Optimal planetary rendezvous with an electric sail

Abstract

Purpose

The aim of this paper is to discuss E-sail-based missions (E-sail – electric solar wind sail) towards Venus and Mars. The analysis takes into account the real three-dimensional shape of the starting and arrival orbits and the planetary ephemeris constraints by using the Jet Propulsion Laboratory (JPL) planetary ephemerides model DE405/LE405.

Design/methodology/approach

Each mission scenario is parameterized with different values of departure date and spacecraft characteristic acceleration, the latter representing the maximum propulsive acceleration when the Sun–spacecraft distance is 1 au. The transfer trajectories are studied in an optimal framework, using a Gauss pseudospectral method in which the initial guesses for the state and control histories are obtained with a genetic algorithm-based approach.

Findings

The paper illustrates the numerical simulations obtained with a spacecraft characteristic acceleration of 1 mm/s², and the results cover a range of launch dates of 17 years for both Earth–Mars and Earth–Venus interplanetary missions. In particular, the numerical results confirm the competitiveness of such a propellantless propulsion system.

Practical implications

A parametric study of the transfer’s flight time corresponding to the optimal departure dates is discussed for different values of the spacecraft characteristic acceleration. The results motivate a further in-depth analysis of the E-sail concept.

Originality/value

This paper extends previous work on optimal trajectories with an E-sail in that the best launch opportunities are investigated. A refined thrust model is also used in all numerical simulations.

Citation

Huo, M., Mengali, G. and Quarta, A.A. (2016), "Optimal planetary rendezvous with an electric sail", Aircraft Engineering and Aerospace Technology, Vol. 88 No. 4, pp. 515-522. https://doi.org/10.1108/AEAT-01-2015-0012