太阳翼驱动机构的可靠性分析
发布时间：2018-12-25 15:35
【摘要】：太阳翼驱动机构(Solar Array Drive Assembly,SADA)对卫星有着极其重要的作用。近年来卫星故障频发,这在很大程度上是由于太阳翼出故障所导致的。而太阳翼驱动机构作为太阳翼系统的重要组成部分,其可靠性研究就尤为重要。由于太空环境的复杂性和随机因素的影响,太阳翼驱动机构的故障变得难以预测;而且受技术和试验条件的限制,地面上不能完全模拟太空环境,故其试验也不能得到满意的结果,所以从理论角度对其可靠性进行探讨,有着重要的意义。现有文献只对太阳翼驱动机构的各个部件进行了建模或分析,没有对其进行系统的可靠性研究。本文将尝试从多个角度对太阳翼驱动机构进行系统的可靠性分析。 首先,建立了太阳翼驱动机构的故障模式及影响分析(Failure Mode and Effects Analysis, FMEA)表。分析太阳翼驱动机构这个复杂系统的工作原理和结构,再对复杂的太空环境的特点进行总结,分析其对太阳翼驱动机构的影响,总结出太阳翼驱动机构的故障模式,然后按照《故障模式、影响及危害性分析指南》(GJB1391-2006)的规范要求生成《太阳翼驱动机构的FMEA表》,为后续可靠性工作的开展奠定了基础。 其次,对太阳翼驱动机构进行动态故障树分析。由于太阳翼驱动机构包含着冷备份、热备份以及其他的动态逻辑器件,故需要采用动态故障树来分析。在权衡了多种动态故障树分析方法后,本文采用二元决策图(Binary Decision Diagram,BDD)和马尔科夫模型(Markov Model)相结合的分析方法,并对Markov模型进行了详细的推导,得出了动态逻辑门的可靠度公式。再根据已知数据得出了故障树顶事件即系统的可靠度。 最后,根据太阳翼驱动机构的力学特性,建立运动可靠性模型。考虑到太阳翼驱动机构在驱动过程中会受到各种摩擦力的阻碍,本文将尝试从摩擦力矩和摩擦力做功两个方面建立摩擦力模型,并结合求随机变量函数的数字特征的矩法,分别得出力矩和做功形式的功能函数,代入数据可得到力矩形式和做功形式的可靠度。最后再采用串联模型计算出整个太阳翼驱动机构的力学形式的可靠度。
[Abstract]:The solar wing driving mechanism (Solar Array Drive Assembly,SADA) plays an extremely important role in the satellite. Satellite failures have occurred frequently in recent years, largely due to solar wing failures. As an important part of solar wing system, the research on the reliability of solar wing driving mechanism is particularly important. Because of the complexity of space environment and the influence of random factors, it is difficult to predict the fault of the solar wing driving mechanism. Due to the limitation of technology and test conditions, the space environment can not be completely simulated on the ground, so the test can not get satisfactory results, so it is of great significance to discuss its reliability from a theoretical point of view. The existing literatures only model or analyze the components of the solar wing drive mechanism, and there is no systematic research on its reliability. This paper attempts to analyze the system reliability of the solar wing drive mechanism from several angles. Firstly, the fault mode and influence analysis (Failure Mode and Effects Analysis, FMEA) table of solar wing drive mechanism are established. This paper analyzes the working principle and structure of the solar wing driving mechanism, summarizes the characteristics of the complex space environment, analyzes its influence on the solar wing driving mechanism, and summarizes the fault mode of the solar wing driving mechanism. Then according to the specification of "failure Mode, impact and Hazard Analysis Guide" (GJB1391-2006), the "FMEA table of solar wing drive mechanism" is generated, which lays a foundation for the subsequent reliability work. Secondly, the dynamic fault tree analysis of the solar wing drive mechanism is carried out. Because the solar wing drive mechanism includes cold backup, hot backup and other dynamic logic devices, it is necessary to use dynamic fault tree to analyze. After weighing a variety of dynamic fault tree analysis methods, this paper adopts the combination of binary decision graph (Binary Decision Diagram,BDD) and Markov model (Markov Model), and deduces the Markov model in detail. The reliability formula of dynamic logic gate is obtained. According to the known data, the reliability of the fault tree top event is obtained. Finally, according to the mechanical characteristics of the solar wing drive mechanism, the motion reliability model is established. Considering that the solar wing drive mechanism will be hindered by various friction forces in the driving process, this paper attempts to establish friction force model from two aspects of friction moment and friction work, and combines the moment method to solve the digital characteristics of random variable function. The function functions of torque and work form are obtained, and the reliability of torque form and work form can be obtained by inserting data. Finally, the series model is used to calculate the reliability of the mechanical form of the whole solar wing drive mechanism.
【学位授予单位】：电子科技大学
【学位级别】：硕士
【学位授予年份】：2011
【分类号】：TH112
本文编号：2391307
[Abstract]:The solar wing driving mechanism (Solar Array Drive Assembly,SADA) plays an extremely important role in the satellite. Satellite failures have occurred frequently in recent years, largely due to solar wing failures. As an important part of solar wing system, the research on the reliability of solar wing driving mechanism is particularly important. Because of the complexity of space environment and the influence of random factors, it is difficult to predict the fault of the solar wing driving mechanism. Due to the limitation of technology and test conditions, the space environment can not be completely simulated on the ground, so the test can not get satisfactory results, so it is of great significance to discuss its reliability from a theoretical point of view. The existing literatures only model or analyze the components of the solar wing drive mechanism, and there is no systematic research on its reliability. This paper attempts to analyze the system reliability of the solar wing drive mechanism from several angles. Firstly, the fault mode and influence analysis (Failure Mode and Effects Analysis, FMEA) table of solar wing drive mechanism are established. This paper analyzes the working principle and structure of the solar wing driving mechanism, summarizes the characteristics of the complex space environment, analyzes its influence on the solar wing driving mechanism, and summarizes the fault mode of the solar wing driving mechanism. Then according to the specification of "failure Mode, impact and Hazard Analysis Guide" (GJB1391-2006), the "FMEA table of solar wing drive mechanism" is generated, which lays a foundation for the subsequent reliability work. Secondly, the dynamic fault tree analysis of the solar wing drive mechanism is carried out. Because the solar wing drive mechanism includes cold backup, hot backup and other dynamic logic devices, it is necessary to use dynamic fault tree to analyze. After weighing a variety of dynamic fault tree analysis methods, this paper adopts the combination of binary decision graph (Binary Decision Diagram,BDD) and Markov model (Markov Model), and deduces the Markov model in detail. The reliability formula of dynamic logic gate is obtained. According to the known data, the reliability of the fault tree top event is obtained. Finally, according to the mechanical characteristics of the solar wing drive mechanism, the motion reliability model is established. Considering that the solar wing drive mechanism will be hindered by various friction forces in the driving process, this paper attempts to establish friction force model from two aspects of friction moment and friction work, and combines the moment method to solve the digital characteristics of random variable function. The function functions of torque and work form are obtained, and the reliability of torque form and work form can be obtained by inserting data. Finally, the series model is used to calculate the reliability of the mechanical form of the whole solar wing drive mechanism.
【学位授予单位】：电子科技大学
【学位级别】：硕士
【学位授予年份】：2011
【分类号】：TH112
【引证文献】
相关期刊论文 前1条
1 李彦锋;黄洪钟;刘宇;肖宁聪;朱顺鹏;;基于贝叶斯网络的卫星太阳翼驱动机构系统可靠性建模与评估[J];中国科技论文;2012年08期
相关博士学位论文 前1条
1 肖宁聪;随机和认知不确定性下的结构可靠性方法研究[D];电子科技大学;2012年
相关硕士学位论文 前1条
1 许英健;航天器太阳翼动态影响测量系统的研究与设计[D];上海交通大学;2012年
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