Gravity satellite formation orbital stability optimization design and earth gravity field precision inversion method

Abstract

The invention relates to a gravity satellite formation orbital stability optimization design and an earth gravity field precision inversion method on the basis of disturbing inter-satellite distance principle, in particular to an orbital stability optimization design method for a four-satellite system (FSS). In order to guarantee the stability of the four-satellite system, the quantity of satellite orbits is optimally designed, orbital semi-major axes, orbital eccentricities, orbital inclinations and right ascensions of ascending nodes keep unchanged, the difference of arguments of perigees each pair of satellites and the difference of mean anomalies of the pair of satellites are 180 degrees respectively, an initial argument of perigee of each satellite is arranged at the equator, an initial mean anomaly of each satellite is arranged at a pole, and the ratio of the semi-major axis of each elliptical orbit of the four-satellite system to a semi-minor axis of the elliptical orbit of the four-satellite system is 2:1. The gravity satellite formation orbital stability optimization design and the earth gravity field precision inversion method have the advantages that an earth gravity field is precisely and quickly inverted on the basis of a disturbing inter-satellite distance process; and the orbits are high in stability owing to the method, the earth gravity field computation precision is effectively improved, the gravity field inversion speed is increased to a great extent, and requirements on the performance of a computer are low.

Description

[0001] technical field [0002] The present invention relates to interdisciplinary technical fields such as space geodesy, satellite gravity, geophysics, and astronautics, and in particular to a four-satellite formation system (FSS: Four-Satellite System) orbit stability optimization design method, and then utilizes satellite Based on the inter-satellite distance of the laser interferometer, the satellite orbit position of the GPS receiver, and the satellite non-conservative force observation data of the accelerometer, the accuracy of the earth's gravity field is effectively improved based on the disturbance inter-satellite distance inversion method. [0003] Background technique [0004] This century is a new era in which satellite-to-Satellite Tracking in the High-Low / Low-Low mode (SST-HL / LL: Satellite-to-Satellite Tracking in the High-Low / Low-Low mode) is used to improve the cognitive ability of "Smart Earth". like figure 1 As shown, the successive successful launches ...

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Problems solved by technology

Although the stability of the overall system can be maintained through each satellite's own orbit and attitude thrus...

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