基于微型涡喷发动机热喷流的无源流体推力矢量喷管的控制规律

doi:10.7527/S1000-6893.2019.23609

Abstract

Abstract: Fluid thrust vector nozzle has many advantages such as fixed surface, less active parts, lighter structure weight, and faster jet deflection. It can provide highly efficient flight control for high maneuvering aircraft, but its control law has not been fully researched, especially in the state of the main jet deflecting under the state of hot jet. Therefore, we design and develop the high temperature nozzle model for the micro turbojet engine, and study the control law of the nozzle under the state of the hot jet based on the micro turbojet engine. The characteristics of the static deflection of the main jet are studied by the infrared thermal imaging technology and the Particle Image Velocimetry (PIV). Using these non-contact optical measurements, the control law of the flow vector angle to the opening of the secondary flow valve is obtained. The mechanical characteristics of passive fluid vector nozzle are studied by a force measurement experiment using box balance, and the control law of thrust vector angle varying with the closure of secondary flow control valve is obtained. The results show that the main jet deflects continuously and controllably. The maximum flow vector angle is -12.3°/12.3°, and the maximum thrust vector angle is -12.9 °/12.8°. The control law is close to linear, and there is no sudden deflection of the main jet.

Key words: passive fluid thrust vector control, Coanda effect, thermal jet flow, jet deflection, flow vector angle, thrust vector angle, control law

CLC Number:

V211.7

GONG Dongsheng, GU Yunsong, ZHOU Yuhang, SHI Nanxing. Control law of passive fluid thrust vector nozzle based on thermal jet of micro turbojet engine[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2020, 41(10): 123609-123609.

References

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Control law of passive fluid thrust vector nozzle based on thermal jet of micro turbojet engine

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