Patents by Inventor Lars Krog
Lars Krog 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).
-
Publication number: 20190127043Abstract: A wing segment for an aircraft includes a first skin element with a material having anisotropic characteristics and a rib element arranged between leading and trailing edges of the wing segment. The first skin element is attached to the rib element such that deformation of the skin element results in a twist of the wing segment with respect to a main extension direction of the wing segment. The wing segment further includes a control unit to control deformation of the skin element in order to adjust the twist of the wing segment to achieve a predetermined twist of the wing segment.Type: ApplicationFiled: October 15, 2018Publication date: May 2, 2019Inventors: LARS KROG, PASQUALE BASSO
-
Patent number: 9126674Abstract: A beam (20) comprising first and second flanges (23, 24), the beam (20) having a first region (28, 30) extending between the flanges (23, 24) and a second region (26) extending between the flanges. The first region (28, 30) is designed to support an applied concentrated shear load and the second region (26) is designed to support a predominantly bending load. The first region comprises a fan-shaped truss comprising a hub (36) adjacent the first flange and a plurality of struts (37) which extend substantially radially from the hub (36), and the second region (26) comprises either a truss structure which is substantially regular in the longitudinal beam direction or a shear web. The beam may, for example, be used as a floor beam for an aircraft fuselage.Type: GrantFiled: July 12, 2011Date of Patent: September 8, 2015Assignees: Airbus Operations Limited, Airbus Operations SL, Airbus Operations SAS, Airbus Operations GmbHInventors: Lars Krog, Andrea Marasco, Stéphane Grihon, Manuela Jürgens, Gary Ryan, Stuart Bates
-
Patent number: 8731870Abstract: A method of designing a composite panel, the panel comprising a plurality of zones, each zone comprising a plurality of plies of composite material arranged in a stacking sequence, each ply in each stacking sequence having a respective orientation angle. For each orientation angle a first layout matrix is created which identifies zones in the panel which contain at least one ply with that orientation angle. A second layout matrix is also created which identifies zones in the panel which contain at least two plies with that orientation angle, and so on up to an Nth layout matrix which identifies zones in the panel which contain at least N plies with that orientation angle. The layout matrices are arranged in a plurality of candidate sequences. Selection criteria are then used to choose one or more of the candidate sequences and stacking sequences are assigned to the zones in accordance with the chosen candidate sequence(s).Type: GrantFiled: April 14, 2009Date of Patent: May 20, 2014Assignee: Airbus Operations LimitedInventor: Lars Krog
-
Publication number: 20130273306Abstract: A beam (20) comprising first and second flanges (23, 24), the beam (20) having a first region (28, 30) extending between the flanges (23, 24) and a second region (26) extending between the flanges. The first region (28, 30) is designed to support an applied concentrated shear load and the second region (26) is designed to support a predominantly bending load. The first region comprises a fan-shaped truss comprising a hub (36) adjacent the first flange and a plurality of struts (37) which extend substantially radially from the hub (36), and the second region (26) comprises either a truss structure which is substantially regular in the longitudinal beam direction or a shear web. The beam may, for example, be used as a floor beam for an aircraft fuselage.Type: ApplicationFiled: July 12, 2011Publication date: October 17, 2013Inventors: Lars Krog, Andrea Marasco, Stéphane Grihon, Manuela Jürgens, Gary Ryan, Stuart Bates
-
Patent number: 8494813Abstract: A method of designing a composite panel, the panel comprising a plurality of zones, each zone comprising a plurality of plies of composite material, each ply in each zone having a respective orientation angle, and some of the plies running continuously between adjacent zones. A design is provided comprising a set of design variables including a thickness for each of the zones, and a ply percentage for each orientation angle for each of the zones, each ply percentage identifying a percentage of plies within a zone having a particular orientation angle.Type: GrantFiled: June 11, 2009Date of Patent: July 23, 2013Assignee: Airbus Operations LimitedInventor: Lars Krog
-
Patent number: 8306789Abstract: A method of designing a composite laminate including a plurality of zones, each zone including a plurality of plies of composite material, each ply having a respective ply orientation angle. A global stacking sequence of stacking sequence elements is determined for the laminate. A local laminate thickness is determined for each zone. A local stacking sequence is then determined for each zone by extracting a subsequence of stacking sequence elements from the global stacking sequence. The global stacking sequence and the laminate thicknesses are determined together in an optimization process in which multiple sub-ply selection variables are assigned to each stacking sequence element. Optimal values are determined for the sub-ply selection variables and the laminate thicknesses. A single one of the sub-ply selection variables is assigned to each stacking sequence element thereby forcing a discrete choice of global ply orientation angle for each stacking sequence element.Type: GrantFiled: November 13, 2009Date of Patent: November 6, 2012Assignee: Airbus Operations LimitedInventor: Lars Krog
-
Publication number: 20110004451Abstract: A method of designing a composite panel, the panel comprising a plurality of zones, each zone comprising a plurality of plies of composite material arranged in a stacking sequence, each ply in each stacking sequence having a respective orientation angle. For each orientation angle a first layout matrix is created which identifies zones in the panel which contain at least one ply with that orientation angle. A second layout matrix is also created which identifies zones in the panel which contain at least two plies with that orientation angle, and so on up to an Nth layout matrix which identifies zones in the panel which contain at least N plies with that orientation angle. The layout matrices are arranged in a plurality of candidate sequences. Selection criteria are then used to choose one or more of the candidate sequences and stacking sequences are assigned to the zones in accordance with the chosen candidate sequence(s).Type: ApplicationFiled: April 14, 2009Publication date: January 6, 2011Inventor: Lars Krog
-
Publication number: 20100223029Abstract: A method of designing a composite panel, the panel comprising a plurality of zones, each zone comprising a plurality of plies of composite material, each ply in each zone having a respective orientation angle, and some of the plies running continuously between adjacent zones. A design is provided comprising a set of design variables including a thickness for each of the zones, and a ply percentage for each orientation angle for each of the zones, each ply percentage identifying a percentage of plies within a zone having a particular orientation angle.Type: ApplicationFiled: June 11, 2009Publication date: September 2, 2010Applicant: AIRBUS UK LIMITEDInventor: Lars Krog
-
Publication number: 20100121625Abstract: A method of designing a composite laminate, the laminate comprising a plurality of zones, each zone comprising a plurality of plies of composite material, each ply in each zone having a respective ply orientation angle. A global stacking sequence is determined for the laminate, the global stacking sequence comprising a sequence of stacking sequence elements. A local laminate thickness is determined for each zone. A local stacking sequence is then determined for each zone by extracting a subsequence of stacking sequence elements from the global stacking sequence. The global stacking sequence and the local laminate thicknesses are determined together in an optimisation process in which multiple sub-ply selection variables are assigned to each stacking sequence element, each sub-ply selection variable representing the density or sub-ply thickness for a respective candidate ply orientation angle. Optimal values are determined for the sub-ply selection variables and the local laminate thicknesses.Type: ApplicationFiled: November 13, 2009Publication date: May 13, 2010Applicant: AIRBUS OPERATIONS LIMITEDInventor: Lars Krog
-
Patent number: 7481398Abstract: An intercostal for an aircraft for dissipating a load from a first frame onto a second frame and/or a skin of the aircraft, the intercostal having a framework.Type: GrantFiled: February 24, 2005Date of Patent: January 27, 2009Assignee: Airbus Deutschland GmbHInventors: Marc Schimmler, Thomas Grauerholz, Alastair Tucker, Lars Krog
-
Publication number: 20060261215Abstract: An intercostal for an aircraft for dissipating a load from a first frame onto a second frame and/or a skin of the aircraft, the intercostal having a framework.Type: ApplicationFiled: February 24, 2005Publication date: November 23, 2006Applicant: Airbus Deutschland GmbHInventors: Marc Schimmler, Thomas Grauerholz, Alastair Tucker, Lars Krog
-
Patent number: D409684Type: GrantFiled: October 14, 1998Date of Patent: May 11, 1999Assignee: INTERLEGO AGInventors: Jesper Elling, Lars Krog Jensen