Small caliber spoiler thrust vector control mechanism

Abstract

The invention relates to a small-diameter spoiler-type thrust vector control mechanism, which comprises a bottom plate with a round hole in the middle, and the round hole is used for docking with an engine nozzle; three spoilers are installed on the bottom plate, three pieces The spoilers are arranged at intervals of 120° around the round hole; the three spoilers are deflected independently by three steering gears, and the steering gear controls the corresponding spoilers through the rocker arm; the spoilers pass through a support Installed on the bottom plate, the middle part of the spoiler is rotatably connected with the support, one end of the rocker arm is fixedly connected with the spoiler, and the other end is movably connected with the steering gear. The invention provides a small-diameter spoiler-type thrust vector control mechanism, which adopts the combination of three pieces and the way away from the outlet end face of the nozzle to realize the adjustment of the thrust direction and size of the engine, and has a simple and reliable structure.

Description

technical field [0001] The invention belongs to the technical field of aircraft thrust vector control, and relates to a thrust vector control mechanism, more specifically, to a small-diameter spoiler type thrust vector control mechanism. Background technique [0002] In order to keep the aircraft flying stably according to the predetermined trajectory, control force is required for attitude adjustment, and air rudder is the most common attitude adjustment method. However, in special cases, such as low-speed flight or outside the atmosphere, the efficiency of the air rudder is low, and the high-temperature gas of the engine is usually used to generate a bias force for attitude adjustment. This type of device is also called a thrust vector control mechanism. The slice is one of the typical thrust vector control methods. [0003] The traditional spoiler is arranged at the engine nozzle, inserted into the engine jet through the spoiler, blocking part of the nozzle outlet area, ...

AI Technical Summary

Problems solved by technology

At the same time, the oblique shock wave and the bow shock wave form a high-pressure area on the windward side of the spoiler, so that the spoiler is subjected to a force opposite to the thrust direction of the nozzle, resulting in a certain thrust loss

The traditional spoiler is arranged close to the nozzle of the engine. In order to avoid a large blockage of the nozzle, affecting the gas flow inside the nozzle and causing the nozzle to burn through, it is generally required that multiple spoilers cannot be inserted into the jet at the same time, so only The adjustment of the thrust direction can be realized, but the adjustment of the thrust cannot be realized; at the same time, the transmission rod of the spoiler is relatively close to the center of the jet flow, and the thermal environment is harsh when working for a long time, and the problem of structural deformation or jamming caused by excessive temperature is prone to occur

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