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Spaceborne GPS Orbit Determination Method Based on Adaptive Measurement Noise Variance Estimation

A technique for measuring noise and variance estimation, applied in the field of spaceborne GPS orbit determination

Active Publication Date: 2018-05-01
WENZHOU UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] In order to overcome the problem of the traditional KF orbit determination method in random model parameter values, the present invention proposes a spaceborne GPS orbit determination method based on Adaptive Measurement Noise Variance Estimation (AMNVE), which can According to the receiver carrier noise ratio (Carrier Noise Ratio, C / N 0 ) adaptively adjusts R, so that it can better reflect the noise statistical characteristics of the measured value, and can obtain higher orbit determination accuracy

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  • Spaceborne GPS Orbit Determination Method Based on Adaptive Measurement Noise Variance Estimation

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Embodiment

[0127] Take the Level 1B data of the GRACE A satellite from January 5th to 6th, 2008 as an example. The data includes L1, L2 dual-frequency pseudo-range measurements and signal-to-noise ratio data collected by the on-board GPS receiver. The AMNVE method proposed by the invention and the traditional EKF algorithm are used to estimate the orbit of the GRACE A satellite in real time, and the result is compared with the post-event precision ephemeris to obtain its orbit determination accuracy.

[0128] Depend on Figure 4 , 5 , 6, it can be seen that the traditional EKF algorithm has errors of 0.93m, 1.27m and 0.83m in the radial direction, tangential direction and normal direction, while the errors of the AMNVE method proposed by the present invention in the three directions are 0.78m, 0.97m and 0.68m , decreased by 16%, 23% and 18% respectively; by Figure 7 It can be seen that the 3D positioning error has dropped from 1.78m to 1.42m, a reduction of 20%. In the traditional EK...

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Abstract

The invention discloses a satellite-borne GPS orbit determination method based on self-adaptive measurement noise variance estimation. (2) According to the tracking loop C / N0 of each channel, calculate the pseudo-range measurement error of the L1, L2 dual-frequency signal; (3) combine the L1, L2 dual-frequency pseudo-range measurement value to obtain The pseudo-range measurement value ρIF of the ionospheric delay and its error σIF; (4) Taking ρIF as the observation quantity, the EKF algorithm is used to estimate the orbit information of the satellite. This method adaptively adjusts the variance matrix of the measurement noise by monitoring the change of the signal carrier-to-noise ratio of each channel of the satellite-borne GPS receiver in real time, so that it can correctly reflect the statistical characteristics of the noise of the observation, and overcomes the problem of the traditional fixed design EKF algorithm with insufficient prior information. The deficiencies in the full and dynamic environment can obtain higher orbit determination accuracy.

Description

technical field [0001] The invention relates to a satellite-borne GPS orbit determination method, in particular to a satellite-borne GPS orbit determination method based on adaptive measurement noise variance estimation. Background technique [0002] With the development of the Global Positioning System (GPS), a new way is provided for spacecraft navigation and orbit determination. Compared with traditional ground-based orbit determination, spaceborne GPS can provide more accurate and continuous navigation and orbit determination services. Therefore, spaceborne GPS technology has gradually become an effective way to determine the orbit of low-orbit satellites. [0003] At present, according to whether the dynamic information of low-orbit satellites is used or not, spaceborne GPS orbit determination is mainly divided into the following three types: 1) Geometric method, which directly uses the pseudorange information of the spaceborne GPS receiver for positioning calculation, ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01S19/37
CPCG01S19/37
Inventor 李理敏林宇豪肖洋曾国强陈孝敬阮秀凯张威
Owner WENZHOU UNIV
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