David
Thu January 16, 2003 10:14am
|
AH-1W Super Cobra
Function: Fire support and security for forward and rear area forces, point target/anti-armor, anti-helicopter, armed escort, supporting arms control and coordination, point and limited area air defense from enemy fixed-wing aircraft, armed and visual reconnaissance.
History: The Marine Corps deployed four of six active force squadrons (48 AH-1Ws) to Southwest Asia during Operation Desert Shield/Desert Storm. These helicopters destroyed 97 tanks, 104 armored personnel carriers and vehicles, 16 bunkers and two antiaircraft artillery sites without the loss of any aircraft. The deployment required no additional augmentation to squadron support personnel and only one Bell Helicopter technical representative.
Description: The AH-1W Super Cobra is a day/night marginal weather Marine Corps attack helicopter that provides enroute escort for our assault helicopters and their embarked forces. The AH-1W is a two-place, tandem-seat, twin-engine helicopter capable of land- or sea-based operations. The AH-1W provides fire support and fire support coordination to the landing force during amphibious assaults and subsequent operations ashore. The AH-1W is operated in eight composite HMLA squadrons composed of 18 AH-1 and 9 UH-1 aircraft. The AH-1W is curretnly being outfitted with a Night Targeting System/Forward Looking Infrared Radar that provides laser rangefinding/designating and camera capabilities.
?General Characteristics, AH-1W Super Cobra
Manufacturer:
Bell Helicopter Textron
Unit Cost:
$10.7 million
Power Plant:
Two General Electric T700-GE-401 engines
Thrust:
Full: 2082 shaft horsepower for 30 minutes (transmission limited)
Continuous: 1775 shaft horsepower
Length:
58 feet (17.67 meters)
Height:
13.7 feet (4.17 meters)
Rotor Diameter:
48 feet (14.62 meters)
Maximum Take-off Weight:
14,750 pounds (6,696.50 kilograms)
Maximum Speed:
180 knots
Ceiling:
18,700 feet (5703.5 meters) in basic combat attack configuration (limited to 10,000 feet (3050 kilometers) by oxygen requirements)
Range:
256 nautical miles (294.4 miles) in basic combat attack configuration
Crew:
Two officers
Armament:
One 20MM turreted cannon with 750 rounds
Four external wing stations that can fire 2.75"/5.0" rockets and a wide variety of precision guided missiles, including TOW/Hellfire (point target/anti-armor), Sidewinder (anti-air), Sidearm (anti-radar)
Introduction Date:
1986
|
|
David
Thu January 16, 2003 10:39am
|
CH-47 Chinook
Function: Fire support and security for forward and rear area forces, point target/anti-armor, anti-helicopter, armed escort, supporting arms control and coordination, point and limited area air defense from enemy fixed-wing aircraft, armed and visual reconnaissance.
History: Development of the medium lift Boeing Vertol (models 114 and 414) CH-47 Series Chinook began in 1956. Since then the effectiveness of the Chinook has been continually upgraded by successive product improvements, the CH-47A, CH-47B, CH-47C, and CH-47D. The amount of load a cargo helicopter can carry depends on the model, the fuel on board, the distance to be flown, and atmospheric conditions.
The CH-47B was introduced by Boeing after a production run of over 350 CH-47A?s . The B model introduced the Lycoming T55-L7C engine, a beefed up airframe. Nonsymmetrical rotor blades, and the blunted aft pylon for better stability. Boeing began delivering the CH-47B in May of 1967 and eventually produced a total of 108 B models before production shifted to the CH-47C.
During Desert Storm the CH-47D was often the only mode of transportation to shift large numbers of personnel, equipment, and supplies rapidly over the vast area in which US forces operated. The cargo capacity and speed provided commanders and logisticians a capability unequalled by any Army in the world." (Army Aviation in Operation Desert Storm, 1991) During the ground phase, the flanking maneuver executed by the XVIII Airborne Corps was planned with the CH-47D as the keystone. Forward Operating Base Cobra was deliberately positioned to accommodate the combat radius of a fully loaded CH-47D. Cobra was initially secured by an air assault of the 101st's 2nd Infantry Brigade. This air assault, consisting of 5000 soldiers, was accomplished by a total of 126 Blackhawks and 60 Chinooks. By the end of the first day the CH-47Ds had lifted 131,000 gallons of fuel along with pallets of combat-configured ammunition for the next day's fight. Forty separate refueling and rearming points were active in FOB Cobra in less than two hours.
During peacekeeping operations in Bosnia, a Chinook company (A company, 5th Battalion, 159th Aviation Regiment) of 16 aircraft flew 2,222 hours, carried 3,348 passengers, and transported over 3.2 million pounds of cargo over a six month period. These numbers equate to carrying 112 infantry platoons, 545 HMMWVs, or 201 M198 Howitzers. The most publicized mission was assisting the 502d Engineer Company build a float bridge across the flooded Sava River allowing the 1st Armored Division to cross into Bosnia. On 29 and 30 December 1995, Big Windy lifted bridge bays and dropped them into the Sava River so the engineers could quickly assemble the bridge. When the Sava River flood washed away the engineer's tentage and personal equipment, Big Windy quickly resupplied the engineers so they could continue their vital mission. Additionally, a key early mission in support of NATO was the recovery of Admiral Smith's aircraft. The Blackhawk had performed a precautionary landing for what was later found to be a transmission seizure. A CH-47D sling-loaded the Blackhawk back to the Intermediate Staging Base (ISB). Big Windy began redeploying to Giebelstadt on 14 June 1996. One platoon of six CH-47Ds remained in Hungary throughout 1997.
Description: The CH-47 is a twin-engine, tandem rotor helicopter designed for transportation of cargo, troops, and weapons during day, night, visual, and instrument conditions. The aircraft fuselage is approximately 50 feet long. With a 60-foot rotor span, on each rotor system, the effective length of a CH-47 (with blades turning) is approximately 100 feet from the most forward point of the forward rotor to the most rearward point on the aft rotor. Maximum airspeed is 170 knots with a normal cruise speed of 130 knots. However, speed for any mission will vary greatly depending on load configuration (internal or external), time of day, or weather conditions. The minimum crew for tactical operations is four, two pilots, one flight engineer, and one crew chief. For more complex missions, such as NVG operations and air assaults, commanders may consider using five crew members and add one additional crew chief.
The CH-47A, first delivered for use in Vietnam in 1962, is a tandem-rotor medium transport helicopter. The Chinook's primary mission is moving artillery, ammunition, personnel, amd supplies on the battlefield. It also performs rescue, aeromedical, parachuting, aircraft recovery and special operations missions. On June 25, 1958 the Army issued an invitation for a General Management Proposal for the US Army Medium Transport Helicopter. Five aircraft selected Vertol to produce the YCH-1B as the Army?s new medium transport helicopter. In July 1962 DoD redesignated all U.S. military aircraft and the HC-1B was redesignated the as the CH-47A. Early production CH-47A?s operated with the 11th Air Assault Division during 1963 and in October of that year the aircraft was formally designated as the Army?s standard medium transport helicopter. In June 1965 the 11th Air Assault Division was redesignated as the 1st Cavalry Division (Airmobile) and readied for deployment to Viet Nam. Chinooks from the 11th Air Assault formed the nucleus of the 228th Assault Helicopter Battalion which began operations in Viet Nam in September, 1965. CH-47A?s deployed to Viet Nam were equipped with Lycoming T55-L7 engines generating 2650 shp. The aircraft had a maximum gross weight of 33,000 pounds allowing for a maximum payload of approximately 10,000 pounds. The hot mountainous conditions of Viet Nam limited the A models performance capabilities and generated a requirement for increased payload and better performance.
The CH-47C Chinook model has a maximum cargo hook capacity of 20,000 pounds. The CH-47C has only a single cargo hook below the center of the aircraft. When hooking a single load, soldiers use the main hook. They must coordinate closely with the aircrew as to which hooks to use when carrying multiple loads. The planning figure for the fore and aft hooks is 10,000 pounds each. The Army?s continued need for further performance improvements lead to the development of the CH-47C. Designed to meet an Army requirement to transport a 15,000 pound sling load over a 30 mile radius, the C model boasted an increased gross weight to 46,000 pounds, increased fuel capacity, the Lycoming T55-L11 engine developing 3750 shp, and addition structural improvements. The first C model flew in late 1967 and became the mainstay of the Chinook fleet until the advent of the CH-47D. Production of the C model continued until 1980 with improvements such as the crash worthy fuel system and fiberglass rotor blades being incorporated into the fleet.
The CH-47D was the result of June 1976 contract for a modernized Chinook. The Army recognized that that the Chinook fleet was rapidly reaching the end of its useful life and signed a contract with Boeing to significantly improve and update the CH-47. Three airframes, CH-47A, CH-47B, and a CH-47C, were stripped down to their basic airframes and then rebuilt with improved systems to provide three CH-47D prototypes. Improvements included upgraded power plants, rotor transmissions, integral lubrication and cooling for the transmission systems, and fiberglass rotor blades. Other improvements included a redesigned cockpit to reduce pilot workload, redundant and improved electrical systems, modularized hydraulic systems, an advanced flight control system, and improved avionics. The Chinook has two tandem three-bladed counter-rotating fiberglass rotors. The CH-47D is powered by two Allied Signal Engines T55-L-712 3750 shp turboshaft engines and has a maximun speed of 163 mph (142 knots). The CH-47D was rolled-out in March 1979. The CH-47D carrys twice the load of a CH-47A and has improved performance. The CH-47D can operate at night and in nearly all weather conditions. The CH-47D is equipped with an air-to-air refueling probe. The Chinook can accommodate a wide variety of internal payloads, including vehicles, artillery pieces, 33 to 44 troops, or 24 litters plus two medical attendants. The Chinook can be equipped with two door mounting M60D 7.62mm machine guns on the M24 armament subsystem and a ramp mounting M60D using the M41 armament subsystem. The "D" model can carry up to 26,000 pounds externally. The CH-47D has three cargo hooks: a center (main) hook and two additional hooks fore and aft of the main hook.
The Fatcow is a CH-47 with the Extended Range Fuel System [ERFS] II system located in the cargo bay. The configuration consists of three or four fuel tanks attached to a refueling system. The system contains 2400 gallons of JP4/8 excluding the CH-47 internal fuel load of 1050 gals. The Fatcow can set up a 1,2,3,or 4 point system using HTARS. The fuel cells must be crash-worthy and self sealing up to 50 caliber hits.
The Improved Cargo Helicopter (ICH) is a remanufactured version of the CH-47D Chinook cargo helicopter with the new T55-GA-714A engines. The ICH program is intended to restore CH-47D airframes to their original condition and extend the aircraft's life expectancy another 20 years (total life of 60 years) until the 2025-2030 timeframe. The program will remanufacture CH-47 aircraft, reduce the aircraft's vibration, thereby reducing Operations and Support costs, and allow the aircraft to operate on the digitized battlefield by incorporating a 1553 data bus. The ICH will also acquire the capability to carry 16,000 pounds of external/internal cargo for a 50 NM combat radius at 4000 feet pressure altitude and 95 degrees fahrenheit. In addition, the following improvements will be incorporated into the aircraft:
- Fuselage stiffening and possible active systems for vibration reduction (this is expected to lead to improved reliability and therefore reduced operating and support costs)
- Integrated cockpit
- Digital architecture for Force XXI compatibility
Additional improvements may be incorporated into the aircraft if funding permits. The ICH will transport weapons, ammunition, equipment, troops, and other cargo in general support of combat units and operations other than war. The ICH is a dominant maneuver platform that provides focused logistics to the force. The ICH program was built as a "bare bones" program to satisfy the battlefield requirements of operations on the 21st century digital battlefield by replacing the existing 1970s technology cockpit with a new cockpit.
The 101st Air Assault Division is scheduled to receive the first ICH in FY03. The First Unit Equipped (FUE) date to the 101st, a company of sixteen aircraft, is FY04. The 101st, 18th Airborne Corps, Korea, and USAREUR will complete fielding through FY09. ICH completes the fielding of 300 aircraft in 2015. Only 300 of the 431 CH-47Ds convert to ICHs based on the fielding of JTR. As the Army fields JTR to Force Package One units, the ICH aircraft will cascade to units that retained CH-47Ds. Those CH-47Ds would retire.
Separate programmatically from the ICH program, the 714 engine program is an Engineering Change Proposal (ECP) to convert the present T-55-712 engines to a T-55-714 engine. This buys back performance on high/hot days lost over time by the addition of weight through modification work order enhancements. Specifically, it will provide an increased lift capability allowing the CH-47 to transport 16,000 pounds for an unrefueled combat radius of 50 nautical miles at 4,000 feet PA and 95 degrees F. The ICH Operational Requirements Document (ORD) requires the CH-47F(ICH) to carry 16,000lbs at 4000ft/95? for a 50nm combat radius (50nm with load, return empty). The CH-47D -714A engine program achieves this requirement. The -714A engine program converts current CH-47D -712 engines to -714A engines. The engine program converts the engines on all 431 CH-47D aircraft. The -714A engine begins fielding in FY99 and, because of recent budget cuts, completes in FY09. 160th (Hunter), 101st, 18th AB Corps, Korea, and Germany are scheduled to be fielded through FY05. The -714A budget constantly fluctuates because of plus-ups and decrements. For this reason, the fielding dates may change.
The MH-47E Special Operations Aircraft (SOA) is a derivative of the Boeing CH-47 Chinook. Included with other modifications is a significantly increased fuel capacity with modified main and auxiliary fuel tanks. The aircraft has modified integrated avionics suites and multi-mode radars and is intended to provide adverse-weather infiltration/exfiltration and support to US Military Forces, country teams, other agencies and special activities. The CH-47D Chinook has been specially modified to perform the special operations mission and has been tested in combat. The three versions of the CH-47 in the Army inventory are the CH-47D, the MH-47D, and the MH-47E. The MH-47D and the MH-47E are air refuelable. It provides long-range penetration, medium assault helicopter support to special operations forces. Depending on the version, it can be ferried 1,100 to 2,000 nautical miles unrefueled. During Operation Just Cause, CH-47s conducted H-hour assaults to support other elements who were air-landing SOF to disrupt enemy responses and seize key facilities. During Operation Desert Storm, the CH-47 conducted infiltration and exfiltration of SOF and CSAR of downed pilots. MH-47E testing was limited to the major change to the aircraft which affects vulnerability. In the case of the MH-47E, this was the addition of an 800 gallon Robertson Auxiliary Fuel Tank in the cabin and Boeing designed sponson tanks with expanded capacity and honeycomb shell construction. Analyses conducted during the test planning phase revealed that the largest potential vulnerability was associated with projectiles entering the fuel tanks in the volume above the liquid fuel. Such impacts could ignite the fuel vapors and cause explosions and/or fires with serious consequences. During test planning, USSOCOM decided to add an inerting system to the fuel tanks to avoid such fires/explosions. This will be a lead-the-fleet system that will be available for similar helicopter variants in other fleets as well.
General Characteristics, CH-47 Chinook
Manufacturer:
Boeing Company
Power Plant:
Two Textron Lycoming T55-L712 engines
Length:
99 feet (30.18 meters), including rotor lengths
Height:
19 feet (5.79 meters)
Rotor Diameter:
60 feet (18.29 meters)
Weight:
Empty: 10,578 kilograms
Maximum: 24,494 kilograms
Useful load: 13,916 kilograms
Forward and aft cargo hooks: 9,072 kilograms
Centre cargo hook 12,701 kilograms
Speed:
Sea level cruise speed: 265 kmh
Speed at maximum continuous power: 269 kmh
Ceiling:
8,448 feet (2,575 meters)
Range:
230 nautical miles
Crew:
Two
Sensors:
Raytheon AN/APQ-174A for terrain following flight, air-to-ground ranging and ground mapping
Raytheon AN/AAQ-16 forward looking infrared (FLIR)
Introduction Date:
1963
|
|
David
Thu January 16, 2003 10:39am
|
HH-60H Seahawk
Function: Twin-engine, medium lift, Combat Search and Rescue and Special Operations Support helicopter.
Description: The HH-60H Seahawk is a twin-engine helicopter used by the Navy in a CSAR/SOS role. Based on the SH-60 airframe (The Naval variant of the basic S-60 Blackhawk utility helicopter) the HH-60H has been optimized for low level insertions and extractions, self defense, enemy small arms fire suppression, and bulk cargo and troop transport. The H variant is also equipped with an externally mounted hoist and is configured for low level night operations with Night Vision Goggle (NVG) compatible instruments and anti-collision aircraft running lights. The HH-60H is capable of transporting a 6,000 pound load externally, and it's gross carrying capacity is rated at 7,400 pounds.
General Characteristics, HH-60H Seahawk
Contractors:
Sikorsky Aircraft Corporation (airframe); General Electric Company (engines); IBM Corporation (avionics components)
Power Plant:
Two General Electric T700-GE-401C engines producing 1,700 shaft horse power each
Length:
64 feet 10 inches (19.6 meters)
Height:
17 feet 2 inches (5.1 meters)
Rotor Diameter:
17 feet 2 inches (5.1 meters)
Maximum Takeoff Weight:
21,884 pounds (9,927 kilograms)
Speed:
180 knots maximum
Ceiling:
14,700 feet (4,410 meters)
Range:
380 nautical miles (600 km) maximum
Crew:
Four plus up to eight passengers
Navigation Sensors:
VHF/UHF DF
TACAN
TACNAV
Doppler Radar
Radar Altimeter
GPS (Provisions)
Forward Looking Infra Red (FLIR) system
Armament:
Variable, but may include any combination of the following:
GCAL-50 machine gun
GAU-17A 7.62mm minigun
2.75" Hydra 70 Folding Fin Aerial Rocket pods
FIM-92A Stinger Surface to Air Missiles
AGM-65 Maverick Air to Ground Missiles
AGM-114 Hellfire Air to Ground Missiles
Countermeasures:
Infrared (IR) Jamming System
Chaff and Flare Dispensers (2)
Radar Warning Receiver
Hover IR Suppressor System
|
|
David
Thu January 16, 2003 10:39am
|
HH/MH-60G Pave Hawk
Function: Twin-engine, medium lift, Combat Search and Rescue and Special Operations Support helicopter.
Description: The HH/MH-60G Pave Hawk is a twin-engine helicopter used by the Airforce in a CSAR/SOS role. Based on the basic S-60 Blackhawk utility helicopter airframe, the Pave Hawk has been optimized for low level insertions and extractions, self defense, enemy small arms fire suppression, and bulk cargo and troop transport. To extend their range, Pave Hawks are equipped with a retractable in-flight refueling probe and internal auxiliary fuel tanks. The HH/MH-60G variant is also equipped with an externally mounted 600 pound capacity hoist and sliding doors on each side of the troop and cargo compartment to allow rapid loading and unloading. The HH/MH-60G is capable of transporting a 8,000 pound load externally and can be equipped with the external stores support system.
General Characteristics, HH/MH-60G Pave Hawk
Contractors:
United Technologies/Sikorsky Aircraft Company
Power Plant:
Two General Electric T700-GE-700 or T700-GE-701C engines producing 1,560-1,630 shaft horsepower
Length:
64 feet, 8 inches (17.1 meters)
Height:
16 feet, 8 inches (4.4 meters)
Rotor Diameter:
53 feet 8 inches (16.4 meters)
Maximum Take-off Weight:
22,000 pounds (9,900 kilograms)
Speed:
180 knots maximum
Range:
504 nautical miles (unlimited with air refueling)
Crew:
Two pilots, one flight engineer, one gunner and up to 10 troops
Navigation Sensors:
VHF/UHF DF
TACAN
TACNAV
Doppler Radar
Radar Altimeter
GPS (Provisions)
Forward Looking Infra Red (FLIR) system
Armament:
Variable, but may include any combination of the following:
Two GCAL-50 machine guns
Two GAU-17A 7.62mm miniguns
2.75" Hydra 70 Folding Fin Aerial Rocket pods
FIM-92A Stinger Surface to Air Missiles
AGM-65 Maverick Air to Ground Missiles
AGM-114 Hellfire Air to Ground Missiles
Countermeasures:
Infrared (IR) Jamming System
Chaff and Flare Dispensers (2)
Radar Warning Receiver
Hover IR Suppressor System
|
|
David
Thu January 16, 2003 10:39am
|
MH-53J Pave Low IIIE
Function: Low-level, long-range, all weather Combat Search and Rescue, Special Operations Support, and heavy equipment transport.
Description: The MH-53J Pave Low IIIE heavy-lift helicopter is the largest, most technologically advanced, and most powerful helicopter in the Airforce. Based on the basic Vietnam era HH-53 Super Jolly Green Giant airframe, the Pave Low IIIE has been optimized for low level insertions and extractions, self defense, enemy small arms fire suppression, and bulk cargo and troop transport. The 53J's terrain-following and terrain-avoidance radar, forward-looking infrared sensor, inertial navigation system with global positioning system, along with a projected map display enable the crew to follow terrain contours and avoid obstacles, making low-level penetration possible. Additionally, the MH-53J is equipped with a aerial refueling probe and is capable of lifting 20,000 pounds of cargo using its external cargo hook.
General Characteristics, MH-53J Pave Low IIIE
Contractor:
Sikorsky Aircraft Company
Power Plant:
Two General Electric T64-GE/-100 engines producing 4,330 shaft horsepower per engine
Length:
92 feet (28 meters)
Height:
25 feet (7.6 meters)
Rotor Diameter:
72 feet (21.9 meters)
Maximum Take-off Weight:
46,000 pounds
Speed:
165 mph (at sea level)
Range:
600 nautical miles (unlimited with air refueling)
Crew:
Two pilots, two flight engineers, two gunners, and up to 38 troops
Navigation Sensors:
VHF/UHF DF
TACAN
TACNAV
Doppler Radar
Radar Altimeter
GPS (Provisions)
Forward Looking Infra Red (FLIR) system
Armament:
Any combination of three GCAL-50 machine guns or GAU-2B/A 7.62mm miniguns
Countermeasures:
Infrared (IR) Jamming System
Chaff and Flare Dispensers (2)
Radar Warning Receiver
Date Deployed:
1981
|
|
David
Thu January 16, 2003 5:31pm
|
MC-130E/H Combat
Function: The MC-130E Combat Talon I and MC-130H Combat Talon II provide global, day, night and adverse weather capability to infiltrate, resupply and exfiltrate U.S. and allied special operations forces.
History: The MC-130E flew combat missions during the war in Southeast Asia and took part in the attempted rescue of Americans held at the Son Tay prisoner of war camp in 1970. In 1983, MC-130E's participated in Operation Urgent Fury to rescue Americans from the island nation of Grenada. One of the Combat Talon crews earned the Mackay Trophy for the most meritorious flight of the year by delivering Army Rangers to Point Salines Airfield amidst a barrage of anti-aircraft fire. In 1989, the MC-130E participated in Operation Just Cause in Panama, helping to seize the airfield at Rio Hato. During Desert Storm the MC-130E's primary role was psychological operations as it airdropped 11 BLU-82/B general purpose bombs and flew multiple missions air dropping and dispersing leaflets. Its secondary role was combat search and rescue.
In 1994, the MC-130E deployed to Haiti with other Air Force Special Operations Command aircraft during operations Restore Democracy and Uphold Democracy.
The MC-130H evacuated Americans from the U.S. Embassy in Liberia in 1996. In 1997, the MC-130H participated in Operation Guardian Retrieval, helping to evacuate Americans from the U.S. Embassy in Zaire. Later that year the MC-130H was part of the special operations forces called on for possible support in Cambodia.
The Talon I provided combat search and rescue and special operations forces support for Operation Southern Watch in Iraq in 1997. In September 1997, the MC-130H participated in the search for a C-141 that collided with another aircraft off the coast of Angola. The aircraft also evacuated noncombatant Americans from the Republic of the Congo in 1997. The mission earned the aircrew the Mackay Trophy.
In 1998, the MC-130s returned to Saudi Arabia during the buildup of U.S. forces to convince Iraq to comply with U.N. weapons inspections.
Description: Both aircraft are equipped with in-flight refueling equipment, terrain-following and terrain-avoidance radar, an inertial and global positioning satellite navigation system, and a high-speed aerial delivery system. The special navigation and aerial delivery systems are used to locate small drop zones and deliver people or equipment with greater accuracy and higher speeds than possible with a standard C-130. The aircraft also can penetrate hostile airspace at low altitudes, and crews are specially trained in night and adverse weather operations.
Combat Talons feature highly automated controls and displays to reduce crew size and workload. The cockpit and cargo areas are compatible with night vision goggles. The integrated control and display subsystem combines basic aircraft flight, tactical and mission sensor data into a comprehensive set of display formats that assist each operator in performing tasks efficiently.
On the MC-130H, the pilot and co-pilot displays on the cockpit instrument panel and the navigator/electronic warfare operator console -- on the aft portion of the flight deck -- each have two video displays and a data-entry keyboard. The electronic warfare operator also has a data-entry keyboard and two video displays, one of which is dedicated to electronic warfare data.
The primary pilot and co-pilot display formats include basic flight instrumentation and situational data. The display formats are available with symbology alone or with symbology overlaid with sensor video.
The navigator uses radar ground map displays, forward-looking infrared displays, tabular mission management displays and equipment status information. The electronic warfare operator's displays are used for viewing electronic warfare data and to supplement the navigators in certain critical phases.
General Characteristics, MC-130E/H Combat Talon I/II
Builder:
Lockheed
Contractor:
Lockheed Martin Federal Systems (MC-130H)
Unit Cost:
MC-130E, $45.2 million
MC-130H, $78 million (fiscal 1998 constant dollars)
Power Plant:
Four Allison T56-A-15 turboprop engines
Thrust:
4,910 shaft horsepower each engine
Length:
MC-130E: 100 feet, 10 inches (30.7 meters)
MC-130H: 99 feet, 9 inches (30.4 meters)
Height:
38 feet, 6 inches (11.7 meters)
Wingspan:
132 feet, 7 inches (40.4 meters)
Speed:
300 mph
Load:
MC-130E: 53 troops, 26 paratroopers
MC-130H: 75 troops, 52 paratroopers
Ceiling:
33,000 feet (10,000 meters)
Maximum Take-off Weight:
155,000 pounds (69,750 kilograms)
Range:
2,700 nautical miles (unlimited with air refueling)
Crew:
MC-130E: Officers - two pilots, two navigators and an electronic warfare officer; enlisted - flight engineer, two loadmasters and communications specialist
MC-130H: Officers - two pilots, a navigator and electronic warfare officer; enlisted - flight engineer and two loadmasters
Inventory:
Active force (MC-130H), 23
Reserve (MC-130E), 14
ANG, 0
Dates Deployed:
MC-130E, 1966
MC-130H, June 1991
|
|
David
Thu January 16, 2003 6:05pm
|
F-15 Eagle
Function: The F-15 Eagle is an all-weather, extremely maneuverable, tactical fighter designed to permit the Air Force to gain and maintain air superiority in aerial combat.
History: The first F-15A flight was made in July 1972, and the first flight of the two-seat F-15B (formerly TF-15A) trainer was made in July 1973. The first Eagle (F-15B) was delivered in November 1974. In January 1976, the first Eagle destined for a combat squadron was delivered.
The single-seat F-15C and two-seat F-15D models entered the Air Force inventory beginning in 1979. These new models have Production Eagle Package (PEP 2000) improvements, including 2,000 pounds (900 kilograms) of additional internal fuel, provision for carrying exterior conformal fuel tanks and increased maximum takeoff weight of up to 68,000 pounds (30,600 kilograms).
The F-15 Multistage Improvement Program was initiated in February 1983, with the first production MSIP F-15C produced in 1985. Improvements included an upgraded central computer; a Programmable Armament Control Set, allowing for advanced versions of the AIM-7, AIM-9, and AIM-120A missiles; and an expanded Tactical Electronic Warfare System that provides improvements to the ALR-56C radar warning receiver and ALQ-135 countermeasure set. The final 43 included a Hughes APG-70 radar.
F-15C, D and E models were deployed to the Persian Gulf in 1991 in support of Operation Desert Storm where they proved their superior combat capability with a confirmed 26:0 kill ratio. F-15 fighters accounted for 36 of the 39 Air Force air-to-air victories. F-15Es were operated mainly at night, hunting SCUD missile launchers and artillery sites using the LANTIRN system.
They have since been deployed to support Operation Southern Watch, the patrolling of the UN-sanctioned no-fly zone in Southern Iraq; Operation Provide Comfort in Turkey; in support of NATO operations in Bosnia, and recent air expeditionary force deployments.
Description: The Eagle's air superiority is achieved through a mixture of unprecedented maneuverability and acceleration, range, weapons and avionics. It can penetrate enemy defense and outperform and outfight any current enemy aircraft. The F-15 has electronic systems and weaponry to detect, acquire, track and attack enemy aircraft while operating in friendly or enemy-controlled airspace. The weapons and flight control systems are designed so one person can safely and effectively perform air-to-air combat.
The F-15's superior maneuverability and acceleration are achieved through high engine thrust-to-weight ratio and low wing loading. Low wing-loading (the ratio of aircraft weight to its wing area) is a vital factor in maneuverability and, combined with the high thrust-to-weight ratio, enables the aircraft to turn tightly without losing airspeed.
A multimission avionics system sets the F-15 apart from other fighter aircraft. It includes a head-up display, advanced radar, inertial navigation system, flight instruments, ultrahigh frequency communications, tactical navigation system and instrument landing system. It also has an internally mounted, tactical electronic-warfare system, "identification friend or foe" system, electronic countermeasures set and a central digital computer.
The head-up display projects on the windscreen all essential flight information gathered by the integrated avionics system. This display, visible in any light condition, provides the pilot information necessary to track and destroy an enemy aircraft without having to look down at cockpit instruments.
The F-15's versatile pulse-Doppler radar system can look up at high-flying targets and down at low-flying targets without being confused by ground clutter. It can detect and track aircraft and small high-speed targets at distances beyond visual range down to close range, and at altitudes down to treetop level. The radar feeds target information into the central computer for effective weapons delivery. For close-in dogfights, the radar automatically acquires enemy aircraft, and this information is projected on the head-up display. The F-15's electronic warfare system provides both threat warning and automatic countermeasures against selected threats.
A variety of air-to-air weaponry can be carried by the F-15. An automated weapon system enables the pilot to perform aerial combat safely and effectively, using the head-up display and the avionics and weapons controls located on the engine throttles or control stick. When the pilot changes from one weapon system to another, visual guidance for the required weapon automatically appears on the head-up display.
The Eagle can be armed with combinations of four different air-to-air weapons: AIM-7F/M Sparrow missiles or AIM-120 advanced medium range air-to-air missiles on its lower fuselage corners, AIM-9L/M Sidewinder or AIM-120 missiles on two pylons under the wings, and an internal 20mm Gatling gun in the right wing root.
Low-drag, conformal fuel tanks were especially developed for the F-15C and D models. Conformal fuel tanks can be attached to the sides of the engine air intake trunks under each wing and are designed to the same load factors and airspeed limits as the basic aircraft. Each conformal fuel tank contains about 114 cubic feet of usable space. These tanks reduce the need for in-flight refueling on global missions and increase time in the combat area. All external stations for munitions remain available with the tanks in use. AIM-7F/M Sparrow missiles, moreover, can be attached to the corners of the conformal fuel tanks.
The F-15E is a two-seat, dual-role, totally integrated fighter for all-weather, air-to-air and deep interdiction missions. The rear cockpit is upgraded to include four multi-purpose CRT displays for aircraft systems and weapons management. The digital, triple-redundant Lear Siegler flight control system permits coupled automatic terrain following, enhanced by a ring-laser gyro inertial navigation system.
For low-altitude, high-speed penetration and precision attack on tactical targets at night or in adverse weather, the F-15E carries a high-resolution APG-70 radar and low-altitude navigation and targeting infrared for night pods.
?General Characteristics, F-15 Eagle
Contractor:
McDonnell Douglas Corporation
Unit Cost:
$15 million
Power Plant:
Two Pratt & Whitney F100-PW-220 or 229 turbofan engines with afterburners
Thrust:
(C/D models) 23,450 pounds each engine
Length:
63.8 feet (19.44 meters)
Height:
18.5 feet (5.6 meters)
Wingspan:
42.8 feet (13 meters)
Maximum Take-Off Weight:
C/D models: 68,000 pounds (30,844 kilograms)
Speed:
Mach 2+
Range:
3,450 miles (3,000 nautical miles) ferry range with conformal fuel tanks and three external fuel tanks
Ceiling:
65,000 feet (19,812 meters)
Crew:
F-15A/C: one
F-15B/D/E: two
Armament:
One internally mounted M-61A1 20mm 20-mm, six-barrel cannon with 940 rounds of ammunition
Four AIM-9L/M Sidewinder and four AIM-7F/M Sparrow air-to-air missiles, or eight AIM-120 AMRAAMs, carried externally
Inventory:
Active force, 423
Reserve, 0
ANG, 45
Date Deployed:
July 1972
|
|
David
Thu January 16, 2003 6:24pm
|
T-34C Turbo Mentor
Function: High performance propeller driven trainer.
Description: Developed in the 1950's as a primary trainer for both the United States Navy and Air Force, the T-34 is used to instruct student pilots in basic flying skills. The original aircraft was designated as the T-34B and was used from 1955 to 1976. In 1978, the turboprop version of the T-34 entered service with the Navy. The T-34C is unpressurized, with a two seat stepped cockpit and and a single large turboprop engine, which, when combined with a light airframe produce flying qualities similar to, but safer than those of military jet aircraft. The Turbo Mentor is used by the Navy for primary flight training as well as intermediate flight training for those pilots destined for propeller driven fleet aircraft or helicopters. In addition, the Navy uses the T-34C for basic and intermediate Naval Flight Officer training, and the Airforce uses it for Navigator training.
General Characteristics, T-34C Turbo Mentor
Builder:
Raytheon Aircraft Company
Power Plant:
Pratt & Whitney PT6A-25 engine producing 550 shaft horsepower
Length:
28 feet, 8 inches
Height:
9 feet, 11 inches
Wingspan:
33 feet, 5 inches
Weight:
3,580 pounds
Maximum Take-off Weight:
4,400 pounds
Speed:
538 miles per hour (Mach .73)
Ceiling:
25,000 feet
Range:
821 miles
Armament:
None
Crew:
Two (instructor and student)
Date Deployed:
1978
|
|
David
Thu January 16, 2003 10:40pm
|
AAVR7A1 Amphibious Recove
Function: Amphibious assault
Description: The AAVR7A1 is an armored assault amphibious full-tracked vehicle. The vehicle is designed to recover similar or smaller size vehicles. It also carries basic maintenance equipment to provide field support maintenance to vehicles in the field.
General Characteristics, AAVR7A1
Manufacturer:
FMC Corporation
Date First Prototype:
1979
Date First Production Vehicle:
1983
Crew:
Five
Weight:
Unloaded: 50,113 pounds (less crew, fuel, OEM and ammo)
Combat Equipped: 52,123 pounds (crew, fuel, OEM and ammo)
Load Capacity:
21 Combat Equipped Troops (@ 285 pounds) or 10,000 pounds of cargo
Fuel Capacity:
171 Gallons
Cruising Range:
Land at 25 mph: 300 Miles
Water at 2600 rpm: seven hours
Maximum Speed Forward:
Land: 45 mph
Water: 8.2 mph
Maximum Speed Reverse:
Land: 12 mph
Water: 4.5 mph
Engine:
Make: Cummins
Model: VT400
Type: 4 cycle, 8 cylinder, 90' Vee, water cooled, turbocharged
Fuel: Multifuel
Recovery Equipment:
Generator: 120 VAC output
Air Compresser: 145 PSIG to 175 PSIG
Welder: Miller Maxtron 300
Hydraulic Crane: 6000 Pounds Capacity
Crane Winch: 23,000 pounds, breaking strength/ length 85 feet
Armament and Ammunition:
M60D machine gun
Unit Replacement Cost:
$2.2 - 2.5 million
|
|
David
Thu January 16, 2003 10:49pm
|
AAVP7A1 Amphibious Wheele
Function: Amphibious Assault.
History: The AAV7A1 is the newest Assault Amphibian in a series that started with the Roebling ALLIGATOR. The Alligator was developed over a period of 7 years, starting in 1932. The first "Gators" were a disappointment, in that the water speed was only 2.5 mph. The land speed was 25 mph. Through design changes, and by using larger engines, the water speed of the Alligator was increased to 8.6 mph by 1939. In 1940, Roebling built a new model which was designated the CROCODILE. The Crocodile had a land speed of 25 mph and a water speed of 9.4 mph. The LVT-1 was a direct copy of the Crocodile, except that it was fabricated from sheet steel instead of aluminum. The LVT-1 was in production from 1941 to 1943. Being heavier, the land speed of the LVT-1 was 18 mph and the water speed was 7 mph. A 6-cylinder, 146 hp Hercules engine was used for power. The LVT-1 was propelled by two endless chains fitted with cleats, both in the water and on land. The first LVT-1's were used as logistic support vehicles only. They were not armored and carried no armament, however, this soon changed. At the Battle of Tarawa, bolted on armor plate was used and the vehicles were equipped with one to four 30 cal. machine guns. The second generation of LVT's was the LVT-2. This vehicle was developed in 1941 and was in production from 1942 to 1945. The LVT-2 was the basic design for a series of vehicles used during WW II. This family of vehicles included the: LVTA1, LVTA2, LVT4, LVTA4, and LVTA5. A few of the LVTA5s were modified in 1949 and continued in service until the mid 1950s. These vehicles were powered with 7-cylinder radial aircraft engines built by Continental Motors. These engines developed 220hp, their service life was very short. Major overhaul was scheduled for 100 hours, however few ever lasted that long. The transmission was a 5 speed, manual shift SPICER that incorporated a manually operated steer differential. This transmission had been developed for the M-3 light tank. As a result, the transmission was too narrow for the LVT. This problem was overcome by using four final drives. The internal finals were bolted to the transmission / differential gear case and supported by two mounting yokes. The external final drives were bolted to the hull and powered the drive sprockets. This generation of LVTs was used through the Okinawa campaign in 1945.
Description: The AAVP7A1 is an armored assault amphibious full-tracked landing vehicle. The vehicle carries troops in water operations from ship to shore, through rough water and surf zone. It also carries troops to inland objectives after ashore.
General Characteristics, AAVP7A1
Manufacturer:
FMC Corporation
Date First Prototype:
1979
Date First Production Vehicle:
1983
Crew:
Three
Weight:
Unloaded: 46,314 pounds (with EAAK, less crew, fuel, OEM and ammo)
Combat equipped: 50,758 pounds (EAAK, crew, fuel, OEM and ammo)
Troop loaded: 56,743 pounds (combat equipped with troops)
Cargo loaded: 60,758 pounds (combat equipped with cargo)
Mine clearance kit: 61,158 pounds (combat equipped with MKl MOD 0 MCS)
Load Capacity:
21 Combat Equipped Troops (at 285 pounds) or 10,000 pounds of cargo
Fuel Capacity:
171 gallons
Cruising Range:
Land: 20 to 30 mph
Water: 6 mph
Cruising Speed:
Land: 20 to 30 mph
Water: 6 mph
Maximum Speed Forward:
Land: 45 mph
Water: 8.2 mph
Maximum Speed Reverse:
Land: 12 mph
Water: 4.5 mph
Engine:
Make: Cummins
Model: VT400
Type: 4 cycle, 8 cylinder, 90' Vee, water cooled, turbocharged
Fuel: Multifuel
Cargo Compartment:
Length: 13.5 feet
Width: 6.0 feet
Height: 5.5 feet
Volume: 445.5 cubic feet
Capacity: 21 combat equipped troops
Armament and Ammunition:
HBM2 .50 caliber machine gun
MK 19 MOD3 40 mm machine gun
Unit Replacement Cost:
$2.2-2.5 million
|
|
David
Thu January 16, 2003 10:55pm
Rating: 10
|
M1A2
Function: Main battle tank (MBT).
Description: The M1A2 is externally very similar in appearance to the M1A1 with the exception of the redesigned Commander's Weapon Station (CWS) and the Commander's Independent Thermal Viewer (CITV.) The powered cupola has been replaced with a manually operated anti aircraft pintle mount, which cannot be fired while the commander is "buttoned up." In addition, the hatch has been enlarged and the vision blocks have been enlarged, improving visibility. The CITV is mounted in an armored rotating cylinder on the turret access plate forward of the Loader's station. The CITV is tall enough to limit the effectiveness of the loader's M240 machine gun through its forward arc of fire.
History: Approved for production in 1990, the M1A2 represents a technological improvement of the basic M1A1 design. Outwardly similar in appearance to the M1A1, the most notable exterior changes on the M1A2 are the redesigned Commander's Weapon Station (CWS) and the addition of a Commander's Independent Thermal Viewer) on the left side of the turret forward of the loader's hatch. Internally, however, the M1A2 has been radically redesigned to take advantage of newer technology. Most notable of these improvements is the addition of the Inter-Vehicle Information System (IVIS.) The IVIS system allows for the automatic and continual exchange of information between vehicles. By incorporating information provided by an on board Position/Navigation (POSNAV) system, unit commander's can track the location and progress of subordinate elements automatically, without tasking vehicle crews. In addition enemy positions can be identified, plotted and disseminated, while reports and artillery requests can be automatically formatted, transmitted, and processed. Lastly, map graphic control measures and operational orders can be rapidly distributed via the IVIS system. To ensure information security, all IVIS data transmissions are routed through the M1A2's SINCGARS radio system. Improving on the "hunter-killer" tank commander-gunner target hand off method pioneered on the German Leopard II, the M1A2 takes this a step further by providing the Tank Commander with an independent thermal sight. This CITV sight allows the commander to independently scan for targets in all weather conditions and through battlefield obscurants. In addition to IVIS and the CITV, the M1A2 incorporates a number of additional electronic upgrades. Power distribution throughout the tank has been improved, relying on multiple bus paths so that in the event one conduit is damaged, power may still be delivered to a component via an alternate path. The driver's instrument display has been upgraded to a more detailed digital display and the Gunner's Primary Sight has been stabilized in two axes for increased accuracy.
Approved for implementation in 1995, the M1A2 SEP (System Enhancement Package) is a technology upgrade and standardization program, whereby the Army's fleet of M1s and M1A2s will all be brought to a common standard. Most notable among the modifications will be the introduction of a standard under armor auxiliary power unit and the addition a crew compartment air conditioning and cooling unit. Other modifications within the vehicle will include upgrades to the IVIS system (color display, full size keyboard, digital mapping and graphics generation capability, and voice recognition capabilities), upgrades to the Gunner's Primary Sight assembly, and improvement in the tank's intercom and radio communications systems. Production of the M1A2 was halted after the initial run of 627 vehicles. As part of the fleet upgrade program, 547 of the Army's current inventory of M1s are being upgraded to M1A2 SEP standards, which will require the complete remanufacturing of the turret, while the current fleet of M1A2s will undergo a retrofit to bring them up to SEP standards.
The M1A2 is currently available for export, albeit with a different armor composition and communications package. Saudi Arabia has purchased 312 M1A2s, equipped with British Jaguar radios, and Kuwait has purchased 218 similarly equipped M1A2s.
|
|
David
Thu January 16, 2003 11:05pm
|
HMMWV High Mobility Multi
Function: The HMMWV provides a variety of wheeled vehicle platforms. These are cargo/troop carrier, armament carrier, TOW missile system carrier, shelter carrier and two ambulance variants (2- and 4-litter). The HMMWV will also be the prime mover for the AN/TRC-170 Radio Digital Terminal and the Pedestal Mounted Stinger System.
Description: The M998 is the baseline vehicle for the M998 series of 1 1/4-ton trucks, which are known as the HMMWV vehicles. The HMMWV vehicles include 11 variants. They are: M998 Cargo/Troop Carrier; M1038 Cargo/Troop Carrier, with winch; M1043 Armament Carrier; M1044 Armament Carrier, with winch; M1045 TOW Carrier; M1046 TOW Carrier, with winch; M997 Ambulance, basic armor 4-Litter; M1035 Ambulance, 2-Litter; M1037 Shelter Carrier; M1042 Shelter Carrier, with winch; M1097 Heavy HMMWV (payload of 4,400 pounds). All HMMWVS are designed for use over all types of roads, in all weather conditions and are extremely effective in the most difficult terrain. The HMMWVS high power-to-weight ratio, four wheeled drive and high ground clearance combine to give it outstanding cross-country mobility.
General Characteristics, HMMWV
Length:
15 feet (4.57 meters)
Width:
7.08 feet (2.16 meters)
Weight:
5,200 pounds (2,359 kilograms)
Height:
6.00 feet (1.83 meters) reducible to 4.5 feet (1.37 meters)
Engine:
9.92 feet (3 meters)
Horsepower:
150 at 3,600 RPM
Transmission:
3 speed, automatic
Transfer case:
2 speed, locking, chain driven
Electrical system:
24 volt, negative ground, 60 amps
Brakes:
Hydraulic, 4-wheeled disc
Fording depth:
Without preparation: 2.5 feet (76.2 centimeters)
With deep water fording kit: 5 feet (1.5 meters)
Fuel type:
Diesel
Fuel capacity:
25 gallons (94.63 liters)
Range:
350 miles (563.15 kilometers) highway
Unit Replacement Cost:
$50,000
Inventory:
19,598
|
|
David
Thu January 16, 2003 11:24pm
|
AGM-84D Harpoon
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
|
|
David
Thu January 16, 2003 11:24pm
|
Mk. 80 Series General Pur
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
|
|
David
Thu January 16, 2003 11:24pm
Rating: 10
|
TOW Missile
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
|
|
|
The Patriot Files Forums
