本文關(guān)鍵詞： 衛(wèi)星 撓性附件 質(zhì)量特性參數(shù) 參數(shù)辨識(shí)　出處：《大連理工大學(xué)》2016年碩士論文　論文類型：學(xué)位論文

【摘要】：地面試驗(yàn)的方法測(cè)量衛(wèi)星質(zhì)量特性參數(shù)存在著成本高,精度低,質(zhì)量特性參數(shù)在軌變化無能為力等問題。在軌辨識(shí)則可以解決這些問題。傳統(tǒng)的衛(wèi)星質(zhì)量特性參數(shù)在軌辨識(shí)研究均是將衛(wèi)星視為剛體,沒有考慮撓性附件振動(dòng)對(duì)質(zhì)量特性參數(shù)辨識(shí)的影響。而隨著衛(wèi)星攜帶的撓性附件越來越大,衛(wèi)星的大型撓性附件振動(dòng)對(duì)衛(wèi)星的質(zhì)量特性參數(shù)在軌辨識(shí)的影響不可忽略。因此開展帶撓性附件衛(wèi)星質(zhì)量特性參數(shù)在軌辨識(shí)研究,不僅可以準(zhǔn)確得知衛(wèi)星的質(zhì)量特性參數(shù),還可以為衛(wèi)星控制系統(tǒng)的設(shè)計(jì)與調(diào)整提供參考依據(jù),具有重要的應(yīng)用價(jià)值。針對(duì)帶撓性附件衛(wèi)星質(zhì)量特性參數(shù)在軌辨識(shí)的問題,本文的主要內(nèi)容主要包括以下幾部分：(1)研究了剛體衛(wèi)星質(zhì)量特性參數(shù)辨識(shí)的方法。剛體衛(wèi)星質(zhì)量特性參數(shù)辨識(shí)的研究是帶撓性附件衛(wèi)星質(zhì)量特性參數(shù)辨識(shí)研究的基礎(chǔ),利用遞推最小二乘法和多變量并發(fā)遞推最小二乘法實(shí)現(xiàn)了剛體衛(wèi)星單個(gè)或多個(gè)質(zhì)量特性參數(shù)的辨識(shí)。(2)研究了衛(wèi)星小角度機(jī)動(dòng)情況下,衛(wèi)星撓性附件振動(dòng)對(duì)質(zhì)量特性參數(shù)辨識(shí)的影響,并提出了帶撓性附件衛(wèi)星質(zhì)量特性參數(shù)辨識(shí)的遞推算法。算法首先推導(dǎo)了質(zhì)量特性參數(shù)的最小二乘描述形式,之后利用卡爾曼濾波算法推導(dǎo)了撓性附件振動(dòng)模態(tài)的狀態(tài)估計(jì),最后將質(zhì)量特性參數(shù)的最小二乘描述形式和撓性附件振動(dòng)模態(tài)的卡爾曼濾波相結(jié)合,形成了完整的遞推算法。仿真算例驗(yàn)證了衛(wèi)星撓性附件振動(dòng)對(duì)質(zhì)量特性參數(shù)辨識(shí)的影響和文中遞推算法的有效性。(3)研究了衛(wèi)星大角度機(jī)動(dòng)情況下,帶撓性附件衛(wèi)星質(zhì)量特性參數(shù)的辨識(shí)算法。當(dāng)衛(wèi)星大角度機(jī)動(dòng)情況時(shí),衛(wèi)星的動(dòng)力學(xué)模型存在非線性,本文提出的最小二乘和卡爾曼濾波相結(jié)合的并發(fā)遞推算法并不適用。針對(duì)這一問題,本文提出了基于擴(kuò)展卡爾曼濾波的帶撓性附件衛(wèi)星質(zhì)量特性參數(shù)的辨識(shí)算法。仿真算例的結(jié)果證明了利用擴(kuò)展卡爾曼濾波算法辨識(shí)帶撓性附件衛(wèi)星質(zhì)量特性參數(shù)是有效的。
[Abstract]:The method of ground test has high cost and low precision in measuring satellite mass characteristic parameters. These problems can be solved by the on-orbit identification of the mass characteristic parameters, which can be solved by the on-orbit identification. The traditional research on the on-orbit identification of the mass characteristic parameters of the satellite is to treat the satellite as a rigid body. The effect of vibration of flexible appendages on the identification of mass characteristic parameters is not considered. However, the flexible appendages carried by satellites are becoming larger and larger. The influence of the large flexible satellite vibration on the on-orbit identification of satellite mass characteristic parameters can not be ignored. Therefore, the research on the on-orbit identification of satellite mass characteristic parameters with flexible appendages is carried out. Not only the parameters of satellite quality characteristics can be accurately obtained, but also the reference for the design and adjustment of satellite control system can be provided. It has important application value, aiming at the problem of on-orbit identification of satellite mass characteristic parameters with flexible appendages. The main contents of this paper include the following parts: 1). The method of mass characteristic parameter identification of rigid satellite is studied. The research of mass characteristic parameter identification of rigid body satellite is the foundation of mass characteristic parameter identification of satellite with flexible attachment. The recursive least square method and multivariable concurrent recursive least square method are used to identify the single or multiple mass characteristic parameters of rigid satellite. The influence of satellite flexible attachment vibration on mass characteristic parameter identification is discussed. A recursive algorithm for mass characteristic parameter identification of satellite with flexible attachment is proposed. First, the least square description of mass characteristic parameter is derived. Then the state estimation of the vibration mode of the flexible attachment is deduced by using the Kalman filter algorithm. Finally, the least square description of the mass characteristic parameters is combined with the Kalman filter of the vibration mode of the flexible attachment. A complete recursive algorithm is formed. A simulation example is given to verify the effect of the vibration of satellite flexible appendages on the identification of mass characteristic parameters and the effectiveness of the recursive algorithm in this paper. Identification algorithm of satellite mass characteristic parameters with flexible appendages. When the satellite maneuvers at large angles, the dynamic model of the satellite is nonlinear. The parallel recursive algorithm combined with least square and Kalman filter is not applicable in this paper. In this paper, an identification algorithm of satellite mass characteristic parameters with flexible attachments based on extended Kalman filter is proposed. The simulation results show that the extended Kalman filter algorithm is used to identify the satellite mass characteristic parameters with flexible attachments. Is valid.
【學(xué)位授予單位】：大連理工大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2016
【分類號(hào)】：V416

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