姿态控制系统冗余设计方法与半实物仿真试验  

Redundancy Design and Hardware-in-the-Loop Simulation of Attitude Control System

作　　者：肖利红 杨德生[1] 

机构地区：[1]北京航天自动控制研究所,100854

出　　处：《航天控制》1997年第3期46-54,共9页Aerospace Control

摘　　要：从系统冗余的角度研究了提高运载火箭姿态控制系统可米住的途径，论述了捷联／捷联，平台／捷联冗余姿态控制系统的组成和工作原理，介绍了用姿态角判别故障和用姿态角速度判别故障的两种故障诊断、切换和重构的模式。对捷联／捷联冗余方案进行了半实物仿真试验。As viewed from system redundancy, a way to increase reliability of launch vehicle control system is studied, Composition and operation principle of SIMU/SIMU and PIMU/SIMU redundancy attitude control systems are discussed, two kinds of methods, i. e. by using attitude angle to discriminate fault and by using attitude angular velocity to discriminate fault, for failure diagnosis , switching and system reconstruction are presend. For SIMU/ SIMU system, hardware - in - the - loop simulation has been carried out, and for PIMU/SIMU system, only mathematic simulattion was done. Both tests prove that so long as only one IMU was failure, the system could still work properly.

关 键 词：冗余技术 姿态控制系统 运载火箭 

分 类 号：V448.12[航空宇航科学与技术—飞行器设计]