Small satellites have been around since the dawn of the Space Age. Small, low cost satellites used to be the exclusive domain of scientific and amateur groups. Micro-Satellites fall into the 10–100 Kg category of Small Satellites. They are prone to single point failure and hence utmost care must be taken to design them with low safety factors. This paper gives the preliminary design procedure for a Micro-Satellite with subsystems. Here a Micro-Satellite has been modeled in CATIA and has been studied using ANSYS Finite Element Method codes. Initially the satellite was modeled for the static loads to be carried and after several iterations the optimized model to take dynamic loads with acceptable safety factor was obtained The Finite Element Model results have been validated with experimental results.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Test Approach for the Mechanical Qualification of a Micro-Satellite Structure and Subsystems


    Additional title:

    Sae Technical Papers


    Contributors:
    Jayaraman, K. (author) / Suresh, K. (author) / Sathesh, M. (author)

    Conference:

    General Aviation Technology Conference & Exhibition ; 2006



    Publication date :

    2006-08-30




    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




    Development of Satellite Mechanical Subsystems

    Stavrinidis, C. / International Astronomical Federation | British Library Conference Proceedings | 1998


    Satellite Subsystems

    Ippolito, Louis J. Jr. | Wiley | 2017


    Aircraft Mechanical Subsystems

    T. Tontarski | NTIS | 1968


    Aircraft Mechanical Subsystems

    A. Dolgich | NTIS | 1968


    VERIFICATION OF OPTICAL PAYLOAD CFRP STRUCTURE FOR SATELLITE THROUGH ANALYSIS AND SPACE QUALIFICATION TEST

    Lee, K.-J. / Oh, H.-U. / Jo, M.-S. et al. | British Library Conference Proceedings | 2012