Design method for low-energy transit among interplanetary fixed orbits based on invariant manifold

Abstract

The invention relates to a design method for low-energy transit among interplanetary fixed orbits based on invariant manifold. The method is particularly suitable for transit between adjacent planetary orbits with approximate manifolds and belongs to the field of an orbital maneuver technology of spacecrafts. The method comprises the following steps of: firstly providing a pulse consumption assessment method and providing a judgment standard for selecting an appropriate invariant manifold; then determining the range of an invariant manifold transit orbit by calculating a poincare map of the invariant manifold on a fixed circular orbit, and obtaining a transit orbit with a minimum speed increment by using a contour map method; and splicing transit orbits at two ends of a heliocentric two-body model after finishing designing an escape transit orbit and a capture transit orbit, and finally finishing designing the design for low-energy transit among interplanetary fixed orbits based on invariant manifold. The method disclosed by the invention has the advantages of simple calculation, high calculation efficiency and the like and is suitable for the initial design of fixed orbits of different planets by using the low-energy transit orbit based on the invariant manifold.

Description

technical field [0001] The invention relates to a low-energy transfer design method between interplanetary fixed orbits based on an invariant manifold, which is particularly suitable for the transfer between adjacent planetary orbits with close manifolds, and belongs to the technical field of spacecraft orbital maneuvering. Background technique [0002] The high fuel consumption of the traditional transfer method seriously restricts the rapid development of deep space exploration. Therefore, the transfer technology using dynamic technology has received more and more attention, especially the use of invariant manifold transfer can effectively reduce energy consumption. . Borrowing the principle of the invariant manifold to rationally utilize the long-term perturbation effect of the main celestial body in the three-body model, thus effectively changing the energy of the orbit. However, invariant manifolds are a collection of naturally occurring trajectories, and no simple des...

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Problems solved by technology

[0005] In view of the inability of the existing design method to select the optimal invariant manifold and the globally optimal orbit transfer opportunity, the present invention proposes an interplanetary fixation based on the invariant manifold in combination with the Poincaré mapping and contour map method Design method for low energy transfer between orbits

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