Aircraft and missile forebody flow control device and method of controlling flow |
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| 申请号 | US13151640 | 申请日 | 2011-06-02 | 公开(公告)号 | US10137979B1 | 公开(公告)日 | 2018-11-27 |
| 申请人 | Troy Prince; Frederick J. Lisy; Mehul P. Patel; Jack M. DiCocco; Reed Carver; Robert N. Schmidt; | 发明人 | Troy Prince; Frederick J. Lisy; Mehul P. Patel; Jack M. DiCocco; Reed Carver; Robert N. Schmidt; | ||||
| 摘要 | 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 or estimating flow separation or side forces on the missile forebody; and a closed loop control system; wherein the closed loop control system is used for activating and deactivating the at least one deployable flow effector based on at least in part the signal of the at least one sensor. | ||||||
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