基本情報
- 所属
- 国立研究開発法人宇宙航空研究開発機構 宇宙科学研究所 教授
- 学位
- 博士(工学)(1993年3月 東京大学)Doctor(Engineering)(The University of Tokyo)
- 研究者番号
- 30256812
- J-GLOBAL ID
- 200901061816089228
- researchmap会員ID
- 1000168973
- 外部リンク
宮崎康行は1993年に東京大学にて航空学の博士の学位を取得し、1993年以降、日本大学に勤務。主な研究分野は柔軟多体動力学および展開大型宇宙構造物の構造動力学である。また、2001年から2002年にかけて、コロラド大学ボウルダ―校にて弾性体の衝突の数値シミュレーションの研究を行っていた。研究成果の宇宙実証にも重点を置き、2001年~2019年にかけて、研究室にて4機のCubeSatを開発し、打ち上げ・運用を行うとともに、2010年にJAXAが打ち上げて宇宙空間にて大型膜面の展開に成功したソーラーセイルIKAROSのプロジェクトメンバーとして、IKAROSの膜面展開のダイナミクスを予測する解析コードを開発した。この他、2012年に実施したISSでの宇宙インフレータブル構造の宇宙実証プロジェクトSIMPLEに参加し、インフレ-タブル伸展マストの研究・開発に従事してきた。
2020年10月にJAXA宇宙科学研究所に移り、現在は宇宙科学・探査用の伸展構造・展開構造の研究・開発に従事している。
研究分野
4経歴
7-
2020年10月 - 現在
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2008年4月 - 2020年9月
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2006年4月 - 2008年3月
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2004年4月 - 2008年3月
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1997年4月 - 2004年3月
学歴
2-
- 1993年
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1984年4月 - 1988年3月
委員歴
13-
2020年5月 - 現在
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2014年4月 - 現在
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2022年3月 - 2024年3月
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2008年4月 - 2024年3月
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2020年6月 - 2023年3月
受賞
7-
2018年3月
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2017年11月
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2015年3月
論文
84-
Progress in Aerospace Sciences 150 101047-101047 2024年10月
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Space Telescopes and Instrumentation 2024: Optical, Infrared, and Millimeter Wave 99-99 2024年8月23日
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Space Telescopes and Instrumentation 2024: Optical, Infrared, and Millimeter Wave 214-214 2024年8月23日
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Acta Astronautica 218 342-355 2024年5月 査読有り
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AIAA SCITECH 2024 Forum 1-15 2024年1月4日 査読有り
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Space Telescopes and Instrumentation 2022: Optical, Infrared, and Millimeter Wave 2022年8月27日
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Acta Astronautica 192 113-121 2022年3月 査読有り
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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 65(1) 11-22 2022年 査読有り
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AIAA Scitech 2020 Forum 1-12 2020年1月6日 査読有り最終著者
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Proceedings of AIAA Scitech 2019 Forum 1-13 2019年1月7日 査読有り
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PROMOTE THE PROGRESS OF THE PACIFIC-BASIN REGION THROUGH SPACE INNOVATION 166 365-370 2019年 査読有りIn recent years, a large space film structure having a thickness of several micro and a shape of several to several tens of meters attracts attention, and various storing methods have been studied. Considering the thickness of the film surface at the time of winding before launching, there is a problem that circumferential difference occurs inside and outside of the folded film surface. In order to solve this problem, a method of solving the difference between the inner and outer circumference by predicting the inner / outer circumferential difference arising from the film surface and the thickness of the device and managing the phase has been proposed. On the other hand, the point that the target value for adjusting the phase is unknown and empirical was pointed out, and as a result of adjusting the phase, the wave-like slack that occurred caused the unevenness of the film thickness in the circumferential direction. In this research, we derive target value of phase management analytically, compare with experiment, and verify.
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Proceedings of the IEEE 106(3) 471-483 2018年3月1日 査読有り招待有りA deployable structure serves an important function in small satellites as their performance is improved steadily. Larger deployable solar array paddles are expected as the satellite requires a larger amount of electric power. The synthetic aperture radar (SAR) system for small satellites requires a deployable antenna. Various deployable membrane structures have been proposed for the deorbit of micro/nanosatellites in low Earth orbit. The actuators and devices for a deployable structure continue to progress along with the development of a deployable structure. The hold-release mechanism has been becoming smaller and simpler. The shape control devices are actively researched for a high-precision deployable structure. There are several requirements imposed on the deployable structures, e.g., low cost, lightweight, small volume in stored configuration, reliable deployment, large aperture in deployed configuration, and accuracy/repeatability of a deployed shape. Dedicated efforts are made to satisfy these requirements in research and development of a deployable structure/device. This paper provides an overview of the past and current research and development of a deployable structure for small satellites.
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Mechanical Engineering Letters 4(17-00441) 1-8 2018年1月30日 査読有り
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Proceedings of 2018 AIAA Modeling and Simulation Technologies Conference (AIAA 2018-2159) 1-14 2018年1月8日 査読有り
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Advances in the Astronautical Sciences 166 365-370 2018年 査読有り© 2018 Univelt Inc. All rights reserved. In recent years, a large space film structure having a thickness of several micro and a shape of several to several tens of meters attracts attention, and various storing methods have been studied. Considering the thickness of the film surface at the time of winding before launching, there is a problem that circumferential difference occurs inside and outside of the folded film surface. In order to solve this problem, a method of solving the difference between the inner and outer circumference by predicting the inner / outer circumferential difference arising from the film surface and the thickness of the device and managing the phase has been proposed. On the other hand, the point that the target value for adjusting the phase is unknown and empirical was pointed out, and as a result of adjusting the phase, the wave-like slack that occurred caused the unevenness of the film thickness in the circumferential direction. In this research, we derive target value of phase management analytically, compare with experiment, and verify.
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AIAA Spacecraft Structures Conference, 2018 (210019) 1-10 2018年 査読有りThe gossamer structures combined with deployable truss structures and membrane structures are suggested for recently proposed large space structures. Several types of the boom are expected as the members of the deployable truss. Tape spring is one of the candidates because the rolled-up tape spring can extend automatically without any actuator by releasing the stored strain energy, i.e. it has self-extensibility. Bi-convex boom and the braid coated biconvex boom (BCONTM boom) are also candidates. If those booms are used for the structural member, the truss can deploy by employing the self-extensibility of the booms, i.e. it has characteristics of self-deployable structure. In this paper, the structural characteristics of those booms are described and the effect of the tension of braid mesh on the stiffness of the boom is investigated. The stiffness of the boom is estimated theoretically and experimentality. This paper the difference between those booms and the closed-section boom with the end of the boom fixed.
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AIAA Spacecraft Structures Conference, 2018 (210019) 1-13 2018年 査読有りRecent expansion of space exploitation, especially advance of micro/nano satellite technology, leads to an increased demand for planer deployable membrane structure. One of the most important requirements is the simplicity and the realiability of the deployment as well as the stiffness of the structure. The self-deployable truss composed of bi-convex booms is one of the candidates that satisfy those requirements. In this paper, a planer membrane structure supported by the self-deployable truss is proposed and its structural characteristics is presented. The technical problems that must be solved for the realization of the proposed structure in space are discussed and the possible solutions of those problems are also given in the paper.
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AIAA Spacecraft Structures Conference, 2018 (210019) 1-9 2018年 査読有りIn recent years, there are a lot of research on membrane space structure. It is essential to estimate the deployment behavior of these structure. However, It is difficult to use actual size membrane for experiment because it is affected by gravity and air drag. Therefore, prediction based on experiments has yet to be done. Accordingly, we make some sexperiment using caled-down model. But small scale models and large scale models do not always perform the same deployment behavior[1]. So if similarity deployment rule between large-scale model and small-scale models is established, we can predict the deployment behavior of the flight model membrane from ground experiments using small-scale membrane. This paper propose the similarity rule between large-scale and small-scale models at deployment.
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AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 2018 (210049) 1-10 2018年 査読有りAs a system for construction of a large space structure and debris mitigation, deployable structural systems are indispensable. Gossamer structure realize a larger and lighter structure by storing and deploying using deformation and buckling of members. In particular, buckling easily occurs in the flexible structural member, and its large deformation enables smooth deployment. Furthermore, external impetus to deploy is suppressed to be small because deformation by the buckling progresses greatly only with the strain energy of the member. The paper proposes a new available deployable structure “Deployable Cube”, which is a bistable structure applying buckling actively. The authors developed a prototype of the Deployable Cube for a Cubesat. In order to investigate the structural properties, eigen mode analysis after deployment of the prototype model was performed, and the stiffness is indicated. Furthermore, dynamic buckling analysis using the original method proposed by the authors was carried out for the initial stage of the deployment, and it is indicated that the estimation of buckling mode is valid.
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Proceedings of 4th AIAA Spacecraft Structure Conference (AIAA 2017-0175) 1-10 2017年1月10日 査読有り
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Proceedings of 4th AIAA Spacecraft Structures Conference (AIAA 2017-0619) 1-11 2017年1月9日 査読有り
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Proceedings of 4th AIAA Spacecraft Structures Conference (AIAA 2017-1114) 1-9 2017年1月9日 査読有り
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Proceedings of the International Astronautical Congress, IAC 12 7844-7852 2017年Deployable structures are necessary for spacecraft to challenge advanced missions. It is important in designing the deployable space structures that they are easily deployable and reliably repeatable. Conventional study for improving the repeatability was conducted by investigating errors and its effect to the deployment. However, there was no general numerical method to evaluate the reliability efficiently and quantitatively, not estimating any errors. Therefore, the authors proposed an original numerical method to evaluate quantitatively the reliability of the deployment by detecting buckling in a dynamic analysis of FEM. The repeatability is decreased due to occurrence of the buckling caused by the errors. Therefore, a structure not occurring the buckling should be selected for designing of a reliably repeatable structure. The buckling is detected by non-positive eigenvalues of a stiffness matrix of the structure in static analysis. However, detection of the buckling in dynamic analysis is difficult because the eigenvalue is also non-positive when the structure has rigid-body motion. This study solved the problem by proposing a method to discriminate the buckling from the rigid-body motion. In the recent study, we found a problem of false detection of the buckling by the conventional method, and we also found a method to solve the problem. The cause of the problem is using the eigenvalue for the judgement of the buckling because it cannot be evaluate that the sign of the eigenvalue derives whether from the rigid-body motion or from the deformation. Therefore, the modified method does not use the eigenvalue but uses the work of the deformation for the judgement of the buckling. Furthermore, a method to evaluate instability of the structure quantitatively is desired when the buckling occurs in the deployment of a structure for the spacecraft. When the buckling occurs, small disturbance sets off grave displacement. Therefore, this study proposed the method to evaluate the instability quantitatively by calculating disturbance force and buckling displacement as index values of the instability based on the equation of motion. Additionally, this study proposed a method to visualize structural instable area in an entire structure. By looking the instable area, developers of a spacecraft can take measures for the instable area, and improve the reliability of the structure. Finally, we applied the proposed method to an analysis of presumed actual space structure, and inquired about the buckling.
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Trans. JSASS, Aerospace Tech. Japan Vol.14(No.ists30) Pc_13-Pc_17 2016年5月 査読有り
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Mechanical Engineering Letters 2(15-00677) 15-00677-15-00677 2016年3月31日 査読有りTechnology of deployable space structures is necessary for spacecraft to challenge advanced missions. It is important in designing the deployable space structures that they are easily deployable and reliably repeatable. Traditional approach for improving the repeatability was conducted by investigating errors and its effect to the deployment. However, the traditional approach has a problem that results change depending on estimation of the errors. With that background, this study proposes numerical methods to enable selection of robust deployable structures against the errors. The repeatability is decreased due to occurrence of the buckling caused by the errors. Therefore, a structure not occurring the buckling should be selected for designing of a reliably repeatable structure. The buckling is detected by non-positive eigenvalues of a stiffness matrix of the structure in static analysis. However, detection of the buckling in dynamic analysis is difficult because the eigenvalue is also non-positive when the structure has rigid-body motion. This study solved the problem by proposing a method to discriminate the buckling from the rigid-body motion. Furthermore, a method to evaluate instability of the structure quantitatively is desired when only structures occurring the buckling are available for the spacecraft. When the buckling occurs, small disturbance sets off grave displacement. Therefore, this study proposed the method to evaluate the instability quantitatively by calculating disturbance force and buckling displacement as index values of the instability based on the equation of motion. Finally, it was confirmed that the proposed methods are appropriate by the dynamic analyses of truss arch.
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Mechanical Engineering Journal 2(6) 1-19 2015年12月15日 査読有りThis paper derives closed-form solutions for the local deformation of a bi-convex boom under circular bending, and the resulting strain energy and self-extending force. Convex tapes and bi-convex booms that consists of a pair of convex tapes can be stored into a small volume and have high specific rigidity. They extert a self-extending force when stored cylindrically. Therefore, they have been proposed as members of deployable space structures. In this paper, two types of bi-convex booms are considered. In the first, the tapes of the bi-convex boom are bonded to each other at their edges; in the second, the tapes are wrapped in a cylindrical braid mesh. The latter is called a BCON (braid-coated bi-convex) boom. The tape of a BCON boom can slip on each other, and do not separate from each other because of the tension of the mesh net. Consequently, the BCON boom can be used in an ultralight self-deployable structure with quite high stowage volume efficiency and specific rigidity. However, structures using convex tapes or BCON booms have been designed and developed through a trial-and-error process because there is no appropriate formula for the self-extending force of convex tapes. This paper proposes a formula for the deformation of a convex tape that is initially bent into a circular shape. The deviation from the circular shape is obtained by solving the equilibrium equations. The deformation of a bi-convex boom is also derived by using the solution for a convex tape. Thus the theory described in this paper contributes to the design of space structures using convex tapes in bi-convex booms, as well as to the structural mechanics of flexible beams.
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2015 7TH INTERNATIONAL CONFERENCE ON RECENT ADVANCES IN SPACE TECHNOLOGIES (RAST) 793-796 2015年 査読有りRecently, space science mission has been more and more complicated and advanced. Its scale has been larger and larger. Accordingly deployable structure grows increasingly important. The space verification is quite important or necessary for deployable structures that have not been proved in space. Thus more and more opportunities with low-cost are desired for the space verification. Nano-satellite in low earth orbit is most suitable for the test-bed of the small scale model of the structures. Moreover, such a deployable structure can be used as the de-orbit device, so that it can be a solution of the space debris issue. This paper discusses the importance and the methodology of the space verification of the key technologies for advanced large deployable structures by using nano-satellites.
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日本航空宇宙学会誌 = Aeronautical and space sciences Japan 62(10) 331-336 2014年10月5日 招待有り大学宇宙工学コンソーシアム(University Space Engineering Consortium:UNISEC)は10年余にわたる国内高専・大学への実践的宇宙開発の支援を経て,宇宙ハンズオントレーニングの有用性・有効性を確信し,活動を宇宙開発新興国を含む他地域に広げるべく,2011年に国際委員会を組織した.国際向けの活動としては,超小型衛星のミッションアイディア国際コンテスト開催,海外の新興国への衛星開発教育の実践,超小型衛星シンポジウムの事務局運営などがある.UNISECでは,2020年までに100以上の国で大学生が実践的宇宙開発に参加できるような世界を作ろうという「VISION 2020-100」を発表し,世界各地にUNISECのような大学連携組織を作り,それらの組織を横断的につなぐUNISEC-Globalを設立しようという提案を国連の会議等で行い,2013年11月には,第1回UNISEC世界大会(The 1st UNISEC-Global Meeting)を実施し,UNISEC-Globalの設立が宣言された.本稿では,UNISEC国際展開の経緯と成果およびその将来展望,課題について考察する.
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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 12(ists29) Pc_63-Pc_67 2014年8月23日 査読有り
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Mechanical Engineering Journal 1(4) 1-16 2014年8月15日 査読有り
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The Journal of Space Technology and Science 27(1) 1_54-1_68 2014年8月14日 査読有り
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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 12(29) Pc_1-Pc_7 2014年4月23日 査読有りA space inflatable extension mast designed on an idea of structural rigidization simulation system has been projected and provided to verify its engineering technology and to obtain the structural property for a long-term operation in space environment. The inflatable mast extended successfully in orbit, and has sent the telemetry data for more than seven months, so far. The experiment progress meets both its minimum and full success criteria for this mast. The simulation model of this mast is made up based upon the ground test, and predicts the natural frequency in orbit. Lightweight extendible masts are fundamental and essential structural elements to construct space structures; therefore a pivotal first step of conditions to utilize space inflatable structures has been actually achieved.
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5th Asian Conference on Multibody Dynamics 2010, ACMD 2010 2 904-909 2014年In recent years, the use of membranes for space craft applications has attracted a great deal of attention, as so called gossamer structures. However gossamer structures do not have practical applications at present. One problem in space research is design time reduction. Currently, JAXA is working on a spin type solar power sail spacecraft. Computational analysis of the sail membrane's complex mathematical model is difficult and time consuming. Therefore this has a negative impact on design problems. The model reduction technique is required. With a feasible shortened computational analysis period, a trade-off would be possible when designing and determining the operation procedure. It is a necessary tool in order to put the gossamer structure to practical use. The authors have already suggested a possible benefici al effect of the empirical model reduction for gossamer stru crure. Unfortunately the method couldn't deal with the geo metric constraint, for example rigid body with cable constra int. The purpose of this research is to construct a reduction model of geometrical constrained gossamer structure. Generally, the equations of motion of gossamer structures are highly nonlinear and stiff differential equations. For this reason we employ the geometrically nonlinear FEM code. The code is based on the energy momentum method (EMM), so the numerical time integration is unconditionally stable. In this paper, we constructed a penalty method for the geometrical constraint based on the EMM. This permits expression of the geometric constraint in a model. It is possible to apply empirical model reduction techniques to this mathematical model. This can make constructing of a reduction model including geometric constraint. We will show the reduction model can approximate the full-order model with sufficient accuracy. Copyright (c) 2010 by JSME.
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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 12(ists29) Pc_75-Pc_82 2014年
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PROCEEDINGS OF 6TH INTERNATIONAL CONFERENCE ON RECENT ADVANCES IN SPACE TECHNOLOGIES (RAST 2013) 1081-1086 2013年 査読有りThis paper reports the history of the student pico-satellite program in Nihon University, especially about how a small laboratory which had no knowledge on satellite technology has succeeded the launch and operation of the student pico-satellite. The author hopes that his method would be a helpful example for supervisors who will start the student satellite program.
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Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference 1-15 2013年 査読有りThis paper proposes a method to store a large solar-sail membrane while ensuring repeatability of its stored configuration. The feasibility and effectiveness of the method is verified through a series of sail-storage experiments using 10m-size membranes. Large membranes used as a solar sail should be stored compactly to save the launch volume; in addition, their stored configuration should be sufficiently predictable in order to guarantee reliable deployment in orbit. However, it is difficult to store a large membrane compactly with sufficient repeatability because of the finite thickness of the membrane. This paper classifies the existing and proposed folding patterns that can consider the finite-thickness of membranes. This paper then demonstrates the feasibility of "bulging roll-up" experimentally, and evaluates the repeatability of its stored configuration quantatively. © 2012 AIAA.
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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 10(ists28) Po_4_21-Po_4_26 2012年12月10日 査読有り
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Journal of Aerospace Engineering, Sciences and Applications 4(4) 79-96 2012年10月 査読有りThe Japan Aerospace Exploration Agency (JAXA) makes the world's first solar power sail craft IKAROS demonstration of photon propulsion and thin film solar power generation during its interplanetary cruise. The spacecraft deploys and spans a membrane of 20 meters in diameter using the spin centrifugal force. It also deploys thin film solar cells on the membrane, in order to evaluate its thermal control property and anti-radiation performance in the real operational field. The spacecraft weighs approximately 310kg, launched together with the agency's Venus Climate Orbiter, AKATSUKI on May 21, 2010. This paper presents the summary of development and operation of IKAROS.
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JASMA : Journal of the Japan Society of Microgravity Application 29(1) 48-55 2012年1月31日 招待有り
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JOURNAL OF SPACECRAFT AND ROCKETS 48(5) 881-890 2011年9月 査読有りThe present study develops a new three-dimensional Timoshenko beam finite element whose length can be varied during transient dynamic analysis. The variable-length element enables the dynamic deployment analysis of flexible appendages with nonnegligible bending stiffness. In addition, the developed scheme employs an implicit time integration whereby energy and momentum in the system are properly conserved, and no artificial numerical dissipation is introduced. The developed beam element is then used in an finite element model of a solar sailcraft, and its deployment dynamics are analyzed allowing for the nonzero bending stiffness of the bundled membranes, as well as the effect of some realistic design imperfections.
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Proceedings of AIAA Modeling and Simulation Technologies Conference 2011 1 1-9 2011年8月8日 査読有り
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62nd International Astronautical Congress 2011, IAC 2011 7 5625-5630 2011年 査読有りJapan Exploration Agency (JAXA) launched a powered solar sail "Interplanetary Kite-craft Accelerated by. Radiation Of the Sun (IKAROS)" on May 21, 2010. One of the primal technologies demonstrated at IKAROS is the deployment of the sail whose diameter is 20m class. After the launch, the deployment operation was performed and successful expansion of the sail was confirmed. The deployment sequence in IKAROS consists of static first stage and dynamic second stage. In this paper, the flight data and observed dynamic motion during the first stage deployment are reported. These are compared with the results of numerical simulations using multi-particle model, and the accuracy and availability of this model is discussed. Copyright ©2011 by the International Astronautical Federation. All rights reserved.
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Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference 1-4 2011年 査読有りThe Solar Sail "IKAROS" (Interplanetary Kite-craft Accelerated by Radiation Of the Sun), which is the first solar sail on orbit, consists of 20m diagonal length square membrane made of 7.5mm thickness polyimide film. The sail membrane is deployed by centrifugal force due to spinning motion of the spacecraft. The wrapping fold is applied to realize stable deployment property. The manufacturing process of the large membrane with the folding techniques are described in detail. Copyright © 2011 by the American Institute of Aeronautics and Astronautics, Inc.
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Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference 1-8 2011年The paper will try to discuss the issue of reducing the time to calculate the nonlinear dynamics simulation of the gossamer structure, especially for the solar sail, because one of the problems in the gossamer structure is design time reduction. Therefore the present paper describes the low-order model of a spin type solar sail dynamics. The model reduction technique is required to shorten the design period. However there is no model reduction methodology about the solar sail dynamics. In this paper the full-order model of a spin type solar sail craft is modeled by geometrically nonlinear FEM based on the energy momentum method (EMM), so the numerical time integration is unconditionally stable. The low-order model is constructed by an empirical model reduction method. To conserve the geometrical relation of constraint conditions on the low-order space, we constructed a penalty method for the geometrical constraint based on the EMM. We will show the reduction model of the spin type solar sail model can approximate the full-order model with sufficient accuracy. Copyright © 2011 by the American Institute of Aeronautics and Astronautics, Inc.
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Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference 1-14 2011年Japan Exploration Agency (JAXA) launched a powered solar sail "Interplanetary Kite-craft Accelerated by Radiation Of the Sun (IKAROS)" on May 21, 2010. One of the primal technologies demonstrated at IKAROS is the deployment of the sail whose diameter is 20m class. After the launch, IKAROS performed the deployment sequence and have confirmed that the membrane was successfully expanded. In this paper, the flight data and observed dynamic motion via deployment are reported. These are compared with the results of numerical simulations using multi-particle model, and the accuracy and availability of this model is discussed. Copyright © 2011 by the American Institute of Aeronautics and Astronautics, Inc.
MISC
11書籍等出版物
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オーム社 2014年8月23日 (ISBN: 9784274505003)模擬人工衛星CanSatに関する解説書.CanSatの歴史,開発の意義,必要となる考え方や心構え,設計から開発,フィールド実験に至るまでに必要な知識や技術について解説.実際の衛星開発との対比も示してあり,CanSat開発について本書で学ぶことで,同時に本物の衛星の開発・利用の基礎を学ぶことができる.
講演・口頭発表等
425-
12th Annual IEEE International Conference on Wireless for Space and Extreme Environments (WISEE 2024) 2024年12月16日
共同研究・競争的資金等の研究課題
22-
日本学術振興会 科学研究費助成事業 2023年4月 - 2026年3月
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日本学術振興会 科学研究費助成事業 2021年4月 - 2024年3月
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日本学術振興会 科学研究費助成事業 2021年4月 - 2024年3月
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文部科学省 宇宙航空科学技術推進委託費 2018年8月 - 2021年3月
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科学研究費補助金 2018年 - 2020年
教育内容やその他の工夫
1-
年月日(From)2001/01/07年月日(To)2021/03/31件名CubeSatの開発・運用を通じたPBL概要研究室にて学生が1U~8UのCubeSatを計4機開発し,打ち上げて運用してきた.これを通じて,実践的な宇宙工学・システム工学の教育を行ってきた.
その他教育活動上特記すべき事項
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年月日(From)2012/03/29年月日(To)2012/03/29件名日本機械学会宇宙工学部門「宇宙賞」受賞概要CubeSat開発・打ち上げ・運用を通じた人材育成に対し,日本機械学会宇宙工学部門「宇宙賞」を受賞した.
● 指導学生等の数
4-
年度2018年度(FY2018)博士課程学生数1修士課程学生数12
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年度2019年度(FY2019)博士課程学生数1修士課程学生数11
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年度2018年度(FY2018)博士課程学生数1修士課程学生数7
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年度2021年度(FY2021)博士課程学生数2受託指導学生数3技術習得生の数2
● 指導学生の表彰・受賞
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指導学生名設樂翔一所属大学日本大学受賞内容(タイトル、団体名等)第62回宇宙科学技術連合講演会学生セッション最優秀発表賞受賞年月日2018年10月25日
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指導学生名山口光史郎所属大学日本大学受賞内容(タイトル、団体名等)千葉県知事賞受賞年月日2018年3月25日
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指導学生名高坂大樹,河原林大思,福永桃子所属大学日本大学受賞内容(タイトル、団体名等)Debris Mitigation Competitionにて1位受賞年月日2017年12月4日
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指導学生名福永桃子所属大学日本大学受賞内容(タイトル、団体名等)第61回宇宙科学技術連合講演会学生セッション優秀発表賞受賞年月日2017年10月26日
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指導学生名福永桃子所属大学日本大学受賞内容(タイトル、団体名等)平成28年度日本航空宇宙学会学生賞受賞年月日2017年3月25日
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指導学生名多田伸所属大学日本大学受賞内容(タイトル、団体名等)Deorbit Device Competitionにて1位受賞年月日2016年10月17日
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指導学生名井上将太, 田村明寛所属大学日本大学受賞内容(タイトル、団体名等)Paper Award in The 8th Asian Conference on Multibody Dynamics受賞年月日2016年8月10日
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指導学生名鈴木智大所属大学日本大学受賞内容(タイトル、団体名等)平成27年度日本航空宇宙学会学生賞受賞年月日2016年3月25日
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指導学生名嶋崎信吾, 村田亮, 丸木悠暉所属大学日本大学受賞内容(タイトル、団体名等)第11回航空機による無重力実験コンテスト最優秀賞受賞年月日2014年11月28日
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指導学生名吉原嘉唯, 河原林大思, 関口幸輝, 立松裕基, 田村明寛, 山田諭, 山田将太所属大学日本大学受賞内容(タイトル、団体名等)衛星設計コンテスト日本天文学会賞受賞年月日2013年11月9日
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指導学生名井上祥子所属大学日本大学受賞内容(タイトル、団体名等)Tsukuba Executive Committee Award of Student Session in rhe 27th International Symposium on Space Technology and Science受賞年月日2009年7月9日
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指導学生名有田公輔所属大学日本大学受賞内容(タイトル、団体名等)平成18年度日本航空宇宙学会学生賞受賞年月日2007年3月25日
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指導学生名山崎政彦, 山口晃, 荒木友太, 有田公輔, 瓜田彰, 岡崎一高, 亀山尚志, 種田惇也, 千葉悠太, 増田敬史所属大学日本大学受賞内容(タイトル、団体名等)第14回衛星設計コンテスト設計大賞受賞年月日2006年10月29日
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指導学生名木下延昭所属大学日本大学受賞内容(タイトル、団体名等)平成16年度日本航空宇宙学会学生賞を受賞年月日2005年3月25日
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指導学生名沖野聡所属大学日本大学受賞内容(タイトル、団体名等)平成15年度日本航空宇宙学会学生賞受賞年月日2004年3月25日
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指導学生名醍醐加奈子所属大学日本大学受賞内容(タイトル、団体名等)平成14年度日本航空宇宙学会学生賞受賞年月日2003年3月25日
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指導学生名塚本裕之所属大学日本大学受賞内容(タイトル、団体名等)平成13年度日本航空宇宙学会学生賞受賞年月日2002年3月25日
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指導学生名平城雅隆, 井上昌久, 大川祐輔, 境野正法, 野村晃司, 日沼俊介所属大学日本大学受賞内容(タイトル、団体名等)第9回衛星設計コンテスト日本航空宇宙学会賞受賞年月日2001年10月21日
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指導学生名桶田昌利, 生井沢正樹,山添由紀子, 石井幸生, 水野妙子, 恩田建作所属大学日本大学受賞内容(タイトル、団体名等)第6回衛星設計コンテスト日本航空宇宙学会賞受賞年月日1999年10月18日
● 専任大学名
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専任大学名総合研究大学院大学(SOKENDAI)