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

流体推力矢量喷管型面固定、活动部件少、结构重量轻，能够为高机动飞行器提供有效的飞行控制手段，但无源流体推力矢量喷管热喷流的偏转控制规律尚未完全掌握。为了推进无源流体推力矢量技术的实用化，本文设计研制了适用于微型涡喷发动机的耐高温喷管模型，对该喷管在微型涡喷发动机热喷流状态下的控制规律进行研究。利用非接触光学显示和测量手段——红外热成像拍摄和粒子图像测速（PIV）技术对主射流流动特性进行研究，获得流动矢量角随二次流控制阀门闭合度变化的控制规律；利用六分量盒式天平测力实验研究无源流体推力矢量喷管的力学特性，获得推力矢量角随二次流控制阀门闭合度变化的控制规律。研究结果表明：该构型喷管在微型涡喷发动机热喷流下主射流连续可控偏转，最大流动矢量角为-12.3°/12.3°，最大推力矢量角为-12.9°/12.8°，控制规律接近线性，不存在主射流偏转突跳问题。

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

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.