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

被引：1
|
作者：
Gong D. [1 ]
Gu Y. [1 ]
Zhou Y. [1 ]
Shi N. [1 ]
机构：
[1] Laboratory of Unsteady Aerodynamics and Flow Control, College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing
来源：
Gu, Yunsong (yunsonggu@nuaa.edu.cn) | 1600年 / Chinese Society of Astronautics卷 / 41期
基金：
中国国家自然科学基金;
关键词：
Coanda effect; Control law; Flow vector angle; Jet deflection; Passive fluid thrust vector control; Thermal jet flow; Thrust vector angle;
D O I：
10.7527/S1000-6893.2019.23609
中图分类号：
学科分类号：
摘要：
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. © 2020, Beihang University Aerospace Knowledge Press. All right reserved.
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