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Aircraft and missile forebody flow control device and method of controlling flow

机译:飞机和导弹前体流量控制装置及流量控制方法

摘要

The present invention relates to a forebody flow control system and more particularly to 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, the at least one sensor being positioned to detect flow separation on the missile or aircraft 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.
机译:本发明涉及一种前体流量控制系统,更具体地说,涉及一种飞机或导弹流量控制系统,用于在高攻角下增强机动性和稳定性。本发明还涉及一种操作流量控制系统的方法。在一个实施例中,本发明包括一种导弹或飞行器,其包括后身和前身。在导弹或飞机前体上至少有一个可部署的流量执行器;至少一个传感器各自具有信号,该至少一个传感器被定位成检测导弹或飞机前体上的流动分离;闭环控制系统;其中所述闭环控制系统用于至少部分地基于所述至少一个传感器的信号来激活和停用所述至少一个可展开的流量执行器。

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