CPC B64C 25/62 (2013.01) | 20 Claims |
1. A landing gear system for an aircraft comprising:
a composite flex beam having through-thickness stitching and a curvature having a radius greater than 5 inches, wherein the through-thickness stitching extends across an entirety of the composite flex beam along a length of the curvature, and wherein a density of the through-thickness stitching is greater near a leading edge and a trailing edge of the composite flex beam; and
a trunnion connected to the composite flex beam and offset from a neutral surface of the composite flex beam.
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