火箭游动发动机的增益伺服控制算法  

Variable Gain Servo Control Algorithm to Suppress the Resonance of Vernier Rocket Engine

作　　者：刘慧[1] 李博伟 王建军 LIU Hui;LI Bo-wei;WANG Jian-jun(Beijing Research Institute of Precise Mechatronic and Controls,Beijing 100076)

机构地区：[1]北京精密机电控制设备研究所,北京100076

出　　处：《液压与气动》2024年第5期62-68,共7页Chinese Hydraulics & Pneumatics

基　　金：国家自然科学基金(51875529);装备预先研究领域基金(80902010302)。

摘　　要：现役火箭游动发动机配套的电液伺服机构具有结构高集成化、大摆角行程的特点,其与发动机组成的推力矢量控制系统具有较大非线性,传统的控制方法容易出现大摆角下发散抖动现象。为解决上述问题,同时满足火箭对推力矢量系统的快速性要求,提高系统可靠性,建立其推力矢量伺服控制模型,分析出易抖动的原因,并提出了变增益PID与陷波函数补偿的复合数字控制方法。仿真与试验结果均表明,该控制方法有效地抑制了电液伺服机构的非线性因素对系统稳定性的影响,最小稳定裕度提高5~7 dB。The supporting/matching electro-hydraulic servo mechanism of the current vernier rocket engine has the characteristics of highly integrated structure and large swing angle stroke.The thrust control system formed by it and the engine had a large nonlinear,and the traditional control method is prone to divergence and jitter at large angles.In order to solve the above problems,meet the rocket’s requirement of the speed of easy jitter,and puts forward the compound digital control method of variable gain PID and trap function compensation.The simulation and experimental results show that the control method can effectively suppress the influence of nonlinear factors of electro-hydraulic servo mechanism on the system stability,and the minimum stability margin is increased by 5~7 dB.

关 键 词：伺服控制 伺服机构 控制算法 非线性 

分 类 号：TH137[机械工程—机械制造及自动化] TB553[理学—物理]