Numerical results are presented for optimizing the perturbed trajectories of spacecraft with finite-thrust. The optimal trajectories are calculated using an indirect approach based on the application of the necessary optimality conditions in the form of the maximum principle, the method of continuation by parameter, and complex dual numbers for high-precision calculation of the necessary derivatives of complicated functions. This approach was presented in the first part of the paper. The aim of optimization problem is to calculate trajectories with minimal fuel consumption for a given angular distance and free transfer duration. A mathematical model of the spacecraft motion in equinoctial elements with an angular independent variable is used. Typical examples of optimal perturbed multi-revolution trajectories between high elliptical orbits, between geostationary transfer orbit and geostationary orbit, and between near-circular low Earth orbits are considered. A comparison is made between the optimal perturbed and unperturbed trajectories. The estimation of the influence of the departure date, the angular distance of the transfer and the set of the perturbing accelerations on the main parameters of the optimal trajectories is given.
Optimization of Perturbed Spacecraft Trajectories Using Complex Dual Numbers. Part 2: Numerical Results
Cosmic Res
Cosmic Research ; 59 , 6 ; 517-528
2021-11-01
12 pages
Article (Journal)
Electronic Resource
English
optimal multi-revolution transfers , perturbed trajectories , maximum principle , continuation method , complex dual numbers Physics , Astronomy, Astrophysics and Cosmology , Astrophysics and Astroparticles , Space Sciences (including Extraterrestrial Physics, Space Exploration and Astronautics) , Physics and Astronomy
On randomly perturbed spacecraft trajectories.
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