Abstract: A composite of I a prepreg made of a solid mixture of a reactive plastic resin and a reinforcing means in the form of a tissue or a fiber and II a removable release film comprising a multilayer structure of a) a release layer of at least one thermoplastic homo- or copolymer of ?,? unsaturated olefins and at least one wax-like compound as a release additive, b) optionally an adhesion promoting layer, c) a layer of at least one thermoplastic polyamide homo- or copolymer, d) optionally an adhesion promoting layer, e) a release layer of at least one thermoplastic homo- or copolymer of ?,? unsaturated olefins having a release coating based on a cured polysiloxane, f) a laminate adhesive layer, and g) a release layer of at least one thermoplastic polyester and a wax-like compound as a release additive.

Abstract: The invention relates to a wingtip extension comprising a leading edge and a trailing edge, which wingtip extension is affixable to an outer end of a wing, wherein the leading edge, at least in some sections, is essentially straight, and the straight section of the leading edge comprises a leading-edge sweep angle that exceeds the leading-edge sweep angle of the wing, and the local depth of the wingtip extension gradually decreases between a connecting region for connection to the wing and the outer end of the wingtip extension. By means of a wingtip extension according to the invention, in a delta wing a vortex burst region is positioned just behind the wingtip, as a result of which vortex burst region the cores of wingtip vortices burst and eventually become unstable, so that as a result of this the wake vortices of the aircraft can be reduced. The invention furthermore relates to a wing, comprising wingtip extensions according to the invention, as well as to an aircraft comprising such a wing.

Abstract: A composite of I a prepreg made of a solid mixture of a reactive plastic resin and a reinforcing means in the form of a tissue or a fiber and II a removable release film comprising a multilayer structure of a) a release layer of at least one thermoplastic homo- or copolymer of ?,? unsaturated olefins and at least one wax-like compound as a release additive, b) optionally an adhesion promoting layer, c) a layer of at least one thermoplastic polyamide homo- or copolymer, d) optionally an adhesion promoting layer, e) a release layer of at least one thermoplastic homo- or copolymer of ?,? unsaturated olefins having a release coating based on a cured polysiloxane, f) a laminate adhesive layer, and g) a release layer of at least one thermoplastic polyester and a wax-like compound as a release additive.

Abstract: A multilayer film is provided, including a layer sequence of a layer (a) of at least one low density polyethylene (LDPE) having a density in the range 0.915-0.930 g/cm3 or a mixture of LDPE with at least one other acyclic C2-C6 olefin polymer or copolymer, a layer (b) of a mixture of at least one low density polyethylene (LDPE) having a density in the range 0.915-0.930 g/cm3 and at least one cyclic olefin copolymer, and a layer (c) of at least one low density polyethylene having a density in the range 0.915-0.930 g/cm3 or a mixture of LDPE with at least one other acyclic C2-C6 olefin polymer or copolymer, such that the film's tear propagation force in both the machine direction and transverse to the machine direction is at most 1000 mN, per the Elmendorf test (per DIN EN ISO 6383-2).

Abstract: A transparent multi-layered film arrangement comprising at least three layers, wherein the film arrangement comprises one layer is made of a biodegradable polylactic acid (PLA) and a polyglycol as plasticizer, said polyglycol having a molecular weight of between 35,000 and 4,000,000, and at least two outer layers, each of said two outer layers being made of PLA.

Abstract: A measuring device for an aircraft is provided in order to determine physical properties of aerosol particles in real time. The device includes a heating device that separates volatile and solid aerosol particles, and a particle sensor that measures acquired data. The physical properties of the solid aerosol particles are determined with an analyzer. The determined analytical data is forwarded to other internal aircraft systems via a communication interface. Due to the formation of a measuring data or analytical data network with several airliners equipped with the measuring device, accurate and up-to-date information on the particle pollution, for example, along flight paths, can be obtained and used for defining no-fly zones, if so required.

Abstract: A wing for an aircraft includes a non-balanced lift gradient because as a result of at least one propeller slipstream flowing onto the wing the induced drag of the wing is increased. To reduce the increased induced drag, the wing comprises a first region with a reduced local wing camber and/or reduced local twist, and a second region with an increased local wing camber and/or increased local twist. The first region is defined as a wing surface situated downstream of the propeller slipstream, upstream of which wing surface the blades of the propeller move upwards. The second region is defined as a wing surface situated downstream of the propeller slipstream, upstream of which wing surface the blades of the propeller move downwards.

Abstract: A method for producing a biodegradable plastic film or a composite film, and the film obtained by such method. The film has barrier properties and is made at least of a biodegradable basic plastic material and a second plastic material having barrier properties. The film is useful in particular for packaging sensitive goods.

Abstract: The invention relates to a wingtip extension comprising a leading edge and a trailing edge, which wingtip extension is affixable to an outer end of a wing, wherein the leading edge, at least in some sections, is essentially straight, and the straight section of the leading edge comprises a leading-edge sweep angle that exceeds the leading-edge sweep angle of the wing, and the local depth of the wingtip extension gradually decreases between a connecting region for connection to the wing and the outer end of the wingtip extension. By means of a wingtip extension according to the invention, in a delta wing a vortex burst region is positioned just behind the wingtip, as a result of which vortex burst region the cores of wingtip vortices burst and eventually become unstable, so that as a result of this the wake vortices of the aircraft can be reduced. The invention furthermore relates to a wing, comprising wingtip extensions according to the invention, as well as to an aircraft comprising such a wing.

Abstract: Film arrangement (1) having at least one film layer, wherein the film arrangement is produced at least from one film layer (3) made of a biodegradable PLA and a long-chain plasticizer.

Abstract: The present invention relates to an aircraft with wings whose maximum lift can be altered by controllable wing components. By means of a regulating device, depending on flight state parameters and the actually measured load on the wings, wing components are acted upon such that, as a precautionary measure, the maximum possible aerodynamic lift does not exceed a desired upper limit value.

Abstract: A wing for an aircraft includes a non-balanced lift gradient because as a result of at least one propeller slipstream flowing onto the wing the induced drag of the wing is increased. To reduce the increased induced drag, the wing comprises a first region with a reduced local wing camber and/or reduced local twist, and a second region with an increased local wing camber and/or increased local twist. The first region is defined as a wing surface situated downstream of the propeller slipstream, upstream of which wing surface the blades of the propeller move upwards. The second region is defined as a wing surface situated downstream of the propeller slipstream, upstream of which wing surface the blades of the propeller move downwards.

Abstract: Process for the production of an extruded mono- or multilayer plastic film, where at least sections of the plastic film are provided with a pattern during or after extrusion, and use of a film produced by this process for packaging purposes.

Abstract: The present invention relates to an aircraft with wings whose maximum lift can be altered by controllable wing components. By means of a regulating device (20), depending on flight state parameters and the actually measured load on the wings (10), wing components (11, 12) are acted upon such that the maximum possible aerodynamic lift does not exceed a desired upper limit value.

Abstract: A method of reducing the bending moment effect of wind gust loads acting on the wing of an aircraft involves adjusting the aerodynamic configuration of the wing so as to alter the distribution of lift generated by the wing during phases of flight in which critical wind gusts are expected to occur. Particularly, during climb and descent phases of flight below cruise altitude, the lift generated by outboard portions of the wings is reduced while the lift generated by inboard portions of the wings is increased. Thereby, the 1 g basis load acting on the outboard portions of the wings is reduced, and consequently the total load applied to the outboard portions of the wings, resulting from the 1 g basis load plus the additional wind gust load, is correspondingly reduced. This leads to a reduction of the bending moments effective on the wings, and of any rolling moment effective on the aircraft.