Two Direct Low Thrust Trajectory Optimization Techniques
- Authors: Trofimov S.P.1, Tselousova A.A.1,2, Shirobokov M.G.1
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Affiliations:
- Keldysh Institute of Applied Mathematics, Russian Academy of Sciences
- Moscow Institute of Physics and Technology
- Issue: Vol 57, No 6 (2018)
- Pages: 989-1000
- Section: Control Systems of Moving Objects
- URL: https://journals.rcsi.science/1064-2307/article/view/220269
- DOI: https://doi.org/10.1134/S1064230718060114
- ID: 220269
Cite item
Abstract
Direct low thrust trajectory optimization techniques that reduce the optimization problem in the class of continuous functions to a nonlinear programming problem are described. Two direct low thrust trajectory optimization methods are implemented; one of them is based on the optimization of thrust acceleration and the other optimizes the impulses approximating the thrust arcs. These methods are compared using a sample problem of transfer from Earth to Mars in terms of runtime, the number of iterations, and the size of the convergence domains. The computations are performed on a personal computer using MATLAB and on a multiprocessor computer.
About the authors
S. P. Trofimov
Keldysh Institute of Applied Mathematics, Russian Academy of Sciences
Email: tselousovaperm@mail.ru
Russian Federation, Moscow, 125047
A. A. Tselousova
Keldysh Institute of Applied Mathematics, Russian Academy of Sciences; Moscow Institute of Physics and Technology
Author for correspondence.
Email: tselousovaperm@mail.ru
Russian Federation, Moscow, 125047; Dolgoprudnyi, Moscow oblast, 141700
M. G. Shirobokov
Keldysh Institute of Applied Mathematics, Russian Academy of Sciences
Email: tselousovaperm@mail.ru
Russian Federation, Moscow, 125047