In Chandrayaan I Mission and Mars Orbiter Mission, ISRO put the spacecraft from Earth Parking Orbit to the trans-lunar/trans-planetary injection point through a series of orbit-raising manoeuvres around Earth. The start time and duration of each burn, along with the size of the intermediate orbits and the burn sequence, must be designed, such that at the end of manoeuvres, the trans-lunar/trans-planetary injection epoch is achieved. This study aims to design the optimal multiple finite burn orbit-raising manoeuvres for trans-lunar and trans-planetary manoeuvres, using differential evolution as the optimization technique. The reduction in the computational time is achieved through multi-threading.


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    Title :

    Optimal Multiple Finite Burn Strategies for Trans-lunar and Trans-planetary Manoeuvres


    Additional title:

    Lect.Notes Mechanical Engineering


    Contributors:


    Publication date :

    2020-05-05


    Size :

    15 pages





    Type of media :

    Article/Chapter (Book)


    Type of material :

    Electronic Resource


    Language :

    English





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