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Astrodynamics 2020, 4(4): 377-392 https://doi.org/10.1007/s42064-020-0084-7
Research Article | Issue | Published: 17 October 2020

The deep-space multi-object orbit determination system and its application to Hayabusa2’s asteroid proximity operations

Show Author's Information Hiroshi Takeuchi1,2( ),  Kent Yoshikawa3,  Yuto Takei3,  Yusuke Oki3,  Shota Kikuchi1,  Hitoshi Ikeda3,  Stefania Soldini1,4,  Naoko Ogawa1,  Yuya Mimasu1,  Go Ono3,  Fuyuto Terui1,  Naoya Sakatani7,  Manabu Yamada5,  Toru Kouyama6,  Shingo Kameda7,  Takanao Saiki1,  Yuichi Tsuda1,2
Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency, Sagamihara 252-5210, Japan
The Graduate University for Advanced Studies, Hayama 240-0193, Japan
Research and Development Directorate, Japan Aerospace Exploration Agency, Sagamihara 252-5210, Japan
University of Liverpool, Liverpool L69 3BX, UK
Chiba Institute of Technology, Narashino 275-0016, Japan
National Institute of Advanced Industrial Science and Technology, Koto-ku 135-0064, Japan
Rikkyo University, Toshima-ku 171-8501, Japan
Keywords:
superior solar conjunction, orbit determination, optical navigation, gravity measurements, delta differential one-way ranging (delta-DOR)
Cite this article:
Takeuchi H, Yoshikawa K, Takei Y, et al. The deep-space multi-object orbit determination system and its application to Hayabusa2’s asteroid proximity operations. Astrodynamics, 2020, 4(4): 377-392. https://doi.org/10.1007/s42064-020-0084-7
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Abstract Full text About this article

The deep-space multi-object orbit determination system (DMOODS) and its application in the asteroid proximity operation of the Hayabusa2 mission are described. DMOODS was developed by the Japan Aerospace Exploration Agency (JAXA) for the primary purpose of determining the trajectory of deep-space spacecraft for JAXA’s planetary missions. The weighted least-squares batch filter is used for the orbit estimator of DMOODS. The orbit estimator supports more than 10 data types, some of which are used for relative trajectory measurements between multiple space objects including natural satellites and small bodies. This system consists of a set of computer programs running on Linux-based consumer PCs on the ground, which are used for orbit determination and the generation of radiometric tracking data, such as delta differential one-way ranging and doppler tracking data. During the asteroid proximity phase of Hayabusa2, this system played an essential role in operations that had very strict navigation requirements or operations in which few optical data were obtained owing to special constraints on the spacecraft attitude or distance from the asteroid. One example is orbit determination during the solar conjunction phase, in which the navigation accuracy is degraded by the effect of the solar corona. The large range bias caused by the solar corona was accurately estimated with DMOODS by combining light detection and ranging (LIDAR) and ranging measurements in the superior solar conjunction phase of Hayabusa2. For the orbiting operations of target markers and the MINERVA-II2 rover, the simultaneous estimation of six trajectories of four artificial objects and a natural object was made by DMOODS. This type of simultaneous orbit determination of multi-artificial objects in deep-space has never been accomplished before.


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About this article

The deep-space multi-object orbit determination system and its application to Hayabusa2’s asteroid proximity operations

Show Author's information Hiroshi Takeuchi1,2( ), Kent Yoshikawa3, Yuto Takei3, Yusuke Oki3, Shota Kikuchi1, Hitoshi Ikeda3, Stefania Soldini1,4, Naoko Ogawa1, Yuya Mimasu1, Go Ono3, Fuyuto Terui1, Naoya Sakatani7, Manabu Yamada5, Toru Kouyama6, Shingo Kameda7, Takanao Saiki1, Yuichi Tsuda1,2
Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency, Sagamihara 252-5210, Japan
The Graduate University for Advanced Studies, Hayama 240-0193, Japan
Research and Development Directorate, Japan Aerospace Exploration Agency, Sagamihara 252-5210, Japan
University of Liverpool, Liverpool L69 3BX, UK
Chiba Institute of Technology, Narashino 275-0016, Japan
National Institute of Advanced Industrial Science and Technology, Koto-ku 135-0064, Japan
Rikkyo University, Toshima-ku 171-8501, Japan

Abstract

The deep-space multi-object orbit determination system (DMOODS) and its application in the asteroid proximity operation of the Hayabusa2 mission are described. DMOODS was developed by the Japan Aerospace Exploration Agency (JAXA) for the primary purpose of determining the trajectory of deep-space spacecraft for JAXA’s planetary missions. The weighted least-squares batch filter is used for the orbit estimator of DMOODS. The orbit estimator supports more than 10 data types, some of which are used for relative trajectory measurements between multiple space objects including natural satellites and small bodies. This system consists of a set of computer programs running on Linux-based consumer PCs on the ground, which are used for orbit determination and the generation of radiometric tracking data, such as delta differential one-way ranging and doppler tracking data. During the asteroid proximity phase of Hayabusa2, this system played an essential role in operations that had very strict navigation requirements or operations in which few optical data were obtained owing to special constraints on the spacecraft attitude or distance from the asteroid. One example is orbit determination during the solar conjunction phase, in which the navigation accuracy is degraded by the effect of the solar corona. The large range bias caused by the solar corona was accurately estimated with DMOODS by combining light detection and ranging (LIDAR) and ranging measurements in the superior solar conjunction phase of Hayabusa2. For the orbiting operations of target markers and the MINERVA-II2 rover, the simultaneous estimation of six trajectories of four artificial objects and a natural object was made by DMOODS. This type of simultaneous orbit determination of multi-artificial objects in deep-space has never been accomplished before.

Keywords: superior solar conjunction, orbit determination, optical navigation, gravity measurements, delta differential one-way ranging (delta-DOR)

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Publication history
Copyright
Acknowledgements

Publication history

Received: 03 February 2020
Accepted: 23 April 2020
Published: 17 October 2020
Issue date: December 2020

Copyright

© Tsinghua University Press 2020

Acknowledgements

This research was carried out at the Institute of Space and Astronautical Science (ISAS) of JAXA. The authors are grateful to the whole Hayabusa2 operation team for supplying the operation data used in this analysis. The authors would like to acknowledge the huge contribution made by the members of the Deep-space Orbit Determination Group in ISAS: S. Taniguchi, N. Fujii, B. Ichikawa, T. Yagami, K. Takezawa, and M. Yoshikawa. Special thanks to N. Fujii who passed away too soon on November 4, 2019, before the project was completed. Most of the tracking data from JAXA’s deep-space stations were calibrated and distributed to the community by him. The authors would like to acknowledge the contributions of the Hayabusa2 navigation team at the Jet Propulsion Laboratory, California Institute of Technology (JPL), J. Bellerose, S. Bhaskaran, Z. B. Tarzi, and J. S. Border for their excellent support to deliver high-quality navigation data from the Deep Space Network. We also acknowledge the contributions of the rest of the Hayabusa2 team at JPL who provided various support in terms of the scheduling and technical assessment, including A. W. Kruger, S. Zadourian, M. A. Ritterbush, T. J. Hofmann, and S. W. Asmar. We also thank the tracking team at the European Space Operations Centre (ESOC) of the ESA for the delivery of Hayabusa2 tracking data from the European Space Tracking (ESTRACK) network. Finally, we are very grateful to two anonymous reviewers for their valuable comments that led to the significant improvement of our paper.

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