|국가/구분||United States(US) Patent 등록|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 3 인용 특허 : 18|
The present invention relates to an afterbody flow control system and more particularly to aircraft or missile flow control system for enhanced maneuverability and stabilization. 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 activatable flow effector on the missile or aircraft afterbody; at least one sensor each having a signal, the at least one sensor being positioned to detect forces or f...
1. A missile or aircraft comprising a missile or aircraft having an afterbody and forebody,the missile or aircraft afterbody having a boattail and tail fins, the missile or aircraft having drag, andthe boattail or tail fins having at least one activatable flow effector or active flow control devicewherein the at least one activatable flow effector or active flow control device is used to reduce the drag of the aircraft or missile. 2. The missile or aircraft in claim 1, further comprising at least one sensor having an electrical signal, the at least one s...