Design method of spacecraft leveraging flight orbit

Abstract

The invention discloses a design method of a spacecraft leveraging flight orbit. The design method comprises the following steps: determining a near-star-point speed calculation parameter of the spacecraft leveraging flight orbit; establishing a near star point velocity equation according to the calculation parameters and solving a velocity vector; determining a Hille sphere boundary state of the spacecraft by using a circular restrictive three-body dynamics model; establishing a mapping relation between a leveraging flight orbit boundary value constraint condition and an initial speed through an artificial neural network so as to obtain an artificial neural network model; using the artificial neural network model to complete the calculation of the initial speed of the three-body Lanbert problem of the spacecraft leveraging flight orbit; designing a leveraging flight orbit of the spacecraft according to the initial speed of the three-body Lanbert problem; the artificial neural network is adopted to solve the three-body Lanbert problem of the leveraging flight orbit, the problem that convergence is difficult due to the fact that the initial speed guess value is not accurate in a strong nonlinear system is solved, and when the initial speed is calculated, the calculation efficiency is high, and the precision is high.

Description

technical field [0001] The invention belongs to the field of a new generation of information technology, and specifically refers to a design method of a spacecraft utilizing force to fly a trajectory. Background technique [0002] Spacecraft leveraged flight is a key technology to greatly reduce the fuel consumption of deep space exploration missions. In the initial design stage of traditional deep space exploration mission orbits, conic splicing method is widely used. However, compared with the results under the high-precision model, the design results of this method have larger errors, and the design results are also relatively large in fuel consumption. In order to reduce the fuel consumption and obtain the solution of the high-precision model, the three-body problem model is used to design the spacecraft's flight path by force. The design of the spacecraft's flight orbit based on the three-body problem model is essentially to solve the three-body Lambert problem. Comp...

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Problems solved by technology

[0003] Aiming at the deficiencies of the above-mentioned prior art, the purpose of the present invention is to provide a design method of a spacecraft's leveraged flight track to solve the problem that it is difficult to realize the three-body Lambert orbit of a spacecraft's powered flight in a short time in the prior art. quick problem solving

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