To reduce the cost of lunar exploration mission, the reusable lunar exploration architecture is proposed. The architecture consists of launch vehicle, propulsion vehicle, lunar lander, reusable human spacecraft (RHS), and low-Earth-orbit space station. The RHS can be reused after a propellant supplement, which distinguishes the reusable architecture from the expendable lunar exploration architecture. The required propellant consumption of RHS is critical to the feasibility of the proposed architecture, which is determined by the required velocity increment. The required velocity increment is made up of rendezvous-docking velocity increment and parking velocity increment. Given that the velocity increment for rendezvous docking is always relatively fixed, the required propellant consumption of RHS is influenced by the parking velocity increment directly. The influence parameters of parking velocity increment are analyzed based on the established aerocapture and post-aerocapture maneuver models. The variable neighborhood negative selection particle swarm optimization is established to obtain the optimal parking velocity increment. The results show that the parking velocity increment of RHS is about 100    m / s using the proposed optimization algorithm. The vehicle mass calculation model is established to support the comparison of the proposed reusable architecture and expendable architecture. The result shows that the proposed reusable architecture is lower regarding mass and cost in the long-term lunar exploration mission.


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    Title :

    Analysis and Optimization of Lunar Exploration Architecture Based on Reusable Human Spacecraft


    Contributors:

    Published in:

    Publication date :

    2019-05-01




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English




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