轴对称矢量喷管执行机构协同控制方案设计  

Design of Actuator Coupling Control Schemes for Axial-symmetric Vectoring Exhaust Nozzle

作　　者：陈杰[1] 周文祥[2] 周永权[1] 杨征山[1] 

机构地区：[1]中航工业航空动力控制系统研究所,江苏无锡214063 [2]南京航空航天大学能源与动力学院,南京210016

出　　处：《航空发动机》2013年第1期30-33,42,共5页Aeroengine

摘　　要：针对在航空发动机轴对称矢量喷管控制中出现的3个执行机构非等时同步运动问题,根据同步控制原理对轴对称矢量喷管执行机构控制回路设计了2种协同控制方案,并通过全数字仿真及半物理试验对基于偏差比例的变电流协同控制方案进行了分析和验证。结果表明:在给定任意偏转角和方位角时,实现了轴对称矢量喷管3个执行机构等时同步运动,矢量偏转控制稳定、安全,且精度高、速度快。In order to solve the problem of three actuator moving out of sync in the control of aeroengine axial-symmetric vectoring exhaust nozzle, two kinds of actuator loop coupling control schemes were designed for vectoring nozzle control based on synchronous control theory, and the loop coupling control scheme of varying electric current based on error proportion was analyzed and verified by digital simulation and semi-physical simulation test. The results show that the loop coupling control scheme of varying electric current based on error proportion realizes three actuators moving synchronically and ending at the same time in certain deflection angle and azimuth, and the vectoring control is steady and safe, which has excellent performance on response speed and accuracy.

关 键 词：轴对称矢量喷管 协同控制 同步运动 半物理仿真 航空发动机 

分 类 号：V211.4[航空宇航科学与技术—航空宇航推进理论与工程]