本文關(guān)鍵詞： 空間碎片 天基光學(xué)觀測 初始軌道確定 距離搜索 角度觀測值　出處：《武漢大學(xué)》2017年碩士論文　論文類型：學(xué)位論文

【摘要】：空間目標(biāo)廣泛分布在不同的軌道上,其中絕大部分為空間碎片,嚴(yán)重威脅了在軌航天器的安全運(yùn)行,需要對這些碎片進(jìn)行有效地監(jiān)測跟蹤并進(jìn)行碰撞預(yù)警�？臻g監(jiān)測的主要技術(shù)手段包括光學(xué)、雷達(dá)和激光測距。地基光學(xué)監(jiān)測手段受到了地理位置和觀測時長的限制,僅僅依靠地基監(jiān)測難以實現(xiàn)對大量空間目標(biāo)的監(jiān)測和編目庫維護(hù)。天基空間監(jiān)測技術(shù)和系統(tǒng)可以有效緩解上述兩項限制:天基光學(xué)監(jiān)測可以每天24小時進(jìn)行;設(shè)計合理的天基監(jiān)測星座可以實現(xiàn)全球覆蓋。因此,天基空間監(jiān)測也成為空間碎片探測的主要發(fā)展趨勢。天、地基結(jié)合可使我國擁有獨(dú)立自主、全球覆蓋和準(zhǔn)實時的空間預(yù)警能力,為確保國家空間戰(zhàn)略基礎(chǔ)設(shè)施的安全提供有力保障。利用天基光學(xué)監(jiān)測技術(shù)建立和維護(hù)空間目標(biāo)編目庫涉及天基系統(tǒng)設(shè)計、觀測值采集和處理、編目庫設(shè)計等一系列問題。本文只對其中個別問題進(jìn)行研究。本文首先分析了天基光學(xué)監(jiān)測的可見性條件,并設(shè)計了一個包含6個軌道12顆衛(wèi)星24個光學(xué)望遠(yuǎn)鏡的SBSS星座,通過仿真該星座在不同觀測時間段內(nèi)的探測能力(可觀測的空間目標(biāo)數(shù)量),驗證了天基光學(xué)觀測手段的有效性。光學(xué)觀測手段得到的觀測值只包含角度信息,僅使用角度觀測值的空間目標(biāo)初軌確定是將新目標(biāo)編目入庫的關(guān)鍵之一。對于天基光學(xué)監(jiān)測而言,使用低軌天基光學(xué)望遠(yuǎn)鏡掃描式觀測低軌空間碎片,由于兩者的相對運(yùn)動較快,只能獲得很短時間內(nèi)的角度觀測值(這里稱之為甚短觀測弧段),使用傳統(tǒng)的Gauss方法和Gooding方法很難確定空間目標(biāo)的初始軌道。針對天基甚短弧段初軌問題,本文提出了一種基于距離搜索的新方法。在給定的一組角度觀測值中,通過搜索其中2個時刻的距離信息,將純角度的初始軌道確定問題轉(zhuǎn)換為基于2個位置矢量的初始軌道確定問題;再利用其他時刻的角度觀測值進(jìn)行檢核和約束,篩選出一個最優(yōu)的初始軌道結(jié)果。利用本文提出的方法對仿真的低軌空間碎片甚短弧段角度觀測值進(jìn)行初始軌道確定實驗,將定軌結(jié)果與Gauss方法和Gooding方法所獲得的結(jié)果進(jìn)行比較,表明本文提出的方法在解的成功率和精度兩方面都顯著優(yōu)于其他兩種方法。對定軌誤差進(jìn)行分析,發(fā)現(xiàn)當(dāng)觀測值變化率較小時,初軌確定的精度明顯下降,表明利用本文方法的初軌確定誤差與角度觀測值變化率之間有很大的關(guān)系。最后,將本文提出的方法擴(kuò)展應(yīng)用到天基高軌目標(biāo)、地基空間目標(biāo)角度觀測值的初始軌道確定,實驗表明,該方法都能得到較好的結(jié)果。仿真結(jié)果對今后開展空間目標(biāo)天、地一體化監(jiān)測系統(tǒng)的設(shè)計,監(jiān)測作業(yè)規(guī)劃、編目庫建設(shè)等有一定的指導(dǎo)意義。
[Abstract]:Space objects are widely distributed in different orbits, most of them are space debris, which seriously threaten the safe operation of orbiting spacecraft. The main technical means of space monitoring include optics, radar and laser ranging. Ground-based optical monitoring means are limited by geographical location and duration of observation, It is difficult to realize the monitoring of a large number of space objects and the maintenance of cataloguing database by relying on ground-based monitoring alone. Space-based space monitoring technology and system can effectively alleviate the above two limitations: Space-based optical monitoring can be carried out 24 hours a day; A reasonably designed constellation of space-based monitoring can achieve global coverage. Therefore, space-based space monitoring has also become a major development trend in space debris detection. Global coverage and quasi-real-time space early warning capabilities to ensure the security of national space strategic infrastructure. The establishment and maintenance of a space-based object inventory using space-based optical monitoring technology involves the design of space-based systems, A series of problems, such as collection and processing of observations, design of cataloguing database, etc., are studied in this paper. Firstly, the visibility conditions of space-based optical monitoring are analyzed. A SBSS constellation consisting of 12 satellites in 6 orbits and 24 optical telescopes is designed. The effectiveness of space-based optical observation is verified by simulating the constellation's detection capability (number of observable space objects) in different observation periods. The observed values obtained from optical observation only contain angle information. The determination of the initial orbit of space objects using only angular observations is one of the keys to cataloguing new objects in the database. For space-based optical monitoring, low-orbit space-based optical telescopes are used to scan the low-orbit space debris. Because the relative motion of the two is faster, Angle observations can only be obtained in a very short period of time (here called very short observation arc). It is difficult to determine the initial orbit of space target by using the traditional Gauss method and Gooding method. In this paper, a new method based on distance search is proposed. The problem of pure angle initial orbit determination is transformed into an initial orbit determination problem based on two position vectors, and then the angle observations at other times are used for checking and constraining. An optimal initial orbit result is obtained, and the method proposed in this paper is used to determine the initial orbit of the simulated very short arc segment of Leo space debris. The results of orbit determination are compared with those obtained by the Gauss method and the Gooding method. The results show that the proposed method is superior to the other two methods in terms of the success rate and accuracy of the solution. The orbit determination error is analyzed. It is found that the accuracy of initial orbit determination decreases obviously when the rate of change of observation value is small, which indicates that there is a great relationship between the error of initial orbit determination and the rate of change of angle observation value by using the method in this paper. Finally, The method proposed in this paper is extended to determine the initial orbit of the space-based high orbit target and the angle observation value of the ground space target. The experimental results show that the method can obtain good results. The simulation results are useful for the future space target days. The design of integrated monitoring system, monitoring operation planning and cataloguing database construction have certain guiding significance.
【學(xué)位授予單位】：武漢大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2017
【分類號】：V412.41;V528

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