The dynamics instrumentation is described which will be flown in the end-mass of the first tethered satellite to be deployed from a Delta II launch vehicle with the SEDS (Small Expendable Deployer System) low-tension deployer. Transducers, signal conditioning, power supply design, data acquisition procedures and data recovery plans are discussed. The effects of temperature variations and other potential error sources are considered.


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    Title :

    End-mass instrumentation for the first SEDS/Delta II mission


    Contributors:
    Deloach, R. (author) / Diamond, J. (author) / Finley, T. (author) / Rhew, R. (author)

    Publication date :

    1990-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




    End-mass instrumentation for the first SEDS/Delta II mission

    DELOACH, R. / DIAMOND, J. / FINLEY, T. et al. | AIAA | 1990



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