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

Astrodynamics 2020年第2期4卷 137-147页

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 Institute of Space and Astronautical Science Japan Aerospace Exploration AgencySagamihara252-5210Japan Research and Development Directorate Japan Aerospace Exploration AgencySagamihara252-5210Japan Research and Development Directorate Japan Aerospace Exploration AgencyTsukuba305-8505Japan Seoul National University Seoul08826Republic of Korea Okayama Observatory Kyoto UniversityAsakuchi719-0232Japan Japan Spaceguard Association Bisei714-1411Japan 不详

This paper describes the guidance and navigation technique used by Hayabusa2 for the asteroid rendezvous operation to reach *** operation results,including the achieved guidance and navigation performance,are also *** assessment and navigation teams worked closely to provide reliable navigation solutions with a short solution delivery *** 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

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Classification of solar sail attitude dynamics with and without angular momentum

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Astrodynamics 2019年第3期3卷 207-216页

作者： Yuichi Tsuda Go Ono Yuya Mimasu Institute of Space and Astronautical Science Japan Aerospace Exploration AgencySagamihara252-5210Japan Japan Aerospace exploration Agency Sagamihara252-5210Japan

This paper describes attitude dynamics properties of spinning,momentum-biased and zero-momentum solar sail *** model called“Generalized Sail Dynamics Model”(GSDM)is introduced,which can deal with general and practical sail configurations,such as arbitrary optical property distribution,shape and surface *** stability criteria and other key dynamical characteristics are derived and compared by compact analytical equations induced from the *** newly derived zero-momentum sail dynamics is compared with that of spinning and momentum-biased *** is shown that the spinning and momentum sails have an advantage in terms of dynamical stability whereas zero-momentum sails are only statically *** this special property,angular momentum-stabilized sails can realize a sun-pointing stable attitude with almost zero-fuel,which are discussed with actual space flight experience of the JAXA’s two interplanetary missions,IKAROS and Hayabusa2.

关键词： solar sail attitude dynamics stability solar system exploration

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