Patents by Inventor Per Hallander

Per Hallander 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).

  • Patent number: 10343372
    Abstract: The present invention regards an article (5) comprising at least one composite material, comprising matrix material (19) and at least one micro-sized reinforcement element distributions (23), arranged in plies (13) positioned on top of each other. The nano-sized reinforcement elements (17, 17?, 17?, 17??) are arranged in between and/or inside the micro-sized reinforcement element distributions (23), the nano-sized reinforcement elements (17, 17?, 17?, 17??) having matrix material accumulation properties so as to provide a tailored increased reinforcement volume of said one or more distributions (23). The present invention regards a method for manufacture of a composite article (5) and use of the article (5).
    Type: Grant
    Filed: July 3, 2014
    Date of Patent: July 9, 2019
    Assignee: SAAB AB
    Inventors: Per Hallander, Pontus Nordin, Goete Strindberg
  • Patent number: 9840041
    Abstract: A stiffening element including at least a first stiffening profile and at least a second stiffening profile. The first stiffening profile includes a profile member. At least one structural flange is connected to the profile member. A through-passage extends through the profile member. At least one support flange is connected to the profile member. The second stiffening profile includes a bottom portion and at least one support side portion connected to the bottom portion. A method for manufacturing a stiffening element. A method for manufacturing a reinforced structure, where the reinforced structure includes at least one structural element and at least one stiffening element.
    Type: Grant
    Filed: December 20, 2013
    Date of Patent: December 12, 2017
    Assignee: SAAB AB
    Inventors: Per Hallander, Anders Lundberg, Tonny Nyman, Mikael Petersson
  • Publication number: 20170129207
    Abstract: The present invention regards an article (5) comprising at least one composite material, comprising matrix material (19) and at least one micro-sized reinforcement element distributions (23), arranged in plies (13) positioned on top of each other. The nano-sized reinforcement elements (17, 17?, 17?, 17??) are arranged in between and/or inside the micro-sized reinforcement element distributions (23), the nano-sized reinforcement elements (17, 17?, 17?, 17??) having matrix material accumulation properties so as to provide a tailored increased reinforcement volume of said one or more distributions (23). The present invention regards a method for manufacture of a composite article (5) and use of the article (5).
    Type: Application
    Filed: July 3, 2014
    Publication date: May 11, 2017
    Applicant: SAAB AB
    Inventors: Per Hallander, Pontus Nordin, Goete Strindberg
  • Publication number: 20160375632
    Abstract: A stiffening element including at least a first stiffening profile and at least a second stiffening profile. The first stiffening profile includes a profile member. At least one structural flange is connected to the profile member. A through-passage extends through the profile member. At least one support flange is connected to the profile member. The second stiffening profile includes a bottom portion and at least one support side portion connected to the bottom portion. A method for manufacturing a stiffening element. A method for manufacturing a reinforced structure, where the reinforced structure includes at least one structural element and at least one stiffening element.
    Type: Application
    Filed: December 20, 2013
    Publication date: December 29, 2016
    Applicant: SAAB AB
    Inventors: Per Hallander, Anders Lundberg, Tonny Nyman, Mikael Petersson
  • Patent number: 9180979
    Abstract: An aircraft article composite forming tool and a method for producing the tool. The aircraft article to be formed includes a composite material including an outer surface. The aircraft article composite forming tool includes a matrix laminate made of at least an upper ply including a forming surface for forming the aircraft article and outer surface. The upper ply includes a nano filament structure embedded therein.
    Type: Grant
    Filed: February 4, 2010
    Date of Patent: November 10, 2015
    Assignee: SAAB AB
    Inventors: Per Hallander, Mikael Petersson, Björn Weidmann, Tommy Grankäll, Göte Strindberg, Pontus Nordin
  • Publication number: 20150290845
    Abstract: A method of manufacture of a composite aircraft article aerodynamic surface by forming the composite aircraft article aerodynamic surface on an aircraft article composite forming tool. The aircraft article composite forming tool includes a matrix laminate including an upper ply including a forming surface for forming the composite aircraft article aerodynamic surface. The upper ply of the aircraft article composite forming tool includes a nano filament structure embedded therein. A blank is conformed onto the aircraft article composite forming tool. The aircraft article is formed on the upper ply of the forming surface. The forming surface of the aircraft article composite forming tool is adapted to form an aerodynamic surface of the aircraft article. The blank is cured into the aircraft article. The composite aircraft article is finished.
    Type: Application
    Filed: April 16, 2015
    Publication date: October 15, 2015
    Inventors: Per HALLANDER, Mikael PETERSSON, Björn WEIDMANN, Tommy GRANKÄLL, Göte STRINDBERG, Pontus NORDIN
  • Publication number: 20150292074
    Abstract: An aerial article including a composite skin, a leading edge facing an airflow during use of the aerial article, an erosion resistant coating including a metallic material, and an aerodynamic surface. The coating at least partly covers the composite skin of the aerial article. The coating has a porosity sufficiently high to provide an open area, diffusion passage way, so as to permit moisture transportation from the composite skin to the aerodynamic surface of the coating. A method of applying an erosion resistant coating including a metallic material to a composite skin of an aerial article. An erosion resistant coating material is provided onto the composite skin over a selected area of the article. The coating is porous. The outer surface of the coating is polished to achieve a smooth aerodynamic surface.
    Type: Application
    Filed: October 31, 2012
    Publication date: October 15, 2015
    Inventors: Pontus Nordin, Per Hallander, Jonas Bohlin, Thomas Hellstrom
  • Patent number: 9040142
    Abstract: A composite article having a longitudinal direction and a transversal direction. The article includes a stack of plies wherein one ply is a bottom ply and one ply is a top ply. Most or all of the plies include fibers. A plurality of plies have fibers substantially in an orthogonal direction and substantially in a same direction as the longitudinally direction of the article. The bottom ply and the top ply have fibers in a substantially orthogonal direction to the longitudinal direction of the article. At least one ply has the fibers substantially in the same direction as the longitudinal direction of the article. At least one of the plies having fibers substantially in the longitudinal direction includes particles selected from the group of thermoplastic tougheners, nano particles, micro particles, elastic particles, elastomer particles and polymer particles or a combination. Also a method of forming an article on a tool.
    Type: Grant
    Filed: May 11, 2010
    Date of Patent: May 26, 2015
    Assignee: SAAB AB
    Inventors: Björn Weidmann, Mikael Petersson, Per Hallander, Pontus Nordin, Tommy Grankäll
  • Patent number: 8916252
    Abstract: A structural composite part made of pre-impregnated fiber plies. The edges of two adjacent fiber plies are connected via a longitudinal composite joint made structural by a nanostructure arranged within the composite joint. A method of producing a structural composite part made of pre-impregnated fiber plies. The edges of two adjacent fiber plies are connected via a longitudinal composite joint made structural by a nanostructure and an aircraft structure comprising such structural composite parts.
    Type: Grant
    Filed: June 11, 2009
    Date of Patent: December 23, 2014
    Assignee: SAAB AB
    Inventors: Per Hallander, Mikael Petersson, Bjorn Weidmann, Tommy Grankäll, Göte Strindberg, Pontus Nordin, Rustan Önnefors
  • Publication number: 20140284431
    Abstract: The present invention regards an aircraft structure comprising an aerodynamic composite shell (7), the interior face (9) of which in whole or in part is bonded with at least one two- or three-dimensional structural composite part (11) by means of a bonding material (15). It also regards a method of manufacture of the aircraft structure. The bonding material (15) comprises a non-structural fiber reinforced resin system, wherein at least one portion of the bonding material, which portion spatially corresponds with an interior face filling volume (21), is thicker than other portions of the bonding material (15), due to settlement of resin of the non-structural fiber reinforced resin system in said interior face filling volume (21) during the viscous phase of the curing of the non-structural fiber reinforced resin system.
    Type: Application
    Filed: December 12, 2011
    Publication date: September 25, 2014
    Applicant: SAAB AB
    Inventors: Tommy Grankaell, Per Hallander, Mikael Petersson, Bjoern Weidmann
  • Patent number: 8840828
    Abstract: An apparatus and a method of conforming a blank onto forming surface sections of a forming tool by drawing a first vacuum against an elastic forming medium for transmitting forming forces from the elastic forming medium to the blank. The elastic forming medium is evacuated with the first vacuum for allowing the elastic forming medium to stretch and conform the blank to the forming surface sections. The elastic forming medium includes at least one void. A second vacuum is applied to the void for achieving a stiffened section of the elastic forming medium corresponding with the location of the void and corresponding with, when the elastic forming medium after the completion lies against the forming tool having the blank in between, a forming surface section of the forming tool where the blank requires a forming force being larger than that of surrounding sections of the elastic forming medium.
    Type: Grant
    Filed: October 29, 2008
    Date of Patent: September 23, 2014
    Assignee: Saab AB
    Inventors: Per Hallander, Mikael Petersson
  • Patent number: 8807983
    Abstract: A thermoforming apparatus for forming a blank into a composite article. The thermoforming apparatus includes a forming tool. A forming member forms the blank over the forming tool. A first chamber is arranged for containing the blank. A second chamber is separated from the first chamber by the forming member. A first air circulator is configured to circulate air in the first chamber for achieving a heat distribution to the blank. The first air circulator includes a controllable valve member. The apparatus also includes a second air circulator. A method for forming a blank during circulation of air in a first chamber.
    Type: Grant
    Filed: November 28, 2008
    Date of Patent: August 19, 2014
    Assignee: SAAB AB
    Inventors: Mikael Petersson, Per Hallander, Jan Andersson, Anders Westerdahl
  • Publication number: 20140147619
    Abstract: The present invention relates to a composite article 801, wherein the article has a longitudinal direction L and a transversal direction T, the article 80 comprises a stack of plies wherein one ply is a bottom ply and one ply is a top ply, most of or all of the plies comprise fibres, and the article comprises a plurality of plies having fibres substantially in the orthogonal direction 810 to the longitudinal direction L of the article 801 and the stack further comprises a plurality of plies having fibres substantially in the same direction 811 as the longitudinally direction L of the article 801 and/or a plurality of plies having fibres in the diagonal direction (812, 813, 815, 816, 817, 818) of the longitudinal direction (L) of the article (801), wherein at least one of the ply/plies having fibres substantially in the orthogonal direction 810 to the longitudinal direction L of the article 801 comprise fibres that are stiffer than the fibres in the other plies which have less stiff fibres.
    Type: Application
    Filed: January 21, 2011
    Publication date: May 29, 2014
    Applicant: SAAB AB
    Inventors: Tommy Grankaell, Per Hallander, Anders Lundberg, Tonny Nyman, Bjoern Weidmann, Mikael Petersson
  • Patent number: 8662452
    Abstract: A structural article including an outer surface that serves as an aerodynamic surface when the structural article is subjected for an air stream. A resin matrix laminate includes an upper ply and a bottom ply. A heating element is arranged in contact with the bottom ply and coupled to a power supply unit in purpose to deice/anti-ice the outer surface. Each ply includes a thermally conductive filament structure having a filament orientation such that the prolongation of the filaments has an extension essentially perpendicular to the extension of the laminate. The thermally conductive filament structure of the upper ply is embedded in the upper ply in such way that at least a portion of the thermally conductive filament structure is exposed in the outer surface.
    Type: Grant
    Filed: January 14, 2010
    Date of Patent: March 4, 2014
    Assignee: SAAB AB
    Inventors: Per Hallander, Mikael Petersson, Björn Weidmann, Tommy Grankäll, Göte Strindberg, Pontus Nordin
  • Publication number: 20130240110
    Abstract: An aircraft article composite forming tool and a method for producing the tool. The aircraft article to be formed includes a composite material including an outer surface. The aircraft article composite forming tool includes a matrix laminate made of at least an upper ply including a forming surface for forming the aircraft article and outer surface. The upper ply includes a nano filament structure embedded therein.
    Type: Application
    Filed: February 4, 2010
    Publication date: September 19, 2013
    Applicant: SAAB AB
    Inventors: Per Hallander, Mikael Petersson, Björn Weidmann, Tommy Grankäll, Göte Strindberg, Pontus Nordin
  • Publication number: 20130129968
    Abstract: A composite article having a longitudinal direction and a transversal direction. The article includes a stack of plies wherein one ply is a bottom ply and one ply is a top ply. Most or all of the plies include fibers. A plurality of plies have fibers substantially in an orthogonal direction and substantially in a same direction as the longitudinally direction of the article. The bottom ply and the top ply have fibers in a substantially orthogonal direction to the longitudinal direction of the article. At least one ply has the fibers substantially in the same direction as the longitudinal direction of the article. At least one of the plies having fibers substantially in the longitudinal direction includes particles selected from the group of thermoplastic tougheners, nano particles, micro particles, elastic particles, elastomer particles and polymer particles or a combination. Also a method of forming an article on a tool.
    Type: Application
    Filed: May 11, 2010
    Publication date: May 23, 2013
    Applicant: SAAB AB
    Inventors: Björn Weidmann, Mikael Petersson, Per Hallander, Pontus Nordin, Tommy Grankäll
  • Publication number: 20120292439
    Abstract: A structural article including an outer surface that serves as an aerodynamic surface when the structural article is subjected for an air stream. A resin matrix laminate includes an upper ply and a bottom ply. A heating element is arranged in contact with the bottom ply and coupled to a power supply unit in purpose to deice/anti-ice the outer surface. Each ply includes a thermally conductive filament structure having a filament orientation such that the prolongation of the filaments has an extension essentially perpendicular to the extension of the laminate. The thermally conductive filament structure of the upper ply is embedded in the upper ply in such way that at least a portion of the thermally conductive filament structure is exposed in the outer surface.
    Type: Application
    Filed: January 14, 2010
    Publication date: November 22, 2012
    Applicant: SAAB AB
    Inventors: Per Hallander, Mikael Petersson, Björn Weidmann, Tommy Grankäll, Göte Strindberg, Pontus Nordin
  • Publication number: 20120256076
    Abstract: A method of producing a forming tool and a forming tool for forming an article. The forming tool includes a composite face sheet having a forming surface and an inner surface opposite the forming surface. A support structure is attached to the inner surface of the composite face sheet. The support structure includes a support shell of composite having a first surface facing the inner surface of the composite face sheet and having a second surface opposite the first surface. The support structure further includes distance members. The support shell is fixed at a distance from the composite face sheet by the distance members.
    Type: Application
    Filed: November 17, 2009
    Publication date: October 11, 2012
    Inventors: Tommy Grankall, Anders Lundberg, Jan Andersson, Mikael Petersson, Björn Weidmann, Jan Waara, Per Hallander
  • Publication number: 20120148789
    Abstract: An aircraft structure including structural composite parts assembled together to form the aircraft structure. A bonding interlayer material bonds the structural composite parts to each other. The bonding interlayer material includes a nanostructure enhanced material. A method of producing an aircraft structure of assembled structural composite parts, being cured or semi-cured before assembly.
    Type: Application
    Filed: June 11, 2009
    Publication date: June 14, 2012
    Inventors: Per Hallander, Mikael Petersson, Björn Weidmann, Tommy Grankäll, Pontus Nordin
  • Publication number: 20120088056
    Abstract: A structural composite part made of pre-impregnated fiber plies. The edges of two adjacent fiber plies are connected via a longitudinal composite joint made structural by a nanostructure arranged within the composite joint. A method of producing a structural composite part made of pre-impregnated fiber plies. The edges of two adjacent fiber plies are connected via a longitudinal composite joint made structural by a nanostructure and an aircraft structure comprising such structural composite parts.
    Type: Application
    Filed: June 11, 2009
    Publication date: April 12, 2012
    Applicant: SAAB AB
    Inventors: Per Hallander, Mikael Petersson, Bjorn Weidmann, Tommy Grankäll, Göte Strindberg, Pontus Nordin, Rustan Önnefors