Patent ID: 8844871
Filing Date: 2014-09-30
Classification: B64C,Y10T

Abstract:
1. An aircraft fuselage structural component comprising: plural longitudinally spaced-apart cross-sectionally reverse C-shaped frame members defining a transversal cross-section of an aircraft fuselage section, the frame members having a center span and spaced-apart upper and lower flanges oriented in a same direction, the frame members defining a plurality of stringer holes therethrough; plural longitudinally oriented stringers, each of the stringers being positioned within a respective one of the stringer holes of the frame members; and plural cross-sectionally reverse S-shaped reinforcement members each having an intermediate flange lap joined by a friction stir weld region to the center span of a corresponding one of the cross-sectionally reverse C-shaped frame members in a vicinity of the stringer holes thereof, wherein an upper flange of each reverse S-shaped structural member is spaced above and oriented in the same direction as the upper flange of the corresponding one of the cross-sectionally reverse C-shaped frame members to which the structural member is lap joined, and wherein a lower flange of each reverse S-shaped structural member is spaced above and extends in an opposite direction relative to the lower flange of the corresponding one of the cross-sectionally reverse C-shaped frame members to which the structural member is lap joined.