Abstract: This work is focused on the detection and computation of “free” transfer trajectories from parking orbits around the Earth to quasiperiodic orbits around the collinear libration point L2, in the Sun‐Earth system; no correction or insertion maneuvers into the final orbits have been considered. The circular restricted three‐body problem is the mathematical model used to describe the motion of a spacecraft, in the gravitational field of the two primaries, computed by integrating the nonlinearized equations of motion. A shooting method has been designed and developed to determine the increment of velocity required for the perigee maneuver, which injects a spacecraft into its transfer trajectory: first the velocity boundary for the Earth escape/capture condition is detected and then an iterative bisection method is applied until the burnout velocity, tangential to the parking orbit, leads the spacecraft to its final Lissajous orbit. For a launch from Kourou at local noon, Ariane5 GTO and Soyuz GTO “equivalent” have been studied and compared, considering fuel minimization for the transfer maneuver and general mission constraints, as maximum excursion of the final Lissajous orbit from the ecliptic plane and eclipses avoidance during the mission. This analysis highlights advantages and drawbacks of various parking orbits. Mission goals are the key factor for the tradeoff among orbit selection, launch options, and the other constraints, fixed by mission requirements.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Trajectory Design for Space Missions to Libration Point L2


    Contributors:

    Published in:

    Publication date :

    2005-12-01


    Size :

    14 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English




    Trajectory Design for Space Missions to Libration Point L~2

    Di Salvo, A. | British Library Conference Proceedings | 2005


    LIbration Point Trajectory Design

    Lo, Martin W. | NTRS | 1996


    Two impulses transfer trajectory design for Sun-Earth libration point missions

    Mingtao, L. / Jianhua, Z. / Xizheng, Y. et al. | British Library Online Contents | 2009


    Trajectory Sensitivities for Sun-Mars Libration Point Missions (AAS 01-327)

    Carrico, J. P. / Strizzi, J. D. / Kutrieb, J. M. et al. | British Library Conference Proceedings | 2001