J2 perturbation Lambert problem solving method based on deep neural network and targeting algorithm

Abstract

The invention discloses a J2 perturbation Lambert problem solving method based on a deep neural network and a targeting algorithm, and the method comprises the steps: obtaining initial speed values ofa start end according to start and tail end position vectors and flight time, carrying out the orbit recursion based on the obtained initial speed values of the start end, and obtaining a tail end position error under the interference of J2 perturbation; according to the tail end position error and starting and tail end positions and flight time in the initial condition, estimating an error of astarting end speed initial value by utilizing a deep neural network obtained by training, and correcting the obtained starting end speed initial value by taking the error as a correction value to obtain a corrected starting end speed initial guessing value; taking the obtained initial guessed value of the starting end speed as an initial value, and performing targeting correction on the initial guessed value of the starting end speed by utilizing a Newton iteration targeting algorithm based on differential approximation until the position precision of the tail end meets the requirement. According to the method, the problems that in the prior art, when the J2 perturbation Lambert problem is solved, the calculation efficiency is low, the convergence stability is insufficient, and the solvingeffect of the multi-circle Lambert problem is poor are solved.

Description

technical field [0001] The invention belongs to the technical field of orbital dynamics, and in particular relates to a method for solving the J2 perturbed Lambert problem based on a deep neural network and a shooting algorithm. Background technique [0002] The Lambert problem is to solve the velocity of the start and end given the position of the start and end and the flight time, which is a basic problem in the field of orbital dynamics. The classic Lambert problem is proposed based on the two-body dynamics model, but the actual motion of the spacecraft is disturbed by various perturbations, which makes the Kepler solution of the classic Lambert problem unable to meet the accuracy requirements of the actual mission. Therefore, considering that the J2 perturbation is the main perturbation term in low and middle orbits, the J2 perturbation Lambert problem is proposed on the basis of the classic Lambert problem. [0003] According to the solving principle, the existing J2 p...

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Problems solved by technology

[0004] Aiming at the deficiencies of the above-mentioned prior art, the object of the present invention is to provide a method for solving the J2 perturbed Lambert problem based on a deep neural network and a shooting algorithm, so as to solve the low computational efficiency in solving the J2 perturbed Lambert problem in the prior art , Insufficient convergence stability and poor solution effect of multi-turn Lambert problem

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