AGM-122 SideARM

The AGM-122 Sidearm was an American air-to-surface anti-radiation missile (ARM). The AGM-122 Sidearm was produced by the remanufacture of AIM-9C missiles which had been taken out of service. Sidearm was first tested in 1981. In 1984 Motorola was issued a contract to convert and upgrade AIM-9Cs to AGM-122A standard. A total of about 700 units were produced between 1986 and 1990. Existing stocks of Sidearm have been depleted, and the missile is no longer in service. The AGM-122 was less capable than newer ARMs like the AGM-88 HARM, but also substantially cheaper, and its lighter weight enabled it to be carried by combat helicopters as well as fighter aircraft and fighter bombers.

AGM-122 SideARM
Class Missile
Type Air to Surface
Manufacturer Motorola, Inc.
Origin United States of America
Country Name Origin Year
United States of America 1987
Country Name Operational Year Retirement Year
United States of America 1987 View
ManufacturerName Production From Production To Quantity
Motorola, Inc. 1984 View

The AGM-122 Sidearm was produced by the re-manufacture of AIM-9C missiles which had been taken out of service. The AIM-9C was a semi-active radar homing variant of the Sidewinder, developed for the US Navy's Vought F-8 Crusader, but used for only a limited period of time. Conceived and developed at China Lake NAWC, the Sidearm was first tested in 1981. In 1984, Motorola was issued a contract to convert and upgrade AIM-9Cs to AGM-122A standard. A total of about 700 units were produced between 1986 and 1990.

Existing stocks of Sidearm have been depleted, and the missile is no longer in service. Proposals for new-build missiles, under the designation AGM-122B, have not been proceeded with to date.

The AGM-122 was less capable than newer antiradiation missiles like the AGM-88 HARM, but also substantially cheaper, and its lighter weight enabled it to be carried by combat helicopters as well as fighter aircraft and fighter bombers.

General Information
Developed by USA
Deployed by USA
Development Year 1984
Deployment Year 1987
Platform any aircraft configured for Sidewinder missile use
Launcher rail launcher
Contractor Motorola,Inc.,Scottsdale,AZ

Dimensions and Performance
Length 2.88m
Body Diameter 12.7cm
Wing/Fin span 63.5cm
Launch Weight 88.5kg
Range 17km
Speed Mach 2.2

Components
Propulsion solid-fuel rocket motor
Engine Mk36 mod11 solid rocket motor (Bermite/Rocketdyne and Thiokol)
Warhead 11kg HE blast/fragmentation
Guidance gimbaled, broadband, passive anti-radiation homing (WGU-15/B)

End notes