The high dynamic and long-endurance movement characteristics of the aerospace vehicles may cause installation error angle between the star sensors and the inertial navigation system in the integrated inertial/celestial integrated navigation system.In this paper, a method for dynamic identification of the installation error angle of a star sensor is designed, the installation error angle model of the star sensor is established, a dynamic identification scheme of the installation error angle of the star sensor based on astronomical angle observation is designed, and the observability of the sensor installation error angle under different maneuvering modes are analyzed.The simulation results show that the designed dynamic identification method based on Kalman filter can quickly calibrate the installation error angle of the star sensor during the maneuver of the aircraft, and the calibration value of the installation error angle can reach 85% of the actual error value. The accuracy of the integrated navigation system is effectively improved.
This article establishes a Kalman filtering model for inertial/astronomical integrated navigation based on altitude and azimuth observations. Through the model, it can be seen that there is a coupling relationship between the mathematical platform error angle of inertial navigation and the installation error angle of star sensors. A filtering model is established to estimate the installation error angle of star sensors through observations. This article designs a dynamic calibration scheme for the installation error of star sensors. Based on the constructed error calibration model, a Kalman filter is used to calibrate the installation error of star sensors in real-time. The simulation results show that this scheme can accurately and quickly estimate the installation errors in three axes in real-time, and the output accuracy of the integrated navigation system has been significantly improved after correction. This proves that the real-time correction algorithm for star sensitive installation errors proposed in this paper can significantly improve the output accuracy of the inertial/celestial integrated navigation system. In addition to theoretical analysis, it is still necessary to combine actual inertial navigation and star sensor measurement data to conduct experimental verification and analysis of the designed scheme algorithm, in order to achieve its engineering value.
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