本文關(guān)鍵詞： 近地空間目標(biāo) 軌道預(yù)報(bào) 初軌確定 跟蹤濾波　出處：《哈爾濱工業(yè)大學(xué)》2015年碩士論文　論文類型：學(xué)位論文

【摘要】：空間目標(biāo)監(jiān)測(cè)是國(guó)家空間戰(zhàn)略信息獲取的重要途徑,對(duì)國(guó)家安全有著重要意義,其中軌道預(yù)報(bào)是空間監(jiān)測(cè)任務(wù)的基礎(chǔ)環(huán)節(jié)。近地軌道由于空間環(huán)境較為復(fù)雜,實(shí)際任務(wù)中往往使用僅考慮地球非球形攝動(dòng)主要攝動(dòng)項(xiàng)的模型進(jìn)行軌道預(yù)報(bào),因此成為該領(lǐng)域的研究熱點(diǎn)和難點(diǎn)。因此,本文針對(duì)近地空間目標(biāo)高精度軌道預(yù)報(bào)算法的研究具有重要的理論意義和應(yīng)用價(jià)值。首先,本文查閱了大量文獻(xiàn),總結(jié)了目前國(guó)內(nèi)外針對(duì)軌道預(yù)報(bào)和初軌確定的研究現(xiàn)狀,介紹了軌道動(dòng)力學(xué)研究所用到的時(shí)間和坐標(biāo)系系統(tǒng),分析了軌道動(dòng)力學(xué)模型和受攝運(yùn)動(dòng)模型,推導(dǎo)了相對(duì)運(yùn)動(dòng)方程。然后,研究了空間合作目標(biāo)的軌道預(yù)報(bào)算法,從絕對(duì)軌道預(yù)報(bào)解析算法和數(shù)值算法兩個(gè)方面展開,結(jié)合軌道動(dòng)力學(xué)中對(duì)攝動(dòng)理論的研究,考慮主要攝動(dòng)因素,建立了較為完善的受攝動(dòng)力學(xué)模型,分析了近地空間目標(biāo)在軌運(yùn)行特征,并給出不同攝動(dòng)條件下的高精度數(shù)值算法。其次,研究了天基觀測(cè)的初軌確定算法。首先分析了天基觀測(cè)的方式和模型,然后從幾何條件和光學(xué)條件兩個(gè)方面出發(fā)研究了天基觀測(cè)的可觀測(cè)性,在傳統(tǒng)Laplace定軌方法基礎(chǔ)上推導(dǎo)了考慮2J攝動(dòng)的定軌方法,同時(shí),研究了考慮2J攝動(dòng)的迭代初值選取問(wèn)題,提高了定軌精度,保證了迭代的收斂性,并進(jìn)行了仿真分析。最后,研究了非合作目標(biāo)軌道跟蹤預(yù)報(bào)問(wèn)題。首先推導(dǎo)了C-W方程的狀態(tài)空間表達(dá)式和天基觀測(cè)的觀測(cè)模型,然后基于卡爾曼濾波原理設(shè)計(jì)跟蹤濾波器,得到相對(duì)軌道數(shù)據(jù),并結(jié)合天基平臺(tái)的數(shù)據(jù)轉(zhuǎn)化為絕對(duì)軌道,實(shí)現(xiàn)了在僅知道當(dāng)前時(shí)刻天基平臺(tái)的軌道數(shù)據(jù)和短弧段內(nèi)對(duì)目標(biāo)的觀測(cè)信息情況下的軌道預(yù)報(bào)技術(shù),并進(jìn)行了數(shù)學(xué)仿真分析。
[Abstract]:Space target monitoring is an important way to obtain national space strategic information, which is of great significance to national security. Orbit prediction is the basic link of space monitoring mission. Low Earth orbit is more complex because of the space environment. In practical missions, the model which only considers the main perturbation terms of the earth's non-spherical perturbation is often used for orbit prediction, so it has become a hot and difficult point in this field. In this paper, the research of high-precision orbit prediction algorithm for near-Earth space targets has important theoretical significance and application value. First, this paper consulted a large number of literature. This paper summarizes the research status of orbit prediction and initial orbit determination at home and abroad, introduces the time and coordinate system used in orbit dynamics research, and analyzes orbit dynamics model and perturbation motion model. The relative motion equation is derived. Then, the orbit prediction algorithm of space cooperative target is studied, which is developed from the two aspects of absolute orbit prediction analytical algorithm and numerical algorithm, combined with the study of perturbation theory in orbit dynamics. Taking into account the main perturbation factors, a more perfect dynamic model of the perturbation is established, and the characteristics of orbiting operation of the near-surface space target are analyzed, and the high-precision numerical algorithm under different perturbation conditions is given. Secondly. The algorithm of determining the initial orbit of space-based observation is studied. Firstly, the mode and model of space-based observation are analyzed, and then the observability of space-based observation is studied in terms of geometry and optical conditions. Based on the traditional Laplace orbit determination method, the orbit determination method considering 2J perturbation is derived. At the same time, the iterative initial value selection problem considering 2J perturbation is studied to improve the orbit determination accuracy. The convergence of the iteration is guaranteed, and the simulation analysis is carried out. Finally, the prediction problem of non-cooperative target orbit tracking is studied. Firstly, the state space expression of C-W equation and the observation model of space-based observation are derived. Then the tracking filter is designed based on the principle of Kalman filter, and the relative orbit data is obtained, and the data of space-based platform is transformed into absolute orbit. In this paper, the orbit prediction technology is realized under the condition of only knowing the orbit data of the space-based platform and the observation information of the target in the short arc segment, and the mathematical simulation analysis is carried out.
【學(xué)位授予單位】：哈爾濱工業(yè)大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2015
【分類號(hào)】：V412.41

【參考文獻(xiàn)】

相關(guān)期刊論文 前4條

1 吳勤;;美國(guó)空間對(duì)抗裝備與技術(shù)新進(jìn)展[J];國(guó)際太空;2010年01期

2 楊維廉;;兩行根數(shù)的精度評(píng)估[J];航天器工程;2009年03期

3 李俊峰,孟鑫,高云峰,李響;J_2攝動(dòng)對(duì)編隊(duì)飛行衛(wèi)星相對(duì)軌道構(gòu)形的影響[J];清華大學(xué)學(xué)報(bào)(自然科學(xué)版);2004年02期

4 童科偉;周建平;何麟書;;近地衛(wèi)星簡(jiǎn)化軌道預(yù)報(bào)方法研究[J];宇航學(xué)報(bào);2009年04期

，

本文編號(hào)：1463872