Method and device for calibrating attitude parameters of airborne inertial navigation system

Abstract

The invention discloses an attitude parameter calibration method and an attitude parameter calibration device of an airborne inertial navigation system. A high-dynamic star sensor is used as a data acquisition method and fixed stars are used as measuring objects; the plurality of fixed stars on a celestial sphere are detected, and start point positioning, star map identification and attitude calculation are carried out to provide attitudes of the star sensor relative to an inertial reference system; then, airplane attitude standard data under an inertial navigation coordinate system is obtained according to a conversion relation between a star sensor coordinate system and the inertial navigation coordinate system; finally, the standard data is used as reference and is compared with the attitude data of the inertial navigation system, so that the dynamic online calibration of the attitude precision of the inertial navigation system is realized under an airborne environment.

Description

technical field [0001] The invention belongs to the technical field of navigation attitude parameter calibration, and in particular relates to an airborne inertial navigation system attitude parameter calibration method and device. Background technique [0002] The inertial navigation system is an autonomous navigation system that does not rely on external information and does not radiate energy to the outside. It has good concealment and is not affected by external electromagnetic interference. In the field of aviation, it is an indispensable navigation system for various aircraft, and its attitude accuracy performance is crucial to aircraft navigation, so the attitude accuracy of the inertial navigation system must be calibrated. Like other airborne equipment, the inertial navigation system must be tested under real flight conditions, so as to provide a technical basis for the design finalization / certification of the new inertial navigation system. However, for a long time...

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Problems solved by technology

The ground turntable test can perform high-precision calibration of the inertial navigation system. However, in practice, the aircraft is affected by weather, airflow, etc., causing the inertial navigation system to work in a complex dynamic environment. This use environment is quite different from the laboratory calibration platform environment. discrepancies, thereby affecting the reliability of laboratory calibration results

[0004] The star sensor uses the star in the celestial inertial coordinate system as a reference, and outputs the absolute attitude information of the carrier in the inertial space. It has the characteristics of no drift and high precision. However, when used in aircraft airborne equipment, the aircraft has strong maneuverability , due to the long exposure time of the traditional star sensor, the phenomenon of imaging spot smearing occurs, resulting in a decrease in the positioning accuracy of the star point, and in serious cases, the attitude cannot even be output

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