|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||F42B-015/01 B64C-005/12 F42B-010/14 F42B-010/62 F42B-015/00 F42B-010/00|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 0 인용 특허 : 31|
The present invention relates to a missile or aircraft with a hierarchical, modular, closed-loop flow control system and more particularly to aircraft or missile with a flow control system for enhanced aerodynamic control, maneuverability and stabilization and methods of operating the flow control system. Various embodiments of the flow control system of the present invention involve flow sensors, active flow control device or activatable flow effectors and/or logic devices with closed loop control architecture. The sensors are used to estimate or determ...
1. A munition comprising: an aerodynamic surface or surfaces, and a forebody and an afterbody;at least two air flow control zones each comprising a discrete area or region and at least one adjustable control surface on the aerodynamic surface or surfaces of the munition, at least one air flow control zone being on the forebody and at least one air flow control zone being on the afterbody, the at least one adjustable control surface being activatable flow effectors adapted to be activated, and controlled once activated; andone or more digital logic device...