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)
Adhesive bonding process for space structures
Klebverbindungsverfahren fuer Konstruktionsteile von Raumfahrzeugen
1979
9 Seiten, 2 Bilder, 2 Tabellen
Conference paper
English
Adhesive Bonding in Car Structures
British Library Online Contents | 1995
Adhesive Bonding in Car Structures
Online Contents | 1995
Adhesive Bonding of Aircraft Primary Structures
SAE Technical Papers | 1980
|Process for Adhesive Bonding of Metal Skins to Aircraft Structures
SAE Technical Papers | 1985
|Adhesive bonding and lightweight structures in shipbuilding
Tema Archive | 2006
|