Strict regression orbit design method considering high-order gravity field

A technology of return orbit and design method, applied in the aerospace field, can solve problems such as only considering the influence of the earth's non-spherical gravitational J2 perturbation

Active Publication Date: 2019-10-25
SHANGHAI JIAO TONG UNIV
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Problems solved by technology

[0003] At present, most of the studies on the return orbit design only consider the perturbation effect of the J2 term of the Earth's non-spherical gravity

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  • Strict regression orbit design method considering high-order gravity field
  • Strict regression orbit design method considering high-order gravity field
  • Strict regression orbit design method considering high-order gravity field

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Embodiment Construction

[0214] The present invention will be described in detail below in conjunction with specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be pointed out that for those of ordinary skill in the art, several changes and improvements can be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0215] According to the present invention, a strict regression orbit design method considering high-order gravity field includes:

[0216] The initial design steps of the satellite orbit: consider the overall input of the satellite orbit design, including the number of return days and return cycles. 2 Analytical design of regression orbit parameters affected by perturbation, the analytical design results are obtained, and the analytical design results are differentially corrected by Ne...

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Abstract

The invention provides a strict regression orbit design method and system considering a high-order gravity field and a medium. The method comprises the following steps: a satellite orbit initial design step: performing regression orbit parameter analysis design considering J2 perturbation influence according to satellite orbit design overall input including a regression day number and a regressioncircle number to obtain an analysis design result, and performing differential correction on the analysis design result through a Newton iteration method to obtain J2 perturbation satellite orbit initial design initial values; a strict regression orbit design step: combining a Newton iteration method with a multi-objective optimization algorithm NSGA-II according to obtained strict regression orbit optimization design initial value..Through a regression orbit hybrid optimization design algorithm under a high-precision gravity field, rapid optimization design of a strict regression orbit is realized. Compared with an existing method, a more accurate dynamic environment is considered, the regression precision can be greatly improved, and the application requirement of a synthetic aperture radar interferometry system is met.

Description

Technical field [0001] The present invention relates to the field of aerospace technology, in particular to a strict regression orbit design method considering the high-order gravitational field of the earth. Background technique [0002] Regression orbit refers to a special type of orbit in which the sub-satellite point track repeats after a period of time, and the distance between adjacent tracks on the same latitude circle is the same. The return orbit can meet the task requirements of periodic dynamic observation of specific ground targets. At present, it has been widely used in tasks such as earth imaging observation and earth science exploration. In particular, the strict regression characteristics of satellite orbits ensure the application and implementation of a new type of space technology such as synthetic aperture radar interferometry (InSAR). The InSAR satellite system needs to obtain the phase difference and spatial distance difference caused by two observations of...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F2119/06G06F30/20
Inventor 邵晓巍张德新蒲明珺李鹏宇陈小平陈重华孙然
Owner SHANGHAI JIAO TONG UNIV
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