|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||B64C-005/12 B64C-023/06 F42B-015/01 F42B-010/64|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 0 인용 특허 : 10|
A forebody flow control system and more particularly an aircraft or missile flow control system for enhanced maneuverability and stabilization at high angles of attack. The present invention further relates to a method of operating the flow control system. In one embodiment, the present invention includes a missile or aircraft comprising an afterbody and a forebody; at least one deployable flow effector on the missile or aircraft forebody; at least one sensors each having a signal associated therewith, the at least one sensor being used for determining o...
1. A method of stabilization and maneuvering a missile or aircraft comprising the steps of a. estimating or determining side forces on a missile or an aircraft forebody based at least in part on a signal from at least one sensor; the missile or aircraft further comprising at least one deployable and retractable flow effector on the missile or aircraft forebody and a closed loop control system for controlling the at least one deployable and retractable flow effector at least in part by indirectly estimating or determining flow separation, or estimating or...