【摘要】：隨著空間技術(shù)的飛速發(fā)展,具有大口徑、高分辨率的空間望遠鏡在民用、商業(yè)、軍工、天文學(xué)等領(lǐng)域的作用越來越大。但是航天器上的運動設(shè)施(如控制力矩陀螺、反作用飛輪、太陽帆板展開機構(gòu)、斯特林制冷機等)產(chǎn)生的微振動會極大的降低空間望遠鏡的成像質(zhì)量。微振動形式復(fù)雜,具有幅值小、頻率分布范圍廣、振動多向等特點,同時大型空間望遠鏡技術(shù)復(fù)雜,涉及學(xué)科內(nèi)容多,現(xiàn)有的振動抑制措施和分析技術(shù)很難滿足其發(fā)展需求,因此研究與之相關(guān)的微振動抑制技術(shù)、振動集成仿真分析、微振動地面模擬平臺等關(guān)鍵技術(shù),對于大口徑空間望遠鏡的研制具有重要意義。設(shè)計了一種結(jié)構(gòu)簡單的用于空間光學(xué)載荷在軌隔振的隔振器。分析了影響隔振器三向剛度的結(jié)構(gòu)參數(shù),針對不同的載荷,探討了隔振器的布置方式,并測試了其隔振性能�？紤]到粘彈性阻尼材料的剛度和阻尼系數(shù)隨溫度和頻率變化的特性,介紹了一種基于復(fù)剛度的分析粘彈性阻尼材料的計算方法。試驗結(jié)果與分析值一致,表明文中關(guān)于隔振器的設(shè)計和分析方法有效、可靠,最后將該隔振器用于某一光學(xué)遙感器的隔振,分析結(jié)果表明該隔振器能有效抑制安裝面?zhèn)鬟f給光學(xué)遙感器的微振動。開展了多維微振動隔振系統(tǒng)在光學(xué)載荷整體隔振中的應(yīng)用研究。建立了隔振系統(tǒng)的理論模型,得到廣義剛度矩陣和廣義阻尼矩陣。推導(dǎo)出計算多維隔振器固有頻率的數(shù)學(xué)解析式,并給出了優(yōu)化隔振系統(tǒng)構(gòu)型的優(yōu)化方法。同時為評估隔振系統(tǒng)的隔振性能及分析微振動對光學(xué)載荷成像質(zhì)量的影響,提出一種基于有限單元法的振動集成仿真分析方法,該方法在有限元中實現(xiàn)結(jié)構(gòu)、光學(xué)、控制模型的集成,具有求解效率高、數(shù)據(jù)傳遞量小及計算精度高等優(yōu)點。為模擬航天器上擾動源產(chǎn)生的微振動,提出了一種基于Gough—Stewart構(gòu)型的微振動模擬平臺,并開展了兩代樣機的研制。分別利用牛頓——歐拉方法結(jié)合拉格朗日方程和凱恩方程建立了兩代模擬平臺的動力學(xué)方程,并利用ADAMS和Matlab/Simulink軟件進行多體系統(tǒng)的聯(lián)合仿真,驗證了理論模型的準(zhǔn)確性。對第一代模擬平臺的工作性能進行了測試。根據(jù)測試結(jié)果,利用雙變量曲面擬合法對第一代模擬平臺的控制算法進行了修正,大大提升了其工作性能�？紤]到理論模型與實際模型之間的差異性,對微振動模擬平臺的控制策略進行了研究,提出一種基于動力學(xué)模型的PI魯棒控制。理論分析和仿真結(jié)果表明,該控制策略魯棒性強、穩(wěn)定性好,能用于模擬平臺的加速度控制。
[Abstract]:With the rapid development of space technology, space telescopes with large aperture and high resolution are playing an increasingly important role in civil, commercial, military, astronomy and other fields. However, the micro-vibration generated by the motion facilities (such as the control moment gyroscope, the reaction flywheel, the solar panel unfurling mechanism, the Stirling refrigerator, etc.) will greatly reduce the imaging quality of the space telescope. The microvibration forms are complex, the amplitude is small, the frequency range is wide, the vibration is multi-directional and so on. At the same time, the technology of large space telescope is complex and involves many subjects, so the existing vibration suppression measures and analysis techniques are very difficult to meet its development needs. Therefore, it is of great significance for the development of large aperture space telescope to study some key technologies, such as micro-vibration suppression technology, vibration integrated simulation analysis, micro-vibration ground simulation platform and so on. A simple structure vibration isolator for space optical load in orbit is designed. The structural parameters affecting the three-dimensional stiffness of the isolator are analyzed. The layout of the isolator under different loads is discussed and its vibration isolation performance is tested. Considering that the stiffness and damping coefficient of viscoelastic damping materials vary with temperature and frequency, a calculation method based on complex stiffness for viscoelastic damping materials is introduced. The experimental results are in agreement with the analytical values, which show that the design and analysis method of the vibration isolator in this paper is effective and reliable. Finally, the isolator is applied to the vibration isolation of an optical remote sensor. The results show that this isolator can effectively suppress the micro vibration of the mounting surface transferred to the optical remote sensor. The application of multi-dimensional micro-vibration isolation system to the whole vibration isolation of optical load is studied. The theoretical model of the vibration isolation system is established, and the generalized stiffness matrix and the generalized damping matrix are obtained. The mathematical analytical formula for calculating the natural frequency of the multi-dimensional vibration isolator is derived, and the optimization method of the configuration of the vibration isolation system is given. In order to evaluate the vibration isolation performance of vibration isolation system and analyze the influence of micro vibration on the imaging quality of optical load, a vibration integrated simulation analysis method based on finite element method is proposed, which realizes the structure and optics in finite element method. The integration of control model has the advantages of high efficiency, low data transfer and high accuracy. In order to simulate the micro-vibration generated by the disturbance source on the spacecraft, a micro-vibration simulation platform based on Gough-Stewart configuration is proposed, and two generation prototypes are developed. Newton-Euler method combined with Lagrange equation and Kane equation are used to establish the dynamic equations of two generations of simulation platform, and the joint simulation of multi-body system using ADAMS and Matlab/Simulink software is carried out to verify the accuracy of the theoretical model. The performance of the first generation simulation platform is tested. According to the test results, the control algorithm of the first generation simulation platform is modified by using the bivariate surface fitting method, which greatly improves its performance. Considering the difference between the theoretical model and the practical model, the control strategy of the micro-vibration simulation platform is studied, and a dynamic model-based PI robust control is proposed. Theoretical analysis and simulation results show that the proposed control strategy is robust and stable, and can be used to control the acceleration of the platform.
【學(xué)位授予單位】：中國科學(xué)院研究生院(長春光學(xué)精密機械與物理研究所)
【學(xué)位級別】：博士
【學(xué)位授予年份】：2016
【分類號】：TB535.1

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