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General Dynamics FIM-43 Redeye Missile The General Dynamics FIM-43 Redeye was a man-portable surface-to-air missile system. It used (More) The General Dynamics FIM-43 Redeye was a man-portable surface-to-air missile system. It used infrared homing to track its target. Production was terminated in September 1969 after about 85,000 rounds had been built - in anticipation of the Redeye II, that would later become the FIM-92 Stinger. The Redeye was withdrawn gradually between 1982 and 1995 as the Stinger was deployed. Development In 1948 the United States Army began looking for new infantry air-defense weapons, as machine guns were proving ineffective against new fast jets. Several gun/rocket systems were investigated but none showed enough promise to pursue. In the mid 1950s Convair began studies of a man portable infrared guided missile. In November 1956 the results of these studies were shown to the US Army and USMC. In 1957 official requirements were formulated, and in 1958 Convair was awarded a contract to start development of the system. In July 1959 the development project began, in March 1960, the first test rounds were fired. Launches from a launch tube followed in May 1961, with a shoulder launch occurring in 1961. Technical problems prevented the missile entering full production: the missile did not live up to its specifications - being slower, less manoeuverable and less accurate. During the testing, substantial use was made of the Atlantic Research MQR-16 Gunrunner expendable target missile. Limited production began as XM41 Redeye Block I. The missile was designated XMIM-43A in June 1963. Block I systems were then evaluated between 1965 and 1966. Block II systems designated XM41E1 began development in 1964, the missile being designated XMIM-43B. The missiles were delivered in April 1966, and included a new gas-cooled detector cell, a slightly redesigned launcher and an improved warhead. In 1965 to 1966 General Dynamics developed the final Redeye Block III configuration, designated at first XM41E2 with XFIM-43C missiles. The missiles retained the seeker from the Block II missile, but included a new rocket motor, warhead and fuse. The launcher also now had an XM-62 open sight and upgraded electronics. The new missile could turn at up to 3g. The missile achieved a kill probability against F9F tactical drones travelling at 430 knots at an altitude of 100 meters of 0.51. From this it was calculated that the kill probability versus a MiG-21 at similar altitude would be 0.403, and 0.53 against helicopters. Kill probability against larger propeller driven aircraft like the AN-12 was estimated at 0.43. Production of the Block III systems began in May 1967. In 1968 Block III was finally declared operational. History Redeye missiles were delivered to the Mujahideen by the US during the Soviet invasion of Afghanistan in 1984, where they were used to shoot down a number of aircraft including several Su-25 jets as well as Mi-24 and Mi-8 helicopters. By November 1985 it had largely been replaced by the dramatically more successful FIM-92 Stinger missiles. The Redeye was known as Hamlet in Danish service. Description The missile is fired from the M171 missile launcher. First the seeker is cooled to operating temperature, the operator then begins visually tracking the target - using the sight unit on the launcher. Once the target is locked onto by the missile a buzzer in the launcher hand grip begins vibrating, alerting the operator. The operator then presses the trigger, which fires the initial booster stage and launches the missile out of the tube at a speed of around 80 feet per second (25 m/s). As the missile leaves the tube spring-loaded fins pop out, 4 stabilizing tail fins at the back of the missile, and two control surfaces at the front of the missile. Once the missile has traveled six meters, the sustainer motor ignites. The sustainer motor takes the missile to its peak velocity of Mach 1.7 in 5.8 seconds. 1.25 seconds after the sustainer is ignited, the warhead is armed. The missile's seeker is only capable of tracking the hot exhausts of aircraft, which limits the engagements to tail-chase only. The missile's blast fragmentation warhead is triggered by an impact fuze requiring a direct hit. As a first generation missile it is susceptible to a variety of countermeasures including flares and hot brick jammers. In addition, its inability to manoeuver at a rate greater than 3 G means that it can be simply out turned if it is spotted. Data for FIM-43C: Length: 1.20 m (3 ft 11.5 in); M171 launcher: 1.26 m (4 ft 1.7 in) Finspan: 14 cm (5.5 in) Diameter: 7 cm (2.75 in) Weight: 8.3 kg (18.3 lb); M171 launcher: 5 kg (11 lb) Speed: Mach 1.7 Ceiling: 2740 m (9000 ft) Range: 4500 m (14800 ft) Propulsion: Atlantic Research M115 solid-fueled rocket motor; consisting of - Booster (Ejector): 3.3 kN (750 lb) for 0.048 s - Sustainer: 1.1 kN (250 lb) for 5.8 s Warhead: M222 1.06 kg (2.35 lb) blast-fragmentation (Less)
ARES Mars Aircraft Aerial Regional-scale Environmental Survey of Mars (ARES) Critical science goals: Crustal (More) Aerial Regional-scale Environmental Survey of Mars (ARES) Critical science goals: Crustal Magnetism: ARES enables an improved understanding of the detailed nature of crustal magnetism on Mars and modeling of Mars' crustal evolution, tectonic history and the chronology of its dynamo. Atmospheric Boundary Layer Composition, Chemistry and Dynamics: ARES enables an improved understanding of the near-surface atmospheric composition, chemistry and dynamic behavior, and the chemical coupling between the surface and atmosphere, with unprecedented accuracy and range. Near-Surface Water: ARES enables an improved understanding of water equivalent hydrogen abundance and its relationship to inferred near-surface water and hydrated minerals. From its unique vantage point 1.5 km above the surface of Mars, ARES will target and explore up to 610 km of diverse terrain in the Southern Highlands. Science data will be returned to Earth on the day of flight for immediate scientific review and public dissemination. ARES Enables a New Class of Science that Complements and Extends the Mars Exploration Program Simultaneous, in-situ, regional-scale measurement of the Mars atmosphere, surface, and interior Bridges critical scale and resolution measurement gaps of remote sensing and surface exploration Scout for future sample return and surface mission site selection. Magnetic survey with spatial resolution two orders of magnitude higher than provided by Mars Global Surveyor, with ability to resolve the crustal magnetism source structure High-resolution measurements that cannot be achieved from orbit Geologic diversity from regional-scale coverage that cannot be achieved by surface missions In-situ atmospheric science Ability to traverse terrain inaccessible to surface vehicles Ability to precisely target science features Ability to execute a controlled, pre-planned aerial survey pattern Robust performance with regard to atmospheric uncertainties (Less)
0750669276 
2009-01-20 - extension: rar - size: 3 MB
0750669276
Flight
Dynamics Principles, 2 Ed: A Linear Systems Approach to
Aircraft Stability and Control
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