Spacecraft Line of Sight Maneuver Control Using Skew-arrayed Two Single-Gimbal Control Moment Gyros
نویسندگان
چکیده
منابع مشابه
Spacecraft Angular Velocity and Line-of-Sight Control Using A Single-Gimbal Variable-Speed Control Moment Gyro
It is well known that complete attitude control of a spacecraft is not possible with only one single-gimbal Variable-Speed Control Moment Gyro (VSCMG) due to the conservation of the angular momentum. However, partial attitude control without violating the angular momentum conservation principle is still possible. In this paper, feedback controllers that stabilize the angular velocity vector of ...
متن کاملSpacecraft Line-of-Sight Control Using a Single Variable-Speed Control Moment Gyro
Complete attitude control of a spacecraft is not possible with only one single-gimbal variable-speed control moment gyro due to the conservation of angular momentum. However, partial attitude control without violating the angular momentum conservation principle is still possible. In this paper feedback controllers using only one singlegimbal variable-speed controlmoment gyro are presented that ...
متن کاملAttitude-Tracking Control with Path Planning for Agile Satellite Using Double-Gimbal Control Moment Gyros
In view of the issue of rapid attitude maneuver control of agile satellite, this paper presents an attitude-tracking control algorithm with path planning based on the improved genetic algorithm, adaptive backstepping control as well as sliding mode control. The satellite applies double gimbal control moment gyro as actuator and is subjected to the external disturbance and uncertain inertia prop...
متن کاملSpacecraft Angular Velocity Stabilization Using A Single-Gimbal Variable Speed Control Moment Gyro
Feedback controllers for the stabilization of the angular velocity vector of a rigid spacecraft using a single-gimbal Variable Speed Control Moment Gyro (VSCMG) are presented. Linearization of the equations of motion show that complete attitude stabilization is not possible via linear methods. Nonetheless, it is shown that the linearized angular velocity equations are controllable, and a simple...
متن کاملAttitude Dynamics/Control of Dual-Body Spacecraft with Variable-Speed Control Moment Gyros
The dynamics equations of a spacecraft consisting of two bodies mutually rotating around a common gimbal axis are derived by the use of the Newton–Euler approach. One of the bodies contains a cluster of single-gimbal variable-speed control moment gyros. The equations include all of the inertia terms and are written in a general form, valid for any cluster configurations and any number of actuat...
متن کاملذخیره در منابع من
با ذخیره ی این منبع در منابع من، دسترسی به آن را برای استفاده های بعدی آسان تر کنید
ژورنال
عنوان ژورنال: TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN
سال: 2016
ISSN: 1884-0485
DOI: 10.2322/tastj.14.pd_31