Static Test of a Wing Box Structure Made of Composite Materials, Phase 1

摘要

The load carrying structure in the wing of a light transport aircraft, (MULA), was tested in a simulated pull up flight maneuver. The structure consisted of a two beam wing box in sandwich construction. Carbon fibers and glass fibers in a vinylester resin were used in the faces and a foam plastic was used as core material. Unidirectional carbon fiber epoxy rods were used in areas subjected to high tensile or compressive loads. All composite parts were vacuum or pressure molded in large components bonded together to form the wind box structure. The fittings were made from steel and attached to the composite surfaces by bonding and bolting.