Interplanetary transfer orbit design method

Abstract

The invention relates to an interplanetary transfer orbit design method, in particular to a transfer orbit design method from a periodical orbit which is near dynamic balance points of a three-body system to a small celestial body and belongs to the technical field of aerospace. Firstly, based on the periodical orbit which is near the dynamic balance points of the three-body system where a detector is located, an initial state of the detector x0=[ r0, v0] is assumed. Secondly, a speed increment delta v is exerted along a tangential direction so that the detector sets off from the periodical orbit near the dynamic balance points. Based on a multiple-body model, relations between the detector and a distance df of the detector and the target small celestial body, a flying period tf and the tangential direction speed increment delta v are built up when the detector flies across the target small celestial body is built. Through an optimizing algorithm, an initial value of the transfer orbit is obtained when the fight distance df is minimum. Finally, a secondary-level differential correction method is used based on the initial value to obtain orbit parameters which can meet two point boundary values. The interplanetary transfer orbit design method can achieve rapid design of flight from the periodical orbit which is near the dynamic balance points of the three-body system to the small celestial body, calculation amount is small and efficiency is high.

Description

technical field [0001] The invention relates to a method for designing an interstellar transfer orbit, in particular to a method for designing a transfer orbit from a periodic orbit near a dynamic balance point of a three-body system to a small celestial body, and belongs to the technical field of aerospace. Background technique [0002] Transfer orbit design is a key technology in the design of interstellar exploration missions. There are not many orbit design methods that use the dynamic balance point of the earth-sun or earth-moon system to transfer to the asteroid near the earth, and there are only prior technologies [1] (see R.W.Farquhar, D.W.Dunham et al.Utilization of libration points for human exploration in the Sun-Earth-Moon system and beyond.Acta Astronautica.2004,55:687-700) proposed a transfer orbital design method based on the stable and unstable manifolds of the periodic orbits at the dynamic equilibrium points of the three-body system , and apply this method...

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Problems solved by technology

[0003] The purpose of the present invention is to propose a transfer orbit design method for flying from a periodic orbit near the dynamic equilibrium point of the three-body system to a small celestial body in order to overcome the defects of the existing design methods that are missing solutions and cannot provide a launch window

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