GNSS (Global Navigation Satellite System)-based Kalman relative positioning method

A relative positioning and relative position technology, applied in the field of satellite navigation, can solve the problems of reducing the real-time performance and reliability of the relative positioning system, low ambiguity floating point solution accuracy, and long ambiguity fixed time.

Active Publication Date: 2017-09-22
CHINESE AERONAUTICAL RADIO ELECTRONICS RES INST
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Problems solved by technology

[0005] (1) The commonly used Kalman filter adopts a uniform motion dynamic model. By setting a large dynamic noise to weaken the influence of the dynamic model on the navigation system under various uncertain motion conditions, only the measurement information is used for filter estimation , for uniform acceleration and variable acceleration motion carriers, it is difficult to build a precise dynamic model, which in turn brings a large relative positioning floating-point solution error
[0006] (2) The commonly used Kalman filtering method must rely on external sensors, such as inert

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  • GNSS (Global Navigation Satellite System)-based Kalman relative positioning method
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  • GNSS (Global Navigation Satellite System)-based Kalman relative positioning method

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[0036] In order to make the objectives, technical solutions and advantages of the present invention clearer, the following further describes the present invention in detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention, but not to limit the present invention. In addition, the technical features involved in the various embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0037] The following will be attached figure 1 And the technical scheme further describes the specific implementation process of the present invention in detail.

[0038] Step 1: Double difference carrier phase establishment

[0039] For receiver A to receive the s-th GNSS satellite, its pseudorange observations and carrier phase observations are:

[0040]

[0041]

[0042] Where They are the pseudo-rang...

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Abstract

The invention discloses a GNSS (Global Navigation Satellite System)-based Kalman relative positioning method. The method comprises steps: 1, a double difference carrier phase is built; 2, relative positioning of a triple difference carrier phase is carried out; 3, a Kalman filter dynamic model is improved adaptively; 4, the Kalman filter state is updated; 5, satellite geometrical configuration changes are processed; 6, Kalman filter measurement is updated; 7, integer ambiguity is solved; and 8, relative position information is outputted. The method is better adaptive to relative positioning of a variably accelerated motion carrier, the precision of ambiguity floating point solution and the integer ambiguity fixing success rate are improved, the initialization time of a relative positioning system is shortened, and the real-time performance and the reliability of relative positioning are enhanced.

Description

technical field [0001] The invention belongs to the technical field of satellite navigation, and more specifically relates to a relative positioning method based on satellite navigation. Background technique [0002] Global Navigation Satellite System (GNSS, Global Navigation Satellite System) is a comprehensive system that uses radio signals emitted by artificial earth satellites for navigation. The satellite navigation system that can provide navigation services on a global scale can provide users with global, all-weather, Real-time 3D navigation service. GNSS-based relative positioning is to install two sets of GNSS receivers and antenna equipment on two carriers respectively, receive GNSS measurement information at the same time, and transmit the GNSS measurement information received by one carrier to the other carrier in real time through the communication data link. In the computer equipment, the relative position information between the two carriers can be obtained b...

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Application Information

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IPC IPC(8): G01S19/44
CPCG01S19/44
Inventor 魏华波庞瑞帆张展宇王洋张小清
Owner CHINESE AERONAUTICAL RADIO ELECTRONICS RES INST
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