基于Petri网的卫星姿态控制系统剩余寿命预测方法研究

发布时间：2018-07-08 10:53

本文选题：卫星姿态控制 + 可重构性　；参考：《南京航空航天大学》2015年硕士论文

【摘要】：姿态控制系统是卫星的关键分系统,其可靠性和寿命对整个卫星的运行具有重要意义。本文针对卫星姿态控制系统,对系统可重构性以及系统的剩余寿命预测方法进行了研究,并在此基础上,考虑系统可重构性对卫星姿态控制系统剩余寿命的影响,研究该情况下的卫星姿态控制系统剩余寿命预测方法。在对卫星姿态控制系统模型和系统组成介绍的基础上,研究了卫星姿态控制系统的可重构性:首先定义了卫星姿态控制系统可重构性的概念,针对卫星姿态控制系统执行器分系统和传感器分系统,分别定义了可重构性判据,并基于控制能耗定义了系统的可重构性度量指标,还针对三正一斜装飞轮和四斜装飞轮配置分别进行了可重构性仿真与分析。针对卫星姿态控制系统剩余寿命预测方法的研究,充分考虑系统组成和系统故障对系统剩余寿命的影响,在对系统组成分析的基础上,定义系统的故障状态,并通过Kaplan Meier估计器和极大似然估计法对系统故障状态间转移概率模型进行估计,建立卫星姿态控制系统的Petri网模型,对Petri网模型进行大量仿真便可实现对卫星姿态控制系统剩余寿命的预测。系统可重构性是卫星姿态控制系统的一个重要性质,也是系统剩余寿命一个重要影响因素,因而基于可重构性对卫星姿态控制系统的剩余寿命预测方法进行研究具有重要的意义。由于执行机构的可重构性判据中涉及到了系统控制能耗,而系统控制能耗的计算需要知道飞轮的有效因子,首先根据飞轮部件的转速、轴温、电流等数据信息和模糊推理方法确定飞轮部件的有效因子,然后对系统的控制能耗进行计算并对系统进行可重构性分析,最后,在此基础上对系统进行故障状态定义,建立卫星姿态控制系统的剩余寿命预测模型,从而实现对考虑可重构性情况下的卫星姿态控制系统剩余寿命的预测,并针对具体的卫星姿态控制系统配置进行了仿真验证。
[Abstract]:Attitude control system is the key subsystem of satellite, and its reliability and lifetime are of great significance to the operation of the whole satellite. In this paper, the reconfiguration of the satellite attitude control system and the residual life prediction method of the system are studied. On this basis, the influence of the reconfiguration of the system on the residual life of the satellite attitude control system is considered. The residual life prediction method of satellite attitude control system is studied in this paper. Based on the introduction of satellite attitude control system model and system composition, the reconfiguration of satellite attitude control system is studied. Firstly, the concept of satellite attitude control system reconfiguration is defined. For satellite attitude control system actuator subsystem and sensor subsystem, reconfigurable criteria are defined, and reconfigurable metrics are defined based on control energy consumption. The reconfigurable simulation and analysis of three straight and one oblique flywheel and four oblique flywheel configuration are also carried out. In view of the research of residual life prediction method of satellite attitude control system, the influence of system composition and system fault on system residual life is fully considered. Based on the analysis of system composition, the fault state of the system is defined. The system transition probability model is estimated by Kaplan Meier estimator and maximum likelihood estimation method, and the Petri net model of satellite attitude control system is established. The residual life of satellite attitude control system can be predicted by a lot of simulation on Petri net model. The reconfiguration of the system is an important property of the satellite attitude control system, and it is also an important influence factor of the residual life of the system. Therefore, it is of great significance to study the residual life prediction method of satellite attitude control system based on reconfiguration. Since the system control energy consumption is involved in the reconfiguration criterion of the actuator, and the calculation of the system control energy consumption needs to know the effective factor of the flywheel, firstly, according to the speed of the flywheel component, the temperature of the shaft, Current and other data information and fuzzy inference method are used to determine the effective factors of flywheel components. Then the control energy consumption of the system is calculated and the reconfiguration of the system is analyzed. Finally, the fault state of the system is defined on this basis. The residual life prediction model of satellite attitude control system is established to predict the residual life of satellite attitude control system considering reconfiguration, and the simulation verification is carried out for the configuration of satellite attitude control system.
【学位授予单位】：南京航空航天大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V448.22

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