一种确定箭体惯组自对准精度的方法、装置、介质及设备
By determining the coordinate transformation matrix and attitude angles of the inertial navigation system (INS), the accuracy of the INS is calibrated, solving the problem of the inability to verify the self-alignment accuracy of the INS and ensuring the accuracy and efficiency of rocket launches.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- AEROSPACE SCI & IND KET TECH CO LTD
- Filing Date
- 2024-01-02
- Publication Date
- 2026-07-17
AI Technical Summary
Existing technologies cannot effectively verify the accuracy of inertial navigation systems with self-alignment capabilities, affecting the efficiency of frequent rocket launches.
By determining the reference coordinate transformation matrix between the reference inertial group and the inertial group to be calibrated, the initial azimuth angle is obtained using optical aiming, and the self-alignment accuracy of the inertial group to be calibrated is calculated, including obtaining the projection and unit vector of gravitational acceleration in different coordinate systems, determining the attitude angle using the Euler angle rotation matrix, and back-calculating the actual azimuth angle of the reference inertial group to calibrate the accuracy of the inertial group to be calibrated.
Accurately determining the self-alignment accuracy of the inertial navigation system to be calibrated ensures the accuracy and efficiency of rocket launches and avoids yaw problems caused by inertial navigation system errors.
Smart Images
Figure CN117870722B_ABST