Rendezvous to asteroid with highly uncertain ephemeris: Hayabusa2’s Ryugu-approach operation result  

作　　者：Yuichi Tsuda Hiroshi Takeuchi Naoko Ogawa Go Ono Shota Kikuchi Yusuke Oki Masateru Ishiguro Daisuke Kuroda Seitaro Urakawa Shin-ichiro Okumura Hayabusa2 Project Team 

机构地区：[1]Institute of Space and Astronautical Science,Japan Aerospace Exploration Agency,Sagamihara,252-5210,Japan [2]Research and Development Directorate,Japan Aerospace Exploration Agency,Sagamihara,252-5210,Japan [3]Research and Development Directorate,Japan Aerospace Exploration Agency,Tsukuba,305-8505,Japan [4]Seoul National University,Seoul,08826,Republic of Korea [5]Okayama Observatory,Kyoto University,Asakuchi,719-0232,Japan [6]Japan Spaceguard Association,Bisei,714-1411,Japan [7]不详

出　　处：《Astrodynamics》2020年第2期137-147,共11页航天动力学（英文）

基　　金：JSPS KAKENHI Grant No.18H01628 also supported this work.

摘　　要：This paper describes the guidance and navigation technique used by Hayabusa2 for the asteroid rendezvous operation to reach Ryugu.The operation results,including the achieved guidance and navigation performance,are also summarized.Multiple assessment and navigation teams worked closely to provide reliable navigation solutions with a short solution delivery cycle.Although the uncertainty of the Ryugu’s ephemeris was considerable before Hayabusa2’s arrival,a combination of radiometric-optical hybrid navigation and a stochastic-constrained optimum guidance method was able to achieve an accuracy of less than 100 m and 1 cm/s,and the arrival was precisely timed.

关 键 词：solar system exploration sample return optical navigation trajectory optimization spacecraft guidance 

分 类 号：P18[天文地球—天文学]