Solar sail attitude control using small reaction wheels and magnetic torquers

被引：16
作者：
Polites, M. [1 ]
Kalmanson, I. [1 ]
Mangus, D. [2 ]
机构：
[1] Orbital Sci Corp, Space Syst Grp, Dulles, VA 20166 USA
[2] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA
来源：
PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART G-JOURNAL OF AEROSPACE ENGINEERING | 2008年 / 222卷 / G1期
关键词：
interplanetary travel; solar sail; solar radiation pressure; attitude control; reaction wheels; magnetic torquers;
D O I：
10.1243/09544100JAERO250
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
The current paper describes an attitude control system that uses small reaction wheels and magnetic torquers to control the attitude of a large flexible solar sail in low-Earth orbit (LEO). This system is being proposed for the NASA New Millenium Programme Space Technology-9 solar sail technology demonstration mission. Controlling the attitude of a solar sail with these actuators in LEO was previously considered difficult and thus never proposed before. What makes it possible is choosing the right orbit and judiciously constraining the attitude of the solar sail in that orbit. Simulation results are presented that validate this design approach for solar sail attitude control in LEO.
引用
收藏
页码：53 / 62
页数：10
相关论文
共 34 条
[1]  
ALEXANDER A, 2004, PLANETARY NEWS 0810
[2]  
COHREN D, 2002, SSCO22D UT STAT U
[3]  
COLOMBO G, 1996, TR665 MIT CSR
[4]   ATTITUDE CONTROL OF A SUN-POINTING SPINNING SPACECRAFT BY MEANS OF SOLAR RADIATION PRESSURE [J].
CROCKER, MC .
JOURNAL OF SPACECRAFT AND ROCKETS, 1970, 7 (03) :357-&
[5]  
Diedrich B. L., 2001, THESIS U WASHINGTON
[6]   SPACE TELESCOPE POINTING CONTROL-SYSTEM [J].
DOUGHERTY, H ;
TOMPETRINI, K ;
LEVINTHAL, J ;
NURRE, G .
JOURNAL OF GUIDANCE CONTROL AND DYNAMICS, 1982, 5 (04) :403-409
[7]  
FRIEDMAN LD, 1988, STAR SAILING SOLAR S
[8]  
GARWIN RL, 1958, JET PROPULSION, V28, P188
[9]  
*GOODR OPT SPAC, 2001, GOODR TORQR TR SER
[10]  
*GOODR OPT SPAC SY, 2001, GOODR TORQWH TW SER
1234