本文選題：航天器微振動(dòng)隔離 + 粘性阻尼并聯(lián)隔振平臺(tái)�。� 參考：《上海交通大學(xué)》2013年碩士論文

【摘要】：當(dāng)代科技的進(jìn)步對(duì)航天器指向穩(wěn)定性和觀測(cè)分辨率提出了越來(lái)越高的要求，，航天器在軌運(yùn)行的微振動(dòng)干擾已成為制約高敏感度有效載荷使用的瓶頸。其中，動(dòng)量輪、飛輪、反作用輪和控制力矩陀螺等姿態(tài)控制組件工作時(shí)產(chǎn)生的擾動(dòng)是影響有效載荷成像質(zhì)量的主要擾動(dòng)源，需要對(duì)其擾動(dòng)進(jìn)行抑制。本論文針對(duì)兩種型號(hào)的航天器，分別研究分析了其姿態(tài)控制組件的微振動(dòng)隔振系統(tǒng)，即：對(duì)于某型號(hào)衛(wèi)星，采用由多桿粘性流體阻尼器構(gòu)成的并聯(lián)隔振平臺(tái)對(duì)其控制力矩陀螺（CMG）組件進(jìn)行振動(dòng)隔離，研究了該并聯(lián)隔振平臺(tái)的隔振性能，并對(duì)構(gòu)成其單桿的流體阻尼器三參數(shù)模型中的特征參數(shù)進(jìn)行優(yōu)化；對(duì)于另一型號(hào)衛(wèi)星，提出了一種新型的隔振裝置——彈性平面索網(wǎng)隔振結(jié)構(gòu)對(duì)其動(dòng)量輪組件進(jìn)行振動(dòng)隔離，對(duì)該隔振裝置進(jìn)行理論研究，并通過(guò)實(shí)驗(yàn)驗(yàn)證其隔振性能，分析結(jié)構(gòu)參數(shù)對(duì)其隔振性能的影響，為進(jìn)一步的設(shè)計(jì)提供了理論基礎(chǔ)和參考。本文的結(jié)構(gòu)和主要研究?jī)?nèi)容如下。 第一章：介紹論文的研究背景、研究意義以及研究的主要內(nèi)容，并基于現(xiàn)有文獻(xiàn)，對(duì)國(guó)內(nèi)外航天器部件微振動(dòng)隔振技術(shù)進(jìn)行了歸納和總結(jié)，尤其對(duì)航天器上微振動(dòng)的主要擾動(dòng)源——姿態(tài)控制組件的隔振技術(shù)進(jìn)行了詳細(xì)介紹。 第二章：基于ANSYS數(shù)值仿真軟件，對(duì)多桿粘性流體阻尼器并聯(lián)隔振平臺(tái)進(jìn)行仿真分析。首先介紹并聯(lián)隔振平臺(tái)有限元模型的建模過(guò)程，再對(duì)模型進(jìn)行模態(tài)、諧響應(yīng)和瞬態(tài)響應(yīng)動(dòng)力學(xué)分析，研究隔振裝置的隔振性能，為進(jìn)一步的優(yōu)化工作提供基礎(chǔ)。 第三章：采用基于頻響函數(shù)綜合的子結(jié)構(gòu)方法對(duì)并聯(lián)隔振平臺(tái)進(jìn)行建模和模型參數(shù)的優(yōu)化。首先將系統(tǒng)劃分為各獨(dú)立的子結(jié)構(gòu)，推導(dǎo)出各子結(jié)構(gòu)的頻響函數(shù)、傳遞函數(shù)，再利用各子結(jié)構(gòu)之間的位移連續(xù)和力平衡推導(dǎo)出總體系統(tǒng)的輸入和輸出的關(guān)系，最后針對(duì)選定的優(yōu)化目標(biāo)，利用靈敏度分析的方法對(duì)阻尼器的特征參數(shù)進(jìn)行優(yōu)化。 第四章：針對(duì)某型號(hào)航天器微振動(dòng)隔離的需求，提出了一種新型的彈性平面索網(wǎng)隔振結(jié)構(gòu)。首先對(duì)該隔振結(jié)構(gòu)的基本要素——張緊弦索的受力特性進(jìn)行分析，建立其受力-變形之間的非線性解析表達(dá)式；其次建立彈性平面索網(wǎng)隔振結(jié)構(gòu)的等效動(dòng)力學(xué)模型，對(duì)彈性平面索網(wǎng)隔振結(jié)構(gòu)的非線性動(dòng)力學(xué)響應(yīng)特性進(jìn)行分析。 第五章：對(duì)彈性平面索網(wǎng)隔振結(jié)構(gòu)進(jìn)行試驗(yàn)研究，通過(guò)錘擊激勵(lì)下的模態(tài)測(cè)試和振動(dòng)臺(tái)激勵(lì)下的傳遞特性測(cè)試，驗(yàn)證平面索網(wǎng)結(jié)構(gòu)的隔振性能。并對(duì)實(shí)驗(yàn)數(shù)據(jù)進(jìn)行整理分析，得出對(duì)指導(dǎo)彈性平面索網(wǎng)隔振結(jié)構(gòu)的設(shè)計(jì)具有較高參考價(jià)值的結(jié)論。 第六章：對(duì)論文的研究工作、創(chuàng)新點(diǎn)以及今后的研究進(jìn)行了總結(jié)和歸納。
[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.
【學(xué)位授予單位】：上海交通大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2013
【分類號(hào)】：TB535.1;V414

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