed to co-fund and co-develop an indigenously-produced Israeli TMD system. In 1988, the US and Israel began what was to evolve into a three-phase program to develop the ARROW series of Anti-Tactical Ballistic Missiles (ATBMs). Arrow II is intended to satisfy the Israeli requirement for an interceptor for defense of military assets and population centers and will support US technology base requirements for new advanced anti-tactical ballistic missile technologies that could be incorporated into the US theater missile defense systems. The Arrow missile, a joint international project with Israel, is a long-range interceptor that offers the United States technology infusion, including lethality data; development of optical window technology applicable to both THAAD and Navy Area Defense programs; data from stage separation at high velocities and dynamic pressures; and, interoperability development that will allow synergistic operations of Arrow with US TMD systems, if required in future contingencies. The Citron Tree battle management center, built by Tadiran, guides the Arrow 2 interceptor, developed by Israel Aircraft Industries' MLM Division. The entire anti-tactical ballistic missile project is called Homa. The Arrow 2 system can detect and track incoming missiles as far way as 500 km and can intercept missiles 50-90 km away [some sources suggest the engagement range is 16 to 48km]. The Arrow 2 uses a terminally-guided interceptor warhead to destroy an incoming missile from its launch at an altitude of 10 to 40km at nine times the speed of sound. Since the missile does not need to directly hit the target--detonation within 40-50 meters is sufficient to disable an incoming warhead. The command and control system is designed to respond to as many as 14 simultaneous intercepts. Comprised of three phases, this intiative began with the Arrow Experiments project (Phase I) that developed the preprototype Arrow I interceptor. Arrow I provided the basis for an informed GOI engineering and manufacturing decision for an ATBM defense capability. The Phase II ARROW Continuation Experiments (ACES) Program was a continuation of Phase I, and consisted of critical lethality tests using the Arrow I interceptor with the Arrow II warhead and the design, development and test of the Arrow II interceptor. The first phase of ACES, completed in the third quarter FY 94, featured critical lethality tests using the Arrow I interceptor with the Arrow II warhead. Since program initiation in 1988, Israel successfully improved the performance of its pre-prototype Arrow I interceptor to the point that it achieved a successful intercept and target destruction in June 1994. The ACES resulted in a successful missile target intercept by a single stage ARROW-1 interceptor. The second phase of ACES consisted of the design, development and test of the Arrow II interceptor, which achieved two successful intercepts of simulated SCUD missiles on August 20, 1996 and March 11, 1997. The ACES Program ended in FY 1997, upon the completion of ARROW intercept tests. The third phase is the Arrow Deployability Project (ADP), which began in FY96, aimed at integrating the entire ARROW Weapon System (AWS) with a planned User Operational Evaluation System (UOES) capability. Continuing through 2001, the ADP will be the cornerstone for US/Israeli BMD cooperation. The Arrow Deployability Program involves a total commitment of $500 million over five years, with $300 million contributed by Israel and $200 million from the United States. This will allow for the integration of the jointly developed Arrow interceptor with the Israeli developed fire control radar, launch control center and battle management center. This project will pursue the research and development of technologies associated with the deployment of the Arrow Weapon System (AWS) and will permit the GOI to make a decision regarding deployment of this system without financial participation by the US beyond the R&D stage. This effort will include system-level flight tests of the US-Israeli cooperatively developed Arrow II interceptor supported by the Israeli-developed fire control radar and fire control center. After US planning activities in FY 94/95, the Arrow Deployability Project (ADP) pursued the research and development of technologies associated with the deployment of the Arrow Weapon System and to permit the Government of Israel to make a decision on its own initiative regarding deployment of this system without financial participation by the US beyond the R&D stage. This effort included three system-level flight tests of the Arrow II interceptor and launcher supported by the Israeli-developed fire control radar and battle management control center. Studies will be done to define interfaces required for Arrow Weapon System interoperability with US TMD systems, lethality, kill assessment and producibility. Prior to obligation of funds to execute ADP R&D efforts, the President must certify to the Congress that a Memorandum of Agreement (MOA) exists with Israel for these projects, that each project provides benefits to the US, that the Arrow missile has completed a successful intercept, and that the Government of Israel continues to adhere to export controls pursuant to the Missile Technology Control Regime (MTCR). Subsequent US-Israeli cooperative R&D on other ballistic missile defense concepts would occur in the future. Although there is a general policy of denial for Category I missile programs as defined in the the Missile Technology Control Regime (MTCR) guidelines, an exception has been made for the Arrow theater missile defense program. In the Arrow program, the challenge the United States faces is to transfer capabilities to defend against missile attacks without releasing technologies for manufacturing missiles. In a test in September 1998 the Arrow 2 simulated an intercept against a point in space 97 seconds after being fired from the Palmachim military base south of Tel Aviv. The first integrated intercept flight test was successfully conducted in Israel on 01 November 1999. The Green Pine radar detected a Scud-class ballistic target and the Citron Tree battle management center commanded the launch of the Arrow II interceptor and communicated with it in-flight to successfully destroy the incoming missile. On 27 August 2001, Israel successfully tested the Arrow-2 anti-missile missile in the ninth test of the anti-ballistic missile system. The target was a missile, called the Black Sparrow, which was dropped from an IAF F-15 fighter jet at high altitude. The Arrow-2 Green Pine radar detected the missile, and the Citron fire-control center launched the Arrow-2 interceptor. The target was intercepted about 100 kilometers from the coastline, the highest and farthest that the Arrow-2 had been tested to date. An interface has been developed and delivered in Israel for AWS interoperability with US TMD systems based on a common JTIDS/Link-16 communications architecture and message protocol. The BMDO-developed Theater Missile Defense System Exerciser (TMDSE) will conduct interactive simulation exercises to test, assess, and validate the JTIDS-based interoperability between the AWS and US TMD systems. Once the TMDSE experiments are completed in FY01, the AWS will be certified as fully interoperable with any deployed US TMD systems. Israel planned to defend itself against short- and medium-range ballistic missile attacks with two Arrow 2 batteries located at only two strategic sites. According to its original 1986 schedule, the Arrow system was supposed to enter operational service in 1995. By 2000 Israel was reported to have deployed several batteries of Arrow-2 anti-missile missiles. According to some [probably erroneous] reports, these were along the Israeli- Lebanese borders. The first Arrow Weapon System (AWS) battery was deployed in Israel in early 2000. The first battery of the Arrow missiles is deployed in the center of the country, with the newly developed missile defense system entering operation on 12 March 2000. According to some reports, the first Arrow battery was operational at the Palmachim base [some reports suggest that the first battery was in the southern Negev desert at the Dimona nuclear facility]. Israel is built a second state-of-the-art anti-missile battery in the center of the country to fend off missile attacks. A second battery is to be placed at Ein Shemer east of Hadera, but was delayed by strong opposition from residents who claim its radar would be hazardous to their health. The new battery, about six miles from the central town of Hadera, was officially "for training purposes" as of mid-2002, but the sources said it already had operational capability. By late 2002 Israel was trying to make the second battery operational before any American attack on Iraq. The Arrow missile launchers from the second battery could be linked to the Green Pine radar of the Palmachim battery to improve its effectiveness. Israel had originally planned to deploy two Arrow 2 batteries but has since sought and won promises of funding for a third battery. The US Congress approved the funding of $81.6 million toward the cost of a third batteries. Each battery reportedly costs about $170m. The joint US-Israeli project, which includes missiles, interceptor launcher batteries, the Green Pine radar and the Citron Tree fire-control system, cost $1.3 billion to develop. The final bill is expected to be double the billion dollars spent so far. This cost could be reduced if the Arrow 2 is sold to other countries which have expressed interest - such as Great Britain, Turkey, Japan and reportedly India. The Green Pine radar used by the Arrow 2 was sold to India with US approval, and was deployed in India in 2001. In early 2002 American officials sought to stop Israel from selling the Arrow 2 interceptor missile to India, arguing that the sale would violate the Missile Technology Control Regime. Although the Arrow 2 interceptor could possibly achieve a range of 300 km, it is designed for intercepts at shorter ranges, and it is unclear whether it could carry a 500-kg payload to the 300-km range specified in the MTCR.

Arrow TMD

David — Fri, 21 Mar 2003 06:41:56 -0800

High-power microwave (HPM

David — Fri, 21 Mar 2003 06:17:39 -0800

by: David

Description: High-power microwave (HPM) sources have been under investigation for several years as potential weapons for a variety of combat, sabotage, and terrorist applications. Due to classification restrictions, details of this work are relatively unknown outside the military community and its contractors. A key point to recognize is the insidious nature of HPM. Due to the gigahertz-band frequencies (4 to 20 GHz) involved, HPM has the capability to penetrate not only radio front-ends, but also the most minute shielding penetrations throughout the equipment. At sufficiently high levels, as discussed, the potential exists for significant damage to devices and circuits. For these reasons, HPM should be of interest to the broad spectrum of EMC practitioners. Electromagnetic Pulse (EMP) and High Powered Microwave (HMP) Weapons offer a significant capability against electronic equipment susceptible to damage by transient power surges. This weapon generates a very short, intense energy pulse producing a transient surge of thousands of volts that kills semiconductor devices. The conventional EMP and HMP weapons can disable non-shielded electronic devices including practically any modern electronic device within the effective range of the weapon. The effectiveness of an EMP device is determined by the power generated and the characteristic of the pulse. The shorter pulse wave forms, such as microwaves, are far more effective against electronic equipment and more difficult to harden against. Current efforts focus on converting the energy from an explosive munitions to supply the electromagnetic pulse. This method produces significant levels of directionally focused electromagnetic energy. Future advances may provide the compactness needed to weaponize the capability in a bomb or missile warhead. Currently, the radius of the weapon is not as great as nuclear EMP effects. Open literature sources indicate that effective radii of “hundreds of meters or more” are possible. EMP and HPM devices can disable a large variety of military or infrastructure equipment over a relatively broad area. This can be useful for dispersed targets. A difficulty is determining the appropriate level of energy to achieve the desired effects. This will require detailed knowledge of the target equipment and the environment (walls, buildings). The obvious counter-measure is the shielding or hardening of electronic equipment. Currently, only critical military equipment is hardened e.g., strategic command and control systems. Hardening of existing equipment is difficult and adds significant weight and expense. As a result, a large variety of commercial and military equipment will be susceptible to this type of attack. The US Navy reportedly used a new class of highly secret, non-nuclear electromagnetic pulse warheads during the opening hours of the Persian Gulf War to disrupt and destroy Iraqi electronics systems. The warheads converted the energy of a conventional explosion into a pulse of radio energy. The effect of the microwave attacks on Iraqi air defense and headquarters was difficult to determine because the effects of the HPM blasts were obscured by continuous jamming, the use of stealthy F-117 aircraft, and the destruction of Iraq's electrical grid. The warheads used during the Gulf War were experimental warheads, not standard weapons deployed with fielded forces. Col. William G. Heckathorn, commander of the Phillips Research Site and the deputy director of the Directed Energy Directorate of the Air Force Research Laboratory, was presented the Legion of Merit medal during special retirement ceremonies in May 1998. In a citation accompanying the medal, Col. Heckathorn was praised for having provided superior vision, leadership, and direct guidance that resulted in the first high-power microwave weapon prototypes delivered to the warfighter. The citation noted that "Col. Heckathorn united all directed energy development within Army, Navy and Air Force, which resulted in an efficient, focused, warfighter-oriented tri-service research program." In December of 1994 he came to Kirtland to become the director of the Advanced Weapons and Survivability Directorate at the Phillips Laboratory. Last year he became the commander of the Phillips Laboratory while still acting as the director of the Advanced Weapons and Survivability Directorate. As with a conventional munition, a microwave munition is a "single shot" munition that has a similar blast and fragmentation radius. However, while the explosion produces a blast, the primary mission is to generate the energy that powers the microwave device. Thus, for a microwave munition, the primary kill mechanism is the microwave energy, which greatly increases the radius and the footprint by, in some cases, several orders of magnitude. For example, a 2000-pound microwave munition will have a minimum radius of approximately 200 meters, or footprint of approximately 126,000 square meters. Studies have examined the incorporation of a high power microwave weapon into the weapons bay of a conceptual uninhabited combat aerial vehicle. The CONOPS, electromagnetic compatibility and hardening (to avoid a self-kill), power requirements and potential power supplies, and antenna characteristics have been analyzed. Extensive simulations of potential antennas have been performed. The simulations examined the influence of the aircraft structure on the antenna patterns and the levels of leakage through apertures in the weapons bay. Other investigations examined issues concerning the electromagnetic shielding effectiveness of composite aircraft structures. Collateral damage from E-bombs is dependent on the size and design of the specific bomb. An E-bomb that utilizes explosive power to obtain its damaging microwaves will result in typical blast and shrapnel damage. Ideally, an E-Bomb would be designed to minimize and dissipate most of the mechanical collateral damage. Human exposure to microwave radiation is hazardous within several meters of the epicenter. However, there is a relatively low risk of bodily damage at further distances. Any non-military electronics within range of the E-bomb that have not been protected have a high probability of being damaged or destroyed. The best way to defend against E-bomb attack is to destroy the platform or delivery vehicle in which the E-bomb resides. Another method of protection is to keep all essential electronics within an electrically conductive enclosure, called a Faraday cage. This prevents the damaging electromagentic field from interacting with vital equipment. The problem with Faraday cages is that most vital equipment needs to be in contact with the outside world. This contact point can allow the electromagentic field to enter the cage, which ultimately renders the enclosure useless. There are ways to protect against these Faraday cage flaws, but the fact remains that this is a dangerous weakpoint. In most circumstances E-bombs are categorized as 'non-lethal weapons' because of the minimal collateral damage they create. The E-bomb's 'non-lethal' categorization gives military commanders more politically-friendly options to choose from.

Moab size comparison

David — Fri, 21 Mar 2003 06:16:32 -0800

by: David

Description: Moab size comparison

Massive Ordnance Air Blas

David — Fri, 21 Mar 2003 06:15:52 -0800

by: David

Description: The US Air Force has developed the 21,000-lb., or 95-hundred kilogram, satellite-guided Massive Ordnance Air Blast Bombs (MOAB) as a successor to the the 15,000-lb. "Daisy Cutters" used in Vietnam and Afghanistan. The Air Force is said to call MOABs (pronounced MOE-ab) the mother of all bombs. As with the earlier Daisy Cutter, these huge bombs are dropped out of the rear of the C-130 cargo plane. Unlike the Daisy Cutter, the MOAB is released without the use of a parachute. As a result, the aircraft releasing the bomb can fly at higher altitudes, thus making it safer for US pilots. This replacement for the BLU-82 bomb uses more of the slurry of ammonium nitrate and powdered aluminum used in the BLU-82. Other reports indicate that the MOAB might use tritonal explosive as opposed to the gelled slurry explosive of the BLU-82. Testing began at Eglin as part of an Air Force Research Lab Technology Demonstration Project. Work on the program began in 2002 and was set for completion in 2003.

Massive Ordnance Air Blas

David — Fri, 21 Mar 2003 06:14:57 -0800

MOAB Bomb Rear View

David — Tue, 11 Mar 2003 17:26:35 -0800

by: David

Description: MOAB, short for "massive ordnance air burst" bomb, is a 21,000-pound bomb that is pushed out the back of a C-130 transport and guided by satellite. Because it is not dropped by parachute, as was the old Daisy Cutter, the aircraft can let it go from far higher altitudes, making it safer for U.S. pilots. The MOAB's massive explosive punch is similar to a small nuclear weapon. It is intended to obliterate a command center hidden in tunnels and bunkers or a concentration of tanks. One important aspect of using this type of weapon will be psychological impact on enemy troops. It is intended to terrorize troops, drastically reducing their desire to continue the fight.

MOAB Bomb

David — Tue, 11 Mar 2003 17:25:26 -0800

Trident Fleet Ballistic M

David — Tue, 11 Feb 2003 13:00:31 -0800

by: David

Description: Function: Intercontinental ballistic missiles launched from submarines. Description: Trident I (C4) and Trident II (D5) missiles are deployed in Ohio- class (Trident) submarines, each carrying 24 missiles. The Trident II (D5) is a three-stage, solid-propellant, inertially guided FBM with a range of more than 4,000 nautical miles (4,600 statute miles). Trident II is more sophisticated than Trident I (C4) with a significantly greater payload capability. All three stages of the Trident II are made of lighter, stronger, stiffer graphite epoxy, whose integrated structure means considerable weight saving. The missile?s range is increased by the aerospike, a telescoping outward extension that reduces frontal drag by about 50 percent. Trident II is launched by the pressure of expanding gas within the launch tube. When the missile attains sufficient distance from the submarine, the first stage motor ignites, the aerospike extends and the boost stage begins. Within about two minutes, after the third stage motor kicks in, the missile is traveling in excess of 20,000 feet (6,096 meters) per second. History: Submarine launched ballistic missiles (SLBMs) have been an integral part of the strategic deterrent for six generations, starting in l956 with the U.S. Navy Fleet Ballistic Missile (FBM) Polaris (A1) program. Since then, the SLBM has evolved through Polaris (A2), Polaris (A3), Poseidon (C3) and today?s force of Trident I (C4) and Trident II (D5). Each generation has been continuously deployed at sea as a survivable retaliatory force and has been routinely operationally tested and evaluated to maintain confidence and credibility in the deterrent. Trident I (C4) was first deployed in 1979 and is planned to be deployed until phased out in the early 2000s. Trident II (D5) was first deployed in 1990 and is planned to be deployed past 2020. The Trident II (D5) missile is also provided to the United Kingdom which equips the missile with UK warheads and deploys the missile on Vanguard Class UK submarines. General Characteristics, Trident I (C4) Contractor: Lockheed Martin Missiles and Space, Sunnyvale, CA Propulsion: Three-stage solid-propellant rocket Length: 34 feet (10.2 meters) Weight: 73,000 pounds (33,142 kilograms) Diameter: 74 inches (1.8 meters) Range: 4,000 nautical miles (4,600 statute miles or 7,360 kilometers) Guidance System: Inertial Warhead: Nuclear MIRV (Multiple Independently Targetable Re-entry Vehicles) Date Deployed: 1979 General Characteristics, Trident II (D5) Contractor: Lockheed Martin Missiles and Space, Sunnyvale, CA Propulsion: Three-stage solid-propellant rocket Length: 44 feet (13.41 meters) Weight: 130,000 pounds (58,500 kilograms) Diameter: 83 inches (2.11 meters) Range: Greater than 4,000 nautical miles (4,600 statute miles, or 7,360 kilometers) Guidance System: Inertial Warhead: Nuclear MIRV (Multiple Independently Targetable Re-entry Vehicles) Date Deployed: 1990 Unit Cost: $30.9 million

Mark 56 Mine

David — Tue, 11 Feb 2003 13:00:31 -0800

by: David

Description: Description: The Mk 56 mine is an explosive-loaded (HBX-3) moored mine operationally planted by B-52H Stratofortress, F/A-18A/D Hornet, and P-3C Orion aircraft. This 2,000-pound mine consists of an anchor, mechanism section, explosive section, and flight gear. Although intended primarily as an anti-submarine weapon, it can also be used effectively against surface craft. The mine employs a magnetic firing mechanism, which uses a total-field magnetometer as its influence detector. Unlike earlier search coils which responded to changes in only one component of a ship's magnetic field, the Mine Mk 56's magnetometer responds to changes in magnitude of the total background field. The mechanism/explosive sections are painted brick red and the anchor is painted black. The Mk 56 training mine is a recoverable, inert-loaded mine identical in size and weight to its Service mine counterpart. It is designed solely for training aviation personnel flying B-52H, F/A-18A/D, and P-3C aircraft in the techniques of carrying mines and planting minefields. This mine consists of a non-functional anchor since it does not separate and moor the mine's mechanism section. It also has an inert-loaded explosive section, an arming device simulator, and functional flight gear. The mechanism and inert-loaded explosive sections are painted either white with orange stripes or orange with white stripes and the anchor remains black.

Mark 67 Submarine Launche

David — Tue, 11 Feb 2003 13:00:31 -0800

by: David

Description: Description: A Mk 67 Submarine Launched Magnetic Mine (SLMM) weighs approximately 1,790 pounds and is launched from submerged submarines. The SLMM propels itself to the planting site where it shuts down and plants itself until recovery. Approximately twenty seconds after the end of the run, all propulsion and control functions are shut down and the fuse ejector disconnects the main motor fuse disconnect. This action prevents the motor from restarting after planting. The Service SLMM is a self-propelled bottom mine with a capability that permits it to be covertly placed in a predetermined bottom planting location. It uses a Target Detection Device (TDD) Mk 57 that utilizes magnetic and seismic sensors to detect stimuli generated by enemy vessels. The SLMM's purpose is to restrict ship and submarine traffic in an operational role. The Service SLMM employs a modified Torpedo Mk 37 as the propulsion vehicle, designated the Body, Mine Main Assembly Mk 4. Forward of this main body is the Explosive Section Mk 13/Nose Section Subassembly (Loaded) which contains the PBXN?103 explosive mixture, Exploder Mechanism Mk 19, Arming Device Mk 2, and TDD Mk 57 with its Battery Mk 131. The Body, Mine Main Assembly Mk 4 is painted green, while the Explosive Section Mk 13 retains its galvanized finish. The training SLMM is used to provide a means for submarine personnel to develop the proficiency required to plant the mine in a minefield. The training SLMM also uses the Body, Mine Main Assembly Mk 4 for propulsion, modified so it does not flood at end of run and so the energized training battery does not run the propulsion motor when first mated to the main body. The Body, Mine Main Assembly Mk 4 is painted green, while the Inert Loaded Explosive Section Mk 13 or Exercise Head Assembly Mk 91 is painted either white with orange stripes or orange with white stripes.

Atlas II

David — Tue, 11 Feb 2003 12:53:21 -0800

by: David

Description: Function: Launch vehicle. Description: Atlas II is a member of the Atlas family of launch vehicles which evolved from the successful Atlas intercontinental ballistic missile (ICBM) program. It is designed to launch payloads into low earth orbit, geosynchronous transfer orbit or geosynchronous orbit. Atlas IIA is a two-and-a-half stage vehicle, primarily used to support the Defense Satellite Communications System III program. The Atlas IIA is capable of lifting approximately 14,500 pounds (6,577 kilograms) into low earth orbit and 6,100 pounds (2,767 kilograms) to a geosynchronous orbit (22,000 miles-plus). The Atlas II provides higher performance than the earlier Atlas I by using engines with greater thrust and longer fuel tanks for both stages. All three engines provide 494,500 pounds of total thrust capability. This series uses an improved Centaur upper stage - the world's first high-energy propellant stage - to increase its payload capability. Centaur propulsion is provided by a Pratt and Whitney liquid rocket engine set consisting of two engines that provide 41,000 pounds of thrust. Atlas II also has lower-cost electronics, an improved flight computer and longer propellant tanks than its predecessor, Atlas I. Atlas IIs are launched from Cape Canaveral Air Force Station, FL, by the 45th Space Wing and, in the future, will be launched by the 30th Space Wing at Vandenberg Air Force Base, CA. History: The Atlas IIA launch vehicle program is managed by the Launch Programs System Program Office at Air Force Materiel Command's Space and Missile Systems Center, Los Angeles AFB, CA. In May 1988, the Air Force chose General Dynamics (now Lockheed-Martin) to develop the Atlas II vehicle. The Atlas was originally fielded as an ICBM in the early 1960s. The Air Force replaced the Atlas ICBMs with Minuteman missiles and converted them into space launch vehicles in the late 1960s. NASA used the Atlas as a space launch vehicle as early as 1958. Atlas served as the launch vehicle for Project SCORE, the world's first communications satellite that broadcast President Eisenhower's pre-recorded Christmas message around the world. An Atlas booster carried U.S. astronaut John Glenn into orbit under Project Mercury, the first U.S. manned space program. Atlas space launch vehicles were used in all three unmanned lunar exploration programs. Atlas Centaur vehicles also launched Mariner and Pioneer planetary probes. General Characteristics, Atlas II Primary Contractor: Lockheed Martin Astronautics: airframe, assembly, test and systems integration Principal Subcontractors: Rocketdyne (Atlas engine); Pratt & Whitney (Centaur engine ) and Honeywell and Marconi (avionics) Power Plant: Three MA-5A Rocketdyne engines, two Pratt & Whitney RL10A-4 Centaur engines Thrust: 494,500 pounds (Rocketdyne engines); 41,000 pounds (Centaur engines) Length: Up to 156 feet (47.54 meters); 16-foot-high engine cluster (4.87 meters) Gross Liftoff Weight: 414,000 pounds (204,343 kilograms) Core Diameter: 10 feet (3.04 meters) First Launch: Feb. 10, 1992 Launch Site: Cape Canaveral Air Station, FL Inventory: Unavailable

Delta II Medium Launch Ve

David — Tue, 11 Feb 2003 12:53:21 -0800

by: David

Description: Function: The Delta II is an expendable launch, medium-lift vehicle used to launch Navstar Global Positioning System (GPS) satellites into orbit, providing navigational data to military users. Additionally, the Delta II launches civil and commercial payloads into low-earth, polar, geo-transfer and geosynchronous orbits. Description: The Delta II stands a total height of 125.9 feet (37.8 meters). The payload fairing -- the shroud covering the third stage and the satellite -- is 9.5 ft wide to accommodate the GPS satellite. A 10-foot (3.3 meters) wide fairing also is available for larger payloads. Six of the nine solid-rocket motors that ring the first stage separate after one minute of flight, and the remaining three ignite, then separate, after burn-out one minute later. The Delta II is launched primarily from Cape Canaveral AFS, FL, but is also launched from Vandenberg Air Force Base, CA. Members of Air Force Space Command's 45th Space Wing, with headquarters at Patrick AFB, FL, and 30th Space Wing at Vandenberg are responsible for the Delta II's military launch missions. History: The Delta launch vehicle family began in 1959 when NASA's Goddard Space Flight Center awarded a contract to Douglas Aircraft Company (now Boeing) to produce and integrate 12 space-launch vehicles. The Delta used components from the U.S. Air Force's Thor intermediate-range ballistic missile as its first stage and the U.S. Navy's Vanguard launch-vehicle program as its second. The first Delta was launched from Cape Canaveral Air Force Station on May 13, 1960 and had the ability to deliver a 100-pound spacecraft into geostationary transfer orbit. In January 1987 the Air Force awarded a contract to McDonnell Douglas, now Boeing, for construction of 18 Delta IIs to launch Navstar GPS satellites, originally programmed for launch on the space shuttle. Since then, the order expanded to accommodate 28 GPS satellite-dedicated launch vehicles. The first Delta II was successfully launched on Feb. 14, 1989, at Cape Canaveral. There are two primary versions of the Delta II (6925 and 7925). The Delta 6925, the first version, carried the initial nine GPS satellites into orbit. The Delta program has more than 245 successful domestic and foreign military and commercial launches. The Delta accomplished many firsts over the years. These include the first international satellite, Telstar I, in 1962; the first geosynchronous-orbit satellite, Syncorn II, in 1963; and the first commercial communications satellite, COMSAT I, in 1965. General Characteristics, Delta II Builder: Boeing Company, Expendable Launch Systems Power Plant, First Stage: One Rocketdyne RS-27 and two LR-101-NA-11 vernier engines; both use refined kerosene and liquid oxygen as its propellants; thrust (sea level), 200,000 pounds Power Plant, Second Stage: Restartable Aerojet AJ10-110K motor; uses nitrogen tetroxide and Aerozine 50 propellants; thrust, 9,750 pounds Payload Assist Module: If used, Star-48B Solid-fuel Rocket, 14,920 pounds Nine Alliant Techsystems strap-on graphite-epoxy motors surround the first stage for augmented lift-off; thrust 100,270 pounds Thrust at Liftoff: 699,250 pounds Height: 125 feet, 9 inches (38.32 meters) Diameter: Fairing: 9.5 feet (2.87 meters) Core: 8 feet (2.4 meters) Weight: 511,190 pounds (231,870 kilograms) Lift Capability: Can carry payloads into near-earth orbits (approximately 100 nautical miles [160 kilometers] in space) Can lift up to 11,100 pounds (4,995 kilograms) into a 28-degree circular near-earth orbit and up to 8,420 pounds (3,789 kilograms) into a 90-degree polar near-earth orbit Can carry up to 4,010 pounds (1,804.5 kilograms) into geo-transfer orbit (approximately 12,000 miles [19,200 kilometers]) and up to 2,000 pounds (909 kilograms) into geosynchronous orbit (approximately 22,000 miles [35,200 kilometers]) Payloads: Three-stage Delta 7925 has carried 29 GPS Block II satellites into orbit, with another 19 slated to launch as needed National Reconnaissance Office's GeoLITE payload will also use a Delta 7925 Two-stage Delta 7920 launched the Advanced Research and Global Observation Satellite, an Air Force Space Test Program mission. Guidance System: Delta Redundant Inertial Flight Control Assembly manufactured by Allied Signal Aerospace Date Deployed: November 26, 1990 (7920/7925 series) Launch Sites: Space Launch Complex 17, Cape Canaveral AFS, FL Space Launch Complex 2, Vandenberg AFB, CA Inventory: Active force, 2 (with more on order) Unit Cost: Unavailable

LG-118A Peacekeeper

David — Tue, 11 Feb 2003 12:53:21 -0800

by: David

Description: Function: The Peacekeeper missile is America's newest intercontinental ballistic missile (ICBM). Its deployment fulfilled a key goal of the strategic modernization program and increased strength and credibility to the ground-based leg of the U.S. strategic triad. Since the end of the Cold War, the United States has been revising its strategic policy and has agreed to eliminate the multiple re-entry vehicle Peacekeeper ICBMs when Russia ratifies the Strategic Arms Reduction Treaty II. Description: The Peacekeeper is capable of delivering 10 independently targeted warheads with great accuracy. It is a four-stage rocket ICBM system consisting of two major sections: the boost system and the post-boost vehicle system that includes the re-entry system. The boost system consists of four rocket stages that launch the missile into space. These rocket stages are mounted atop one another and fire successively. Each of the first three stages exhausts its solid propellant materials through a single movable nozzle that guides the missile along its flight path. Following the burnout and separation of the boost system's third rocket stage, the fourth stage post-boost vehicle system, in space, maneuvers to deploy the re-entry vehicles in sequence. The post-boost vehicle system is the Peacekeeper Stage IV that has a guidance and control system and re-entry system. The post-boost vehicle rides atop the boost system. Stage IV weighs about 2,500 pounds (1,333 kilograms) and is 3.5 feet (1.07 meters) long. The top section of the Peacekeeper post-boost vehicle is the re-entry system. It consists of the deployment module, up to 10 cone-shaped re-entry vehicles and a protective shroud. The shroud protects the re-entry vehicles during ascent. It is topped with a nose cap, containing a rocket motor to separate it from the deployment module. The deployment module provides structural support for the re-entry vehicles and carries the electronics needed to activate and deploy them. The vehicles are covered with material to protect them during re-entry through the atmosphere to their targets and are mechanically attached to the deployment module. The attachments are unlatched by gas pressure from an explosive cartridge broken by small, exploding bolts, which free the re-entry vehicles, allowing them to separate from the deployment module with little disturbance. Each deployed re-entry vehicle follows a ballistic path to its target. History: The Air Force successfully conducted the first test flight of the Peacekeeper June 17, 1983, from Vandenberg Air Force Base, CA. The missile traveled 4,190 miles (6,704 kilometers) before dropping six unarmed test reentry vehicles to planned target sites in the Kwajalein Missile Test Range in the Pacific Ocean. The first two test phases consisted of 12 test flights to ensure the Peacekeeper's subsystems performed as planned, and to make final assessments of its range and payload capability. The missile was fired from aboveground canisters in its first eight tests. Thereafter, test flights were conducted from test launch facilities reconfigured to simulate operational Peacekeeper sites. The Air Force achieved initial operational capability of 10 deployed Peacekeepers at F.E. Warren AFB, WY, in December 1986. Full operational capability was achieved in December 1988 with the establishment of a squadron of 50 missiles. The former Ballistic Missile Office began full-scale development of the Peacekeeper in 1979. This organization, formerly located at San Bernardino, CA, integrated the activities of more than 27 civilian contractors and numerous subcontractors to develop and build the Peacekeeper system. General Characteristics, LG-118A Peacekeeper Contractor: Boeing Aerospace and Electronics Assembly and Test: Lockheed Martin and Denver Aerospace Power Plant: First three stages - solid propellant; fourth stage - storable liquid (by Thiokol, Aerojet, Hercules and Rocketdyne) Thrust: First stage, 500,000 pounds Length: 71 feet (21.8 meters) Weight: 195,000 pounds (87,750 kilograms) including re-entry vehicles Diameter: 7 feet, 8 inches (2.3 meters) Range: Greater than 6,000 miles (5,217 nautical miles) Speed: Approximately 15,000 miles per hour at burnout (Mach 20 at sea level) Warheads: 10 Avco MK21 re-entry vehicles Guidance System: Inertial; integration by Boeing North American IMU: Northrop and Boeing North American Inventory: Active force, 50 ANG, 0 Reserve, 0 Date Deployed: December 1986 Unit Cost: $70 million

LGM-30 Minuteman III

David — Tue, 11 Feb 2003 12:53:21 -0800

by: David

Description: Function: The LGM-30G Minuteman intercontinental ballistic missile (ICBM) is an element of the nation's strategic deterrent forces. Description: The Minuteman is a strategic weapon system using a ballistic missile of intercontinental range. Missiles are dispersed in hardened silos to protect against attack and connected to an underground launch control center through a system of hardened cables. Launch crews, consisting of two officers, perform around-the-clock alert in the launch control center. A variety of communication systems provide the National Command Authorities with highly reliable, virtually instantaneous direct contact with each launch crew. Should command capability be lost between the launch control center and remote missile launch facilities, specially-configured E-6B airborne launch control center aircraft automatically assume command and control of the isolated missile or missiles. Fully qualified airborne missile combat crews aboard airborne launch control center aircraft would execute the NCA orders. An extensive life extension program is under way to keep the missiles safe, secure and reliable well into the 21st century. These major programs include: replacement of the aging guidance system, remanufacture of the solid-propellant rocket motors, replacement of standby power systems, repair of launch facilities, and installation of updated, survivable communications equipment, and new command and control consoles to enhance immediate communications. History: The Minuteman weapon system was conceived in the late 1950s and Minuteman I was deployed in the early 1960s. Minuteman was a revolutionary concept and an extraordinary technical achievement. Both the missile and basing components incorporated significant advances beyond the relatively slow-reacting, liquid-fueled, remotely-controlled intercontinental ballistic missiles of the previous generation. From the beginning, Minuteman missiles have provided a quick-reacting, inertially guided, highly survivable component to America's nuclear Triad. Minuteman's maintenance concept capitalizes on high reliability and a "remove and replace" approach to achieve a near 100 percent alert rate. Through state-of-the-art improvements, the Minuteman system has evolved to meet new challenges and assume new missions. Modernization programs have resulted in new versions of the missile, expanded targeting options, improved accuracy and survivability. Today's Minuteman weapon system is the product of almost 35 years of continuous enhancement. The current Minuteman force consists of 500 Minuteman III's located at F.E. Warren Air Force Base, Wyo., Malmstrom AFB, Mont., and Minot AFB, N.D. The last round of base realignment and closing decisions has forced a realignment of Minuteman missiles from Grand Forks AFB, N.D., to Malmstrom AFB. The possible implementation of Start II, means that Minuteman III will become the only land-based ICBM in the Triad. General Characteristics, LGM-30 Minuteman III Contractor: Boeing Corporation Power Plant: Three solid-propellant rocket motors First stage: Thiokol Second stage: Aerojet-General Third stage - United Technologies Chemical Systems Division Thrust: First stage, 202,600 pounds Length: 59.9 feet (18 meters) Weight: 79,432 pounds (32,158 kilograms) Diameter: 5.5 feet (1.67 meters) Range: 6,000-plus miles (5,218 nautical miles) Speed: Approximately 15,000 mph (Mach 23 or 24,000 kph) at burnout Ceiling: 700 miles (1,120 kilometers) Load: Re-entry vehicle: Lockheed Martin Missiles and Space MK 12 or MK 12A Guidance System: Inertial system: Boeing North American Ground electronic/security system: Sylvania Electronics Systems and Boeing Co. Inventory: Active force, 500 ANG, 0 Reserve, 0 Date Deployed: June 1970, production cessation: December 1978 Unit Cost: $7 million

Titan IVB

David — Tue, 11 Feb 2003 12:53:21 -0800

by: David

Description: Function: The Titan IVB is a heavy-lift space launch vehicle used to carry government payloads such as Defense Support Program, Milstar and National Reconnaissance Office satellites into space. It is launched from Patrick Air Force Base, Fla., and Vandenberg AFB, CA. Description: The Titan IVB is the most recent and largest unmanned space booster used by the Air Force. It provides assured capability for launch of space shuttle-class payloads. The vehicle is flexible because it can be launched with no upper stage, or one of two optional upper stages for greater and varied carrying ability. The Titan IVB consists of a liquid-fueled core and two large solid rocket boosters for increased performance. During a launch the strap-on rocket boosters are fired first. When the solid propellant is almost depleted, about two minutes into flight, the first stage is fired and the solid motors are separated from the vehicle. The second and upper stages are fired as the previous stage is depleted of fuel and separated. The Titan IVB's core consists of an LR87 liquid-propellant rocket that features structurally independent tanks for its fuel (Aerozine 50) and oxidizer (Nitrogen Tetroxide). This minimizes the hazard of the two mixing if a leak should develop in either tank. Additionally the engines' propellant can be stored in a launch-ready state for extended periods. The use of propellants stored at normal temperature and pressure eliminates delays and gives the Titan IVB the capability to meet critical launch windows. The second stage consists of an LR91 liquid propellant rocket engine attached to an airframe, like stage 1. History: The Titan family was established in October 1955 when the Air Force awarded Lockheed Martin (the former Martin Company) a contract to build a heavy-duty space system. It became known as the Titan I, the nation's first two-stage, intercontinental ballistic missile (ICBM) and first underground silo-based ICBM. Titan I provided many structural and propulsion techniques that were later incorporated into the Titan II. Years later, the Titan IVB evolved from the Titan III family and is similar to the Titan 34D. It was originally developed as a backup for the space shuttle in the 1980s, but has become a mainstay for heavy payloads. The last Titan IVA was launched in August 1998. The Titan IVB is an upgraded rocket having a new guidance system, flight termination system, ground checkout system, solid rocket motor upgrade and a 25 percent increase in thrust capability. The first Titan IVB flew on Feb. 23, 1997. General Characteristics, Titan IVB Builder: Lockheed-Martin Astronautics Power Plant, First Stage: Stage 0 currently consists of two solid-rocket motors; Stage 1 uses an LR87 liquid-propellant rocket engine; Stage 2 uses the LR91 liquid-propellant engine Optional upper stages include the Centaur and inertial upper stage Thrust: Solid rocket motors provide 1.7 million pounds per motor at liftoff First stage provides an average of 548,000 pounds and second stage provides an average of 105,000 pounds Optional Centaur upper stage provides 33,100 pounds Inertial upper stage provides up to 41,500 pounds Lift Capability: Can carry up to 47,800 pounds (21,682 kilograms) into a low-earth orbit up to 12,700 pounds (5,761 kilograms) into a geosynchronous orbit when launched from Cape Canaveral Air Station, FL Can carry up to 38,800 pounds (17,599 kilograms) into a low-earth polar orbit when launched from Vandenberg AFB. Using inertial upper stage, can transport up to 5,250 pounds (2,381 kilograms) into geosynchronous orbit Length: Up to 204 feet (62.17 meters) Maximum Takeoff Weight: Approximately 2.2 million pounds (997,913 kilograms) Guidance System: Ring laser gyro guidance system manufactured by Honeywell Date Deployed: June 1989 Launch Sites: Cape Canaveral AS, FL Vandenberg AFB, CA Inventory: 14 (changes with each launch) Unit Cost: Approximately $250-350 million, depending on launch configuration

Mk155 Mine Clearance Laun

David — Thu, 16 Jan 2003 23:48:43 -0800

by: David

Description: Function: To clear a lane through a minefield during breaching operations. The MK155 Launcher, Mine Clearance (LMC) is part of the Mark 2 Mine Clearance System which also includes one M58A3/A4 Linear Demolition Charge (LDC) and one MK22 Mod 3/4 Rocket. The MK155 LMC, mounted on an M353 Trailer Chassis, will normally be towed by an Assault Amphibious Vehicle (AAVP7A1). The LDC will clear a lane 100 meters long by 16 meters wide and will be the initial minefield breaching asset used. Because the LDC is only effective against single impulse, non-blast resistant, pressure fused mines, a mechanical proofing device must also be used in a lane that has been explosively breached. Description: The MK155 LMC is a hydraulic system which can be installed onto any M353 Trailer Chassis. All of the hydraulics are self contained. A hand pump is used to store hydraulic pressure in an accumulator. A lanyard, which runs from the accumulator to inside the towing vehicle, is used to remotely raise the launch rail to its proper firing position. A power cable is fed from the launcher to the towing vehicle which enables the operator to use the M34 Blasting Machine to launch the MK22 Rocket and detonate the LDC from inside the vehicle. The over-pressure created by the LDC will clear a path 16 meters wide and 100 meters long through a minefield consisting of single impulse, non-blast resistant, pressure-fused mines. The width of the lane and the ability to neutralize mines is dependent upon the mine type and fusing. History: The LDC has been in the US inventory since the 1960's, with wartime use in Vietnam. The early employment, used during the Viet Nam war, was with the LVTE tractor. When the LVTP7 family of vehicles replaced the LVTP5 family of vehicles, an engineer variant of the amphibious tractor was not procured. Throughout the late 1960's and into the late 1970's, the only way to employ the LDC was with a ground-mounted system. Due to the difficulty in moving and employing the LDC in this configuration, the MK155, Trailer Mounted Mine Clearing Line Charge Launcher was developed so that the LDC could be towed behind a tracked vehicle. The trailer-mounted LDC solved the mobility problem for ground operations but did not provide an amphibious breaching capability. General Characteristics, MK155 Mine Clearance Launcher Manufacturer: Several Host Vehicle: M353 General Purpose, 3-1/2 Ton, 2-Wheeled, Trailer Chassis Weight (includes trailer and launch railing): 3,775 pounds (1,699 kilograms) Fully loaded (includes 1 Linear Demolition Charge and 1 rocket): 6,405 pounds (2,883 kilograms) Shipping Height: 74 inches (1.88 meters) Unit Cost: $4,660

M18A1 Claymore

David — Thu, 16 Jan 2003 23:48:43 -0800

by: David

Description: Description: The M18A1 antipersonnel mine was standardized in 1960, and replaced the M18 antipersonnel mine. Both mines are similar in appearance and functioning. The M18A1 claymore mine is a fragmentation munition that contains 700 steel balls and 682 grams of composition C4 explosive. It weighs 1.6 kilograms and can be detonated by command It is activated by electric or nonelectric blasting caps that are inserted into the detonator well. When employed in the controlled role, it is treated as a one-shot weapon. It is primarily designed for use against massed infantry attacks; however, its fragments are also effective against light vehicles. The M18A1 mine is equipped with a fixer plastic slit-type sight (knife-edge sight on later model), adjustable legs, and two detonator wells. The number of ways in which the Claymore may be employed is limited only by the imagination of the user. The Claymore is used primarily as a defensive weapon, but has its application in the offensive role. It must be emphasized that when the Claymore is referred to as a weapon, this implies that it is employed in the controlled role. In the uncontrolled role, the Claymore is considered a mine or boobytrap. When detonated, the M18A1 mine will deliver its spherical steel fragments over a 60? fan-shaped pattern that is 2 meters high and 50 meters wide at a range of 50 meters. These fragments are moderately effective up to a range of 100 meters and can travel up to 250 meters forward of the mine. The optimum effective range (the range at which the most desirable balance is achieved between lethality and area coverage) is 50 meters.

M2 SLAM

David — Thu, 16 Jan 2003 23:48:43 -0800

by: David

Description: Description: The M2 selectable lightweight attack munition (SLAM) is a multipurpose munition with an anti-tamper feature. The SLAM is compact and weighs only 1 kilogram, so it is easily portable. The SLAM is intended for use against APCs, parked aircraft, wheeled or tracked vehicles, stationary targets (such as electrical transformers), small fuel-storage tanks (less than 10,000-gallon), and ammunition storage facilities. The explosive formed projectile (EFP) warhead can penetrate 40 millimeters of homogeneous steel. The SLAM has two models -- one is self-neutralizing (M2) and the other is self-destructing (M4): The M2 is solid green and has no labels, brands, or other distinguishing marks. This device is used by SOF and is not available to other units. The M4 is green with a black warhead (EFP) face. This device is normally used by units designated as light, airborne, air assault, crisis response, and rapid deployment. The SLAM has four possible modes of detonation--bottom attack, side attack, timed demolition, and command detonation. Bottom Attack: The SLAM has a built-in magnetic sensor, so it can be used as a magnetic- influenced munition against trucks and light armored vehicles. It can be concealed along trails and roads where target vehicles operate and can be camouflaged with dry leaves, grass, and so forth without affecting EFP performance. Mud, gravel, water, and other debris that fill the EFP cup have minimal impact on EFP formation and effectiveness as long as the debris does not extend beyond the depth of the EFP cup. The magnetic sensor is designed to trigger detonation when it senses a vehicle's overpass. For the EFP to form properly, it needs a minimum of 13 centimeters from the point of emplacement to the target. The bottom-attack mode is active when the selector switch is set to 4, 10, or 24 HOURS and the passive infrared sensor (PIRS) cover is in place. The SLAM will self-destruct (M4) or self-neutralize (M2) if the selected time expires before the SLAM is detonated by a vehicle. Side Attack: The SLAM is equipped with a PIRS that was specifically developed for the side-attack mode. The PIRS detects trucks and light armored vehicles by sensing the change in background temperature when vehicles cross in front of the PIRS port. The PIRS is directional and aligned with the EFP when the device is aimed. The side-attack mode is active when the SLAM selector switch is set to 4, 10, or 24 HOURS and the PIRS cover is removed to expose the PIRS. The SLAM will self-destruct (M4) or self-neutralize (M2) if the selected time expires before it is detonated by a vehicle. Timed Demolition: The SLAM's built-in timer will trigger detonation at the end of a selected time. The timed-demolition mode is active when the SLAM selector switch is set to 15, 30, 45, or 60 MINUTES. In this mode, the magnetic sensor and the PIRS are inoperable, and the SLAM will detonate after the selected time has expired. Command Detonation: This mode provides manual warhead initiation using standard military blasting caps and a priming adapter (Figure 4-7). The command-detonation capability bypasses the SLAM's fuse and safing and arming (S&A) assembly. The SLAM has an anti-tamper feature that is only active in the bottom- and side-attack modes. The SLAM will detonate when an attempt is made to change the selector switch's position after arming.

M93 Hornet

David — Thu, 16 Jan 2003 23:48:43 -0800

by: David

Description: Description: The M93 Hornet is an anti-tank off-route munition made of lightweight material (35 pounds) that one person can carry and employ. The Hornet is a non-recoverable munition that is capable of acquiring targets by using sound and motion detection methods. It will automatically search, detect, recognize, and engage moving targets by using top attack at a standoff distance up to 100 meters from deployment site. It is employed by combat engineers, rangers, and SOF. The RCU is a hand-held encoding unit that interfaces with the Hornet when the remote mode is selected at the time of employment. After encoding, the RCU can be used to arm the Hornet, reset its self-destruct (SD) times, or destroy it. The maximum operating distance for the RCU is 2 kilometers. High winds, heavy rain, snow, ice, extreme cold, and extreme heat reduce the Hornet's ability to detect targets at maximum range. Radio-frequency (RF) jamming devices (such as the hand-emplaced, expandable jammer [HEXJAM]), limit the Hornet's communication capabilities if they are placed in the munition field, but they will not affect the Hornet's ability to engage targets and will not damage the system. RF jamming devices will also affect the remote arming of current Hornet systems. The Hornet's active battery pack is inserted during pre-arming and has an estimated life of four hours. The active battery pack powers the munition from the time it is inserted until the end of the safe-separation time, when the built-in reserve battery is activated. To prevent munitions from becoming duds, do not pre-arm them too early. Allow adequate time for traveling to the obstacle site, emplacing mines, throwing arming switches, and expiration of safe-separation times. Once the Hornet is armed and the self-test is performed, the munition will remain active until its SD time expires or until it is encountered. The SD time (4 hours, 48 hours, 5 days, 15 days, or 30 days) is determined by the user. The munition will self-detonate after the SD time has expired. Hornet munitions have an employed life of 60 days in the pre-armed mode (remote arming) and 30 days in the armed mode. If the temperature exceeds 100?F, the employed life drops to 15 days in the pre-armed mode and 30 days in the armed mode.

SLAM-ER

David — Thu, 16 Jan 2003 23:24:36 -0800

by: David

Description: Function: The Standoff Land Attack Missile - Expanded Response (SLAM-ER), an evolutionary upgrade to the combat-proven SLAM, is a day/night, adverse weather over-the-horizon, precision strike missile. Description: SLAM-ER addresses the Navy's requirements of a precision-guided Standoff Outside of Area Defense weapons. SLAM-ER extends the weapon system's combat effectiveness into the next century, providing an effective, long range, precision strike option for both pre-planned and Target of Opportunity attack missions against land and ship targets. Most significant among these enhancements are: a highly accurate, GPS-aided guidance system; improved missile aerodynamic performance characteristics that allow both greater range and more effective terminal attack profiles; a redesigned ordnance section for increased penetrating power and lethality; and a more user-friendly interface for both Man-in-the-Loop control and mission planning. SLAM-ER will be the first weapon to feature Automatic Target Acquisition (ATA), a revolutionary technological breakthrough which will automate and improve target acquisition in cluttered scenes, and overcome most countermeasures and environmentally degraded conditions. History: SLAM-ER roots go back to the original Harpoon anti-ship missile placed in the fleet in the late 1970s. Because of emerging operational requirements, missile for land attack was developed as a derivative of the Harpoon. The SLAM was developed and fielded in less than 48 months and was successfully employed by F/A-18 and A-6 aircrews in Desert Storm even before operational testing had begun. The potential of SLAM spurred further development of its standoff capabilities, to provide even greater improvements in range, accuracy, warhead penetration, dive angle and mission planning. Because of the Navy's growing focus on littoral warfare, SLAM-ER program initiatives were formalized in December 1994 when the Assistant Secretary of the Navy for Research, Development and Acquisition gave the go ahead to proceed with engineering and manufacturing development and accelerate SLAM-ER production and deployment to the fleet. General Characteristics, SLAM ER Missile Systems Contractor: The Boeing Company Power Plant: Teledyne Turbojet and solid propellant booster for surface and submarine launch Thrust: Greater than 600 pounds (272.16 kilograms) Length: 14 feet 4 inches (4.36 meters) Weight: 1,400 pounds (635.04 kilograms) Diameter: 13.5 inches (34.29 centimeters) Wingspan: 7.158 feet (2.1819 meters) Range: Over-the-horizon, in excess of 150 nautical miles (277.95 kilometers) Speed: High subsonic Guidance System: Ring laser gyro Inertial Navigation System (INS) with multi-channel GPS Infrared seeker for terminal guidance with Man-in-the-Loop control data link from the controlling aircraft Upgraded missiles will incorporate Automatic Target Acquisition (ATA) Inventory: Classified Date Deployed: Mid-1999 Unit Cost: $500,000

TOW Missile

David — Thu, 16 Jan 2003 23:24:36 -0800

by: David

Description: Function: Guided missile weapon system. Description: The basic TOW Weapon System was fielded in 1970. This system is designed to attack and defeat tanks and other armored vehicles. It is primarily used in antitank warfare, and is a command to line of sight, wire-guided weapon. The system will operate in all weather conditions and on the "dirty" battlefield. The TOW 2 launcher is the most recent launcher upgrade. It is compatible with all TOW missiles. The TOW 2 Weapon System is composed of a reusable launcher, a missile guidance set, and sight system. The system can be tripod mounted. However because it is heavy, it is generally employed from the HMMWV and LAV-AT. The missile has a 20-year maintenance-free storage life. All versions of the TOW missile can be fired from the current launcher. History: The original TOW missile had a diameter of 5 inches and a range of 3000 meters. Considerable improvements have been made to the missile since 1970. The Improved TOW (ITOW) was delivered in 1982. This missile has a 5-inch diameter warhead, and includes an extended probe for greater standoff and penetration. An enhanced flight motor was included in the ITOW, increasing the missile's range to 3750 meters. The TOW 2 series of improvements includes TOW 2 Hardware, TOW 2 Missile, TOW 2A Missile, and TOW 2B Missile. The TOW 2 Hardware improvements included a thermal beacon guidance system enabling the gunner to more easily track a target at night and numerous improvements to the Missile Guidance System (MGS). The TOW 2 Missile has a 6-inch diameter warhead and the extended probe first introduced with ITOW. The TOW 2B Missile incorporates new fly-over, shoot-down technology. General Characteristics, TOW Missile Weapon System Manufacturer: Hughes Aircraft Corporation and Raytheon Corporation Length: TOW 2A Missile: 50.40 inches (128.02 centimeters) TOW 2B Missile: 48.0 inches (121.9 centimeters) Weight: Launcher w/TOW 2 Mods: 204.6 pounds (92.89 kilograms) Missile Guidance Set: 52.8 pounds (23.97 kilograms) TOW 2 Missile: 47.4 pounds (21.52 kilograms) TOW 2A Missile: 49.9 pounds (22.65 kilograms) TOW 2B Missile: 49.8 pounds (22.60 kilograms) Diameter: TOW 2A Missile: 5.87 inches (14.91 centmeters) TOW 2B Missile: 5.8 inches (14.9 centimeters) Maximum Effective Range: 2.33 miles (3.75 kilometers) Armor Penetration: T-80 + Time of Flight to Maximum Effective Range: TOW 2A Missile: 20 seconds TOW 2B Missile: 21 seconds Inventory: 1,247 TOW launchers Introduction Date: 1970 Unit Cost: $180,000

1 comment

GBU-15

David — Thu, 16 Jan 2003 23:24:36 -0800

by: David

Description: Function: The Guided Bomb Unit or GBU-15 is an unpowered, glide weapon used to destroy high value enemy targets. It was designed for use with F-15E, F-111F and F-4 aircraft, but the U.S. Air Force is currently only deploying it from the F-15E. Description: The weapon consists of modular components that are attached to either a MK-84 general purpose or BLU-109 penetrating warhead. Each weapon has five components -- a forward guidance section, warhead adapter section, control module, airfoil components, and a weapon data link. The guidance section is attached to the nose of the weapon and contains either a television guidance system for daytime or an imaging infrared system for night or limited, adverse weather operations. A data link in the tail section sends guidance updates to the control aircraft that enables the weapon systems operator to guide the bomb by remote control to its target. An external electrical conduit extends the length of the warhead which attaches the guidance adapter and control unit. The conduit carries electrical signals between the guidance and control sections. The umbilical receptacle passes guidance and control data between cockpit control systems of the launching aircraft and the weapon prior to launch. The rear control section consists of four wings that are in an "X"-like arrangement with trailing edge flap control surfaces for flight maneuvering. The control module contains the autopilot, which collects steering data from the guidance section and converts the information into signals that move the wing control surfaces to change the weapon's flight path. The GBU-15 may be used in either a direct or an indirect attack. In a direct attack, the pilot selects a target before launch, locks the weapon guidance system onto it and launches the weapon. The weapon automatically guides itself to the target, enabling the pilot to leave the area. In an indirect attack, the weapon is guided by remote control after launch. The pilot releases the weapon and, via remote control, searches for the target. Once the target is acquired, the weapon can be locked to the target or manually guided via the data-link system. This highly maneuverable weapon has an optimal, low-to-medium altitude delivery capability with pinpoint accuracy. It also has a standoff capability. In Desert Storm, F-111F pilots used GBU-15 glide bombs to seal flaming oil pipeline manifolds sabotaged by Saddam Hussein's troops. History: The Air Force Development Test Center, Eglin Air Force Base, FL, began developing the GBU-15 in 1974. It was a product improvement of the early guided bombs used during the Southeast Asia conflict. Flight testing of the weapon began in 1975. The GBU-15 with television guidance, completed full-scale operational test and evaluation in November 1983. In February 1985, initial operational test and evaluation was completed on the imaging infrared guidance seeker. In December 1987, the program management responsibility for the GBU-15 weapon system transferred from the Air Force Systems Command to the Air Force Logistics Command. The commands merged to become the Air Force Materiel Command in 1992. During the integrated weapons system management process, AGM-130 and GBU-15 were determined to be a family of weapons because of the commonality of the two systems. The Precision Strike Program Office at Eglin AFB became the single manager for the GBU-15, with the Air Logistics Center at Hill AFB, UT providing sustainment support. General Characteristics, GBU-15 Contractors: Boeing North American Length: Boeing North American Launch Weight: 2,500 pounds (1,125 kilograms) Diameter: 2,500 pounds (1,125 kilograms) Wingspan: 4 feet, 11 inches (1.49 meters) Range: 5-15 nautical miles Ceiling: 30,000-plus feet (9,091 meters) Speed: Classified Warhead: MK-84 general purpose or BLU-109 penetrating bombs Guidance System: Television or imaging infrared seeker via data link Inventory: Classified Date Deployed: 1983 Unit Cost: TV: $242,500; IIR: $245,000

GBU-28 "Bunkerbuster

David — Thu, 16 Jan 2003 23:24:36 -0800

by: David

Description: Function: Bomb with guidance control system. Description: The Guided Bomb Unit-28 (GBU-28) is a special weapon developed for penetrating hardened Iraqi command centers located deep underground. The GBU-28 is a 5,000-pound laser-guided conventional munition that uses a 4,400-pound penetrating warhead. The bombs are modified Army artillery tubes, weigh 4,637 pounds, and contain 630 pounds of high explosives. They are fitted with GBU-27 LGB kits, 14.5 inches in diameter and almost 19 feet long. The operator illuminates a target with a laser designator and then the munition guides to a spot of laser energy reflected from the target. The GBU-28 "Bunker Buster" was developed specifically to destroy Iraqi underground hardened command bunkers during the Gulf War. Scratch built from a section of surplus 8" howitzer barrel filled with 600 pounds of explosives, the 5,000 pound GBU-28 is capable of penetrating more than 20 feet of reinforced concrete and deeper than 100 feet underground. Equipped with essentially the same guidance hardware as the GBU-10 Paveway II, the GBU-28 is capable of hitting discrete, hardened targets deep underground. The GBU-28 was successfully used twice during the Gulf War, with each of the weapons being released by FB-111F Aardvarks for use against buried command bunkers. Background: Precision-guided munitions (PGM) can trace their origins back to World War Two. These early weapons, such as the QB-17G "Aphrodite" were essentially airframes packed with explosives and guided via radio direction signals to their target, where they would crash and explode. While guidance was extremely crude by today's standards, these weapons were more accurate than conventional dropped munitions, and did not expose aircrews to deadly enemy anti-aircraft fire. Unfortunately, such weapons were unwieldy, unsuitable for small targets, and were themselves subject to defensive fire. The first truly precision-guided munitions did not appear until the Vietnam War. Serving as a major supply conduit for North Vietnam, the mile long Paul Doumer Bridge over the Red River was the most important ground target of the war. Unfortunately, it was also one of the most heavily defended, its approaches ringed with anti-aircraft guns and surface to air missile emplacements. While American pilots were able to attack the bridge using conventional munitions, such missions were extremely hazardous and casualties were high. In 1967 the Rockwell International Corporation was tasked with producing a precision munition using electro-optical guidance technology. The end result was the GBU (Guided Bomb Unit) 8 or Homing Bomb System (HOBOS), a conventional Mk. 84 2,000 pound bomb with a TV like electro-optical guidance package in the nose to provide direction and a modified tail fin assembly in the rear to provide lift. To launch the GBU-8 the pilot aligned the TV camera sight in the bomb with the target and the weapons officer locked the bomb's seeker onto the target. Once aligned, the bomb could be released well away from the target area and it would guide itself into the target with a high degree of accuracy. History: The GBU 28 "Bunker Buster" was put together in record time to support targeting of the Iraqi hardened command bunker by adapting existing materiel. The GBU-28 was not even in the early stages of research when Kuwait was invaded. The USAF asked industry for ideas in the week after combat operations started. The bomb was fabricated starting on 1 February, using surplus 8-inch artillery tubes. The official go-ahead for the project was issued on 14 February, and explosives for the initial units were hand-loaded by laboratory personnel into a bomb body that was partially buried upright in the ground outside the laboratory in New York. The first two units were delivered to the USAF on 16 and 17 February, and the first flight to test the guidance software and fin configuration was conducted on 20 February. These tests were successful and the program proceeded, with a contract let on 22 February. A sled test on 26 February proved that the bomb could penetrate over 20 feet of concrete, while an earlier flight test had demonstrated the bomb's ability to penetrate more than 100 feet of earth. The first two operational bombs were delivered to the theater on 27 February. The Air Force produced a limited quantity of the GBU-28 during Operation Desert Storm to attack multi-layered, hardened underground targets. Only two of these weapons were dropped in Desert Storm, both by F-111Fs. One weapon hit its precise aimpoint, and the onboard aircraft video recorder displayed an outpouring of smoke from an entrance way approximately 6 seconds after impact. After Operation Desert Storm, the Air Force incorporated some modifications, and further tested the munition. The Fy1997 budget request contained $18.4 million to procure 161 GBU-28 hard target penetrator bombs.

CBU-87 Cluster Bomb

David — Thu, 16 Jan 2003 23:24:35 -0800

by: David

Description: Function: Combined effects sub-munition dispenser. Background: The CBU-87 Combined Effects Munition (CEM) cluster bomb was introduced in 1986 as a replacement for earlier, Vietnam War-era cluster bombs. The CBU-87 CEM comprises the SUU-64/B Tactical Munitions Dispenser (TMD), the FZU-39 proximity fuse, and 202 BLU-97/B Combined Effect Bomb (CEB) sub-munitions. The CBU-87 can be delivered at any altitude and at any airspeed. In addition, because the CBU-87 is proximity fused, it can be "toss" delivered, to increase the target standoff distance in high threat environments, and still detonate at the appropriate altitude. The bomblete dispersal pattern and impact area can be modified by adjusting the rate of spin on the munition dispenser and the altitude at which it opens. Set to a low rate of spin (e.g. less than 500 rpm) and opened at low altitude (e.g. less than 300 feet) a single CBU-87 will dispense bomblets over an area of 120 by 200 feet, with an average of 9 feet between bomblets. Depending on spin rate and altitude of dispersal, the coverage pattern can range from 70 x70 feet to 800 x 400 feet. The BLU-97/B sub-munition is a combined effects munition, providing both anti-armor and anti-personnel effects, as well as an incendiary capability. The munition itself is essentially a small anti-armor shaped charge housed inside a scored steel case, designed to break up into 300 pre-formed fragments upon detonation. Description: The SUU-64/B is made of fiberglass, and is olive drab in color. The dispenser is approximately 16 inches in diameter, 7.5 feet long, weighs approximately 950 pounds, and on deployment breaks apart into 6 separate pieces. The BLU-97/B bomblet is yellow in color, approximately 7 inches long, 2.5 inches in diameter, and weighs 3.41 pounds. Prior to deployment the tail end of the bomblet is ringed with a series of copper metal drogue tabs. Once released, the drogue tabs orient the bomblet and deploy the munition's inflatable decelerator (essentially an air inflated pillow which both slows the munition down but orients the warhead.) General Characteristics, CBU-87 Combined Effects Munition Manufacturer: Alliant Techsystems Length: 7.6 feet (2.35 meters) Diameter: 15.6 inches Date Deployed: 1986 Weight: 950 lbs. (432 kg.) Sub-Munition type: 202 x BLU-97/B CEB Unit Cost: $13,941

GBU-12 Paveway I/II

David — Thu, 16 Jan 2003 23:24:35 -0800

by: David

Description: Function: Bomb with guidance support system. Description: The Guided Bomb Unit-12 (GBU-12) utilizes a 500-pound general purpose warhead. The operator illuminates a target with a laser designator and then the munition guides to a spot of laser energy reflected from the target. The GBU-12 Paveway II is a smaller version of the GBU-10 Laser Guided Bomb (LGB). Utilizing the same principles as the GBU-10, the GBU-1 uses the Mk. 82 500 pound bomb with the same seeker head technology as the GBU-10. Targets may be designated by either the launching aircraft or another aircraft in the area, by an Unmanned Aerial Vehicle (UAV), or by personnel on the ground. In addition, since the GBU-12 orients itself on the reflected laser, rather than the target, it can be directed towards a different target after launch simply by pointing the designator at a different target. The munition was used during Operation Desert Storm, and, according to the Air Force, hit 88 percent of its targets. During Desert Storm the GBU-12 was dropped by F-lllFs, F-15Es, and A-6s, mostly against fixed armor. It was the F-111F tank-busting weapon of choice. Of the 4,493 GBU-12s employed, over half were dropped by the F-lllF. There are two generations of GBU-12 LGBs: Paveway I with fixed wings and Paveway II with folding wings. Paveway II models have the following improvements: detector optics and housing made of injec- tion-molded plastic to reduce weight and cost; increased detector sensitiv- ity; reduced thermal battery delay after release; increased maximum canard deflection; laser coding; folding wings for carriage, and increased detector field of view. (Paveway II's instantaneous field of view is thirty percent greater than that of the Paveway I's field of view). Background: Precision-guided munitions (PGM) can trace their origins back to World War Two. These early weapons, such as the QB-17G "Aphrodite" were essentially airframes packed with explosives and guided via radio direction signals to their target, where they would crash and explode. While guidance was extremely crude by today's standards, these weapons were more accurate than conventional dropped munitions, and did not expose aircrews to deadly enemy anti-aircraft fire. Unfortunately, such weapons were unwieldy, unsuitable for small targets, and were themselves subject to defensive fire. The first truly precision-guided munitions did not appear until the Vietnam War. Serving as a major supply conduit for North Vietnam, the mile long Paul Doumer Bridge over the Red River was the most important ground target of the war. Unfortunately, it was also one of the most heavily defended, its approaches ringed with anti-aircraft guns and surface to air missile emplacements. While American pilots were able to attack the bridge using conventional munitions, such missions were extremely hazardous and casualties were high. In 1967 the Rockwell International Corporation was tasked with producing a precision munition using electro-optical guidance technology. The end result was the GBU (Guided Bomb Unit) 8 or Homing Bomb System (HOBOS), a conventional Mk. 84 2,000 pound bomb with a TV like electro-optical guidance package in the nose to provide direction and a modified tail fin assembly in the rear to provide lift. To launch the GBU-8 the pilot aligned the TV camera sight in the bomb with the target and the weapons officer locked the bomb's seeker onto the target. Once aligned, the bomb could be released well away from the target area and it would guide itself into the target with a high degree of accuracy.

GBU-24 Paveway III

David — Thu, 16 Jan 2003 23:24:35 -0800

by: David

Description: Description: The GBU-24 Paveway III represents the next step beyond the GBU-10 series of Laser Guided Bomb. Reacting to increased air defense lethality, which force attack aircraft to penetrate the target area in a nap of the earth (NOE) profile, as well as provide a low level LGB option in the event of poor battlefield visibility or low ceiling, the GBU-24 was specifically designed for low altitude deliveries. Utilizing the same principles as the GBU-10, the GBU-24 uses either the Mk. 84 2,000 pound bomb or the BLU-109 penetration bomb with an improved seeker head optimized for low-level release. To increase standoff range and improve low level glide characteristics, the GBU-24 is equipped with significantly larger guidance fins. As with the Paveway I and II, targets may be designated by either the launching aircraft or another aircraft in the area, by an Unmanned Aerial Vehicle (UAV), or by personnel on the ground. In addition, since the GBU-24 orients itself on the reflected laser, rather than the target, it can be directed towards a different target after launch simply by pointing the designator at a different target. The Guided Bomb Unit-24 (GBU-24) Low Level Laser Guided Bomb [LLLGB] consists of either a 2,000-pound MK-84 general purpose or BLU-109 penetrator bomb modified with a Paveway III low-level laser-guided bomb kit to add the proportional guidance in place of the bang-bang type used in the Paveway II. The LLLGB was developed in response to Sophisticated enemy air defenses, poor visibility, and to counter limitations in low ceilings. The weapon is designed for low altitude delivery and with a capability for improved standoff ranges to reduce exposure. The GBU-24 LLLGB/Paveway III has low-level, standoff capability of more than 10 nautical miles. Performance envelopes for all modes of delivery are improved because the larger wings of the GBU-24 increases maneuverability. Paveway III also has increased seeker sensitivity and a larger field of regard. The operator illuminates a target with a laser designator and then the munition guides to a spot of laser energy reflected from the target. One way to deliver LGBs from low altitude is a loft attack. In this maneuver, the aircraft pulls up sharply at a predetermined point some miles from the target and the LGB is lofted upward and toward the target. However, if the LGB guidance system detects reflected laser energy from the target designator too soon after release, it tends to pull the LGW down below its required trajectory and the bomb will impact well short of the target. This bomb is not nearly as delivery parameter sensitive as is the Paveway II LGB, nor is it affected by early laser designation. After a proper low altitude delivery, the LLLGB will maintain level flight while looking for reflected laser energy. If it does not detect reflected laser energy, it will maintain level flight to continue beyond the designated target, overflying friendly positions, to impact long, rather than short of the target. Unlike the Paveway II LGB, the LLLGB can correct for relatively large deviations from planned release parameters in the primary delivery mode (low-altitude level delivery). It also has a larger delivery envelope for the dive, glide and loft modes than does the earlier LGB. The wide field of view and midcourse guidance modes programmed in the LLLGB allow for a "Point Shoot" delivery capability. This capability allows the pilot to attack the target by pointing the aircraft at the target and releasing the weapon after obtaining appropriate sight indications. The primary advantage of this capability is that accurate dive/tracking is not required to solve wind drift problems. The Multi-Segment Hard Target Penetrator (MSHTP) concept has been designed to use the penetration capability of a BLU-113 or BLU-109 linked to the void counting hard target smart fuse. This weapon detonates a copper cutter charge upon entering the target and cuts the rear portion of the bomb off, which then detonates. The rest of the weapon continues down to the next level. BLU-116 Advanced Unitary Penetrator [AUP] GBU-24 C/B (USAF) / GBU-24 D/B (Navy) Air Force Research Laboratory Munitions Directorate engineers have completed development of a new warhead known as the Advanced Unitary Penetrator, or AUP. The warhead was successfully transitioned to the Precision Strike System Program Office at Eglin AFB, Fla. for Engineering Manufacturing Development (EMD) and production. The AUP was developed in less than three years at a cost of less than $8M. AFRL's emphasis on operational suitability as part of AUP weapon design will allow the EMD program to be completed in less than half the time of a normal EMD program. The Advanced Unitary Penetrator [AUP] hard target penetrator features an elongated narrow diameter case made of a tough nickel-cobalt steel alloy called Air Force 1410. With the official designation of BLU-116, and designated the GBU-24 C/B (USAF) and GBU-24 D/B (Navy), is designed to provide at least twice the penetration capability of existing BLU-109 2000-pound bombs. The AUP is being demonstrated with Boeing as prime and Lockheed-Martin as subcontractor. Penetration capability is directly proportional to the warhead's sectional density--its weight divided by its cross section. The AUP maximizes sectional density by reducing the explosive payload and using heavy metals in the warhead case. Lower explosive payload will diminish dispersion of NBC agents to help reduce collateral effects. The AUP will retain the carriage and flight characteristics of the BLU-109, and it will be compatible with the GBU-24, GBU-27, and GBU-15/AGM-130 series of precision-guided bombs. Thus, the AUP will be capable of delivery from a wider inventory of aircraft, including stealth platforms, than the BLU-113/GBU-28. A proposal to replace the current CALCM warhead with an AUP warhead provides 2.5 times BLU-109 penetration capability. The AUP development effort was conducted in support of the Counterproliferation Initiative (CPI) Advanced Concept Technology Demonstration (ACTD). The program objective was to develop and demonstrate a weapon that could be rapidly transitioned for Air Force and Navy use against hardened targets associated with the production, storage, and weaponization of chemical or biological agents. Normally, the introduction of a new weapon is a very long, expensive, and tedious process - as long as ten years or more. The associated cost may be tens of millions of dollars. The 1700-pound AUP warhead is tucked inside a lightweight aerodynamic shroud. This "outer skin" gives the AUP the exact physical and aerodynamic characteristics of the BLU-109. The shroud strips away from the internal penetrator when the weapon impacts the target. Compared to the BLU-109, the AUP has thicker case walls, a tougher case material, an improved nose shape, and a smaller explosive charge. The cross-sectional area of the AUP penetrator, however, is only half as great as the cross-sectional area of the BLU-109. A smaller explosive charge reduces collateral damage potential by reducing blast overpressure that could expel chemical or biological agents from the target. A long testing series demonstrated AUP's compatibility with the Munitions Directorate-developed Hard Target Smart Fuze (HTSF). The HTSF allows the AUP to be detonated at the optimal point within a target to inflict maximum damage. That ability compensates for the reduction in explosive charge. Because it is a "twin" to the BLU-109, the AUP can utilize a proven system of hardbacks, guidance units, and tail fin kits. The costs associated with developing new kits is eliminated. The operational users - pilots, weapon handlers and load crews - will gain the improved war fighting capabilities of the AUP without the costs associated with retraining support personnel or the acquisition of new delivery systems and support equipment. Battle commanders will also have increased ability to neutralize deeply buried hardened targets. GBU-24E/B GBU-24E/B, an Enhanced Paveway Laser Guided Bomb, is a precision-guided hardened target penetrator used to destroy hardened aircraft hangers and underground bunkers. It integrates a Global Positioning System and a ring laser gyro inertial measuring unit (IMU) to the already fielded GBU-24B/B "Paveway III" with the existing laser guidance. A new guidance and control unit has been modified to incorporate GPS electronics, GPS antenna, IMU and software for precision GPS/INS guidance. Testing of this system began in late 1999. Background: Precision-guided munitions (PGM) can trace their origins back to World War Two. These early weapons, such as the QB-17G "Aphrodite" were essentially airframes packed with explosives and guided via radio direction signals to their target, where they would crash and explode. While guidance was extremely crude by today's standards, these weapons were more accurate than conventional dropped munitions, and did not expose aircrews to deadly enemy anti-aircraft fire. Unfortunately, such weapons were unwieldy, unsuitable for small targets, and were themselves subject to defensive fire. The first truly precision-guided munitions did not appear until the Vietnam War. Serving as a major supply conduit for North Vietnam, the mile long Paul Doumer Bridge over the Red River was the most important ground target of the war. Unfortunately, it was also one of the most heavily defended, its approaches ringed with anti-aircraft guns and surface to air missile emplacements. While American pilots were able to attack the bridge using conventional munitions, such missions were extremely hazardous and casualties were high. In 1967 the Rockwell International Corporation was tasked with producing a precision munition using electro-optical guidance technology. The end result was the GBU (Guided Bomb Unit) 8 or Homing Bomb System (HOBOS), a conventional Mk. 84 2,000 pound bomb with a TV like electro-optical guidance package in the nose to provide direction and a modified tail fin assembly in the rear to provide lift. To launch the GBU-8 the pilot aligned the TV camera sight in the bomb with the target and the weapons officer locked the bomb's seeker onto the target. Once aligned, the bomb could be released well away from the target area and it would guide itself into the target with a high degree of accuracy.

Joint Direct Attack Munit

David — Thu, 16 Jan 2003 23:24:35 -0800

by: David

Description: Description: The Joint Direct Attack Munition (JDAM) GBU-31 is a tailkit under development to meet both USAF and Navy needs, with the Air Force as the lead service. The program will produce a weapon with high accuracy, all-weather, autonomous, conventional bombing capability. JDAM will upgrade the existing inventory of general purpose and penetrator unitary bombs, and a product improvement may add a terminal seeker to improve accuracy. JDAM can be launched from approximately 15 miles from the target and each is independently targeted. JDAM is not intended to replace any existing weapon system; rather, it is to provide accurate delivery of general purpose bombs in adverse weather conditions. The JDAM will upgrade the existing inventory of Mk-83 1,000- and Mk-84 2,000-pound general purpose unitary bombs and the 2,000-pound hard target penetrator bomb by integrating a guidance kit consisting of an inertial navigation system/global positioning system guidance kit. The 1,000-pound variant of JDAM is designated the GBU-31, and the 2,000-pound version of the JDAM is designated the GBU-32. JDAM variants for the Mk-80 250-pound and Mk-81 500-pound bombs are designated GBU-29 and GBU-30, respectively. Hard Target penetrators being changed into low-cost JDAMs included the 2,000 pound BLU-109 and 1,000 pound BLU-110. The JDAM will be continuously updated by aircraft avionics systems prior to release. Once released, the bomb's INS/GPS will take over and guide the bomb to its target regardless of weather. Guidance is accomplished via the tight coupling of an accurate GPS with a 3-axis INS. The Guidance Control Unit provides accurate guidance in both GPS-aided INS modes of operation and INS-only modes of operation. This inherent JDAM capability will counter the threat from near-term technological advances in GPS jamming. The weapon system allows launch from very low to very high altitude and can be launched in a dive, toss, loft or in straight and level flight with an on-axis or off-axis delivery. JDAM also allows multiple target engagements on a single pass delivery. JDAM provides the user with a variety of targeting schemes, such as preplanned and inflight captive carriage retargeting. Potential Upgrades The JDAM product improvement program may add a terminal seeker for precision guidance and other system improvements to existing JDAMs to provide the Air Force with 3-meter precision and improved anti-jamming capability. The Air Force is evaluating several alternatives and estimates that the seeker could be available for operations by 2004. The seeker kit could be used by both the 2,000-pound blast fragmentation and penetrator JDAMs. The Advanced Unitary Penetrator (AUP), a candidate to be integrated with a GBU-31 guidance kit, is a 2000 lb. class penetrator warhead intended as an upgrade/replacement for the BLU-109 warhead in applications requiring increased penetration. The AUP is designed to provide increased penetration capability over the BLU-109 warhead while maintaining the same overall weight, mass properties, dimensions, and physical interfaces associated with the BLU-109 warhead. This concept integrates the AUP warhead with the GBU-31, the JDAM tail kit for 2,000 lb class warheads. This concept uses the Hard Target Smart Fuze (HTSF), an accelerometer based electronic fuze which allows control of the detonation point by layer counting, distance or time. The accelerometer senses G loads on the bomb due to deceleration as it penetrates through to the target. The fuze can distinguish between earth, concrete, rock and air. The boosted penetrator concept is based on achieving maximum penetration without sacrificing operational flexibility. Total system weight will be less than 2,250 pounds so that it can be carried by all AF tactical aircraft and bombers as well as the Navy?s F/A-18. The goal is to achieve greater penetration than the GBU-28 with a near term, affordable design. A dense metal warhead will be used with a wraparound rocket motor to allow internal carriage in the F-117. Advanced explosives will be used to compensate for the reduced charge weight. This concept integrates the boosted penetrator warhead with a JDAM guidance kit with an adverse weather Synthetic Aperture Radar (SAR). The Ballasted Penetrator in GBU-32 concept is a 1000 pound dense or ballasted penetrator integrated with a GBU-32 guidance kit using compressed carriage for internal carriage in advanced fighters (F-22, JSF) or carriage in cruise missiles (JASSM, CALCM, ACM, ATACMS, Tomahawk.) The warhead would either be designed with a dense metal case or contain dense metal ballast for maximum penetration. The warhead will be filled with an advanced insensitive explosive to compensate for the reduced charge weight. The warhead will be integrated with the GBU-32, the JDAM tail kit for 1,000 lb class warheads. The Boosted Unitary Penetrator concept is based on achieving maximum penetration in a weapon that will fit internally in the F-22. Total system weight will be less than 1300 pounds. A dense metal warhead will be used with a wraparound rocket motor. Use of next generation compressed seekers and aero-control designs along with reaction jet control will allow the size to shrink sufficiently to fit inside F-22 and JSF. Advanced explosives will be used to compensate for the reduced charge weight. This concept integrates the boosted penetrator warhead with a JDAM guidance kit with an adverse weather Synthetic Aperture Radar (SAR). The JDAM/BLU-113 concept improves the GBU-28 by enhancing the nose design of the BLU-113 warhead for improved penetration. The warhead nose reshape will improve BLU-113 penetration by more than 25%. The penetration could potentially be further improved by replacing the traditional HE fill with a dense explosive. The design involves integrating the improved BLU-113 warhead with a JDAM tail kit. The Compressed Carriage GBU-32, J1K, enhanced fill concept is a JAST-1000 warhead with enhanced fill integrated with a GBU-32 guidance kit using compressed carriage for internal carriage in advanced fighters (F-22, JSF) or carriage in cruise missiles (JASSM, CALCM, ACM, ATACMS, Tomahawk.) The warhead is a combined penetrator and blast/fray warhead. The warhead shape is optimized for penetration and the enhanced fill and internal liner provide blast and controlled fragmentation capability. The warhead is shrouded to match the MK-83 mass properties and interfaces. The warhead will be integrated with the GBU-32, the JDAM tail kit for 1,000 lb class warheads. Use of aero-control designs along with reaction jet control will allow the size to shrink sufficiently to fit inside F-22 and JSF. This concept uses the Hard Target Smart Fuze (HTSF). The Direct Attack Munitions Affordable Seeker (DAMASK) Fleet Advanced Demonstration (FAD) accuracy enhancement kit is a seeker of the lowest possible cost that will improve JDAM accuracy to three-meter circular error probability (CEP). The three-year FAD began in FY 98 and continued through FY 00. DAMASK includes a very low-cost sensor mounted to the front of a JDAM and an off-the-shelf signal processor mounted in the existing JDAM tail kit. It uses an uncooled imaging-infrared focal plane array (UIIFPA) sensor and low-cost optics, both developed for the consumer automobile market. An off-the-shelf, commercially available signal processor is the final component of the accuracy upgrade kit, estimated to cost less than $12.7 thousand per seeker in quantity. During the final stages of weapon flight, DAMASK's unique guidance system will image the target area, locate a mission-planned aimpoint and update the JDAM target location. The mission-planning image can come from satellite, uninhabited air vehicles or reconnaissance aircraft. A template is then automatically produced from the mission-planning image and loaded on board the aircraft with the baseline JDAM mission plan. Organic targeting is possible because the target area can be imaged with onboard synthetic aperture radar (SAR) or forward looking infrared (FLIR) sensors, and the pilot can then select the desired impact point using a heads-down display. History: JDAM is being developed by Lockheed Martin and Boeing [McDonald Douglas]. In October 1995, the Air Force awarded a contract for EMD and for the first 4,635 JDAM kits at an average unit cost of $18,000, less than half the original $40,000 estimate. As a result of JDAM's pilot program status, low-rate initial production was accelerated nine months, to the latter half of FY 1997. On April 30, 1997, the Air Force announced the decision to initiate low-rate initial production (LRIP) of JDAM, with the first production lot of 937 JDAM kits. The JDAM Integrated Product Team achieved a phenomenal 53 guided JDAM weapon releases in the six months prior to the LRIP decision. JDAM demonstrated high reliability and outstanding accuracy. Twenty-two of the weapon releases were accomplished during an early Air Force operational assessment. Over a four-week period operational crews put JDAM through an operationally representative evaluation, including targets shrouded by clouds and obscured by snow. All 22 weapons successfully performed up to their operational requirements including overall accuracy of 10.3 meters, significantly better than the 13 meter requirement. Early operational capability JDAMs have been delivered to Whiteman Air Force Base, MO, and low-rate, initial production JDAM deliveries begin on 02 May 1998. McDonnell Douglas Corporation of Berkeley, MO, was awarded on 02 April 1999, a $50,521,788 face value increase to a firm-fixed-price contract to provide for low rate initial production of 2,527 Joint Direct Attack Munition (JDAM) kits. The work is expected to be completed by January 2001. The JDAM program is nearing the end of its development phase. More than 250 flight tests involved five Air Force and Navy aircraft. JDAM will be carried on virtually all Air Force fighters and bombers, including the B-1, B-2, B-52, F-15E, F-16, F-22, F-117, and F/A-18. JDAM was certified as operational capable on the B-2 in July 1997. Limited Initial Operational Capability was achieved on the B-52 in December 1998.

Penguin

David — Thu, 16 Jan 2003 23:24:35 -0800

by: David

Description: Function: The Penguin is a helicopter launched anti-ship missile developed for use on Lamps III helicopters and NATO allies. Description: The Penguin missile has an indirect flight path to target. It is also operated in "fire-and-forget" mode to allow multiple target aqusition. The Penguin is fired from a launcher or a stage weighing approximately 1,100 pounds (500 kilograms). History: The Penguin was developed by and for the Norwegian Navy. The original Penguin became operational on Norwegian fast attack boats in 1972. General Characteristics, Penguin Anti-Ship Missile Contractors: Kongsberg Vaapenfabrikk (Norway) Power Plant: Solid propellant rocket motor and solid propellant booster Length: 120.48 inches (3.06 meters) Launch Weight: 847 pounds (385 kilograms) Diameter: 11.2 inches (28.45 centimeters) Wingspan: 39 inches (71.12 centimeters) Range: 21.7 miles (25 nautical miles/35 kilometers) Speed: 1.2 Mach maximum Warhead: 265 pounds (120.5 kilograms), semi armor piercing Guidance System: Inertial and infrared terminal Date Deployed: Fourth quarter 1993

Tomahawk

David — Thu, 16 Jan 2003 23:24:35 -0800

by: David

Description: Function: Long range, subsonic cruise missile used for land attack warfare, launched from surface ships and submarines. Description: Tomahawk Block II uses a Terrain Contour Matching (TERCOM) and Digital Scene Matching Area Correlation (DSMAC) missile guidance system. Block III adds a Global Positioning Satellite guidance capability to TERCOM and DSMAC. Radar detection of the missile is extremely difficult because of the small radar cross-section and low altitude. Tomahawk has two warhead configurations: a 1,000-pound blast/fragmentary unitary warhead and a general-purpose submunition dispenser with combined effect bomblets. The capabilities of the future Tomahawk, Block IV or Tactical Tomahawk, will include battle damage assessment, in flight retargeting, and mission planning from the launch platform. It is projected to enter service in 2003. History: Tomahawk cruise missiles are designed to fly at extremely low altitudes at high subsonic speeds, and are piloted over an evasive route by several mission tailored guidance systems. The first operational use was in Operation Desert Storm, 1991. The missile has since been successfully used in several other conflicts. In 1995 the governments of the United States and United Kingdom signed a Foreign Military Sales Agreement for the acquisition of 65 missiles, marking the first sale of Tomahawk to a foreign country. After a November 1998 launch and live warhead test, the U.K. declared operational capability. General Characteristics, Tomahawk Cruise Missile Manufacturer: Raytheon Systems Company, Tucson, AZ Power Plant: Williams International F107-WR-402 cruise turbo-fan engine; CSD/ARC solid-fuel booster Length: 18 feet 3 inches (5.56 meters) With booster: 20 feet 6 inches (6.25 meters) Weight: 2,900 pounds (1,315.44 kilograms) With booster: 3,500 pounds (1,587.6 kilograms) Diameter: 20.4 inches (51.81 centimeters) Wingspan: 8 feet 9 inches (2.67 meters) Range: 870 nautical miles (1000 statute miles, 1609 kilometers) Speed: Subsonic - about 550 mph (880 kmh) Guidance System: TERCOM, DSMAC, and GPS (Block III only) Warheads: 1,000 pounds or conventional submunitions dispenser with combined effect bomblets Dates Deployed: 1986 - IOC 1994 - Block III 2003 - Tactical Tomahawk Unit Cost: Approximately $600,000 (from the last production contract)

AGM-65 Maverick

David — Thu, 16 Jan 2003 23:24:35 -0800

by: David

Description: Function: The AGM-65 Maverick is a tactical, air-to-surface guided missile designed for close air support, interdiction and defense suppression mission. It provides stand-off capability and high probability of strike against a wide range of tactical targets, including armor, air defenses, ships, transportation equipment and fuel storage facilities. Description: The Maverick is a modular design weapon. A different combination of the guidance package and warhead can be attached to the rocket motor section to produce a different weapon. The Maverick has three different seekers and two different warheads. The solid-rocket motor propulsion section is common to all variants. The seeker options are electro-optical (EO) imaging, imaging infrared (IR) or a laser guidance package. The warhead is in the missile's center section. Either a 125-pound shaped-charge warhead or a 300-pound penetrator warhead can be used. A contact fuse in the nose fires the shaped-charge warhead. The penetrator uses a delayed-fuse, allowing the warhead to penetrate the target with its kinetic energy before firing. The latter is very effective against large, hard targets. The AGM-65 has a cylindrical body with long-chord delta wings and tail control surfaces mounted close to the trailing edge of the wing of the aircraft using it. A-10, F-15E and F-16 aircraft carry Mavericks. As many as six Mavericks can be carried by an aircraft, usually in three round, underwing clusters, allowing the pilot to engage several targets on one mission. The missile also has "launch-and-leave" capability that enables a pilot to fire it and immediately take evasive action or attack another target as the missile guides itself to the target. Mavericks can be launched from high altitudes to tree-top level and can hit targets ranging from a distance of a few thousand feet to 13 nautical miles at medium altitude. Maverick B models have an electro-optical television guidance system. After the protective dome cover is automatically removed from the nose of the missile and its video circuitry activated, the scene viewed by the guidance system appears on a cockpit television screen. The pilot selects the target, centers cross hairs on it, locks on, then launches the missile. The Maverick B also has a screen magnification capability that enables the pilot to identify and lock on smaller and more distant targets. The Maverick D has an imaging infrared guidance system, operated much like that of the A and B models, except that infrared video overcomes the daylight-only, adverse weather limitations of the other system. The infrared Maverick D can track heat generated by a target and provide the pilot a pictorial display of the target during darkness and hazy or inclement weather. The Maverick E model is the only version having the laser-guided seeker section. It uses the heavyweight penetrator warhead. The U.S. Marine Corps are the only users of this variant. The Maverick F is a naval variant of the D/G model (IR) currently in use by the U.S. Navy. It also uses the 300-pound penetrator warhead. The Maverick G model essentially has the same guidance system as the D, with some software modifications that track larger targets. The G model's major difference is its heavyweight penetrator warhead, while Maverick B and D models employ the shaped-charge warhead. Maverick K models are currently in development. They were developed by taking a G model and replacing the IR guidance system with an electro-optical (EO) television guidance system. History: The Air Force accepted the first AGM-65A Maverick in August 1972. A total of 25,750 A and B Mavericks were purchased by the Air Force. Maverick As have recently been phased out of the inventory. The Air Force is exploring the possibility of converting phased out A's and near obsolete B's and making an EO version to be named AGM-65H. The software in the H would be upgraded increasing its capability. The Air Force took delivery of the first AGM-65D in October 1983, with initial operational capability in February 1986. Delivery of operational AGM-65G missiles took place in 1989. More than 5,000 AGM-65 A/B/D/E/F/G's were employed during Operation Desert Storm, mainly attacking armored targets. Mavericks played a large part in the destruction of Iraq's significant military force. General Characteristics, AGM-65 Maverick Contractors: Raytheon Systems Corporation Power Plant: Thiokol TX-481 solid-propellant rocket motor Launch Weight: AGM-65B, 462 pounds (207.90 kilograms) AGM-65D, 485 pounds (218.25 kilograms) AGM-65E, 777 pounds (353.2 kilograms) AGM-65F, 804 pounds (365.5 kilograms) AGM-65G, 670 pounds (301.50 kilograms) AGM-65K, 793 pounds (360.45 kilograms) Diameter: 1 foot (30.48 centimeters) Wingspan: 2 feet, 4 inches (71.12 centimeters) Range: Classified Speed: Classified Aircraft: Used aboard A-10, F-15E and F-16 Warhead: AGM-65B/D: 125 pounds (56.25 kilograms), cone shaped AGM-65E/F/G/K: 300 pounds (135 kilograms) delayed-fuse penetrator, heavyweight Guidance System: AGM-65B/K: electro-optical television AGM-65D/F/G: imaging infrared AGM-65E: laser guided Inventory: Classified Date Deployed: August 1972 Unit Cost: $17,000 to $110,000 depending on the Maverick variant

AGM-88 HARM

David — Thu, 16 Jan 2003 23:24:35 -0800

by: David

Description: Function: The AGM-88 HARM (high-speed antiradiation missile) is an air-to-surface tactical missile designed to seek and destroy enemy radar-equipped air defense systems. Description: The AGM-88 can detect, attack and destroy a target with minimum aircrew input. The proportional guidance system that homes in on enemy radar emissions has a fixed antenna and seeker head in the missile nose. A smokeless, solid-propellant, dual-thrust rocket motor propels the missile. The F-16C has the capability to employ the AGM-88, and is the only aircraft in the current inventory to use the AGM-88. History: The Defense Systems Acquisition Review Council approved the AGM-88 missile for full production in March 1983. The Air Force equipped the F-4G Wild Weasel with the AGM-88 to increase the F-4G's lethality in electronic combat. The missile worked with the APR-47 radar attack and warning system on the aircraft. The missile is operationally deployed throughout the Air Force and in full production as a joint U.S. Air Force-U.S. Navy project. General Characteristics, AGM-88 HARM Contractors: Texas Instruments Power Plant: Thiokol dual-thrust rocket motor Thrust: Dual thrust Length: 13 feet, 8 inches (4.14 meters) Launch Weight: 800 pounds (360 kilograms) Diameter: 10 inches (25.40 centimeters) Wingspan: 3 feet, 8 inches (101.60 centimeters) Range: 30 plus miles (48 plus kilometers) Speed: Supersonic Aircraft: Used aboard the F-16C Warheads: High explosive Guidance System: Proportional Date Deployed: 1984 Unit Cost: $200,000

AGM-154A Joint Standoff W

David — Thu, 16 Jan 2003 23:24:35 -0800

by: David

Description: Description: The AGM-154A Joint Standoff Weapon or JSOW is currently under development by Raytheon [Texas Instruments] for the Air Force and the Navy. The AGM-154A (Formerly Advanced Interdiction Weapon System) is intended to provide a low cost, highly lethal glide weapon with a standoff capability. JSOW family of kinematically efficient, air-to-surface glide weapons, in the 1,000-lb class, provides standoff capabilities from 15 nautical miles (low altitude launch) to 40 nautical miles (high altitude launch). The JSOW will be used against a variety of land and sea targets and will operate from ranges outside enemy point defenses. The JSOW is a launch and leave weapon that employs a tightly coupled Global Positioning System (GPS)/Inertial Navigation System (INS), and is capable of day/night and adverse weather operations. The JSOW uses inertial and global positioning system for midcourse navigation and imaging infra-red and datalink for terminal homing. The JSOW is just over 13 feet in length and weighs between 1000-1500 pounds. Extra flexibility has been engineered into the AGM-154A by its modular design, which allows several different submunitions, unitary warheads, or non-lethal payloads to be carried. The JSOW will be delivered in three variants, each of which uses a common air vehicle, or truck, while substituting various payloads. Weapon planning will be accomplished using the Navy's Tactical Automated Mission Planning System (TAMPS) and the Air Force Mission Support System (AFMSS). Aircraft-to-weapon communications will be via the MIL-STD-1760 interface, making inflight programming/targeting possible, as well as preflight data loading. The weapon will be deployed from both carrier- and land-based aircraft, employing insensitive munitions technology. The JSOW will be employed on the following aircraft: F/A-18A/B, C/D, and E/F; AV-8B; F-14A/B and /D; F-16C/D; F-15E; F-117; B-1B; and B-52. History: Texas Instruments (TI) Defense Systems & Electronics (DS&E) began Engineering and Manufacturing Development (E&MD) of JSOW in 1992. In December 1995, the Navy and Texas Instruments completed Development Test IIB (DT-IIB) at the Naval Air Weapon Center, (NAWC) China Lake and Point Mugu, California, with 10 for 11 successful flights of the AGM-154A BLU-97 dispenser variant. On January 6, 1997, it was announced that Texas Instruments Defense Systems & Electronics was being purchased by Raytheon Company, Lexington, Massachusetts. The U.S. Navy began Operational Evaluation (OPEVAL) testing in February 1997, after successful development testing and initial operational testing programs. The test program resulted in a 42 for 44 success rate or greater than 96% successful JSOW launches. The Air Force began Development Test & Evaluation (DT&E) flight testing of JSOW on the F-16 at Eglin Air Force Base, Florida, in March 1996. Air Force testing of the baseline JSOW was hindered by less than desired progress in the area of F-16/JSOW integration. The AGM-154A (Baseline variant) system entered Low Rate Initial Production (LRIP) on schedule. The $65.9 million LRIP contract was awarded by the Naval Air Systems Command (NAVAIR), in Arlington, Virginia, for 111 JSOW AGM-154A/baseline systems. LRIP for the other two variants are scheduled for FY99 and FY00, respectively. On 29 December 1998 Raytheon Systems was awarded a $133,881,355 firm-fixed-price contract to provide funding for the Full Rate Production Lot 1 of JSOW AGM-154A and the Low Rate Initial Production Lot I of the JSOW AGM-154B (AGM-154A: Navy - 328 and Air Force - 75) (AGM-154B: Navy - 3 and Air Force - 21). Work is expected to be completed by March 2001. JSOW test articles were deployed in 1997 aboard the USS Nimitz and are currently deployed on the USS Eisenhower. JSOW's initial introduction to the operational commands was on the Navy/Marine Corps F/A-18 in mid-1998. As of late 1997 a number of remaining JSOW test assets were on an interim deployment for further operational evaluation. USS Carl Vinson 's air wing first employed the JSOW during combat over southern Iraq on January 25, 1999. On December 29, 1999 Raytheon Systems Company, Tucson, AZ, was awarded a $109,573,867 modification to previously awarded contract N00019-99-C-1014 to exercise an option for the full rate production Lot 2 of the Joint Standoff Weapon AGM-154A for the U.S. Navy (414) and U.S. Air Force (74). Work will be performed in Tucson, AZ, and was expected to be completed by March 2002.

AIM-9 Sidewinder

David — Thu, 16 Jan 2003 23:24:35 -0800

by: David

Description: Function: The AIM-9 Sidewinder is a supersonic, heat-seeking, air-to-air missile carried by fighter aircraft. It has a high-explosive warhead and an active infrared guidance system. The Sidewinder was developed by the U.S. Navy for fleet air defense and was adapted by the U.S. Air Force for fighter aircraft use. Early versions of the missile were extensively used in the Southeast Asia conflict. Description: The AIM-9 has a cylindrical body with a roll-stabilizing rear wing/rolleron assembly. Also, it has detachable, double-delta control surfaces behind the nose that improve the missile's maneuverability. Both rollerons and control surfaces are in a cross-like arrangement. The missile's main components are an infrared homing guidance section, an active optical target detector, a high-explosive warhead and a rocket motor. The infrared guidance head enables the missile to home in on target aircraft engine exhaust. An infrared unit costs less than other types of guidance systems, and can be used in day/night and electronic countermeasures conditions. The infrared seeker also permits the pilot to launch the missile, then leave the area or take evasive action while the missile guides itself to the target. History: The AIM-9A, a prototype of the Sidewinder, was first fired successfully in September 1953. The initial production version, designated AIM-9B, entered the Air Force inventory in 1956 and was effective only at close range. It could not engage targets close to the ground, nor did it have nighttime or head-on attack capability. These shortcomings were eliminated on subsequent versions. The AIM-9J, a conversion of the AIM-B and E models, has maneuvering capability for dogfighting, and greater speed and range, giving it greater enhanced aerial combat capability. Deliveries began in 1977 to equip the F-15 and other Sidewinder-compatible aircraft. The AIM-9L added a more powerful solid-propellant rocket motor as well as tracking maneuvering ability. An improved active optical fuse increased the missile's lethality and resistance to electronic countermeasures. A conical scan seeker increased seeker sensitivity and improved tracking stability. The L model was the first Sidewinder with the ability to attack from all angles, including head-on. Production and delivery of the AIM-9L began in 1976. The AIM-9P, an improved version of the J model, has greater engagement boundaries, enabling it to be launched farther from the target. The more maneuverable P model also incorporated improved solid-state electronics that increased reliability and maintainability. Deliveries began in 1978. The AIM-9P-1 has an active optical target detector instead of the infrared influence fuse; the AIM-9P-2 added a reduced-smoke motor. The most recently developed version, the AIM-9P-3, combined both the active optical target detector and the reduced-smoke motor. It also has added mechanical strengthening to the warhead as well as the guidance and control section. The improved warhead uses new explosive material that is less sensitive to high temperature and has a longer shelf life. The AIM-9M, currently the only operational variant, has the all-aspect capability of the L model, but provides all-around higher performance. The M model has improved defense against infrared countermeasures, enhanced background discrimination capability, and a reduced-smoke rocket motor. These modifications increase ability to locate and lock-on a target and decrease the missile's chances for detection. Deliveries of the M model began in 1983. The AIM-9M-9 has expanded infrared countermeasures detection circuitry. AIM-9X is a future variant currently under development. General Characteristics, AIM-9 Sidewinder Contractors: Raytheon and Loral Martin Power Plant: Hercules and Bermite Mk 36 Mod 11 Thrust: Classified Length: 9 feet, 5 inches (2.87 meters) Launch Weight: 190 pounds (85.5 kilograms) Diameter: 5 inches (0.13 meters) Finspan: 2 feet, 3/4 inches (0.63 meters) Warhead: Annular blast fragmentation Guidance System: Solid-state, infrared homing system Inventory: Classified Introduction Date: 1956 Unit Cost: Approximately $84,000

AIM-120 AMRAAM

David — Thu, 16 Jan 2003 23:24:35 -0800

by: David

Description: Function: The AIM-120 advanced medium-range air-to-air missile (AMRAAM) is a new generation air-to-air missile. It has an all-weather, beyond-visual-range capability and is scheduled to be operational beyond 2000. The AMRAAM is being procured for the Air Force, U.S. Navy and America's allies. Description: The AMRAAM program improves the aerial combat capabilities of U.S. and allied aircraft to meet current and future threat of enemy air-to-air weapons. AMRAAM is compatible with the Air Force F-15, F-16 and developmental F-22; Navy F-14 D/D (R) and F/A-18 C/D; German F-4 and the British Sea Harrier aircraft. AMRAAM is a follow-on to the AIM-7 Sparrow missile series. The missile is faster, smaller and lighter, and has improved capabilities against low-altitude targets. It incorporates active radar with an inertial reference unit and micro-computer system, which makes the missile less dependent upon the fire-control system of the aircraft. Once the missile closes on a target, its active radar guides it to intercept. This enables the pilot to aim and fire several missiles simultaneously at multiple targets. The pilot may then perform evasive maneuvers while the missiles guide themselves to their targets. AMRAAM has three variants - AIM-120A/B/C -- operational on U.S. Air Force F-15 and F-16 aircraft. History: The AMRAAM program completed its conceptual phase in February 1979 when the U.S. Air Force selected two of five competing contractors, Hughes Aircraft Co. and Raytheon Co., to continue into the validation phase. During the 33-month validation phase the contractors continued missile development by building actual hardware to demonstrate their technological concepts. The program phase concluded in December 1981 after both contractors demonstrated that their flight-test missiles could satisfy Air Force and Navy requirements. The Air Force competitively selected Hughes Aircraft Co.'s Missile System Group, Canoga Park, CA, as the full-scale developer. During the full-scale development phase, Hughes Aircraft Co. completed missile development and Raytheon was selected as a follower producer. A production contract to both vendors was awarded in 1987. More than 200 of the test missiles were launched during flight tests at Eglin AFB, FL; White Sands Missile Range, NM; and Point Mugu, CA. AMRAAM is combat tested, scoring two kills during Operation Southern Watch, and one kill in Bosnia. General Characteristics, AIM-120 AMRAAM Contractors: Hughes Aircraft Corporation and Raytheon Corporation Power Plant: High performance Length: 143.9 inches (366 centimeters) Launch Weight: 335 pounds (150.75 kilograms) Diameter: 7 inches (17.78 centimeters) Wingspan: 20.7 inches (52.58 centimeters) Range: 20+ miles (17.38+ nautical miles) Speed: Supersonic Warheads: Blast fragmentation Guidance System: Active radar terminal/inertial midcourse Date Deployed: September 1991 Unit Cost: $386,000

CBU-78/89 Gator Air-Deliv

David — Thu, 16 Jan 2003 23:24:35 -0800

by: David

Description: Function: Air delivered mine system. Background: The CBU-89 Gator mine system is a 1,000-pound class air-deliverable area denial weapon. The CBU-89 Gator comprises the SUU-64/B Tactical Munitions Dispenser, the FZU-39 proximity fuse, and a combination of two sub-munitions. Each CBU-89 contains 72 BLU-91/B anti-tank mines and 22 BLU-92/B anti-personnel mines. The CBU-78/B used by the U.S. Navy is a 500-pound class variant of the 89, uses the Rockeye Mk. 7 dispenser, and contains 45 BLU-91/B and 15 BLU-92/B mines. The Gator mines arm immediately on impact with the ground. The BLU-91/B antitank mine has an integral magnetic influence sensor capable of detecting and distinguishing between armored and unarmored vehicles, and will detonate when the target is most vulnerable. The BLU-92/B antipersonnel mine is equipped with self-deployed trip wire detonators. The Gator mines can also have several time fuse options. The variable time option causes the mines to explode randomly over a period of days, for area denial and harassment operations. The set time option will detonate all of the mines at a specific time, thus facilitating friendly combat operations planning. Both mines are also equipped with anti-handling devices to make removal more difficult. The size and density of the minefield are determined by the altitude at which the mines are dispersed and the rate of spin on the canister prior to opening. Description: The SUU-64/B TMD is made of fiberglass, and is olive drab in color. The dispenser is approximately 16 inches in diameter, 7.5 feet long, weighs approximately 710 pounds when loaded, and on deployment breaks apart into 6 separate pieces. The Rockeye Mk. 7 dispenser is white in color, approximately 13 inches in diameter and 7 feet long, and weighs 490 pounds when loaded. When deployed the clamshell dispenser breaks apart into two separate pieces. The BLU-91/B and BLU-92/B mines are very similar in appearance. Both are approximately 5.75 x 5.5 x 2.6 inches on a side. The 91/B weighs 4.3 lbs. And the 92/B weighs 3.7 pounds. Each mine is round in shape and encased in a number of stabilization fins that activate on impact and ensure the mine is deployed properly in an upright position. The four trip wires on the BLU-92/B deploy out of the top of the mine. ?General Characteristics, CBU-78/89 Gator Air-Delivered Mines Manufacturer: Aerojet Ordnance Company Length: CBU-78: 7.08 feet (2.17 meters) CBU-89: 7.67 feet (2.36 meters) Diameter: CBU-78: 13 inches CBU-89: 16 inches Weight: CBU-78: 490 lb (222 kg) CBU-89: 710 lb (322 kg) Sub-munition Type: CBU-78: 45 x BLU-91/B AT mines 15 x BLU-92/B AP mines CBU-89: 72 x BLU-91/B AT mines 22 x BLU-92/B AP mines Unit Cost: CBU-78: CBU-89: $39,963

GBU-10 Paveway I/II

David — Thu, 16 Jan 2003 23:24:35 -0800

by: David

Description: Function: Bomb with guidance support system. Description: The Guided Bomb Unit-10 (GBU-10) utilizes the 2,000-pound general purpose or penetrating warhead. The operator illuminates a target with a laser designator and then the munition guides to a spot of laser energy reflected from the target. The GBU-10 consists of an MK-84 2,000 pound bomb with an added laser guidance package. The GBU-1OI mates a BLU-109B weapon with a Paveway II laser guidance kit. This improved 2,000-pound bomb is used against targets requiring deeper penetration. The GBU-10 Paveway represents the next phase in precision-guided munition (PGM) technology. Utilizing the same principles as the GBU-8, the GBU-10 uses the same Mk. 84 2,000 pound bomb but with a seeker head which homes in on laser energy reflected off of a "designated" target. Targets may be designated by either the launching aircraft or another aircraft in the area, by an Unmanned Aerial Vehicle (UAV), or by personnel on the ground. In addition, since the GBU-10 orients itself on the reflected laser, rather than the target, it can be directed towards a different target after launch simply by pointing the designator at a different target. There are currently two versions of the GBU-10 in the American inventory; the original Paveway I, which has fixed guidance fins on the bomb's tail section, and the improved Paveway II, which has an improved seeker head and low profile "pop out" retractable guidance fins. The munition was used during Operation Desert Storm, and, according to the Air Force, hit 78 percent of its targets. In Operation Desert Storm, GBU-10/10Is were used extensively by F-15Es and F-111Fs mainly against bridges, Scuds, C3I (command, control, communications, intelligence) nodes, and bunkers. Of the 2,637 expended,'44 over one- third were dropped by F-111Fs, and the rest by F-117s, F-15Es, and Navy and Marine Corps aircraft. There are two generations of GBU-10 LGBs: Paveway I with fixed wings and Paveway II with folding wings. Paveway II models have the following improvements: detector optics and housing made of injec- tion-molded plastic to reduce weight and cost; increased detector sensitiv- ity; reduced thermal battery delay after release; increased maximum canard deflection; laser coding; folding wings for carriage, and increased detector field of view. (Paveway II's instantaneous field of view is thirty percent greater than that of the Paveway I's field of view). Background: Precision-guided munitions (PGM) can trace their origins back to World War Two. These early weapons, such as the QB-17G "Aphrodite" were essentially airframes packed with explosives and guided via radio direction signals to their target, where they would crash and explode. While guidance was extremely crude by today's standards, these weapons were more accurate than conventional dropped munitions, and did not expose aircrews to deadly enemy anti-aircraft fire. Unfortunately, such weapons were unwieldy, unsuitable for small targets, and were themselves subject to defensive fire. The first truly precision-guided munitions did not appear until the Vietnam War. Serving as a major supply conduit for North Vietnam, the mile long Paul Doumer Bridge over the Red River was the most important ground target of the war. Unfortunately, it was also one of the most heavily defended, its approaches ringed with anti-aircraft guns and surface to air missile emplacements. While American pilots were able to attack the bridge using conventional munitions, such missions were extremely hazardous and casualties were high. In 1967 the Rockwell International Corporation was tasked with producing a precision munition using electro-optical guidance technology. The end result was the GBU (Guided Bomb Unit) 8 or Homing Bomb System (HOBOS), a conventional Mk. 84 2,000 pound bomb with a TV like electro-optical guidance package in the nose to provide direction and a modified tail fin assembly in the rear to provide lift. To launch the GBU-8 the pilot aligned the TV camera sight in the bomb with the target and the weapons officer locked the bomb's seeker onto the target. Once aligned, the bomb could be released well away from the target area and it would guide itself into the target with a high degree of accuracy.

Mk. 80 Series General Pur

David — Thu, 16 Jan 2003 23:24:35 -0800

by: David

Description: Function: General Purpose, low drag free-fall bomb. Background: The Mk 80 series bombs are is a non-guided, low drag, free-fall, general purpose explosives. The cases are relatively light; approximately 45 percent of their total weight is explosive filler and are designed to be streamlined, so as to reduce aerodynamic resistance. Mk. 80 GP bombs are typically used in situations where pin-point accuracy is not critical and where maximum blast and explosive effects are desired. There are currently four variants of the Mk. 80 GP bomb: the Mk. 81 250 pound bomb, the Mk. 82 500 pound bomb, the Mk. 83 1,000 pound bomb, and the Mk. 84 2,000 pound bomb. These bombs are usually equipped with both nose and tail mechanical fuses for ground bursts, or a radar-proximity fuse for air-bursts. For low altitude delivery, the Mk. 80 series bombs may be equipped with either a high-drag "popout" tail fin assembly or "ballute" (combination balloon/parachute) drogue assembly. These retardation devices slow the descent rate of the bomb significantly, allowing the releasing aircraft to maneuver clear of the target area prior to detonation. Thermally protected versions of the Mk. 80 series were developed for use on aircraft carriers. These weapons are filled with a less sensitive explosive and treated to resist "cook off" in the event of exposure to an aviation fuel fire. Two hard target penetration variants of the Mk. 80 series are currently in production. The BLU-111 is the 500lb variant and the BLU-110 is the 1,000 pound variant. The bomb case is made from forged steel, and the H-6 or Tritonal explosive filler has been replaced with PBNX-109. Description: The basic Mk. 80 GP bomb consists of a an explosive filled metal case. Specific fuses may be added to the nose and tail sections of the case, depending on the desired blast effect, and the case can be equipped with either low drage guidance fins or a high drag "popout" fin or "ballute" assembly. General Characteristics, Mk. 80 Series General Purpose Free Fall Bombs Length: Mk.81: 46 in. (1.18 meters) Mk.82: 66.15 in. (2.21 meters) Mk.83: 119.49 in. (3 meters) Mk.84: 129 in.(3.31 meters) Diameter: Mk.81: 8.9 in. Mk.82: 10.75 in. Mk.83: 14.06 in. Mk.84: 18 in. Filler types: H-6, Minol II, PBNX-109, Tritonal Date Deployed: 1950s Weight: Mk.81: 250 lb (113 kg) Mk.82: 500 lb (227 kg) Mk.83: 1,000 lb (455 kg) Mk.84: 2,000 lb (909 kg) Filler Weight: Mk.81: Mk.82: 192 lb (89 kg) Mk.83: 385 lb (202 kg) Mk.84: 945 lb (430 kg) Unit Cost: Mk.81: Mk.82: $268.50 Mk.83: Mk.84: $3,100

AGM-45 Shrike

David — Thu, 16 Jan 2003 23:24:34 -0800

by: David

Description: Function: Antiradiation missile that homes in on hostile antiaircraft radars. Description: The Shrike was developed by the Naval Weapons Center at China Lake in 1963. It is an antiradiation missile designed to home in on hostile antiaircraft radars. It is currently used by U.S. and Israeli air forces. General Characteristics, AGM-45 Shrike Missile Propulsion: Solid-fuel rocket Length: 10 feet (3.05 meters) Weight: 390 pounds (177.06 kilograms) Diameter: 8 inches (20.32 centimeters) Wingspan: 3 feet (.914 meters) Warhead: Conventional Guidance System: Passive radar homing Platforms: A-4 Skyhawk, A-6 Intruder Unit Cost: $32,000

AGM-84D Harpoon

David — Thu, 16 Jan 2003 23:24:34 -0800

by: David

Description: Function: The AGM-84D Harpoon is an all-weather, over-the-horizon, anti-ship missile system produced by McDonnell Douglas. Its low-level, sea-skimming cruise trajectory, active radar guidance and warhead design assure high survivability and effectiveness. Description: The AGM-84D Harpoon has been adapted for use on B-52H bombers, which can carry from eight to 12 missiles. The Harpoon missile and its launch control equipment provide the warfighter capability to interdict ships at ranges well beyond those of other aircraft. History: Originally developed for the U.S. Navy to serve as its basic anti-ship missile for fleetwide use, the AGM-84D Harpoon also has been adapted for use on Air Combat Command's B-52H bombers. At the direction of Headquarters Strategic Air Command, the Harpoon Air Command and Launch Control Set was fully integrated into a fully operational B-52G from Mather AFB, CA, in March 1983. Three successful live launches at the Naval Air Warfare Center, Point Mugu, Calif., led to the modification of a total of 30 B-52Gs with Harpoon launch control equipment, enough to provide two squadrons of Harpoon-capable B-52Gs by June 30, 1985. The 42nd Bombardment Wing, Loring Air Force Base, Maine, and the 43rd Bombardment Wing, Andersen Air Force Base, Guam, were first tasked to perform the Harpoon mission. Both wings refined tactics and doctrine to merge the long-range, heavy-payload capability of the B-52 with the proven reliability of this superior stand-off attack weapon. After Loring AFB closed and the retirement of the last B-52G at Castle AFB, Calif., the Harpoon mission was moved to the 2nd Bomb Wing at Barksdale AFB, La. Four B-52H models were rapidly modified (as an interim measure) to accept Harpoon launch control equipment pending B-52H fleet modification. By 1997, all B-52H airframes will be Harpoon capable, providing both the 5th Bomb Wing at Minot AFB, ND, and the 2nd Bomb Wing at Barksdale, full squadron strength capability. General Characteristics, AGM-84D Harpoon Missile Contractors: McDonnell Douglas Power Plant: Teledyne Turbojet Thrust: 660 pounds Length: 12 feet, 7 inches (3.79 meters) Weight: 1,145 pounds (515.25 kilograms) Diameter: 13.5 inches (34.29 centimeters) Wingspan: 3 feet (91.44 centimeters) Range: Over the horizon Speed: High subsonic Warheads: Penetration high-explosive blast (488 pounds) Guidance System: Sea-skimming cruise monitored by radar altimeter, active radar terminal homing Inventory: Classified Date Deployed: 1985 Unit Cost: Not available

AGM-130

David — Thu, 16 Jan 2003 23:24:34 -0800

by: David

Description: Function: The AGM-130 is a powered air-to-surface missile designed for high- and low-altitude strikes at standoff ranges against a variety of targets. Description: Carrying forward the modular concept of the GBU-15 guided weapon system, the AGM-130 employs a rocket motor for extended range and an altimeter for altitude control. The AGM-130 provides a significantly increased standoff range than the GBU-15. The AGM-130 has to two variants, based on the warhead. The AGM-130A is a MK-84 blast/fragmentation warhead and the AGM-130C is a BLU-109 penetrator. The AGM-130 is equipped with either a television or an imaging infrared seeker and data link. The seeker provides the launch aircraft a visual presentation of the target as seen from the weapon. During free flight this presentation is transmitted by the AXQ-14 data-link system to the aircraft cockpit monitor. The seeker can be either locked onto the target before or after launch for automatic weapon guidance, or it can be manually steered by a weapon systems officer. Manual steering is performed through the two-way data link. The AGM-130 is designed for use in the F-15E aircraft. Development of the AGM-130 began in 1984 as a product improvement of the GBU-15 guided glide bomb. For the primary mode of operation, the aircraft flies to a pre-briefed launch position. The survivability of aircraft and crew is enhanced by launching the weapon at low altitude and significant standoff range, thus avoiding detection by enemy air defenses. After launch, the weapon flies through glide-powered-glide phases toward the target area with midcourse guidance updates provided by global positioning system (GPS) navigational information or by the weapon systems officer through the data link. Upon termination of the powered flight phase the rocket motor is ejected. As the target comes into view, the weapon systems officer has dual flexibility in guiding the weapon via the data link. For automatic terminal homing, the guidance tracker is locked on target but can be manually updated for precision bombing. When total manual guidance is used, the operator manually guides the weapon to the target aimpoint. For those aircraft not equipped with a data-link pod, the weapon may be launched in the direct attack mode. History: The first unit was operational in 1994. General Characteristics, AGM-130 Missile Contractor: Boeing Company Thrust: Classified Length: 12 feet, 10.5 inches (3.90 meters) Launch Weight: 2,917 pounds (1,312.65 kilograms) Diameter: 18 inches (45.72 centimeters) Wingspan: 59 inches (149.86 centimeters) Range: Classified Ceiling: 30,000-plus feet (9,091 meters) Speed: Classified Guidance System: television or imaging infrared seeker Inventory: The missile is currently in production or retrofit; when in the inventory the number will be classified Date Deployed: 1994 Unit Cost: Approximately $450,000 per weapon

AIM-7 Sparrow

David — Thu, 16 Jan 2003 23:24:34 -0800

by: David

Description: Function: The AIM-7 Sparrow is a radar-guided, air-to-air missile with a high-explosive warhead. The versatile Sparrow has all-weather, all-altitude operational capability and can attack high-performance aircraft and missiles from any direction. It is a widely deployed missile used by U.S. and North Atlantic Treaty Organization forces. Description: The missile has four major sections: guidance section, warhead, control and rocket motor. It has a cylindrical body with four wings at mid-body and four tail fins. Although external dimensions of the Sparrow remained relatively unchanged from model to model, the internal components of newer missiles represent major improvements with vastly increased capabilities. History: The AIM-7F joined the Air Force inventory in 1976 as the primary medium-range, air-to-air missile for the F-15 Eagle. The AIM-7M, the only current operational version, entered service in 1982. It has improved reliability and performance over earlier models at low altitudes and in electronic countermeasures environments. It also has a significantly more lethal warhead. The latest software version of the AIM-7M is the H-Build that has been produced since 1987 and incorporates additional improvements in guidance. The F-15 Eagle and F-16 Fighting Falcon fighters carry the AIM-7M Sparrow. U.S. and NATO navies operate a surface-to-air/surface version of this missile called the RIM-7F/M Sea Sparrow. In the Persian Gulf War, the radar-guided AIM-7 Sparrow proved to be a potent air-to-air weapon used by Air Force fighter pilots. Twenty-two Iraqi fixed-wing aircraft and three Iraqi helicopters were downed by radar-guided AIM-7 Sparrow missiles. General Characteristics, AIM-7 Sparrow Contractors: Raytheon Corporation Power Plant: Hercules MK-58 solid-propellant rocket motor Thrust: Classified Length: 12 feet (3.64 meters) Launch Weight: Approximately 500 pounds (225 kilograms) Diameter: 8 inches (0.20 meters) Wingspan: 3 feet, 4 inches (1 meter) Range: Classified Speed: Classified Warhead: Annular blast fragmentation Guidance System: Raytheon semiactive on either continuous wave or pulsed Doppler radar energy Inventory: Classified Date Deployed: AIM-7F: 1976 AIM-7M: 1982 Unit Cost: Approximately $125,000

AIM-54 Phoenix

David — Thu, 16 Jan 2003 23:24:34 -0800

by: David

Description: Function: Long-range air-to-air missile, carried in clusters of up to six missiles on the F-14 Tomcat. Description: The Phoenix missile is the Navy's only long-range air-to-air missile. It is an airborne weapons control system with multiple-target handling capabilities, used to kill multiple air targets with conventional warheads. Near simultaneous launch is possible against up to six targets in all weather and heavy jamming environments. The improved Phoenix, the AIM-54C, can better counter projected threats from tactical aircraft and cruise missiles. General Characteristics, AIM-54 Phoenix Missile Contractors: Hughes Aircraft Corporation and Raytheon Corporation Power Plant: Solid propellant rocket motor built by Hercules Length: 13 feet (3.9 meters) Weight: 1,024 pounds (460.8 kilograms) Diameter: 15 inches (38.1 centimeters) Wingspan: 3 feet (.9 meter) Range: In excess of 100 nautical miles (115 statute miles, 184 kilometers) Speed: In excess of 3,000 mph (4,800 kmh) Warhead: Proximity fuse, high explosive Warhead Weight: 135 pounds (60.75 kilograms) Guidance System: Semi-active and active radar homing Date Deployed: 1974 Unit Cost: $477,131

BLU-82 "Daisy Cutter

David — Thu, 16 Jan 2003 23:24:34 -0800

by: David

Description: Function: 15,000 pound special purpose bomb. Background: Introduced in March of 1970 as a field expedient method for carving out helicopter landing zones in the jungles of Vietnam (known as Commando vault airlift operations), the 15,000-pound BLU-82B, more popularly known as the "Daisy Cutter", is arguably the world's largest non-nuclear conventional airdropped munition. The BLU-82 is filled with 12,600 pounds of GSX explosive slurry and when detonated creates a blast wave of over 1,000 lbs. per square inch, which is sufficient to shear an 8" diameter tree off at its base and clear an area approxiamately 260 feet in diameter. The BLU-82 is equipped with a 38" stand-off detonator fuse, which facilitates in the formation of the blast wave and can only be delivered by Special Operations MC-130 Combat Talon cargo aircraft. Because the BLU-82 must be dropped from at least 6,000 feet AGL (to avoid collateral damage to the dropping aircraft) and the aircraft itself is not equipped with an offensive air-ground radar system, accurate delivery of the weapon is dependent upon precise aircraft alignment (this can be achieved through either internal, on board navigational and positioning equipment or through steering cues provided by either ground or aerial radar control stations) and strict adherence to the bomb run profile. Because of its blast potential, the Commando Vault is extremely effective in urban or built up areas as well as collapsing defensive fortifications and bunker complexes. The BLU-82 is also of limited effectiveness as a minefield clearing munition. Description: The BLU-82 is essentially a large, explosive filled cylinder. The cylinder is olive drab in color, 4.5 feet in diameter, approximately 12 feet long, and equipped with a conical aerodynamic nose cone and tipped with a 38-inch standoff detonator. The bomb itself is unguided and utilizes a drogue parachute to both orient the weapon "nose first" and to control its rate of descent. Prior to deployment the BLU-82 is mounted on a sled-like loading/delivery pallet. To launch the bomb, a cargo extraction parachute is deployed which, in turn, pulls the palletized bomb out of the aircraft. Once the bomb has left the aircraft a static line automatically deploys the bomb stabilization chute. The cargo extraction chute and delivery cradle are both discarded once the bomb stabilization chute deploys. ?General Characteristics, BLU-82 Commando Vault Length: 11.8 feet (3.63 meters) Diameter: 4.5 feet (1.38 meters) Unit Cost: $27,318 each Weight: 15,000 lbs (6,818 kg.) Filler type: 12,600 lbs GSX Aluminum-based slurry Introduction date: March 1970

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