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Guidance, navigation, and control of Hayabusa2 touchdown operations

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Astrodynamics 2020年第4期4卷 393-409页

作者： Fuyuto Terui Naoko Ogawa Go Ono Seiji Yasuda Tetsuya Masuda Kota Matsushima takanao saiki Yuichi Tsuda Institute of Space and A stronautical Science Japan A erospace Exploration AgencyKanagawa 252-5210Japan The 3nd Space Technology Department Space System DirisionNEC CorporationTokyo 183-8501Japan

Hayabusa2 is a Japanese sample return mission from the asteroid *** Hayabusa2 spacecraft was launched on 3 December 2014 and arrived at Ryugu on 27 June *** stayed there until December 2019 for in situ observation and soil sample collection,and will return to the Earth in November or December *** the stay,the spacecraft performed the first touchdown operation on 22 February 2019 and the second touchdown on 11 July 2019,which were both completed *** the surface of Ryugu is rough and covered with boulders,it was not easy to find target areas for *** were several technical challenges to overcome,including demanding guidance,navigation,and control accuracy,to realize the touchdown *** this paper,strategies and technical details of the guidance,navigation,and control systems are *** flight results prove that the performance of the systems was satisfactory and largely contributed to the success of the operation.

关键词： small body exploration touchdown astrodynamics guidance navigation control

Design and flight results of GNC systems in Hayabusa2 descent operations

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Astrodynamics 2020年第2期4卷 105-117页

作者： Go Ono Fuyuto Terui Naoko Ogawa Yuya Mimasu Kent Yoshikawa Yuto Takei takanao saiki Yuichi Tsuda Japan Aerospace Exploration Agency Sagamihara252-5210Japan

Hayabusa2 is a Japanese sample return mission from the near-Earth asteroid *** Hayabusa2 spacecraft was launched on December 3,2014,and reached the asteroid on June 27,*** remained there until November 13,2019 for in situ observation and soil sample collection and will return to the Earth in November or December *** its stay at the asteroid,Hayabusa2 performed descent operations 16 *** paper presents an overview of a guidance,navigation,and control method used in such descent *** method consists of on-board and on-ground guidance systems to control the spacecraft and an image-based navigation technique that uses a shape model and ground control points of the *** results in the first touchdown operation are shown as an example,which demonstrate that the method showed a good performance overall and contributed to the success of the mission.

关键词： small body exploration astrodynamics guidance navigation control

Modeling and analysis of Hayabusa2 touchdown

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Astrodynamics 2020年第2期4卷 119-135页

作者： Kent Yoshikawa Hirotaka Sawada Shota Kikuchi Naoko Ogawa Yuya Mimasu Go Ono Yuto Takei Fuyuto Terui takanao saiki Seiji Yasuda Kota Matsushima Tetsuya Masuda Yuichi Tsuda Japan Aerospace Exploration Agency Sagamihara252-5210Japan NEC Corporation Fuchu183-8501Japan

The Hayabusa2 asteroid explorer mission focuses principally on the touchdown and sampling on near-Earth asteroid 162173 ***2 successfully landed on its surface and ejected a projectile for sample collection on February 22,***2 later landed near a crater formed by an impactor and executed the sampling sequence again on July 11,*** a successful mission,a thorough understanding and evaluation of spacecraft dynamics during touchdown were *** most challenging aspect of this study was the modeling of such spacecraft phenomena as the dynamics of landing on a surface with unknown *** particular,a Monte Carlo analysis was used to determine the parameters of the operational design for the final descent and touchdown *** paper discusses the dynamical modeling of the simulation during the touchdown of Hayabusa2.

关键词： contact dynamics resistive force theory(RFT) astrodynamics Hayabusa2 planetary exploration

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)

Image-based autonomous navigation of Hayabusa2 using artificial landmarks: The design and brief in-flight results of the first landing on asteroid Ryugu

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Astrodynamics 2020年第2期4卷 89-103页

作者： Naoko Ogawa Fuyuto Terui Yuya Mimasu Kent Yoshikawa Go Ono Seiji Yasuda Kota Matsushima Tetsuya Masuda Hiroki Hihara Junpei Sano Takashi Matsuhisa Satoshi Danno Manabu Yamada Yasuhiro Yokota Yuto Takei takanao saiki Yuichi Tsuda Japan Aerospace Exploration Agency Sagamihara252-5210Japan NEC Corporation Fuchu183-8501Japan NEC Space Technologies Ltd.Fuchu183-8551Japan Systems Engineering Consultants Co. Ltd.Tokyo158-0097Japan Planetary Exploration Research Center Chiba Institute of TechnologyNarashino275-0016Japan

Hayabusa2 is an asteroid sample return mission carried out by the Japan Aerospace Exploration *** spacecraft was launched in 2014 and arrived at the target asteroid Ryugu on June 27,*** the 1.5-year proximity phase,several critical operations(including two landing/sampling operations)were successfully *** were based on autonomous image-based descent and landing *** paper describes an imagebased autonomous navigation scheme of the Hayabusa2 mission using artificial landmarks named target markers(TMs).Its basic algorithm,and the in-flight results of the first touchdown and its rehearsal,are shown.

关键词： Hayabusa2 Ryugu image-based navigation target marker tracking

Solar power sail mission of OKEANOS

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Astrodynamics 2020年第3期4卷 233-248页

作者： Osamu Mori Jun Matsumoto Toshihiro Chujo Masanori Matsushita Hideki Kato takanao saiki Yuichi Tsuda Jun'ichiro Kawaguchi Fuyuto Terui Yuya Mimasu Go Ono Naoko Ogawa Yuki Takao Yuki Kubo Kaoru Ohashi Ahmed Kiyoshi Sugihara Tatsuaki Okada Takahiro Iwata Hajime Yano Japan Aerospace Exploration Agency Sagarmihara 252-5210Japan Tokyo Institute of Technology Tokyo 152-8550Japan The University of Tokyo Tokyo 113-8654Japan Patchedconics LLCSagarmihara 252-5210Japan

The solar power sail is an original Japanese concept in which electric power is generated by thin-film solar cells attached on the solar sail *** Aerospace Exploration Agency(JAXA)successfully demonstrated the world’s first solar power sail technology through IKAROS(Interplanetary Kite-craft Accelerated by Radiation of the Sun)mission in *** demonstrated photon propulsion and power generation using thin-film solar cells during its interplanetary *** up,solar power sails can generate enough power to drive high specific impulse ion thrusters in the outer planetary *** this concept,we propose a landing or sample return mission to directly explore a Jupiter Trojan asteroid using solar power sail-craft OKEANOS(Oversize Kite-craft for Exploration and AstroNautics in the Outer Solar System).After rendezvousing with a Trojan asteroid,a lander separates from OKEANOS to collect samples,and perform in-situ analyses in three proposed mission sequences,including sending samples back to *** paper proposes a system design for OKEANOS and includes analyses of the latest mission.

关键词： solar power sail Trojan asteroid landing in-situ analysis outer solar system OKEANOS

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

Motion reconstruction of the small carry-on impactor aboard Hayabusa2

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Astrodynamics 2020年第4期4卷 289-308页

作者： takanao saiki Yuya Mimasu Yuto Takei Manabu Yamada Hirotaka Sawada K azunori Ogawa Naoko Ogawa Hiroshi Takeuchi Akira Miura Yuri Shimaki Koji Wada Rie Honda Yasuhiro Yokota Kei Shirai Naruhisa Sano Hirohito Ohtsuka Go Ono Kent Yoshikawa Shota Kikuchi Chikako Hirose Yukio Yamamoto Takahiro Iwata Masahiko Arakawa Seiji Sugita Satoshi Tanaka Fuyuto Terui Makoto Yoshikawa Satoru Nakazawa Sei-ichiro Watanabe Yuichi Tsuda Japan Aerospace Exploration Agency Sagamihara 252-5210Japan Chiba Institute of Technology Narashino 275-0016Japan Kobe University K obe 657-8501Japan The Graduate University for Aduanced Studies Sagamihara 252-5210Japan Kochi University Kochi 780-8520Japan IHI Aerospace Co. LtdTomioka 370-2398Japan The University of Tokyo Tokyo 113-0033Japan Nagoya University Nagoya 464-8601Japan

Subsurface exploration is one of the most ambitious scientific objectives of the Hayabusa2 mission.A small device called small carry-on impactor(SCI)was developed to create an artificial crater on the surface of asteroid *** enables us to sample subsurface materials,which will provide a window to the *** physical properties of the resulting crater are also useful for understanding the internal structure of *** understanding of the crater and ejecta properties,including the depth of excavation of subsurface materials,requires accurate information on impact *** particular,the impact angle is a critical factor because it greatly influences the size and shape of the *** April 5,2019,the Hayabusa2 spacecraft deployed the SCI at 500 m of altitude above the asteroid *** SCI gradually reduced its altitude,and it shot a 2 kg copper projectile into the asteroid 40 min after *** the position of the released SCI is essential for determining the impact *** study describes the motion reconstruction of the SCI based on the actual operation *** results indicate that the SCI was released with high accuracy.

关键词： small body exploration Hayabusa2 kinetic impact artificial crater motion reconstruction