垂直起降火箭垂直返回段自适应容错控制算法  

VTVL Rocket Fault-tolerant Control for Its Return Trajectory

作　　者：张亮[1] 黄盘兴 徐大富 韦常柱[1] 黄荣[1] 

机构地区：[1]哈尔滨工业大学航天工程系,哈尔滨150001 [2]上海宇航系统工程研究所,上海201109

出　　处：《战术导弹技术》2015年第2期63-69,共7页Tactical Missile Technology

基　　金：上海市科技人才计划项目支持(14XD1423300);中央高校基本科研业务费专项资金资助(HIT.NSRIF.2015037)

摘　　要：针对垂直起降火箭(VTVL)返回段的容错控制问题,设计了自适应的快速故障检测与可重构控制算法。它由一个基本控制器、执行器动力学模块、可重构控制器和一个离散化的故障检测(FDI)模块构成,能够应对单个或多个执行器卡死或失效故障。针对火箭返回段弹道设计了参考模型并对垂直起降火箭的动力学模型进行了建模。在单个或多个执行器卡死或失效故障条件下的仿真结果表明,该算法能够快速进行故障检测并进行可重构控制。An adaptive algorithm for rapid fault detection and reconfigurable control is proposed, in order to solve the fault-tolerant control problem in the return period of the vertical takeoff and vertical landing rockets. It consists of a basic controller, actuator dynamics module, reconfigurable controller and a dis- cretization of the fault detection and identify module. This algorithm solves the problems associated with single or multiple stuck actuators or failed actuators. Based on the dynamics of vertical takeoff and verti- cal landing rocket, the reference model has been proposed for the return trajectory of the rocket. Under the conditions of single or multiple actuators stuck or loss of effectiveness failure, the simulated results show that the algorithm can detect the failure rapidly and process the reconfigurable control successfully.

关 键 词：垂直起降火箭 容错控制 参考模型 故障检测与分离 

分 类 号：V412[航空宇航科学与技术—航空宇航推进理论与工程]