Systems and methods for evading heat seeking missles
View Patent ↗A method and system in an airborne aircraft to evade a heat seeking missile includes the steps of detecting the launch or “lock on” of a heat seeking missile and reducing the radiation from the aircraft's engine by reducing the engine speed to idle. The method may also include the steps of shutting down and restarting an engine and taking countermeasures to distract the missile or distorting its tracking system. In addition, a method and system for automatically shutting down an engine and/or injecting cooling water into the engine's exhaust port are disclosed.
1. A system for use in an airborne helicopter for evading a heat seeking missile comprising:
means for detecting the launch of a heat seeking missile;
automatic means for reducing a helicopter's engine speed to its least sustainable speed in response to the launch of a heat seeking missile;
means for automatically ejecting a pyrotechnic flare as an alternative target;
automatic means for increasing the lift of the helicopter after the threat by a missile has passed and which includes:
means for detecting a safe zone based on altitude and speed of the helicopter and wherein it is relatively safe to shutdown and restart an engine before contacting the ground; and automatically shutting down means for the engine if the helicopter is within the safe zone at the time a missile is detected, and automatic means for restarting the engine after a preselected time and before the helicopter is in imminent danger of striking the ground.
2. A system for use in an airborne helicopter according to claim 1 , which includes means for injecting a mass of water into the engine's exhaust port to cool the engine.
3. A system for use in an airborne helicopter according to claim 2 , which includes means for pushing the helicopter's collective down to thereby cause auto rotation and a rapid reduction in altitude.
4. A system for use in an airborne helicopter according to claim 3 , which includes means for deflecting a helicopter engine's exhaust upwardly.
5. A system for use in an airborne helicopter according to claim 4 , which includes means for a pilot to bypass the system and continue flight at any time.