用星敏感器和地平儀測(cè)量星光與地平之間的“星光仰角”為觀測(cè)量, 利用推廣卡爾曼濾波方法實(shí)時(shí)估計(jì)航天器的最佳位置, 使航天器在失去地面遙控的情況下, 能夠自主準(zhǔn)確地確定運(yùn)行軌道。由于航天器自主定位系統(tǒng)在工作期間會(huì)受到硬、軟件等諸多因素的影響, 因而使其定位精度達(dá)不到預(yù)計(jì)要求。在此我們通過(guò)大量仿真計(jì)算, 指出一些對(duì)自主定位系統(tǒng)精度影響較大的因素, 并對(duì)它們進(jìn)行了比較分析。
關(guān)鍵詞: 自主式導(dǎo)航; 地平儀; 光學(xué)傳感器; 方法; 精度
Abstract: The best po sit ion of spacecraft is real2t imely determ ined by using the extended kalman filtering in o r2 der that spacecraft can run in scheduled o rbit autonomously and accurately w ithout the remo te cont ro l of ground command. The elevat ion angular of star is observed by star senso r and ho rizontal inst rument. During thewo rk peri2 od of spacecraft, the system can be influenced by many facto rs related to hardw ere and softw ere, the p recision of o rbit determ inat ion can be sho rt of request. By emulat ing calculat ion, some facto rs that influence largely on the p re2 cision of determ ining po sit ion are po inted out, compared and analyzed earnest ly.
Key words: A utonomous navigat ion; Ho rizon; L igh t sensit ive senso r; M ethod; P recision