An interior/exterior covering member for an automobile having excellent sound-absorbing performance is provided. The interior/exterior covering member includes an air-permeable fiber layer 2 and a thermoplastic resin layer 3 laminated on one surface of the fiber layer 2. The melt flow rate of the thermoplastic resin is in a range of 2 g/10 min to 500 g/10 min, and a plurality of through-holes 11 penetrating the resin layer in the thickness direction is formed in the thermoplastic resin layer 3.

A bonding method bonds a buffer member to an adherend member, and includes: an adhesive application step of applying an adhesive to a part of the buffer member, the part being bonded to the adherend member; a first heating step of heating a part of the adherend member, the part being bonded to the buffer member; a second heating step of heating the part of the adherend member after the first heating step; and an attachment step of attaching the buffer member to the adherend member after the second heating step.

A method for coupling a tube to a tube fitting includes radially outwardly expanding a tubular compression collar from a constricted state to an expanded state, the compression collar having a throughway extending there through and being made of a resiliently flexible material. An end of the tube is inserted within the throughway of the expanded compression collar, the tube bounding a passageway. A tube fitting is inserted within the passageway of the tube. The compression collar is allowed to resiliently rebound back towards the constricted state so that the compression collar pushes the tube against the tube fitting.

According to one implementation, a composite material structure includes a first member and a second member. The first member has at least one first bonded surface. The second member has at least one second bonded surface to be bonded to the at least one first bonded surface. The second member is made of a composite material. At least one surface formed by fibers forming the composite material is used as the at least one second bonded surface by disposing end portions of the fibers, in the first member side, inside the composite material.

A method for forming a connection between two tubular sections having a polymeric outer surface jacket, using electrofusion to fusion bond a casing of similar, non-crosslinked polymer to the outer surface of the tubular sections.

Embodiments provide a method for forming a groove on a pile encapsulation jacket to form an interlocking joint on the pile encapsulation jacket. A spacer may be used to form the groove. First, a pile jacket laminate is formed on a mandrel surface. The pile jacket laminate may be partially cured to have a solid but sticky surface. The spacer may be placed on the pile jacket laminate. An additional layer of laminate may be formed on at least a portion of the pile jacket laminate and at least a portion of the spacer. The entire structure may be cured and the spacer may be removed. A groove is formed between the pile jacket laminate and the additional layer of laminate at a space previously occupied by the spacer. The groove has the same width as the portion of the spacer that was covered with the additional layer of laminate.

A method of manufacturing a hollow composite structure is provided. The method includes curing a first portion of the hollow composite structure having at least one open region and at least one wall, the at least one wall partially defining a hollow interior. The method also includes bonding a laminate shell to the first portion of the hollow composite structure proximate to at least one location of the wall to cover the open region and enclose the hollow interior. The method further includes disposing a second portion of the hollow composite structure over the laminate shell, the second portion comprising a plurality of plies. The method yet further includes curing the first portion and the second portion during a final cure.

The disclosure relates to a component device, in particular for a primary supporting component of an aircraft, the component device having a first component element, a second component element, a bonding providing a connection between the first component element and the second component element, and a detector device having at least one interior space sensor device configured to measure a change in a pressure and/or a concentration of a gas surrounding the interior space sensor device. The first component element, the second component element, and the bonding confine an interior space. The interior space sensor device is arranged in the interior space.

The disclosure relates to a component device, in particular for a primary supporting component of an aircraft, which comprises a first component element, a second component element, a bonding providing a connection between the first component element and the second component element, a marker substance device configured to dispense a volatile marker gas to the environment when in contact with the surrounding air and being hermetically sealed from the surrounding air by the first component element, the second component element, and/or the bonding if the bonding is not damaged, and a detector device configured to detect the marker gas dispensed by the marker substance device.

A composite structure is fabricated by staging at least a portion of an uncured, first composite component. The first composite component is assembled with a second composite component, and the staged portion of the first composite component is cocured with the second composite component.