Shadow Analysis Method of Earth-Moon L2 Point Halo Orbit Based on Ephemeris Model

Abstract

The invention discloses an ephemeris model-based method for analyzing the shade of an earth-moon L2 point Halo orbit, and belongs to the technical field of aerospace. The method comprises the steps of building a kinetic equation under a restricted three-body model formed by the earth, the moon and the planet and generating the Halo orbit near an L2 point under an earth-moon rotation system; selecting on-orbit time th and a corresponding task moment T within a Halo orbit period and converting the Halo orbit under a rotary coordinate system into an inertia system; judging the shielding conditions of the earth and the planet on the satellite by using a conical shadow model according to the sun-earth-planet relative position and the sun-moon-planet relative position under an inertia coordinate system; changing the task moment T, and calculating the sun-earth-planet relative position and the sun-moon-planet relative position, carrying out shadow analysis by using the conical shadow model again until the orbit is completed; and changing the on-orbit time th of the Halo orbit, repeating the analysis, and calculating the shadow distribution conditions at different positions. The real degree is high, and the shadow analysis consideration is more comprehensive.

Description

technical field [0001] The invention is a shadow analysis method of the Halo orbit of the Earth-Moon L2 point based on an ephemeris model, which is suitable for analyzing the shadow distribution of the Halo orbit of the Earth-Moon L2 point at different times and phases in a real ephemeris environment, and belongs to aerospace technology field. Background technique [0002] The periodic orbit near the L2 point of the earth and the moon has unique dynamic characteristics. The satellites in the Halo orbit near the L2 point have the advantages of a relatively fixed position relationship with the moon, a long visible time with the earth, and a small cost for orbit maintenance. Ideal mission orbit for following satellites. The illumination condition of the satellite is one of the important constraints in the orbit design of the relay mission. The design of the satellite power supply system is affected by the length of the occlusion time. Longer shadows will lead to insufficient b...

AI Technical Summary

Problems solved by technology

Although this method can analyze the periodic orbit shadow of the Earth-Moon L2 point, its dynamic model is still a circular restricted three-body model, which does not consider the influence of the real ephemeris environment; in addition, the lunar occultation zone The analysis model is a simplified model, and the shadow analysis does not consider the occlusion effect of the earth

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