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Navigation satellite orbit extrapolation software design method

An orbit extrapolation and navigation satellite technology, applied in the field of navigation satellites, can solve the problems of difficulty in improving the stability of navigation satellites, and achieve the effects of stable and accurate real-time performance, improved accuracy and reliability.

Pending Publication Date: 2021-05-25
INNOVATION ACAD FOR MICROSATELLITES OF CAS +1
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Problems solved by technology

[0003] The purpose of the present invention is to provide a software design method for navigation satellite orbit extrapolation to solve the problem that the stability of existing navigation satellites is difficult to improve

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  • Navigation satellite orbit extrapolation software design method
  • Navigation satellite orbit extrapolation software design method
  • Navigation satellite orbit extrapolation software design method

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Embodiment Construction

[0141]The following is a further detailed description of the navigation satellite orbit extrapolation software design method proposed by the present invention in conjunction with the accompanying drawings and specific embodiments. Advantages and features of the present invention will be apparent from the following description and claims. It should be noted that all the drawings are in a very simplified form and use imprecise scales, and are only used to facilitate and clearly assist the purpose of illustrating the embodiments of the present invention.

[0142] In addition, unless otherwise stated, features in different embodiments of the present invention can be combined with each other. For example, a feature in the second embodiment may be used to replace a corresponding or functionally identical or similar feature in the first embodiment, and the resulting embodiment also falls within the scope of disclosure or description of the present application.

[0143] The core idea...

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Abstract

The invention provides a navigation satellite orbit extrapolation software design method. The method comprises the steps that: an orbit data preprocessing module receives measurement and control uploading orbit elements, navigation satellite ephemeris and celestial navigation attitude data to serve as orbit data to be calculated; the orbit data backup and recovery module is used for performing data backup on the measurement and control upper injection orbit elements; an orbit source preprocessing self-checking module performs self-checking on the to-be-calculated orbit data according to the checking codes and performs mutual checking on the to-be-calculated orbit data; an orbit self-diagnosis module selects measurement and control upper injection orbit elements, navigation satellite ephemeris or celestial navigation attitude data as orbit extrapolation calculation data according to an orbit self-diagnosis algorithm; an orbit extrapolation calculation module obtains real-time orbit data of the satellite by using the orbit extrapolation calculation data, and the real-time orbit data is used for closed-loop calculation of a satellite attitude control system; and an orbit source autonomous selection and switching module performs autonomous selection and switching of the orbit data to be calculated according to the orbit priority, the orbit switch state and the orbit data self-diagnosis result.

Description

technical field [0001] The invention relates to the technical field of navigation satellites, in particular to a software design method for navigation satellite orbit extrapolation. Background technique [0002] The main function of navigation satellites is to provide all-weather, high-precision navigation and timing services to global users, which has high requirements for service continuity. Maintaining the high-reliability satellite orbit of navigation satellites can not only ensure the attitude and pointing accuracy of navigation satellites, but also ensure the high-precision positioning of ground navigation receiving terminals. The stability of existing navigation satellites cannot fully meet the above requirements, so it is urgent to carry out research on methods to improve the stability of navigation satellites. Contents of the invention [0003] The purpose of the present invention is to provide a navigation satellite orbit extrapolation software design method to ...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/20G06F119/14
CPCG06F30/20G06F2119/14
Inventor 王正凯林夏贺芸王学良林宝军
Owner INNOVATION ACAD FOR MICROSATELLITES OF CAS
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