AIRCRAFT INFRARED GUIDED DEFENSE MISSILE SYSTEM

Abstract

A defense missile system for an aircraft to provide protection against hostile attack on the aircraft, the system including an aerodynamically shaped launch housing structured for external mounting on the aircraft, and a missile assembly fitted within an interior launch chamber of the launch housing. The missile assembly includes at least one, and preferably several infrared guided missiles each contained within an elongate tube and having a propulsion engine at one end and a seeker head at the opposite end. A missile support structure holds each of the missiles within the launch chamber such that the missile seeker heads are at least partially exposed through an open aft end of the launch housing. A cylinder containing pressurized coolant gas is supported within the launch chamber and is interconnected to each of the missiles for providing coolant gas to the respective seeker heads. A missile fire activation system interconnects with a fire control located in the aircraft's cockpit which is electronically interconnected to each of the missiles to facilitate sequential release of the coolant gas and electrical power to each seeker head and subsequent firing of the missile, so as to effectively launch the missile in an aft direction relative to the aircraft. A drag inducing stage is provided for use with higher speed aircraft, such as fighter jets, including a tube fitted with a ballute which inflates when the tube is ejected from the launch chamber, effectively decelerating the forward speed of the tube so that the missile can be fired into the air stream with a positive aerodynamic stability in the rearward direction relative to the aircraft.

Source: Google Patents

35 USC §181 Secrecy Order

Inventor

• 1DONALD B. ECKSTEIN

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