Lunar orbit light condition analytical method

Abstract

The invention provides a lunar orbit light condition analytical method which comprises the steps that an epoch moment is set, and a sun position and a lunar orbit element are computed; according to the lunar orbit element, a first transferring matrix from a geocenter equator inertial system to a selenocenter equator inertial system is computed; according to the first transferring matrix, a second transferring matrix from the selenocenter equator inertial system to an observing coordinate system is computed; a first true anomaly is recorded and is used as an orbit simulation initial point for computing time of different lunar orbits at a shadow zone; and the first true anomaly is used for carrying out orbit simulation, an eclipse factor and a lighting factor are computed, and accordingly light conditions on different lunar orbits are analyzed. Therefore, according to the lunar orbit light condition analytical method, computing is easy and flexible, the computing results are accurate, the inner relation between the lunar orbit light conditions and lunar orbit parameters can be analyzed conveniently, scene setting is easy, and workload is greatly lowered.

Description

technical field [0001] The invention relates to the technical field of spacecraft overall design and illumination condition analysis, and more specifically, relates to a method for analyzing illumination conditions of a spacecraft flying in orbit 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 il...

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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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