Method of reducing influences of gravity satellite centroid adjustment errors to earth gravitational field accuracy

Abstract

The invention discloses a method of reducing influences of gravity satellite centroid adjustment errors to earth gravitational field accuracy. The method is based on a novel disturbance energy theory, influences of gravity satellite centroid adjustment errors to earth gravitation potential coefficient accuracy are reduced effectively through a built gravity satellite centroid adjustment observation equation, and the earth gravitational field inversion with high accuracy and high spatial resolution is realized. The method is high in satellite gravity inversion accuracy, small in influences of centroid adjustment errors to gravitational field accuracy, easy to analyze satellite gravity system needs, clear in satellite observation equation physical meanings, and low in computer performance requirements. So the disturbance energy theory is an effective method of building a high accuracy and high spatial resolution earth gravitational field model.

Description

1. Technical field [0001] The present invention relates to satellite geodesy, satellite gravity, aerospace and other interdisciplinary technical fields, in particular to a method based on a novel disturbance energy principle, by establishing an observation equation for adjusting the center of gravity of gravity satellites, effectively reducing the impact of the adjustment error of the center of gravity of the gravity satellite on the gravitational position of the earth. The coefficient precision influences the method, and then inverts the Earth's gravity field with high precision and high spatial resolution. 2. Background technology [0002] Since the first artificial satellite Sputnik-1 was successfully launched on October 4, 1957, many scholars at home and abroad have made brilliant achievements in the precise detection of the earth's gravity field using satellite technology. The 21st century is a new era for human beings to use SST (Satellite-to-Satellite Tracking) and SG...

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Problems solved by technology

Second, on-orbit flight error sources: due to the complexity of the space environment (temperature, pressure, etc.), the deformation of the satellite in orbit and the real-time orbit and attitude control of the satellite cause jet fuel consumption (1 injection every 2 to 3 minutes) , each injection time is 200~300ms), which will cause real-time deviation of the center of mass of the GRACE satellite body and the on-board accelerometer inspection mass

The deviation of the center of mass of the GRACE star and accelerometer inspection mass and the introduction of satellite attitude measurement errors will inevitably add disturbance errors to the three-axis measurement of the accelerometer, thereby affecting the accuracy of the Earth's gravity field inversion

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