FIM-43 Redeye

Template:Infobox weapon

The General Dynamics FIM-43 Redeye is a man-portable surface-to-air missile system. It uses passive infrared homing to track its target. Production began in 1962 andTemplate:Sndin anticipation of the Redeye II, which later became the FIM-92 Stinger Template:Sndended in the early 1970s (production for the US Army continued until 1969. Afterwards, production was extended until 1973 to fulfill export orders)Template:Sfn<ref>STINGER: Redeye Missile Replacement Being Developed for 1980s, Army Research and Development, October–November 1972, 13 (7):18.</ref> 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 The Redeye was withdrawn gradually between 1982 and 1995 as the Stinger was deployed, though it remained in service with various armed forces of the world until quite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,Template:When being supplied via the Foreign Military Sales program. 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.<ref>{{#invoke:citation/CS1|citation |CitationClass=web }}</ref>

DevelopmentEdit

Post-war developmentsEdit

In May 1946, the War Department Equipment Board published a report on the future of infantry weapons. 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 Template:Convert.Template:Sfn When considering anti-aircraft weapons, they concluded that the M45 Quadmount mounting four M2 Browning machine guns would not be capable against future high-performance aircraft. They published a new requirement for a weapon suitable for engagements between Template:Convert against targets flying up to Template:Convert.Template:Sfn

In response, in June 1948 the United States Army Ordnance Corps began development of the "Stinger" system, essentially an updated version of the Quadmount mounting four T17 machine guns firing the more powerful 0.60 round and aimed by an automated radar system. Development on this system continued until 1951, when the requirement was extended to Template:Convert, which could not be met by the 0.60 round. A new concept using a revolver cannon firing a new 37 mm round emerged, but proved too complex and was cancelled.Template:Sfn

Porcupine and OctopusEdit

At the 1950 Tripartite Conference in 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 Template:Convert Folding-Fin Aerial 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.Template:Sfn

By the mid-1950s, new medium and high-altitude surface-to-air missile (SAMs) were rendering higher altitude flight increasingly dangerous, and attack aircraft were now expected to fly at low altitudes. This led to a 1954 requirement for a lightweight system able to engage targets from 0 to Template:Cvt, and larger weapons that raised the ceiling to Template:Cvt. In order to improve its capability in poor visibility, it was suggested that the weapon be aimed using infrared homing.Template:Sfn

File:Soldier with Redeye missile launcher 1959.png

A 1959 mock-up of a Redeye prototype. The final design became larger and heavier as development progressed

Redeye emergesEdit

In 1955, Convair, recently purchased by General Dynamics, began examining a weapon that would fill both of these requirements.Template:Sfn 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 Template:Convert warhead.Template:Sfn Convair's prototype initially used a miniaturized version of the AIM-9 Sidewinder seeker and was small, weighing Template:Cvt, a gripstock/launch tube weighing Template:Cvt. The overall weight of the prototype was Template:Cvt, while unit cost was initially estimated at about $700 (Template:Inflation) compared to about $3000 (Template:Inflation) for a Sidewinder missile.Template:Sfn

The resulting concept mockups were demonstrated to the Army and Marine Corps in November 1956. Simulations suggested that it would have an average miss distance of Template:Convert, and a direct-hit probability of 0.35 to 0.40.Template:Sfn The design proved extremely interesting, and in 1957 official requirements were formulated. This led to the Army's Redstone Arsenal receiving several unsolicited proposals for similar weapons from other companies:Template:Sfn

Template:Visible anchor, a crew-served partially portable surface-to-air missile system, designed by the Drone and Missile Flight Control DepartmentTemplate:Efn of Sperry Gyroscope, Garden City, New York
Template:Visible anchor (Shoulder-Launched Antiaircraft Missile), a man-portable surface-to-air missile system, designed by the Autonetics Division of North American Aviation, Downey, California
an undesignated system by Lockheed 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.)<ref>REDEYE II SOLE SOURCE PROCUREMENT, Statement of Lt. Col. James E. Linka, Office, Chief Research and Development, Department of the Army, Hearings on S. 3108, March 10, 1972, p. 3701.</ref>

The competing designs were rejected for being too heavy, while US Army engineers deemed that while the Redeye design was the most promising, it also needed further substantial studies on the IR seeker before development could begin. They also concluded that improvements on the IR seeker (and subsequent weight increase) were necessary for the system to perform as claimed on the proposal. Convair objected to the Army evaluation, stating that it already performed exhaustive research in private, while the United States Marine Corps were more enthusiastic about the Redeye and insisted that the weapon was ready for development, offering an initial funding of $1 million (equivalent to $Template:Inflation million in Template:Inflation/year) to accelerate the program.Template:Sfn Template:Sfn

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

TestingEdit

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 at Twentynine Palms proving ground and Camp Pendleton, California, to assess human factors and ergonomics of 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 the flight test phase of the feasibility demonstration program began.<ref>Redstone Arsenal Historical Information: Redeye Background and System Chronology, U.S. Army Aviation and Missile Command Official Web-site. Verified 05.12.2017</ref>

File:MICOM CG Gen John G. Zierdt holds Redeye missile June 1964.jpg

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

The first test launchs were conducted with unguided missiles, while in March 1959 the first tests with guided missiles were conducted. After these tests proved that the basic concept was feasible, engineering development phase began in October 1960. Convair contracted the Philco Corporation and the Atlantic Research Corporation to work on the development of the seeker and the two-stage rocket motor respectively.Template:Sfn

The US Army evaluation proved to be prescient: development was more difficult than expected, stretching to seven years, research costs tripled, and the Redeye weight increased from Template:Cvt to Template:Cvt. Early testing also revealed technical problems with the propulsion system and pop-out tail fins. The uncooled lead-sulfide IR detector performance was also disappointing, with a 2−2.7μm sensitivity band it could only lock on the hot exhaust of jet aircraft, making the missile a tail-chaser only. After experimenting with thermoelectric cooling and a Hughes-designed gas-cooled seeker, the US Army eventually decided to eschew uncooled detectors in favor of a next-generation gas-cooled seeker, which gave the missile a limited ability to target other portions of the aircraft other than the tail. Another change introduced during development was turning the detachable gripstock and the launcher tube into a single piece. Once fired the single-piece launcher could be recycled and reloaded at the nearest supply depot up to eight times. Teething problems were gradually solved by 1963. During fiscal year 1963, 75 test launches were conducted against drones, with the first successful hit being made on 14 December 1962, against a QF-9F Panther jet drone flying at Template:Convert. In October 1963, 13 missiles were fired, with 11 direct hits while the remaining two within Template:Cvt from the thermal source. In light of these successes, the US Army was convinced to start the industrialization phase of the program.Template:Sfn

File:Redeye launcher comparison.png

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

Limited production began in June 1963 as XM41 Redeye Block I. The missile was designated XMIM-43A and included the Mod 60 thermoelectrically cooled seeker. 300 systems were then evaluated between September 1965 and May 1966. After the Block I missiles were expended during engineering and service tests, the Block II systems designated XM41E1 came next, the improved missile being designated XMIM-43B and included a Mod 60A gas-cooled infrared detector cell. Deliveries of the missiles began in April 1966 alongside the final Block I missiles. In February 1967, the first Block II missiles were issued to US Army units for familiarization. A total of 1,743 XFIM-43B missiles were built for engineering tests and troop training.Template:Sfn

The final Redeye Block III configuration, designated as the M41 Block III was a major redesign of the Redeye. The FIM-43C missiles retained the gas-cooled seeker from the Block II missile, but incorporated new components and electronics, including the new and improved M115 rocket motor, and M222 warhead. The new M171 launcher was fitted with a folding optical sight.Template:Sfn The new missile could turn at up to 3g. The missile achieved a kill probability against F9F Panthers travelling at Template:Cvt at an altitude of Template:Cvt of 51%. From this it was calculated that the kill probability versus a Mikoyan-Gurevich MiG-21 at similar altitude would be 40.3%, and 53% against helicopters (specifically the Mil Mi-6 and US H-13 and H-21). Kill probability against larger propeller driven aircraft like the Antonov An-12 was estimated at 43%.<ref name="History"/> Production of the Block III systems began in May 1967, with the first deliveries to the US Army and US Marine Corps starting in March 1968, but it was only cleared up for service in extreme climates in October 1968. On 18 December 1968, the M41 Block III was formally standardized as the FIM-43C, roughly six years behind schedule.Template:Sfn

DescriptionEdit

File:Redeye Surface to Air Missile Launch.jpg

FIM-43C Redeye just after launch

The missile is fired from the M171 missile launcher. First, the seeker is cooled to operating temperature and 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.<ref name="History">Template:Cite book</ref>

Early prototypes used an uncooled missile seeker which was capable only of acquiring and tracking the hot exhaust of aircraft, which limits the engagements to tail-chase only. The FIM-43C used a second-generation gas-cooled seeker which not only could lock on the rear aspect of enemy jets, but also other IR-emitting portions of the aircraft, giving it a limited ability of engaging from other angles. The FIM-43C seeker was sensitive enough to track propeller-driven light aircraft, but still remained most effective when fired at the rear of enemy jets. The probability to hit was estimated at 30% against high-performance, maneuvering jet aircraft and 50% against slower moving targets such as helicopters.Template:Sfn

VariantsEdit

File:Gunner aiming mini-Redeye from foxhole.png

Test firing a prototype from a foxhole

Block I FIM-43, XM-41 − Consisted of a XFIM-43A guided missile XM-147 launcher, and the XM-147 TRIPAK shipping and storage containter. The missile was fitted with a Mod 60 Peltier device-cooled lead-sulfide (PbS) seeker. The thermoelectrical cooling was deemed inadequate against IR interference and dropped in favor of cryogenic cooling in subsequent variants.Template:Sfn
Block II FIM-43B, XM-41E1 – Improved version modified to increase performance and facilitate mass-production. The major components were the XFIM-43B guided missile, the XM-147E1 launcher and the XM-547E1 TRIPAK shipping and storage container. The missile was fitted with a Mod 60A gas-cooled seeker and improved warhead and fuse. The launcher was capable of firing XM-44E1 practice missiles.Template:Sfn
Block III FIM-43C, XM-41E2 – Production version; The XM-171 launcher, which used a open sight in place of the more expensive telescopic sight and new electronics to improve reliability and high volume production.Template:Sfn The FIM-43C missile incorporated the Mod 60A gas-cooled seeker, a new M222 warhead, and the improved XM-115 rocket motor.Template:Sfn The XM-571 MONOPAK shipping and storage container was lighter and less bulky than its predecessors, weighing in Template:Cvt empty and Template:Cvt loaded in comparison to the TRIPAK which weighted in Template:Cvt empty and Template:Cvt. Each MONOPAK container carried the complete weapon plus three battery and coolant (Freon) units.Template:Sfn
Air Force RAM − In the late 1967, the United States Air Force launched the Redeye Air-launched Missile (RAM) program aimed at developing a system capable of tracking with accuracy maneuvering targets after being fired from maneuvering aircraft and with short-range capabilities included. Some modifications were made to allow the missile to be air-launched, including wiring the ejector and sustainer motors together for simultaneous ignition and lengthened tail fins to increase airframe stability. It was test fired from F-4 Phantom aircraft, but abandoned for budgetary reasons and restrictions found when launching the missiles at supersonic speeds.Template:Sfn
Helicopter RAM − Experimental air-to-surface missile designed to be mounted on helicopters. Like the Air Force RAM program, the missiles were adapted for air-launch by wiring the ejector and sustainer motors together. Other modifications included the installation of interfacing equipment between the helicopter and launching pods, and an improved lead selenide (PbSe) seeker. While tests demonstrated the feasibility of the system, the testing commission recommended against its use in the configuration evaluated and that further studies with a modified seeker were needed, but development was eventually abandoned.Template:Sfn
Navy Redeye − Experimental version intended for shipboard use. Modifications included a sight compatible with the United States Navy helmet and earphone set, and electromagnetic radiation shielding. While the program was successful, ultimately the Navy did not procure any missiles.Template:Sfn

Comparison chartEdit

System	9K32M Strela-2M (missile: 9M32M)	9K34 Strela-3 (missile: 9M36)	FIM-43C Redeye
Service entry	1970	1974	1968
Weight of system ready to shoot	Template:Cvt	Template:Cvt	Template:Cvt
Missile weight	Template:Cvt	Template:Cvt	Template:Cvt
Length	Template:Cvt Template:Sfn	Template:Cvt Template:Sfn	Template:Cvt
Warhead weight	Template:Cvt	Template:Cvt	Template:Cvt Template:Sfn
Warhead type	High-explosive fragmentation Template:Sfn	High-explosive fragmentationTemplate:Sfn	High-explosive fragmentation (M222)Template:Sfn
Missile engagement aspect	Tail-chase onlyTemplate:Sfn	Limited forward hemisphere (all-aspect) capability	Limited forward hemisphere (all-aspect) capabilityTemplate:Sfn
Seeker type	Peltier-cooled PbS detector element (1–2.8 μm sensitivity range).	Nitrogen-cooled PbS detector element (3.5–5 μm sensitivity range).	Freon-cooledTemplate:Sfn PbS detector elementTemplate:Sfn
Engagement range	Template:Cvt	Template:Cvt	Template:Cvt Template:Sfn
Missile speed	Template:Cvt	Template:Cvt	Template:Cvt Template:Sfn
Engagement altitude	Template:Cvt	Template:Cvt	?−Template:Cvt Template:Sfn
Source	Template:Sfn	Template:Sfn	Template:Sfn

HistoryEdit

Fifty Redeye systems were delivered to the mujahideen by the United States during the Soviet–Afghan War in 1984,<ref>{{#invoke:citation/CS1|citation |CitationClass=web }}</ref> where they were used to shoot down aircraft including several Sukhoi Su-25 jets, as well as Mil Mi-24 and Mi-8 helicopters.<ref>Sukhoi Su-25 Frogfoot: Described / SU-25 In Afghanistan Template:Webarchive airtoaircombat.com</ref> By November 1986 it had largely been replaced by the dramatically more successful FIM-92 Stinger missiles.

During the Guinea-Bissau War of Independence, Portugal repeatedly attempted to obtain Redeyes to bolster its defenses in Portuguese Guinea, but due the American arms embargo, these attempts ultimately failed.Template:Sfn

All Redeye missiles were numbered and inventoried by the US Army Missile Command to prevent them from disappearance or otherwise unnoticed losses.<ref>Hearings on thefts and losses of military weapons, November 1975, p. 74.</ref> No Redeye missiles were reported lost or stolen from the Army inventory,<ref>Hearings on thefts and losses of military weapons, November 1975, p. 57.</ref> 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.<ref>For SA-7 read Redeye?, Flight International, 17 January 1974, 105 (3384):91.</ref>

The Redeye was known as Hamlet in Danish service and as RBS 69 (Robot 69) in Swedish service. In West German service, the system was designated as the Fliegerfaust-1 or FLF-1Template:Sfn

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