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Method for calculating solar radiation pressure moment of navigation GEO satellite

A technology of solar radiation and radiation pressure, used in computing, special data processing applications, instruments, etc., and can solve problems such as the angle of the northward bias of the S/L antenna that is not considered.

Active Publication Date: 2014-07-23
BEIJING INST OF SPACECRAFT SYST ENG
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Problems solved by technology

[0005] The calculation of the solar radiation pressure of the first-generation navigation GEO satellite takes into account factors such as the shape of the satellite, the optical properties of the surface material, and the shading between components, but does not take into account the northward bias angle of the S / L antenna

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  • Method for calculating solar radiation pressure moment of navigation GEO satellite
  • Method for calculating solar radiation pressure moment of navigation GEO satellite
  • Method for calculating solar radiation pressure moment of navigation GEO satellite

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Embodiment Construction

[0058] refer to figure 1 Shown flow chart, the concrete steps of the inventive method are as follows:

[0059] The first step is to obtain the input conditions. The input conditions required for the calculation mainly include: satellite configuration, geometric dimensions, and satellite surface characteristic parameters; satellite barycenter position; solar wing position, size, and surface characteristic parameters; S / L antenna position geometric dimensions and surface characteristic parameters. Prepare for pressure moment;

[0060] The second step is to calculate the radiation pressure moment of the sun on each panel of the star body according to the satellite configuration, geometric size, satellite mass center and satellite surface characteristic parameters. There is occlusion between the east panel of the star and the S / L antenna. In order to consider the influence of occlusion, the micro-element The division method is used to calculate the radiation pressure moment of t...

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Abstract

The invention discloses a method for calculating the solar radiation pressure moment of a navigation GEO satellite. The method comprises the following steps of (1) acquiring an input bar, (2) calculating the radiation pressure moment to a satellite body of the sun, (3) calculating the radiation pressure moment to a solar wing of the sun, (4) calculating the radiation pressure moment to an S / L antenna of the sun, (5) conducting Fourier fitting on the radiation pressure moment to the satellite body, the radiation pressure moment to the solar wing and the radiation pressure moment to the antenna to obtain Fourier fitting coefficients of solar radiation pressure moment. The Fourier fitting coefficients of the solar radiation pressure moment are used for conducting overall satellite design, according to the shape of the navigation GEO satellite and the optical property of surface materials, the sheltering factors and the like between parts are considered, the angle of the S / L antenna tilting northwards is considered, meanwhile, a model is established according to the meshed S / L antenna, the solar radiation pressure moment of the navigation GEP satellite is calculated, and the precision of the calculating result of the solar navigation pressure moment of the navigation GEO satellite is guaranteed.

Description

technical field [0001] The invention belongs to the field of aerospace vehicle design and relates to a calculation method for the solar radiation pressure moment of a navigation GEO satellite. Background technique [0002] Satellite navigation has been widely used because of its advantages such as large coverage area, long operating distance, and little damage from natural disasters. Since GEO satellites can cover fixed areas, my country has been applied in regional constellations. The solar radiation pressure is the main interference force during the long-term working period after the navigation GEO satellite is fixed, and its force causes the satellite orbital eccentricity to change in a long period. When the pressure center corresponding to the solar radiation pressure is inconsistent with the center of mass of the satellite, the solar radiation pressure moment will be generated, which is the most important disturbance moment affecting the satellite attitude movement. T...

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Application Information

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IPC IPC(8): G06F19/00
Inventor 高照照杨慧王东张云彤李美红郝文宇陈闽
Owner BEIJING INST OF SPACECRAFT SYST ENG
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