FIM-43 Redeye Totally Explained

Everything about Fim-43 Redeye totally explained

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 The Redeye was withdrawn gradually between 1982 and 1995 as the Stinger was deployed.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 didn't 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
   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's 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's spotted.

Variants

Block I FIM-43/XFIM-43A/XMIM-43A -
Block II FIM-43B/XFIM-43B/XMIM-43B - Fitted with a gas cooled seeker and improved warhead and fuse and modified launcher.
- XFEM-43B Experimental test missile, with data logging capability
Block III FIM-43C/XFIM-43C Production version - Improved warhead and fuse section, and a new launcher.
- XFEM-43C Experimental test missile, with data logging capability
FIM-43D Upgraded missile, with unknown capabilities.

Comparison chart

System	9K32M Strela-2M (missile: 9M32M)	9K34 Strela-3 (missile: 9M36)	FIM-43C Redeye
Service entry	1968	1974	1968
Weight of system ready to shoot	15 kg	16 kg	13.3 kg
Missile weight	9.8 kg	10.3 kg	8.3 kg
Length	1.44 m	1.47 m	1.40 m
Warhead weight	1.17 kg	1.17 kg	1.06 kg
Warhead type	Directed-energy blast fragmentation	Directed-energy blast fragmentation	Blast fragmentation (M222)
Warhead explosive content	0.39 kg HMX	0.39 kg HMX and small secondary charge	0.36 kg HTA-3
Missile engagement aspect	Tail-chase only	Limited forward hemisphere (all-aspect) capability	Tail-chase only
Seeker type	Uncooled PbS detector element (1–2.8 µm sensitivity range).	Nitrogen-cooled PbS detector element (2–4.3 µm sensitivity range).	Uncooled PbS detector element.
Seeker modulation	AM-modulated (spin scan)	FM-modulated (conical scan)	AM-modulated
Maximum range	4,200 m	4,100 m	4,500 m
Missile speed	500 m/s	450 m/s	580 m/s
Maximum speed target speed	260 m/s (receding)	310 m/s (receding)	225 m/s
Engagement altitude	0.05-2.3 km	0.03-2.3 ... 3.0 km	0.05-2.7 km

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