Abstract: The invention relates to a window unit W for aircraft cabins, comprising an outer window frame 1, an inner window frame 3, a window pane 2 lying between them, and possibly having a sun-visor 4, a roller blind 34 or the like arranged between the inner window frame 3 and a possible covering frame 5, the window unit W being insertable into the opening 7 in a side-wall panel 6 or the like in the aircraft cabin. In order to make it possible for the window unit W to be rapidly and simply installed and removed, the invention makes provision for the window unit W to have a centering device and at least two snap fastenings 13, advantageously with locking devices, to detachably connect it to the side-wall panel 6, or to components connected thereto, the side-wall panel 6, or components connected thereto, having any necessary mating parts for the centering device for the snap fastenings 13.

Abstract: A device for releasably fastening covering panels, in particular ceiling panels in aircraft, on a load-bearing structure, having at least two fastening elements. In order to make it possible for the covering panels to be removed and fastened quickly and easily without the aid of tools, and for loose constituent parts to be avoided, it is provided that all the constituent parts of the fastening elements are connected either to the covering panel and/or to the load-bearing structure, and that all those constituent parts of the fastening elements which are connected to the covering panel are arranged exclusively on that side of the covering panel which is directed toward the load-bearing structure, and that at least one fastening element is designed as a movable bearing, e.g. as a bolt, for absorbing the forces which act essentially perpendicularly with respect to the covering panel, and at least one fastening element is designed as a fixed bearing, e.g.

Abstract: In order to provide a container 1 having a door 2, in particular a luggage compartment for aircraft, the door 2 being mounted via at least one hinge or the like on the container 1 such that it can pivot, having an apparatus for assisting the movement of the door 2 into the open position and for holding the door 2 in the open position, and having an apparatus for holding the door 2 in the closed position, in the case of which container the structural components have as small a physical size as possible and thus occupy as little volume in the container 1 as possible. It is provided that the apparatus for assisting the movement of the door 2 and, possibly, an apparatus for damping the movement of the door 2 are arranged essentially around the pivoting axis of the door 2. The components relating to this are ideally integrated in the or each hinge. The damping of the movement of the door 2 advantageously reduces as the opening angle .alpha.

Abstract: Woven or non-woven fabric, in particular for the manufacture of prepregs especially for the manufacture of structural components in the aviation industry, manufactured of fibers, preferably carbon fibers having an elasticity modulus in excess of 80 000 N/mm.sup.2, preferably of 200 000 N/mm.sup.2 and a specific gravity of preferably 1,5 g/cm.sup.3, and not more than 2,1 g/cm.sup.3, wherein the fibers are composed of mono-filaments, and the fibers and therefore also the fabrics have been pressed flat, preferably calendered. In order to produce a woven or non-woven fabric which is mechanically particularly strong and yet can be manufactured economically, each fiber is composed of at least 2000, preferably 3000 individual mono-filaments (3K=200 tex=200 g/1000 m). The woven or non-woven fabric is preferably used for the manufacture of prepregs and henceforth for lightweight structural components especially for the aviation industry and in particular for overhead luggage compartments.

Abstract: A component for cladding apertures in the fuselage of an aircraft is to be of lighter weight and more corrosion resistant as compared with known claddings. The component is manufactured of carbon fibre reinforced curable synthetic resin and comprises a base layer (2) onto which U-profiles (4, 4') and L-profiles (5, 5') are placed in spaced apart interrelationship, which during the manufacture are held in place by a grid (14) comprising angular bridge members. A vacuum foil 7 is applied over this assembly and is adhesively bonded along the edges of the base layer (2') to the supporting surface (1). The space between the vacuum foil (7) and the supporting surface (1) is evacuated and curing proceeds at an elevated temperature and pressure. After complete curing the vacuum foils (7) and the grid (14) are removed.

Abstract: In a pipe line for an engine, in particular a cooling line in aircraft construction, the walls of the pipe line are composed of a load-bearing inner layer (2) of fibre reinforced, curable synthetic resin and of a heat insulating outer layer (3) of fibre reinforced curable synthetic resin, bonded to the inner layer (2). For the production of the two layers (2, 3) a removable core (1) is used, for example composed of a low melting metal alloy.