A method for the adhesive bonding of aerospace structures to optimize joint efficiency without introducing deleterious residual thermal stresses in a space environment is described. The process involves initially applying a high temperature curing film adhesive to the adherend surfaces to maximize surface energetics, and then bonding the adherends together with a room temperature curing adhesive to minimize residual thermal stresses in the bondline. The process is especially suited for bonding dissimilar thermal expansion materials, e.g. graphite/epoxy composites to metals, which will experience large thermal excursions in space. Lap shear strengths were measured at various temperatures on magnesium-to-composite specimens. Results are compared to conventional single adhesive applications. The integrity of double-adhesive bonded specimens after thermal cycling exposures (-30 F to +140 F) is also demonstrated. (Kursetz)


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Adhesive bonding process for space structures


    Additional title:

    Klebverbindungsverfahren fuer Konstruktionsteile von Raumfahrzeugen


    Contributors:


    Publication date :

    1979


    Size :

    9 Seiten, 2 Bilder, 2 Tabellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




    Adhesive Bonding in Car Structures

    British Library Online Contents | 1995



    Adhesive Bonding of Aircraft Primary Structures

    Hart-Smith, L. J. | SAE Technical Papers | 1980


    Process for Adhesive Bonding of Metal Skins to Aircraft Structures

    Phillips, P. M. / Aker, S. C. | SAE Technical Papers | 1985


    Adhesive bonding and lightweight structures in shipbuilding

    Weitzenböck, Jan R. / Brede, Markus | Tema Archive | 2006