Periodic orbit escape method by utilizing near-earth-moon balance points

Abstract

The invention discloses a periodic orbit escape method by utilizing near-earth-moon balance points, and belongs to the technical field of aerospace. The implementation method comprises the following steps: establishing an earth-moon rotating coordinate system and three-body dynamics, and solving a state transition matrix characteristic root and a characteristic vector of a periodic orbit; formingan unstable manifold through a periodic orbit near the balance point, selecting the unstable manifold close to the moon, solving deorbiting maneuver through differential correction, obtaining a transfer orbit meeting the requirement of the near-moon point constraint, and enabling the detector to apply corresponding maneuver to enable the detector to be transferred to the near-moon point. Near-moonpoint maneuver is solved through differential correction, a moon-ground transfer orbit meeting near-site constraints is obtained, the application maneuver makes full use of the gravitation effect ofthe moon, and the detector applies corresponding maneuver to transfer the detector to a near site. According to the escape speed requirement, the detector applies maneuver on the near site again, theapplied maneuver fully utilizes the earth-moon gravitation effect, and the speed increment of the detector escaping from the periodic orbit to the earth-moon system is reduced.

Description

technical field [0001] The invention relates to a method for escaping from a periodic orbit of a balance point close to the Earth and the Moon, and is especially suitable for orbit selection and escape velocity evaluation methods for escaping from the Earth starting from the L2 point orbit of the Earth and the Moon, and belongs to the field of aerospace technology. Background technique [0002] The L2 point of the Earth-Moon balance point has good dynamic characteristics, and is suitable for deploying a relay star for relay communication and data transmission between the probe on the back of the moon and the Earth. Departing from orbit to escape from the earth for deep space exploration requires less fuel consumption than directly departing from earth orbit, so it can also be used as a parking orbit for space stations or probes. In order to realize the deep space exploration starting from the balance point periodic orbit, it is necessary to design the escape orbit. [0003]...

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Problems solved by technology

[0004] Prior art [2] (see: Nakamiya M, Yamakawa H, Scheeres D J, et al. Interplanetary transfers between halo orbits: connectivity between escape and capture trajectories [J]. Journal of guidance, control, and dynamics, 2010, 33(3) :803-813.) studied the transfer orbit using the escape of the unstable manifold at the equilibrium point, but the escape efficiency of this method is low, and the fuel consumption increases significantly with the increase of the required escape velocity

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