Patents by Inventor Timo Voss
Timo Voss 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: 8844878Abstract: A high lift system for an aircraft includes: a main wing, a flap disposed on the main wing of the aircraft that can be adjusted between a retracted position and several extended positions relative to the main wing by way of a flap actuating mechanism and a drive device, a carrier part disposed on the main wing to which the flap actuating mechanism is coupled and relative to which the flap actuating mechanism for adjusting the flap can be moved, where the carrier part is disposed on the main wing by way of a bearing device including an adjusting device with which the orientation of the carrier part relative to the orientation of the main wing can be adjusted.Type: GrantFiled: August 6, 2008Date of Patent: September 30, 2014Assignee: Airbus Operations GmbHInventors: Timo Voss, Joachim Loerke
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Patent number: 8651430Abstract: The invention pertains to a spoiler (5) for an aerodynamically active surface of an aircraft (1), particularly for an airfoil of an aircraft, wherein said spoiler is supported on the aerodynamically active surface such that it is articulated about an axis (11) extending transverse to the air flow direction and can be adjusted relative to the air flow. According to the invention, the spoiler features two or more segments (6, 7) that are arranged behind one another referred to the air flow direction and extend transverse to the air flow direction, wherein said segments are connected to one another in an articulated fashion and can be adjusted to different angles referred to the air flow. The successively arranged segments of the spoiler (5) can be actuated, in particular, by means of an actuating device (8, 9, 10) in such a way that the rear segment (7) is adjusted relative to the air flow by a greater angle than the front segment (6).Type: GrantFiled: February 25, 2008Date of Patent: February 18, 2014Assignee: Airbus Operations GmbHInventors: Timo Voss, Joachim Loerke
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Patent number: 8444094Abstract: A high-lift system for an aircraft includes a main wing, a lift flap arranged on the main wing of the aircraft, which lift flap is adjustable, between a retracted position and several extended positions relative to the main wing of the aircraft, by means of a flap adjustment mechanism for coupling the lift flap to the main wing and by means of a drive device, wherein the flap adjustment mechanism comprises at least two adjustment devices arranged so as to be spaced apart from each other in the wingspan direction, with each adjustment device including a first lever and a second lever, where the first end piece of the second lever is pivotally and slidably held on the main wing, while the second end piece of said second lever is pivotally held on the lift flap.Type: GrantFiled: December 29, 2008Date of Patent: May 21, 2013Assignee: Airbus Operations GmbHInventors: Timo Voss, Joachim Loerke
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Publication number: 20110114795Abstract: An aerodynamic flap with an articulation device to form an axis of rotation for purposes of a rotatable mounting of the aerodynamic flap on a wing section or structural section, with the flap coupled to the wing section in accordance with its intended purpose, with a front flap section situated upstream of the axis of rotation, as viewed in the flow direction, with a front edge line, and a rear flap section situated behind the axis of rotation, wherein a multiplicity of extension pieces are arranged on the front flap section, distributed over the span width of the flap, whose ends project beyond the front edge line of the flap as exposed parts, as viewed from the axis of rotation, wherein the extension pieces are rigid and arranged on the flap, such that one surface of the extension pieces forms an aerodynamically uniform surface with the upper or lower side of the flap, and such that when the flap is deflected the exposed ends of the extension pieces on one surface of the flap are directed at an angle againsType: ApplicationFiled: July 14, 2009Publication date: May 19, 2011Applicant: Airbus Operations GmbHInventors: Timo Voss, Klaus Bender
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Publication number: 20110101174Abstract: A high lift system for an aircraft includes: a main wing, a flap disposed on the main wing of the aircraft that can be adjusted between a retracted position and several extended positions relative to the main wing by means of flap actuating means and a drive device, said system further comprising a carrier part disposed on the main wing to which the flap actuating means are coupled and relative to which the flap actuating means for adjusting the flap can be moved, wherein the carrier part is disposed on the main wing by means of a bearing device comprising an adjusting device with which the orientation of the carrier part relative to the orientation of the main wing can be adjusted.Type: ApplicationFiled: August 6, 2008Publication date: May 5, 2011Applicant: Airbus Operations GmbHInventors: Timo Voss, Joachim Loerke
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Publication number: 20110011984Abstract: A high-lift system for an aircraft includes a main wing, a lift flap arranged on the main wing of the aircraft, which lift flap is adjustable, between a retracted position and several extended positions relative to the main wing of the aircraft, by means of a flap adjustment mechanism for coupling the lift flap to the main wing and by means of a drive device, wherein the flap adjustment mechanism comprises at least two adjustment devices arranged so as to be spaced apart from each other in the wingspan direction, with each adjustment device including a first lever and a second lever, where the first end piece of the second lever is pivotally and slidably held on the main wing, while the second end piece of said second lever is pivotally held on the lift flap.Type: ApplicationFiled: December 29, 2008Publication date: January 20, 2011Applicant: AIRBUS OPERATIONS GMBHInventors: Timo Voss, Joachim Loerke
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Publication number: 20100320332Abstract: The invention pertains to a spoiler (5) for an aerodynamically active surface of an aircraft (1), particularly for an airfoil of an aircraft, wherein said spoiler is supported on the aerodynamically active surface such that it is articulated about an axis (11) extending transverse to the air flow direction and can be adjusted relative to the air flow. According to the invention, the spoiler features two or more segments (6, 7) that are arranged behind one another referred to the air flow direction and extend transverse to the air flow direction, wherein said segments are connected to one another in an articulated fashion and can be adjusted to different angles referred to the air flow. The successively arranged segments of the spoiler (5) can be actuated, in particular, by means of an actuating device (8, 9, 10) in such a way that the rear segment (7) is adjusted relative to the air flow by a greater angle than the front segment (6).Type: ApplicationFiled: February 25, 2008Publication date: December 23, 2010Applicant: AIRBUS OPERATIONS GMBHInventors: Timo Voss, Joachim Loerke