Mars global remote sensing orbit design method and system based on near fire point drift

Abstract

The invention provides a Mars global remote sensing orbit design method and system based on near fire point drift, and relates to the technical field of orbit design of deep space exploration spacecrafts, and the method comprises the steps: S1, determining a near fire point height upper limit, and enabling the near fire point height at the end of life to be greater than the fire atmosphere height; S2, calculating a track inclination angle adjusting range; S3, calculating the argument change rate of the near fire point; S4, calculating the right ascension change rate of the ascending node; and S5, analyzing and calculating orbit semi-major axis parameters according to parameters of a near fire point argument change rate and an ascending node right ascension change rate required by a remote sensing detection task. According to the invention, the requirements of low-orbit target imaging and high-orbit ground communication can be met; the emission weight of the deep space detector is saved; and the engineering task requirements of global coverage, full-range coverage detection of different orbit heights and detailed detection of key areas can be met.

Description

technical field [0001] The invention relates to the technical field of orbit design of deep space exploration spacecraft, in particular to a Mars global remote sensing orbit design method and system based on near-fire point drift. Background technique [0002] Remote sensing detection of extraterrestrial planets by deep space probes is an important scientific task in the field of deep space exploration. Compared with earth remote sensing satellites that usually work in near-earth circular orbits or geostationary orbits, deep-space probes are limited by weight, and maneuvering to lower circular orbits consumes a lot of fuel, so they cannot maneuver to low-altitude circular orbits. In addition, in order to cover the detection requirements of different orbital heights of target celestial bodies, remote sensing detection missions are usually carried out on large elliptical orbits. In the task arrangement, the detectors conduct fire observation near the fire point, and communica...

AI Technical Summary

Problems solved by technology

This study pointed out the design ideas and calculation constraints for the Mars orbit design, but in the field of deep space remote sensing exploration, the orbit needs to meet the mission conditions such as global coverage and sub-satellite point revisiting, and the frozen orbit is suitable for the needs of relay communication tasks. Meet the needs of remote sensing detection

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