The AIM-9 Sidewinder is a supersonic, heat-seeking, air-to-air missile carried by fighter aircraft. It has a high-explosive warhead and an active infrared guidance system. The Sidewinder was developed by the US Navy for fleet air defense and was adapted by the U.S. Air Force for fighter aircraft use. Early versions of the missile were extensively used in the Southeast Asian conflict. In September 1958 Chinese Nationalist F-86s fired the first Sidewinder air-to-air missiles to down 11 communist Chinese MiG-17s over the Formosa Straits. Until that time, aircraft defensive means where primarily limited to pilots and tail gunners firing small caliber ammunition in dog-fight situations.

The AIM-9 has a cylindrical body with a roll-stabilizing rear wing/rolleron assembly. Also, it has detachable, double-delta control surfaces behind the nose that improve the missile's maneuverability. Both rollerons and control surfaces are in a cross-like arrangement.

The missile's main components are an infrared homing guidance section, an active optical target detector, a high-explosive warhead, and a rocket motor.

The infrared guidance head enables the missile to home on target aircraft engine exhaust. An infrared unit costs less than other types of guidance systems, and can be used in day/night and electronic countermeasures conditions. The infrared seeker also permits the pilot to launch the missile, then leave the area or take evasive action while the missile guides itself to the target.

Variants
The development process has produced increased capabilities with each missile modification.

The AIM-9A, prototype of the Sidewinder, was first fired successfully in September 1953. The initial production version, designated AIM-9B, entered the Air Force inventory in 1956 and was effective only at close range. It could not engage targets close to the ground, nor did it have nighttime or head-on attack capability. These shortcomings were eliminated on subsequent versions.

The AIM-9G provided the capability to lock on and launch against a target offset from the axis of the launch aircraft.

The AIM-9H configuration replace vacuum tubes with solid-state modules and a thermal battery replaced the turbo-alternator. The AIM-9H was configured with a continuous-rod bundle warhead.

The AIM-9J, a conversion of the AIM-B and E models, has maneuvering capability for dogfighting, and greater speed and range, giving it greater enhanced aerial combat capability. Deliveries began in 1977 to equip the F-15 and other Sidewinder-compatible aircraft.

The AIM-9L added a more powerful solid-propellant rocket motor as well as tracking maneuvering ability. Improvements in heat sensor and control systems have provided the AIM-9L missile with an all-aspect attack capability and improved guidance characteristics. The L model was the first Sidewinder with the ability to attack from all angles, including head-on. An improved active optical fuze increased the missile's lethality and resistance to electronic countermeasures. A conical scan seeker increased seeker sensitivity and improved tracking stability. The AIM-9L is configured with an annular blast fragmentation warhead. Production and delivery of the AIM-9L began in 1976. The all aspect heatseeking Lima model of the established AIM-9 Sidewinder missile was one of the most significant air combat weapons of its time. The AIM-9L did not require a tail chase position to lock on to a tailpipe, and could lock on from any angle including 12 o'clock ie head-on. Soon after deployment the AIM-9L proved that existing air combat tactics were obsolete, since instantaneous turning performance became far more important than sustained turning performance. The ability to point the aircraft's nose at an opponent and quickly fire a missile became far more important than the ability to follow through multiple turning maneuvers to acquire a tail aspect gun/heatseeker firing position. While a tail aspect position did improve the AIM-9L kill probability by reducing the target's evasive maneuver options, the AIM-9L's all aspect performance was still superb, as learned the hard way by the Argentine and Syrian air forces in 1982.

The AIM-9M missile utilizes a guidance control section with counter-countermeasures and improved maintainability and producibility. The AIM-9M is configured with an annular blast fragmentation warhead.

The AIM-9P, an improved version of the J model, has greater engagement boundaries, enabling it to be launched farther from the target. The more maneuverable P model also incorporated improved solid-state electronics that increased reliability and maintainability. Deliveries began in 1978.

The AIM-9P-1 has an active optical target detector instead of the infrared influence fuze; the AIM-9P-2 added a reduced-smoke motor. The most recently developed version, the AIM-9P-3, combined both the active optical target detector and the reduced-smoke motor. It also has added mechanical strengthening to the warhead as well as the guidance and control section. The improved warhead uses new explosive material that is less sensitive to high temperature and has a longer shelf life.

The AIM-9M, currently the only operational variant, has the all-aspect capability of the L model, but provides all-around higher performance. The M model has improved defense against infrared countermeasures, enhanced background discrimination capability, and a reduced-smoke rocket motor. These modifications increase ability to locate and lock-on a target and decrease the missile's chances for detection. Deliveries of the M model began in 1983.

The AIM-9M-9 has expanded infrared counter measures detection circuitry.

The AIM-9X Sidewinder Air-to-Air missile program will develop a short range heat seeking weapon to be employed in both offensive and defensive counter-air operations. Offensively, the weapon will assure that US and combined air forces have the ability project the necessary power to insure dominant maneuver. In the defensive counter-air role, the missile system will provide a key capability for force protection. The multi-service Air Intercept Missile (AIM-9X Sidewinder) development will field a high off-boresight capable short range heat seeking missile to be employed on US Air Force and Navy/Marine Corps fighters. The missile will be used both for offensive and defensive counter-air operations as a short range, launch and leave air combat missile that uses infra red guidance. The AIM-9X will complement longer range radar guided missiles such as the Advanced Medium Range Air-to-Air Missile (AMRAAM).

The new missile is required to reestablish the parity of US aircraft in short range air combat, vis-?-vis improved foreign export aircraft and missiles. Specific deficiencies exist in the current AIM-9M in high off-boresight angle capability, infra-red counter-countermeasures robustness, kinematic performance, and missile maneuverability. The MiG-29 with its AA-10/AA-11 missiles are the major threat to US forces. Additionally, there are a number of other missiles on the world market that outperform the current US inventory AIM-9M weapon system in the critical operational employment areas.

The AIM-9X will expand the capabilities of the current AIM-9M by developing a new seeker imaging infra-red focal plane array, a high performance airframe, and a new signal processor for the seeker/sensor. The current acquisition strategy seeks to retain the warhead, fuze, and rocket motor of the current design in order to capitalize on the large existing inventory of AIM-9 weapons. The F-15C/D and the F/A-18C/D will be the initial platforms for integration and T&E.

The early operational assessment of the Hughes and Raytheon DEMVAL results was that both the Hughes and Raytheon missiles showed potential for meeting both the mission effectiveness and suitability requirements of the AIM-9X operational requirements document. Specifically, all critical operational issues were rated green (potentially effective/suitable) except counter-countermeasures capability, lethality, built in test functionality, and reprogrammability. Counter-countermeasures capability of both missiles was initially below the operationally required threshold values, however the Hughes missile showed a rapid improvement through the course of the evaluation. The missiles demonstrated acceptable performance levels in the air-to-air phase. The other assessment areas not resolved as green had insufficient data for conclusive evaluation. However, again, the risk of either DEMVAL missile not meeting the threshold requirement was rated as low. The results of the operational assessment were integral to the Service source selection decision to award the engineering, manufacturing, development contract to Hughes Missile Systems Corporation.

The early operational assessment of the British ASRAAM foreign comparative test (FCT) focused on the risk areas of the ASRAAM: focal plane array effectiveness, seeker signal processing, warhead effectiveness, rocket motor testing, and kinematic/guidance ability to support the lethality requirements of the AIM-9X. The resulting assessment was that the ASRAAM (as is) cannot meet the AIM-9X operational requirements in high off-boresight angle performance, infrared counter-countermeasures robustness, lethality, and interoperability.

The AIM-9X is a supersonic, air-to-air, guided missile which employs a passive IR target acquisition system, proportional navigational guidance, a closed-loop position servo Control Actuation Section (CAS), and an AOTD. The AIM-9X is launched from an aircraft after target detection to home in on IR emissions and to intercept and destroy enemy aircraft. The missile interfaces with the aircraft through the missile launcher using a forward umbilical cable, a mid-body umbilical connector and three missile hangars. The AIM-9X has three basic phases of operation: captive flight, launch, and free flight.

The AIM-9X utilizes the existing AIM-9M AOTD, warhead, and rocket motor, but incorporates a new Guidance Section (GS), new hangars, a new mid-body connector, new harness and harness cover, new titanium wings and fins, and a new CAS. The missile is propelled by the AIM-9M solid-propellant rocket motor, but uses a new Arm and Fire Device (AFD) handle design. Also, the AIM-9M rocket motor is modified to mount the CAS on its aft end. Aerodynamic lift and stability for the missile are provided by four forward-mounted , fixed titanium wings. Airframe maneuvering is accomplished by four titanium control fins mounted in line with the fixed wings and activated by the CAS, which includes a thrust vector control system that uses four jet vanes to direct the flow of the rocket motor exhaust. The AIM-9X is configured with the AIM-9M Annular Blast Fragmentation (ABF) warhead, which incorporates a new Electronic Safe and Arm Device (ESAD) to arm the warhead after launch. The AIM-9M AOTD is used to detect the presence of a target at distances out to the maximum effective range of the missile warhead and command detonation.

Guidance Section. The GS provides the missile tracking, guidance, and control signals. It consists of three major subassemblies: (1) a mid-wave IR Focal Plane Array (FPA) seeker assembly for detecting the target, (2) an electronics unit that converts the detected target information to tracking and guidance command signals, and (3) a center section containing the cryoengine, contact fuze device, two thermal batteries, and required harnesses and connectors. The coolant supply for the GS is provided by the twin-opposed-piston, linear drive, Stirling cryoengine.

Forward Hangar/Mid-body Umbilical Connector and Buffer Connector. The hangers on the AIM-9M rocket motor are replaced by slightly "taller" hangers for AIM-9X. These taller hangers provide additional separation between the missile and the launcher. This separation is needed to provide adequate clearance for the AIM-9X on all the launcher configurations. The middle and aft hanger mounting is unchanged from the AIM-9M configuration. The forward hanger is replaced by an integrated forward hanger/mid-body umbilical assembly. The mid-body umbilical connector adds a mid-body interface with the LAU-127 launcher. This connection provides the missile MIL-STD-1553 digital communications with the launching aircraft, and requires a buffer connector similar to the Advanced Medium-Range Air-to-Air Missile (AMRAAM) buffer connector. The forward hanger/mid-body umbilical assembly is an integrated assembly that consists of the hanger, the mid-body umbilical connector, the umbilical cabling, and the rocket motor AFD wiring to the hanger striker points. The rocket motor AFD wiring is unchanged from that used in the AIM-9M and will interface with the striker points as in the AIM-9M configuration.

Harness and Harness Cover. Unlike the AIM-9M, an electronic harness has been added to the AIM-9X to provide the communications interface between the electronics unit in the GS and the other missile components. Due to the lack of space internally, the harness had to be mounted externally on the underside of the missile surface. The harness cover spans most of the length of the missile and provides an aerodynamic surface and protective cover for the electronic harness and the CAS electronic circuit board.

The AIM-9X will utilize mid-wave IR FPA seeker technology in lieu of the single-element IR seeker used in the AIM-9M. The AIM-9X will be a digital missile with Built-In-Test (BIT) and re-programming capability that is not present in the the analog AIM-9M. A buffer connector must be used on the mid-body umbilical connector when the AIM-9X is loaded on the LAU-127 launcher. The AIM-9X will use an internal cryogenic engine, called a cryoengine, for IR element cooling. The cryoengine does not require externally-supplied coolant, e.g., nitrogen, and thus does not use the nitrogen receiver assemblies contained in the LAU-7 and LAU-127 launchers, which provide IR element coolant for the AIM-9M. The AIM-9X will use titanium wings and fins. Also, the AIM-9X will use a CAS to direct movement of the aft fins and four internal jet vanes. The jet vanes direct the flow of the rocket motor exhaust to generate thrust vector control.

In the past, hundreds of live firings were conducted at great expense, to properly test a missile. Now, using simulations, this number is drastically reduced. For example, in 1964 the Sidewinder AIM-9D required 129 firings. In the 70's, the AIM-9L only required 69 and the AIM-9M only required 35. The newest generations of Sidewinder will probably require less than 20 live tests before it is ready for the fleet.

Fleet introduction of the AIM-9X missile is planned to begin in FY02 via aircraft carrier load outs. Low-Rate Initial Production (LRIP) All-Up-Round (AUR) missile deliveries begin in FY01 and continue through FY04, when Full-Rate Production deliveries begin.

The AIM-9X seeks and homes in on IR energy emitted by the target. When an IR-emitting source enters the seeker field of view, an audio signal is generated by the electronics unit. The pilot hears the signal through the headset, indicating that the AIM-9X has acquired a potential target. One method of cueing the AIM-9X to the target?s IR energy source is referred to as boresight, whereby the missile is physically pointed toward the target via the pilot maneuvering the aircraft. The IR energy gathered by the missile seeker is converted to electronic signals that enable the missile to acquire and track the target up to its seeker gimbal limits. A second method of cueing the AIM-9X to the target?s IR energy is the Sidewinder Expanded Acquisition Mode (SEAM). SEAM slaves the AIM-9X seeker to the aircraft radar. The aircraft avionics system can slave the missile seeker up to a given number of degrees from the missile/aircraft boresight axis. The missile seeker is slaved until an audible signal indicates seeker target acquisition. Upon target acquisition, a seeker interlock in the missile is released (uncaged) and the missile seeker begins tracking the target. The AIM-9X seeker will then continue to track the target. A third method for cueing the AIM-9X to the target?s IR energy is through use of the JHMCS. This method allows the pilot to cue the AIM-9X seeker to high off-boresight targets via helmet movement. The pilot can launch the AIM-9X anytime after receipt of the appropriate audible signal.

The AIM-9X is required to be compatible, at full capability, with the F/A-18C/D/E/F, F-15C/D/E, F-16C/D, and F-22 aircraft, and be capable of being used in a reduced capacity on other aircraft with MIL-STD-1760 signal set capability (F-14B Upgrade, F-14D, AV-8B, and AH-1W). The AIM-9X is also backward compatible to aircraft/launchers only capable of AIM-9M analog communication. For analog interfaces, the AIM-9X operates, and is identified, as an AIM-9M. This backward compatibility includes the analog seeker slave mode. The AIM-9X will be integrated with the Joint Helmet Mounted Cueing System (JHMCS), a helmet-mounted display with capability to cue and verify cueing of high off-boresight sensors and weapons. This missile-helmet marriage will provide the aircrew with first-look, first-shot capability in the air-to-air, within visual range, combat arena. Increased off-boresight acquisition angle and improved situational awareness will be achieved through the integrated combination of the AIM-9X missile, the JHMCS and the aircraft.

For the USN and United States Marine Corps (USMC), two guided missile launchers are available to carry and launch the AIM-9X on the F/A-18 aircraft. The LAU-7 guided missile launcher can be used on all applicable Sidewinder weapons stations, however, it requires modification of the current power supply and the addition of digital and addressing lines to the forward umbilical to carry and launch the AIM-9X. With these modifications, it will be designated the LAU-7D/A. The LAU-127 guided missile launcher can be used on the F/A-18 aircraft wing stations only. F/A-18 aircraft wing stations require a LAU-115 guided missile launcher in order to attach the LAU-127.



Specifications
Primary Function Air-to-air missile
Contractor Naval Weapons Center
Power Plant Hercules and Bermite Mk 36 Mod 71, 8 solid-propellant rocket motor
Thrust Classified
Speed Supersonic Mach 2.5
Range 10 to 18 miles depending on altitude
Length 9 feet, 5 inches (2.87 meters)
Diameter 5 inches (0.13 meters)
Finspan 2 feet, 3/4 inches (0.63 meters)
Warhead Annular blast fragmentation warhead
25 lbs high explosive for AIM-9H
20.8 lbs high explosive for AIM-9L/M

Launch Weight 190 pounds (85.5 kilograms)
Guidance System Solid-state, infrared homing system
Introduction Date 1956
Unit Cost Approximately $84,000
Inventory Classified