Dept. of Space Flight Systems

佐藤 泰貴

サトウ ヤスタカ  (yasutaka satou)

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 宇宙飛翔工学研究系 准教授

J-GLOBAL ID
202001003226441587
researchmap会員ID
R000014429

研究キーワード

 1

論文

 47
  • 田中 宏明, 岩佐 貴史, 小木曽 望, 勝又 暢久, 坂本 啓, 池田 忠繁, 岸本 直子, 樋口 健, 藤垣 元治, 土居 明広, 佐藤 泰貴, 山谷 昌大
    宇宙航空研究開発機構研究開発報告 23(003) 1-21 2024年2月  査読有り
  • Yasutaka Satou, Hiroshi Furuya, Shoko Kaida, Tomoyuki Miyashita
    AIAA JOURNAL 2022年5月  
    This paper addresses the ways by which the releasing and deploying behaviors of a creased space membrane can be predicted accurately. Although existing studies have analyzed the released shape of a creased membrane by considering the elasto-plastic properties, the shape did not agree with the experimental results when the membrane was tightly creased. To examine the released shape of the membrane, creasing and releasing experiments are first conducted. The experimental results indicate that the opening angle of the crease increases with increasing elapsed time after the release due to stress relaxation. The stress relaxation behavior is predicted using finite element analysis (FEA) by considering the visco-elasto-plastic material properties. In addition, an analytical model of the releasing and deploying membrane has been proposed here. The results of the FEA and the analytical model indicate that the released angles are in good agreement with those in the experimental results. Thus, the effects of viscosity are considered important for predicting the releasing behavior of the space membrane.
  • Yamada, Y, Inamori, T, Park, J. H, Satou, Y, Sugawara, Y, Yamaguchi, K
    Advances in Space Research 2022年2月  査読有り
  • 松下 将典, 高橋 秀幸, 佐藤 泰貴, 岩佐 貴史
    航空宇宙技術 21 53-61 2022年  
  • Yuki Takao, Osamu Mori, Masanori Matsushita, Nobukatsu Okuizumi, Yasutaka Satou, Junichiro Kawaguchi
    Journal of Spacecraft and Rockets 59(1) 295-311 2022年1月  
    A novel approach for shape control of membrane structures is presented to realize their use in three-dimensional and variable configurations. The shape control is accomplished by exciting a spinning membrane. The membrane forms a shape consisting of several vibration modes, depending on the input frequency, and the wave surface stands still when its frequency is synchronized with the spin rate; that is, the wave propagation and the spin cancel each other, resulting in a static wave surface in the inertial frame. This idea enables control of continuous membrane structures with large deformation using fewer actuators than conventional methods. This paper describes the general theory of the static wave-based shape control. The mathematical model of membrane vibration, the classification of control input, and the control system for exciting a static wave are summarized. The proposed method is demonstrated through a ground experiment. A 1 m large polyimide film is rotated and vibrated in a vacuum chamber, and the output shape is measured using a real-time depth sensor. It is shown that the observed shapes agree with numerical simulation results. An additional simulation that models the Japanese solar sail Interplanetary Kite-craft Accelerated by Radiation Of the Sun (IKAROS) demonstrates that the proposed method also works with a practically large-scalemembraneinthespaceenvironment.

MISC

 5
  • 前田康博, 佐藤泰貴, 石村康生
    構造強度に関する講演会講演集 65th 2023年  
  • 藤田和央, 大槻真嗣, 馬場満久, 佐藤泰貴, 上住昂生
    宇宙科学技術連合講演会講演集(CD-ROM) 66th 2022年  
  • Masaya Kurakawa, Osamu Mori, Nobukatsu Okuizumi, Yasutaka Sato, Yasuyuki Miyazaki, Hiraku Sakamoto, Yoshiki Sugawara, Kazuya Saito
    Advances in the Astronautical Sciences 166 365-370 2018年7月  
    © 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.
  • Rikushi Kato, Osamu Mori, Toshihiro Chujo, Yasutaka Sato, Nobukatsu Okuizumi, Hiroaki Tsunoda
    Advances in the Astronautical Sciences 166 349-364 2018年7月  
    © 2018 Univelt Inc. All rights reserved. Solar power sail technique was demonstrated in the IKAROS mission. However, unexpected phenomena were confirmed. The membrane surface of IKAROS has deformed to a shape that was not flat. In the shape change of the film surface, it is known that the whole membrane surface changes greatly like an umbrella shape or a saddle shape depending on the warping direction of the thin film solar cell. Objection of this study is to clarify mechanism of influence on solar radiation pressure torque due to warp of membrane device and its solution method. Therefore, the shape of the overall membrane surface is clarified by using a simple FEM model and the SRP torque with respect to the shape is calculated, and the mechanism of the overall shape change in warpage and its influence is clarified. As a result, the influence on SRP is related to membrane surface stiffness and warped direction and it was found that it is best that the membrane is warped in the radial direction and its outermost stiffness is high.
  • 稲守 孝哉, 菅原 佳城, 佐藤 泰貴, 大槻 兼資
    機械力学・計測制御講演論文集 2015 "419-1"-"419-11" 2015年8月25日  
    A varaety of satellites are presently utilizing deployable large area structures in orbit. As a novel deployment method for these structures, this study proposes a deployment and retracting method using an electromagnetic force for extensible panels on satellites. Using the proposed method, panels can be deployed quasi-statically to reduce the impulsive force exerted on fragile panels in the deployment. Furthermore, a satellite can also retract panels to a much smaller volume to avoid damage from space debris and achieve agile attitude maneuvers in small moment of inertia. Finally, to assess the proposed method, numerical simulations using multibody dynamics were conducted.

講演・口頭発表等

 156

共同研究・競争的資金等の研究課題

 9