發(fā)布時(shí)間：2018-01-23 20:40

  本文關(guān)鍵詞： 兩行軌道根數(shù) 空間碎片 環(huán)境建模 T-H方程 誤差傳播 空域劃分 空間密度 速度分布 碰撞流量　出處：《國(guó)防科學(xué)技術(shù)大學(xué)》2013年碩士論文　論文類(lèi)型：學(xué)位論文

【摘要】：空間碎片環(huán)境建模是一項(xiàng)復(fù)雜的、綜合性的工程項(xiàng)目,是保障在軌航天器的安全運(yùn)行,維護(hù)我國(guó)空間安全,保護(hù)空間環(huán)境必須研究的課題。本文結(jié)合歷史軌道數(shù)據(jù),對(duì)空間碎片環(huán)境建模中的關(guān)鍵技術(shù)問(wèn)題進(jìn)行了研究,并對(duì)觀測(cè)數(shù)據(jù)的誤差傳播進(jìn)行了分析。論文的主要研究成果如下:基于T-H方程研究了橢圓軌道初始誤差傳播。利用相對(duì)運(yùn)動(dòng)理論研究初始誤差傳播,將軌道預(yù)報(bào)誤差看作空間目標(biāo)預(yù)報(bào)位置相對(duì)真實(shí)位置的相對(duì)運(yùn)動(dòng)�；赥-H方程推導(dǎo)了同時(shí)適用于圓軌道和橢圓軌道的顯式誤差傳播函數(shù),得到了圓軌道和橢圓軌道上初始誤差的傳播規(guī)律。并對(duì)橢圓軌道近地點(diǎn)處誤差傳播的非高斯特性進(jìn)行了分析與修正。確定了等面積空域劃分方案及空間單元編號(hào)規(guī)則和結(jié)構(gòu)體設(shè)計(jì)。建立了等面積空域劃分方法的數(shù)學(xué)模型,并結(jié)合論文中采用的劃分方案對(duì)空間單元的編號(hào)規(guī)則進(jìn)行了詳細(xì)的說(shuō)明,對(duì)用于存儲(chǔ)空間單元信息的結(jié)構(gòu)體進(jìn)行了設(shè)計(jì)。研究了空間碎片的空間密度模型與計(jì)算方法。在假設(shè)空間碎片的位置關(guān)于軌道高度、緯度及經(jīng)度的分布獨(dú)立的基礎(chǔ)上,對(duì)空間密度函數(shù)進(jìn)行了研究,得到了空間碎片在高度、緯度和經(jīng)度上的停留概率函數(shù),并根據(jù)工程應(yīng)用對(duì)空間密度函數(shù)進(jìn)行簡(jiǎn)化。對(duì)LEO區(qū)域和GEO區(qū)域的空間密度進(jìn)行驗(yàn)證,得到了與MASTER2005模型類(lèi)似的結(jié)果。研究了空間碎片的碰撞流量模型與計(jì)算方法�？臻g碎片的碰撞流量是目標(biāo)軌道在一個(gè)運(yùn)行周期內(nèi)遭受到的空間碎片的碰撞統(tǒng)計(jì),首先對(duì)一個(gè)空間單元內(nèi)碰撞流量的計(jì)算方法進(jìn)行了研究,然后擴(kuò)展到整個(gè)目標(biāo)軌道碰撞流量的計(jì)算。并對(duì)空間目標(biāo)在當(dāng)?shù)厮矫鎯?nèi)的碰撞幾何進(jìn)行了分析,得到了在當(dāng)?shù)厮矫鎯?nèi)碰撞方位角的計(jì)算公式。對(duì)LEO區(qū)域的國(guó)際空間站和GEO區(qū)域的銀河通信衛(wèi)星受到的空間碎片碰撞流量進(jìn)行了數(shù)值仿真。對(duì)空間碎片碰撞流量的應(yīng)用進(jìn)行了研究�；赥-H方程研究了空間碎片實(shí)際位置的散布情況,得到實(shí)際位置散布在以預(yù)報(bào)位置為中心的誤差橢球內(nèi)的結(jié)論,并對(duì)未來(lái)空間碎片瞬時(shí)分布進(jìn)行短期預(yù)測(cè),驗(yàn)證T-H方程用于軌道預(yù)報(bào)的可行性。詳細(xì)分析了美俄衛(wèi)星碰撞事件對(duì)LEO區(qū)域空間碎片環(huán)境的影響,驗(yàn)證了空間碎片環(huán)境模型的實(shí)用性。
[Abstract]:Space debris environment modeling is a complex and comprehensive engineering project, which is to ensure the safety operation of orbiting spacecraft and to maintain the space security of our country. This paper studies the key technology of space debris environment modeling based on the historical orbit data. The main research results are as follows: the initial error propagation of elliptical orbit is studied based on T-H equation and the initial error propagation is studied by relative motion theory. The orbit prediction error is regarded as the relative motion of the relative real position of the space target. Based on the T-H equation, the explicit error propagation function is derived, which is suitable for both circular orbit and elliptical orbit. The propagation law of initial error in circular orbit and elliptical orbit is obtained. The non-#china_person0# characteristic of error propagation at perigee of elliptical orbit is analyzed and corrected. The plan of equal area space division and the number of space unit are determined. Rules and structure design. The mathematical model of equal area space division method is established. Combined with the partition scheme adopted in the paper, the numbering rules of space units are explained in detail. The space density model and calculation method of space debris are studied. The orbital height is assumed to be the position of space debris. On the basis of the independent distribution of latitude and longitude, the spatial density function is studied, and the retention probability functions of space debris in altitude, latitude and longitude are obtained. The spatial density function is simplified according to the engineering application. The spatial density of LEO region and GEO region is verified. The result is similar to that of MASTER2005 model. The collision flow model and calculation method of space debris are studied. The collision flux of space debris is the space that the target orbit suffers in one operating cycle. Collision statistics of debris. First, the calculation method of collision flow in a space unit is studied, and then extended to the calculation of collision flow of the whole target orbit, and the collision geometry of space target in the local horizontal plane is analyzed. The formula for calculating the azimuth of collision in the local horizontal plane is obtained. The space debris collision flow from the International Space Station in the LEO region and the Galactic Communications Satellite in the GEO region is numerically simulated. The application of collision flow is studied. The dispersion of space debris is studied based on T-H equation. The conclusion that the actual position is scattered in the error ellipsoid centered on the prediction position is obtained, and the short-term prediction of the instantaneous distribution of space debris in the future is made. The feasibility of applying T-H equation to orbit prediction is verified. The effects of the collision events between the United States and Russia on the space debris environment in the LEO region are analyzed in detail, and the practicability of the space debris environment model is verified.
【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(lèi)號(hào)】：V528;X738
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本文編號(hào)：1458188