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- Title
Attitude control of a spacecraft during an orbital maneuver for fast rejection of large disturbance torque without using the reaction control system.
- Authors
Kouhi, H.
- Abstract
During an impulsive orbital maneuver, thrust vector misalignment from the Center of Mass (CM) generates a large exogenous disturbance torque that results in attitude deviation. This paper aims to eliminate the need for application of Reaction Control System (RCS) for spacecraft attitude control. In order to reject large disturbance very fast, a new control system is proposed. In this method, the large disturbance torque is rejected quickly without using RCS. The control system is based on one Degree of Freedom (1DoF) gimbaled-thruster, spin-stabilization, and two Control Moment Gyros (CMG). The nonlinear two-body dynamics of the mentioned spacecraft is formulated. Given that RCS is not used, this method is an efficient and implementable one for attitude control of a small spacecraft. Numerical simulation shows that thrust vector deviation converges to zero despite disturbance torques. Through this method, the disturbance is rejected very fast, hence an accurate orbital velocity change can be obtained. This method can eliminate the initial attitude deviation easily and overcome disturbance rejection. The results exhibited the good performance and superiority of the proposed method compared to some other thrusting maneuver methods.
- Subjects
TORQUE; COMPUTER simulation; TEMPERATURE; KINEMATICS; FREE precession
- Publication
Scientia Iranica. Transaction B, Mechanical Engineering, 2022, Vol 29, Issue 2, p597
- ISSN
1026-3098
- Publication type
Article
- DOI
10.24200/sci.2021.56648.4835