Sun-synchronous circular orbit satellite sun exposure factor calculation method, device and electronic equipment

A circular orbit and sun technology, applied in the aerospace field, can solve the problems of complex calculation process, high requirements for designers, and long calculation time, and achieve the effect of fast and accurate calculation

Active Publication Date: 2022-03-11
成都国星宇航科技股份有限公司
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Problems solved by technology

[0004] This application provides a sun-synchronous circular orbit satellite sun exposure factor calculation method, device and electronic equipment to solve the complex calculation process of the sun-synchronous circular orbit satellite sun exposure factor calculation process in the prior art, the calculation takes a long time, and the requirements for designers are relatively high. high problem

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  • Sun-synchronous circular orbit satellite sun exposure factor calculation method, device and electronic equipment
  • Sun-synchronous circular orbit satellite sun exposure factor calculation method, device and electronic equipment
  • Sun-synchronous circular orbit satellite sun exposure factor calculation method, device and electronic equipment

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Embodiment approach

[0058] In one embodiment, the preset orbital inclination can be determined according to the pre-acquired orbital height and semi-major axis of the sun-synchronous circular orbit satellite: i represents the orbital inclination, h represents the orbital height, and a e represents the semi-major axis of the orbit, then the orbital inclination can be obtained by the following formula:

[0059]

[0060] Among them, acos represents the arc cosine function, and the orbit height h is numerically equal to the semi-major axis of the orbit minus the radius of the earth, indicating the distance between the orbit of a planet or various aircraft and the surface of the central celestial body.

[0061] In order to facilitate understanding, based on the right ascension of the ascending node of the sun-synchronous circular orbit satellite at the preset time and the preset orbital inclination, the process of obtaining the normal vector of the satellite's orbital plane, the following uses i to ...

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Abstract

The application provides a sun-synchronous circular orbit satellite sun exposure factor calculation method, device and electronic equipment, which belong to the field of aerospace technology. The method includes: obtaining the equatorial vector of the sun in the equatorial coordinate system at a preset time, and obtaining the The normal vector of the satellite orbit plane where the sun-synchronous circular orbit satellite is located in the equatorial coordinate system, the equatorial vector is the unit vector pointing from the origin of the equatorial coordinate system to the center point of the sun at the preset moment; based on the normal vector and the equatorial vector, the satellite orbit is obtained The angle between the plane and the equator vector; based on the angle and the pre-acquired semi-major axis of the orbit of the sun-synchronous circular orbit satellite, the sun exposure factor of the sun-synchronous circular orbit satellite is obtained. This method does not need to calculate the orbit forecast of the sun and the satellite, nor does it need to calculate the time when the satellite enters and exits the earth's shadow, thereby simplifying the calculation process of the sun exposure factor of the sun-synchronous circular orbit satellite, shortening the calculation time, and reducing the requirements for designers.

Description

technical field [0001] The present application relates to the field of aerospace technology, in particular, to a method, device and electronic equipment for calculating the sun exposure factor of a sun-synchronous circular orbit satellite. Background technique [0002] Calculation and analysis of satellite insolation factor is an essential part of satellite orbit design, which provides a basis for the design of solar panels and on-board power supplies. The current sun exposure factor calculation method is to calculate the orbit based on the real satellite orbit and the position of the sun, and calculate the satellite sun exposure according to the ratio of each satellite entering and leaving the earth shadow (the earth's shadow, that is, the shadow cast by the earth itself on the atmosphere) factor. [0003] However, this method not only needs to calculate the orbit forecast of the sun and satellite based on information such as satellite orbit and sun position (same as the c...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/10
CPCG06F17/10
Inventor 赵宏杰陆川金勇
Owner 成都国星宇航科技股份有限公司
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