| 摘要 |
A yaw control device for an aircraft, eg a UCAV or drone, having a supersonic nozzle 210 with a rectangular or flat section comprises a supersonic throat 211 extended by a diverging portion 212 in which supersonic flow Esup occurs. In order to enable the aircraft to be controlled in yaw in the absence of a vertical fin, the device of the invention makes use of jet control surfaces in the form of airfoils 220 disposed in the diverging portion 212 of the nozzle. The airfoils 220 are movable about respective pivot axes 221 in order to generate a lateral force when in a deflected position, so as to enable the aircraft to turn about its yaw axis 202. Each airfoil 220 is protected from the supersonic flow by an upstream stationary element 240 presenting an aerodynamic leading edge.
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