Doppler Positioning Calculation Method for LEO Satellite Backup Navigation System

A low-orbit satellite, positioning and solving technology, applied in the field of Doppler positioning and solving, to achieve the effects of high use value, improved positioning accuracy, and low computational complexity

Active Publication Date: 2019-02-15
NO 54 INST OF CHINA ELECTRONICS SCI & TECH GRP
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Problems solved by technology

[0009] According to the above-mentioned background technology, in order to solve the continuous positioning and solving problem of the low-orbit satellite backup navigation system under the condition of adapting to the number of different visible stars, the present invention provides a Doppler algorithm combining grid search and Newton least squares iterative calculation. Lex location solution method

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  • Doppler Positioning Calculation Method for LEO Satellite Backup Navigation System
  • Doppler Positioning Calculation Method for LEO Satellite Backup Navigation System
  • Doppler Positioning Calculation Method for LEO Satellite Backup Navigation System

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Embodiment Construction

[0048] Below in conjunction with specific embodiment and accompanying drawing, the present invention will be further described:

[0049] Doppler positioning calculation method for low-orbit satellite backup navigation system. This method uses Doppler observation information and real-time ephemeris information of one or more low-orbit navigation satellites to realize ground static or low dynamic user positioning calculation. The specific implementation Steps such as figure 1 Shown, it is characterized in that comprising the following steps:

[0050] Step 1: According to the number of satellites visible to different users, obtain the satellite three-dimensional position, three-dimensional velocity and Doppler frequency observations required for positioning calculation at the same time or at different times;

[0051] Step 2: Calculate the Doppler positioning residual value based on the satellite's three-dimensional position, three-dimensional velocity and Doppler frequency obse...

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Abstract

The invention discloses a Doppler positioning solution method for a low-orbit satellite backup navigation system. The method is a combination of large-area grid search coarse positioning and Newton least squares iterative calculation applicable to any number of visible stars. Combined Doppler positioning solution method. The present invention mainly includes the following three aspects: 1. The method is suitable for a variety of visible star observation conditions through flexible selection of positioning solution observations; The initial position value of the method is determined; 3. The Newton least squares iterative calculation method is used to realize the Doppler positioning solution, and the positioning accuracy is further improved by the multi-epoch positioning solution result smoothing method after removing outliers. The invention can realize large-area high-precision Doppler positioning solution under the conditions of multiple different numbers of low-orbit visible stars, and has low calculation amount and high positioning accuracy.

Description

technical field [0001] The invention relates to a Doppler positioning solution method for a low-orbit satellite backup navigation system, in particular to a Doppler positioning solution that is applicable to large-area grid search coarse positioning and Newton least squares iterative calculation that is applicable to any number of visible stars method. Background technique [0002] A large number of low-cost navigation terminals without special anti-jamming measures will not be able to work in the complex electromagnetic interference environment of the GNSS navigation system. In the north and south polar regions, due to the low inclination design of the GNSS system constellation, the coverage is greatly reduced. Therefore, building a GNSS backup radio navigation system is an important way to improve the availability of GNSS navigation systems. [0003] Low-orbit satellites have the characteristics of wide coverage, all-weather work, and good observability. Micro-nano satell...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01S19/42
CPCG01S19/42
Inventor 邓志鑫范广伟何成龙
Owner NO 54 INST OF CHINA ELECTRONICS SCI & TECH GRP
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