Class / Patent application number | Description | Number of patent applications / Date published |
244124000 | Sectional | 7 |
20090001218 | Stifffened multispar torsion box - The invention relates to an integrated structure of a composite material multispar torsion box ( | 01-01-2009 |
20090072088 | FLYAWAY KABOBS - An aircraft wing made of a composite material, and its method of manufacture, require a plurality of kabobs (i.e. substantially rectangular shaped hollow tubes having an open end and a closed end). Of these kabobs, several are aligned end-to-end, to create a section. Several sections are then positioned side-by-side and covered by a layer of composite material to define an aerodynamic surface for the wing. The juxtaposed sections also establish spar webs for the wing, and the closed ends of the juxtaposed sections establish transverse ribs for the wing. Thus, the kabobs form the main load-bearing member of the wing. The sections of composite material are co-cured with the composite material of the aerodynamic surface. | 03-19-2009 |
20090302159 | Aircraft Wing Including a Plurality of Dismountable Members - The invention relates to an aircraft wing including two members removably connected end to end by a coupling means including: a male coupling part with spaced opposed upper and lower faces, a first face being planar while the second face has a longitudinal relief ( | 12-10-2009 |
20130037655 | METHOD OF SEALING A GAP - A method of sealing a gap between first and second aerodynamic surfaces. The width of the gap between the two surfaces is measured to obtain a gap measurement. The width of a seal member is pre-formed in accordance with the gap measurement. The seal member is fitted into the gap such that the seal member is substantially flush with the first and second aerodynamic surfaces. Apparatus for performing the method is also described. The apparatus comprising: a metrology device adapted to measure the width of the gap between the first and second aerodynamic surfaces; a seal member dispenser for dispensing a seal member; and a cutter adapted to cut the seal member to size in accordance with the measurements obtained by the metrology device. | 02-14-2013 |
20130068888 | AIRFOIL STRUCTURE - An airfoil structure including a plurality of molded monolithic members that extend in a side-by-side manner along the spanwise direction of the airfoil structure. Each molded monolithic member is realized from continuous material that is molded to form a corrugated portion with top and bottom flange portions extending from the corrugated portion. As a result of the molding operation, the corrugated portion is integrally formed with and structurally joined to the top and bottom flange portions. The top flange portions of the side-by-side arrangement of molded monolithic members define a portion of the top surface of the airfoil structure. The bottom flange portions of the side-by-side arrangement of molded monolithic members define a portion of the bottom surface of the airfoil section. The corrugated portions of the side-by-side arrangement of monolithic members define internal support structures (preferably closed-cell cores) extending along the spanwise direction of the airfoil structure. The side-by-side arrangement of monolithic members structurally integrates portions of the top skin and bottom skin to support structures that extend between such top and bottom surface portions. Such structural integration provides enhanced structural resistance to torsional loading of the airfoil section due to the fact that such loads are resisted by the continuous material that makes up the both top and bottom surfaces as well as the support structures extending therebetween. | 03-21-2013 |
20150014482 | UNMANNED AERIAL VEHICLE (UAV) WITH INTER-CONNECTING WING SECTIONS - An unmanned aerial vehicle (UAV) is described. The UAV may include a fuselage assembly and a plurality of inter-connecting wing sections. The inter-connecting wing section may include a connecting assembly on opposing lateral ends. The connecting assembly may be complementary on opposing ends. The fuselage assembly may include a complementary set of the connecting assembly on opposing lateral ends. The complementary set of the connecting assembly may be configured to connect to at least two of the inter-connecting wing sections. At least a portion of the inter-connecting wing sections may include a solar array having solar panels. | 01-15-2015 |
20150053818 | UPPER JOINTS BETWEEN OUTBOARD WING BOXES AND WING CENTER SECTIONS OF AIRCRAFT WING ASSEMBLIES - An upper joint of a wing assembly of an aircraft includes an outboard upper wing panel, a center upper wing panel, a rib, and an upper joint assembly operatively interconnecting the outboard upper wing panel, the center upper wing panel, and the rib. In some embodiments, outboard upper stringers may be configured differently than center upper stringers. In some embodiments, a subset of the center upper stringers may not directly oppose the outboard upper stringers. In other embodiments, for at least a substantial fore/aft span of the upper joint, each of the center upper stringers may directly oppose an outboard upper stringer. | 02-26-2015 |