Method for determining sheltering of solar cell array during in-orbit running of satellite and application of method

A solar battery array and a technology to determine the method, which is applied to the power supply system of aerospace vehicles, etc., can solve problems such as abnormal charging array current, achieve the effects of improving utilization efficiency, broad application prospects, and improving rationality

Active Publication Date: 2014-08-13
SHANGHAI SATELLITE ENG INST
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Problems solved by technology

[0005] In order to study the situation that the solar cell array is blocked by the stars when the satellite is in orbit, the present invention provides a method for determining the solar cell array is blocked by the stars when the satellite is in orbit Abnormal charging array current and other problems

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  • Method for determining sheltering of solar cell array during in-orbit running of satellite and application of method
  • Method for determining sheltering of solar cell array during in-orbit running of satellite and application of method
  • Method for determining sheltering of solar cell array during in-orbit running of satellite and application of method

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Embodiment Construction

[0037] The embodiments of the present invention are described in detail below. This embodiment is implemented on the premise of the technical solution of the present invention, and detailed implementation manners and specific operation procedures are given, but the protection scope of the present invention is not limited to the following embodiments.

[0038] The present invention combines a certain satellite for analysis. The satellite is a sun-synchronous orbit satellite, which uses a three-axis stable ground attitude control method. The annual average change of the satellite orbit illumination angle is like image 3 As shown, the change of the sun’s elevation angle with latitude during the orbit of the satellite is as Figure 4 Shown.

[0039] The satellite solar cell array has a double-wing configuration, with 3 pieces per wing, each with an area of ​​1.7m×1.4m (1.4m is the unfolding direction). When launching, the two-wing solar cell arrays are respectively condensed on the ±...

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Abstract

The invention relates to a method for determining the sheltering of a solar cell array during the in-orbit running of a satellite and the application of the method. The method comprises the following steps of: making researches on solar illumination angle annual average change rules of a satellite orbit and the conditions of change of solar elevation along with the latitude during the in-orbit running of the satellite, judging whether the solar cell array of the satellite is sheltered or not by star, combining the configuration characteristics of the satellite, calculating a sheltered area, and obtaining the change trends of the sheltered area within one orbit and a year, so that the problem of abnormal charging array current caused by the sheltering of the solar cell array during the in-orbit running of the satellite can be solved according to results, and the problem of the optimal design of a cell distribution mode for solar cells of the satellite is also solved. The configuration design rationality of a spacecraft such as the satellite adopting the solar cell array as a main energy supply is improved, the utilization efficiency of the solar cells is improved, and good effects are achieved. The application has the advantages of lowering the cost of the cells of the spacecraft, improving the effective power supply capability of the spacecraft, improving the performance of the spacecraft, and the like.

Description

Technical field [0001] The invention relates to a spacecraft overall design technology, in particular to a method for determining the obstruction of a satellite solar cell array in orbit and its application. Background technique [0002] For spacecraft that use solar arrays as their main energy supply, such as satellites, solar arrays are an important component and the only source of energy required for the spacecraft's maneuvering orbit change and normal operation of a single plane. The solar array can convert sunlight energy into electrical energy, ensuring the daily operation of the spacecraft. The main factors affecting energy supply are the photoelectric conversion efficiency of solar cells, the angle of sunlight, and the effective illumination area of ​​the solar cell array. [0003] After a satellite enters orbit, it is found that the current of the +Y-wing solar array charging array is significantly lower than the design value, and the -Y-wing solar array charging array cu...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/44
Inventor 韩旭侯建文杨珺马文佳
Owner SHANGHAI SATELLITE ENG INST
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