|
|
|
题名
|
作者
|
年代
|
出处
|
被引量
|
| 1 | Evaluation of small bowel blood flow in healthy subjects receiving low-dose aspirin显示文摘AIM:To investigate the relationship between low-dose aspirin-induced small bowel mucosal damage and blood flow,and the effect of rebamipide. METHODS:Ten healthy volunteers were enrolled in this study.The subjects were divided into two groups:a placebo group given low-dose aspirin plus placebo and a rebamipide group given low-dose aspirin plus rebamipide for a period of 14 d.Capsule endoscopy and contrast-enhanced ultrasonography were performed before and after administration of drugs.Areas under the curves and peak value of time-intensity curve were calculated. RESULTS:Absolute differences in areas under the curves were-1102.5(95%CI:-1980.3 to-224.7,P=0.0194) in the placebo group and-152.7(95%CI:-1604.2 to 641.6,P=0.8172) in the rebamipide group. Peak values of time intensity curves were-148.0(95% CI:-269.4 to-26.2,P=0.0225) in the placebo group and 28.3(95%CI:-269.0 to 325.6,P=0.8343) in the rebamipide group.Capsule endoscopy showed mucosal breaks only in the placebo group. CONCLUSION:Short-term administration of low-dose aspirin is associated with small bowel injuries and blood flow. | Urara Nishida Mototsugu Kato Mutsumi Nishida Go Kamada Takeshi Yoshida Shouko Ono Yuichi Shimizu Masahiro Asaka | 2011 | World Journal of Gastroenterology2011，17，2： | 3 |
| 2 | Image-based autonomous navigation of Hayabusa2 using artificial landmarks: The design and brief in-flight results of the first landing on asteroid Ryugu显示文摘Hayabusa2 is an asteroid sample return mission carried out by the Japan Aerospace Exploration Agency.The spacecraft was launched in 2014 and arrived at the target asteroid Ryugu on June 27,2018.During the 1.5-year proximity phase,several critical operations(including two landing/sampling operations)were successfully performed.They were based on autonomous image-based descent and landing techniques.This 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. | 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 | 2020 | Astrodynamics2020，4，2： | 2 |
| 3 | Rendezvous to asteroid with highly uncertain ephemeris: Hayabusa2’s Ryugu-approach operation result显示文摘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. | Yuichi Tsuda Hiroshi Takeuchi Naoko Ogawa Go Ono Shota Kikuchi Yusuke Oki Masateru Ishiguro Daisuke Kuroda Seitaro Urakawa Shin-ichiro Okumura Hayabusa2 Project Team | 2020 | Astrodynamics2020，4，2： | 2 |
| 4 | The influence of donor age on liver regeneration and hepatic progenitor cell populations显示文摘 | Yoshihiro Ono Shigeyuki Kawachi Tetsu Hayashida Masatoshi Wakui Minoru Tanabe Osamu Itano Hideaki Obara Masahiro Shinoda Taizo Hibi Go Oshima Noriyuki Tani Kisyo Mihara Yuko Kitagawa | 2011 | Surgery2011，，2： | 2 |
| 5 | The deep-space multi-object orbit determination system and its application to Hayabusa2’s asteroid proximity operations显示文摘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. | 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 | 2020 | Astrodynamics2020，4，4： | 2 |
| 6 | Classification of solar sail attitude dynamics with and without angular momentum显示文摘This paper describes attitude dynamics properties of spinning,momentum-biased and zero-momentum solar sail spacecraft.The 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 wrinkles.Attitude stability criteria and other key dynamical characteristics are derived and compared by compact analytical equations induced from the GSDM.The newly derived zero-momentum sail dynamics is compared with that of spinning and momentum-biased sails.It is shown that the spinning and momentum sails have an advantage in terms of dynamical stability whereas zero-momentum sails are only statically stable.With 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. | Yuichi Tsuda Go Ono Yuya Mimasu | 2019 | Astrodynamics2019，3，3： | 1 |
| 7 | Orbit insertion strategy of Hayabusa2’s rover with large release uncertainty around the asteroid Ryugu显示文摘This paper describes the orbit design of the deployable payload Rover 2 of MINERVA-II,installed on the Hayabusa2 spacecraft.Because Rover 2 did not have surface exploration capabilities,the operation team decided to experiment with a new strategy for its deployment to the surface.The rover was ejected at a high altitude and made a semi-hard landing on the surface of the asteroid Ryugu after several orbits.Based on the orbital analysis around Ryugu,the expected collision speed was tolerable for the rover to function post-impact.Because the rover could not control its position,its motion was entirely governed by the initial conditions.Thus,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 irregularities.This 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 policy.Upon 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. | 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 | 2020 | Astrodynamics2020，4，4： | 1 |
| 8 | Modeling and analysis of Hayabusa2 touchdown显示文摘The Hayabusa2 asteroid explorer mission focuses principally on the touchdown and sampling on near-Earth asteroid 162173 Ryugu.Hayabusa2 successfully landed on its surface and ejected a projectile for sample collection on February 22,2019.Hayabusa2 later landed near a crater formed by an impactor and executed the sampling sequence again on July 11,2019.For a successful mission,a thorough understanding and evaluation of spacecraft dynamics during touchdown were crucial.The most challenging aspect of this study was the modeling of such spacecraft phenomena as the dynamics of landing on a surface with unknown properties.In particular,a Monte Carlo analysis was used to determine the parameters of the operational design for the final descent and touchdown sequence.This paper discusses the dynamical modeling of the simulation during the touchdown of Hayabusa2. | 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 | 2020 | Astrodynamics2020，4，2： | 1 |
| 9 | Guidance, navigation, and control of Hayabusa2 touchdown operations显示文摘Hayabusa2 is a Japanese sample return mission from the asteroid Ryugu.The Hayabusa2 spacecraft was launched on 3 December 2014 and arrived at Ryugu on 27 June 2018.It stayed there until December 2019 for in situ observation and soil sample collection,and will return to the Earth in November or December 2020.During 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 sucssfully.Because the surface of Ryugu is rough and covered with boulders,it was not easy to find target areas for touchdown.There were several technical challenges to overcome,including demanding guidance,navigation,and control accuracy,to realize the touchdown operation.In this paper,strategies and technical details of the guidance,navigation,and control systems are presented.The flight results prove that the performance of the systems was satisfactory and largely contributed to the success of the operation. | Fuyuto Terui Naoko Ogawa Go Ono Seiji Yasuda Tetsuya Masuda Kota Matsushima Takanao Saiki Yuichi Tsuda | 2020 | Astrodynamics2020，4，4： | 1 |
| 10 | Solar power sail mission of OKEANOS显示文摘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 membrane.Japan 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 2010.IKAROS demonstrated photon propulsion and power generation using thin-film solar cells during its interplanetary cruise.Scaled up,solar power sails can generate enough power to drive high specific impulse ion thrusters in the outer planetary region.With 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 Earth.This paper proposes a system design for OKEANOS and includes analyses of the latest mission. | 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 | 2020 | Astrodynamics2020，4，3： | 0 |
| 11 | Hayabusa2’s superior solar conjunction mission operations: Planning and post-operation results显示文摘In late 2018,the asteroid Ryugu was in the Sun's shadow during the superior solar conjunction phase.As the Sun-Earth-Ryugu angle decreased to below 3°,the Hayabusa2 spacecraft experienced 21 days of planned blackout in the Earth-probe communication link.This was the first time a spacecraft had experienced solar conjunction while hovering around a minor body.For 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 km.The trajectory was planned with the newly developed optNEAR tool and validated with real time data.This article shows the results of the conjunction operation,from planning to fight data. | 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 | 2020 | Astrodynamics2020，4，4： | 0 |
| 12 | Motion reconstruction of the small carry-on impactor aboard Hayabusa2显示文摘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 Ryugu.This enables us to sample subsurface materials,which will provide a window to the past.The physical properties of the resulting crater are also useful for understanding the internal structure of Ryugu.Accurate understanding of the crater and ejecta properties,including the depth of excavation of subsurface materials,requires accurate information on impact conditions.In particular,the impact angle is a critical factor because it greatly influences the size and shape of the crater.On April 5,2019,the Hayabusa2 spacecraft deployed the SCI at 500 m of altitude above the asteroid surface.The SCI gradually reduced its altitude,and it shot a 2 kg copper projectile into the asteroid 40 min after separation.Estimating the position of the released SCI is essential for determining the impact angle.This study describes the motion reconstruction of the SCI based on the actual operation data.The results indicate that the SCI was released with high accuracy. | 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 | 2020 | Astrodynamics2020，4，4： | 0 |
| 13 | Ground-based low altitude hovering technique of Hayabusa2显示文摘The asteroid explorer Hayabusa2 carries multiple rovers and separates them to land on an asteroid surface.One of these rovers,called MASCOT,was developed under the international cooperation between the Deutsches Zentrum f¨ur Luft-und Raumfahrt and the Centre National d’Etudes Spatiales.This rover was designed to be separated to land and perform several missions on an asteroid surface.To support these missions,the mother ship Hayabusa2 must separate this rover at a low altitude of approximately 50 m and hover at approximately 3 km after separation to achieve are liable communication link with MASCOT.Because the on-board guidance,navigation,and control(GNC)does not have an autonomous hovering function,this hovering operation is performed by ground-based control.This paper introduces the GNC operation scheme for this hovering operation and reports on its flight results. | Yuya Mimasu Kent Yoshikawa Go Ono Naoko Ogawa Fuyuto Terui Yuto Takei Takanao Saiki Yuichi Tsuda | 2020 | Astrodynamics2020，4，4： | 0 |
| 14 | Hayabusa2’s station-keeping operation in the proximity of the asteroid Ryugu显示文摘The Japanese interplanetary probe Hayabusa2 was launched on December 3,2014 and the probe arrived at the vicinity of asteroid 162173 Ryugu on June 27,2018.During its 1.4 years of asteroid proximity phase,the probe successfully accomplished numbers of record-breaking achievements including two touchdowns and one artificial cratering experiment,which are highly expected to have secured surface and subsurface samples from the asteroid inside its sample container for the first time in history.The Hayabusa2 spacecraft was designed not to orbit but to hover above the asteroid along the sub Earth line.This orbital and geometrical configuration allows the spacecraft to utilize its high-gain antennas for telecommunication with the ground station on Earth while pointing its scientific observation and navigation sensors at the asteroid.This paper focuses on the regular station-keeping operation of Hayabusa2,which is called“home position”(HP)-keeping operation.First,together with the spacecraft design,an operation scheme called HP navigation(HPNAV),which includes a daily trajectory control and scientific observations as regular activities,is introduced.Following the description on the guidance,navigation,and control design as well as the framework of optical and radiometric navigation,the results of the HP-keeping operation including trajectory estimation and delta-V planning during the entire asteroid proximity phase are summarized and evaluated as a first report.Consequently,this paper states that the HP.keeping operation in the framework of HPNAV had succeeded without critical incidents,and the number of trajectory control delta-V was planned fficiently throughout the period. | Yuto Takei Takanao Saiki Yukio Yamamoto Yuya Mimasu Hiroshi Takeuchi Hitoshi Ikeda Naoko Ogawa Fuyuto Terui Go Ono Kent Yoshikawa Tadateru Takahashi Hirotaka Sawada Chikako Hirose Shota Kikuchi Atsushi Fuji Takahiro Iwata Satoru Nakazawa Masahiko Hayakawa Ryudo Tsukizaki Satoshi Tanaka Masanori Matsushita Osamu Mori Daiki Koda Takanobu Shimada Masanobu Ozaki Masanao Abe Satoshi Hosoda Tatsuaki Okada Hajime Yano Takaaki Kato Seiji Yasuda Kota Matsushima Tetsuya Masuda Makoto Yoshikawa Yuichi Tsuda | 2020 | Astrodynamics2020，4，4： | 0 |
| 15 | Design and flight results of GNC systems in Hayabusa2 descent operations显示文摘Hayabusa2 is a Japanese sample return mission from the near-Earth asteroid Ryugu.The Hayabusa2 spacecraft was launched on December 3,2014,and reached the asteroid on June 27,2018.It remained there until November 13,2019 for in situ observation and soil sample collection and will return to the Earth in November or December 2020.During its stay at the asteroid,Hayabusa2 performed descent operations 16 times.This paper presents an overview of a guidance,navigation,and control method used in such descent operations.The 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 asteroid.Flight 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. | Go Ono Fuyuto Terui Naoko Ogawa Yuya Mimasu Kent Yoshikawa Yuto Takei Takanao Saiki Yuichi Tsuda | 2020 | Astrodynamics2020，4，2： | 0 |
| 16 | Correction to: Orbit insertion strategy of Hayabusa2’s rover with large release uncertainty around the asteroid Ryugu显示文摘Correction to:Oki,Y.,Yoshikawa,K.,Takeuchi,H.et al.Orbit insertion strategy of Hayabusa2's rover with large release uncertainty around the asteroid Ryugu.Astrodynamics 2020,4(4):309-329 http://gffzzd3cc09b8251d45dfswf5v0ckwc55066uf.ffgz.tsg.suse.edu.cn/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 access.After 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. | 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 | 2021 | Astrodynamics2021，5，2： | 0 |
您所在的机构暂未开通此部分的功能，请联系管理员