Abstract
Due to their high specific strength and high specific stiffness properties the use of honeycomb panels is particularly attractive in spacecraft structures. However, the dynamic loads produced during the launch of a satellite can subject the honeycomb cores of these sandwich structures to numerous stress cycles, potentially leading to early fatigue failures. Knowledge of the fatigue behavior of these honeycomb cores is thus a key requirement when considering their use in spacecraft structural applications. This paper presents the findings of an experimental test campaign carried out to investigate the static and fatigue behaviors of aluminum hexagonal honeycomb cores subject to in-plane shear loads. The investigation involved carrying out both static and fatigue tests using the single block shear test method. These tests were conducted for both of the two principal cell orientations (L and W) and from the results S-N fatigue curves for both cell orientations are presented, confronted and discussed. These results are also discussed in relation to the observed damage and failure modes which have been reported for the statically tested specimens and for the fatigue tested specimens at various stages of fatigue life. Copyright © 2009 by the American Institute of Aeronautics and Astronautics, Inc.