The AIM-9 Sidewinder is a short-range air-to-air missile. It entered service with the United States Navy in 1956 and the Air Force in 1964, and is one of the oldest, cheapest, and most successful air-to-air missiles. Its latest variants (AIM-9X) remain standard equipment in most Western-aligned air forces. The Soviet K-13 (AA-2 "Atoll"), a reverse-engineered copy of the AIM-9B, was also widely adopted. Low-level development started in the late 1940s, emerging in the early 1950s as a guidance system for the modular Zuni rocket. This modularity allowed for the introduction of newer seekers and rocket motors, including the AIM-9C variant, which used semi-active radar homing and served as the basis of the AGM-122 Sidearm anti-radar missile. Due to the Sidewinder's infrared guidance system, the brevity code "Fox two" is used when firing the AIM-9. Originally a tail-chasing system, early models saw extensive use during the Vietnam War, but had a low success rate (8% hit rate with the AIM-9E variant). This led to all-aspect capability in the L (Lima) version, which proved an effective weapon during the 1982 Falklands War and Operation Mole Cricket 19 in Lebanon. Its adaptability has kept it in service over newer designs like the AIM-95 Agile and SRAAM that were intended to replace it. The Sidewinder is the most widely used air-to-air missile in the West, with more than 110,000 missiles produced for the U.S. and 27 other nations, of which perhaps one percent have been used in combat. It has been built under license by Sweden and other nations. The AIM-9 has an estimated 270 aircraft kills. In 2010, Boeing won a contract to support Sidewinder operations through to 2055. In 2021 an Air Force spokesperson said that its relatively low cost, versatility, and reliability mean it is "very possible that the Sidewinder will remain in Air Force inventories through the late 21st century".
== Design == The AIM-9 was a product of the US Naval Weapons Center at China Lake in the Mojave Desert. It features a lightweight, compact design with cruciform canards and tail fins. It uses a solid rocket motor for propulsion, similar to most conventional missiles, a continuous-rod fragmentation warhead, and an infrared seeker. The seeker tracks a difference in temperatures detected and uses proportional guidance to achieve impact. Older variants such as the AIM-9B with uncooled seeker heads could track only the high temperatures of engine exhaust, making them strictly rear-aspect. Later variants, however, featured liquid nitrogen coolant bottles in the launchers, allowing the missile to track any part of the aircraft heated by air resistance due to high-speed flight, giving modern Sidewinders all-aspect capabilities. The nose canards provide maneuverability for the AIM-9, with the AIM-9X using thrust vectoring to augment this. The hot gases generated were used to actuate the nose canards in older models, while newer variants use thermal batteries. To minimize the amount of energy devoted to actuating control surfaces, the AIM-9 does not use active roll stabilization. Instead, it uses rollerons, small finned metal discs protruding out of the aft end of the tips of the tail fins which are spun by the passing airflow as the missile flies through the air, providing gyroscopic stabilization. The AIM-9 uses a passive infrared proximity fuze to detonate its warhead near an enemy aircraft, scattering fragments that aim to damage the aircraft, rendering it inoperable. The continuous rod warhead features rods welded together to form a cylindrical outer shell, with explosive filler inside. Upon detonation, the rods expand in a toroidal shape, ensuring that at least some portion of the shrapnel hits enemy aircraft. Newer models of the AIM-9 sought to increase the range that the seeker head's gimbal can turn, allowing the missile to track aircraft at greater angles from its direct line of sight, or boresight. Models such as the AIM-9L, AIM-9M, and AIM-9X feature high off-boresight capabilities, meaning they are able to track targets at high seeker gimbal angles, or highly distant from the boresight.
== Guidance == The Sidewinder is guided not by the actual position recorded by the detector, but by the change in position since the last sighting. So if the target remains at 5 degrees left between two rotations of the mirror, the electronics would not output any signal to the control system. Consider a missile fired at right angles to its target; if the missile is flying at the same speed as the target, it should "lead" it by 45 degrees, flying to an impact point far in front of where the target was when it was fired. If the missile is traveling four times the speed of the target, it should follow an angle about 11 degrees in front. In either case, the missile should keep that angle all the way to interception, which means that the angle that the target makes against the detector is constant. It was this constant angle that the Sidewinder attempted to maintain. This "proportional pursuit" system is straightforward to implement and offers high-performance lead calculation almost for free and can respond to changes in the target's flight path, which is much more efficient and makes the missile "lead" the target.
History
Origins
During World War II, various researchers in Germany designed infrared guidance systems of various complexity. The most mature development of these, codenamed Hamburg, was intended for use by the Blohm & Voss BV 143 glide bomb in an anti-ship role. Hamburg used a single IR photocell as its detector along with a spinning disk with lines painted on it, alternately known as a "reticle" or "chopper". The reticle spun at a fixed speed, causing the output of the photocell to be interrupted in a pattern, and the precise timing of the resulting signal indicated the bearing of the target. Although Hamburg and similar devices like Madrid were essentially complete, the work of mating them to a missile had not been carried out by the time the war ended. In the immediate post-war era, Allied military intelligence teams collected this information, along with many of the engineers working on these projects. Several lengthy reports on the various systems were produced and disseminated among the Western aircraft firms, while a number of the engineers joined these companies to work on various missile projects. By the late 1940s a wide variety of missile projects were underway, from huge systems like the Bell Bomi rocket-powered bomber to small systems like air-to-air missiles. By the early 1950s, both the US Air Force and Royal Air Force had started major IR seeker missile projects.
The development of the Sidewinder missile began in 1946 at the Naval Ordnance Test Station (NOTS), Inyokern, California, now the Naval Air Weapons Station China Lake, as an in-house research project conceived by William B. McLean. McLean initially called his effort "Local Fuze Project 602" using laboratory funding, volunteer help and fuze funding to develop what they called a heat-homing rocket. The name Sidewinder was selected in 1950 and is the common name of Crotalus cerastes, a rattlesnake, which uses infrared sensory organs to hunt warm-blooded prey. It did not receive official funding until 1951 when the effort was mature enough to show to Admiral William "Deak" Parsons, the Deputy Chief of the Bureau of Ordnance (BuOrd). It subsequently received designation as a program in 1952. Originally called the Sidewinder 1, the first live firing was on 3 September 1952. The missile intercepted a drone for the first time on 11 September 1953. The missile carried out 51 guided flights in 1954, and in 1955 production was authorized. In 1954, the US Air Force carried out trials with the original AIM-9A and the improved AIM-9B at the Holloman Air Development Center. The first operational use of the missile was by Grumman F9F-8 Cougars and FJ-3 Furies of the United States Navy in the middle of 1956.
=== First generation rear-aspect variants === Nearly 100,000 of the first generation (AIM-9B/C/D/E) of the Sidewinder were produced with Raytheon and General Electric as major subcontractors. Philco-Ford produced the guidance and control sections of the early missiles. The NATO version of the first-generation missile was built under license in Germany by Bodenseewerk Gerätetechnik; 9,200 examples were built.
=== AIM-9A (AAM-N-7 Sidewinder I) (USN) === AIM-9A was a pre-production of the Sidewinder, first fired successfully in September 1953. Missile production began in 1955, and the first models entered the Navy's fleet service in 1956. Generally, it was a prototype production run, with 240 pieces being produced, and mainly intended for training pilots in air combat techniques. The AIM-9A was initially called the AAM-N-7 before the tri-service designation change in 1962. The AIM-9A and AIM-9B were originally fitted with a non-propulsive attachment (NPA) for their MK 15 and MK 17 rocket motors. If the motor accidentally ignited while kept in storage, during transport, or while it was fitted to the aircraft hardpoints, the NPA would direct the exhaust gases at right angles rather than straight back. In these cases, the missile would not move. While the NPA safety device itself suffered no failures, some ordnance men forgot to remove them after hanging the missiles in the hardpoints. When the pilots attempted to fire the missiles in flight, the hot exhaust gases were redirected directly towards the wings, severely damaging the aircraft. After losing three aircraft in this manner, the US Navy withdrew the NPA from use.
AIM-9B (AAM-N-7 Sidewinder IA) (USAF/USN)
The AIM-9B is very similar to the AIM-9A, but the "B" has a more sophisticated rear and more aerodynamical front fins. The AIM-9B is a very limited weapon, but it had no serious competitors and counters when it was introduced, causing it to be adopted by the USAF and NATO as a standard weapon, with around 80,000 units being produced from 1958 to 1962. The viewing angle of the AIM-9B's sensor was a minuscule 4 degrees, so at launch, the pilot had to accurately aim the aircraft's sight over or above the target (to account for drag). The speed of the conical scan was very slow, additionally, the uncooled missile had a low sensitivity and was liable to extraneous heat. The AIM-9B was recommended for use on non-threatening targets (like bombers), only from behind (so it can lock on the thermal radiation from the target engines) and only with the sun behind or to the side of the launching aircraft (as the missile would lock onto it due to its thermal radiation). It was famously the first Sidewinder variant to be fired in anger as on 24 September 1958, it achieved the world's first successful kill with an air-to-air missile, when Taiwanese F-86Fs shot down Communist Chinese MiG-15s using AIM-9Bs supplied and fitted by the U.S. Navy (USN).
==== AIM-9B derivatives ==== RB24: A license built AIM-9B Sidewinder from Sweden.
K-13/R-3 (AA-2): The K-13/R-3 was reverse-engineered from the American AIM-9B Sidewinder. During the Taiwan Strait conflict in 1958, an AIM-9B Sidewinder missile fell near Wenzhou without exploding and was recovered by Chinese forces. The Soviets later learned that the Chinese had obtained the missile, and after negotiations, they persuaded the Chinese to send one to the Soviet Union, which enabled them to develop the K-13. K-13/R-3 (AA-2) variants: K-13/R-3 (Object 300) (AA-2 Atoll): It was the standard variant and entered limited service only two years later in 1960. K-13A/R-3S (Object 310) (AA-2A Atoll): This entered service in 1962. The R-3S was the first version to enter widespread production, in spite of a very long seeker settling time around 22 seconds, as opposed to 11 seconds for the original version. PL-2: Chinese-produced R-3S. A-91: Romanian-produced R-3S. K-13R/R-3R (Object 320) (AA-2B/C Atoll): While the R-3S was being introduced in 1961, work started on a semi-active radar homing (SARH) version for high-altitude use, with 8 km range, similar to the little-used US Navy AIM-9C Sidewinder. This took longer to develop, and did not enter service until 1966. K-13M/R-13M (Object 380) (AA-2D Atoll): The R-13M is a much improved version of the R-3S and has capabilities similar to the AIM-9G Sidewinder. The R-13M is still a tail engagement missile only but is far more capable than the R-3S due to its new seeker and rocket motor. The new cooled seeker is more accurate and somewhat more resistant to countermeasures. The new rocket motor burns longer and the redesigned body makes the R-13M more maneuverable. K-13M1/R-13M1: Improved R-13M with new forward fins introduced in 1976.
=== AIM-9C (AAM-N-7 Sidewinder IC (SARH)) (USN) === The lackluster performance of the AIM-9B caused the Navy to look for a successor. In 1963 the AAM-N-7 Sidewinder IC was developed in two variations: a SARH (semi-active radar homing) variant (AIM-9C) and an IR (AIM-9D) in 1963. The AIM-9C's semi-active radar was exclusively tied to the F-8 Crusader's radar and fire control system (FCS). A total of around 1,000 AIM-9C missiles were launched from 1965 to 1967, but their usage in the Vietnam war proved unsuccessful, downing no enemies. A filter modification program for reworked units (to allow high altitude capability up to 18,288m (60,000 feet)) was the only planned modification. In 1984, long after the variant's retirement, Motorola was contracted to re-manufacture remaining stocks of AIM-9C missiles into the AGM-122A Sidearm, a low cost air-to-surface anti-radiation missile.
=== AIM-9D "Delta" (AAM-N-7 Sidewinder IC (IR)) (USN) === Recognizing the limitations of the initial AIM-9B, the US Navy (USN) worked to improve the missile's performance. They changed the missile nose to an aerodynamical ogival nose. The seeker was improved with a wider field of view beyond 25 degrees and a reduced instantaneous field of view of 2.5 degrees to reduce foreign thermal interference (primarily from flares). A nitrogen cooling system was added for the fuze, enhancing the missile's heat sensitivity. Maneuverability was also improved with a faster tracking rate and a new actuator system. The Sidewinder's range was improved as well, with the new Hercules MK 36 solid-fuel rocket motor allowing the missile to fly up to 18 km. Finally, a new Mk 48 continuous-rod warhead was fitted to the missile for increased damage; this also meant infrared or a radio proximity fuze could be used. These improvements were all added to the AIM-9D and went into service with the USN. Around 1,000 AIM-9D units were produced from 1965 to 1969. A significant issue with the AIM-9D was breakup during launch. The AIM-9D was eventually developed into the AIM-9G.
==== AIM-9D derivatives ==== ATM-9D (USN): AIM-9D used for captive flight target acquisition training. GDU-1/B: AIM-9D used for firing practice.
=== AIM-9E "Echo" (USAF) === The AIM-9E "Echo" was the first version developed solely by the U.S. Air Force (USAF). The AIM-9E allows the expansion of the weapons acquisition envelope, especially at low-altitude, increasing its Probability of Kill (P[k]). It achieved this using a new low-drag conical nose head, being a distinguishing feature of USAF Sidewinders. A magnesium fluoride seeker dome was introduced, along with a more compact optical assembly, an improved guidance control system, new electronics, and significant changes to the internal wiring harnesses. These improvements facilitated a better 100 Hz reticle rate, and a 16.5 deg/sec tracking rate. The most significant design change was the addition of cooling for the PbS detector, adding Peltier (thermoelectric) cooling, giving the advantage of unlimited cooling when positioned on the launch rail, but is only active when electrical power is present. The AIM-9E gives greater range over the AIM-9B, but is worse than the "D". Over 5,000 AIM-9B's were rebuilt into AIM-9E's. The AIM-9E appeared in Vietnam after the conclusion of the Operation Rolling Thunder in 1968, with the U.S. Air Force (USAF), becoming one of their main missile armaments. Up until Operation Linebacker in 1972 intense air-to-air activity in Vietnam was not present. There were 71 AIM-9E launch attempts from January to October 1972, however, only 6 missiles managed to down an aircraft, with 1 other hitting an aircraft, but not causing complete destruction. Reasons for the poor success rate was listed as "poor air crew training, launches out of the envelope, the tactical situation, marginal tone, tone discrimination, the missile going ballistic, and other malfunctions".
==== AIM-9E variants ==== AIM-9E: Standard production model. AIM-9E-2: Some "E" models are equipped with reduced-smoke rocket motors and have the designation AIM-9E-2
=== AIM-9B FGW.2 Sidewinder (AIM-9F) === As the Sidewinder was being acquired by NATO forces, licensed production was given to West Germany and they would produce around 15,000 units. Like the Americans, the West Germans sought to improve the AIM-9B design due to its limitations. The only visible exterior difference is a greenish sensor window, but many tech improvements were added beneath the shell. Unnoticed improvements include solid state electronics (instead of vacuum tubes), carbon dioxide seeker cooling, a new nose dome and superior optical filtering. Conversions were done to European AIM-9Bs to upgrade them to the FGW.2 standard. The official designation is the AIM-9B FGW.2 but it is known as the AIM-9F in US nomenclature.
=== AIM-9G "Golf" (USN) === The AIM-9G was very similar to the AIM-9D in most aspects, and did not differ externally. The AIM-9G was an AIM-9D that used an improved AIM-9D seeker head with SEAM (Sidewinder Extended Acquisition Mode), this allowed the slewing of the optics through a search pattern to acquire the enemy (most likely using a rosette scan), it also allowed the slaving of the optics to a radar or helmet sight. This was connected to the onboard computer of the aircraft, which gave the capability of capturing the target using the data coming from the airborne radar. This meant that the target could be locked without being in the sights, and the missile automatically got pre-launch instructions. The conical scanning speed was also increased greatly. The seeker head was now able to seek in a 25˚ circular scan. This allowed the AIM-9G to have an improved chance of acquiring the target than earlier models. This, along with other upgraded solid-state modules, culminated in the AIM-9G. The improvement was substantial enough that an order of 5,000 AIM-9D seekers was stopped at 1,850 units, with the rest being ordered to AIM-9G seeker specifications instead. Around 2120 AIM-9G were built by Raytheon from 1970 to 1972. The AIM-9G would be used with its predecessor, the AIM-9D, during the Vietnam War, as the US Navy's choice of IR missile. A 46% hit rate with the AIM-9G during Operation Linebackers I and II in 1972 was achieved, of which 14 aircraft were MiG-17s and the other 7 were MiG-21s. This was due to the missile design and USN fighter pilot training at TOPGUN. The United States Air Force attempted to attain AIM-9Gs from the USN, due to bad experience with their AIM-9 Sidewinders models (B, E, and J), but they were incompatible with US Air Force's Sidewinder launchers due to the different cooling mechanisms. (the USN used a nitrogen gas container on the launcher, which the USAF did not use)
==== AIM-9G derivatives ==== ATM-9G (USN): AIM-9G used for captive flight target acquisition training.
=== AIM-9H (USN) === Within December 1965, two designers McLean and LaBerge (who were employed by Philco-Ford) came together to create ways to improve the AIM-9G's reliability. One submission was to advance all the remaining missile electronic components from vacuum to solid-state gradually. The US Air Force adhered to this steady replacement of their AIM-9s to solid-state, however the Navy opted for a different approach after Walt Freitag, a USN engineer proposed a full change to solid-state in one missile. The "H" variant had major changes over the AIM-9D/G, which had multiple issues with reliability. One of the issues was the intolerance of the vacuum tubes to repeated 20 ft/sec sink rate landings by US Navy aircraft on carrier decks. The "H" was the first Sidewinder to be fully solid state, replacing the original vacuum tubes. The AIM-9H also included a new lead sulphide detector, using nitrogen cooling. The new guidance package was built using semiconductors. When the engineers redesigned these electronics, they essentially kept the AIM-9G's optical system, but the tracking rate increased further, from the original 12˚ to 20˚ degrees per second, this complementing the more powerful 120 lb.ft actuators that had been installed. They also replaced the thermal battery with a turbo-alternator. The AIM-9H also included a continuous-rod bundle warhead, improving its destructive capability. The AIM-9H was the last and most maneuverable of the rear-aspect USN Sidewinders, with USN moving to the all-aspect AIM-9L. The AIM-9H was actually used at the very end of the Vietnam war, with it being introduced into the US navy service in 1972 and being used in Operation Linebacker. A total of around 7,700 AIM-9H units would be manufactured from 1972 to 1974 by Philco-Ford and Raytheon. The AIM-9H was the basis for the all-aspect USAF/USN AIM-9L.
==== AIM-9H derivatives ==== ATM-9H: Was a training version of the AIM-9H for captive flight target acquisition.
=== AIM-9K (USN) === The AIM-9K was a planned U.S. Navy (USN) upgrade to the AIM-9H, but the development was abandoned in favor of USAF/USN joint AIM-9L.
=== AIM-9J (USAF) === As the AIM-9E Sidewinder was entering service in Southeast Asia during the conclusion of Operation Rolling Thunder, the USAF started the development the next generation Sidewinders to replace the AIM-9E. In November 1968, the testing of an AIM-9E upgrade the "Extended Performance" began. The missile was designed to give pilots a more capable close-range IR missile against a maneuvering target. It would eventually be designated the AIM-9J. Preliminary testing of the AIM-9J ended on 3 July 1972, indicating that further in-depth testing and evaluation were necessary prior to replacing the AIM-9B/E. On 8 June 1972, the AIM-9J was authorized for introduction into Southeast Asia under Phase IIA of its evaluation program, and approval to employ it in combat was received on 31 July 1972. The first combat flight of the AIM-9J occurred on 2 August 1972, but it wasn't until 9 September 1972 that the first three AIM-9Js were fired in combat. Only 31 combat firings were attempted before the cease fire in January, 1973. Considering the original intent of its development, the AIM-9J performance was relatively unimpressive in combat. Nevertheless, compared to its competitors (the AIM-7E-2 and the AIM-9E), the AIM-9J did appear relatively successful. The AIM-9J kill rate per missile fired was 13 percent from September to December 1972, compared to 5 percent and 8 percent registered by the AIM-7E-2 and AIM-9E, respectively. When viewed on the basis of effectiveness per engagement, the AIM-9J fared better with 33 percent kills per engagement, versus 11 percent and 15 percent for the AIM-7E-2 and AIM-9E, respectively. The AIM-9J was an upgrade to the AIM-9E. It included:
The partial replacement of old-fashioned tube electronics with solid-state electronics. A longer-burning gas generator, which increased flight time to 40 seconds. More powerful actuators, driving new square-tipped double-delta canards. This doubled the single-plane "g" capability. Around 6,700 AIM-9Js were built from 1972 onward. These were mostly converted existing AIM-9B/E missiles.
==== AIM-9J variants ==== AIM-9J: The base variant. AIM-9J-1 (AIM-9N): AIM-9J-1 (later redesignated the AIM-9N) was an upgrade to the AIM-9J. The AIM-9N had a similar missile configuration to the AIM-9J, but the three main circuit boards were substantially redesigned to help improve seeker performance. Around 7,000 of the AIM-9N were built/rebuilt. AIM-9J-3: AIM-9J-1 with the new SR116 motor.
=== AIM-9P === The AIM-9P Sidewinder missile was a USAF sponsored family of export missiles based on the AIM-9J/N, and would be upgraded multiple times over its lifespan. The AIM-9P was an improved AIM-9J with a new motor, fuze and better reliability. It included a greater engagement range, allowing it to be launched farther from the target. The AIM-9P was more maneuverable than the AIM-9J, and also included improved solid-state electronics that increased reliability and maintainability. The AIM-9P was either a rebuilt B/E or J or all-new production. Deliveries of the AIM-9P began in 1978.
==== AIM-9P Variants ==== AIM-9P: The base model. AIM-9P-1: Introduced the DSU-15/B AOTD laser proximity fuze, replacing the previous infrared influence fuze with an active optical target detector. AIM-9P-2: Includes a reduced-smoke rocket motor. AIM-9P-3: Includes a reduced-smoke motor, an active optical target detector, an improved guidance and control section, mechanical strengthening to the warhead, guidance system and control section, and a new insensitive munitions warhead. The warhead uses a new explosive material, this explosive material is less sensitive to high temperature and has a longer shelf life. AIM-9P-4: Introduced the ALASCA features and technology found on the AIM-9L/M variants. AIM-9P-5: Added improved IRCCM from the AIM-9M.
==== AIM-9P derivatives ==== RB24J: Swedish designation for the AIM-9P-3
Note: the speed of the B model was around 1.7 Mach and the other models above 2.5.
Later generation all-aspect variants
AIM-9L (USAF/USN)
The next major advance in IR Sidewinder development was the AIM-9L ("Lima") model which was in full production in 1977. This was the first "all-aspect" Sidewinder with the ability to attack from all directions, including head-on, which had a dramatic effect on close-in combat tactics.
Its first combat use was by a pair of US Navy F-14s in the Gulf of Sidra in 1981 versus two Libyan Sukhoi Su-22s, both of the latter being destroyed by AIM-9Ls. Its first use in a large-scale conflict was by the United Kingdom during the 1982 Falklands War. In this campaign the "Lima" reportedly achieved kills from 80% of launches, scoring 17 kills and 2 shared kills against Argentine aircraft.
==== AIM-9L Derivatives ==== DATM-9L (USAF/USN): This is an AIM-9L used to train ground personnel in missile assembly, disassembly, loading, transportation, and storage procedures and techniques. GDU-6/C: Was a training version of the AIM-9L, may have been an earlier designation of the DATM-9L. RB74 (RB24L): The RB74 was the Swedish designation of the AIM-9L. The RB24L was the original designation, but was changed to the RB74. AIM-9L/I: German modification produced by Diehl with a better seeker. AIM-9L/I-1: German modification produced by Diehl with a better seeker.
=== AIM-9M (USAF/USN) === The AIM-9M is an improved AIM-9L inheriting the all-aspect capability of the L model, but providing all-around higher performance. Having a better background rejection and infrared countermeasures discrimination (WGU-4/B), a low-smoke motor to reduce the visual signature of the weapon, and improved guidance control section with counter-countermeasures and improved maintainability and producibility. The AIM-9M uses an annular blast fragmentation warhead. These modifications increase ability to locate and lock-on a target and decrease the missile's chances for detection. It was deployed in large numbers during the 1991 Gulf War, the AIM-9M was responsible for all 10 Sidewinder kills recorded during that conflict. The AIM-9M was used by the RAAF's being their standard dogfight AAM, carried by the F/A-18 and F-111.
==== AIM-9M Variants ==== AIM-9M (USAF/USN): The standard model AIM-9M Model. AIM-9M-1 (USN): The AIM-9M-1 has very little information other than it uses the same Guidance Control System (GCS) as the AIM-9M-3. AIM-9M-2: No information other than the confirmation of its existence. AIM-9M-3 (USN): The only information regarding the AIM-9M-3 is that it uses the same GCS as the AIM-9M-1. AIM-9M-4 (USN): AIM-9M variant used by United States Navy, using a different GCS, other information on them is currently unknown. AIM-9M-5: No information other than the confirmation of its existence. AIM-9M-6 (USN): AIM-9M variant used by United States Navy using a different GCS, other information on them is currently unknown. AIM-9M-7: Variant modified for Operation Desert Storm/Shield to combat expected threats better. The nature of the upgrade is unknown. AIM-9M-8 (USN): Principal USN Production variant, this upgrade entailed replacing the motor with the new MK 36 MOD 11, a new guidance section (WGU-4E/B), and AOTD (DSU-15B/B).(This was achieved through the replacement of five circuit cards and the associated parent board) AIM-9M-9 (USAF): Principal USAF Production variant, this upgrade entailed replacing the motor with the new MK 36 MOD 11, a new guidance section (WGU-4E/B), and AOTD (DSU-15B/B) AIM-9M-10 (USN): Modified AIM-9M-8 variant for use on the F/A-18E/F Super Hornet, these are retrofitted AIM-9-8's. The AIM-9M-10 differs by replacement to the wings and forward hanger. AIM-9M modified for surface-to-air operation, developed by Ukraine from January 2025, claimed to have shot down Russian aircraft in May 2025.
==== AIM-9M Derivatives ==== AIM-9Q (USN): The AIM-9Q is an AIM-9M modified with upgraded guidance-control section, further information on the missile is unknown and it was either canceled or became an AIM-9M sub-variant. CATM-9M (USAF/USN): A training AIM-9M Used for pilot training in aerial target acquisition and use of aircraft controls/displays. CATM-9M-1: This was used for AIM-9M-1/3 training. CATM-9M-2: This was used for AIM-9M-1/3 training. CATM-9M-4: This was used for AIM-9M-1/3 training. CATM-9M-6: This was used for AIM-9M-1/3 training. CATM-9M-8: This was used for AIM-9M-1/3 training. CATM-9M-12: This was used for AIM-9M-8/9 training. CATM-9M-14: This was used for AIM-9M-8/9 training. CATM-9M-27: This variant was used for AIM-9M-10 training. NATM-9M (USAF/USN): It is a permanent test missile version of the AIM-9M. The modification into a test missile includes the replacing live-test warhead and/or telemetry section.
==== NATM-9M Variants ==== NATM-9M-1: No information other than the confirmation of its existence as a test missile. NATM-9M-2: No information other than the confirmation of its existence as a test missile. NATM-9M-3: No information other than the confirmation of its existence as a test missile. NATM-9M-4: No information other than the confirmation of its existence as a test missile.
