A Design Method for Spacecraft Flight Trajectory by Power

Abstract

The invention discloses a method for designing a orbit of a spacecraft using force to fly, which includes: determining the calculation parameters of the apse star point speed of the space vehicle use force flight track; establishing a speed equation of the apse star point according to the calculation parameters and solving the velocity vector; The shape-restricted three-body dynamics model determines the Hill sphere boundary state of the spacecraft; establishes the mapping relationship between the boundary value constraints of the leveraged flight orbit and the initial velocity through the artificial neural network, thereby obtaining the artificial neural network model; using the artificial neural network The network model completes the calculation of the initial velocity of the three-body Lambert problem of the spacecraft's leveraged flight orbit; designs the orbit of the spacecraft's leveraged flight according to the initial velocity of the three-body Lambert problem; The solution of the three-body Lambert problem on the flight track solves the problem of convergence difficulties caused by inaccurate initial velocity guessing values ​​in strongly nonlinear systems. When calculating the initial velocity, the calculation efficiency is high and the accuracy is high.

Description

technical field [0001] The invention belongs to the field of new generation information technology, and specifically refers to a design method of a space vehicle flying orbit by force. Background technique [0002] The use of spacecraft to fly 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, the conic section splicing method is widely used. However, the design result of this method has a large error compared with the result under the high-precision model, and the fuel consumption of the design result is also relatively large. In order to reduce fuel consumption and obtain the solution of the high-precision model, the three-body problem model is used to design the orbit of the spacecraft by force. Based on the three-body problem model, the design of the orbit of the spacecraft by force is essentially to solve the three-body Lambert problem. Compar...

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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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