一种双周期姿态预估及修正的时序设计方法
By employing a timing design method for dual-cycle attitude prediction and correction, the problem of mismatched data update frequencies between gyroscopes and star sensors in the satellite attitude control system was solved, achieving a balance between high-precision attitude measurement and the main mission, and improving the efficiency and accuracy of the satellite attitude control system.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- BEIJING INST OF CONTROL ENG
- Filing Date
- 2023-01-10
- Publication Date
- 2026-07-17
AI Technical Summary
In existing technologies, satellite attitude control systems struggle to balance high-precision attitude measurement and main task completion under high-maneuver conditions, especially when the gyroscope data update frequency is high in short cycles while the star sensor data update frequency is low. This results in complex timing design and an inability to meet high-frequency communication requirements.
A timing design method for dual-cycle attitude prediction and correction is adopted, which divides the timing of gyroscope attitude prediction and star sensor attitude correction into M control cycles. The interrupt method is used to perform gyroscope data processing and attitude prediction in the short cycle, and star sensor data update and attitude correction in the long cycle. The interrupt handling function is used to achieve efficient use of data.
It improves the utilization efficiency of gyroscope data update frequency, enhances the accuracy of star attitude measurement, ensures high-frequency and high-precision updates of high-frequency attitude data, and adapts to the data update rate of star sensors to meet high-frequency communication requirements.
Smart Images
Figure CN116409472B_ABST