Minimum-Time Earth-to-Mars Interplanetary Orbit Transfer Using Adaptive Gaussian Quadrature Collocation

摘要: The problem of minimum-time, low-thrust, Earth-to-Mars interplanetary orbital trajectory optimization is considered. minimum-time transfer modeled as a four-phase optimal control where the four phases correspond to planetary alignment, Earth escape, heliocentric transfer, and Mars capture. then solved using direct collocation adaptive Gaussian quadrature method. following three models are used in study: (1) circular motion; (2) elliptic (3) motion with gravity perturbations, begins geostationary orbit terminates Mars-stationary orbit. Results for all cases provided, one particular case studied detail show key features solutions. Using value thrust specific force $0.00098\times 10^{-4}~\textrm{m}\cdot\textrm{s}^{-2}$, it was found that minimum times (1), (2), are, respectively, 215 d, 196 198 d departure dates, 1 July 2020, 30 June 28 2020. Finally, formulation developed this study compared against prior work on an results research significant improvement time relative work.