本文關(guān)鍵詞： 衛(wèi)星編隊(duì) 相對(duì)運(yùn)動(dòng) 卡爾曼濾波 相對(duì)定位 定軌 GPS　出處：《國(guó)防科學(xué)技術(shù)大學(xué)》2013年碩士論文　論文類型：學(xué)位論文

【摘要】：編隊(duì)飛行衛(wèi)星是目前國(guó)內(nèi)外航天領(lǐng)域重點(diǎn)研究的問題之一,因其飛行軌道距離很近,軌道精度需求高,依靠傳統(tǒng)的無線電載波測(cè)量的定軌方法,已無法滿足編隊(duì)飛行衛(wèi)星定軌的要求。隨著航天技術(shù)的發(fā)展,國(guó)內(nèi)外提出了基于GPS的編隊(duì)飛行衛(wèi)星定軌方案。本文在研究編隊(duì)飛行衛(wèi)星相對(duì)運(yùn)動(dòng)規(guī)律的基礎(chǔ)上,重點(diǎn)討論了以典型的兩顆衛(wèi)星為代表的編隊(duì)飛行衛(wèi)星的GPS定軌問題。主要研究?jī)?nèi)容如下:1.進(jìn)行了編隊(duì)飛行衛(wèi)星GPS定軌設(shè)計(jì),GPS為編隊(duì)飛行衛(wèi)星提提供厘米級(jí)相對(duì)定位位置信息,幾十納秒級(jí)的相對(duì)時(shí)差測(cè)量精度時(shí)間信息。2.分析了基于GPS的絕對(duì)定位的誤差。由分析可以得出,利用GPS定軌能夠提供6cm高精度相對(duì)定軌測(cè)量精度指標(biāo),完全能夠滿足編隊(duì)飛行衛(wèi)星對(duì)相對(duì)時(shí)間精度要求。3.設(shè)計(jì)了編隊(duì)飛行衛(wèi)星GPS定軌算法,該方法以位置或相對(duì)位置為參數(shù)建立狀態(tài)方程,并采用卡爾曼濾波算法對(duì)絕對(duì)和相對(duì)定位濾波方程進(jìn)行狀態(tài)估計(jì)。4.進(jìn)行了衛(wèi)星編隊(duì)飛行GPS定軌的仿真系統(tǒng)設(shè)計(jì)。該仿真系統(tǒng)主要進(jìn)行基于GPS模擬信號(hào)仿真,并將GPS仿真器輸出的仿真值與理論值的比對(duì)和分析,得出誤差結(jié)果。
[Abstract]:Formation flying satellite is one of the key research problems in the field of spaceflight at home and abroad. Because of its close orbit distance and high orbit precision, it relies on the traditional method of orbit determination based on radio carrier measurement. It can not meet the requirements of orbit determination of formation flying satellites. With the development of space technology. The orbit determination scheme of formation flying satellites based on GPS is put forward at home and abroad. In this paper, the relative motion rules of formation flying satellites are studied. The GPS orbit determination of formation flying satellites represented by two typical satellites is discussed emphatically. The main research contents are as follows: 1. The design of GPS orbit determination for formation flying satellites is carried out. GPS provides centimeter-level relative position information for formation flying satellites. The accuracy time information of relative time difference measurement of tens of nanoseconds. 2. The error of absolute positioning based on GPS is analyzed. GPS orbit determination can provide 6 cm high precision relative orbit determination precision index, which can completely meet the relative time precision requirements of formation flying satellites. 3. The GPS orbit determination algorithm of formation flying satellites is designed. The equation of state is established with the parameter of position or relative position. The Kalman filtering algorithm is used to estimate the absolute and relative position filtering equations. Finally, the simulation system of GPS orbit determination for satellite formation flight is designed. The simulation system is mainly based on GPS analog signal. Simulation. The simulation value and theoretical value of GPS simulator are compared and analyzed, and the error results are obtained.
【學(xué)位授予單位】：國(guó)防科學(xué)技術(shù)大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2013
【分類號(hào)】：V412.41;P228.4

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本文編號(hào)：1490613