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Trajectory optimization of space vehicle in rendezvous proximity operation with evolutionary feasibility conserving techniques
Shirazi, A.
; Ceberio, J.; Lozano, J.A. (2022-10-09)
; Ceberio, J.; Lozano, J.A. (2022-10-09)
In this paper, a direct approach is developed for discovering optimal transfer trajectories of close-range rendezvous of satellites considering disturbances in elliptical orbits. The control vector representing the inputs ...
EDA++: Estimation of Distribution Algorithms with Feasibility Conserving Mechanisms for Constrained Continuous Optimization
Shirazi, A.; Ceberio, J.; Lozano, J.A. (2022-02-25)
; Ceberio, J.; Lozano, J.A. (2022-02-25)
Handling non-linear constraints in continuous optimization is challenging, and finding a feasible solution is usually a difficult task. In the past few decades, various techniques have been developed to deal with linear ...
Efficient meta-heuristics for spacecraft trajectory optimization
Shirazi, A. (2021-03)
(2021-03)
Meta-heuristics has a long tradition in computer science. During the past few years, different types of meta-heuristics, specially evolutionary algorithms got noticeable attention in dealing with real-world optimization ...
Simulation Framework for Orbit Propagation and Space Trajectory Visualization
Shirazi, A.; Ceberio, J.; Lozano, J.A. (2021)
; Ceberio, J.; Lozano, J.A. (2021)
In this paper, an interactive tool for simulation of satellites dynamics and autonomous spacecraft guidance is presented. Different geopotential models for orbit propagation of Earth-orbiting satellites are provided, which ...
An evolutionary discretized Lambert approach for optimal long-range rendezvous considering impulse limit
Shirazi, A.; Ceberio, J.; Lozano, J.A. (2019-09-18)
; Ceberio, J.; Lozano, J.A. (2019-09-18)
In this paper, an approach is presented for finding the optimal long-range space rendezvous in terms of fuel and time, considering limited impulse. In this approach , the Lambert problem is expanded towards a discretized ...
Optimal multi-impulse space rendezvous considering limited impulse using a discretized Lambert problem combined with evolutionary algorithms
Shirazi, A.; Ceberio, J.; Lozano, J.A. (2019-07-01)
; Ceberio, J.; Lozano, J.A. (2019-07-01)
In this paper, a direct approach is presented to tackle the multi-impulse rendezvous problem considering the impulse limit. Particularly, the standard Lambert problem is extended toward several consequential orbit transfers ...
Spacecraft Trajectory Optimization: A review of Models, Objectives, Approaches and Solutions
Shirazi, A.; Ceberio, J.; Lozano, J.A. (2018)
; Ceberio, J.; Lozano, J.A. (2018)
This article is a survey paper on solving spacecraft trajectory optimization problems. The solving process is decomposed into four key steps of mathematical modeling of the problem, defining the objective functions, ...
Evolutionary algorithms to optimize low-thrust trajectory design in spacecraft orbital precession mission
Shirazi, A.; Ceberio, J.; Lozano, J.A. (2017-06-06)
; Ceberio, J.; Lozano, J.A. (2017-06-06)
In space environment, perturbations make the spacecraft lose its predefined orbit in space. One of these undesirable changes is the in-plane rotation of space orbit, denominated as orbital precession. To overcome this ...
Analysis of a hybrid Genetic Simulated Annealing strategy applied in multi-objective optimization of orbital maneuvers
Shirazi, A. (2017-03-27)
(2017-03-27)
Optimization of orbital maneuvers is one of the main issues in conceptual and preliminary design of spacecraft in different space missions. The main issue in optimization of high-thrust orbit transfers is that the common ...
Multi-objective Optimization of Orbit Transfer Trajectory Using Imperialist Competitive Algorithm
Shirazi, A. (2017-03-04)
(2017-03-04)
This paper proposes a systematic direct approach to carry out effective multi-objective optimization of space orbit transfer with high-level thrust acceleration. The objective is to provide a transfer trajectory with ...