Patents by Inventor Gerd Heller
Gerd Heller has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 10995780Abstract: An assembly for arrangement to the surface of an aerodynamic profile comprises an array of actuators, which are designed as piezo actuators and plasma actuators.Type: GrantFiled: November 30, 2017Date of Patent: May 4, 2021Assignees: Airbus Defence and Space GmbH, Airbus Operations GmbHInventors: Ralf Caspari, Robert Weichwald, Emanuel Ermann, Gerd Heller, Detlev Konigorski, Stefan Schnäubelt, Nicole Jordan
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Patent number: 10946951Abstract: An aircraft (5) including a wing (3) and a winglet (1) at the end of the wing, the winglet including: a root (7); a tip (9); a transition region (11) extending away from the root; and a wing-like region (13) extending from the distal end of the transition region to the tip. When the aircraft wing (3) is under the worst-case static loading, the tip of the winglet is located at the maximum spanwise extent of the winglet (1), but when the aircraft wing (3) is under the no-load condition, the wing-like region (13) is canted inboard such that the tip (9) of the winglet (1) is located inboard of the maximum spanwise extent of the winglet.Type: GrantFiled: February 20, 2018Date of Patent: March 16, 2021Assignees: AIRBUS OPERATIONS LIMITED, AIRBUS OPERATIONS GMBHInventors: Ben Commis, Christopher Wright, Kasidit Leoviriyakit, Gerd Heller
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Patent number: 10821486Abstract: A microelectronic module for cleaning a surface is described. The microelectronic module comprises at least one voltage converter for converting a provided first voltage into a higher, lower, or identical second voltage. The module also comprises at least one actuator. The actuator comprises at least one generator for generating an ionic current, an electrical plasma, harmonic components and/or an electrostatic field from the second voltage which is provided by the voltage converter. At least the voltage converter and the actuator are disposed on a thin-film, planar substrate. At least most of at least one object adhering to the surface is removed by the actuator.Type: GrantFiled: November 4, 2016Date of Patent: November 3, 2020Assignees: Airbus Defence and Space GmbH, Airbus Operations GmbHInventors: Ralf Caspari, Robert Weichwald, Emanuel Ermann, Gerd Heller
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Patent number: 10472052Abstract: An aircraft flow body includes a flow surface exposed to an airstream during flight, at least one structural component attached to an interior of the flow surface, at least one perforated area having a plurality of openings extending through the flow surface, a manifold positioned interior to the flow surface in fluid communication with the openings and upstream of the at least one structural component, and at least one suction duct having a first end in communication with the manifold and a second end placed exterior to the flow surface downstream of the structural component. The at least one suction duct includes a suction opening facing away from the first end and adapted for inducing a suction force into the at least one suction duct when the flow surface is exposed to the airstream during flight, thereby inducing a flow of air from through the openings to the suction opening.Type: GrantFiled: January 24, 2017Date of Patent: November 12, 2019Assignee: Airbus Operations GmbHInventor: Gerd Heller
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Publication number: 20180237162Abstract: A method of designing a winglet (3) for an aircraft (7) including: defining the location of the winglet root; defining a maximum height for the winglet tip; defining a maximum span for the winglet; creating the winglet shape by locating the winglet root (13?), locating the winglet tip (15?) at the location of maximum height and maximum span, and connecting the winglet root (13?) to the winglet tip (15?) using a winglet shape. The winglet shape includes a curved transition region (17?) extending away from the root, and a wing-like region extending from the distal end of the transition region (17?) to the winglet tip (15?). The step of creating the winglet shape includes iteratively changing the curvature and/or the location of the center of the curvature of the transition region, whilst maintaining the locations of the winglet root and winglet tip.Type: ApplicationFiled: February 20, 2018Publication date: August 23, 2018Inventors: Christopher WRIGHT, Ben COMMIS, Kasidit LEOVIRIYAKIT, Gerd HELLER
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Publication number: 20180237128Abstract: An aircraft (5) including a wing (3) and a winglet (1) at the end of the wing, the winglet including: a root (7); a tip (9); a transition region (11) extending away from the root; and a wing-like region (13) extending from the distal end of the transition region to the tip. When the aircraft wing (3) is under the worst-case static loading, the tip of the winglet is located at the maximum spanwise extent of the winglet (1), but when the aircraft wing (3) is under the no-load condition, the wing-like region (13) is canted inboard such that the tip (9) of the winglet (1) is located inboard of the maximum spanwise extent of the winglet.Type: ApplicationFiled: February 20, 2018Publication date: August 23, 2018Inventors: Ben COMMIS, Christopher WRIGHT, Kasidit LEOVIRIYAKIT, Gerd HELLER
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Patent number: 9988142Abstract: A wing for an aircraft, including a main wing and a wing tip device, a front blade and a rear blade of the wing tip device extending from an attachment end, a front blade leading edge extending in front of a rear blade leading edge and a front blade trailing edge extending in front of a rear blade trailing edge, in a chord direction, and at a front blade tip the front blade extending under a different dihedral angle than the rear blade at a rear blade tip. The front blade leading and trailing edges, as well as the rear blade leading and trailing edges have a tangent-continuous developing. The front blade leading edge extends tangent-continuously with the wing leading edge. The rear blade trailing edge extends tangent-continuously with the wing trailing edge. The front blade trailing edge extends behind the rear blade leading edge, in the chord direction.Type: GrantFiled: March 15, 2017Date of Patent: June 5, 2018Assignee: Airbus Operations GmbHInventor: Gerd Heller
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Publication number: 20180149178Abstract: An assembly for arrangement to the surface of an aerodynamic profile comprises an array of actuators, which are designed as piezo actuators and plasma actuators.Type: ApplicationFiled: November 30, 2017Publication date: May 31, 2018Inventors: Ralf CASPARI, Robert WEICHWALD, Emanuel ERMANN, Gerd HELLER, Detlev KONIGORSKI, Stefan SCHNÄUBELT, Nicole JORDAN
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Publication number: 20170247105Abstract: A wing for an aircraft, including a main wing and a wing tip device, a front blade and a rear blade of the wing tip device extending from an attachment end, a front blade leading edge extending in front of a rear blade leading edge and a front blade trailing edge extending in front of a rear blade trailing edge, in a chord direction, and at a front blade tip the front blade extending under a different dihedral angle than the rear blade at a rear blade tip. The front blade leading and trailing edges, as well as the rear blade leading and trailing edges have a tangent-continuous developing. The front blade leading edge extends tangent-continuously with the wing leading edge. The rear blade trailing edge extends tangent-continuously with the wing trailing edge. The front blade trailing edge extends behind the rear blade leading edge, in the chord direction.Type: ApplicationFiled: March 15, 2017Publication date: August 31, 2017Inventor: Gerd Heller
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Publication number: 20170217568Abstract: An aircraft flow body includes a flow surface exposed to an airstream during flight, at least one structural component attached to an interior of the flow surface, at least one perforated area having a plurality of openings extending through the flow surface, a manifold positioned interior to the flow surface in fluid communication with the openings and upstream of the at least one structural component, and at least one suction duct having a first end in communication with the manifold and a second end placed exterior to the flow surface downstream of the structural component. The at least one suction duct includes a suction opening facing away from the first end and adapted for inducing a suction force into the at least one suction duct when the flow surface is exposed to the airstream during flight, thereby inducing a flow of air from through the openings to the suction opening.Type: ApplicationFiled: January 24, 2017Publication date: August 3, 2017Applicant: Airbus Operations GmbHInventor: Gerd Heller
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Publication number: 20170144199Abstract: A microelectronic module for cleaning a surface is described. The microelectronic module comprises at least one voltage converter for converting a provided first voltage into a higher, lower, or identical second voltage. The module also comprises at least one actuator. The actuator comprises at least one generator for generating an ionic current, an electrical plasma, harmonic components and/or an electrostatic field from the second voltage which is provided by the voltage converter. At least the voltage converter and the actuator are disposed on a thin-film, planar substrate. At least most of at least one object adhering to the surface is removed by the actuator.Type: ApplicationFiled: November 4, 2016Publication date: May 25, 2017Inventors: Ralf CASPARI, Robert WEICHWALD, Emanuel ERMANN, Gerd HELLER
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Patent number: 9555874Abstract: A fixed wing of an aircraft, having a main wing extending over a half-span with a wing box including spars extending along the spanwise direction of the main wing, ribs arranged one in back of the other viewed in the spanwise direction, and an outer skin. The wing box includes a wing box base section (K10) and a wing box adapter section, that forms the outer end area of the wing box, as viewed from the wing root, and is designed to secure a wing tip device. In its nominal state of construction, the dihedral angle of the wing box adapter section referring to the respective local spanwise direction continuously increases by at most 60 degrees from the outer rib of the wing box base section (K10) up to the outermost rib of the wing box adapter section.Type: GrantFiled: May 15, 2015Date of Patent: January 31, 2017Assignees: Airbus Operations GmbH, Airbus Operations Ltd.Inventors: Gerd Heller, Alexander Buescher, Frank Theurich, Tom Gibson, Michael Karwin, Stephen Powell
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Publication number: 20150321746Abstract: A fixed wing of an aircraft, having a main wing extending over a half-span with a wing box including spars extending along the spanwise direction of the main wing, ribs arranged one in back of the other viewed in the spanwise direction, and an outer skin. The wing box includes a wing box base section (K10) and a wing box adapter section, that forms the outer end area of the wing box, as viewed from the wing root, and is designed to secure a wing tip device. In its nominal state of construction, the dihedral angle of the wing box adapter section referring to the respective local spanwise direction continuously increases by at most 60 degrees from the outer rib of the wing box base section (K10) up to the outermost rib of the wing box adapter section.Type: ApplicationFiled: May 15, 2015Publication date: November 12, 2015Inventors: Gerd Heller, Alexander Buescher, Frank Theurich, Tom Gibson, Michael Karwin, Stephen Powell
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Patent number: 9056671Abstract: A fixed wing of an aircraft, having a main wing extending over a half-span with a wing box including spars extending along the spanwise direction of the main wing, ribs arranged one in back of the other viewed in the spanwise direction, and an outer skin. The wing box includes a wing box base section (K10) and a wing box adapter section, that forms the outer end area of the wing box, as viewed from the wing root, and is designed to secure a wing tip device. In its nominal state of construction, the dihedral angle of the wing box adapter section referring to the respective local spanwise direction continuously increases by at most 60 degrees from the outer rib of the wing box base section (K10) up to the outermost rib of the wing box adapter section.Type: GrantFiled: October 12, 2012Date of Patent: June 16, 2015Assignees: Airbus Operations GmbH, Airbus Operations Ltd.Inventors: Gerd Heller, Alexander Buescher, Frank Theurich, Tom Gibson, Michael Karwin, Stephen Powell
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Publication number: 20140151511Abstract: An aircraft includes at least two aircraft fuselages and two elongate main wings, wherein the main wings each have an extension direction which are at an angle to one another that differs from zero. Each of the two main wings is connected to the at least two aircraft fuselages. The main wings can thus be equipped mechanically simply and so as to have a low weight, and at the same time the transmission of forces between the wings and the fuselages is performed via a plurality of connections, and this leads to a relatively low material stress.Type: ApplicationFiled: December 4, 2013Publication date: June 5, 2014Applicant: Airbus Operations GmbHInventor: Gerd Heller
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Publication number: 20130277504Abstract: A fixed wing of an aircraft, having a main wing extending over a half-span with a wing box including spars extending along the spanwise direction of the main wing, ribs arranged one in back of the other viewed in the spanwise direction, and an outer skin. The wing box includes a wing box base section (K10) and a wing box adapter section, that forms the outer end area of the wing box, as viewed from the wing root, and is designed to secure a wing tip device. In its nominal state of construction, the dihedral angle of the wing box adapter section referring to the respective local spanwise direction continuously increases by at most 60 degrees from the outer rib of the wing box base section (K10) up to the outermost rib of the wing box adapter section.Type: ApplicationFiled: October 12, 2012Publication date: October 24, 2013Inventors: Gerd Heller, Alexander Buescher, Frank Theurich, Tom Gibson, Michael Karwin, Stephen Powell
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Patent number: 8286921Abstract: A high-lift system on a wing with a curved nose and a leading-edge flap mounted via levers for movement between retracted and extended positions while expanding the airfoil profile, increasing its curvature and exposing a gap for guiding air from under the flap to above the wing. The levers form a four bar mechanism including first and second levers respectively pivotably connected at one end to spaced first and second points on the wing. The other ends of the levers are connected to opposite ends of a third lever forming part of the flap. The length and positions of the levers and the curvature of the wing nose are matched such that during initial extension from retracted position to an intermediate position the trailing edge of the flap blocks the gap between the flap and wing, and during further extension beyond the intermediate position the gap is exposed.Type: GrantFiled: May 5, 2008Date of Patent: October 16, 2012Assignee: Airbus Operations GmbHInventor: Gerd Heller
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Publication number: 20100155542Abstract: A high-lift system on the airfoil of an aircraft, comprising a main wing (H) which has a curved main wing nose (N) and comprising a leading-edge flap (V) is disposed retractably on the main wing (H) by means of an arrangement of several levers (a, b, c) so that said leading-edge flap can be moved from a retracted position (I) whilst increasing the expansion of the airfoil profile in the chord direction and whilst increasing its curvature and whilst exposing a gap (g) which guides energetic air from the underside of the leading-edge flap (V) to the upper side of the main wing (H), as far as a fully extended position (III).Type: ApplicationFiled: May 5, 2008Publication date: June 24, 2010Applicant: Airbus Operations GmbHInventor: Gerd Heller
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Patent number: 6722615Abstract: The present invention relates to a wing tip extension (7) for a wing, having an upper and a lower surface (10 and 11) and a leading edge and a trailing edge (12 and 13), the geometries of which are such that between a connection region (8), for connection with a wing, and the tip (9) of the wing tip extension (7) there is provided a continuous increase of the local dihedral, a continuous increase both of the sweepback angle of the leading edge (12) and also of the trailing edge (13), and a continuous decrease of the chord of the wing tip extension (7), and in that the wing tip extension (7) in the connection region (8) carries on from the wing in substance continuously. The wing tip extension (7) in accordance with the invention thereby ensures a significant reduction of the overall drag.Type: GrantFiled: April 5, 2002Date of Patent: April 20, 2004Assignee: Fairchild Dornier GmbHInventors: Gerd Heller, Manfred Maisel, Peter Kreuzer
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Publication number: 20020162917Abstract: The present invention relates to a wing tip extension (7) for a wing, having an upper and a lower surface (10 and 11) and a leading edge and a trailing edge (12 and 13), the geometries of which are such that between a connection region (8), for connection with a wing, and the tip (9) of the wing tip extension (7) there is provided a continuous increase of the local dihedral, a continuous increase both of the sweepback angle of the leading edge (12) and also of the trailing edge (13), and a continuous decrease of the chord of the wing tip extension (7), and in that the wing tip extension (7) in the connection region (8) carries on from the wing in substance continuously. The wing tip extension (7) in accordance with the invention thereby ensures a significant reduction of the overall drag.Type: ApplicationFiled: April 5, 2002Publication date: November 7, 2002Applicant: Fairchild Dornier GmbHInventors: Gerd Heller, Manfred Maisel, Peter Kreuzer