|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||B64C-013/00 G01C-023/00 F41G-007/00|
|미국특허분류(USC)||701/003; 244/003.22; 244/003.24; 244/175|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 1 인용 특허 : 8|
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. The present invention further relates to a method of operating the flow control system. Various embodiments of the flow control system of the present invention involve different elements including flow sensors, active flow control device or activatable flow effectors and logic devices with closed loop...
1. A missile or an aircraft comprising: a. an aerodynamic surface or aerodynamically-coupled surfaces;b. at least two air flow control zones on the same aerodynamic surface or aerodynamically-coupled surfaces;c. at least one of the air flow control zones comprising at least one activatable flow effector capable of being activated and deactivated, wherein the at least one activatable flow effector is deactivated when the activatable flow effector is flush or nearly flush to the aerodynamic surface or aerodynamically-coupled surfaces of the missile or airc...