Patents by Inventor Christian Maenz
Christian Maenz 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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Publication number: 20240109641Abstract: An aircraft cabin floor arrangement includes two floor support part-structures, each having vertical support members, a beam member, cantilevering members and a seat rail. The beam member and the seat rail extend in a first direction with the seat rail being carried by the beam member. The cantilevering members cantilever in a second direction transverse to the first direction. The vertical support members extend in a third direction transverse to the first and second directions. The two floor support part-structures are each configured to be arranged along opposing side portions within an aircraft fuselage structure and are configured to transfer load from the cantilevering members and the beam member to the fuselage structure. The cantilevering members and the beam member are configured to carry a cabin floor configured to provide a load transfer in a plane direction of the floor and to contribute to a stiffening of the fuselage structure.Type: ApplicationFiled: September 7, 2023Publication date: April 4, 2024Inventors: Christian MÄNZ, Hermann BENTHIEN
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Publication number: 20230358261Abstract: A connection system includes at least a first part and at least a second part, both comprising a connection surface and being configured to be connected to each other. A plurality of engagement elements is protruding from the connection surface of the first part and from the connection surface of the second part. For connecting different components, the parts are positioned such that their connection surfaces are facing each other. A ductile material is positioned between the connection surfaces of the parts to be connected to each other. The parts are pressed together, wherein the engagement elements are pressed into the ductile material at required positions, thereby compensating position deviations.Type: ApplicationFiled: May 3, 2023Publication date: November 9, 2023Inventor: Christian MÄNZ
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Patent number: 9315256Abstract: A flap arrangement includes a basic body, a hinge arrangement, and a flap that by the hinge arrangement is movably held on the basic body. The hinge arrangement includes at least three bearing points spaced apart from each other and arranged on a shared hinge line, wherein two bearing points are rigidly connected to the basic body and to the flap, and wherein the remaining bearing points in each case allow local movement between the basic body and the flap in at least one first spatial direction perpendicularly to the hinge line. Thus, load-induced constraint forces between the basic body and the control surface can be prevented.Type: GrantFiled: March 25, 2013Date of Patent: April 19, 2016Assignee: Airbus Operations GmbHInventor: Christian Maenz
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Patent number: 9284039Abstract: A rudder system for an aircraft includes a center box, a rudder and actuators, wherein the rudder is pivoted around a hinge line relative to the center box. The actuators are arranged at an acute angle relative to the hinge line, and connected with at least one pivoted pivot lever, wherein the pivot lever is fastened to the rudder by way of a first push rod. This provides considerably more installation space in a vertical stabilizer of an aircraft for a center box, so that the latter can comprise a distinctly smaller wall thickness than usual in prior art to absorb air load-induced torsion and bending stresses.Type: GrantFiled: May 10, 2013Date of Patent: March 15, 2016Assignee: Airbus Operations GmbHInventor: Christian Maenz
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Patent number: 8602356Abstract: A wing box for an aircraft wing with a framework and a first shell. The framework is connected to the first shell such that a load acting on the first shell can be transferred by the framework.Type: GrantFiled: August 17, 2006Date of Patent: December 10, 2013Assignee: Airbus Operations GmbHInventor: Christian Maenz
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Publication number: 20130320137Abstract: A rudder system for an aircraft includes a centre box, a rudder and actuators, wherein the rudder is pivoted around a hinge line relative to the centre box. The actuators are arranged at an acute angle relative to the hinge line, and connected with at least one pivoted pivot lever, wherein the pivot lever is fastened to the rudder by way of a first push rod. This provides considerably more installation space in a vertical stabilizer of an aircraft for a centre box, so that the latter can comprise a distinctly smaller wall thickness than usual in prior art to absorb air load-induced torsion and bending stresses.Type: ApplicationFiled: May 10, 2013Publication date: December 5, 2013Applicant: AIRBUS OPERATIONS GMBHInventor: Christian Maenz
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Publication number: 20130256461Abstract: A flap arrangement includes a basic body, a hinge arrangement, and a flap that by the hinge arrangement is movably held on the basic body. The hinge arrangement includes at least three bearing points spaced apart from each other and arranged on a shared hinge line, wherein two bearing points are rigidly connected to the basic body and to the flap, and wherein the remaining bearing points in each case allow local movement between the basic body and the flap in at least one first spatial direction perpendicularly to the hinge line. Thus, load-induced constraint forces between the basic body and the control surface can be prevented.Type: ApplicationFiled: March 25, 2013Publication date: October 3, 2013Applicant: AIRBUS OPERATIONS GMBHInventor: Christian Maenz
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Patent number: 8276847Abstract: A cover for an aircraft structure, in particular for nose parts of the vertical tail, horizontal tail or the wing, including a skin and support structure. The skin is arranged on the support structure and the support structure includes a plurality of ribs and a plurality of stringers. The plurality of stringers are arranged on the plurality of ribs to support the skin. Also provided is an aircraft having such a cover.Type: GrantFiled: November 18, 2009Date of Patent: October 2, 2012Assignee: Airbus Operations GmbHInventor: Christian Mänz
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Patent number: 8205834Abstract: A support structure for an aircraft, includes one or several bar elements and one or several junction elements. At least one bar element includes a transition region which can be made to engage at least one junction element. When the transition region of the bar element engages at least one junction element, centric force transmission takes place between the bar element and the junction element.Type: GrantFiled: August 16, 2006Date of Patent: June 26, 2012Assignee: Airbus Deutschland GmbHInventor: Christian Maenz
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Patent number: 8104709Abstract: A lateral force joint, with which a plate-like spar can be fastened to a fuselage strap mounted on an airplane fuselage. The plate-like spar has a through bore, into which a fastening cylinder mounted on the flange can be inserted for connecting both components. In order to allow for the location of the spar to be adjusted with respect to the fuselage strap, a bearing bush of the spar is eccentrically fitted into the through bore. Correspondingly, the fastening cylinder of the fuselage strap is mounted eccentrically on a bearing bush so that a rotation of the bearing bushes allows the lateral force joint to be adjusted.Type: GrantFiled: May 11, 2006Date of Patent: January 31, 2012Assignee: Airbus Deutschland GmbHInventor: Christian Mänz
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Patent number: 7931234Abstract: An attachment system for attaching a tail unit to an attachment surface of an aircraft is disclosed. An attachment surface may be a fuselage, for example. In an arrangement, the attachment system includes a mounting with a first bearing surface that is capable of resting against the tail unit, and a second bearing surface that is capable of resting against the attachment surface. The first bearing surface and the second bearing surface, of which there is at least one, include a common line of contact. In the arrangement, the planes of the first bearing surface and of the second bearing surface are at an angle that differs from 0° and 180°.Type: GrantFiled: August 14, 2006Date of Patent: April 26, 2011Assignee: Airbus Deutschland GmbHInventor: Christian Maenz
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Publication number: 20100170995Abstract: A support structure for an aircraft, includes one or several bar elements and one or several junction elements. At least one bar element includes a transition region which can be made to engage at least one junction element. When the transition region of the bar element engages at least one junction element, centric force transmission takes place between the bar element and the junction element.Type: ApplicationFiled: August 16, 2006Publication date: July 8, 2010Applicant: Airbus Deutschland GmbHInventor: Christian Maenz
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Publication number: 20090294590Abstract: A wing box for an aircraft wing with a framework and a first shell. The framework is connected to the first shell such that a load acting on the first shell can be transferred by the framework.Type: ApplicationFiled: August 17, 2006Publication date: December 3, 2009Applicant: AIRBUS DEUTSCHLAND GmbHInventor: Christian Maenz
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Publication number: 20090200424Abstract: A lateral force joint, with which a plate-like spar can be fastened to a fuselage strap mounted on an airplane fuselage. The plate-like spar has a through bore, into which a fastening cylinder mounted on the flange can be inserted for connecting both components. In order to allow for the location of the spar to be adjusted with respect to the fuselage strap, a bearing bush of the spar is eccentrically fitted into the through bore. Correspondingly, the fastening cylinder of the fuselage strap is mounted eccentrically on a bearing bush so that a rotation of the bearing bushes allows the lateral force joint to be adjusted.Type: ApplicationFiled: May 11, 2006Publication date: August 13, 2009Applicant: Airbus Deutschland GmbHInventor: Christian Mänz
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Publication number: 20090114772Abstract: An attachment system for attaching a tail unit to an attachment surface of an aircraft is disclosed. An attachment surface may be a fuselage, for example. In an arrangement, the attachment system includes a mounting with a first bearing surface that is capable of resting against the tail unit, and a second bearing surface that is capable of resting against the attachment surface. The first bearing surface and the second bearing surface, of which there is at least one, include a common line of contact. In the arrangement, the planes of the first bearing surface and of the second bearing surface are at an angle that differs from 0° and 180°.Type: ApplicationFiled: August 14, 2006Publication date: May 7, 2009Applicant: Airbus Deutschland GmbHInventor: Christian Maenz
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Publication number: 20080203228Abstract: The present invention relates to a center box (5) for an aircraft wing, as well as to an aircraft comprising such a center box (5). The center box (5) essentially comprises two lateral surfaces (6), which in turn essentially comprise two internal and external skins (2, 1) that are arranged so as to be spaced apart from each other. In order to provide adequate stability to the lateral surface (6), the internal skin (2) and the external skin (1) are interconnected by way of a multitude of profiles (3).Type: ApplicationFiled: May 11, 2006Publication date: August 28, 2008Applicant: Airbus Deutschland GmbHInventor: Christian Maenz