【摘要】：為了在地面高精度評估激光通信終端對衛(wèi)星平臺擾動以及軌道姿態(tài)變化的適應能力,研究了衛(wèi)星擾動模擬技術和衛(wèi)星隨動仿真模擬技術,據(jù)此提出了激光通信系統(tǒng)地面驗證方案。首先開展了激光通信鏈路隨動探測誤差對系統(tǒng)隨動性能影響分析、衛(wèi)星擾振源特性分析及建模工作。其次,分析了衛(wèi)星擾動模擬和隨動模擬的關鍵技術及解決措施。最后,結合目前衛(wèi)星激光通信及衛(wèi)星平臺技術水平,利用典型數(shù)據(jù)開展了擾動和隨動仿真,完成了激光通信系統(tǒng)測試。實驗結果證明:基于雙反饋環(huán)路的高精度光束瞄準控制能夠大幅提高衛(wèi)星擾動模擬器光束瞄準的控制精度,光束控制精度優(yōu)于0.1″;采用高低頻聯(lián)合衛(wèi)星擾動模擬設計方法,實現(xiàn)了控制帶寬優(yōu)于1kHz的高精度光束控制;高精度隨動系統(tǒng)在全衛(wèi)星運行區(qū)域內(nèi)對衛(wèi)星光通信終端隨動性能的檢測精度可達0.1″。
[Abstract]:In order to evaluate the adaptability of laser communication terminal to satellite platform disturbance and orbit attitude change, satellite disturbance simulation technology and satellite tracking simulation technology are studied in order to evaluate the adaptability of laser communication terminal to satellite platform disturbance and orbit attitude change. Based on this, a ground verification scheme for laser communication system is proposed. Firstly, the influence of the detection error of laser communication link on the servo performance of the system is analyzed, and the characteristics of the satellite disturbance source are analyzed and modeled. Secondly, the key techniques and solutions of satellite disturbance simulation and follow-up simulation are analyzed. Finally, combined with the current technology level of satellite laser communication and satellite platform, the disturbance and follow simulation are carried out using typical data, and the laser communication system test is completed. The experimental results show that the high precision beam aiming control based on double feedback loop can greatly improve the control accuracy of the satellite disturbance simulator beam aiming, and the beam control accuracy is better than 0.1 "; The high precision beam control with better control bandwidth than 1kHz is realized by using the simulation design method of high and low frequency satellite disturbance, and the precision of detecting the tracking performance of satellite optical communication terminal in the whole satellite operation area is up to 0.1 ".
【作者單位】： 北京理工大學光電學院光電成像技術與系統(tǒng)教育部重點實驗室;中國空間技術研究院北京空間飛行器總體設計部;
【基金】：高新二期衛(wèi)星研發(fā)平臺資助項目
【分類號】：TN927.2

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