The dynamics associated with the jettisoning of heat shield fairings from the parent launch vehicle is investigated. The analysis considers a zip-cord based mechanism employed to jettison the fairings from the accelerating on-going stage. A scheme for characterization of the zip-cord system is described. The geometry of collision is analysed for a known, precomputed structural response. The no- collision domain is constructed in flexibility parameter space for an arbitrarily assumed impulse level. Alternatively, the minimum impulse required for a collision-free separation is also computed as a function of design parameters. Finally, the analysis enables generation of the upper limits on payload size as well as that of the external mountings for a clean separation. This methodology has led to the successful separation of shield heat fairings for the two developmental flights of the Indian launcher Polar Satellite Launch Vehicle (PSLV).


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    Title :

    Separation dynamics of heat shield fairings


    Contributors:
    Lochan, R (author) / Adimurthy, V (author) / Kumar, K (author)


    Publication date :

    1997-02-01


    Size :

    14 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English




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