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    Multi-objective suborbit/orbit trajectory optimisation for spaceplanes  
    Bae, sangjun(Chalmers University of Technology)
    Nederland | Acta Astronautica
    2020-01-28 | 바로가기
    Spaceplanes, Re_exit_trajectory
    Cited by

    ■  View full text

    Acta Astronautica

    Received 16 February 2019, Revised 29 December 2019, Accepted 1 January 2020, Available online 28 January 2020.

    https://doi.org/10.1016/j.actaastro.2020.01.003

     

     

    ■  Researchers

    Sangjun Baea,b, Hyo-SangShinb, Al Savvarisb, LappasVaiosc, AntoniosTsourdosb

     

    a  Electrical Engineering, Chalmers University of Technology

    b  School of Aerospace, Transport and Manufacturing, Cranfield University

    c  Department of Aerospace Engineering, University of Patras

     

     

    ■  Abstract

    In this paper, a suborbit to orbit mission profile is analysed for spaceplanes. The proposed mission profile for spaceplanes is currently being considered for multiple earth observation missions and is considered as an extension of the skip re-entry problem which is a highly coupled and nonlinear problem. To solve the problem, we utilise both the Fuzzy Satisfactory Goal Programming (FSGP) method and the Radau Pseudospectral Method (RPM) as the problem includes more than two objective functions conflicting with each other, and needs to be optimised with pre-emptive priorities. A realistic spaceplane model is used with equality and inequality constraints, to demonstrate the feasibility of suborbit-orbit-suborbit manoeuvres through numerical simulations. The simulation results generated by the proposed methodology show that significant propellant savings can be made using multi-objective trajectory optimisation for spaceplanes for future theatre observation missions.

     

     

     

     

     

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