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题名	小卫星用姿态控制飞轮系统关键技术研究
作者	王辉
学位类别	博士
答辩日期	2015-05
授予单位	中国科学院大学
导师	吴一辉
关键词	小卫星 姿态控制 飞轮系统 永磁无刷直流电机 有限元
其他题名	Research on Key Technology of Attitude Control Flywheel System for Small Satellites Application
学位专业	机械制造及其自动化
中文摘要	飞轮是现代卫星高精度姿态控制的主要执行机构，高精度、低功耗、小体积、高可靠性一直是现代飞轮技术发展的目标。本文以微小姿态控制飞轮系统的应用需求为背景，从飞轮系统结构形式、飞轮电机设计方法和系统优化方法三个方面对其中的关键技术展开深入研究，主要研究内容包括以下几个方面： (1) 驱动电机是飞轮系统结构的核心，电磁设计的准确性会直接影响飞轮系统的性能，飞轮电机具有径向大、轴向小的结构特殊性，论文采用场路结合的方法，对影响飞轮驱动电机性能的关键参数进行了分析，给出了气隙参数、等效计算极弧系数、等效漏磁系数和电枢电路参数的计算方法，从而为飞轮电机的电磁设计与分析提供理论基础； (2) 提高飞轮电机的效率有利于降低系统的功耗，论文提出了一种满足飞轮电机高效率、低功耗要求的永磁无刷直流电机的设计方法，实现了飞轮系统电磁设计的逆问题求解，并以此为基础，设计了一种轮缘驱动式飞轮系统，研究了充磁方式、极对数、端部间隙等磁路关键参数对飞轮电机性能的影响。仿真结果表明，该方法具有较高的设计精度，最大设计误差约为10.7%； (3) 为了优化系统整体性能，论文将多学科优化技术应用于对飞轮轮体的优化设计中，兼顾了机械系统力学性能与电机电磁学性能，从质量、体积、气隙磁密等多个方面实现了对飞轮转子组件的多目标优化；为提高飞轮系统的可靠性，基于有限元分析了系统的结构强度、模态和随机载荷激励等力学特性，结果表明，优化后的结构能满足工程应用中的力学环境需求； (4) 常规飞轮系统轴向尺寸大、结构分散，导致功能密度较低。论文提出了一种基于PCB绕组和轴向磁通电机的微小平面飞轮系统，目的在于提高系统集成度和相关技术的可移植性；建立了PCB绕组电磁参数计算的数学模型，提出了波形PCB绕组形式，消除了反向转矩对飞轮性能和系统损耗的影响；分析了印制导体的内部涡流形式，并通过采用分割印制式导体和普通盘式绕线绕组来减小导体涡流损耗； (5) 论文的最后研制出满足工程应用需求的飞轮样机，进行了轮缘驱动式飞轮样机总体性能测试，并开展了飞轮系统功耗研究；通过对样机进行高低温、热真空实验、随机振动等试验，保证了系统的可靠性和安全性。 本文的研究成果密切联系现代工程应用需要，对小卫星用姿态控制飞轮系统的小型化、轻量化与低功耗设计具有重要的理论意义和工程价值。
英文摘要	Flywheel is the main implementing component of satellite attitude control system. High precision, low power consumption, small size and high reliability have been the main goals during the development of flywheel technology. The research of this paper is carried out under the background of the attitude control flywheel systems for small satellites application. The key technologies including the design of structure and the permanent magnet brushless DC motor (BLDCM) as well as the optimization method for flywheel system are investigated. The main contents are as follows: (1) The driving motor is the core part of the flywheel system and its accuracy of the electromagnetic design has great effect on the overall performance of the system. As the driving motor has large radial dimension and small axial length, the coupled field-circuit method is adopted to determine the parameters including the air-gap length, the equivalent calculating polar arc factor, the leakage magnetic coefficient and the armature winding parameters, laying foundation for electromagnetic design. (2) The power consumption of the flywheel system can be reduced by improving the efficiency of the driven motor. A method realizing the inverse electromagnetic design for the permanent magnet BLDCM is proposed, which meets the low power consumption and high efficiency demands of the motor. Based on this method, a rim-driven flywheel system is designed and the key elements affecting the motor’s performance are investigated, such as the permanent magnets’ magnetizing models, the pole pairs and the axial air-gap. High design accuracy of the method is manifested in simulation and the maximum design error is about 10.7%. (3) To optimize the system's performance, the multidisciplinary optimization techniques are applied to the multi-objective optimization of the flywheel body after considering the mechanical properties, which involve the mass, volume and air-gap flux density, and the motor’s electromagnetic performance. To improve the flywheel system’s reliability, the structural strength and stiffness, mode distribution and random excitation responses are analyzed based on the finite element analysis (FEA), and the results show that the structure can meet the engineering requirements after optimization. (4) Traditional flywheel systems usually has large axial size and relaxed structure, leading to lower function density. To improve integration and technical portability, a flywheel system based on an axial flux motor and a PCB winding stator is proposed. The mathematic model of the PCB winding is established to predict the main parameters of motor’s performances. A wave form PCB winding is designed to eliminate the anti-torque's effect on the performance of flywheel system and the power consumption. The eddy current in the winding conductors is analyzed and the intersected track as well as ordinary disc type winding are used to reduce the losses. (5) The flywheel system prototypes are fabricated for the engineering application and their power consumption performances are investigated. And the prototypes' performances in high temperature, thermal vacuum and random vibration environment are tested to ensure the reliability and safety. The works in this essay closely tracks the modern engineering applications, which are significant for both the theoretical research and engineering application in the miniaturization and lightweight design and low power consumption design of attitude control flywheel systems for small satellites application.
公开日期	2015-12-24
内容类型	学位论文
源URL	[http://ir.ciomp.ac.cn/handle/181722/48907]
专题	长春光学精密机械与物理研究所_中科院长春光机所知识产出
推荐引用方式 GB/T 7714	王辉. 小卫星用姿态控制飞轮系统关键技术研究[D]. 中国科学院大学. 2015.

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