Abstract: A shim assembly includes a shim material configured to be positioned between a first component and a second component. A wire is in contact with the shim material. The wire is configured to heat the shim material to above a predetermined temperature, and the shim material becomes moldable above the predetermined temperature such that the shim material is able to conform to the first component and the second component.

Abstract: A shim assembly includes a shim material configured to be positioned between a first component and a second component. A wire is in contact with the shim material. The wire is configured to heat the shim material to above a predetermined temperature, and the shim material becomes moldable above the predetermined temperature such that the shim material is able to conform to the first component and the second component.

Abstract: A shim assembly includes a shim material configured to be positioned between a first component and a second component. A wire is in contact with the shim material. The wire is configured to heat the shim material to above a predetermined temperature, and the shim material becomes moldable above the predetermined temperature such that the shim material is able to conform to the first component and the second component.

Abstract: An aircraft comprises a forward-facing aircraft section including composite aircraft skin and a substructure for the skin. The substructure includes a plurality of hoop-shaped composite frames. The frames are designed to deflect elastically under bird impact loads.

Abstract: A shim assembly includes a shim material configured to be positioned between a first component and a second component. A wire is in contact with the shim material. The wire is configured to heat the shim material to above a predetermined temperature, and the shim material becomes moldable above the predetermined temperature such that the shim material is able to conform to the first component and the second component.

Abstract: In accordance with the present invention an aircraft stringerless fuselage structure is provided comprising an impact compliant outer skin having a plurality of resin impregnated skin fibers forming an outer skin surface, an inner stringerless skin surface, and a skin thickness. A plurality of stiffeners is included, each comprising a plurality of resin impregnated stiffener fibers integrated into the inner stringerless skin structure. The plurality of resin impregnated skin fibers are not aligned with the plurality of resin impregnated stiffener fibers.

Abstract: In accordance with the present invention an aircraft stringerless fuselage structure is provided comprising an impact compliant outer skin having a plurality of resin impregnated skin fibers forming an outer skin surface, an inner stringerless skin surface, and a skin thickness. A plurality of stiffeners is included, each comprising a plurality of resin impregnated stiffener fibers integrated into the inner stringerless skin structure. The plurality of resin impregnated skin fibers are not aligned with the plurality of resin impregnated stiffener fibers.

Abstract: In accordance with the present invention an aircraft stringerless fuselage structure is provided comprising an impact compliant outer skin having a plurality of resin impregnated skin fibers forming an outer skin surface, an inner stringerless skin surface, and a skin thickness. A plurality of stiffeners is included, each comprising a plurality of resin impregnated stiffener fibers integrated into the inner stringerless skin structure. The plurality of resin impregnated skin fibers are not aligned with the plurality of resin impregnated stiffener fibers.

Abstract: An aircraft pivot joint bushing has enhanced thermal conductivity due to the bushing having an inner cylindrical portion which has a first thermal dissipating capacity, and an outer cylindrical portion on the inner cylindrical portion which has a second thermal dissipating capacity, where the second thermal dissipating capacity is less than the first thermal dissipating capacity.

Abstract: An aircraft forward pressure bulkhead and an aircraft crown panel are described herein. The forward pressure bulkhead includes a malleable and deformable dome that is configured to “catch” foreign objects, such as birds. The dome is intentionally designed to deform in response to a foreign object strike that imparts at least a threshold amount of impact energy to the bulkhead. The dome is free of rigid stiffeners and non-deformable reinforcement members that would otherwise hinder the flexible characteristic of the dome. Practical embodiments of the bulkhead utilize fewer parts, are less heavy, and are less expensive than traditional bulkheads that utilize rigid stiffeners. The crown panel has similar compliant characteristics. The crown panel is designed to simultaneously deform and deflect in response to foreign object impacts such as birds and hail. The crown panel is formed from a monolithic one-piece material, such as aluminum, and various reinforcing features are integrally formed in the material.

Abstract: An aircraft forward pressure bulkhead and an aircraft crown panel are described herein. The forward pressure bulkhead includes a malleable and deformable dome that is configured to “catch” foreign objects, such as birds. The dome is intentionally designed to deform in response to a foreign object strike that imparts at least a threshold amount of impact energy to the bulkhead. The dome is free of rigid stiffeners and non-deformable reinforcement members that would otherwise hinder the flexible characteristic of the dome. Practical embodiments of the bulkhead utilize fewer parts, are less heavy, and are less expensive than traditional bulkheads that utilize rigid stiffeners. The crown panel has similar compliant characteristics. The crown panel is designed to simultaneously deform and deflect in response to foreign object impacts such as birds and hail. The crown panel is formed from a monolithic one-piece material, such as aluminum, and various reinforcing features are integrally formed in the material.

Abstract: An aircraft forward pressure bulkhead and an aircraft crown panel are described herein. The forward pressure bulkhead includes a malleable and deformable dome that is configured to “catch” foreign objects, such as birds. The dome is intentionally designed to deform in response to a foreign object strike that imparts at least a threshold amount of impact energy to the bulkhead. The dome is free of rigid stiffeners and non-deformable reinforcement members that would otherwise hinder the flexible characteristic of the dome. Practical embodiments of the bulkhead utilize fewer parts, are less heavy, and are less expensive than traditional bulkheads that utilize rigid stiffeners. The crown panel has similar compliant characteristics. The crown panel is designed to simultaneously deform and deflect in response to foreign object impacts such as birds and hail. The crown panel is formed from a monolithic one-piece material, such as aluminum, and various reinforcing features are integrally formed in the material.

Abstract: Energy absorbing structure disposed beneath the cargo area of an aircraft provides maximum energy absorption and structural strength using carbon fiber reinforced epoxy composites. The energy absorbing structure uses laminated stanchions having ply drop-offs to produce stable, progressive crushing of the stanchions during a wheels-up crash landing. Integrally formed flanges on the stanchions allow direct mounting of the stanchions on the structural members of the aircraft, without the need for specialized fittings.

Abstract: A pressurized bulkhead or panel for an aircraft includes an energy absorbing skin that deforms in response to an object strike that imparts at least a threshold amount of impact energy to the skin. The skin may be configured as a dome or a lofted panel that is essentially free of rigid stiffeners and non-deformable reinforcement members that would otherwise hinder the flexible characteristics of the skin. The skin may be formed from a monolithic one-piece material, such as metal of composites, and may include various integrally formed reinforcing features.

Abstract: An aircraft forward pressure bulkhead and an aircraft crown panel are described herein. The forward pressure bulkhead includes a malleable and deformable dome that is configured to “catch” foreign objects, such as birds. The dome is intentionally designed to deform in response to a foreign object strike that imparts at least a threshold amount of impact energy to the bulkhead. The dome is free of rigid stiffeners and non-deformable reinforcement members that would otherwise hinder the flexible characteristic of the dome. Practical embodiments of the bulkhead utilize fewer parts, are less heavy, and are less expensive than traditional bulkheads that utilize rigid stiffeners. The crown panel has similar compliant characteristics. The crown panel is designed to simultaneously deform and deflect in response to foreign object impacts such as birds and hail. The crown panel is formed from a monolithic one-piece material, such as aluminum, and various reinforcing features are integrally formed in the material.

Abstract: A composite panel structure for an aircraft includes a plurality of annular, hat-shaped frames disposed coaxially along a long axis of the aircraft in a spaced, parallel relationship, an inner skin having an inner surface bonded to an outer surface of the hat frames, a plurality of elongated, hat-shaped stringers disposed in a longitudinal direction along an outer surface of the inner skin in a spaced, parallel relationship, a solid or rigid foam offset bonded to an outer surface of each of the stringers, and an outer skin having an inner surface bonded to an upper surface of each of the offsets. The inner skin carries the loads of the structure and the outer skin defines an aerodynamic surface of the aircraft and provides impact and lighting protection. The frames, inner skin and stringers are formed on a single forming tool and cured and bonded with each other simultaneously.

Abstract: An aircraft comprises a forward-facing aircraft section including composite aircraft skin and a substructure for the skin. The substructure includes a plurality of hoop-shaped composite frames. The frames are designed to deflect elastically under bird impact loads.

Abstract: An aircraft forward pressure bulkhead as described herein includes a malleable and deformable dome that is configured to “catch” foreign objects, such as birds. The dome is intentionally designed to deform in response to a foreign object strike that imparts at least a threshold amount of impact energy to the bulkhead. The dome is free of rigid stiffeners and non-deformable reinforcement members that would otherwise hinder the flexible characteristic of the dome. Practical embodiments of the bulkhead utilize fewer parts, are less heavy, and are less expensive than traditional bulkheads that utilize rigid stiffeners.

Abstract: Energy absorbing structure disposed beneath the cargo area of an aircraft provides maximum energy absorption and structural strength using carbon fiber reinforced epoxy composites. The energy absorbing structure uses laminated stanchions having ply drop-offs to produce stable, progressive crushing of the stanchions during a wheels-up crash landing. Integrally formed flanges on the stanchions allow direct mounting of the stanchions on the structural members of the aircraft, without the need for specialized fittings.

Abstract: An energy absorbing structural strut employs a composite tube bonded to an end fitting with the bond being slightly lower in strength than the crushing strength of the tube in axial compression. The end fitting incorporates an anvil to rupture the tube and absorb energy upon shearing of the bond with the strut in compression.