Abstract: An aerodynamic body operable to both promote laminar flow and satisfy structural requirements is disclosed. A perforated panel skin comprises an inner surface and an outer surface of the aerodynamic body. At least one hollow member is coupled to the inner surface and is operable to suction air from the outer surface and through the perforated panel skin. The at least one hollow member is oriented in a substantially chord-wise direction relative to an airflow over the aerodynamic body.

Abstract: According to an embodiment a current return network assembly, for an aircraft having a predetermined potential lightning strike zone, is mounted within the predetermined potential lightning strike zone. The current return network assembly includes an electrically conductive honeycomb central core that conducts electrical current both through the assembly and through the predetermined potential lightning strike zone. The electrical current is caused by a lightning strike on the aircraft at the predetermined potential lightning strike zone. According to an embodiment, an aircraft has a predetermined potential lightning strike zone. A current return network assembly is within the zone. An electrically conductive honeycomb central core is provided for conducting electrical current through the assembly and through the zone wherein the electrical current has been caused by a lightning strike on the aircraft at the zone.

Abstract: The invention relates to a mounting device in an aircraft. In one aspect of the invention, a method is disclosed for assembling a metal securement member of the mounting device. In another aspect of the invention, a mounting device is disclosed. In another aspect of the invention, a method is disclosed for installing and using a mounting device in an aircraft.

Abstract: The invention relates to a mounting device in an aircraft. In one aspect of the invention, a method is disclosed for assembling a metal securement member of the mounting device. In another aspect of the invention, a mounting device is disclosed. In another aspect of the invention, a method is disclosed for installing and using a mounting device in an aircraft.

Abstract: A test fixture for determining circumferential shear properties of an arcuate test specimen may include an outer fixture and an inner fixture. The outer fixture may be coupled to an outer side of the test specimen, and may be rotatably mounted on a central pin and may include a rocker arm. The inner fixture may be coupled to an inner side of the test specimen, and may be rotatably mounted on the central pin and may include a load arm extending in a direction opposite the rocker arm. The inner fixture and the outer fixture may be configured such that application of a test load to the rocker arm and the load arm causes rotation thereof about the central pin producing circumferential movement of the inner side relative to the outer side and inducing a circumferential shear load in the test specimen.

Abstract: The invention relates to a mounting device in an aircraft. In one aspect of the invention, a method is disclosed for assembling a metal securement member of the mounting device. In another aspect of the invention, a mounting device is disclosed. In another aspect of the invention, a method is disclosed for installing and using a mounting device in an aircraft.

Abstract: A test fixture for determining circumferential shear properties of an arcuate test specimen may include an outer fixture and an inner fixture. The outer fixture may be coupled to an outer side of the test specimen, and may be rotatably mounted on a central pin and may include a rocker arm. The inner fixture may be coupled to an inner side of the test specimen, and may be rotatably mounted on the central pin and may include a load arm extending in a direction opposite the rocker arm. The inner fixture and the outer fixture may be configured such that application of a test load to the rocker arm and the load arm causes rotation thereof about the central pin producing circumferential movement of the inner side relative to the outer side and inducing a circumferential shear load in the test specimen.

Abstract: An aerodynamic body operable to both promote laminar flow and satisfy structural requirements is disclosed. A perforated panel skin comprises an inner surface and an outer surface of the aerodynamic body. At least one hollow member is coupled to the inner surface and is operable to suction air from the outer surface and through the perforated panel skin. The at least one hollow member is oriented in a substantially chord-wise direction relative to an airflow over the aerodynamic body.

Abstract: An aerodynamic body operable to both promote laminar flow and satisfy structural requirements is disclosed. A perforated panel skin comprises an inner surface and an outer surface of the aerodynamic body. At least one hollow member is coupled to the inner surface and is operable to suction air from the outer surface and through the perforated panel skin. The at least one hollow member is oriented in a substantially chord-wise direction relative to an airflow over the aerodynamic body.

Abstract: A testing apparatus for characterizing a tension strength of a fillet bond of a test specimen may include a lower fixture and an upper fixture. The test specimen may include a skin component bonded to a stiffener component. The lower fixture may maintain the stiffener component in a fixed position. The upper fixture may engage the skin component at a pair of discrete engagement locations on opposite sides of the fillet bond. The upper fixture may be mechanically coupled to a gimbal joint and may substantially isolate the filet bond from asymmetric bending during application of a tension test load to the fillet bond.

Abstract: A testing apparatus for characterizing a tension strength of a fillet bond of a test specimen may include a lower fixture and an upper fixture. The test specimen may include a skin component bonded to a stiffener component. The lower fixture may maintain the stiffener component in a fixed position. The upper fixture may engage the skin component at a pair of discrete engagement locations on opposite sides of the fillet bond. The upper fixture may be mechanically coupled to a gimbal joint and may substantially isolate the filet bond from asymmetric bending during application of a tension test load to the fillet bond.

Abstract: A hybrid contoured load-spreading washer is disclosed. An illustrative embodiment of the washer includes a washer body having a composite layer and a metal layer bonded to the composite layer and a fastener opening extending through the washer body. A floor beam seat track attachment assembly and a method of transmitting a load from a seat track to a floor beam web in a seat track attachment assembly are also disclosed.

Abstract: A hybrid contoured load-spreading washer is disclosed. An illustrative embodiment of the washer includes a washer body having a composite layer and a metal layer bonded to the composite layer and a fastener opening extending through the washer body. A floor beam seat track attachment assembly and a method of transmitting a load from a seat track to a floor beam web in a seat track attachment assembly are also disclosed.

Abstract: The invention relates to a method of bonding two members together utilizing a stack of solid film adhesive and a layer of solid film adhesive, both disposed between the members. A pressure-applying device may be utilized to apply low pressure to force the members together. The pressure may force the stack to compress and expand in varying directions in order to substantially remove air-bubbles between the layer and one of the members. A heating device may be utilized to change the layer and the stack into liquid states in order to bond the members together with a void-free bond-line.

Abstract: The invention relates to a method of bonding two members together utilizing a stack of solid film adhesive and a layer of solid film adhesive, both disposed between the members. A pressure-applying device may be utilized to apply low pressure to force the members together. The pressure may force the stack to compress and expand in varying directions in order to substantially remove air-bubbles between the layer and one of the members. A heating device may be utilized to change the layer and the stack into liquid states in order to bond the members together with a void-free bond-line.

Abstract: An aerodynamic body operable to both promote laminar flow and satisfy structural requirements is disclosed. A perforated panel skin comprises an inner surface and an outer surface of the aerodynamic body. At least one hollow member is coupled to the inner surface and is operable to suction air from the outer surface and through the perforated panel skin. The at least one hollow member is oriented in a substantially chord-wise direction relative to an airflow over the aerodynamic body.

Abstract: Composite structural members and methods for forming the same are disclosed. In one embodiment, a composite structural member includes a central structural portion that extends in a first direction and having a first flange portion and a second flange portion that are spaced apart in a second direction perpendicular to the first direction by a web portion, the web portion further including a periodic or a non-periodic undulation extending in the first direction. A first reinforced polymer-based substrate is fixedly coupled to the first flange portion, and a second reinforced polymer-based substrate is fixedly coupled to the second flange portion.

Abstract: The invention relates to a mounting device in an aircraft. In one aspect of the invention, a method is disclosed for assembling a metal securement member of the mounting device. In another aspect of the invention, a mounting device is disclosed. In another aspect of the invention, a method is disclosed for installing and using a mounting device in an aircraft.

Abstract: The invention relates to a mounting device in an aircraft. In one aspect of the invention, a method is disclosed for assembling a metal securement member of the mounting device. In another aspect of the invention, a mounting device is disclosed. In another aspect of the invention, a method is disclosed for installing and using a mounting device in an aircraft.

Abstract: A fitting and an associated grommet are provided for supporting a conduit penetrating a panel and limiting energy transfer between the conduit and panel. The fitting may include a grommet having annular first and second sections spaced apart from one another and an annular wall extending between the first and second sections such that the wall and first and second sections define a bore. A plurality of ribs protrude from the annular wall, the ribs being distributed circumferentially around the annular wall and spanning between the first and second sections. A tubular liner extends through the bore of the grommet and contacts the first and second sections. The plurality of ribs extend into the bore, and at least some of the ribs contact the liner.