David
Thu January 16, 2003 12:43am
|
EC-130E Commando Solo
Function: Airborne Psycological Warfare/ Electronic Warfare platform.
Background: Fielded in 1992, the Rivet Rider variant of the Commando Solo electronic warfare support aircraft is a highly modified C-130 Hercules transport designed to serve as an airborne television and radio broadcasting platform. Flown exclusively by the 193rd Special Operations Wing (Pennsylvania Air National Guard), the EC-130E is capable of broadcasting in all AM, FM, HF, TV (Color/ B&W) and military communications bands in support of psychological warfare operations and civil affairs broadcast missions. Rivet Rider aircraft are capable of overriding local transmitters with their own message, thus ensuring message reception.
As an EW support aircraft, Commando Solo aircraft are tasked by the 4th Psychological Operations Group (Airborne) to broadcast specific messages to a designated target audience. These messages are prepared by the 4th and are specifically designed to meet requirements dictated by the U.S. State department or the Theater Area Commander. In addition to performing PSYOP operations, Commando Solo is capable of serving in a humanitarian aid and support capacity, broadcasting public service and emergency relief information. Because of the aircraft's transmitting capabilities, the EC-130E is also capable of serving in a limited capacity as an airborne command and control aircraft as well as an electronic warfare jamming platform.
Description: Though based on the basic C-130H tactical cargo aircraft, the Commando Solo/Rivet Joint airframe has been heavily modified, both internally and externally. The Rivet Rider aircraft is equipped with three large blade antennae, one each mounted vertically underneath outside edge of the wing and one incorporated into the leading edge of the aircraft vertical stabilizer. A fourth, X-shaped, antenna is incorporated into the vertical stabilizer. Outboard of the wing antennae are two large (6 foot diameter x 23 feet long) equipment pods. When conducting broadcasting operations the aircraft streams two flexible wire antennae; one trails out behind the aircraft and another is suspended from underneath the aircraft, held in a vertical position by a suspended 500 lb. weight. For self defense the EC-130E is equipped with on-board electronic warfare radar jamming equipment, a radar warning receiver, as well as electronic and infrared counter-measures dispensers.
?General Characteristics, EC-130E Commando Solo/ Rivet Rider
Prime Contractor:
Airframe: Lockheed Aeronautic
Electronics: Lockheed-Martin
Power plant:
Four Allison T56-A-15 Turboprop Engines, 4,910 shaft horsepower per engine
Wingspan:
132 ft 7 in (40.4 meters)
Length:
100 ft 6 in (30.9 meters)
Height:
38 ft 6 in (11.7 meters)
Speed:
299 mph (478 kph)
Service Ceiling:
20,000 ft (6,154 meters)
Range:
2,100 miles (3,380 km); capable of in-flight refueling
Crew:
Four officers (pilot, copilot, navigator, mission control chief/EWO); seven enlisted (flight engineer, loadmaster, five mission crew)
Maximum Take-off Weight:
155,000 lbs (70,455 kg)
Unit Cost:
$70 million each
Date Deployed:
1992
|
|
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
|
CH-53E Super Stallion
Function: Transportation of heavy equipment and supplies during the ship-to-shore movement of an amphibious assault and during subsequent operations ashore.
History: Derived from an engineering change proposal to the twin-engine CH-53D helicopter, the CH-53E has consistently proven its worth to the Fleet commanders with its versatility and range. With four and one half hours' endurance, the Super Stallion can move more equipment over rugged terrain in bad weather and at night. During Operation Eastern Exit two CH-53Es launched from amphibious ships and flew 463 nautical miles (532.45 miles) at night, refueling twice enroute, to rescue American and foreign allies from the American Embassy in the civil war-torn capital of Mogadishu, Somalia in January of 1990. Two CH-53Es rescued Air Force Capt. Scott O'Grady in Bosnia in June 1995.
Description: The CH-53E is a follow-on for its predecessor, the CH-53D. Improvements include the addition of a third engine to give the aircraft the ability to lift the majority of the Fleet Marine Force's equipment, a dual point cargo hook system, improved main rotor blades, and composite tail rotor blades. A dual digital automatic flight control system and engine anti-ice system give the aircraft an all-weather capability. The helicopter seats 37 passengers in its normal configuration and has provisions to carry 55 passengers with centerline seats installed. With the dual point hook systems, it can carry external loads at increased airspeeds due to the stability achieved with the dual point system.
As the Marine Corps' heavy lift helicopter designed for the transportation of material and supplies, the CH-53E is compatible with most amphibious class ships and is carried routinely aboard LHA (Landing, Helicopter, Assault: an amphibious assault ship), LPH (Landing Platform, Helicopter: an amphibious assault ship) and now LHD (Landing, Helicopter, Dock: an amphibious assault ship) type ships. The helicopter is capable of lifting 16 tons (14.5 metric tons) at sea level, transporting the load 50 nautical miles (57.5 miles) and returning. A typical load would be a 16,000 pound (7264 kilogram) M198 howitzer or a 26,000 pound (11,804 kilogram) Light Armored Vehicle. The aircraft also can retrieve downed aircraft including another CH-53E. The 53E is equipped with a refueling probe and can be refueled in flight giving the helicopter indefinite range.
General Characteristics, CH-53E Super Stallion
Contractor:
Sikorsky Aircraft
Unit Cost:
$26.1 million
Power Plant:
Three General Electric T64-GE-416 turboshaft engines producing 4380 shaft horsepower each
Thrust:
1,770 horsepower
Length:
99 feet 5 inches (2.64 meters)
Height:
28 feet 4 inches (.81 meters)
Rotor Diameter:
79 feet (24.07 meters)
Maximum Take-off Weight:
Internal load: 69,750 pounds (31,666 kilograms)
External load: 73,500 pounds (33,369 kilograms)
Speed:
172.5 mph (150 knots)
Range:
Without refueling: 621 miles (540 nautical miles)
With aerial refueling: indefinite
Crew:
Three
Armament:
Two XM-218 .50 caliber machine guns
Introduction Date:
June 1981
|
|
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 10:39am
|
UH-60 Blackhawk
Description: The Black Hawk is the Army?s front-line utility helicopter used for air assault, air cavalry, and aeromedical evacuation units. It is designed to carry 11 combat-loaded, air assault troops, and it is capable of moving a 105-millimeter howitzer and 30 rounds of ammunition. First deployed in 1978, the Black Hawk?s advanced technology makes it easy to maintain in the field. The Black Hawk has performed admirably in a variety of missions, including air assault, air cavalry and aeromedical evacuations. In addition, modified Black Hawks operate as command and control, electronic warfare, and special operations platforms.
The Black Hawk is the primary division-level transport helicopter, providing dramatic improvements in troop capacity and cargo lift capability compared to the UH-1 Series "Huey" it replaces. The UH-60A, with a crew of three, can lift an entire 11-man fully-equipped infantry squad in most weather conditions. It can be configured to carry four litters, by removing eight troop seats, in the MedEval role. Both the pilot and co-pilot are provided with armor-protective seats. Protective armor on the Black Hawk can withstand hits from 23mm shells. The Black Hawk has a cargo hook for external lift missions. The Black Hawk has provisions for door mounting of two M60D 7.62mm machine guns on the M144 armament subsystem, and can disperse chaff and infrared jamming flares using the M130 general purpose dispenser. The Black Hawk has a composite titanium and fiberglass four-bladed main rotor, is powered by two General Electric T700-GE-700 1622 shp turboshaft engines, and has a speed of 163 mph (142 knots).
Elements of the U.S. Army Aviation UH-60A/l Blackhawk helicopter fleet will begin reaching their sevice life goal of 25 years in 2002. In order for the fleet to remain operationally effective through the time period 2025-2030 the aircraft will need to go through an inspection, refurbishment, and modernization process that will validate the structural integrity of the airframe, incorporate improvements in sub-systems so as to reduce maintenance requirements, and modernize the mission equipment and avionics to the levels compatible with Force XXI and Army After Next (AAN) demands.
A Service Life Extension Program (SLEP) is planned for the UH-60 beginning in FY99. The UH-60 modernization program will identify material requirements to effectively address known operational deficiencies to ensure the Black Hawk is equipped and capable of meeting battlefield requirements through the 2025-2030 timeframe. Primary modernization areas for consideration are: increased lift, advanced avionics (digital communications and navigation suites), enhanced aircraft survivability equipment (ASE), increased reliability and maintainability (R & M), airframe service life extension (SLEP), and reduced operations and support (O & S) costs. Suspense date for the approved Operational Requirements Document (ORD) is December 1998.
History: The UH-60A, first flown in October 1974, was developed as a result of the Utility Tactical Transport Aircraft System (UTTAS) program. The UTTAS was designed for troop transport, command and control, MedEvac, and reconnaissance, to replace the UH-1 Series "Huey" in the combat assault role. In August 1972, the U.S. Army selected the Sikorsky (model S-70) YUH-60A and the Boeing Vertol (model 237) YUH-61A (1974) as competitors in the Utility Tactical Transport Aircraft System (UTTAS) program. The Boeing Vertol YUH-61A had a four-bladed composite rotor, was powered by the same General Electric T700 engine as the Sikorsky YUH-60A, and could carry 11 troops. In December 1976 Sikorsky won the competition to produce the UH-60A, subsequently named the Black Hawk.
Variants: The Army began fielding the UH-60 in 1978. From 1978 until 1989 the Army procured UH-60A model aircraft. In October 1989, a power train upgrade resulted in a model designation change from UH-60A to UH-60L. The UH-60L version that provides 24 percent more power than the original 1970 UH-60A model. As of the end of FY97, the Army had procured 483 UH-60L models for a total UH-60 acquisition of 1,463 aircraft. The Army is in the fifth and final year of a multi-year procurement contract calling for the delivery of 60 aircraft per year.
UH-60L: In October 1989, the engines were upgraded to two General Electric T700-GE-701C 1890 shp turboshaft engines, and an improved durability gear box was added, resulting in a model designation change from UH-60A to UH-60L. The T700-GE-701C has better high altitude and hot weather performance, greater lifting capacity, and improved corrosion protection.
The UH-60 Firehawk is a Reseach and Development program to provide the UH-60 series helicopter with both a wartime and peacetime fire fighting capability by use of a detachable 1,000 gal. belly tank. Qualification issues include design and testing required to maintain the combat capabilities of the UH-60 Black Hawk and the safe flight envelope of the aircraft with the tank.
The EH-60A Electronic Countermeasures (ECM) variant has a unique external antenna designed to intercept and jam enemy communications. The EH-60E is powered by two General Electric T700-GE-700 1622 shp turboshaft engines.
The EH-60B version has a Stand-Off Target Acquisition System designed to detect the movement of enemy forces on the battlefield and relay the information to a ground station.
UH-60Q Medevac: The UH-60Q MEDEVAC helicopter provides significant enroute patient care enhancements. The UH-60Q provides a 6 patient litter system, on-board oxygen generation, and a medical suction system. UH-60Q is a UH-60A derivative and incorporates approximate UH-60A characteristics. It is simply the best in aeromedical evacuation. Building on the BLACK HAWK's heritage of saving lives in Grenada, Panama, Kuwait and Somalia, the UH-60Q delivers exceptional patient care, increased survivability, longer range, greater speed and added missions capability. For military combatants. War victims. Civilians injured in natural disasters. It has a state-of-the-art medical interior that can accomodate a crew of three and up to six acute care patients. The UH-60Q's leading-edge technology incorporates an improved environmental control system. Cardiac monitoring systems. Oxygen generation, distribution and suction systems. Airway management capability. Provision for stowing IV solutions. And an external electrical rescue hoist. And in addition to extensive immediate care, the UH-60Q can perform all weather terrain battlefield evacuation, combat search and rescue, hospital ship lifeline missions, deep operations support, forward surgical team transport, medical logistics resupply, medical personnel movement, patient regulating, disaster/humanitarian relief, and MAST/HELP state support.
The UH-60Q's medical interior can accomodate three to six acute care patients and their medical attendants. Ergonomic design has maximized the UH-60Q cabin space, placing sophisticated, life-saving instruments and equipment at the fingertips of the medical attendants. A unique platform design allows the interior to transport either six litter of seven ambulatory systems, oxygen distribution and suction systems, airway management capability, and provisions for stowing intravenous solutions. The interior also features these additional capabilities, essentical to providing the highest degree of patient care when every second counts:
- Oxygen Generating Systems
- NVG Compatible Lighting Throughout
- Environmental Control System
- Medical Equipment
- Patient Monitoring Equipment
- Neonatal Isolettes
Modernizing the Medical Evacuation (MEDEVAC) system is the Army Surgeon General's number one near term priority. The UH-60Q communications architecture provides situational awareness and digital communications and is expected to be the model for anticipated fleet-wide improvements to the UH-60. Other improvements include integrated Doppler/GPS, Personnel Locator System, NVG interior lighting, and FLIR.
General Characteristics, UH-60 Black Hawk
Contractor:
Sikorsky
Power Plant:
Two T700-GE-701Cs
Thrust:
3,120 shaft horsepower
Length:
64 feet, 7 inches (19.7 meters)
Height:
16 feet, 10 inches
Main Rotor Diameter:
53 feet, 6 inches (16.3 meters)
Weight:
11,500 pounds
External Cargo Hook:
Handles up to 8000 pounds (3629 kilograms)
Maximum Speed:
150 knots
Ceiling:
19,000 feet (5,790 meters)
Range:
315 nautical miles
Crew:
Two pilots and two crew; 11 to 14 armed troops
Armament:
Up to two 7.62mm M60 machine guns in cabin
Two 7.62-mm (0.3-in) miniguns or two GECAL 0.50-in Gatling guns on pintle mount
Date Deployed:
1978
|
|
David
Thu January 16, 2003 10:39am
|
CH-46D/E Sea Knight
Function: Medium lift assault helicopter, primarily used to move cargo and troops.
History: The CH-46 Sea Knight was first procured in 1964 to meet the medium-lift requirements of the Marine Corps in all combat and peacetime environments since that time. The Sea Knight fleet is currently being maintained until a suitable replacement is approved.
Description: The CH-46D Sea Knight helicopter is used by the Navy for shipboard delivery of cargo and personne. The CH-46E is used by the Marine Corps to provide all-weather, day-or-night assault transport of combat troops, supplies and equipment. Troop assault is the primary function and the movement of supplies and equipment is secondary. Additional tasks may be assigned, such as combat support, search and rescue, support for forward refueling and rearming points, aeromedic evacuation of casualties from the field and recovery of aircraft and personnel.
General Characteristics, CH-46D/E Sea Knight
Contractor:
Boeing Vertol Company
Power Plant:
Two GE-T58-16 engines
Thrust:
1,770 horsepower
Length:
45 feet, 8 inches (13.89 meters) with rotors folded
84 feet, 4 inches (25.7 meters) with rotors spread
Height:
16 feet, 8 inches (5.08 meters)
Rotor Diameter:
51 feet (15.54 meters)
Maximum Takeoff Weight:
24,300 pounds (11,032 kilograms)
Speed:
145 knots (166.75 mph)
Ceiling:
10,000 feet plus
Range:
132 nautical miles (151.8 miles) for land assault mission
Crew:
Four: pilot, copilot, crew chief, mechanic
Payload:
Combat: maximum of 22 troops and two aerial gunners
Medical evacuation: 15 litters, two attendants
Cargo: 5,000 pounds (2270 kilograms) maximum
Introduction Date:
January 1978
|
|
David
Thu January 16, 2003 10:39am
|
CH-53D Sea Stallion
Function: The CH-53D is a medium lift helicopter designed to transport personnel, supplies and equipment in support of amphibious and shore operations.
History: The CH-53D was ordered in the early 1960s to satisfy a Marine Corps requirement for a heavy lift helicopter. It has since been replaced in the heavy lift mission by the CH-53E Super Stallion. All Marine Corps CH-53D helicopters are currently assigned to Marine Corps Base Hawaii, Kaneohe Bay. The CH-53D, along with the CH-46E, is slated for replacement by the MV-22 Osprey.
General Characteristics, CH-53D Sea Stallion
Contractor:
Sikorsky Aircraft Division of United Technologies Corporation
Power Plant:
Two General Electric T64-GE-413 turboshaft engines (3,925 shaft horsepower each)
Length:
67.5 feet (20.3 meters)
Height:
24 feet, 11 inches (7.2 meters)
Rotor Diameter:
72 feet, 3 inches (21.7 meters)
Load:
37 troops or 24 litter patients plus four attendants or 8,000 pounds (3,600 kilograms) cargo
Speed:
160 knots (184 mph, 294 kmh)
Ceiling:
12,450 feet
Range:
578 nautical miles (665 statute miles, 1064 km); 886 nautical miles ferry range
Crew:
Two pilots, one aircrewman
Date Deployed:
First flight: Oct 14, 1964
Operational:
November 1966
|
|
David
Thu January 16, 2003 10:39am
|
SH-60 Seahawk
Function: A twin-engine, medium lift, utility or assault helicopter.
History: The UH-60 Black Hawk was fielded by the Army in 1979. The Navy received the SH- 60B Seahawk in 1983 and the SH-60F in 1988. The Air Force received the MH-60G Pave Hawk in 1982 while the Coast Guard received the HH-60J Jayhawk in 1992. The unit cost varies with the version. For example, the unit cost of the Army's UH-60L Black Hawk is $5.9 million while the unit cost of the Air Force MH-60G Pave Hawk is $10.2 million.
Description: The Seahawk is a twin-engine helicopter. It is used for anti-submarine warfare, search and rescue, drug interdiction, anti-ship warfare, cargo lift, and special operations. The Navy's SH-60B Seahawk is an airborne platform based aboard cruisers, destroyers, and frigates and deploys sonobouys (sonic detectors) and torpedoes in an anti-submarine role. They also extend the range of the ship's radar capabilities. The Navy's SH-60F is carrier-based. Some versions, such as the Air Force's MH-60 G Pave Hawk and the Coast Guard's HH-60J Jayhawk, are equipped with a rescue hoist with a 250 foot (75 meter) cable that has a 600 pound (270 kg) lift capability, and a retractable in-flight refueling probe. The Army's UH-60L Black Hawk can carry 11 soldiers or 2,600 pounds (1,170 kg) of cargo or sling load 9,000 pounds (4,050 kg) of cargo. Other versions are the UH-60 Black Hawk (Army); HH-60H (Navy); MH-60G Pave Hawk (Air Force); HH-60J Jayhawk (Coast Guard).
General Characteristics, SH-60 Seahawk
Contractors:
Sikorsky Aircraft Corporation (airframe); General Electric Company (engines); IBM Corporation (avionics components)
Power Plant:
Two General Electric T700-GE-700 or T700-GE-701C engines
Thrust:
Up to 1,940 shaft horsepower
Length:
64 feet 10 inches (19.6 meters)
Height:
Varies with the version; from 13 to 17 feet (3.9 to 5.1 meters)
Rotor Diameter:
53 feet 8 inches (16.4 meters)
Weight:
Varies; 21,000 to 23,000 pounds (9,450 to 10,350 kilograms)
Maximum Speed:
180 knots
Ceiling:
35,000 feet (10,668 meters)
Range:
Generally about 380 nautical miles (600 kilometers); range becomes unlimited with air refueling capability
Crew:
Usually three or four
Armament:
Usually two 7.62mm machine guns mounted in the windows
Can also be equipped with AGM-114 Hellfire or AGM-119 Penguin missiles, three Mk46 or Mk 50 torpedoes or additional .50-caliber machine guns mounted in the doors
|
|
David
Thu January 16, 2003 10:39am
|
UH-1N Iroquois
Function: The UH-1N is a light-lift Air Force utility helicopter used for support of Department of Defense contingency plans. The helicopter has a number of uses. Its primary mission includes airlift of emergency security and disaster response forces, medical evacuation, security surveillance of off-base movements of nuclear weapons convoys and test range areas during launch conditions. It is also used for space shuttle landing support, priority maintenance dispatch support, and search and rescue operations. Other uses include airlift of missile support personnel, airborne cable inspections and distinguished visitor transport.
History: The UH-1N entered the Air Force inventory in 1970 to provide search and rescue capabilities. The missions expanded to include missile, distinguished visitor and survival school support. Some of the UH-1Fs supporting the missile wings were eventually replaced by the UH-1N due to the greater safety and capability offered by the twin engine. Manufactured by Bell Helicopter/Textron Inc., the UH-1N is the military version of the Bell 212.
Description: The UH-1N is capable of flight in instrument and nighttime conditions. The crew complement is normally two (pilot and copilot), but may be flown single-pilot depending on weather and mission requirements. The crew complement for hoist, over water and navigational operations is three, adding a flight engineer. When configured for passengers, the UH-1N can seat up to 13 people, but actual passenger loads are dependent on fuel loads and atmospheric conditions. The medical evacuation configuration can accommodate up to six litters. Without seats or litters, the cabin can carry bulky, oversized cargo. Access to the cabin is through two full-sized sliding doors, one on each side of the aircraft.
General Characteristics, UH-1N Huey
Contractor:
Bell Helicopter Company
Power Plant:
Two Pratt and Whitney T400-CP-400 turboshaft engines
Thrust:
1,770 horsepower
Length:
57 feet, 3 inches (17.44 meters)
Width:
9 feet, 5 inches (2.87 meters)
Height:
12 feet, 10 inches (3.9 meters)
Main Rotor Diameter:
48 feet (14.63 meters)
Tail Rotor Diameter:
8 feet, 6 inches (2.6 meters)
Maximum Gross Weight:
10,500 pounds (4,763 kilograms)
Maximum Speed:
149 mph (130 knots)
Cruise Speed:
103-115 mph (90-100 knots)
Ceiling:
15,000 feet (4,572 meters)
10,000 feet (3,048 meters) for gross weights above 10,000 pounds (4,536 kilograms)
Range:
300-plus miles
Crew:
Pilot with co-pilot and flight engineer, depending upon mission
Inventory:
Active force, 63
Reserve, 0
ANG, 0
Date Deployed:
1970
|
|
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 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 10:59pm
|
M1 Abrams
Function: Main battle tank (MBT).
Description: The M1 has a very angular appearance, reflecting the modular nature of its armor components, with the turret mounted centrally on the hull. The M1 has a crew of four. The driver sits centered in the hull and forward of the turret, while the loader, gunner and tank commander occupy the turret, with the loader situated to the left of the main gun and the gunner and tank commander sitting in tandem on the right side. The driver's hatch has three periscope vision blocks which provide for forward vision. The center vision block may be removed and replaced with an AN/TVS-2 low-light periscope. The engine is mounted in the rear of the vehicle with the exhaust coming out from a louvered grill centrally mounted in the rear of the hull. The M1 utilizes a torsion bar suspension with seven pairs of cast aluminum road wheels and two return rollers. The drive sprocket is to the rear, an idler compensation wheel is located forward, and there is a gap between the first and second pair of road wheels. The M1 has armored skirts running the full length of the track. M1 track is made up of vulcanized rubber blocks (M156 variety) or removable rubber pads (M158.) The turret is also angular in appearance, with the main gun mounted in an exposed mantlet in the center of the turret face. The M68 rifled cannon is equipped with a metal thermal shroud, a bore gas evacuator located two-thirds of the way down on the barrel, and is equipped with a Muzzle Reference System collimator on the muzzle itself. The M240 coaxial (COAX) machine gun is located to the right of the main gun, with the flash tube extending through the main gun mantlet. The Gunner's Auxiliary Sight (GAS) aperture is located below the COAX flash tube on the right side of the main gun. The M1 has two turret access hatched, mounted side by side, in the middle of the turret roof. The loader's hatch, located on the left side, is equipped with a pintle mounted M240 7.62mm machine gun. The hatch itself is equipped with a single vision periscope on a rotating base. When not in use, the drivers AN/TVS-2 sight may be used in the loader's hatch vision block. The tank commander's hatch is ringed by vision periscopes and the Commander's Weapon Station cupola is equipped with an M2 HB caliber .50 machine gun. The M2 may be fired while the commander is "buttoned up" but the commander must be exposed to reload the weapon. The CWS can be reconfigured to fire an M240 as a replacement weapon. The Gunner's Primary Sight (GPS) is located forward of the commander's cupola. The GPS is housed in an armored box with hinged doors shielding the optics when not in use. The GPS is divided into two halves; a clear glass window for normal daylight viewing and an IR transparent Germanium coated window for the thermal imaging sight. The Laser Range Finder (LRF) is fired through the daylight window. There are individual sponson boxes located on either side of the turret for equipment storage. These boxes are approximately three feet (1m) long and are bracketed by a three-rail cargo rack which runs the length of the turret side. The smoke grenade launchers are located on either side of the turret, forward of the turret sponson boxes. There are mounting points for two radio antennae, one on either side of the turret rear, and the cross wind sensor is mounted upright in the center of the turret rear. A cargo bustle rack is mounted on the rear of the turret and runs the length of the turret rear (in early production M1s this rack was omitted and a fabric cargo net mounted in it's place. An Auxiliary Power Unit (APU) may be mounted in the turret bustle rack or on the rear of the hull.
History: Fielded in February 1980, the M1 General Abrams main battle tank revolutionized armored warfare. Incorporating an advanced shoot-on-the-move fire control system, a thermal imaging sight, a 1500 horsepower gas turbine engine and an advanced armor design similar to the Chobham armor developed in England, the M1 was the most lethal armored vehicle in the world. Conceived in 1971 as a replacement for the aging M60 tank, which was itself an extension of the 1050s era M 47/48 program, the M1 was going to be of a completely new design, establishing a new family of American main battle tanks. Providing the Abrams with a true shoot on the move capability, the fire control system automatically corrects for range, turret slew (motion) rate, crosswind, and tank axial tilt (cant). In addition, the gunner manually enters ammunition or weapon type, air and ammunition temperatures, barometric pressure, and gun tube wear, while range is instantly calculated by a Nd:YAG (Neodymium doped Yttrium Aluminum Garnet) near infrared laser rangefinder. Lastly, the gunner can compensate for gun tube deformation (caused either by heat generated from firing the cannon or atmospheric changes) through the use of a muzzle reference system, which allows for a rapid realignment of the cannon and the gunner's primary sight.
The Chobham armor built into the M1 represents a veritable leap in armor technology. Composed of layers of metal, ceramics, and spaces, this new armor is far superior to RHA (Rolled Homogeneous Armor) in defeating kinetic and chemical energy weapons. To increase crew safety and survivability, all of the M1's ammunition is stored in armored compartments which are designed vent dangerous gasses and fragments away from the crew in the event of an ammunition explosion. The crew and engine compartments are equipped with an automatic fire suppression system, utilizing numerous fire detection sensors and pressurized Halon gas, which can react to and suppress a compartment fire in less than 250 ms.
To survive on the NBC (Nuclear, Biological, Chemical) battlefield the M1 is also equipped with both an over pressurization and air sterilization system which will protect the crew from these hazards and allow them to continue combat operations without having to wear protective overgarments and masks while buttoned up inside the vehicle.
Lastly, the M1 was the first land combat vehicle to utilize a gas turbine multi fuel engine, which offers a higher power to weight ratio than any other contemporary tank power plant and gives the Abrams unparalleled tactical mobility and cross country speed. The M1 retains the M68 105mm rifled cannon used on the M60 series tanks, which was originally based on the British M7 105mm cannon design, and is capable of firing both rifled and fin stabilized ammunition. In addition, the M1 is equipped with two M240 7.62mm machine guns; one mounted coaxially with the main gun and fired by gunner, and the other mounted at the loader's station. The Commanders Weapon Station (CWS) is equipped with an M2 heavy barrel Caliber .50 machine gun. The CWS can be reconfigured to fire the M240 machine gun as a substitute.) The M1 is equipped with a pair of M250 red phosphorus smoke grenade launchers and is capable of generating smoke by injecting diesel fuel into the engine exhaust.
Originally designated the XM1, the first production model was designated the M1, of which 2,374 were built between 1982 and 1985. In 1984 the M1IP (Improved Product) was introduced, which was outwardly identical to the M1, but which incorporated a number of internal automotive, electronic and armor improvements. Production of the M1IP was halted at 84 tanks in 1986, when the Lima and Detroit tank plants were reconfigured to produce the up-gunned 120mm M1A1. In 1992 a study was conducted evaluating the feasibility of upgrading the Army's fleet of M1s to M1A2 SEP (Standard Equipment Package) standard and low rate production was approved in 1994. Since then the Army had agreed to convert 547 M1s to the M1A2 SEP standard.
|
|
|
The Patriot Files Forums
