Minor planet detection optimal multi-impulse transfer method of interplanetary multibody system

Abstract

The invention discloses a minor planet detection optimal multi-impulse transfer method of an interplanetary multibody system, and belongs to the technical field of aerospace engineering. The method includes steps of firstly, building a detector kinetic equation under a geological core rotating system, namely, a high-precision kinetic model; selecting a target minor planet according to task restriction and providing an initial state of the detector under the geological core rotating coordinate system; applying a disturbance method to obtain a detector single-impulse minor planet flyover track;applying an optimization algorithm to obtain a single-impulse minor planet flyover transfer track with the minimum flyover distance; based on a main vector theory, performing a multi-impulse transfertrack design, and acquiring an optimal multi-impulse transfer track which meets the main vector condition; bringing the acquired optimal multi-impulse transfer track to the high-precision kinetic model to progressively induce; amending the transfer track by a multi-grade parallel differential amending method, and realizing the accurate track transfer of minor planet detection under a multi-celestial-body strong disturbance nonlinear environment. The minor planet detection optimal multi-impulse transfer method has the advantages of small speed increment, good applicability, and good astringency.

Description

technical field [0001] The present invention relates to an optimal multi-pulse transfer method for asteroid detection in an interplanetary multi-body system, in particular to an optimal multi-pulse orbit transfer method for asteroid detection at a heliotropic point under the multi-constraint condition of a non-autonomous system, belonging to Aerospace technology field. Background technique [0002] The design of the transfer orbit from the orbit near the translation point of the three-body system, such as the Lissajous orbit of the sun-earth L2 point, to the target celestial body is usually realized by searching the intersection of the orbital instability manifold of the translation point and the orbit of the target celestial body. However, under real conditions, the detector is affected by multi-body gravitational disturbances and orbital eccentricity, and the dynamic environment is very different from the ideal circular restricted three-body system (autonomous system), wit...

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Problems solved by technology

The present invention has the following advantages: (1) the speed increment is small, and the optimality of the transfer orbit is judged by the principal vector method, and the multi-pulse transfer orbit with optimal energy can be obtained; (2) the applicability is good, and it can be used for different detection It is suitable for the orbit transfer problem with complex task constraints; (3) the convergence is good, and the orbit is corrected under the real ephemeris by using multi-level parallel differential correction to ensure that the orbit is not affected by strong disturbances. Convergence in Linear Dynamics

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