排序方式: 共有6条查询结果,搜索用时 234 毫秒
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Masanori Matsushita Toshihiro Chujo Jun Matsumoto Osamu Mori Rikio Yokota Hiroyuki Toyota Yasutaka Satou Nobukatsu Okuizumi Hideki Kato Tetsuya Nakamura Yuichi Shibata Tatsuro Nakao Kazuyuki Mori Sanae Fujii Yuki Takao Yuki Kubo Yuya Miyamoto Yuichiro Nada Yudai Kimishima 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2021,67(9):2899-2911
This paper reports on the manufacturing and evaluation of a solar power sail membrane prototype for the OKEANOS project. The in-house prototype was built by the Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency. Mechanical and electrical evaluation tests were conducted. The membrane, thin-film solar cells, reflectivity control devices were good condition after the manufacturing and handling. The improvements in the manufacturing process and design were found. The manufacturing process and design were fundamentally established. After the prototype, improvement plans for the manufacturing process and design were tried. We have a prospect of manufacturing the flight model sail and continue to the development. 相似文献
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Sergey Verlinski ;Nimitt Patel ;Tyler Arsenault ;Philip Yuya ;Pier Marzocca 《南京航空航天大学学报(英文版)》2014,(2):169-174
Experimental investigations and associated methods are provided to characterize the mechanical properties of a lithium-ion battery accounting for operating temperature variation and thermal effects. Material properties for LiFeP04 cathode and anode samples taken from an off-the-shelf battery are evaluated in new and fatigued (subjec- ted to charging and discharging cycles) conditions. 相似文献
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Ryu Funase Yoji ShirasawaYuya Mimasu Osamu MoriYuichi Tsuda Takanao SaikiJun’ichiro Kawaguchi 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2011
This paper introduces a new attitude control system for a solar sail, which leverages solar radiation pressure. This novel system achieves completely fuel-free and oscillation-free attitude control of a flexible spinning solar sail. This system consists of thin-film-type devices that electrically control their optical parameters such as reflectivity to generate an imbalance in the solar radiation pressure applied to the edge of the sail. By using these devices, minute and continuous control torque can be applied to the sail to realize very stable and fuel-free attitude control of the large and flexible membrane. The control system was implemented as an optional attitude control system for small solar power sail demonstrator named IKAROS (Interplanetary Kite-craft Accelerated by Radiation Of the Sun). In-orbit attitude control experiments were conducted, and the performance of the controller was successfully verified in comparison with the ground-based analytical performance estimation. 相似文献
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The transient and thermo-electric finite element analysis (FEA) of a 2D lithium-on (Li-ion) battery is presented. The process of recharging and discharging of thin film lithium-ion (LiFePO4) battery in the presence of a transversal crack is numerically investigated. During this process significant temperature load influences the be- havior of the battery and thermal fields can affect the way crack propagates into the thin film media. The simula- tions infer about relationship between temperature and electric field and their effect on crack propagation. A Li-ion battery model suitable for this investigation is implemented in the multi-physics software package by COMSOL Inc. , and it is extended to include the thermal and electrical effects. Results and discussion are accompanied with pertinent conclusions. 相似文献
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Yuya Mimasu Tomohiro Yamaguchi Michihiro Matsumoto Masaki Nakamiya Ryu Funase Jun’ichiro Kawaguchi 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2011
The orbit of a solar sail can be controlled by changing the attitude of the spacecraft. In this study, we consider the spinning solar power sail IKAROS (Interplanetary Kite-craft Accelerated by Radiation Of the Sun), which is managed by Japan Aerospace Exploration Agency (JAXA). The IKAROS attitude, i.e., the direction of its spin-axis, is nominally controlled by the rhumb-line control method. By utilizing the solar radiation torque, however, we are able to change the direction of the spin-axis by only controlling its spin rate. With this spin rate control, we can also control indirectly the solar sail’s trajectory. The main objective of this study is to construct the orbit control strategy of the solar sail via the spin-rate control method. We evaluate this strategy in terms of its propellant consumption compared to the rhumb-line control method. Finally, we present the actual flight attitude data of IKAROS and the change of its trajectory. 相似文献
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