Attitude maneuver of spacecraft with a variable-speed double-gimbal control moment gyro

被引：28

作者：

Jikuya, Ichiro ^{[1
]}

Fujii, Kenta ^{[2
]}

Yamada, Katsuhiko ^{[3
]}

机构：

[1] Kanazawa Univ, Fac Elect & Comp Engn, Kanazawa, Ishikawa 9201192, Japan

[2] Mitsubishi Electr Corp, Adv Technol R&D Ctr, 8-1-1 Tsukaguchi Honmachi, Amagasaki, Hyogo 6618661, Japan

[3] Osaka Univ, Dept Mech Engn, 2-1 Yamadaoka, Suita, Osaka 5650871, Japan

来源：

ADVANCES IN SPACE RESEARCH | 2016年 / 58卷 / 07期

关键词：

Spacecraft; Attitude control; Variable-speed double-gimbal control moment gyro; Attitude maneuver; Time trajectory; FEEDBACK-CONTROL; GYROSCOPES; SYSTEM;

D O I：

10.1016/j.asr.2016.06.010

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

In this paper, two types of computational procedures are presented for a rest-to-rest spacecraft maneuver using a variable-speed double-gimbal control moment gyro (VSDGCMG). The first procedure is a numerical computational procedure in which a quasi time-optimal trajectory satisfying several physical constraints is obtained by repeating the Newton's method. The other procedure is an approximate computational procedure in which an analytical solution is obtained by approximately solving a series of linear optimal control problems. The two procedures play complementary roles: the former is suitable for implementation, and the latter can be used to select an initial value for use in the former. The effectiveness of the proposed procedures is demonstrated by plotting the surfaces of maneuvering time for all rotational axes and by plotting time responses for several maneuvering examples. (C) 2016 COSPAR. Published by Elsevier Ltd. All rights reserved.

引用

页码：1303 / 1317

页数：15

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