动力系统故障下运载火箭推力与质量辨识方法  

Identification Method for Thrust and Mass of Launch Vehicle under Power System Fault

作　　者：于海森 谭述君[1,2] 刘浩[1] 毛玉明 YU Haisen;TAN Shujun;LIU Hao;MAO Yuming(State Key Laboratory of Structural Analysis,Optimization and CAE Software for Industrial Equipment,Dalian University of Technology,Dalian 116024,China;Key Laboratory of Advanced Technology for Aerospace Vehicles of Liaoning Province,Dalian University of Technology,Dalian 116024,China;Aerospace system engineering Shanghai,Shanghai 201109,China)

机构地区：[1]大连理工大学工业装备结构分析优化与CAE软件全国重点实验室,大连116024 [2]大连理工大学辽宁省空天飞行器前沿技术重点实验室,大连116024 [3]上海宇航系统工程研究所,上海201109

出　　处：《宇航学报》2023年第6期895-905,共11页Journal of Astronautics

基　　金：国防科技基础加强计划;国家自然科学基金(11972101)。

摘　　要：为了精确辨识动力系统故障下运载火箭的推力和质量,提出了一种最小二乘法与卡尔曼滤波相结合的联合校正辨识方法。以两级运载火箭二级飞行段为研究对象,采用惯性敏感器件测量的视加速度信息作为辨识的观测量,根据视加速度观测信息和上一时刻的推力参数估计值,通过卡尔曼滤波估计当前时刻火箭的质量等状态量,再利用渐消记忆的递推最小二乘方法估计当前时刻火箭的推力参数,从而实现火箭质量和推力参数联合校正辨识。进一步,提出利用视加速度向量2范数差分判断推力参数突变时刻,并从突变时刻重新进行最小二乘辨识的改进策略,提高对推力参数突变的跟踪能力。数值仿真结果表明,对不同大小、不同类型的动力系统故障,所提出的方法都给出了运载火箭推力和质量参数的高精度辨识结果,尤其是结合故障检测的改进策略,大大提高了对推力参数突变的跟踪能力。In order to accurately identify the thrust and mass of launch vehicle under power system fault,a joint correction identification method based on least square method and Kalman filter is proposed.Taking the second flight phase of a two-stage launch vehicle as the research object,the apparent acceleration information measured by inertial sensors is used for identification.According to the measured information of apparent acceleration and the estimated value of thrust parameters at the previous time,the mass and other state variables of the launch vehicle at the current time are estimated by Kalman filtering,and then the thrust parameters of the launch vehicle at the current time are estimated by using the recursive least square method of fading memory,Thus,the mass and thrust parameters of the launch vehicle can be jointly corrected and identified.Furthermore,an improved strategy is proposed to use the 2-norm difference of the apparent acceleration vector to judge the sudden change time of the thrust parameters,and to conduct the least squares identification again from the sudden change time,so as to improve the tracking ability of the sudden change of the thrust parameters.Numerical simulation results show that the proposed method can provide high-precision identification results of the thrust and mass parameters of the launch vehicle for power system faults of different sizes and types.Especially,combined with the improved strategy of fault detection,the tracking ability of thrust parameter mutation is greatly improved.

关 键 词：运载火箭 动力系统故障 推力辨识 最小二乘方法 卡尔曼滤波 

分 类 号：V475.1[航空宇航科学与技术—飞行器设计]