The Patriot Files

Patriot PAC-3 ERINT

David — Fri, 21 Mar 2003 06:49:57 -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.

AN/APY-1/2

David — Tue, 11 Feb 2003 14:14:28 -0800

by: David

Description: Function: Early Warning sensor. Description: Housed in a dome 30 feet (9.1 meters) in diameter, six feet (1.8 meters) thick, and suspended 11 feet (3.3 meters) above the fuselage on two struts, the AN/APY-1/2 radar is the most notable feature of the E-3 Airborne Early Warning aircraft. Introduced in 1977, the APY-1/2 equipped Sentry aircraft have served as the primary AEW sensor for both America and NATO. When in operation, the radar turns at 6 revolutions per minute, and is capable of scanning the sea, ground, and air in a 200 mile (320km) radius around the aircraft. The APY-1 radar is sensitive enough to detect and track slow moving, low altitude air targets over any terrain, and can track both sea and air targets simultaneously. The AN/APY-1/2 can operate in a variety of modes; Pulse Doppler Non Elevation Scan for surveillance of airborne targets, Pulse Doppler Elevation Scan to determine the elevation, beyond the horizon pulse radar mode, receive only mode for passive operation, and maritime mode which uses very short pulse width for surface ship detection.

AN/SPY-1

David — Tue, 11 Feb 2003 14:14:28 -0800

by: David

Description: Function: Phased array radar. Description: Introduced in 1983 as the heart of the Aegis Combat System and the new Ticonderoga class Guided Missile cruiser, the AN/SPY-1 multi-function, phased array radar was a radical departure from prior conventional radar systems. The AN/SPY-1 held several advantages over earlier radars; First, where a conventional radar such as the AN/SPS-49 must sweep through a 360 degree arc looking for targets, and can only see those targets while they are within the radar's rotating "cone" the AN/SPY-1 radar is made up of four flat panels on the ship's superstructure which continuously radiate in all directions simultaneously, thereby allowing the system to acquire multiple targets coming in from multiple directions. Second, while a second radar is required to direct weapons to the target once it is acquired by the search radar, the phased array SPY-1 is capable performing both tasks simultaneously. Radiating four million watts of power, the AN/SPY-1 can acquire and track targets as far out as 250 miles and as far up as low Earth orbit. In addition, the phased array system can track 100 targets simultaneously and engage them automatically, prioritizing targets by threat characteristics. There are currently four versions of the SPY-1 radar in service. Block I, the SPY-1A, was introduced with the USS Ticonderoga (CG47) and installed through the USS Philippine Sea(CG 58). Block II, the SPY-1B and it's later upgrade, the SPY-1B(V), was installed on the USS Princeton (CG59) and all subsequent Aegis cruisers, through USS Port Royal (CG 73). Introduced on July 4, 1991, the Arleigh Burke class Guided Missile destroyers are all equipped with the improved AN/SPY-1D. Finally, there is a reduced capacity version of the SPY-1D, designated the SPY-1F, available for installation on frigate sized vessels. While the United States does not currently intend to back-fit any of its Oliver Hazard Perry class frigates with the SPY-1F, the system is available for export.

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AN/MPQ-53

David — Tue, 11 Feb 2003 14:14:28 -0800

by: David

Description: Function: Phased array radar. Description: Introduced in 1977 and part of the most sophisticated air defense system in the world, the AN/MPQ-53 phased array radar carries out search, target detection, track and identification, missile tracking and guidance and electronic counter-countermeasures (ECCM) functions for the MIM-104 Patriot long range theater air defense system. The radar is mounted on a trailer and is automatically controlled by the digital weapons control computer in the Engagement Control Station (AN/MSQ-104), via a cable link. The radar system has a range of up to 100 km, capacity to track up to 100 targets and can provide missile guidance data for up to nine missiles. The AN/MSQ-104 Engagement Control Station is the only manned station in a Patriot Fire Unit. The Control Station communicates with the M901 Launching Stations, other Patriot batteries and the higher command headquarters.

AN/PAQ-3 Modular Universa

David — Tue, 11 Feb 2003 14:08:47 -0800

by: David

Description: Function: Target locator and guide for laser-guided projectiles. Description: The MULE is a man-portable tripod-mounted or shoulder-fired unit which incorporates a laser range-finder/target designator which works with all laser-guided weapons now under development. It is used to locate targets and to guide laser-guided projectiles to their targets. It can track moving targets and combine range, azimuth, and elevation into a digital message to be sent to the tactical fire control center. The major components are the Laser Designator/Rangefinder Module and the Stabilized Tracking Tripod Module. A supporting item of equipment is the North Finding Module. The system is capable of operating on 24 volt DC rechargeable batteries, or from 24 volt DC vehicle power using an external power adapter. It can effectively range a moving target to 3,000 meters, and a stationary target to 5,000 meters. Background: When the MULE was approved and fielded, certain shortcomings, such as the weight and bulk of the system and the inability to boresight the sight with the laser at the unit level, were both understood and accepted. The Mule provided a sorely needed target acquisition device that used emerging technology and was relatively successful. General Characteristics, AN/PAQ-3 Modular Universal Laser Equipment (MULE) Manufacturer: Hughes Aircraft Weight: Daylight operations: 42 pounds (19.07 kilograms) With night sight: 108 pounds (49.03 kilograms) In shipping cases: 220 pounds (99.88 kilograms) Laser designator/rangefinder module: Field of view: 4 degrees Magnification: 10x Stabilized tracking tripod module: Field of rotation: 360? Elevation: Up: 16.9 degrees, down 22.5 degrees Terrain capability: 0 degrees to 15 degrees Power Requirements: Batteries: 24 volts, nickel-cadmium Battery life: rechargeable (Indefinite) Run Time: 10 minutes Recharge time: 7 hours Unit Replacement Cost: $6,500

M90 Radar Chronograph

David — Tue, 11 Feb 2003 14:08:47 -0800

by: David

Description: Function: To measure the muzzle velocity of field artillery weapons. Description: The M90 Radar Chronograph provides muzzle velocity data to the Fire Direction Center (FDC), enabling the FDC to compute accurate fire control solutions. This data input is critical to FD computations. Each artillery battery has one M90. The M90 Radar Chronograph is a Doppler radar system that consists of a radio frequency antenna, transmitter-receiver, readout display, mounting brackets that are semi-permanently mounted to each artillery weapon, and the necessary cables. The antenna and transmitter-receiver are mounted on a nonrecoiling part of the howitzer and are connected to the display/control unit by a 30-meter cable. The radar chronograph is powered by an external source of 18 - 30 volts DC. The M90 is not able to measure muzzle velocities of rocket-assisted projectiles or basebleed projectiles. General Characteristics, M90 Radar Chronograph Length: 33 inches (83.82 centimeters) Width: 380 inches (96.52 centimeters) Height: 20 inches (50.8 centimeters) Weight: 200 pounds (90.8 kilograms) including transit case and accessories Unit Replacement Cost: $23,034

AN/TMQ-41 Meteorological

David — Tue, 11 Feb 2003 14:08:47 -0800

by: David

Description: Function: To acquire and process meteorological data, including wind speed and direction, humidity, temperature and pressure. Description: This is a lightweight, automated, electronic system with essentially the same performance requirements as the current AN/TMQ-31 MDS. The major differences are size and weight. General Characteristics, AN/TMQ-41 Meteorological Measuring Set (MMS) Manufacturer: ETG Crew Size: Five Set-Up Time: 15 minutes Modes: LORAN, Omega, VLF, RDF Range: 75-165 km Accuracy: Wind speed: <2 knots Position: <40 knots Temperature: 0.5? C Humidity: 3% Pressure: 2 millibars Support Vehicles: One generator and two HMMWVs w/trailers Units: One per artillery battalion, consolidated at regimental HQ Battery Unit Replacement Cost: $462,471

M94 Muzzle Velocity Syste

David — Tue, 11 Feb 2003 14:08:47 -0800

AN/ALQ-131

David — Tue, 11 Feb 2003 14:04:39 -0800

by: David

Description: Function: Radar jamming system. Description: The pod provides self protection jamming for tactical fighter aircraft and is designed to operate in a dense, hostile environment of radar directed (RF) threats that require high duty cycle (pulse doppler) or CW jamming techniques. The ALQ-131 is modularly constructed, containing numerous receivers, antennas, and transmitters, active over up to five frequency bands, designed to jam, deceive, and confuse threat radar homing missiles. Because the ALQ-131 pod is modular, the system can be configured to cope with a range of threats by selecting individual modules for inclusion in the pod. The AN/ALQ-131 pod is capable of producing both "white noise" and deception jamming signals. The pod is controlled from the cockpit by both automatic and manual systems. Basic hardware components include an Interface and control module, 2 or 3 Band modules that cover a portion of the pod's total frequency range, and the Receiver/Processor (R/P) module. The R/P module combines an accurate signal identification capability with power management. An important function of the R/P is the management of "look through" which permits periodic surveillance of the threat environment while jamming is in progress. The AN/ALQ-131 pod is certified for use with All American tactical aircraft as well as many Western or NATO tactical aircraft.

AN/ALQ-144

David — Tue, 11 Feb 2003 14:04:39 -0800

by: David

Description: Function: Infrared countermeasures device. Description: The AN/ALQ-144 system is an active infrared countermeasures device designed to protect helicopters from infrared (heat seeking) air-to-air and surface-to-air threats. The continuously operating, omni-directional jammer utilizes variable frequency infrared pulses to decoy or jam an incoming missile's seeker head. The AN/ALQ-144A (1) and (3) are upgraded versions of the AN/ALQ-144 (V)1 and (V)3 for helicopter applications. The fixed-wing version is designated the AN/ALQ-147A (V)1 and (V)2. The AN/ALQ-144 system consists of a transmitter assembly and an operator control unit (OCU) with dual capabilities. The total system weight is 30 pounds.

AN/ALQ-135

David — Tue, 11 Feb 2003 14:04:39 -0800

by: David

Description: Function: Internal countermeasures set. Description: The F-15 TEWS consists of the AN/ALR-56C radar warning receiver (RWR), the AN/ALQ-135 internal countermeasures set (ICS), the AN/ALQ-128 electronic warfare warning set, and the AN/ALE-40/45 countermeasures dispenser. The TEWS provides electronic detection and identification of both surface and airborne threats. In addition, it allows for activation of appropriate countermeasures to include electronic jamming and dispensing of expendables such as chaff and flares Integral to the F-15 TEWS, the ALQ-135 ICS is an internally mounted responsive jammer designed to counter surface to air threats with minimum air crew activity. The system is sized to fit into the limited space of the F-15E interdiction aircraft's ammunition bay although upgraded components have also been retrofitted into the F-15C air superiority variant. The system has an improved reprogramming support capability to rapidly change pre-flight message (PFM) software in response to changing threat parameters and mission requirements. The ALQ-135 ICS has been fielded in several phases to provide incremental improvements to jamming coverage. Phase one has provided an initial Band 3 capability that includes integrated operation with both the F-15E fire control radar and the ALR-56C RWR. ALQ-135 ICS Band 3 capability currently allows full interoperability and robust jamming techniques against modern pulse Doppler radar. Full system capability requires the installation and integration of Band 1.5 hardware to provide coverage against threats operating in the lower frequency range. . The F-15 TEWS AN/ALQ-135 Band 1.5 contributes to full-dimensional protection by improving individual aircraft probability of survival through improved air crew situation awareness of the radar guided threat environment, cueing of both active and passive counter measures in Band 1.5 frequency spectrum, and waveform select feature for jamming optimization against specific threats. AFOTEC was directed to conduct an interim TEWS OA to characterize the operational capabilities and limitations of the fielded systems and assess readiness for IOT&E. The OA concluded in September 1994 recommended five ALQ-135 improvements: interoperability with the APG-70 radar; system response times; built-in-test (BIT) displays; BIT accuracy; and low band frequency coverage for the F-15E (i.e., Band 1.5). FOT&E operations conducted by the United States Air Force Air Warfare Center (USAFAWC) concluded in August of 1996, addressed ALQ-135 Band 3 ICS interoperability with the APG-70 radar and improvements in the BIT displays. The USAFAWC is currently conducting FOT&E at the Multi-Spectral Threat Environment (MSTE) range located at Eglin AFB to evaluate intra-flight (wing man) compatibility, the advanced threat de-interleave processor (for improved system response times), and jamming effectiveness and BIT upgrades. History: The ALQ-135 is an outgrowth of an early 1980s feasibility demonstration and follow-on quick reaction capability (QRC) high band jammer developed to counter rapidly changing threats. Developmental problems precipitated a restructuring of the ALQ-135 ICS program in 1988 to provide incremental capabilities. A TEWS EOA of the Phase I Band 3 ICS was planned in July 1989 to support F-15E IOC. However, technical problems delayed EOA start until July 1990. Fifteen sorties were flown against threat simulators on the Eglin AFB, FL range complex in air-to-air and air-to-ground mission scenarios. The ICS demonstrated the capability to identify and counter most current threats in a limited density environment, but the test indicated additional software and hardware development was needed to achieve desired operational capabilities.

Laser Rangefinder AN/GVS-

David — Tue, 11 Feb 2003 14:01:28 -0800

by: David

Description: Function: Laser rangefinder for target acquisition. Description: The AN/GVS-5 is a lightweight, hand-held, binocular-like laser rangefinder used for observation and target acquisition. It contains a panel assembly, optical assembly, and laser transmitter module. It can use either battery or vehicle power (using an adapter cable). The rangefinder provides the operator with the capability to accurately determine range to targets. The AN/GVS-5's special features include: 7 x 15 sighting optics, a multiple target indicator, and minimum range adjustment. The rangefinder can take one ranging per second. It can take approximately 100 rangings before requiring a new battery. Background: This system was procured to provide the user a means of verifying the location of targets to be engaged by air or ground fire support means. The rangefinder can also assist in the adjustment of rounds on the target by aiding in the determination of the impact of the rounds in relation to the targets. The system is fully operational in the Fleet Marine Force. General Characteristics, Laser Rangefinder AN/GVS-5 Manufacturer: Radio Corporation and various vendors Length: 9 inches (22.86 centimeters) Width: 8 inches (20.32 centimeters) Height: 4 inches (10.16 centimeters) Weight: 5 pounds (2.27 kilograms) with battery Emission Wave Length: 1.06 microns Beam Divergence: 1 milliradian Range Measurements Limits: 200 - 9,990 meters Range Error: + or - 10 meters Power Requirements: 24 volts Eye Safe Range (Unattenuated): 1,100 meters Safe Attenuated Ranges (For Training): 120 and 20 meters (using different filters) Unit Replacement Cost: $5,370

LANTIRN

David — Tue, 11 Feb 2003 14:01:28 -0800

by: David

Description: Function: Aircraft targeting and low-altitude navigation system. Description: Designated as the Low Altitude Navigation and Targeting Infrared for Night, LANTIRN is a system for use on the F-15E Strike Eagle, F-16C/D Falcon and the F-14 Tomcat. LANTIRN significantly increases the combat effectiveness of these aircraft, allowing them to fly at low altitudes, at night and under-the-weather to attack ground targets with a variety of precision-guided and unguided weapons. The LANTIRN system consists of two externally mounted pods, an AN/AAQ-13 navigation pod and a AN/AAQ-14. The navigation pod provides high-speed penetration and precision attack on tactical targets at night and in adverse weather. The navigation pod also contains a terrain-following radar and a fixed infrared sensor, which provides a visual cue and input to the aircraft's flight control system, enabling it to maintain a pre-selected altitude above the terrain and avoid obstacles. This sensor displays an infrared image of the terrain in front of the aircraft, to the pilot, on a head-up display. The navigation pod enables the pilot to fly along the general contour of the terrain at high speed, using mountains, valleys and the cover of darkness to avoid detection. The targeting pod contains a high-resolution, forward-looking infrared sensor (which displays an infrared image of the target to the pilot), a laser designator-rangefinder for precise delivery of laser-guided munitions, a missile boresight correlator for automatic lock-on of AGM-65D imaging infrared Maverick missiles, and software for automatic target tracking. These features simplify the functions of target detection, recognition and attack and permit F-16 pilots to attack targets with precision-guided weapons on a single pass. History: The research and development program began in September 1980 with Martin Marietta Corporation as contractor. Initial operational test and evaluation of the LANTIRN navigation pod was successfully completed in December 1984. The Air Force approved low rate initial production of the navigation pod in March 1985 and full-rate production in November 1986. The first production pod was delivered to the Air Force on March 31, 1987.

Defense Satellite Communi

David — Tue, 11 Feb 2003 13:14:23 -0800

by: David

Description: Function: The Defense Satellite Communications Systems (DSCS) is an important part of the comprehensive plan to support globally distributed military users. Description: Air Force Space Command operates ten Phase III DSCS satellites that orbit the earth at an altitude of more than 22,000 miles. Each satellite uses six super high frequency transponder channels capable of providing secure voice and high rate data communications. DSCS III also carries a single-channel transponder for disseminating emergency action and force direction messages to nuclear-capable forces. The system is used for high priority command and control communication such as the exchange of wartime information between defense officials and battlefield commanders. The military also uses DSCS to transmit space operations and early warning data to various systems and users. Background: The Air Force began launching the DSCS IIIs in 1982. The system is built with single, multiple-beam antennas that provide more flexible coverage than its predecessor. The single steerable dish antenna provides an increased power spot beam which can be tailored to suit the needs of different size user terminals. DSCS III satellites can resist jamming and are expected to operate twice as long as the previous generation. DSCS users operate on the ground, at sea or in the air. Members of the 50th Space Wing's 3rd Space Operations Squadron at Schriever Air Force Base, Colo., provide satellite bus command and control for all DSCS satellites. Air Force Materiel Command's Space and Missile Systems Center at Los Angeles AFB, Calif., is responsible for development and acquisition of DSCS satellites and ground systems. General Characteristics, Defense Satellite Communications System Primary Contractor: Lockheed Martin Missiles and Space Power Plant: Solar arrays generating average of 1,500 watts Dimensions: Rectangular body is 6 feet long (1.8 meters), 6 feet high (1.8 meters), and 7 feet wide (2.1 meters); 38-foot span (11.5 meters) with solar arrays deployed) Weight: 2,716 pounds (1,232 kilograms) Orbit Altitude: 22,230 miles (35,887 kilometers) Launch Vehicle: Atlas II, later the evolved expendable launch vehicle Inventory: 4 Unit Replacement Cost: $200 million

Milstar Satellite Communi

David — Tue, 11 Feb 2003 13:14:23 -0800

by: David

Description: Function: Global surviving and enduring military communications system. Description: Milstar is a joint service satellite communications system that provides worldwide secure, jam resistant and low probability of detection nuclear-event resistant communications for all forces across the spectrum of conflict. The multi-satellite constellation will link command authorities with a wide variety of resources, including ships, submarines, aircraft, land vehicles and manned-portable systems. Milstar is the most advanced military communications satellite system to date and represents the future of the U.S. communications capability. The operational Milstar satellite constellation will consist of four satellites positioned around the Earth in geosynchronous orbits. Each mid-latitude satellite weighs approximately 10,000 pounds (4,536 kilograms) and have a design life of 10 years. Each Milstar satellite serves as a smart switchboard in space by directing traffic from terminal to terminal anywhere on the Earth. Since the satellite actually processes the communications signal and can link with other Milstar satellites through crosslinks, the requirement for ground controlled switching is significantly reduced. The satellite establishes, maintains, reconfigures and disassembles required communications circuits as directed by the users. Milstar terminals provide encrypted voice, data, teletype or facsimile communications. A key goal of Milstar is to provide interoperable communications among the users of Army, Navy, and Air Force Milstar terminals. Geographically dispersed mobile and fixed control stations provide survivable and enduring operational command and control for the Milstar constellation. The Milstar system is composed of three segments: space (the satellites), terminal (the users), and mission control. Air Force Materiel Command's Space and Missile Systems Center (SMC) at Los Angeles AFB, CA, is responsible for development and acquisition of the Milstar space and mission control segments. The Electronics Systems Center (ESC) at Hanscom AFB, MA is responsible for the Air Force portion of the terminal segment development and acquisition. The 4th Space Operations Squadron at Schriever AFB, CO, is the front line organization providing real time satellite platform control and communications payload management. History: The first Milstar satellite was launched Feb. 7, 1994 aboard a Titan IV expendable launch vehicle. The second was launched Nov. 5, 1995. Beginning with the fourth launch in 2000, the satellites will have greatly increased capacity because of an additional medium data rate payload. A total of three launches remain. General Characteristics, Milistar Satellite Communications System Primary Contractor: Lockheed Martin Missiles and Space Power Plant: Solar panels generating 5,000 watts Payload: All satellites: Low data rate communications (voice, data, teletype and facsimile) at 75 bps to 2,400 bps Medium data rate communications (voice, data, teletype, facsimile) at 4.8 kbps to 1.544 bps (Satellites 4 through 6 only) Weight: About 10,000 pounds (4,536 kilograms) Orbit Altitude: 22,300 nautical miles (inclined geostationary orbit) Launch Vehicle: Titan IVB/Centaur upper stage Inventory: 2 Unit Replacement Cost: $800 million

Single Channel Ground and

David — Tue, 11 Feb 2003 13:14:23 -0800

by: David

Description: Function: Tactical communications radio. Description: Provides the primary means of command, control and communications (C3) for the Ground Combat Element (GCE), Air Combat Element (ACE), and Combat Service Support Element (CSSE) of the Marine Air Ground Task Force (MAGTF). Capable of transmitting voice and analog or digital data up to 16 kbps. Employs electronic counter-countermeasures (ECCM) to minimize vulnerability to enemy electronic warfare and provides secure communications with an integrated communications security (ICOM) device. Replaces the AN/PRC-77 and VRC-12 series radios and provides improved reliability, availability, and maintainability. General Characteristics, Single Channel Ground and Airborne Radio System (SINCGARS) Manufacturer: ITT Aerospace Communications Division Length: 10 inches (25.3 centimeters) Width: 10.7 inches (27.1 centmeters) Height: 3.4 inches (8.7 centimeters) Weight: 15.4 pounds (7 kilograms) Inventory: AAO - 25,390 Unit Replacement Cost: $6,500

Defense Support Program S

David — Tue, 11 Feb 2003 13:14:23 -0800

by: David

Description: Function: Primary mission: Strategic and tactical missile launch detection. Description: Air Force Space Command-operated Defense Support Program (DSP) satellites are a key part of North America's early warning systems. In their 22,000 miles-plus geosynchronous orbits, DSP satellites help protect the United States and its allies by detecting missile launches, space launches and nuclear detonations. DSP satellites use an infrared sensor to detect heat from missile and booster plumes against the earth's background. In 1995, a new means of processing DSP data called Attack and Launch Early Reporting to Theater (ALERT) was brought on line. This capability provides improved warning of attack by short-range missiles against U.S. and allied forces overseas. Numerous improvement projects have enabled DSP to provide accurate, reliable data in the face of evolving missile threats. On-station sensor reliability has provided uninterrupted service well past their design lifetime. Recent technological improvements include enhanced sensor resolution, increased on-board signal-processing capability to improve clutter rejection, and enhanced reliability and survivability improvements. In the 21st century, the Space-Based Infrared System (SBIRS) will replace DSP. The 21st Space Wing, located at Peterson Air Force Base, Colo., has units that operate DSP satellites and report warning information, via communications links, to the North American Aerospace Defense Command and U.S. Space Command early warning centers within Cheyenne Mountain, located near Colorado Springs, Colo. These centers immediately forward data to various agencies and areas of operations around the world. The 50th Space Wing at Schriever AFB, Colo., provides command and control support for the satellites. The Defense Support Program is managed by Space and Missile Systems Center (Air Force Materiel Command), Space Based Infrared System Program office at Los Angeles AFB, Calif. The office is responsible for development and acquisition of the satellites. Typically, DSP satellites are launched into geosynchronous orbit on a Titan IV booster and inertial upper stage combination. However, one DSP satellite was launched using the space shuttle on mission STS-44 (Nov. 24, 1991). History: The program came to life with the first launch of a DSP satellite in the early 1970s. Since that time, DSP satellites have provided an uninterrupted early warning capability. The original DSP weighed 2,000 pounds and had 400 watts of power, 2,000 detectors and a design life of 1.25 years. In the 1970s, the satellite was upgraded to meet new mission requirements. As a result, the weight grew to 5,250 pounds, the power to 1,275 watts, the number of detectors increased by threefold to 6,000 and the design life was three years with a goal of five years. DSP's effectiveness was proven during Desert Storm, when DSP detected the launch of Iraqi Scud missiles and provided warning to civilian populations and coalition forces in Israel and Saudi Arabia. ?General Characteristics, Defense Support Program Satellites Contractor Team: Thompson Ramo Woolridge (TRW) and Aerojet Electronics Systems Power Plant: Solar arrays generate 1,485 watts Weight: 5,250 pounds (2,386 kilograms) Height: 32.8 feet (10 meters) on orbit 28 feet (8.5 meters) at launch Diameter: 22 feet (6.7 meters) on orbit 13.7 feet (4.2 meters) at launch Design Life: Block II/IIA: 7.5 years Block IIR: 10 years Orbit Altitude: 22,000 miles (35,200 kilometers) Date Deployed: 1970 Latest Satellite Block: Sat 23 Inventory: Classified Unit Replacement Cost: $400 million

NAVSTAR Global Positionin

David — Tue, 11 Feb 2003 13:14:23 -0800

by: David

Description: Function: Precise navigation, timing and velocity information worldwide. Description: The Navstar Global Positioning System (GPS) is a space-based constellation of orbiting satellites that provides navigation data to military and civilian users all over the world. The system is operated and controlled by the 50th Space Wing, located at Schriever Air Force Base, CO. The GPS constellation is designed and operated as a 24-satellite system, consisting of six planes, with a minimum of four satellites per plane. GPS satellites orbit the earth every 12 hours, emitting continuous navigation signals. With the proper equipment, users can receive these signals to calculate time, location and velocity. The signals are so accurate, time can be figured to within a millionth of a second, velocity within a fraction of a mile per hour and location to within 100 feet. Receivers have been developed for use in aircraft, ships and land vehicles, as well as for hand carrying. GPS provides 24-hour navigation services including: - Extremely accurate, three-dimensional location information (latitude, longitude and altitude), velocity and precise time - A worldwide common grid that is easily converted to any local grid - Passive all-weather operations - Continuous real-time information - Support to an unlimited number of users and areas - Support to civilian users at a slightly less accurate level The Delta II expendable launch vehicle is used to launch GPS satellites from Cape Canaveral Air Station, Fla., into nearly 11,000-mile circular orbits. While circling the earth, the systems transmit signals on two different L-band frequencies. Their design life is 7.5 years. Background: The GPS master control station, operated by the 50th Space Wing's 2nd Space Operations Squadron at Schriever AFB, Colo., is responsible for monitoring and controlling the GPS satellite constellation. The GPS-dedicated ground system consists of five monitor stations and four ground antennas located around the world. The monitor stations use GPS receivers to passively track the navigation signals on all satellites. Information from the monitor stations is then processed at the master control station and used to update the satellites' navigation messages. The master control station crew sends updated navigation information to GPS satellites through ground antennas using an S-band signal. The ground antennas are also used to transmit commands to satellites and to receive state-of-health data (telemetry). GPS capabilities were put to the test during the U.S. involvement in operations Desert Shield and Desert Storm. Allied troops relied heavily on GPS to navigate the featureless Saudi Arabian desert. Forward air controllers, pilots, tank drivers and even cooks used the system successfully. Air Force Materiel Command's Space and Missile Systems Center at Los Angeles AFB, Calif., acts as the executive agent for the Department of Defense in acquiring GPS satellites and user equipment. Activities within the DOD are well under way to equip all U.S. military forces with GPS receivers by the year 2000. General Characteristics, NAVSTAR Global Positioning System Primary Contractor: Block I and II/IIA, Rockwell International (Boeing North American); Block IIR, Lockheed Martin; Block IIF, Boeing North American Power Plant: Solar panels generating 800 watts Weight: Block IIA: 3,670 pounds (1,816 kilograms) Block IIR: 4,480 pounds (2,217 kilograms Height: Block IIA: 136 inches (3.4 meters) Block IIR: 70 inches (1.7 meters) Width (Includes Wingspan): Block IIA: 208.6 inches (5.3 meters) Block IIR: 449 inches (11.4 meters) Design Life: Block II/IIA: 7.5 years Block IIR: 10 years Date of First Launch: 1978 Launch Vehicle: Delta II Date Constellation Operational: July 1995 (at full operational capacity) Inventory: Block II/IIA: 27 fully operational satellites Contract for 21 Block IIR and 6 Block IIF satellites Unit Replacement Cost: $800 million