This research started in 2015 and completed in the end of FY2017 under the support by Grant-in-Aid for Scientific Research (B) of MEXT (KAKENHI).

Progress [March 31, 2018]

The progress of the research was shown below.

March 1, 2018 The invited paper "Deployable Techniques for Small Satellites" (Author: Yasuyuki Miyazaki) is published in Proceedings of the IEEE.
January 30, 2018 The paper "Modified method of detecting dynamic buckling" (Author:Shoko Arita, Yasuyuki Miyazaki) is published on the web site of Mechanical Engineering Letters.
January 8-12, 2018 The SciTech Forum was held in Orando. Ms. Fukunaga presented "Structural Characteristics of The Self-extensible boom", Mr. Tomohiro Suzuki presented "Similarity Rule of Deployment Behavior for Spin Deployment Membrane".
December 4, 2017 The Debris Mitigation Competition was held in University of Rome. Mr. Kousaka, Mr. Kawarabayashi, and Ms. Fukunaga presented "Membrane Deplyment De-orbit Device Composed of Self-Deployable TrussStructure" and won th e first place.
November 17, 2017 We conducted the deployment experiment of 30m-sized self-deployable truss(video: https://youtu.be/XinWA9eavJM)
November 15, 2017 We conducted the deployment experiment of 2m-sized self-deployable 3D truss(video: https://youtu.be/ANl2IXZ80hs)
October 30, 2017 We conducted the deployment experiment of 20m-sized self-deployable truss (video: https://youtu.be/apV0g6r6jTI)
October 26, 2017 The 61st Space Sciences and Technology Conference was held in Toki Messe, Niigata, Japan. Ms. Fukunaga (M1) presented "Improvement of Deployment of Self-Deployable Truss" in the poster session, and won the young presentation award.
April 18, 2017 We conducted the deployment experiment of self-deployable membrane truss srtucture (video:https://youtu.be/42C8XcUh-dM)
January 9-13, 2017 Mr. Tada presented his research "Membrane Deployment de-orbit System by convex tapes", Mr. Tatematsu "Verification of the Similarity Rules for Spin Deployment Membrane in the ground experiment ", and Mr. Tamura "Deployment Dynamics of Selfdeployable Truss Structure Consisting of Bi-convex Booms" at SciTech.
October 17-23, 2016 The Deorbit Device Competition was held at Barna, Bulgaria, and Mr. Tada (M2) won the first place by his proposal "Membrane Deployment De-orbit System by Convex Tapes".
August 8-10, 2016 The international conference ACMD2016 was held in Kanazawa city for 3 days from 8 August to 10 August. Mr. Tamura (M2) had the presentation about his research "Report on Microgravity Experiments of Self-Deployable Truss Structure Consisting of BCON Booms", and Mr. Tatematsu had the presentation "Similarity Rules for Spin Deployment Membrane". Mr. Tamura, Mr. Inoue, Mr. Hyodo, and Prof. Miyazaki won the paper award.
August 9, 2016 We conducted the deployment experiment of self-deployable truss srtucture (video:https://www.youtube.com/watch?v=sH7NHZwPzMM)
March 31, 2016The paper "A study of dynamic evaluation of structural buckling" (Author: Shoko Arita, Yasuyuki Miyazaki) is published on the web site of Mechanical Engineering Journal.
February 4-5, 2016We conducted the deployment experiment under micro-gravity environment by the parabolic flight of small airplane.
December 15, 2015The paper "Analytical solution of the bending of a bi-convex boom" (Author: Yasuyuki Miyazaki, Shota Inoue, Akihiro Tamura) is published on the web site of Mechanical Engineering Journal.
July, 2015We introduced a parallel computer made by HPC Systems.


This research is conducted on the basis of the results obtained by past research project by KAKENHI. The objectives of this researchis to formulate a theory for a fast and highly precise dynamic analysis of large gossamer multi-body space structure, and to understand the essense of the motion of such a structure by using the theory . Here large gossamer multi-body structure means a structure that consists of gossamer structure such as large membrane and cable, and support structures such as extensible booms and spacecraft main body. We pursure the following three theme:

  1. To develop a large scale parallel analysis code NEDA3.0 that can calculate 10 milion time steps of the motion of large gossamer multi-body structure such as so-called "IKAROS2" (DOF is around 200 thousands), ans to show the condition for stable spin deployment and for maintainance of deployed shape of IKAROS2 (for example, appropriate initial spin rate, the amount of solar pressure torque to be cancelled by actuators, and so on),
  2. To show appropriate experimental method of small scale model of large gossamer structure on the flat table (1G, 1atom), in large vacuum chamber (1G, 0 atom), and under micro-gravity environment (0G, 1 atom) using the spin deployment of membrane and self-deployment of membrane truss as examples, to establish a similarity rule to predict the motion of large gossamer structure on orbit from the ground experiment of its small scale model, and to verify the proposed similarity rule by comparing with the numerical results and flight data of IKAROS,
  3. To establish the prediction method of dynamics of large gossamer structure on orbit from small scale ground experiment and numerical analysis results, to show the method to evaluate the effect of each design parameter on the whole motion of the structure quickly by applying the model reduction procedure and error estimation method of model reduction, and to clarify the feature, essense of the motion of large gossamer structure by the examples of spin deployment of membrane and self-deployment of membrane truss.

So-called "IKAROS2"is the spacecraft to explore the Troijan asteroid that is now under study by solar power sail WG of JAXA. It deploy membrane of about 50m square that is covered with thin membrane solar cells. IKAROS2 employs ion thrusters usin ght electric power generated by the solar cells, and explore to the asteroid by way of Jupiter. The area of the membrane is more than ten times of that of IKAROS that has 14m square membrane. The spacecraft main body looks like a tiny object put on large membrane. That's surely "large gossamer muti-body space structure". As you can see at the web site of ISAS

This middle sail (it becomes large spacecraft if it deploys the membrane. But the dimension and the mass of the spacecraft at the launch is middle, so that it is called &middle% sail) uses the membrane as the solar array to supply large electric power to the ion thrusters rather than solar sail propulsion.

"Self-deployment of membrane truss" mentioned above means the self-deployable truss consisting of bi-convex booms that is researched in the project "Realization of large space structure by ultra-light high stiffness convex boom" supported by KAKENHI until FY2014. If membrane is attached to this truss, it becomes a typical gossamer multi-body structure that consists of membrane, flexible booms, and nodes of rigid body. We are also interested in the way to attach the membrane to the truss structure, how to stretch the membrane (how to minimize the effect of the crease of the membrane, how to stretch with wrinkle-free).


奥泉信克,白澤洋次,森治,佐藤泰貴,松永三郎,名取通弘,古谷寛,坂本啓,山浦弘,宮崎康行,井上遼太,菊池隼仁,水森主,北尾啓,佐藤剛志,西澤匡士,横松卓,倉重宏康,木星トロヤ群探査に向けた大型ソーラー電力セイル膜面展開構造・機構に関する検討,宇宙科学シンポジウム,P-260,2015年1月6日〜7日, 宇宙科学研究所, 2015.

丸木悠暉,宮崎康行,嶋崎信吾,村田亮, 地上実験結果を用いた柔軟宇宙構造物の軌道上挙動推定法, 2014 年度日本機械学会年次大会講演論文集, S1920203, p.1-5, 2014年9月7日〜9月10日, 東京電機大学, 2014.

Go ONO, Kengo SHINTAKU, Yoji SHIRASAWA, Osamu MORI, Yasuyuki MIYAZAKI, Saburo MATUNAGA, "Study of Asynchronous Solar Sail Deployment Using Finite Element Method", TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN, Vol. 12 (2014) No. ists29 p. Pc_63-Pc_67, August 2014, DOI: http://dx.doi.org/10.2322/tastj.12.Pc_63.

宮崎康行, 「BCONブームの曲げ理論」, 第56回構造強度に関する講演会講演集, 1A18(JSASS-2014-3019), pp.48-50, 平成26年8月6日〜8月9日, 浜北文化センター, 2014.

村田亮, 井上翔太, 宮崎康行, 「宇宙構造物の伸展部材用コンベックステープの展開挙動」, 第56回構造強度に関する講演会講演集, 1A17(JSASS-2014-3018), pp.45-47, 平成26年8月6日〜8月9日, 浜北文化センター, 2014.

嶋崎信吾, 村田亮, 丸木悠暉,「パラボリックフイトによる微小重力環境を利用した柔軟宇宙構造物の軌道上挙動推定法」, Int. J. Microgravity Sci. Appl. Vol. 31 No. 3, pp.142-149, 2014.

College of Science and Technology, Nihon University
Department of Aerospace Engineering
Space Structure Systems Laboratory
College of Science and Technology, Nihon University
7-24-1 Narashinodai, Funabashi, Chiba 274-8501, Japan
e-mail: asel (at) forth.aero.cst.nihon-u.ac.jp