David
Sat January 3, 2004 8:43pm
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M61A1 20mm Cannon
Description: The current version of the M61, the M61A1, remains relatively unchanged from past models. In its basic form the M61A1 is a six barreled rotary cannon firing a variety of electrically primed 20mm cannon shells. The gun can be mounted either internally in aircraft, or externally in a pod arrangement, and has been mounted on both ground vehicles and trailers for use as an air defense weapon. The M61A1 can be driven hydraulically, electrically, or by ram air and has a variable rate of fire of between 4,000 and 7,200 rounds per minute (depending on individual settings and performance requirements).
Background: Soon after the end of the Second World War the newly formed United States Air Force identified a need for an improved gun system for its aircraft. While adequate as an air combat / ground attack weapon during World War Two, the Browning M2 .50 caliber machine gun had been rendered obsolete by jet aircraft and needed to be replaced by a weapon with increased range, rate of fire, and projectile lethality. Realizing that singled barreled automatic weapons had essentially reached their design limits, the U.S. Army Ordnance Research and Development Service hit on the idea of re-introducing the multi-barreled rotary weapon invented by Richard J. Gatling in the 1880s. Initial tests proved promising as a vintage Gatling gun, now powered by an electric motor in place of the usual hand crank, was able to achieve rates of fire in excess of 4,000 rounds per minute.
In 1946 the General Electric company received the contract for this new program, code named "Project Vulcan," and was tasked with producing functional prototypes in a number of calibers for further testing. In 1952 GE produced three different guns; .60 caliber, 20mm, and 27mm. After extensive testing, the 20mm version was selected for further testing to determine its suitability as an aircraft mounted weapon. In 1956 the gun was standardized as the M61 20mm cannon and entered service with both the United States Army and Air Force.
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David
Sat January 3, 2004 8:47pm
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M198 155mm Medium Howitze
Function: Provides field artillery fire support for all Marine Corps Air Ground Task Force organizations.
Description: The M198 Medium Towed Howitzer is a 155mm field artillery howitzer. It is constructed of aluminum and steel, and is air transportable by CH-53E helicopter, and C-130 or larger fixed-wing aircraft. The M198 provides increased range, and improved reliability and maintainability over the former standard towed 155mm howitzer, the M114A2. The use of rocket-assisted projectiles significantly extends the range, lethality, and counterbattery fires of the direct support artillery battalions. The M198 fires all current and developmental 155mm ammunition.
Background: The first 10 M198 Howitzers were delivered to the 10th Marine Regiment in January 1982.
General Characteristics, M198 155mm Medium Howitzer, Towed
Manufacturer:
Rock Island
Contractor:
AMCCOM
Length:
In tow: 40 feet, 6 inches (12.30 meters)
Firing: 36 feet, 2 inches (11.01 meters)
Width in Tow:
9 feet, 2 inches (2.79 meters)
Height in Tow:
9 feet, 6 inches (2.89 meters)
Weight:
15,758 pounds (7.154 kilograms)
Bore Diameter:
155mm
Maximum Effective Range:
Conventional ammunition: 22,400 meters (13.92 miles)
Rocket-assisted projectile: 30,000 meters (18.64 miles)
Rates of Fire:
Maximum: 4 rounds per minute
Sustained: 2 rounds per minute
Crew:
Nine enlisted
Unit Replacement Cost:
$527,337
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David
Sat January 3, 2004 8:47pm
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M-252 Mortar
Function: Provides field artillery fire support for all Marine Corps Air Ground Task Force organizations.
Description: The M252 81mm Medium Extended Range Mortar is a crew-served, medium weight mortar which is highly accurate and provides for a greater range (4,500 meters to 5,650 meters) and lethality than the previous versions. The cannon has a crew-removable breech plug and firing pin. The muzzle end has a short tapered lead-in which acts as a blast attenuator device. The breech end is finned for better cooling. This mortar also uses the standard M64 mortar sight of the 60mm mortar, M224.
Background: This mortar replaced the previous Marine Corps 81mm mortar in 1986. The M252 is an adaptation of the standard British 81mm mortar developed in the 1970s. It is mostly commonly found in the mortar platoon of an infantry battalion. A Blast Attenuation Device (BAD) is attached to the muzzle of the weapon to reduce the blast effects on the mortar crew. The M252 is ideally suited to support airborne, air assault and light infantry units.
General Characteristics, M-252 Mortar
Length:
56 inches (142.24 centimeters)
Weight:
Mortar Assembly: 35 pounds (15.89 kilograms)
Bipod: 26 pounds (11.80 kilograms)
Baseplate: 25.5 pounds (11.58 kilograms)
Sight Unit: 2.5 pounds (1.14 kilograms)
Total: 89 pounds (40.41 kilograms)
Bore Diameter:
81mm
Maximum Effective Range:
5700 meters
Rates of Fire:
Maximum: 33 rounds per minute Sustained: 16 rounds per minute Elevation: 45 to 85 degrees
Minimum Range:
80 meters
Unit Replacement Cost:
$24,717
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David
Sat January 3, 2004 9:09pm
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AN/PSS-12 Metallic Mine D
Function: Mine Detection.
Description: The AN/PSS-12 Mine Detector is a light weight, hand held, metallic mine detector. It is capable of detecting very small metallic objects such as small firing pins in plastic and wooden mines. The AN/PSS-12 Mine Detector is capable of detecting mines in fresh or salt water, and objects buried up to 20 inches in the ground.
History: The AN/PSS-12 mine detector replaces the PSS-11 Metallic Mine Detector. The PSS-11 had reached its end of service life, and needed to be replaced with state-of-the-art technology. The AN/PSS-12 represents a world-class mine detector capable of detecting small amounts of metal found in modern land mines.
General Characteristics, AN/PSS-12 Metallic Mine Detector
Manufacturer:
Schiebel Instruments, Inc.
Power Supply:
Four 1.5 V batteries
Weight:
Mine Detector in transport case: 13.7 lbs. (6.2 kilograms) Mine Detector: 8.5 lbs. (3.8 kg.)
Operating Time:
70 hours
Deployment Method:
Hand Held
Materials:
Telescopic pole consists of an inner plastic tube and outer aluminum tube
Inventory:
547: approximately 300 are currently fielded to FMF units and training commands; the majority of these assets are held in the Combat Engineer Battalions, Engineer Support Battalions and Marine Wing Support Squadrons
Unit Replacement Cost:
$1,196
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David
Sat January 3, 2004 9:09pm
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Mattax
Function: The Mattax is a dual-purpose tool combining the functions of a mattock and an ax and is intended for hand excavation which is difficult to perform with the entrenching tool.
Description: The Mattax has a two-sided metal head between 9-11 inches long: one side is a mattock and the other side is an ax. It comes with a carrying case which can be affixed to the equipment belt or pack. It has a 24-inch handle constructed of wood. The handle is replaceable and separable from the head. Normally one man in the fireteam will have this tool. This tool is for use with the entrenching tool. It will assist in loosening hard ground and chopping through roots.
General Characteristics, Mattax
Production Rate:
2,542 in FY 94; 6,126 in FY 95
Length:
22 inches
Width:
12 inches
Height:
2.25 inches
Weight:
4.5 pounds
Unit Replacement Cost:
$22.50
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David
Sat January 3, 2004 9:09pm
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M49 Telescope
Function: Daytime telescope for making ground observations.
Description: The M49 Observation Telescope is a 20-power daytime telescope. The telescope is used for making ground observations of a target area and effectiveness artillery fire. Having no reticle, it is not used as a sighting device. Associated equipment is the M15 Tripod which has adjustable metal legs and a carrying strap. It allows for full rotation of the mounted telescope. The basic components of the M49 are the objective assembly, body tube, prism housing assembly, and eyepiece assembly with focusing sleeve. The front end of the body tube extends 3/4 of an inch beyond the objective, thereby providing a permanent sunshade. The telescope is furnished with an objective cover and an eyepiece cover cap which are screwed in place to protect the lenses when the telescope is not in use.
History: The M49 has seen several decades of general purpose use as a daytime observation device. Its most common application is in the scout/sniper section of the infantry battalion where it is used to detect and identify targets.
General Characteristics, M49 Telescope
Manufacturer:
IMO, VARO, Garland, Texas and various other vendors
Length:
13.5 inches (34.29 centimeters)
Weight (Without Tripod):
2.75 pounds (1.25 kilograms)
Magnification:
20x
Unit Replacement Cost:
$511
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David
Sat January 3, 2004 9:38pm
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An-124 Condor
Function: High payload, long range cargo aircraft.
History: Introduced in 1982 as a long range, heavy lift cargo and troop transport aircraft, the Antonov An-124 Ruslan (NATO designation Condor) is currently the world's largest and heaviest payload aircraft in production in the world. Outclassing the C-5 Galaxy by nearly 20 tons in payload capacity, and the Ilyushin Il-76 by more than 100 tons, the An-124 is only exceeded in lifting ability by the special purpose An-225 Mriya (NATO designation Cossack) which was purpose built to transport the Russian space shuttle, and of which only two were built.
Currently in production at the AVIASTAR facility in Ulyanovsk and the AVIANT State Aviation Plant in Kiev, the An-124, in addition to serving with the Russian military as a long range high payload cargo aircraft capable of delivering or airdropping troops, and equipment, is also in service with a number of civilian organizations as a dedicated cargo transport. Antonov Airlines, Volga-Dniepr, and Poliot all employ the An-124, using it to transport heavy and over sized equipment such as hydraulic turbines, mobile cranes, railway locomotives, earthmovers and dump trucks, and sailing vessels. The An-124 is even capable of transporting other aircraft, ferrying partially disassembled passenger planes to customers worldwide.
To facilitate the loading and unloading of cargo, the nose section is hinged to open upwards, and the tail section is fitted with a pair of clamshell doors. Both nose and tail sections are equipped with integral loading ramps. In addition, the An-124 also employs two traveling cranes, two winches, a rollgang and tie down equipment which limit it's dependence on ground equipment for cargo handling and manipulation. The Ruslan is equipped with multi leg, self-orienting landing gear and is rough surface capable. The landing gear height can be adjusted on the ground, to facilitate loading cargo.
In addition to the An-124-100 currently in production, Air Foyle (UK) in conjunction with Antonov and Aviastar has proposed the construction of two new versions, the An-124-210, and the An-124-100M. Both versions will be equipped with Western and Russian digital instruments and displays which will reduce the crew size from 6 to 4. In addition, both will be equipped with a traffic alert collision and avoidance system, ground proximity warning system and a satellite communications system. The 210 will be outfitted with Rolls-Royce RB211-52H-T engines, while the 100M will be equipped with the Series 3 D-18 engines, produced by the Progress Design Bureau in Zaporozhe. Each of these engine upgrades will increase the Ruslan's range by 10% and reduce take off distance.
Description: Typical of most cargo aircraft, the An-124 body forms a thick oval cross-section, with a tapered aft section and rounded nose to facilitate cargo handling. The fuselage is of a twin deck design, the upper deck being the flight deck, and the lower deck serving as the cargo hold. On the flight deck are the cockpit, with stations for the six crewmembers, a relief crew compartment, and seating for an additional 88 passengers. The loadmaster's station is on the cargo deck.
The wings are mounted high on the fuselage at a negative dihedral, are tapered and swept, with a relatively high cross-section to increase efficiency and range. The four Lotarev D-18T turbofans are mounted on pylons underneath the wings. The horizontal stabilizers are also swept back and tapered, and are mounted at mid level on the fuselage, aft of the vertical stabilizer.
General Characteristics, AN-124 Condor
Power Plant:
Four D-18T turbofans (An-124-100)
Four D-18T Series 3 (An-124-100M)
Four RB211-524H-T (An-124-210)
Thrust:
229 kN (153,558 pounds)
An-124-210: 264 kN (177,027 pounds)
Length:
69.1 meters (226.4 feet)
Height:
21.08 meters (69.2 feet)
Wingspan:
73.3 meters (240.5 feet)
Cargo Hold Dimensions:
Floor length including ramps: 36.5 meters
Width at floor level: 6.4 meters
Height: 4.4 meters
Volume cargo hold: 1,270 cubic meters
Speed:
800 to 850 kmh
Cruise speed at an altitude of 9 km: 750 to 800 kmh
Ceiling:
12,000 meters (39,370 feet)
Load-Carrying Capacity:
120 tons using a 2,800 meter runway (2300 meters for An-124-210)
150 tons using a 3,000 meter runway (2500 meters for An-124-210)
Maximum Takeoff Weight:
392 tons
Range:
With maximum fuel: 13,300 kilometers (7,980 miles) (15,250 for An-124-210)
With 40-ton payload: 10,960 kilometers (6,576 miles) (12,730 for An-124-210)
With 120-ton payload: 5,030 kilometers (3,018 miles) (5,950 for An-124-210)
Crew:
Seven (An 124)
Four (An-124-100)
Four (An-124-100M)
Three (An-124-210)
Runway:
3000 meters (2,420 for An-124-210)
Takeoff run on concrete runway: 2520 meters (2,420 for An-124-210)
Landing roll on concrete runway: 900 meters
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David
Sat January 3, 2004 9:38pm
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MiG-21 Fishbed
Function: High performance Cold War era air combat and air superiority fighter.
History: Originally designed as a replacement for the MiG-19 Farmer, the Mikoyan-Gurevich Design Bureau passed on sophisticated technology in favor of pure airframe performance using solid, reliable technology which was easy to maintain. The end result was Soviet workhorse capable of performing a wide variety of missions, from close air support, to tactical aerial reconnaissance to air superiority and air combat. The MiG-21 design has been so successful that more MiG-21s have been produced than any other fighter aircraft and, 25 years after its introduction, it is still in production in a number of countries. The first prototype flew in 1955 and its existence was made public in 1956. Conceived as high performance daylight fighter-interceptor, the Fishbed sacrificed endurance and all weather capability for pure speed and aerobatic performance. Although the MiG-21 lacked the ordinance capacity of its contemporaries, the F-4 Phantom II and the F-105 Thunderchief, it was more maneuverable, and because of its simple design, it was both easier and cheaper to maintain by the cash poor countries which purchased it.
Since its introduction over 15 different variants of the Fishbed have been produced. Initial prototypes MiG-21s (Fishbed-B) were armed with two NR-30 30mm cannons but this was reduced to one in later (Fishbed-C) production runs as the Soviet Union followed the West in converting fighters from gun to missile platforms. In addition to eliminating one of the cannons, the Fishbed-C had an increased internal fuel capacity and launch rails for two AA-2 Atoll IR Missiles or rocket pods for ground support missions. The Fishbed-D eliminated the internal cannon armament while increasing internal fuel load as well as redesigning the Spin Scan radar located in the movable nose cone. The Fishbed-E is essentially a sub variant of the D model, incorporating a number of minor modifications, including the reintroduction of a cannon armament in the form of a GP 9 gun pod. The Fishbed-F was the final "first generation" production aircraft. In addition to improvements in the fuselage, internal fuel capacity and control surfaces, the F model incorporated a new radar which allowed it to fire semi-active medium range radar homing air to air missiles.
The "Second Generation" MiG-21s represented a divergence from the original lightweight fighter concept. These aircraft would be characterized by larger fuel loads, more advanced electronics, greater ordnance capacity, and better performance. The first of the "Second Generation" aircraft were the Fishbed-H, a dedicated reconnaissance and offensive electronic warfare variant, and the Fishbed-J, which dispensed with the GP 9 pod in favor of a single, internally mounted GSh-23L 23mm cannon. Wing pylons were also increased from two to four. The last of the "Second Generation" MiG-21s introduced was the Fishbed-H which was similar to the J but featured a greatly enlarged dorsal spine which housed additional fuel. Unfortunately this increased weight so reduced performance that its carrying capacity had to be cut by 50 percent.
"Third Generation" Fishbeds represent the final iteration of MiG-21 evolution. Though "Third Generation" aircraft represent a real improvement over earlier versions, in comparison to current aircraft, the lack of a Beyond Visual Range (BVR) missile capability, poor endurance and poor slow speed/high G handling limit its combat utility. The Fishbed-L was the first of the next generation aircraft, incorporating numerous technological improvements, and was designed with low altitude performance in mind. Though the MiG-21 remains in limited production in a number of countries, the Fishbed is likely to remain in service for many more years, thanks to an aggressive aftermarket product improvement program. Many countries, such as Israel, Russia, India, and China offer aftermarket upgrade packages, where countries can refit older versions of the MiG-21 with more advanced, to include Western technology, components.
General Characteristics, MiG-21 Fishbed
Designer:
Mikoyan-Gurevich Design Bureau
Power Plant:
Fishbed-F: one Tumanskii R-11F2S-300 turbojet rated at 8,600 pounds thrust dry and 13,613 pounds thrust on afterburner
Fishbed-J: one Tumanskii/Gavrilov R-13-300 turbojet rated at 8,972 pounds thrust dry and 14,307 pounds thrust on afterburner
Fishbed-L: one Tumanskii R-25-300 turbojet rated at 9,038 pounds thrust dry and 15,653 pounds thrust on afterburner; the R-25-300 is capable of producing 21,825 pounds of thrust above Mach 1 and up to 13,000 feet for periods of up to three minutes
Length:
12.285 meters (40 feet, 3.9 inches)
Height:
4.125 meters (13 feet, 6.2 inches)
Wingspan:
7.154 meters (23 feet, 5.7 inches)
Speed:
Fishbed-F: 2,125 kmh (1,320 mph) at 11,000 meters (36,090 feet)
Fishbed-J: 2,230 kmh (1,385 mph) at 11,000 meters (36,090 feet); maximum level speed at sea level 1,300 kmh (807 mph)
Fishbed-L: 2175 kmh (1,351.5 mph) at 13000 meters (42,650 feet)
Ceiling:
Fishbed-F: 19,000 meters (62,335 feet)
Fishbed-J: 18,200 meters (59,711 feet)
Fishbed-N: 17,500 meters (57,415 feet)
Weight:
Fishbed-F: 5,350 kilograms (11,795 pounds) empty
Fishbed-J: 5350 kilograms (11,795 pounds) empty
Fishbed-N: 5450 kg (12,015 pounds) empty
Maximum Takeoff Weight:
Fishbed-F: 9,080 kilograms (20,018 pounds)
Fishbed-J: 9,400 kilograms (20,723 pounds)
Fishbed-N: 10,400 kilograms (22,928 pounds)
Range:
Fishbed-F: Maximum ferry range with one external fuel tank 1300 kilometers (808 miles)
Fishbed-J: Maximum ferry range with three external fuel tanks 1,800 km (1,118 miles)
Fishbed-N: Maximum ferry range with one external fuel tank 1,470 km (913 miles)
Crew:
One
Armament:
Fishbed-F: One NR-30 30mm cannon in an external pod plus either two AA-2 short range Infrared homing air to air missiles or up to 500kg (1,100 pounds) of external ordnance on two pylons
Fishbed-J,N: One GSh-23L internally mounted 23mm cannon plus either four air to air missiles or up to 2000 kilograms (4,409 pounds) of external ordnance carried on four pylons
Date Deployed:
1956 (Fishbed-C)
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David
Sat January 3, 2004 9:38pm
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Su-35 Flanker
Function: Multi role air superiority, ground attack fighter.
Description: Developed as a variant to the Su-27 Flanker B, the Su-35 is an improved version of the earlier aircraft, incorperating many of the new systems found on the Su-34 strike aircraft. These improvements include improved offensive and defensive avionics, movable forward mounted canards for increased maneuverability, an advanced pulse doppler pased array radar in the nose as well as a rearward facing radar capqable of detecting, tracking, and directing R-73 or R-77 AAMs at persuing enemy aircraft.
General Characteristics, Su-35 Flanker
Designer:
Sukhoi Design Bureau
Power Plant:
Two Lyulka AL-31FM afterburning turbofans
Thrust:
30,855 pounds each
Length:
22.18 meters (72.76 feet)
Height:
6.84 meters (22.44 feet)
Wingspan:
15.16 meters (49.73 feet)
Speed:
2,500 kmh (1,553 mph) at 30,000 feet
Ceiling:
18,000 meters (59,055 feet)
Weight:
23,249 kilograms (51,257 pounds) empty
Maximum Takeoff Weight:
44,359 kilograms (97,796 pounds)
Range:
4,200 kilometers (2,610 miles)
Crew:
One
Armament:
One GSh-30-1 30mm internally mounted cannon with 150 rounds of ammunition
8,000 kilograms (17,635 pounds) of external ordinance including missiles, rockets, gravity bombs, and guided munitions carried on 11 hardpoints
Date Deployed:
1996
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David
Sat January 3, 2004 9:38pm
Rating: 8
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Il-76 Candid
Function: Medium range, medium lift cargo aircraft.
History: The Ilyushin Il-76 (NATO designation Candid) was fielded by the Soviet Air Force in 1974 as a medium range, medium payload, rough surface capable cargo aircraft. Produced by the Ilyushin Aviation Complex Joint Stock Company in Moscow and the Tashkent Aircraft Production Corporation in Tashkent, Uzbekistan, the Il-76 was purpose built as a combat support aircraft who's primary mission was to deliver infantry and light armored vehicles. The Il-76 is also paratrooper capable, and can air deliver palletized cargo and specially prepared military vehicles.
To facilitate rough field operations, the Il-76 is equipped with a low ground pressure landing gear system and extendable trailing flaps and leading edge slats on the wings to generate additional lift at low airspeeds. To support airborne cargo delivery missions, the Candid is equipped with a telpher; an over-head electrically operated track from which cargo can be suspended and deployed, as well as a deck mounted roller conveyer system. The Il-76 can also be converted to a litter capable airborne ambulance.
Since its introduction, the Il-76 has undergone a number of modifications. The Il-76M is virtually identical to the base line Il-76 in terms of physical appearance, and flight characteristics, but with almost twice the payload capacity (47 tons for the M model, up considerably from the 28 tons of the basic model.) The Il-76MD is essentially an Il-76M with structural modifications to increase fuel load and range. The additional fuel carried increased the MD's maximum take off weight by 20 tons, and increased the range of the aircraft by 40%. The Il-76MF variant incorporates a 6.6-meter insertion into the fuselage to increase cargo hold dimensions, as well as improved engines, replacing the four D-30KP turbofan engines with four more powerful PS-90A-76 turbofans. These new engines improve range by 20% over the MD model. The MF's maximum take off weight has been increased to 210 tons, and the maximum payload has been increased to 52 tons.
In addition to serving as a cargo aircraft, the basic Il-76 design has been modified to fill a number of additional aircraft requirements. The A-50 Mainstay Airborne Early Warning radar aircraft is derived from the Il-76 design, and the Il-78 Midas aerial tanker is derived from a modified MD airframe.
Description: As with most cargo aircraft, the Il-76 body was designed to maximize available space. The fuselage is long and more rounded in cross-section than the more contemporary An-124 Condor, with a tapered aft section and rounded nose. The tail has a pair of clamshell doors and integral loading ramp for cargo. The nose, un-like the C-5 Galaxy or the An-124 Condor, is fixed, and the lower section is glassed in for observation. Directly behind the glass nose section is an oval radome, which extends laterally beyond the sides of the frame.
The wings are mounted high on the fuselage at a slight negative dihedral, and are tapered and swept. The four turbofans are mounted on pylons underneath, and forward of the wings. The horizontal stabilizers are also swept back and tapered, and are mounted high on the vertical stabilizer.
Designed as a combat aircraft, the Il-76 is capable of mounting an electronic warfare ECM package, to include radar warning receiver, and chaff and flare dispensers, to defend the aircraft from radar guided and heat seeking missile threats, and is capable of mounting air dropped ordnance on external, wing mounted ejector racks. In addition, the tail section incorporates a manned weapons station, mounting two 23mm cannons and a fire direction radar. This tail gun station is retained on many Russian owned, civilian operated Il-76s, as they were expected to serve with the Air Force during a time of war.
General Characteristics, Il-76 Candid
Power Plant:
Four D-30KP turbofans
Thrust:
12,000 kef
Length:
46.6 meters (152.9 feet)
Height:
14.42 meters (47.31 feet)
Wingspan:
50.5 meters (165.7 feet)
Cargo Hold Dimensions:
Length (less ramp): 20 meters
Width: 3.45 meters
Height 3.4 meters
Speed:
Cruise speed at an altitude of
9 to 12 kilometers: 760 to 780 kmh
Ceiling:
20,695 meters (67,900 feet)
Load-Carrying Capacity:
47 tons
Maximum Takeoff Weight:
170 tons
Range:
With 20-ton payload: 6,100 kilometers (3,660 miles)
With 47-ton payload: 3,000 kilometers (1,800 miles)
Crew:
Six or seven
Runway:
Takeoff run on concrete runway: 1,600 meters
Landing roll on concrete runway: 780 to 1,000 meters
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David
Sat January 3, 2004 9:38pm
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MiG-25 Foxbat
Function: High speed, high altitude strategic bomber interceptor.
History: Designed in 1962 as a purpose built interceptor to combat the American XB-70 Valkyrie supersonic strategic bomber as well as other high altitude, high speed threats, the MiG-25, was and offically still is, the fastest production fighter aircraft ever built. Possessing a rudimentary yet powerful long range missile guidance radar and completely lacking in air combat maneuverability, the Foxbat relies on ground control radars for guidance and its incredable speed to rapidly close in on and engage threat aircraft.
Although the XB-70 was eventually dropped by the U.S. Air Force, production of the MiG-25 continued, with a reconnosance variant, the MiG-25R, entering service in 1968 and a bomber variant, the MiG-25RB, and a fighter variant, the MiG-25P, being introduced in 1970. The latest version of the Foxbat, the MiG-25PD, incorperates improved engines and fire control radar, and is still in service with the Russian Airforce and being produced for export.
General Characteristics, MiG-25 Foxbat
Designer:
Mikoyan-Gurevich Design Bureau
Power Plant:
Two Soyuz/Tumansky R-15BD-300 afterburning turbojets
Thrust:
24,700 pounds each
Length:
23.82 meters (78.17 feet)
Height:
6.1 meters (20 feet)
Wingspan:
14.02 meters (46 feet)
Speed:
1,200 kmh (745 mph) at sea level
3,000 kmh (1,865 mph) at 30,000 feet)
Ceiling:
20,695 meters (67,900 feet)
Weight:
19,999.8 kilograms (44,092 pounds) empty
Maximum Takeoff Weight:
36,199.8 kilograms (79,807 pounds)
Range:
1,730 kilometers (1,075 miles)
Crew:
One
Armament:
Two R-23 and two R-40 Air to Air Missiles (AAM), or four R-60 AAMs, or four R-73A AAMs
Date Deployed:
1968
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David
Sat January 3, 2004 9:38pm
Rating: 10
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Su-25 Frogfoot
Function: Dedicated Close Air Support (CAS) ground attack fighter.
History: Introduced in 1980, the Su-25 Frogfoot was the first dedicated ground attack aircraft produced by the Soviet Union since the World War Two era propeller driven Il-2 Shturmovik. drawing heavily on lessons learned by the American Air Force during the vietnam war, and mirroring the performance of the American A-10 Warthog, the Frogfoot is a rugged aircraft capable of accuratly delivering a heavy payload from low altitude and surviving in the low level, high threat forward area environment. Though the Sukhoi Design Bureau originally sought to rely on speed to survive, it was determined that increased speed reduced the low level battlefield effectiveness of the aircraft. In short, if the aircraft was to perform its job effectivly, it would have to be capable of operating at low speeds; speed would be sacrificed for low speed maneuverability and heavy armor.
After several design changes, the first prototypes were approved in 1980. The first production Frogfoots were equipped with twin multi-fuel non afterburning turbojet engines, a twin barreled internally mounted 30mm cannon, titanium armor around the pilot and control surfaces, and foam filled, non-explosive self sealing fuel cells. The Su-25 was equipped with eleven underwing and under body hard points, was capable of delivering 4000 kilograms (8,818 pounds) of ordnance and could be operated off of unimproved dirt strips.
Following combat experience in Afganistan, an improved version, the Frogfoot-B, was fielded in 1984. The B model was a production modified version of the two seat Frogfoot-A trainer. The second seat was removed, as was the internal gun, and additional fuel, armor, and avionics were installed, in addition to an improved 30mm cannon, mounted in an external pod. In addition, the Frogfoot's lack of all weather, night time capability was addressed by incorperating a Forward Looking Infra Red (FLIR) low light navigation system as well as a TV camera and laser designator, spot tracker and rangefinding package.
Although the Frogfoot has been out of production for a number of years, it still remains in front line service with Russia's Frontal Aviation as well as many export nations, including Iraq.
General Characteristics, Su-25 Frogfoot
Designer:
Sukhoi Design Bureau
Power Plant:
Two MNPK Tumanskii R-195 turbojets
Thrust:
9,921 pounds thrust each
Length:
15.53 meters (50 feet, 11.5 inches)
Height:
4.80 meters (15 feet, 9 inches)
Wingspan:
14.36 m (47 feet, 1.4 inches)
Speed:
950 kmh (590 mph) at sea level
Date Deployed:
1980
Ceiling:
7,000 meters (22,965 feet)
Weight:
9,800 kilograms (21,605 pounds) empty
Maximum Takeoff Weight:
18,600 kilograms (41,005 pounds)
Range:
Combat radius 495 kilometers (308 miles)
Crew:
One
Armament:
One AO-17A 30-mm twin barreled cannon
4,000 kilograms (8,818 pounds) of external ordinance including missiles, rockets, gravity bombs, and guided munitions carried on 11 hardpoints
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David
Sat January 3, 2004 9:38pm
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Shenyang J-8 (F-8 Finback
Function: Twin-engined, single-seat aircraft is primarily used for air combat, with the capability of ground attack.
History: Introduced in 1964, the J-8 was the first People's Liberation Army Air Force (PLAAF) aircraft utilizing a wholly Chinese design. While similar in configuration to the Soviet MiG-21 or the Chinese J-7, the J-8 airframe has been enlarged to accommodate two engines. Although the design was approved in 1964, prototype production was not completed until 1969. Because of the civil unrest caused by the Cultural Revolution (1966-76), the prototypes would see only limited flight activity through 1976, delaying production further. Production of the J-8 began in December 1979, with very few airframes actually entering service. These first-run aircraft were equipped with a single axial air intake supplying air to both engines, with a centrally mounted ranging radar, which gave the aircraft an appearance similar to the Mig-21/J-7. These aircraft were also equipped with two Type 30 30mm cannons and four under wing hardpoints, capable of firing the PL-2B short-range air-to-air missile. First-run production was completed in 1987.
The second run J-8 I "Finback A" entered production in 1985. Similar to the original J-8, the J-8 I had an improved radar which gave it all-weather capability. In addition, the two 30mm cannons were replaced by a single twin-barreled 23mm cannon. Production was halted in 1987 after some 100 aircraft were built (including original J-8 aircraft converted to the J-8 I design).
The completely redesigned J-8 II "Finback B" was first flown in 1984 and made public in 1986. The forward section of the airframe has been completely redesigned, replacing the single combination air intake-radome with two separate intakes, mounted laterally on the fuselage just aft of the cockpit, and a solid nose housing the aircraft's search radar. The solid nose also increases the amount of space available for additional after-market avionics. The J-8 II also incorporates a ventral stabilizer fin for increased maneuverability, which can folded for takeoff and landing. The export model of the J-8 II, designated the F-8 II, has improved avionics, to include digital electronics, a Heads Up Display (HUD), and Doppler radar, and engines, along with leading edge slats and in-flight refueling capabilities, giving it improved performance characteristics.
The J-8 IIM is a private venture (sponsored by Shenyang Aircraft Company) to improve the performance, and marketability, of the Basic J-8 II design. The J-8 IIM is capable of launching a variety of air-to-air and air-to-ground ordnance, including the PL-8, R-27/AA-10 and PL-5B. In addition, conventional iron bombs can be carried on seven hardpoints. The J-8 IIM also incorporates the advanced Russian made Zhuk-8II (FG-8) look-down, shoot-down radar, which replaces the older Chinese Type-208 radar. The Zhuk-8II has a range of 70 nautical miles, is able to track up to 10 targets at once and engage 2 targets simultaneously with radar-guided missiles such as the AA-10, as well as to launch anti-ship missiles such as the Kh-31. While the J-8 IIM also incorporates improved engines, the J-8 IIM is actually heaver than the baseline model, so aircraft range and performance are down slightly. Though the J-8 IIM completed its first test flight in 1998, none have been exported.
The most recent variant of the J-8 introduced, the J-8D, appears to be a basic J-8 II modified with a fixed in-flight refueling probe. In addition, it would seem that the avionics package has been upgraded to allow the ability to fire the PL-8 IR missile and the PL-11 semi-active radar guided missile.
Description: The basic J-8 design is very similar in appearance to the Soviet MiG-21 and Chinese J-7 aircraft, with the modified delta wing, swept horizontal and vertical stabilizers and central combination air intake-radar housing. The J-8's laterally mounted twin engines, however, readily give it away, the twin exhausts easily visible below and aft of the vertical stabilizer. The J-8 II replaces the MiG-21 forward section with a completely new design, incorporating the same single seat stepped cockpit, but with a solid nose and two laterally mounted, one on each side of the fuselage, square air intakes. The back half of the J-8 II, however, remains largely unchanged from the original J-8 design.
General Characteristics, Shenyang J-8 (F-8 Finback)
Country:
People's Republic of China
Designation:
Jian-8 Finback
Type:
Intercept
Builder:
Shenyang Aircraft
Power Plant:
Two open 13A-II turbojets at 14,815 pounds thrust
Length:
70 feet, 10 inches (21.6 meters)
Wingspan:
30 feet ( 9.3 meters)
Weight:
Empty: 21,600 pounds (9,820 kilograms)
Normal Takeoff: 31,500 pounds (14,300 kilograms)
Maximum Takeoff: 39,200 pounds (17,800 kilograms)
Speed:
Maximum Speed: 1,450 mph (2,340 kmh, Mach 2.2)
Cruising Speed: 800 mph (1,300 kmh)
Ceiling:
18-20,000 meters
Range:
Combat Radius: 2,500 miles (800 kmh)
Cruise Radius: 800 miles (1,300 kilometers)
Ferry Range: 1,400 miles (2,200 kilometers)
Internal Fuel Capacity:
3994 kilograms
Armament:
Two 23mm cannons (J-8 only; not found on J-8II)
One underfuselage hardpoint
Six underwing hardpoints for fuel, bombs, rockets or missiles
Four PL-2 or PL-7 and 800 L drop tank (680 nm)
Two PL-2 or PL-7 and two 480 L drop tanks and one 800 L drop tank (741nm)
Sensors:
Izmurd raging radar
RWR
Ballistic bomb sight
Crew:
One
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David
Sat January 3, 2004 9:38pm
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Su-37 Flanker
Function: Multi role air superiority, ground attack fighter.
Description: Developed as an improved version of the basic Su-27 Flanker designed, the Su-37 is based on the Su-35 airframe but with thrust vectoring nozzles to give it unsurpassed maneuverability. In addition to providing more power than previous engines, the engines on the Su-37 utilize steerable nozzles which can vector the engine thrust through +/- 15 degrees of travel in the vertical axis. This thrust vectoring is fully intigrated with the aircraft's flight control systems, and requires no input or manipulation by the pilot. In the event of a system failure, an emergency system will return the nozzles to their normal position. Other modifications to the Su-37 include improved offensive and defensive avionics, an improved pulse doppler phased array radar in the nose as well as the rearward facing radar already present on the Su-34 and 35.
General Characteristics, Su-37 Flanker
Designer:
Sukhoi Design Bureau
Power Plant:
Two Lyulka AL-37FU vectored thrust afterburning turbofans
Thrust:
30,855 pounds each
Length:
21.94 meters (71.98 feet)
Height:
6.84 meters (22.44 feet)
Wingspan:
15.16 meters (49.73 feet)
Speed:
2,440 kmh (1,516 mph) at 30,000 feet
Ceiling:
18,000 meters (59,055 feet)
Weight:
18,400 kilograms (40,565 pounds) empty
Maximum Takeoff Weight:
33,999 kilograms (74,956 pounds)
Range:
3,500 kilometers (2,175 miles)
Crew:
One
Armament:
One GSh-30-1 30mm internally mounted cannon with 150 rounds of ammunition
8,200 kilograms (18,075 pounds) of external ordinance including missiles, rockets, gravity bombs, and guided munitions carried on 11 hardpoints
Date Deployed:
Still under development
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David
Sat January 3, 2004 10:02pm
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ZPU-4 14.5mm Anti-Aircraf
Function: Lightweight towed anti-aircraft gun.
Background:Introduced in 1949 the ZPU-4 is a quad version of the basic Soviet 14.5mm machine gun. The ZPU-4 saw service with North Korea during the Korean War and with Iraq during the Gulf War. During the Vietnam war the ZPU-4 was considered to be the most dangerous anti-helicopter weapon of the war. Exported to numerous countries worldwide, the ZPU-4 was also manufactured in China as the Type 56.
Description: The ZPU-4 system is made up four air-cooled, fully automatic 14.5mm machineguns mounted on a 4 wheeled, two axle chassis. While the ZPU-4 may be fired while limbered for traveling, the gun can be jacked off of the ground, using built in leveling jacks, for increased stability.
General Characteristics, ZPU-4 14.5mm Anti-Aircraft Gun
Length:
4 feet (1.2 meters)
Width:
5 feet (1.5 meters)
Height:
6 feet (1.8 meters)
Weight:
1 ton
Rate of Fire:
550-600 rounds per minute, per gun.
Maximum Range:
1,400m vs. air targets
Introduction Date:
1949
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