A Calibration Method of Spaceborne Accelerometer Based on Atmospheric Physical Mechanism

Abstract

The invention relates to a method for calibrating a spaceborne accelerometer based on an atmospheric physical mechanism, belonging to the technical field of satellite gravity detection, comprising the following steps: collecting an original data set; preprocessing the original data set to obtain non-conservative force observations and non-conservative forces Physical model value; build a calibration model based on non-conservative force observations and non-conservative force physical model values; solve the calibration model to obtain the full matrix solution of the scale factor and deviation parameters. The invention can effectively avoid the coupling phenomenon of accelerometer calibration parameters and gravity field related parameters caused by the simultaneous solution method of satellite precise orbit determination and gravity field modeling, and at the same time, it does not require prior information constraints, and the calibration step size is refined and the parameter estimation is comprehensive, thereby improving the accuracy of the satellite. Load accelerometer calibration performance. Compared with the same solution method, the algorithm principle proposed by the present invention is simple and efficient, the parameter estimation is comprehensive, and the practicability is strong, which is worthy of promotion.

Description

technical field [0001] The invention belongs to the technical field of satellite gravity detection, and in particular relates to a method for calibrating an on-board accelerometer based on an atmospheric physical mechanism. Background technique [0002] The on-board accelerometer is the key equipment for separating conservative force and non-conservative force in satellite gravity measurement. The quality of its data directly affects the accuracy of the satellite orbit and the final gravity field model. Real-time changes lead to bias terms in the accelerometer observations, so the onboard accelerometer needs to be calibrated. [0003] Using the same solution method is to simultaneously calculate the accelerometer calibration parameters, the satellite orbit and the Earth’s gravity field parameters in the process of satellite precise orbit determination and gravity field inversion. Since there is no direct standard value, the satellite orbit is usually used as an indirect stan...

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Problems solved by technology

[0003] Using the same solution method is to simultaneously calculate the accelerometer calibration parameters, the satellite orbit and the Earth’s gravity field parameters in the process of satellite precise orbit determination and gravity field inversion. Since there is no direct standard value, the satellite orbit is usually used as an indirect standard, causing The mutual coupling between the accelerometer calibration parameters and the relevant parameters of the gravitational field; in addition, prior information constraints need to be considered; at the same time, the mathematical model formula is complex, and the variational equation needs to be solved, which requires high computing resources and time-consuming calculation; in addition, the calibration model scale Factor simplification only considers diagonal arrays and monthly step calculations, resulting in limited calibration accuracy and efficiency of onboard accelerometers

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