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Invention Publication
CN106809377A 一种用于控制飞行器的空气动力学的简化流体振荡器 有权

一种用于控制飞行器的空气动力学的简化流体振荡器
Abstract:
本申请公开了一种使用主动流动控制系统(301)控制飞行器的空气动力学的方法和装置。在一个示例中，主动流控制系统(301)包括机身(302)和多个流体振荡器(200)。机身(302)包括入口(310)，其配置用于从亚音速到超高音速范围的飞行速度。多个流体振荡器(200)被安装在机身(302)的弯曲部分周围。每个流体振荡器(200)包括主体和耦接到主体(202)的整体喷管。主体(202)具有流入部分(206)和在流入部分(206)对面形成的窄喷管入口(208)。整体喷管(204)通过窄喷管入口(208)耦接到主体(202)。窄喷管入口(208)形成了从流入部分(206)到窄喷管入口(208)的单一的流体流动路径(218)。
Abstract(English):

Method and apparatus for controlling the aerodynamics of an aircraft using an active flow control system (301) is disclosed herein. In one example, the active flow control system (301) includes an airframe (302) and a plurality of fluidic oscillators (200). The airframe (302) includes an inlet (310) configured for flight speeds ranging from subsonic to hypersonic. The plurality of fluidic oscillators (200) is mounted about a curvature of the airframe (302). Each fluidic oscillator (200) includes a body and an integral nozzle coupled to the body (202). The body (202) has an inflow portion (206) and a narrow nozzle inlet (208) formed opposite the inflow portion (206). The integral nozzle (204) is coupled to the body (202) by the narrow nozzle inlet (208). The narrow nozzle inlet (208) forms a single fluid flow path (218) from the inflow portion (206) to the narrow nozzle inlet (208).

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