|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||F42B-015/01 F42B-010/00 F42B-015/00|
|미국특허분류(USC)||244/003.21; 244/003.1; 244/003.15; 244/003.22; 244/158.1; 244/171.1|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 6 인용 특허 : 29|
A reliable and inexpensive attitude control system uses a plurality of pitch-over thrusters to perform rapid and precise attitude maneuvers for a flight vehicle. The pitch-over thrusters create rotational moments that directly pitch and yaw the flight vehicle. The use of very simple thrusters and control techniques provides for a reliable and cost effective solution. The ability to perform overlapping pitch and yaw maneuvers with single-shot fixed-impulse thrusters provides for high-speed maneuverability.
We claim: 1. An attitude control system for a flight vehicle selected from a missile, kill vehicle (KV) or space craft, comprising: at least four thrusters on the flight vehicle and displaced from the vehicle center of gravity, said thruster generating thrust vectors with a fixed impulse that produce rotational moments to directly pitch and yaw the flight vehicle; and a fire controller configured to issue start firing commands to a first set of said thrusters to slew the flight vehicle and to issue stop firing commands to a second set of said thrusters ...