Abstract
The hybrid subsystem design could be an attractive approach for future spacecraft to cope with their demands. The idea of combining the conventional Attitude Control System and the Electrical Power System is presented in this article. The Combined Energy and Attitude Control System (CEACS) consisting of a double counter rotating flywheel assembly is investigated for small satellites in this article. Another hybrid system incorporating the conventional Attitude Control System into the Thermal Control System forming the Combined Attitude and Thermal Control System (CATCS) consisting of a fluid wheel and permanent magnets is also investigated for small satellites herein. The governing equations describing both these novel hybrid subsystems are presented and their onboard architectures are numerically tested. Both the investigated novel hybrid spacecraft subsystems comply with the reference mission requirements. The hybrid subsystem design could be an attractive approach for futurespacecraft to cope with their demands. The idea of combining theconventional Attitude Control System and the Electrical Power System ispresented in this article. The Combined Energy and Attitude ControlSystem (CEACS) consisting of a double counter rotating flywheel assemblyis investigated for small satellites in this article. Another hybrid systemincorporating the conventional Attitude Control System into the ThermalControl System forming the Combined Attitude and Thermal ControlSystem (CATCS) consisting of a fluid wheel and permanent magnets isalso investigated for small satellites herein. The governing equationsdescribing both these novel hybrid subsystems are presented and theironboard architectures are numerically tested. Both the investigated novelhybrid spacecraft subsystems comply with the reference missionrequirements.
Highlights
The requirements for the space missions in terms of their performances are gradually increasing
The novelty in this paper lies in the attitude performance comparison of the two novel hybrid subsystems for small satellites, i.e., the Combined Energy and Attitude Control System (CEACS) and the Combined Attitude and Thermal Control System (CATCS)
CATCS The Combined Attitude and Thermal Control System (CATCS) couples an existing onboard temperature gradient with the magnetohydrodynamic (MHD) effects for its operation
Summary
The requirements for the space missions in terms of their performances are gradually increasing. The novelty in this paper lies in the attitude performance comparison of the two novel hybrid subsystems for small satellites, i.e., the Combined Energy and Attitude Control System (CEACS) and the Combined Attitude and Thermal Control System (CATCS). 2.1 THE CEACS ONBOARD PERFORMANCES A reference mission is proposed for the numerical performance evaluation as follows: 100 kg satellite with 1 × 1 × 1 m3 of volume, 5 years of mission duration, a circular orbit at 500 km with an inclination of 53°, pitch axis attitude requirement < 0.2°, and 98 W of power requirement [4].
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