载人运载火箭姿态故障检测门限研究  

Study on Attitude Failure Detection Thresholds in Manned Launch Vehicle

作　　者：邓舞燕 王楠 张智[2] DENG Wuyan;WANG Nan;ZHANG Zhi(Beijing Institute of Astronautical Systems Engineering,Beijing 100076,China;China Academy of Launch Vehicle Technology,Beijing 100076,China)

机构地区：[1]北京宇航系统工程研究所,北京100076 [2]中国运载火箭技术研究院,北京100076

出　　处：《载人航天》2018年第2期157-162,共6页Manned Spaceflight

摘　　要：载人运载火箭一般通过姿态角偏差和姿态角速率信息来判断与姿态相关的火箭故障,其故障检测门限的制定对是否能够检测出故障至关重要。对此提出了一种载人运载火箭姿态故障检测门限的工程设计方法,通过引入蒙特卡洛仿真初步确定门限值,再通过故障仿真和半实物仿真进行校验,并对不能满足要求的故障检测门限进行修订,完成制定门限。设计结果得到了半实物仿真以及飞行试验的检验。A manned launch vehicle usually uses attitude angle deviation and attitude angular veloci-ty to determine the rocket fault related to the attitude.The establishment of the fault detection thresh-old is critical to whether the fault can be detected.In this paper,a method for setting up the fault detection threshold for manned launch vehicle was proposed.Monte Carlo simulation was used to preliminarily determine the threshold value which was then checked by fault digital simulation and hardware in the loop simulation.The engineering design method that could not meet the require-ments of the fault detection threshold was revised to establish the threshold.The design was verified by the hardware in the loop simulation and the real flight.The results showed that the design of the attitude fault threshold was reasonable and feasible.

关 键 词：故障检测门限 故障仿真 半实物仿真 

分 类 号：V421.6[航空宇航科学与技术—飞行器设计]