基于PWM作动器的运载火箭伺服系统建模与仿真  

Modeling and Simulation of Launch Vehicle Servo System based on PWM Actuator

作　　者：梁俊龙[1] 呼延霄[2] 张贵田[1] 尤裕荣[2] Liang Jun-long;Hu Yan-xiao;Zhang Gui-tian;You Yu-rong(National Key Laboratory of Combustion Flow and Thermo-Structure,Northwestern Polytechnical University,Xi'an,710072;Xi’an Aerospace Propulsion Institute,Xi’an,710100)

机构地区：[1]西北工业大学燃烧、热结构与内流场重点实验室,西安710072 [2]西安航天动力研究所,西安710100

出　　处：《导弹与航天运载技术》2021年第5期78-84,共7页Missiles and Space Vehicles

摘　　要：根据运载火箭伺服系统工作特点,设计了基于PWM作动器的火箭发动机位置伺服控制系统。完成了作动器、非对称作动筒等关键部件数学建模,获得了位置伺服系统的控制模型。针对获得的控制系统传递函数,对系统的稳态误差和稳定裕度进行了分析。采用Matlab/Simulink设计了基于抗积分饱和算法的PID控制器,并建立了整个非线性控制系统AMESim仿真模型,验证了控制系统的稳态控制精度和动态调节特性。最后通过地面负载试验验证了控制算法及控制系统方案的可行性。Based on the working characteristics of launch vehicle servo system,a position control servo system based on PWM actuator is designed.The mathematical models of key parts such as the actuator and the asymmetric hydraulic cylinders are established,and the control model of the positional servo system is obtained.According to the obtained transfer function,steady-state errors and stability margins of the system are analyzed.A PID controller based on the anti-integral saturation algorithm is designed by Matlab/Simulink technique.The AMESim simulation model of whole nonlinear control system is established,and steady-state control precisions and dynamic adjusting characteristics of the control system are verified.Finally,the feasibility of control algorithm and scheme are verified by ground load tests.

关 键 词：火箭发动机 位置伺服系统 PWM作动器 建模与仿真 

分 类 号：V433[航空宇航科学与技术—航空宇航推进理论与工程]