基于三个控制力矩陀螺的斜置帆板卫星长期对日控制方法
By using a configuration and attitude calculation method based on three control moment gyroscopes, long-term solar orientation control of an inclined solar panel satellite was achieved, solving the problem that traditional methods are not applicable, reducing overall satellite power consumption and improving energy supply.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- SHANGHAI AEROSPACE CONTROL TECH INST
- Filing Date
- 2024-02-02
- Publication Date
- 2026-07-17
AI Technical Summary
Traditional methods of sun-oriented control are not suitable for obliquely mounted solar panels and cannot achieve long-term sun-oriented control.
Using a simplified configuration of three control moment gyroscopes, a solar inertial coordinate system is established by using the fixed inertial frame vector and the solar vector to determine the solar orientation attitude. The control moment gyroscopes are then installed along different axes to calculate the three-axis command torque and command speed for attitude control, thereby achieving long-term solar orientation of the inclined solar panel.
It enables solar pointing at the sun with solar panels at any angle, reduces the overall power consumption of the satellite, solves the problem of long-term solar orientation control for satellites with inclined solar panels, and alleviates the energy shortage in inclined orbits.
Smart Images
Figure CN118145017B_ABST