Structure layout parameter determination method of agile satellite

Abstract

A structure layout parameter determination method of an agile satellite comprises two parts of solar panel layout parameter optimization and star sensor layout parameter optimization. An optimization goal of the solar panel layout parameter optimization is set as an energy generation value of each track of a solar panel, bounded variables of the optimization goal are track parameters, attitude parameters and solar panel effective charging conditions, and variable parameters are solar panel installation angles. Optimal values of the solar panel installation angles are determined by mathematical solution. An optimization goal of the star sensor layout parameter optimization is set as a star sensor available time period, bounded variables of the optimization goal are track parameters and attitude parameters, and variable parameters are star sensor installation angles. The star sensor installation angles are iteratively computed by mathematical solution, and an available time period optimal value of each track of a star sensor can be obtained. The structure layout parameter determination method can maximumly improve application effectiveness of the agile satellite under the premise of satisfaction of a working mode of the agile satellite and a satellite mission application mode.

Description

technical field [0001] The invention belongs to the field of satellite overall design, and relates to a method for determining satellite structure layout parameters. Background technique [0002] The design of the agile small satellite platform emphasizes high functional density ratio and high performance. Therefore, the research on the optimal design method of the agile small satellite platform, especially the research on the overall parameter optimization design, is very important for improving the performance and functional density ratio of the agile small satellite platform. is of great significance. [0003] The overall optimization design of the agile small satellite platform is mainly to solve the contradiction between the two requirements of high-quality and high-efficiency applications. In particular, agile small satellites emphasize improving the application efficiency of satellites, which requires system-level optimization design for satellite system material flo...

AI Technical Summary

Problems solved by technology

[0007] The problem solved by the technology of the present invention is: to overcome the problems in the prior art that the installation parameters of the fixed solar wing are not conducive to the acquisition of energy and the layout parameters of the star sensor cannot ensure that at least one is available during the satellite attitude maneuvering process, and provide an agile The method of determining the structural layout parameters of the satellite can complete the design of the high functional density ratio of the agile small satellite, and solve the coupling contradiction between the attitude maneuver of the agile satellite, energy guarantee and high-quality and high-efficiency imaging

Images