Optimization of Earth-Mars transfer trajectories with launch constraints

Chen, Lidan; Li, Junfeng

doi:10.1007/s10509-021-04025-2

Cited by 4 publications

(1 citation statement)

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“…In this work, we analyze the design of an interplanetary Earth-Mars transfer to reach the areostationary orbit with the minimum impulsive maneuvers cost. Several authors have studied the optimization of interplanetary trajectories: in [10,11] transfer trajectories to the Moon and Jupiter, respectively, passing close to a Lagrangian point, are considered; in [12], a method is developed to obtain approximate near-optimal low-thrust interplanetary transfers using solar electric propulsion spacecraft; in [13], the optimization is performed with a cost function with variable coefficients; in [14], launch constraints are imposed for the optimization. We derive the heliocentric elliptic transfer characterizing the launch windows using an heuristic optimization method for determining an optimal time of flight (TOF) that minimizes the characteristic energies [15,16].…”

Section: Introductionmentioning

confidence: 99%

Modelization of Low-Cost Maneuvers for an Areostationary Preliminary Mission Design

Sánchez-García,

Barderas,

Romero

2023

MCA

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The aim of this paper is to analyze the determination of interplanetary trajectories from Earth to Mars to evaluate the cost of the required impulse magnitudes for an areostationary orbiter mission design. Such analysis is first conducted by solving the Lambert orbital boundary value problem and studying the launch and arrival conditions for various date combinations. Then, genetic algorithms are applied to investigate the minimum-energy transfer orbit. Afterwards, an iterative procedure is used to determine the heliocentric elliptic transfer orbit that matches at the entry point of Mars’s sphere of influence with an areocentric hyperbolic orbit imposing specific conditions on inclination and periapsis radius. Finally, the maneuvers needed to obtain an areostationary orbit are numerically computed for different objective condition values at the Mars entry point to evaluate an areostationary preliminary mission cost for further study and characterization. Results show that, for the dates of the minimum-energy Earth–Mars transfer trajectory, a low value for the maneuvers to achieve an areostationary orbit is obtained for an arrival hyperbola with the minimum possible inclination and a capture into an elliptical trajectory with a low periapsis radius and an apoapsis at the stationary orbit. For a 2026 mission with a TOF of 304 for the minimum-energy Earth–Mars transfer trajectory, for a capture with a periapsis of 300 km above the Mars surface the value achieved will be 2.083 km/s.

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