Airbus Operations Gmbh

Martin Gerber

Freerk Syassen

Geza Schrauf

Bernd Räckers

An flow body comprises a curved suction skin having a first perforation, a leading edge and two skin sections extending therefrom, wherein each skin section has an outer end facing away from the leading edge, an interior suction duct having a second perforation and extending through an inside of the curved suction skin in a distance from the leading edge, and two sidewall members, connected to the outer ends, wherein the sidewall members are made of a composite material. The suction skin comprises a profiled contour shape, which determines a pressure distribution over at least one of the two skin sections when air flows over the curved suction skin, wherein the pressure distribution comprises a stagnation point, a suction peak and a subsequent local pressure maximum downstream of the suction peak, wherein the first perforation extends from a stagnation point on the suction skin to the local pressure maximum.

Flow body, method for manufacturing a flow body and aircraft having such a flow body

An aircraft with a fuselage, wings, horizontal stabilizers and a vertical stabilizer, wherein on a front portion of the vertical stabilizer an elongated one-piece nose element is mounted which forms lateral air guide surfaces. To the front end of the nose element a perforated metal plate nose member is attached. The front end of the nose element being closed and between this closed front end and the nose member an elongated air channel is formed.

Leading edge nose structure on the vertical stabilizer of an aircraft

A method for manufacturing a shell element reinforced with support elements comprises providing a skin element that has an outer surface and an inner surface opposite the outer surface, providing a first support element that has an attaching side and a free side opposite the attaching side, attaching the first support element on the skin element such that the attaching side of the first support element faces the inner surface of the skin element. A first recess is introduced into the first support element that proceeds from the free side of the first support element and extends transversely to the first axis. A second support element is provided that has a support side and a front side opposite the support side. The second support element is inserted into the first recess of the first support element such that the support side faces the inner surface of the skin element.

Method for manufacturing a shell element reinforced with support elements

A profile plate portion is disclosed for use as an outer wall of a flow body including a first profile plate panel that is fluid permeable, a second profile plate panel extending along the first profile plate panel, and a reinforcing device for supporting the first profile plate panel and the second profile plate panel on one another. Fluid can flow through the reinforcing device, and/or fluid of the flow present at the first profile plate panel, which flows through the first profile plate panel, can flow through the reinforcing device in the local profile plate thickness direction from the first profile plate panel to the second profile plate panel and in some regions can flow through to an inside that is situated opposite the flow side. A method is disclosed for manufacturing a profile plate portion and a flow body component with a suction-extraction device for fluid.

Profile plate portion for use as an outer wall of a flow body, method for manufacturing a profile plate portion and flow body component comprising a suction-extraction device for fluid

A device for boundary layer suction on the outer skin of an aircraft, on which outer skin a surface where drawing off by suction can take place comprising openings is connected to a suction source by way of at least one suction line, wherein the surface where drawing off by suction can take place is formed by at least one panel-shaped composite component that comprises an extruded profile, made of light metal, as a base body, which extruded profile comprises several suction channels that are open towards the outer skin, onto which base body, for the purpose of forming the outer skin, a micro-perforated metal cover sheet has been applied in the region of the surface where drawing off by suction can take place.

Device for boundary layer suction and composite component therefor

A flow body is disclosed, particularly for aircraft. The flow body includes an outer side impinged on in a predetermined manner by a fluid in a direction of impinging flow, the flow body having on its outer side at least one flow control device including micro-perforations arranged in at least one segment of the outer side, at least one connecting passage communicated with the micro-perforations via at least one suction chamber so fluid flowing through the micro-perforations flows via the suction chamber into the connecting passage, at least one suction device having a first inlet communicated with the connecting passage, a second inlet communicated with at least one ram fluid feed line, wherein the ram fluid feed line is in a region of the flow body opposite to the direction of impinging flow of the flow body, and an outlet device for discharging the fluid.

Growing community of inventors

Bremen, Germany

Martin Gerber