Satellite orbit transformation method and device, electronic equipment and storage medium

An orbit conversion and satellite orbit technology, which is applied in the aerospace field and can solve the problems of complex satellite orbit conversion methods and low solution efficiency.

Pending Publication Date: 2021-10-22
陕西星邑空间技术有限公司
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Problems solved by technology

[0003] The embodiments of the present disclosure provide a satellite orbit transformation method, device, electronic equipment and storage medium, w

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  • Satellite orbit transformation method and device, electronic equipment and storage medium
  • Satellite orbit transformation method and device, electronic equipment and storage medium
  • Satellite orbit transformation method and device, electronic equipment and storage medium

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[0139] Reference will now be made in detail to the exemplary embodiments, examples of which are illustrated in the accompanying drawings. When the following description refers to the accompanying drawings, the same numerals in different drawings refer to the same or similar elements unless otherwise indicated. The implementations described in the following exemplary examples do not represent all implementations consistent with the present disclosure. Rather, they are merely examples of apparatuses and methods consistent with aspects of the present disclosure as recited in the appended claims.

[0140] figure 1 It is a flow chart of a satellite orbit transformation method provided by an embodiment of the present disclosure. Such as figure 1 As shown, the method includes:

[0141] S101. Obtain the target velocity increment and target yaw angle required for a single transformation of the satellite from the initial orbit to the target orbit, where the initial orbit is the apog...

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Abstract

The invention provides a satellite orbit transformation method and device, electronic equipment and a storage medium, relates to the field of aerospace, and can solve the problems that the satellite orbit transformation method is relatively complex and low in solving efficiency. According to the satellite orbit transformation method, the method comprises the steps of obtaining a target speed increment and a target yaw angle required by a satellite for single transformation from an initial orbit to a target orbit; according to the target speed increment, the target yaw angle and the orbital transformation frequency n, determining the optimal speed increment delta vi and the optimal yaw angle beta i of the satellite in each orbital transformation from the initial orbit to the target orbit through n times of orbital transformation, n is an integer larger than 1, and i is an integer larger than 0 and smaller than or equal to n; according to the delta vi and the rocket thrust F, determining the ignition moment tidev and the orbital transfer ignition duration delta ti of the satellite during orbital transfer each time; and performing orbit transformation on the satellite according to the beta i, the tidev and the delta ti. According to the method, the satellite orbit transformation strategy can be obtained through optimization and accurate calculation, and the solving efficiency is improved.

Description

technical field [0001] The present disclosure relates to the field of aerospace, and in particular to a satellite orbit changing method, device, electronic equipment and storage medium. Background technique [0002] Due to the limitation of the thrust of the rocket, the synchronous satellite usually can only enter the initial orbit of a large ellipse with a certain inclination angle after launch, and then the satellite's own engine will change the orbit multiple times to transfer the satellite from the initial orbit to the geosynchronous orbit. In the prior art, it is usually necessary to plan and establish a numerical optimization model based on the orbit parameters of the initial satellite orbit and various constraints, and then determine the fuel-optimized multiple satellite orbit transformation strategy according to the numerical optimization model. Since the satellite engine itself is a continuous thrust, if the numerical optimization model is directly established, the ...

Claims

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Application Information

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IPC IPC(8): B64G1/24
CPCB64G1/242
Inventor 车征韩晓妮
Owner 陕西星邑空间技术有限公司
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