| 摘要 |
Invention is embodied in an airplane having at least one jet engine with its longitudinal axis substantially parallel to the longitudinal axis of the airplane and with a tail pipe discharging rearwardly to produce reaction thrust. A variable nozzle is provided for attachment co-extensively to the tail pipe to receive and control the exhaust gas stream. The nozzle comprises a pair of fixedly mounted side plates laterally spaced and having parallel opposed planar faces, between which are mounted a pair of nozzle sections having predetermined profiles in continuation of the profile of the tail pipe. The outer marginal side walls of the sections are in slidable sealed engagement with the opposed faces of the side plates, and are movable toward and away from the engine axis between stowed and deployed positions to vary the cross sectional area of the exhaust gas flow path and to modify the combined profile of the tail pipe and nozzle for varying flight regimes so that optimum flow-pressure requirements may be satisfied. In addition, the sections may be independently actuated for differential movement which alters the effective thrust axis and provides directional control moments to aid in steering the aircraft or for emergency steering control. Direction of movement of sections at installation determines whether pitching or yawing movements are produced. In multiple engine installations both pitch and yaw control may be provided.
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