As rideshare launches become more available within the U.S., secondary payloads are still challenged by the limited choice of orbits and risk-adverse nature of primary payloads to allow for flexibility in the deployment sequence. The result is that a secondary payload's final orbit is limited by its host and the propulsion capability of the individual spacecraft. Many of these challenges can be met through the use of a propulsive rideshare adapter. The Lunar Crater Observation and Sensing Satellite (LCROSS) mission demonstrated the use of a propulsive EELV Secondary Payload Adapter (ESPA) ring to expand and enhance an existing mission by utilizing the mass margin on a lunar launch. Similar propulsive ESPA technologies can be used as a baseline to provide orbit flexibility and optimization that was previously unattainable for secondary payloads.


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    Title :

    Mission case studies using the rideshare enabling Orbital Maneuvering Vehicle


    Contributors:


    Publication date :

    2015-03-01


    Size :

    1609431 byte




    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English




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