發(fā)布時(shí)間：2018-05-05 07:30

  本文選題：小衛(wèi)星 + 平面可展開(kāi)結(jié)構(gòu)�。� 參考：《浙江大學(xué)》2015年碩士論文

【摘要】：小衛(wèi)星由于其重量輕、成本低、研制周期短等優(yōu)點(diǎn)受到越來(lái)越多的研究單位的重視,特別是在高校范圍內(nèi)掀起一陣小衛(wèi)星研究的熱潮。但目前的小衛(wèi)星上很少搭載工作平臺(tái),使小衛(wèi)星功能受限。為了拓寬小衛(wèi)星的應(yīng)用領(lǐng)域,迫切需要一種較大的、能夠安裝在小衛(wèi)星上的平臺(tái)結(jié)構(gòu),能夠安裝各種有效載荷。用可展開(kāi)結(jié)構(gòu)作為搭載平臺(tái),能使該平臺(tái)在發(fā)射階段占用空間少、使用時(shí)具有較大的空間,適合在小衛(wèi)星上使用。 論文首先根據(jù)實(shí)際的使用功能需求,提出了一種適合于搭載在小衛(wèi)星上的展開(kāi)結(jié)構(gòu)平臺(tái)設(shè)計(jì)方案,并分別論述了該方案各分系統(tǒng)的方案設(shè)計(jì),從而滿(mǎn)足所有的使用需求。 采用拉索替代分析法對(duì)展開(kāi)狀態(tài)進(jìn)行了模態(tài)分析,并與地面測(cè)試試驗(yàn)作對(duì)比,提出了提高剛度的建議供設(shè)計(jì)參考。 詳細(xì)介紹了用ADAMS軟件對(duì)該平面展開(kāi)結(jié)構(gòu)的展開(kāi)過(guò)程進(jìn)行了仿真,并和地面測(cè)試實(shí)驗(yàn)結(jié)果進(jìn)行了對(duì)比；最后分析了展開(kāi)結(jié)構(gòu)與衛(wèi)星連成整體后在太空中的展開(kāi)過(guò)程,并給出該過(guò)程中的動(dòng)力學(xué)參數(shù)變化趨勢(shì),有助于改善結(jié)構(gòu)設(shè)計(jì)。 基于非接觸攝影測(cè)量法,推導(dǎo)了以桿件與參考平面的傾斜角為表征量的平面度計(jì)算公式并利用無(wú)接觸攝影測(cè)量系統(tǒng)進(jìn)行了平面度測(cè)量；分析了三種不同的重力消除方法對(duì)平面度測(cè)量的影響,對(duì)比了各自的優(yōu)缺點(diǎn)；最后提出了一些保證平面度的措施。這些對(duì)平面可展開(kāi)結(jié)構(gòu)的設(shè)計(jì)有很好的指導(dǎo)作用。 最后,對(duì)收攏狀態(tài)的模型進(jìn)行了整星基頻掃描試驗(yàn)、低頻正弦振動(dòng)試驗(yàn)和隨機(jī)振動(dòng),驗(yàn)證了結(jié)構(gòu)的安全性。
[Abstract]:Because of its advantages of light weight, low cost and short research period, small satellites have been paid more and more attention by more and more research units, especially in colleges and universities. But at present the small satellite rarely carries the working platform, which limits the function of the small satellite. In order to broaden the application field of small satellites, it is urgent to have a large platform structure which can be installed on small satellites and to install various payloads. Using the deployable structure as the platform can make the platform occupy less space in the launch phase and have a large space when used, so it is suitable for use on small satellites. Firstly, according to the actual functional requirements, a design scheme of the unfolded structure platform is proposed, which is suitable for carrying on the small satellite, and the scheme design of each subsystem of the scheme is discussed respectively, so as to meet the needs of all the applications. The modal analysis of the unfolding state is carried out by using the cable substitution analysis method, and compared with the test results on the ground, some suggestions for improving the stiffness are put forward for the design reference. This paper introduces in detail the simulation of the development process of the plane unfolded structure by using ADAMS software, and compares with the experimental results of the ground test, and finally analyzes the unfolding process in space after the unfolded structure and the satellite are connected as a whole. The change trend of dynamic parameters in the process is given, which is helpful to improve the structural design. Based on the contactless photogrammetry, the calculation formula of flatness based on the tilt angle between the bar and the reference plane is derived, and the flatness measurement is carried out by using the contactless photogrammetry system. This paper analyzes the influence of three different gravity elimination methods on flatness measurement, compares their advantages and disadvantages, and finally puts forward some measures to ensure flatness. These can guide the design of planar deployable structures. Finally, the whole satellite fundamental frequency scanning test, low frequency sinusoidal vibration test and random vibration are carried out to verify the safety of the structure.
【學(xué)位授予單位】：浙江大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2015
【分類(lèi)號(hào)】：V423;V416

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本文編號(hào)：1846793