Fuselage structure using advanced technology fiber reinforced composites
First Claim
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1. A fuselage structure comprising:
- a fuselage having a longitudinal axis;
an external skin of alternate layers of composite material, oriented at a biased angle relative to the longitudinal axis and at approximately 90°
to the biased angle;
stringers, having outboard and inboard ends;
frames;
circumferential pads of composite material located on an inner surface of the external skin between said external skin and said frames and oriented at approximately 90°
relative to the longitudinal axis;
first reinforcement means, associated with the outboard ends of the stringers, said first reinforcement means being composite material oriented as approximately 0°
relative to the longitudinal axis;
second reinforcement means, associated with the inboard ends of the stringers, said second reinforcement means being composite material oriented at approximately 0°
relative to the longitudinal axis; and
third reinforcement means associated with the frames and the external skin whereby the frames are fastened to the external skin through the reinforcement means and through shear ties.
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Abstract
A fuselage structure is disclosed in which the skin is comprised of layers of a matrix fiber reinforced composite, with the stringers reinforced with the same composite material. The high strength to weight ratio of the composite, particularly at elevated temperatures, and its high modulus of elasticity, makes it desirable for use in airplane structures.
195 Citations
25 Claims
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1. A fuselage structure comprising:
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a fuselage having a longitudinal axis; an external skin of alternate layers of composite material, oriented at a biased angle relative to the longitudinal axis and at approximately 90°
to the biased angle;stringers, having outboard and inboard ends; frames; circumferential pads of composite material located on an inner surface of the external skin between said external skin and said frames and oriented at approximately 90°
relative to the longitudinal axis;first reinforcement means, associated with the outboard ends of the stringers, said first reinforcement means being composite material oriented as approximately 0°
relative to the longitudinal axis;second reinforcement means, associated with the inboard ends of the stringers, said second reinforcement means being composite material oriented at approximately 0°
relative to the longitudinal axis; andthird reinforcement means associated with the frames and the external skin whereby the frames are fastened to the external skin through the reinforcement means and through shear ties. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16, 17, 18, 19)
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20. A fuselage structure comprising:
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a fuselage; skin means covering said fuselage with metal matrix fiber reinforced composites; stringer means; and means for reinforcing the connection of said stringer means to said skin means;
said reinforcing means attached to and supporting said skin means on said stringer means;said fuselage including a frame means consisting of inner and outer channels and webs between the channels, said frame means being connected to said stringer means, to maintain the cross-sectional shape of the fuselage, wherein the said skin means, stringer means, and frame means are so disposed as to provide maximum continuity to the primary load-bearing material; said skin means is alternate layers of borsic aluminum, oriented at approximately 0°
, approximately 45°
, approximately 90°
, and approximately 315°
to the fuselage longitudinal axis;said stringer means being reinforced with borsic aluminum oriented at approximately 0°
to the fuselage longitudinal axis;clips fastening said frame means to said stringer means and shear ties fastening said frame means to said skin means; a pad means of borsic aluminum, oriented in alternate layers at approximately 45° and
approximately 315°
to the fuselage longitudinal axis, attached to said skin means in the area of the shear ties; andthe stringer means including tabs in the vicinity of the frame means and clips fastened to said tabs, to attach the stringer means, so that there are no fasteners in the highly loaded portion of the stringer means. - View Dependent Claims (21, 22, 23, 24, 25)
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Specification