A method for on-orbit calibration of space vehicle guidance tools based on adaptive filtering

Abstract

The invention discloses an adaptive filtering-based spacecraft guidance instrument on-orbit calibration method. According to the method, carrier position and attitude output by a strapdown inertial navigation device and an attitude matrix output by a star sensor are used for construction and measurement, and a measurement equation is built. A self-adaptive filtering algorithm is designed and estimated values of gyroscope random constant drift and star sensor installation error are acquired through filtering calculation so that combined system on-orbit self-calibration is realized. The method solves the problem that the existing guidance tool error separation technology causes misalignment of the spacecraft in the sky and ground coordinates, realizes real-time on-orbit calibration of an error coefficient of the guidance tool, utilizes a simple algorithm and is easy to project.

Description

technical field [0001] The invention relates to the field of space vehicle navigation and control, in particular to an on-orbit calibration method for space vehicle guidance tools based on adaptive filtering. Background technique [0002] The inertial instrument is the heart of the strapdown inertial navigation system, and its error will directly affect the spacecraft's orbital accuracy and landing point deviation. The on-orbit calibration of error coefficients of SINS guidance tools is an important means to improve the navigation accuracy of spacecraft, and the core of error coefficient separation work is the research of parameter estimation methods. At present, the ground calibration method of the inertial system is relatively mature, but when the inertial system is actually applied to the flight mission, the error coefficient of the ground calibration due to the vibration of the aircraft and the change of the space environment cannot meet the requirements of the long-term...

AI Technical Summary

Problems solved by technology

At present, the ground calibration method of the inertial system is relatively mature, but when the inertial system is actually applied to the flight mission, the error coefficient of the ground calibration due to the vibration of the aircraft and the change of the space environment cannot meet the requirements of the long-term flight of the aircraft and spacecraft in space. positioning requirements

Images