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Astrodynamics 2020, 4(2): 137-147 https://doi.org/10.1007/s42064-020-0074-9
Research Article | Issue | Published: 18 June 2020

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

Show Author's Information Yuichi Tsuda1( ),  Hiroshi Takeuchi1,  Naoko Ogawa1,  Go Ono2,  Shota Kikuchi1,  Yusuke Oki3,  Masateru Ishiguro4,  Daisuke Kuroda5,  Seitaro Urakawa6,  Shin-ichiro Okumura6
Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency, Sagamihara 252-5210, Japan
Research and Development Directorate, Japan Aerospace Exploration Agency, Sagamihara 252-5210, Japan
Research and Development Directorate, Japan Aerospace Exploration Agency, Tsukuba 305-8505, Japan
Seoul National University, Seoul 08826, Republic of Korea
Okayama Observatory, Kyoto University, Asakuchi 719-0232, Japan
Japan Spaceguard Association, Bisei 714-1411, Japan
Keywords:
optical navigation, trajectory optimization, solar system exploration, sample return, spacecraft guidance
Cite this article:
Tsuda Y, Takeuchi H, Ogawa N, et al. Rendezvous to asteroid with highly uncertain ephemeris: Hayabusa2’s Ryugu-approach operation result. Astrodynamics, 2020, 4(2): 137-147. https://doi.org/10.1007/s42064-020-0074-9
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Abstract Full text About this article

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.


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About this article

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

Show Author's information Yuichi Tsuda1( ), Hiroshi Takeuchi1, Naoko Ogawa1, Go Ono2, Shota Kikuchi1, Yusuke Oki3, Masateru Ishiguro4, Daisuke Kuroda5, Seitaro Urakawa6, Shin-ichiro Okumura6
Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency, Sagamihara 252-5210, Japan
Research and Development Directorate, Japan Aerospace Exploration Agency, Sagamihara 252-5210, Japan
Research and Development Directorate, Japan Aerospace Exploration Agency, Tsukuba 305-8505, Japan
Seoul National University, Seoul 08826, Republic of Korea
Okayama Observatory, Kyoto University, Asakuchi 719-0232, Japan
Japan Spaceguard Association, Bisei 714-1411, Japan

Abstract

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.

Keywords: optical navigation, trajectory optimization, solar system exploration, sample return, spacecraft guidance

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Publication history
Copyright
Acknowledgements

Publication history

Received: 24 January 2020
Accepted: 22 March 2020
Published: 18 June 2020
Issue date: June 2020

Copyright

© Tsinghua University Press 2020

Acknowledgements

The authors are grateful to the entire Hayabusa2 operation team for achieving this goal and supplying the operation product used in this analysis. JSPS KAKENHI Grant No. 18H01628 also supported this work.

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