太陽(yáng)帆航天器軌道和姿態(tài)耦合設(shè)計(jì)與優(yōu)化
發(fā)布時(shí)間：2019-05-27 04:52
【摘要】：太陽(yáng)帆以其無(wú)燃料推進(jìn)、比沖無(wú)限大、任務(wù)豐富等優(yōu)勢(shì),最有可能成為未來(lái)深空探測(cè)實(shí)際而有效的推進(jìn)方式之一。太陽(yáng)帆軌道和姿態(tài)耦合設(shè)計(jì)與優(yōu)化對(duì)太陽(yáng)帆系統(tǒng)設(shè)計(jì)有著至關(guān)重要的意義和實(shí)際工程價(jià)值。本文在考慮太陽(yáng)帆軌道和姿態(tài)耦合情況下,系統(tǒng)地研究了懸浮軌道設(shè)計(jì)與控制、轉(zhuǎn)移軌道設(shè)計(jì)與優(yōu)化、柔性太陽(yáng)帆動(dòng)力學(xué)與控制問(wèn)題,開(kāi)發(fā)了工具軟件。主要研究?jī)?nèi)容如下:首先,研究了太陽(yáng)帆日心懸浮軌道和姿態(tài)耦合設(shè)計(jì)與控制問(wèn)題。基于日心懸浮軌道穩(wěn)定性條件,設(shè)計(jì)了僅要求姿態(tài)角保持不變的被動(dòng)控制律,仿真表明該控制律可使太陽(yáng)帆穩(wěn)定在懸浮軌道附近。研究了基于LQR的主動(dòng)控制律,取得了較高的懸浮軌道控制精度。通過(guò)研究懸浮軌道和開(kāi)普勒軌道空間位置關(guān)系,提出了懸浮軌道參數(shù)和開(kāi)普勒軌道六根數(shù)之間的關(guān)系式以及懸浮軌道之間拼接的條件。其次,研究了太陽(yáng)帆轉(zhuǎn)移軌道和姿態(tài)耦合設(shè)計(jì)和優(yōu)化問(wèn)題。基于能量變化率最大的控制律設(shè)計(jì)逃逸地球影響球軌道,比較了理想和非理性帆面、考慮地影和不考慮地影時(shí)對(duì)飛行時(shí)間的影響。提出了太陽(yáng)帆行星際轉(zhuǎn)移軌道全局優(yōu)化算法,地球到火星轉(zhuǎn)移算例驗(yàn)證了該算法的有效性。針對(duì)太陽(yáng)帆飛向日心懸浮軌道的轉(zhuǎn)移軌道問(wèn)題,提出了通過(guò)將姿態(tài)角離散成分段函數(shù),并利用遺傳算法和SQP聯(lián)合運(yùn)算獲得全局高精度解的方法,該方法在滿足懸浮軌道約束下能夠快速獲取轉(zhuǎn)移軌道。提出了附加行星借力和太陽(yáng)光壓輔助的太陽(yáng)帆逃逸太陽(yáng)系轉(zhuǎn)移方法,并與直接逃逸和僅太陽(yáng)光壓輔助逃逸這兩種方法進(jìn)行了比較,仿真表明聯(lián)合借力所需飛行時(shí)間最少。針對(duì)太陽(yáng)帆轉(zhuǎn)移軌道任務(wù)設(shè)計(jì)周期長(zhǎng)和分析能力有限的問(wèn)題,提出了基于STK的太陽(yáng)帆轉(zhuǎn)移軌道任務(wù)仿真方法,該方法能夠快速而靈活地支持復(fù)雜太陽(yáng)帆任務(wù),并增強(qiáng)了任務(wù)場(chǎng)景的可視化,易于工程應(yīng)用。再次,研究了柔性太陽(yáng)帆動(dòng)力學(xué)與控制問(wèn)題。設(shè)計(jì)了太陽(yáng)帆姿態(tài)控制系統(tǒng)的敏感器配置、執(zhí)行機(jī)構(gòu)和控制器方案。通過(guò)有限元仿真分析表明太陽(yáng)帆可視為中心剛體附加撓性附件模型來(lái)計(jì)算耦合系數(shù)。針對(duì)剛體太陽(yáng)帆模型對(duì)撓性帆面振動(dòng)的缺失,建立的中心剛體附加撓性附件形式的柔性太陽(yáng)帆姿態(tài)動(dòng)力學(xué)模型既能足夠準(zhǔn)確地描述太陽(yáng)帆姿態(tài)運(yùn)動(dòng),又便于進(jìn)行姿態(tài)控制,仿真結(jié)果具有一定的工程參考價(jià)值。針對(duì)太陽(yáng)帆高精度長(zhǎng)期飛行的需求,建立的全柔性太陽(yáng)帆動(dòng)力學(xué)模型體現(xiàn)了軌道、姿態(tài)和振動(dòng)耦合的全部特性,分析表明忽略太陽(yáng)帆柔性振動(dòng)的影響,將導(dǎo)致星際轉(zhuǎn)移軌道和姿態(tài)偏離理論軌道和姿態(tài)數(shù)據(jù),并最終影響飛行任務(wù)。最后,開(kāi)發(fā)了太陽(yáng)帆軌道和姿態(tài)耦合仿真的工具軟件。介紹了“太陽(yáng)帆航天器軌道設(shè)計(jì)與控制軟件”、“太陽(yáng)帆航天器姿態(tài)控制仿真系統(tǒng)”和“采用引力輔助和太陽(yáng)光壓輔助的太陽(yáng)帆飛往外太陽(yáng)系任務(wù)仿真軟件”的軟件功能和軟件結(jié)構(gòu),結(jié)合文中部分算例給出了相應(yīng)的操作說(shuō)明。完成了軟件升級(jí)版本“太陽(yáng)帆航天器軌道和姿態(tài)耦合仿真軟件”的架構(gòu)設(shè)計(jì)、用戶界面和相關(guān)操作。
[Abstract]:The solar sail has the advantages of no fuel propulsion, infinite impulse and rich task, and is most likely to be one of the practical and effective ways to detect the future deep space. The design and optimization of the solar sail rail and attitude coupling are of great importance to the design of the solar sail system and the practical engineering value. In this paper, the design and control of the suspension rail, the design and optimization of the transfer track, the dynamics and control of the flexible solar sail are systematically studied in the light of the orbital and attitude coupling of the solar sail, and the tool software is developed. The main contents of the study are as follows: First, the design and control of the sun-sail sun-core suspension orbit and the attitude coupling are studied. Based on the stability of the sun-core suspension orbit, a passive control law is designed to keep the attitude angle unchanged, and the simulation shows that the control law can stabilize the solar sail near the levitation track. The active control law based on LQR is studied, and the control precision of the suspension track is obtained. By studying the relation between the suspension orbit and the Kepler orbit space, the relation between the suspension orbit parameter and the six-root number of Kepler orbit and the condition of the joint between the suspended track and the floating track are put forward. Secondly, the design and optimization of the transfer orbit and attitude of the solar sail are studied. The control law based on the maximum energy change rate is designed to escape the earth to influence the ball track, and the ideal and non-rational sailplane is compared, and the effect on the time of flight is considered when the shadow is taken into account and the shadow is not taken into account. In this paper, a global optimization algorithm for the interplanetary transfer orbit of the solar sail is proposed, and the validity of the algorithm is verified by an example of the earth-to-Mars transition. In order to solve the problem of the transfer orbit of the sun-sail to the sun-core suspension orbit, a method for obtaining a global high-precision solution by combining the position-angle discrete component function and the combination of genetic algorithm and SQP is proposed. The method can quickly acquire the transfer orbit under the constraint of the suspension orbit. The method of the solar-sail escape solar system with additional planetary force and sunlight pressure is proposed, and the two methods are compared with the direct-escape and the solar-pressure-assisted escape, and the simulation results show that the flying time required by the combined borrowing force is the least. Aiming at the problems of long design period and limited analytical capacity of the solar sail transfer orbit task, a method for simulating the task of a sun-sail transfer orbit based on STK is proposed, which can support the task of the complex solar sail quickly and flexibly, and enhance the visualization of the task scene and is easy for engineering application. Thirdly, the dynamics and control of the flexible solar sail are studied. The sensor configuration, actuator and controller scheme of the attitude control system of the solar sail are designed. The finite element simulation analysis shows that the solar sail can be regarded as an additional flexible attachment model of the central rigid body to calculate the coupling coefficient. aiming at the deficiency of the rigid body solar sail model to the vibration of the flexible sail surface, the flexible solar sail attitude dynamic model in the form of an additional flexible attachment of the central rigid body can not only accurately describe the attitude movement of the solar sail, but also facilitate the attitude control, The simulation results are of certain reference value. Aiming at the requirement of high-precision long-term flying of the solar sail, the full-flexible solar-sail dynamic model is established, and all the characteristics of the orbit, the attitude and the vibration coupling are reflected, the analysis shows that the influence of the flexible vibration of the solar sail is ignored, and the interplanetary transfer orbit and the attitude deviation are caused to deviate from the theoretical track and the attitude data, And ultimately affect the mission. Finally, the tool software for the simulation of the solar sail orbit and the attitude coupling is developed. The software functions and software structure of the "The orbit design and control software of the solar-sail spacecraft", the "Attitude control simulation system for solar-sail spacecraft" and the "Simulation software of solar sail to external solar system by using gravity-assisted and solar-pressure-assisted sun-sail" are introduced, and the corresponding operation instructions are given in the paper. The architecture design, user interface, and related operations of the software upgrade version "Simulation software for orbital and attitude coupling of solar-sail spacecraft" are completed.
【學(xué)位授予單位】：中國(guó)科學(xué)院研究生院(空間科學(xué)與應(yīng)用研究中心)
【學(xué)位級(jí)別】：博士
【學(xué)位授予年份】：2015
【分類號(hào)】：V448.2
本文編號(hào)：2485912
[Abstract]:The solar sail has the advantages of no fuel propulsion, infinite impulse and rich task, and is most likely to be one of the practical and effective ways to detect the future deep space. The design and optimization of the solar sail rail and attitude coupling are of great importance to the design of the solar sail system and the practical engineering value. In this paper, the design and control of the suspension rail, the design and optimization of the transfer track, the dynamics and control of the flexible solar sail are systematically studied in the light of the orbital and attitude coupling of the solar sail, and the tool software is developed. The main contents of the study are as follows: First, the design and control of the sun-sail sun-core suspension orbit and the attitude coupling are studied. Based on the stability of the sun-core suspension orbit, a passive control law is designed to keep the attitude angle unchanged, and the simulation shows that the control law can stabilize the solar sail near the levitation track. The active control law based on LQR is studied, and the control precision of the suspension track is obtained. By studying the relation between the suspension orbit and the Kepler orbit space, the relation between the suspension orbit parameter and the six-root number of Kepler orbit and the condition of the joint between the suspended track and the floating track are put forward. Secondly, the design and optimization of the transfer orbit and attitude of the solar sail are studied. The control law based on the maximum energy change rate is designed to escape the earth to influence the ball track, and the ideal and non-rational sailplane is compared, and the effect on the time of flight is considered when the shadow is taken into account and the shadow is not taken into account. In this paper, a global optimization algorithm for the interplanetary transfer orbit of the solar sail is proposed, and the validity of the algorithm is verified by an example of the earth-to-Mars transition. In order to solve the problem of the transfer orbit of the sun-sail to the sun-core suspension orbit, a method for obtaining a global high-precision solution by combining the position-angle discrete component function and the combination of genetic algorithm and SQP is proposed. The method can quickly acquire the transfer orbit under the constraint of the suspension orbit. The method of the solar-sail escape solar system with additional planetary force and sunlight pressure is proposed, and the two methods are compared with the direct-escape and the solar-pressure-assisted escape, and the simulation results show that the flying time required by the combined borrowing force is the least. Aiming at the problems of long design period and limited analytical capacity of the solar sail transfer orbit task, a method for simulating the task of a sun-sail transfer orbit based on STK is proposed, which can support the task of the complex solar sail quickly and flexibly, and enhance the visualization of the task scene and is easy for engineering application. Thirdly, the dynamics and control of the flexible solar sail are studied. The sensor configuration, actuator and controller scheme of the attitude control system of the solar sail are designed. The finite element simulation analysis shows that the solar sail can be regarded as an additional flexible attachment model of the central rigid body to calculate the coupling coefficient. aiming at the deficiency of the rigid body solar sail model to the vibration of the flexible sail surface, the flexible solar sail attitude dynamic model in the form of an additional flexible attachment of the central rigid body can not only accurately describe the attitude movement of the solar sail, but also facilitate the attitude control, The simulation results are of certain reference value. Aiming at the requirement of high-precision long-term flying of the solar sail, the full-flexible solar-sail dynamic model is established, and all the characteristics of the orbit, the attitude and the vibration coupling are reflected, the analysis shows that the influence of the flexible vibration of the solar sail is ignored, and the interplanetary transfer orbit and the attitude deviation are caused to deviate from the theoretical track and the attitude data, And ultimately affect the mission. Finally, the tool software for the simulation of the solar sail orbit and the attitude coupling is developed. The software functions and software structure of the "The orbit design and control software of the solar-sail spacecraft", the "Attitude control simulation system for solar-sail spacecraft" and the "Simulation software of solar sail to external solar system by using gravity-assisted and solar-pressure-assisted sun-sail" are introduced, and the corresponding operation instructions are given in the paper. The architecture design, user interface, and related operations of the software upgrade version "Simulation software for orbital and attitude coupling of solar-sail spacecraft" are completed.
【學(xué)位授予單位】：中國(guó)科學(xué)院研究生院(空間科學(xué)與應(yīng)用研究中心)
【學(xué)位級(jí)別】：博士
【學(xué)位授予年份】：2015
【分類號(hào)】：V448.2
【參考文獻(xiàn)】
相關(guān)期刊論文 前8條
1 ;Displaced orbits generated by solar sails for the hyperbolic and degenerated cases[J];Acta Mechanica Sinica;2012年01期
2 駱軍紅;李曉東;馮軍華;;太陽(yáng)帆航天器被動(dòng)姿態(tài)控制研究[J];飛行力學(xué);2008年05期
3 吳季;;中國(guó)的空間探測(cè)及其科學(xué)內(nèi)涵[J];中國(guó)工程科學(xué);2008年06期
4 羅超;鄭建華;;采用滑塊和RSB的太陽(yáng)帆姿態(tài)控制[J];哈爾濱工業(yè)大學(xué)學(xué)報(bào);2011年03期
5 ;Control of large angle maneuvers for the flexible solar sail[J];Science China(Physics,Mechanics & Astronomy);2011年04期
6 韓艷鏵;張震亞;賈杰;;太陽(yáng)帆航天器姿態(tài)控制技術(shù)綜述[J];航天器環(huán)境工程;2013年06期
7 秦建飛;寶音賀西;李俊峰;;飛向Halo軌道的太陽(yáng)帆航天器軌跡優(yōu)化設(shè)計(jì)[J];清華大學(xué)學(xué)報(bào)(自然科學(xué)版);2007年08期
8 龔勝平;李俊峰;寶音賀西;;太陽(yáng)帆參數(shù)對(duì)穩(wěn)定性的影響[J];宇航學(xué)報(bào);2008年03期
相關(guān)博士學(xué)位論文 前1條
1 曾祥遠(yuǎn);深空探測(cè)太陽(yáng)帆航天器新型軌道設(shè)計(jì)[D];清華大學(xué);2013年
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