Synchronous orbit star group multi-target observation orbit plane common path design method

A public path and synchronous orbit technology, applied in the field of satellite observation, can solve the problems of short observation time, missed effective observation opportunities of target stars, and low efficiency of observation and imaging, so as to save fuel consumption and improve the effective observation coverage of targets

Pending Publication Date: 2022-08-09
CHINA XIAN SATELLITE CONTROL CENT
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Problems solved by technology

In practical engineering applications, if the above-mentioned conventional observation path design idea is adopted, during the observation of the target star with a large orbital inclination angle, due to the high norm

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  • Synchronous orbit star group multi-target observation orbit plane common path design method
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  • Synchronous orbit star group multi-target observation orbit plane common path design method

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Embodiment Construction

[0057] Example embodiments will now be described more fully with reference to the accompanying drawings. Example embodiments, however, can be embodied in various forms and should not be construed as limited to the examples set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the concept of example embodiments to those skilled in the art. The described features, structures, or characteristics may be combined in any suitable manner in one or more embodiments.

[0058] Furthermore, the drawings are merely schematic illustrations of embodiments of the present disclosure and are not necessarily drawn to scale. The same reference numerals in the drawings denote the same or similar parts, and thus their repeated descriptions will be omitted. Some of the block diagrams shown in the figures are functional entities that do not necessarily necessarily correspond to physically or logically separate entities...

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Abstract

The invention relates to a synchronous orbit star group multi-target observation orbit plane common path design method. The method comprises the following steps: acquiring orbit ephemeris of n target stars of a synchronous orbit star group and an initial orbit ephemeris of an observation satellite; establishing an observation orbital plane common path model of the observation satellite, and forming an objective function model formula of the observation orbital plane common path of the observation satellite through a plurality of observed quantities; establishing a preset iterative algorithm model, and traversing and solving extreme points of the objective function model; setting a threshold value epsilon (1) of a preset iterative algorithm model; and when the extreme point of the objective function model formula is less than or equal to a threshold value epsilon, operation is stopped, and the optimal common path of the observation orbit surface is obtained. According to the embodiment of the invention, one-time orbital plane control is adopted, and an invariable observation plane public path is established, so that node single-satellite multi-batch orbital plane control is avoided while the maximum effective observation of the observation target is met, and the fuel consumption is greatly saved.

Description

technical field [0001] The embodiments of the present disclosure relate to the technical field of satellite observation, and in particular, to a method for designing a common path of an orbital plane for multi-object observation of a constellation constellation in a synchronous orbit. Background technique [0002] The geosynchronous orbital belt (GEO orbital belt for short) refers to a 360° annular belt with a width of 22077km within a range of ±15° inclination near 35785km above the Earth's equator. The dynamic characteristics of the geosynchronous orbital belt endow it with good coverage stability relative to the surface, that is, the satellites in the orbital belt have the same or similar characteristics as the earth's rotation angular velocity, and the satellites in the orbital belt are stationary relative to the ground when viewed from the ground. , so that the satellites arranged in this orbital belt can stare at the fixed area on the ground 24 hours a day without inte...

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Application Information

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IPC IPC(8): G06F30/15G06F30/20G06F119/20
CPCG06F30/15G06F30/20G06F2119/20
Inventor 边宝刚王鼎蔚王小乐方东银炜李园敏王鑫郭明玮
Owner CHINA XIAN SATELLITE CONTROL CENT
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