Composite structure, aircraft wing and aircraft fuselage including composite structure, and method of manufacturing composite structure
A composite structure ( 3 ) formed of a composite member which extends in one direction, includes holes ( 5 ), and is made of fiber reinforced plastics. A tensile load and/or a compressive load are applied to the composite structure ( 3 ) in the one direction. Tensile stiffness and/or compression stiffness of peripheral areas ( 3 a ) of the holes ( 5 ) is lower than tensile stiffness and/or compression stiffness of the other area ( 3 b ), which surrounds the peripheral areas ( 3 a ), in the one direction, and the width of the peripheral area ( 3 a ) in a direction orthogonal to the one direction is set to 1.1 times or less of the diameter of the hole ( 5 ) in the direction orthogonal to the one direction.
1. A composite structure, comprising:
a holed structural member that is a composite material made of fiber reinforced plastic, the holed structural member extending in one direction,
wherein holes are formed in the holed structural member, the holes being arranged along an axial line extending in the one direction,
wherein the holed structural member is composed of a peripheral area that is positioned around the holes and an other area that surrounds the peripheral area,
wherein the holed structural member is formed of an integrated composite member which is not divided and which includes oriented carbon fiber reinforced plastic as a main component,
wherein a ratio of an orientation of carbon fiber of the peripheral area is different from a ratio of an orientation of carbon fiber of the other area,
wherein the holed structural member has a first lateral side extending in a direction in which the composite structure is shortest and a second lateral side extending in the direction in which the composite structure is shortest,
wherein a length of the peripheral area extends from the first lateral side of the holed structural member to the second lateral side of the holed structural member,
wherein a centerline of the peripheral area extends along the axial line extending in the one direction,
wherein the peripheral area adjoins at least a portion of a perimeter of each of the holes,
wherein the holed structural member is configured to receive a tensile load and/or a compressive load applied to the composite structure in the one direction,
wherein tensile stiffness and/or compression stiffness of the peripheral area of the holes in the one direction is lower than tensile stiffness and/or compression stiffness of the other area in the one direction,
wherein a width of the peripheral area in a direction orthogonal to the one direction is set to a range of 0.54 to 1.0 times a diameter of one of the holes in the direction orthogonal to the one direction, and
wherein the holes are access holes that are formed at a lower outer plate of a wing of an aircraft.
2. The composite structure according to claim 1 ,
peripheral area, the carbon fiber is oriented in a direction of ±30° to ±60° in a state in which the one direction is 0°.
3. The composite structure according to claim 1 ,
wherein, in the peripheral area, the carbon fiber is oriented in a direction of ±45° in a state in which the one direction is 0°.
4. An aircraft wing comprising:
the composite structure according to claim 1 .
5. A composite structure, comprising:
a holed structural member that is a composite material made of fiber reinforced plastic, the holed structural member extending in one direction,
wherein holes are formed in the holed structural member, the holes being arranged along an axial line extending in the one direction,
wherein the holed structural member is composed of a peripheral area that is positioned around the holes and an other area that surrounds the peripheral area,
wherein the holed structural member is formed of an integrated composite member which is not divided and which includes oriented carbon fiber reinforced plastic as a main component,
wherein a ratio of an orientation of the carbon fiber of the peripheral area is different from a ratio of an orientation of the carbon fiber of the other area,
wherein the holed structural member has a first lateral side extending in a direction in which the composite structure is shortest and a second lateral side extending in the direction in which the composite structure is shortest,
wherein a length of the peripheral area extends from the first lateral side of the holed structural member to the second lateral side of the holed structural member,
wherein a centerline of the peripheral area extends along the axial line extending in the one direction,
wherein the peripheral area adjoins at least a portion of a perimeter of each of the holes,
wherein the holed structural member is configured to receive a tensile load and/or a compressive load applied to the composite structure in the one direction,
wherein tensile stiffness and/or compression stiffness of the peripheral area of the holes in the one direction is lower than tensile stiffness and/or compression stiffness of the other area in the one direction,
wherein a width of the peripheral area in a direction orthogonal to the one direction is set to a range of 0.54 to 1.0 times a diameter of one of the holes in the direction orthogonal to the one direction, and
wherein the holes are window holes that are formed at an outer plate of a fuselage of an aircraft.
6. The composite structure according to claim 5 ,
wherein, in the peripheral area, the carbon fiber is oriented in a direction of ±30° to ±60° in a state in which the one direction is 0°.
7. The composite structure according to claim 5 ,
wherein, in the peripheral area, the carbon fiber is oriented in a direction of ±45° in a state in which the one direction is 0°.
8. An aircraft fuselage comprising:
the composite structure according to claim 5 .