航天器典型部件微振动隔离技术研究

发布时间：2018-05-18 08:12

本文选题：航天器微振动隔离 + 粘性阻尼并联隔振平台　；参考：《上海交通大学》2013年硕士论文

【摘要】：当代科技的进步对航天器指向稳定性和观测分辨率提出了越来越高的要求，，航天器在轨运行的微振动干扰已成为制约高敏感度有效载荷使用的瓶颈。其中，动量轮、飞轮、反作用轮和控制力矩陀螺等姿态控制组件工作时产生的扰动是影响有效载荷成像质量的主要扰动源，需要对其扰动进行抑制。本论文针对两种型号的航天器，分别研究分析了其姿态控制组件的微振动隔振系统，即：对于某型号卫星，采用由多杆粘性流体阻尼器构成的并联隔振平台对其控制力矩陀螺（CMG）组件进行振动隔离，研究了该并联隔振平台的隔振性能，并对构成其单杆的流体阻尼器三参数模型中的特征参数进行优化；对于另一型号卫星，提出了一种新型的隔振装置——弹性平面索网隔振结构对其动量轮组件进行振动隔离，对该隔振装置进行理论研究，并通过实验验证其隔振性能，分析结构参数对其隔振性能的影响，为进一步的设计提供了理论基础和参考。本文的结构和主要研究内容如下。第一章：介绍论文的研究背景、研究意义以及研究的主要内容，并基于现有文献，对国内外航天器部件微振动隔振技术进行了归纳和总结，尤其对航天器上微振动的主要扰动源——姿态控制组件的隔振技术进行了详细介绍。第二章：基于ANSYS数值仿真软件，对多杆粘性流体阻尼器并联隔振平台进行仿真分析。首先介绍并联隔振平台有限元模型的建模过程，再对模型进行模态、谐响应和瞬态响应动力学分析，研究隔振装置的隔振性能，为进一步的优化工作提供基础。第三章：采用基于频响函数综合的子结构方法对并联隔振平台进行建模和模型参数的优化。首先将系统划分为各独立的子结构，推导出各子结构的频响函数、传递函数，再利用各子结构之间的位移连续和力平衡推导出总体系统的输入和输出的关系，最后针对选定的优化目标，利用灵敏度分析的方法对阻尼器的特征参数进行优化。第四章：针对某型号航天器微振动隔离的需求，提出了一种新型的弹性平面索网隔振结构。首先对该隔振结构的基本要素——张紧弦索的受力特性进行分析，建立其受力-变形之间的非线性解析表达式；其次建立弹性平面索网隔振结构的等效动力学模型，对弹性平面索网隔振结构的非线性动力学响应特性进行分析。第五章：对弹性平面索网隔振结构进行试验研究，通过锤击激励下的模态测试和振动台激励下的传递特性测试，验证平面索网结构的隔振性能。并对实验数据进行整理分析，得出对指导弹性平面索网隔振结构的设计具有较高参考价值的结论。第六章：对论文的研究工作、创新点以及今后的研究进行了总结和归纳。
[Abstract]:The progress of modern science and technology demands more and more high requirements for the direction stability and the observational resolution of the spacecraft. The micro vibration interference of the spacecraft on orbit has become a bottleneck restricting the use of the high sensitivity payload. Among them, the disturbance produced by the momentum wheel, flywheel, reaction wheel and control moment gyroscope is the shadow. The main disturbance source of the acoustic payload imaging quality needs to suppress the disturbance. In this paper, the micro vibration isolation system of the attitude control components is studied and analyzed for two types of spacecraft. For a certain type of satellite, a parallel vibration isolation platform composed of multi rod viscous fluid dampers is used to control the torque gyroscope. (CMG) vibration isolation of the component, the vibration isolation performance of the parallel vibration isolation platform is studied, and the characteristic parameters in the three parameter model of the single rod fluid damper are optimized. A new type of vibration isolation device, elastic plane cable net isolation structure, is proposed for the vibration isolation of the momentum wheel component for the other model satellite. The vibration isolation device is theoretically studied, and the vibration isolation performance is verified by experiments and the influence of structural parameters on its vibration isolation performance is analyzed. The theoretical basis and reference are provided for further design. The structure and main research contents of this paper are as follows.
The first chapter introduces the research background, the significance and the main content of the research. Based on the existing literature, the micro vibration isolation technology of the spacecraft components at home and abroad is summarized and summarized, especially the main disturbance source of the micro vibration on the spacecraft, the vibration isolation technology of the attitude control component.
The second chapter: Based on the ANSYS numerical simulation software, the simulation analysis of the multi rod viscous fluid damper parallel vibration isolation platform is carried out. First, the modeling process of the finite element model of the parallel vibration isolation platform is introduced. Then the model, the harmonic response and the transient response dynamics are analyzed, and the vibration isolation performance of the vibration isolation device is studied, and the further optimization work is proposed. For the foundation.
In the third chapter, a substructure method based on the synthesis of frequency response functions is used to model the parallel vibration isolation platform and optimize the parameters of the model. First, the system is divided into independent substructures, and the frequency response functions of each substructure are derived, the transfer function is derived, and the input of the overall system is derived from the displacement continuity and force balance among the substructures. Finally, aiming at the selected optimization target, the characteristic parameters of the damper are optimized by sensitivity analysis.
In the fourth chapter, a new type of elastic plane cable net isolation structure is proposed in view of the demand of the micro vibration isolation of a certain type of spacecraft. First, the basic element of the vibration isolation structure, the stress characteristic of the tension string cable, is analyzed, and the nonlinear analytical table of the force deformation is established. Secondly, the elastic plane cable net isolation junction is established. The equivalent dynamic model of the structure is used to analyze the nonlinear dynamic response characteristics of the elastic plane cable net isolation structure.
In the fifth chapter, the vibration isolation structure of the elastic plane cable net is tested. The vibration isolation performance of the plane cable net structure is verified by the modal test and the transmission characteristic test excited by the vibrator, and the experimental data are arranged and analyzed. The results are of high reference value for the design of the elastic plane cable net isolation structure. The conclusion.
The sixth chapter summarizes and summarizes the research work, innovation and future research.
【学位授予单位】：上海交通大学
【学位级别】：硕士
【学位授予年份】：2013
【分类号】：TB535.1;V414

【参考文献】