A holding device for a wall module 10 of the cabin lining in an aircraft includes two different clamping devices. The first clamping device 30 has a clamping body 33 having a first clamping jaw 31, which is fixed relative to the clamping body, and a second clamping jaw 32, which is movable relative to the clamping body 33, which in turn is operatively connected or can be temporarily connected to an actuating lever 35. In the closed state, the clamping jaws 31, 32 form a receiving space 36 for the wall module 10. An interlocking device 37 fixes the position of the clamping jaws 31, 32 relative to one another in the closed state.

A fairing assembly for an aerial vehicle having a tank that forms a body of the vehicle and a wing coupled to the tank is provided. The fining assembly includes a substructure configured to couple with a tank skin of the tank, a thermal protection system coupled to the substructure, and a seal assembly coupled to the substructure, the seal assembly being configured to overlap at least a portion of an edge of the wing.

A device for securing at least one thermal protection mat to an internal fixed structure of a nacelle includes at least one removable fastening element for securing the at least one thermal protection mat to the internal fixed structure designed to be arranged between the mat and the internal fixed structure. The device includes at least one gripping element connected to the removable fastening element to project relative to the mat on the opposite side to the internal fixed structure, the removable fastening element being intended to be detached from the internal fixed structure by a pulling force exerted on the gripping element.

A sealable securing system and method include a hook member including a first seal. The hook member is configured to be secured to a first component. A first alignment member coupled to the hook member. A loop member includes a second seal. The loop member is configured to be secured to a second component. A second alignment member coupled to the loop member. The first alignment member coupled to the second alignment member verifies that the first seal of the hook member sealingly engages the second seal of the loop member.

An aircraft interior lining component is formed at least partially of a thermoplastic foam material and includes a first surface which faces an interior of an aircraft cabin when the aircraft interior lining component is mounted in an aircraft, and a second surface which faces away from the interior of the aircraft cabin when the aircraft interior lining component is mounted in an aircraft. The second surface of the aircraft interior lining component includes at least one supporting section and at least one surface section adjacent to the supporting section and recessed relative to the supporting section. The supporting section is dimensioned and arranged so that it is supported, when the aircraft interior lining component is mounted in an aircraft, on an element of a primary structure of the aircraft at least when a predetermined load acts on the first surface of the aircraft interior lining component.

A device for fixing cabin side wall and cabin light paneling to a structural component of an aircraft and spacecraft includes: a structure holding component; and a cabin side wall holding component. The structure holding component has a surface for fixing the holding component to the structural component, and an adjustable surface for fixing the side wall holding component. The side wall holding component has an intermediate bracket and a side wall receiver for fixing cabin side wall paneling. The intermediate bracket is arranged between the adjustable fixing surface and the side wall receiver. The intermediate bracket has an intermediate guide element which guides the intermediate bracket, and the side wall receiver has a receiver guide element which guides the side wall receiver. The intermediate bracket has a fixing element for locking the intermediate bracket, and the side wall receiver has a fixing element for locking the side wall receiver.

A mounting bracket assembly is configured to securely couple to a structure. The mounting bracket assembly includes a securing cradle defining a securing chamber, a pivot arm that pivotally couples to the securing cradle through a first hinge, and a locking arm that pivotally couples to the pivot arm through a second hinge. The pivot arm and the locking arm are configured to pivotally move via the first hinge and the second hinge into an over-center securing position within the securing chamber to securely lock the mounting bracket assembly to the structure.

In order to facilitate the thermoacoustic insulation of an aircraft portion, a method for manufacturing a thermoacoustic insulation module for an aircraft comprises a step of providing a mat configured to provide thermoacoustic insulation of an aircraft portion, followed by a step of attaching a bendable structure to the mat, followed by a step of bending the bendable structure, along a bending axis parallel to a longitudinal direction of the mat, such that the bendable structure forms a load-bearing structure supporting the mat in a curved shape.

In order to facilitate the thermoacoustic insulation of an aircraft portion, a thermoacoustic insulation module for an aircraft comprises a mat and a load-bearing structure detachably attached to the mat and supporting the mat in a curved shape, with an axis of curvature parallel to a longitudinal direction of the mat. A thermoacoustic insulation method for insulating an aircraft portion comprises a step of inserting the thermoacoustic insulation module into the aircraft portion, followed by a step of detaching the mat from the load-bearing structure, followed by a step of attaching the mat to an aircraft structure delimiting the aircraft portion, followed by a step of removing the load-bearing structure from the aircraft portion.

The invention relates to a method of fastening panels to a substrate, and a fastener, accordingly there is a method of fastening a panel to a substrate, comprising the steps of i. providing on the substrate a first projection, ii. attaching a fastener which comprises an elongate projection, to said first projection, wherein said fastener comprises an elongate projection, wherein the elongate projection is longer than said first projection, iii. attaching a panel onto said elongate projection,