Method for determining gravitational field model based on gravity satellite inter-satellite laser ranging system

A laser ranging and gravitational field technology, applied in the field of satellite gravity detection, can solve problems such as poor calculation accuracy, low measurement accuracy, and large observation noise

Active Publication Date: 2020-07-03
EAST CHINA UNIV OF TECH
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Problems solved by technology

[0003] At present, when determining the gravitational field model, the conventional method is to use high-low satellite tracking satellite technology inversion method, but the accuracy of this method is poor, the high-frequency error is amplified, and the observation noise is large, so the measurement accuracy is low

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Embodiment 1

[0084] Such as figure 1 As shown, a method for determining the gravitational field model based on the gravitational satellite intersatellite laser ranging system provided by the present invention comprises the following steps:

[0085] Step 1: Data Preprocessing

[0086] The data source adopts GRACE-Follow On gravity satellite data, and the collected data information includes gravity double star orbit, inter-satellite laser ranging system, on-board accelerometer and its attitude and other data.

[0087] The original observations of the intersatellite laser ranging system need to be corrected geometrically and light-time;

[0088] The gravitational double star orbit requires gross error detection and elimination;

[0089] Attitude data needs to be linearly interpolated;

[0090] The gravitational binary star orbit data, the on-board accelerometer and its attitude data need to be time-synchronized with the observation data of the inter-satellite laser ranging system.

[0091...

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Abstract

The invention relates to a method for determining a gravitational field model based on a gravity satellite inter-satellite laser ranging system, and belongs to the technical field of satellite gravitydetection. The method comprises the following steps: acquiring an original data set; preprocessing the original data set to obtain a sight line direction acceleration value, a sight line direction combined observation value and an inter-satellite acceleration residual error; establishing an observation equation based on the line-of-sight direction acceleration value, the line-of-sight direction combined observation value and the inter-satellite acceleration residual error; and solving an observation equation, and solving a gravitation potential spherical harmonic coefficient. According to themethod, the inter-satellite distance, the change rate of the inter-satellite distance and the inter-satellite acceleration are obtained on the basis of a gravity satellite inter-satellite laser ranging system, an observation equation is established according to the Newton's second law of motion, and finally the gravitation potential spherical harmonic coefficient is estimated through least squares. Compared with a classic high-low satellite tracking satellite technology inversion method, the method does not need numerical value micro-decomposition calculation, and can effectively avoid high-frequency error amplification, thereby improving the gravitational field model calculation precision.

Description

technical field [0001] The invention belongs to the technical field of satellite gravity detection, in particular to a method for determining a gravitational field model based on a gravity satellite intersatellite laser ranging system. Background technique [0002] The gravitational field is a theoretical model that describes the mutual attraction effect between space objects. Due to the uneven distribution of data inside the earth, it is not a force field that changes according to a simple law. Therefore, it is important to study the fine structure of the gravitational field and build a high-precision gravitational field model It is one of the main scientific tasks of related disciplines. [0003] At present, when determining the gravitational field model, the conventional method is the inversion method using high-low satellite tracking satellite technology, but this method has poor calculation accuracy, amplifies high-frequency errors, and has large observation noise, so t...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01V7/00
CPCG01V7/00
Inventor 吴汤婷卢立果鲁铁定王建强陈本富
Owner EAST CHINA UNIV OF TECH
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