A fastening system including a structure holding element fastenable to a structural component. The fastening system includes a component holding element fastenable to a component to be fastened and movable relative to the structure holding element between first and second operating positions. A first lever element is connected to the structure holding element to be rotatable about a first rotation axis and is connected to the component holding element to be rotatable about a second rotation axis. The fastening system includes a connection element, connected to the component holding element to be rotatable about a third rotation axis and connected to the structure holding element to be displaceable in translation relative to the structure holding element, such that the second rotation axis, when the component holding element is transferred from its first into its second operating position, is displaced in a plane extending perpendicularly to the second rotation axis.

An aircraft cabin section includes a door frame, which forms a door opening, a passenger door, which is arranged on the door frame and is configured to close the door opening, and a door insulation arrangement, which is larger in at least one direction than the door opening. The door insulation arrangement is produced from a textile which is heat-insulating and/or airflow-inhibiting. Furthermore, a corresponding door insulation arrangement and an aircraft having such an aircraft cabin section or such a door insulation arrangement are disclosed.

A self-perforating spacer has a first part and a second part, the first part including a through-seat, the first and second parts being designed to be assembled together and the self-perforating spacer including a cutting system that cuts when the self-perforating spacer is assembled. A method for assembling a self-perforating spacer on an insulation blanket and an insulation blanket fitted with at least one self-perforating spacer is also described.

A component holder, in particular for aircraft, for indirectly securing components to the fuselage or body shell. The component holder has a base portion and an attachment element which is lockable to the base portion and has a component receiving member arranged thereon. The base portion has a circular shell form, and the upper edge has retention and locking elements. The lockable attachment element has a s dome-like basic structure, and the lower edge region has retention and locking elements which complement those of the base portion and are lockable therewith. The component receiving member is formed integrally on the attachment element and arranged at a dome zenith on the outer side. The dome is formed from at least three frames which are angularly offset on the circumference. The frames extend from the dome lower edge region to the base location of the component receiving member at the dome zenith.

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.

A fastener assembly for affixing insulation blankets to a substrate is provided. The fastener assembly includes an attachment member having a construction for affixing to a substrate as well as a first fastener member preferably in the form of a male threaded stud. The fastener assembly further includes a cap fastener. The cap fastener includes a cap member and a second fastener member preferably in the form of a female threaded extension for threadably affixing to the first fastener member. The cap member has an exterior side and an interior side. The cap member's exterior side preferably has a shape for rotation by a tool. Meanwhile, the cap member's interior side has a circular recess concentric with the cap fastener's female threaded extension. When assembled, the circular recess forms a circular insulating cavity between the cap member and an insulation blanket.

A connection system includes two connecting elements each having a respective connecting flange on which a plurality of coupling elements are arranged along a peripheral direction and which has a substantially round external profile; and a coupling belt, on which a plurality of opposing coupling elements are arranged which are configured to form a positive-locking connection with the coupling elements of the two connecting elements for the mutual rotation-proof fixing of the two connecting elements.

A mounting clip may be provided that is configured to be secured to a stiffener and provide attachment of external components to the stiffener. In one example, the mounting clip includes a frame with a base and legs. Opposing engagement members extend from the legs. The opposing engagement members each include a pair of deformable flexures and a pad, which engages a surface of the stiffener. The stiffener may be inserted into a channel defined by engagement members and translated upwards, thus, translating the pads upward and inward. Subsequently, the pads and deformable flexures provide a compressive clamping stress on the stiffener and therefore permanently secure the mounting clip to the stiffener.

A thermal expansion includes a bottom portion extending between a support structure and a trailing edge, and the support structure is positioned proximate to a heat source. Furthermore, the thermal expansion joint includes a side portion. In some embodiments, the thermal expansion joint includes an overlapping portion coupled to the bottom portion and extending from a flange portion towards the side portion. Moreover, the overlapping portion overlays and is biased against the side portion to enable thermal expansion during heating by extending towards the flange portion and sliding along a top surface of the side portion.

Systems and methods for noise suppression for aircraft are disclosed. The aircraft may include a fuselage. The aircraft may include a plurality of wings connected to or formed with the fuselage. The aircraft may include at least one engine configured to generate a propulsion force to propel the aircraft. The at least one engine may include a nozzle assembly having a nozzle body with an outlet that releases an exhaust air or a jet flow. The aircraft may include a noise suppression assembly. The noise suppression assembly may be configured to interact with the exhaust air or jet flow to substantially suppress, mitigate, reduce, or otherwise modify noise generated by the aircraft.