FIM-43 Redeye

FIM-43 Redeye
Inert FIM-43 Redeye
Type	Man-portable surface-to-air missile
Place of origin	United States
Service history
In service	1967–1995
Used by	SeeOperators
Wars	Vietnam War Soviet–Afghan War Nicaraguan Revolution Lebanese Civil War War in Afghanistan Salvadoran Civil War Mali War
Production history
Designer	Convair
Designed	July 1959
Manufacturer	General Dynamics
Produced	1962–1971
No.built	85,000
Variants	SeeVariants
Specifications (FIM-43 Redeye)
Mass	8.3 kg (18.3 lb)
Length	1.20 m (3 ft 11.5 in)
Diameter	70 mm (2.75 in)
Crew	1
Effective firing range	4,500 m (14,800 ft)
Warhead	M222 Blast-fragmentation
Warhead weight	1.06 kg (2.35 lb)
Detonation mechanism	Impact Fuze
Engine	First stage – Booster (Ejector): 3.3 kN (750 lbf) for 0.048 s Second stage – Sustainer: 1.1 kN (250 lbf) for 5.8 s
Maximum speed	Mach 1.7 (580 m/s)
Guidance system	Infrared homing

TheGeneral DynamicsFIM-43 Redeyeis aman-portablesurface-to-air missilesystem. It uses passiveinfrared homingto track its target. Production began in 1962 and – in anticipation of the Redeye II, which later became theFIM-92 Stinger– ended in the early 1970s (delivery of the last Redeye for the US Army was completed inJuly 1971)after about 85,000 rounds had been built. The Redeye was withdrawn gradually between 1982 and 1995 as the Stinger was deployed, though it remained in service with various armed forces of the world until quite recently,being supplied via theForeign Military Salesprogram. It was initially banned from being sold overseas, to avoid missiles falling into the hands of terrorist organizations. However, after the export ban was lifted, the weapon was never actually used by terrorists against civil aircraft, in contrast with other MANPADS. While the Redeye and 9K32 Strela-2 (SA-7) were similar, the missiles were not identical. Nonetheless, the CIA concluded that the Soviet SA-7 had benefited from the Redeye's development.

Development

Post-war developments

In May 1946, the War Department Equipment Board published a report on the future ofinfantryweapons. They called for the development of new weapons that would be the best in the world, while also being able to be separated into loads of no more than 25 pounds (11 kg).When considering anti-aircraft weapons, they concluded that theM45 Quadmountmounting fourM2 Browningmachine gunswould not be capable against future high-performance aircraft. They published a new requirement for a weapon suitable for engagements between 25 and 2,500 yards (23 and 2,300 m) against targets flying up to 1,000 miles per hour (1,600 km/h).

In response, in June 1948 theUnited States ArmyOrdnance Corps began development of the "Stinger" system, essentially an updated version of the Quadmount mounting four T17 machine guns firing the more powerful0.60round and aimed by an automatedradarsystem. Development on this system continued until 1951, when the requirement was extended to 14,000 feet (4,300 m), which could not be met by the 0.60 round. A new concept using arevolver cannonfiring a new 37 mm round emerged, but proved too complex and was cancelled.

Porcupine and Octopus

At the 1950Tripartite Conferencein London, the US, UK and France agreed that the M2 would remain effective up until about 1960, but new weapons would be needed after that time. This led to development of the Porcupine and Octopus concepts in the US. Porcupine, started in 1951, was a 64-barrel rocket launcher firing salvos of 2.75-inch (7.0 cm)Folding Fin Arial Rockets(FFARs) at an effective rate of 6,000 rounds per minute. The system was never built in complete form, and cancelled in February 1956. Octopus, from 1953, re-examined the.50 and.60 rounds, as well as the emerging 20 mm round based on the latter. This project also failed to deliver an operational system.

By the mid-1950s, new medium and high-altitudesurface-to-air missile(SAMs) were rendering higher altitude flight increasingly dangerous, andattack aircraftwere now expected to fly at low altitudes. This led to a 1954 requirement for a lightweight system able to engage targets from 0 to 1,000 ft (300 m), and larger weapons that raised the ceiling to 10,000 ft (3,000 m). In order to improve its capability in poor visibility, it was suggested that the weapon be aimed usinginfrared homing.

Redeye emerges

In 1955,Convair,recently purchased byGeneral Dynamics,began examining a weapon that would fill both of these requirements.When initial studies proved promising, in January 1956 the company began an 11-month study which they named "Redeye" due to its infrared seeker. To lower prototype costs, the missile would initially be based on the unguided FFAR, which was already in widespread production. This would be turned into a missile by replacing the contact-fused warhead of the FFAR with a new seeker system and smaller 1.2-pound (0.54 kg) warhead.In production models, the motor would be modified to burn only briefly to propel it about 25 feet (8 m) at low speed before firing at full thrust.

The resulting concept mockups were demonstrated to the Army andMarine Corpsin November 1956. Simulations suggested that it would have an average miss distance of 4 to 8 feet (1.2 to 2.4 m), and a direct-hit probability of 0.35 to 0.40.The design proved extremely interesting, and in 1957 official requirements were formulated. This led to the Army'sRedstone Arsenalreceiving several unsolicited proposals for similar weapons from other companies:

• Lancer,a crew-served partially portable surface-to-air missile system, designed by the Drone and Missile Flight Control DepartmentofSperry Gyroscope,Garden City, New York,
• SLAM(Shoulder-Launched Antiaircraft Missile), a man-portable surface-to-air missile system, designed by theAutonetics DivisionofNorth American Aviation,Downey, California,
• an undesignated system byLockheed Missile Systems Division,Sunnyvale, California(Col. James E. Linka, a supervising officer with OCRD Air Defense and Missiles Division, responsible for Stinger, later recalled that Lockheed entered the competition in 1959, but no details were ever disclosed.)

The competing designs were based on various USair-to-air missiles,adapted for ground use and scaled-down to be operated by hand and launched from a disposable tube. The lead that Convair had over these weapons was unapproachable, and their proposal was strongly supported by the Marines, who pressed the Army to begin development. They also suggested that the system would suffer from a number of issues during development related to the airframe and seeker, but felt that these were not enough to hold up development.

On 14 April 1958, the development contract was released and Convair was awarded a contract to start development of the system.

Testing

The original design consisted of a simple tube with a clip-on grip system. The operator would simply point the tube in the general direction of the target, and fire when he heard the seeker make its "growl" sound, indicating it was locked onto the target. In May 1958 six unguided launches were conducted by US Marines atTwentynine Palms proving groundandCamp Pendleton,California,to assesshuman factors and ergonomicsof the new weapon, as well as a trooper's capability to aim and launch a missile from the shoulder safely and accurately towards an imaginary target. In June 1958 theflight testphase of thefeasibility demonstration programbegan.

MICOM Commander General John G. Zierdt inspecting interim Redeye production model, disposable variant (note the optics and launcher design)

In July 1959 the development project began, in March 1960, the advanced 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 maneuverable and less accurate. During the testing, substantial use was made of the Atlantic ResearchMQR-16 Gunrunnerexpendable target missile.

Deficiencies and shortcomings were experienced during the system development phase—mainly seeker inability to discriminate target against cloudy background or in a heavy clutter environment, coupled with absence of night operation capability and inability to engage head-on targets—which were never resolved (eventually leading to the Stinger development). Consequently, several other unsolicited proposals competed with the Redeye in the early 1960s. These included both guided (engaging target using techniques other than infrared homing) and unguided (directionally-controlled) missile systems.

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.

The block I/II launcher above, the block III launcher below

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 infrared 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 newrocket motor,warhead and fuze. The launcher 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 490 mph (800 km/h) at an altitude of 330 ft (100 m) of 0.51. From this it was calculated that the kill probability versus aMikoyan-Gurevich MiG-21at similar altitude would be 0.403, and 0.53 against helicopters (specifically theMil Mi-6and US H-13 and H-21). Kill probability against larger propeller driven aircraft like theAntonov An-12was estimated at 0.43.Production of the Block III systems began in May 1967. In 1968 Block III was declared operational.

History

Fifty Redeye systems were delivered to themujahideenby the United States during theSoviet–Afghan Warin 1984,where they were used to shoot down aircraft including severalSukhoi Su-25jets, as well asMil Mi-24andMi-8helicopters.By November 1986 it had largely been replaced by the dramatically more successfulFIM-92 Stingermissiles.

All Redeye missiles were numbered and inventorized by the US Army Missile Command to prevent them from disappearance or otherwise unnoticed losses.No Redeye missiles were reported lost or stolen from the Army inventory,but losses occurred after Redeyes were supplied to foreign troops. This happened first in Belgium in January 1974, causing a strengthening of security measures in the major West European and British airports.

The Redeye was known asHamletin Danish service and as RBS 69 in Swedish service.

Redeye missiles provided to theFDNby the US were also used by the Nicaraguan "Contras"to shoot down at least four Soviet Mil Mi-8 helicopters during theNicaraguan Revolution.

Description

The missile is fired from the M171 missile launcher. First, the seeker is cooled tooperating temperatureand then the operator begins to visually track 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—four 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. The warhead is armed 1.2 seconds after the sustainer is ignited.

The missile's seeker is capable only of acquiring and tracking the hot exhaust of aircraft, which limits the engagements to tail-chase only, tracking the rapidly receding target. The missile's blast fragmentation warhead is triggered by an impactfuze,requiring a direct hit. As a first-generation missile it is susceptible tocountermeasures,includingflaresand hot brick jammers. Its inability to turn at a rate greater than 3g means that it can be outmaneuvered, if detected.

Variants

One of the earliest designs

Foxhole variant being field-tested

FIM-43C Redeye just after launch

During its development, the weapon underwent several major design changes. Initially, its gripstock was literally just a gripstock with grips, stock and trigger only, later evolved in a separable launch unit with optics, electronics, and battery input.Several designs had no optical sighting device; the gunner was supposed to rely on the auditory alarm when the seeker acquired the target. Those with optical sights differed one from another in shape,field of viewand themagnificationof their optics,and were either separable or non-separable, which in turn could be built-in or molded-in primitive mechanical sight with flashing diodes inside diopter to inform gunner of seeker's lock-on. The launch tube changed its design and shape several times, from pipelike straight-shaped one to the variable-diameter tube with a wider rear section to provide the missile with better acceleration, and back to a straight tube to prevent its explosion due to a critical pressure drop or accidental booster detonation.Canards of the basic missile design were housed within the missile body during the entire flight, coming outside only to correct the course deviation of each roll cycle and folding back within a split second,variable incidence (instead of fixed) canards were used to improve terminal guidance accuracy.The seeker also changed drastically, with multiple modifications made during the test phase,the most important of which making itcooled,increasing its discrimination capability (though extending reaction time in order to adjust its subsystems tooperating temperature,) and reducing the field of view to increase the missile's capability against single engine jets.Among the design improvements made in the seeker gyro were an increased aperture to provide greater sensitivity; a new center post design for supporting the secondary mirror to improve background discrimination; a new gyro gimbal of increased rigidity; an improved lead sulfide cell, doubling its sensitivity; and an improved reticle with a reduced field of view.Unorthodox designs included the "Foxhole Redeye," which was small enough to be stored and fired from a rifleman'sfoxhole,and the "unitized launcher Redeye" fire-and-discard variant as a fully discardable throw-away unit with no separable elements for use with the USMC andCONARCunits.All interim designs were dropped in favor of the one which was considered the best possible choice by the Army Missile Command, and mass-produced at the General Dynamics facilities within theGreater Los Angeles Area.The following is the list, featuring the basic model, designated FIM-43A and approved for production along with its derivatives:

• 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 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 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	33 lb (15 kg)	35 lb (16 kg)	29 lb (13.3 kg)
Missile weight	22 lb (9.8 kg)	23 lb (10.3 kg)	18 lb (8.3 kg)
Length	57 in (1.44 m)	58 in (1.47 m)	55 in (1.40 m)
Warhead weight	2.6 lb (1.17 kg)	2.6 lb (1.17 kg)	2.3 lb (1.06 kg)
Warhead type	Directed-energy blast fragmentation	Directed-energy blast fragmentation	Blast fragmentation (M222)
Warhead explosive content	0.82 lb (0.37 kg)HMX	0.82 lb (0.37 kg)HMX and 0.71 oz (20 g) secondary charge	0.79 lb (0.36 kg)HTA-3
Missile engagement aspect	Tail-chaseonly	Limited forward hemisphere (all-aspect) capability	Tail-chase / limited forward-hemisphere (depending on conditions and version)
Seeker type	Uncooled PbS detector element (1–2.8 μm sensitivity range).	Nitrogen-cooled PbS detector element (2–4.3 μm sensitivity range).	Gas-cooled (FIM-43A: Peltier cooled) PbS detector element
Seeker modulation	AM-modulated (spin scan)	FM-modulated (conical scan)	AM-modulated
Maximum range	13,800 ft (4,200 m)	13,500 ft (4,100 m)	14,800 ft (4,500 m)
Missile speed	1,100 mph (500 m/s)	1,000 mph (450 m/s)	1,300 mph (580 m/s)
Maximum target speed	580 mph (260 m/s) (receding)	690 mph (310 m/s) (receding)	500 mph (225 m/s)
Engagement altitude	160 to 7,500 ft (0.05 to 2.3 km)	100 to 10,000 ft (0.03 to 3.0 km)	160 to 8,900 ft (0.05 to 2.7 km)

Operators

Map with former FIM-43 operators in red

Former operators

Sources:

States

• Australia
• Bosnia and Herzegovina
• Chad
• Croatia
• Denmark
• El Salvador
• Greece
• Israel
• Jordan
• Pakistan
• Saudi Arabia
• Somalia
• Sudan
• Sweden
• Thailand
• Turkey
• United States
• West Germany

Groups

• Afghan Mujahideen
• FAN
• Coordination of Azawad Movements
• ContraGuerrillas
• FMLN

See also

• List of U.S. Army rocket launchers by model number
• SA-7Grail– (Soviet Union)
• Anza– (Pakistan)
• Misagh-2– (Iran)
• Qaem– (Iran)

References

Sources cited

• Cagle, Mary T. (23 May 1974).History of the Redeye Weapon System(PDF).Redstone Arsenal, U.S. Army Missile Command. Archived fromthe original(PDF)on 22 February 2004.

External links

• General Dynamics FIM-43 Redeye - Designation Systems