空天飞行器的舵伺服系统设计  

Design of Rudder Servo System for Aerospace Vehicle

作　　者：冉令峰[1] 何卫国[1] Ran Lingfeng;He Weiguo(China Airborne Missile Academy,Luoyang 471009,China)

机构地区：[1]中国空空导弹研究院

出　　处：《计算机测量与控制》2020年第1期120-126,151,共8页Computer Measurement &Control

摘　　要：空天飞行器对舵伺服系统的性能要求越来越高,不仅要求承载能力强、质量小,还必须可靠性高和维护方便;针对此类要求,对空天飞行器的舵伺服系统进行了设计,以电气双余度控制和双绕组永磁同步电机为关键技术;其中驱动控制器采用1553B总线、CAN总线和422总线相结合的形式,解决了与飞控、系统内部和测试设备的通讯问题;作动器采用双余度齿轮副和滚珠丝杠副直推式传动机构,并通过锁定电机轴的方式来实现舵面的锁定功能,提高了系统的可靠性;进行了系统联合仿真分析,实现了最大工作舵偏角为25°、角速度为53.2°/s、系统线性度偏差为0.2%、不对称度为0.4%、超调10%以内和过渡时间193ms以内等主要指标,结果满足系统指标要求;经在航天总体单位中的实际应用,舵伺服系统满足空天飞行器的性能要求。The requirement to high performance of rudder servo system for aerospace vehicle is getting higher,not only strong bearing capacity and small quality,but also high reliability and convenient maintenance.In response to such requirements,the rudder servo system for aerospace vehicle is designed.Electrical dual-redundancy control and dual-winding permanent synchronous motor are the key technologies.The driver adopts the combination of 1553 Bbus,CAN bus and 422 bus,which solves the communication problems with flight control,system interior and test equipment.Actuator adopts double redundant gear pair and ball screw pair direct drive mechanism,and the locking function of the rudder surface is realized by locking the motor shaft,which improves the reliability of the system.The co-simulation analysis of the system is carried out,and the maximum working rudder deviation angle was 25°,the angular velocity was 53.2°/s,the system linearity deviation was 0.2%,the unsymmetry was 0.4%,the overshoot was within 10%,and the transition time was within 193 ms.These results meet system requirements.The result is satisfactory.The rudder servo system meets the performance requirements of aerospace vehicle through the practical applications in spaceflight general unit.

关 键 词：空天飞行器 舵伺服系统 双余度 1553B总线 联合仿真 

分 类 号：V441[航空宇航科学与技术—飞行器设计]