基于扰流片式推力矢量发动机的推力调节模型研究

Thrust Regulation Model Based on Spoiler Thrust Vector Engine

关键词:  诱饵弹  扰流片  推力矢量系统模型  推力矢量调节  悬浮机动

Key words:  Decoy missile  Thrust tab  Thrust vector system model  Thrust vector control  Floating maneuvering

摘要:

为研究扰流片式推力矢量机构通过推力调节，实现诱饵弹定高悬浮机动飞行的机理，本文在拟合得到推力调节幅度和伺服机构位移的函数关系的基础上，建立了一种扰流片式推力矢量系统模型。模型根据俯仰、偏航和高度通道输出的期望推力指令，反算出伺服机构位移，进而控制扰流片组合差动，对悬浮式诱饵弹产生主推力调节和侧向力调节。诱饵弹60m定高飞行仿真试验表明：推力矢量系统模型输出的主推力和侧向力与控制系统输出的期望推力一致，推力响应时间在100ms内。说明该模型能够实现诱饵弹定高悬浮和悬浮机动飞行中的姿态调节，且模型在快响应系统中具有实现性。扰流片非同步旋转的原理样机点火试验表明：推力矢量系统模型产生的主推力与试验结果偏差在5%以内，侧向力与试验结果偏差在3%以内，验证了该模型计算得到的推力矢量具有正确性。

Abstract:

In order to research the mechanism of spoiler thrust vector system to realize the decoy elastic suspension maneuvering flight with fixed height through thrust regulation， a model of spoiler type thrust vector system is established on the basis of fitting the function relation between thrust regulation amplitude and servo displacement. According to the expected thrust instruction output from pitch， yaw and height channel， the displacement of servo mechanism was calculated， then the main thrust and lateral force were regulated for decoy projectile suspending controlled by spoilers differential action. The 60m simulation test of decoy projectile shows that the main thrust and lateral force output by thrust vector system model are consistent with expected thrust output by control system， and the time of thrust response is within 100ms. It shows that the model can realize the attitude regulation in fixed-altitude suspension and maneuvering flight of decoy projectile， also the model can be applied in fast response system. The principle engine ignition test of non-synchronous spoiler rotating shows that the deviation between main thrust and test result is within 5%， and the deviation between lateral force and test result is within 3%， which verifies the correctness of calculation results by the model.