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Adaptive filtering-based spacecraft guidance instrument on-orbit calibration method

A space vehicle, adaptive filtering technology, applied in the direction of instruments, measuring devices, etc., can solve the problem that the error coefficient cannot meet the aircraft, and achieve the effect of overcoming the inconsistency of heaven and earth, simple algorithm, and easy engineering.

Inactive Publication Date: 2017-07-28
BEIJING AEROSPACE AUTOMATIC CONTROL RES INST
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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

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  • Adaptive filtering-based spacecraft guidance instrument on-orbit calibration method
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[0031] In order to make the object, technical solution and advantages of the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings and examples.

[0032] Aiming at the deficiency of "inconsistency between heaven and earth" in the existing guidance tool error separation technology, the present invention proposes a space vehicle guidance tool on-orbit error separation method based on adaptive filtering. The invention uses the carrier position and attitude output by the strapdown inertial navigation and the attitude matrix output by the star sensor to construct the measurement and establish the measurement equation. An adaptive filtering algorithm is designed, and the estimated value of the random constant drift of the gyroscope and the installation error of the star sensor is obtained through filtering calculation, so as to realize the on-orbit self-calibration of the combined system.

[0033] The p...

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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...

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Application Information

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IPC IPC(8): G01C25/00
CPCG01C25/005
Inventor 李超兵王晋麟肖称贵李学锋禹春梅祁琪徐帆徐国强
Owner BEIJING AEROSPACE AUTOMATIC CONTROL RES INST
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