Electromagnetic panel deployment and retraction in satellite missions

被引：2
|
作者：
Inamori, Takaya [1 ]
Satou, Yasutaka [2 ]
Sugawara, Yoshiki [3 ]
Ohsaki, Hiroyuki [1 ]
机构：
[1] Univ Tokyo, SYS C, Expt Room Elect Energy Syst 2F, Kashiwa, Chiba 2778561, Japan
[2] Tokyo Inst Technol, Midori Ku, Yokohama, Kanagawa 2268502, Japan
[3] Akita Univ, Engn & Resource Studies, Akita 010, Japan
来源：
ACTA ASTRONAUTICA | 2015年 / 109卷
关键词：
Extensible structure; Deployment; Retraction; Electromagnetic force; FUROSHIKI SATELLITE; POWER; PROPULSION; GRAPHENE; SYSTEM;
D O I：
10.1016/j.actaastro.2014.11.035
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
An increasing number of satellites is presently utilizing extensible and deployable large area structures after launch, while in orbit. A deployment and retracting method using an electromagnetic force for extensible panels on satellites is proposed. Using the proposed method, a satellite can retract panels to a much smaller volume to avoid damage from space debris and achieve agile attitude maneuvers. Furthermore, panels can be deployed quasi-statically using electromagnetic forces to reduce the impulsive force exerted on fragile panels in the deployment operation. Finally, numerical simulations were conducted to assess the usefulness of the proposed method using multibody dynamics (MBD). From these simulations, the satellite can deploy 10 panels in 6000 s using 1 A current for a small cubic satellite of 20 cm dimension. Under the same conditions, the satellite can retract the 10 panels in 1400 s. (C) 2014 IAA. Published by Elsevier Ltd. All rights reserved.
引用
收藏
页码：14 / 24
页数：11
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