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

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Astrodynamics 2020年第4期4卷 377-392页

作者： Hiroshi Takeuchi Kent Yoshikawa Yuto Takei yusuke oki Shota Kikuchi Hitoshi Ikeda Stefania Soldini Naoko Ogawa Yuya Mimasu Go Ono Fuyuto Terui Naoya Sakatani Manabu Yamada Toru Kouyama Shingo Kameda Takanao Saiki Yuichi Tsuda Institute of Space and A stronautical Science Japan A erospace Exploration AgencySagamihara 252-5210Japan The Graduate University for Aduanced Studies Hayama 240-0193Japan Research and Development Directorate Japan Aerospace Exploration AgencySagamihara 252-5210Japan University of Liverpool Liverpool L693BXUK Chiba Institute of Technology Narashino 275-0016Japan National Institute of Aduanced Industrial Science and Technology Koto-ku 135-0064Japan Rikkyo University Toshima-ku 171-8501Japan

The deep-space multi-object orbit determination system(DMOODS)and its application in the asteroid proximity operation of the Hayabusa2 mission are *** 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 *** weighted least-squares batch filter is used for the orbit estimator of *** 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 *** 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 *** 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 *** example is orbit determination during the solar conjunction phase,in which the navigation accuracy is degraded by the effect of the solar *** 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 *** 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 *** type of simultaneous orbit determination of multi-artificial objects in deep-space has never been accomplished before.

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

Hayabusa2’s superior solar conjunction mission operations: Planning and post-operation results

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Astrodynamics 2020年第4期4卷 265-288页

作者： Stefania Soldini Hiroshi Takeuchi Sho Taniguchi Shota Kikuchi Yuto Takei Go Ono Masaya Nakano Takafumi Ohnishi Takanao Saiki Yuichi Tsuda Fuyuto Terui Naoko OgawaYuya MimasuTadateru Takahashi Atsushi Fujii Satoru NakazawaKent Yoshikawa yusuke oki Chikako Hirose Hirotaka Sawada Tomohiro Yamaguchi Makoto Yoshikawa Department of Mechanical Materials and Aerospace EngineeringUniversity of LiverpoolLiverpool L693BXUK Institute of Space and Astronautical Science Japan Aerospace Exploration AgencySagamihara 252-5210Japan Fujitsu Limited Tokyo 105-7123Japan Mitsubishi Electric Corporation Tokyo 100-8310Japan

In late 2018,the asteroid Ryugu was in the Sun's shadow during the superior solar conjunction *** the Sun-Earth-Ryugu angle decreased to below 3°,the Hayabusa2 spacecraft experienced 21 days of planned blackout in the Earth-probe communication *** was the first time a spacecraft had experienced solar conjunction while hovering around a minor *** the safety of the spacecraft,a low energy transfer trajectory named Ayu was designed in the Hill reference frame to increase its altitude from 20 to 110 *** trajectory was planned with the newly developed optNEAR tool and validated with real time *** article shows the results of the conjunction operation,from planning to fight data.

关键词： superior solar conjunction Hayabusa2 Ryugu hovering satellite mission operations

Orbit insertion strategy of Hayabusa2’s rover with large release uncertainty around the asteroid Ryugu

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Astrodynamics 2020年第4期4卷 309-329页

作者： yusuke oki Kent Yoshikawa Hiroshi Takeuchi Shota Kikuchi Hitosi Ikeda Daniel JScheeres Jay WMcMahon Junichiro Kawaguchi Yuto Takei Yuya Mimasu Naoko Ogawa Go Ono Fuyuto Terui Manabu Yamada Toru Kouyama Shingo K ameda Kazuya Yoshida Kenji Nagaoka Tetsuo Yoshimitsu Takanao Saiki Yuichi Tsuda Japan A erospace Exploration Agency T'sukuba 305-8505Japan Japan Aerospace Exploration Agency Sagamihara 252-5210Japan University of Colorado BoulderCO 80309USA Planetary Exploration Research Center Chiba Institute of TechnologyNarashino 275-0016Japan National Institute of Aduanced Industrial Science and Technology Koto-ku 135-0064Japan Rikkyo University Toshima-ku 171-8501Japan Department of A erospace Engineering Tohoku UniversitySendai 980-8579Japan Kyushu Institute of Technology Kitakyusyu 804-8550Japan

This paper describes the orbit design of the deployable payload Rover 2 of MINERVA-II,installed on the Hayabusa2 *** Rover 2 did not have surface exploration capabilities,the operation team decided to experiment with a new strategy for its deployment to the *** rover was ejected at a high altitude and made a semi-hard landing on the surface of the asteroid Ryugu after several *** on the orbital analysis around Ryugu,the expected collision speed was tolerable for the rover to function *** the rover could not control its position,its motion was entirely governed by the initial ***,the largest challenge was to insert the rover into a stable orbit(despite its large release uncertainty),and avoid its escape from Ryugu due to an environment strongly perturbed by solar radiation pressure and gravitational *** study investigates the solution space of the orbit around Ryugu and evaluates the orbit’s robustness by utilizing Monte Carlo simulations to determine the orbit insertion *** analyzing the flight data of the rover operation,we verified that the rover orbited Ryugu for more than one period and established the possibility of a novel method for estimating the gravity of an asteroid.

关键词： solar radiation pressure augmented elliptic Hill three-body problem gravitational irregularity

Correction to: Orbit insertion strategy of Hayabusa2’s rover with large release uncertainty around the asteroid Ryugu

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Astrodynamics 2021年第2期5卷 183-183页

作者： yusuke oki Kent Yoshikawa Hiroshi Takeuchi Shota Kikuchi Hitosi Ikeda Daniel J.Scheeres Jay W.McMahon Junichiro Kawaguchi Yuto Takei Yuya Mimasu Naoko Ogawa Go Ono Fuyuto Terui Manabu Yamada Toru Kouyama Shingo Kameda Kazuya Yoshida Kenji Nagaoka Tetsuo Yoshimitsu Takanao Saiki Yuichi Tsuda Japan Aerospace Exploration Agency Tsukuba305-8505Japan Japan Aerospace Exploration Agency Sagamihara252-5210Japan University of Colorado BoulderCO80309USA Planetary Exploration Research Center Chiba Institute of TechnologyNarashino275-0016Japan National Institute of Advanced Industrial Science and Technology Koto-ku135-0064Japan Rikkyo University Toshima-ku171-8501Japan Department of Aerospace Engineering Tohoku UniversitySendai980-8579Japan Kyushu Institute of Technology Kitakyusyu804-8550Japan

Correction to:oki,Y.,Yoshikawa,K.,Takeuchi,*** *** insertion strategy of Hayabusa2's rover with large release uncertainty around the asteroid *** 2020,4(4):309-329 https://***/10.1007/s42064-020-0080-y The article“Orbit insertion strategy of Hayabusa2’s rover with large release uncertainty around the asteroid Ryugu”written by yusuke oki,Kent Yoshikawa,Hiroshi Takeuchi et al.,was originally published electronically on the publisher’s internet portal(currently SpringerLink)on 05 November 2020 without open *** publication in Volume 4,Issue 4,page 309–329,the author(s)decided to opt for Open Choice and to make the article an open access publication.

关键词： asteroid insertion release