A configuration design method for satellite solar wings that meets the requirements of payloads for sun observation

Abstract

The invention relates to a design method of a satellite solar wing configuration to meet the requirement of payload observation to the sun. The method comprises the following steps: 1, analyzing the field of view requirements of payload observation to the sun, and determining the field of view envelope of payload according to the payload working mode; 2, analyze that arrangement requirements of the solar fin in-orbit state, and determining the relative positional relationship between the solar fin and the satellite body according to the variation of the solar illumination angle; 3, analyze that restriction requirements of the carry rocket on the satellite outline size, and determining an optional arrangement form of the load and the solar wing launch state according to the outline state ofthe satellite body; Step 4, according to the constraint conditions determined in the above three steps, embedding the payload solar observation field into the solar wing, defining the layout positionof the payload and the solar wing on the satellite body, and forming a satellite solar wing configuration satisfying the payload solar observation demand. The invention breaks through the functionallimitation that the solar fin is only used for supplying power to the satellite, and enables the solar fin to give consideration to the function of allowing the sunlight to pass through the solar finso as to load the solar observation.

Description

technical field [0001] The invention relates to the technical field of satellite overall design, in particular to a configuration design method of a satellite solar wing that meets the requirements of payloads for sun observation. Background technique [0002] With the development of satellite technology, users have more and more urgent needs for satellites to monitor solar activities. Therefore, satellites need to be loaded with sun observation loads on the basis of loading earth observation loads. [0003] In traditional satellite configuration design, the arrangement of the solar wing is usually first determined according to the characteristics of orbital illumination, and then the layout design of the load is carried out. The failure to coordinate the configuration design of the solar wing and the load often leads to insufficient compactness of the satellite layout, and the longitudinal center of mass Height, weight and other issues. Contents of the invention [0004]...

AI Technical Summary

Problems solved by technology

[0003] In traditional satellite configuration design, the arrangement of the solar wing is usually first determined according to the characteristics of orbital illumination, and then the layout design of the load is carried out. The failure to coordinate the configuration design of the solar wing and the load often leads to insufficient compactness of the satellite layout, and the longitudinal center of mass Height, heavy weight and other issues

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