The present invention relates to sandwich panels used as aircraft interior parts. In addition to provide a finishing function, the sandwich panels need to have certain mechanical properties and have sufficient fire resistance to retard the spread of fire within the vehicle interior. The present invention provides an aircraft interior panel with skins comprising natural fiber reinforced composites based either on an inorganic thermoset resin or a thermoplastic resin. Such panels provide the required flame and heat resistance, allow easy recycling and disposal, are cheaper and offer significant weight savings over conventional sandwich panels.

A method for manufacturing a lining panel with an integrated electrical connector for a lining of a passenger cabin of an aircraft or spacecraft. An additive manufacturing (AM) or 3D printing technique is used to laterally form electrically conductive pins on a panel body of the lining panel to provide an electrical connector. The electrically conductive pins connect to electric lines attached to or formed on or into the panel body. A lining panel with an integrated electrical connector for a lining of a passenger cabin of an aircraft or spacecraft is disclosed. The lining panel has a panel body, electric lines attached to or formed on or into the panel body, and an electrical connector with electrically conductive pins formed laterally on the panel body of the lining panel using an AM or 3D printing technique. The electrically conductive pins are configured to connect to the electric lines.

An aviation laminate includes an intumescent backer sheet covered by a decorative sheet. The aviation laminate is generally fire-resistant, may be structural, and may be used to construct various components within an aircraft cabin that may be held to government/regulatory fire mitigation requirements.

An interior trim arrangement for an aircraft cabin, having lateral ceiling elements, and an angled element having limbs limb extending from one another, one lateral ceiling element arranged offset upwardly and to a first side, the angled element arranged with the first limb adjoining a lateral ceiling element towards the first side, the free end of the first limb located opposite the free end, towards the first side, of a lateral ceiling element, the other limb extending towards the other lateral ceiling element, the free end of the second limb spaced apart from the first free end, towards a lateral ceiling element, of the other lateral ceiling element, a light source for the other lateral ceiling element between the free end of the second limb and the first free end, towards a lateral ceiling element, of the other lateral ceiling element, and the angled element having a lighting element.

A self-releasing panel support latch allows easy installation of an aesthetic panel, for example a ceiling panel, over an access opening in an aircraft interior and easy removal of the panel from over the opening without the use of any tools or release mechanisms.

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.

An arrangement in the cabin of a vehicle includes a floor, a first equipment component, a second equipment component and a partitioning device. The partitioning device is set up to provide a wall surface between the first equipment component and second equipment component largely perpendicular to the floor. The partitioning device is positionable in at least two positions along a length running between the first equipment component and second equipment component. The partitioning device is lockable in its respective position on at least one of the floor, a cabin ceiling and a cabin lining.

An insulation component to be attached to a fuselage structure of an aircraft. The insulation component extends in a planar manner, and at least one peripheral recess, running transversely to the at least one longitudinal recess, is formed in a first surface of the insulation component configured to receive a respective associated peripheral support of the fuselage structure.

A structural panel may be configured for attenuating noise. This panel includes a first skin, a second skin and a core forming a plurality of cavities vertically between the first skin and the second skin. The core may include a wall connected to and extending vertically between the first skin and the second skin. The wall may be laterally between and fluidly separate at least a first of the cavities from a second of the cavities. The wall may include a vertical stiffener. One or more perforations in the first skin may be fluidly coupled with the first of the cavities.

An interior component carrier system for use in assembly of aircraft interior components in an aircraft includes a retaining system with at least one retaining element. A first connection device for connecting the retaining element to a first aircraft interior component and a second connection device are provided on the retaining element. On the retaining element a structural retainer is provided for fastening the retaining element to an aircraft structure. The interior component carrier system includes a hinge connectable to a second and a third aircraft interior component such that the third aircraft interior component is pivotable about a longitudinal axis of the hinge relative to the second aircraft interior component. The second connection device mounted on the retaining element is configured to be connected to the hinge and/or to a region of the second or third aircraft interior component, that is adjacent to the hinge.