Method for analysis and computation of illumination on spacecraft lunar orbits

Abstract

The invention provides a method for analysis and computation of illumination on spacecraft lunar orbits. The method comprises the steps that epoch moments are set, and the position of sun and lunar orbit elements are computed; according to the lunar orbit elements, a first conversion matrix from an earth core equator inertial system to a lunar core equator inertial system is computed; according to the first conversion matrix, a second conversion matrix from the lunar core equator inertial system to an observation coordinate system is computed; a first true anomaly is recorded and taken as a track simulation initial point used for computation of stay duration of different lunar orbits in a shadow area; and the first true anomaly is used for track simulation, and a satellite eclipse factor and an illumination factor are computed, so illumination conditions on the different lunar orbits are analyzed. Hence, with the method for analysis and computation of illumination on the spacecraft lunar orbits provided by the invention, computation is simpler and more flexible; computation results are more accurate; internal relations between the lunar orbit illumination conditions and lunar orbit parameters can be analyzed conveniently; scene setting is simple; and workloads are reduced greatly.

Description

technical field [0001] The invention relates to the technical field of spacecraft overall design and illumination condition analysis, and more specifically, to a method for analyzing and calculating illumination of a spacecraft orbiting around the moon. Background technique [0002] When a spacecraft is in orbit, its main energy comes from sunlight. When the spacecraft is in the illuminated area, the solar energy can be converted into electrical energy through the solar wings; when the spacecraft is in the shadow area, it needs to be powered by its own battery. Therefore, the analysis and calculation of the illumination conditions of the spacecraft is the basis for the design of the energy subsystem scheme. Not only that, the illumination conditions of the spacecraft have a direct impact on the temperature of its structure, the perturbation by the solar light pressure, and the optical observation of the spacecraft on the ground. [0003] In the prior art, most illumination...

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Problems solved by technology

[0005] (1) The kernel algorithm has strong encapsulation, and it is not easy to learn and master the calculation principle of lighting conditions;

[0006] (2) When analyzing the influence of orbital parameters on the illumination conditions, it is necessary to set up multiple circumlunar orbit spacecraft. The scene setting is complex and the workload is heavy, which is not conducive to the analysis of the internal relationship between the orbital illumination conditions and the parameters of the circumlunar orbit; as well as

[0007] (3) The calculation of the illumination factor is carried out in the form of orbital simulation, and there may be discontinuities in the illumination area, which is not convenient for calculating and counting the illumination conditions in a single orbital period, and the calculation flexibility is poor

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