飞行器初始姿态校核方法、装置、设备及可读存储介质
By using the accelerometer of the aircraft's own inertial navigation system and the quaternion method, the problem of relying on external equipment for initial attitude verification of the aircraft was solved, realizing autonomous and accurate attitude verification and reducing costs and risks.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD
- Filing Date
- 2025-05-13
- Publication Date
- 2026-07-17
AI Technical Summary
The initial attitude verification of an aircraft before launch relies on external equipment, which is costly and risky. Existing methods are complex to operate and easily affected by the external environment.
By utilizing the aircraft's own inertial navigation system, the attitude is updated and accuracy is verified by calculating the pitch and roll angles of the aircraft from the accelerometer outputs, and then using the quaternion method and differential solution method. This includes multiple calculations and comparisons of attitude angles in both horizontal and vertical states to achieve autonomous verification.
It eliminates the need for external equipment, reducing costs and risks, simplifying operations, and improving the accuracy and efficiency of verification.
Smart Images
Figure CN120593739B_ABST