Class / Patent application number | Description | Number of patent applications / Date published |
244123800 | Main spar | 7 |
20090194636 | STRINGER FOR AN AIRCRAFT WING AND A METHOD OF FORMING THEREOF - The present invention relates to a stringer for an aircraft wing and a method of forming such a stringer in which the stringer is formed from a single piece of material and then machined to optimise the dimensions and weight of the stringer. | 08-06-2009 |
20100032524 | APPARATUSES AND METHODS FOR JOINING COMPOSITE MEMBERS AND OTHER STRUCTURAL MEMBERS IN AIRCRAFT WING BOXES AND OTHER STRUCTURES - Apparatuses and methods for joining composite members and other structural members in aircraft wings and other structures. An aircraft wing box structure configured in accordance with one embodiment of the invention includes a first composite member having a first surface portion positioned at an angel relative to a second surface portion of a second composite member. The wing box structure of this embodiment further includes at least one metallic joining member having an upstanding leg portion extending from a base portion. The base portion of the joining member is bonded to the first surface portion of the first composite member with a first portion of adhesive, and the upstanding leg portion of the metallic joining member is bonded to the second surface portion of the second composite member with a second portion of adhesive. | 02-11-2010 |
20100170990 | COMPOSITE SPARS - According to one aspect, the present invention relates to a method of manufacturing at least one non-uniform thickness composite spar component. The method comprises braiding a plurality of fibres over a non-cylindrical mandrel to form a variable thickness shaped fibre preform, flattening the shaped fibre preform and cutting the flattened shaped fibre preform to obtain the at least one non-uniform thickness composite spar component. Spars made according to various embodiments of the present invention are faster and less expensive to manufacture than conventional composite spar components. | 07-08-2010 |
20120193473 | TORSION BOX SKIN STIFFENED WITH NON PARALLEL STRINGERS - Torsion box of an aircraft stabilizing surface comprising a front spar ( | 08-02-2012 |
20160039513 | LONGITUDINAL PLY LAYUP OF COMPOSITE SPAR - A structural component, including a composite tapered wing spar having a web and two flanges on opposite sides of the web, the composite tapered wing spar having a first fiber layer made up of a plurality of plies, wherein the plies have respective longitudinal axes that are straight, wherein a first ply of the plurality of plies is effectively parallel to a respective direction of extension of one of the flanges at a first transition zone of the one flange and web, wherein a second ply of the plurality of plies is effectively parallel to a respective direction of extension of the other of the flanges at a second transition zone of the other flange and web, and wherein at least most plies of the plurality of plies of the first layer located between the first ply and the second ply extend at respective oblique angles relative to the respective directions of extensions of the first ply and the second ply. | 02-11-2016 |
20160039514 | LATERAL PLY LAYUP OF COMPOSITE SPAR - A structural component, including a composite tapered wing spar including a first fiber layer and a main web, wherein respective longitudinal axes of fibers making up the first layer at least substantially lying on a plane corresponding to the main web of the wing spar are curved over at least most of the respective lengths of the fibers. | 02-11-2016 |
244123900 | Tubular spar | 1 |
20130240671 | Attachment of Aircraft Ribs to Spars Having Variable Geometry - An aircraft wing includes a rib attached by a joint to a tubular spar that varies in cross sectional shape during flight. The joint includes a ring attached to the tubular spar, and pivot pins connecting the ring with the rib. The pivot pins allow relative movement between the rib and the tubular spar as the tubular spar varies in cross sectional shape. | 09-19-2013 |