Patent application number | Description | Published |
20080210820 | AIRCRAFT FLOOR AND METHOD OF ASSEMBLY - The invention relates to aircraft floor assemblies and to methods for their assembly. In one embodiment, an aircraft comprises at least one fuselage section and at least one floor section. At least one system component is installed to the floor section prior to installation of the floor section in the fuselage of the aircraft. In another embodiment, a floor section adapted to be installed in an aircraft includes at least one system component installed to the floor section while it is outside of the aircraft. In yet another embodiment, a method is disclosed for assembling an aircraft. The method comprises installing at least one system component to a floor section, and installing the floor section into a fuselage section of the aircraft. | 09-04-2008 |
20080282523 | COMPOSITE SEAT PAN STRUCTURE FOR A LIGHTWEIGHT AIRCRAFT SEAT ASSEMBLY - An aircraft passenger seat configured in accordance with an embodiment of the invention utilizes composite materials to achieve significant weight savings relative to conventional seat designs. The seat includes one or more lightweight composite support legs, a lightweight composite seat pan, and a lightweight composite seat back structure. The support legs are coupled to the seat pan, which is in turn coupled to the seat back structure. The support legs utilize composite frame elements that are formed as continuous compression molded composite extrusions. The seat pan includes composite fore and aft cross beams that are also formed as continuous compression molded composite extrusions. The aft cross beam includes a rear flange that serves as a flexible “hinge” for the seat back structure. The seat can leverage producible and relatively inexpensive composite manufacturing techniques such that the seat can be economically produced for use as an economy class seat. | 11-20-2008 |
20080290242 | COMPOSITE LEG STRUCTURE FOR A LIGHTWEIGHT AIRCRAFT SEAT ASSEMBLY - An aircraft passenger seat configured in accordance with an embodiment of the invention utilizes composite materials to achieve significant weight savings relative to conventional seat designs. The seat includes one or more lightweight composite support legs, a lightweight composite seat pan, and a lightweight composite seat back structure. The support legs are coupled to the seat pan, which is in turn coupled to the seat back structure. The support legs utilize composite frame elements that are formed as continuous compression molded composite extrusions. The seat pan includes composite fore and aft cross beams that are also formed as continuous compression molded composite extrusions. The aft cross beam includes a rear flange that serves as a flexible “hinge” for the seat back structure. The seat can leverage producible and relatively inexpensive composite manufacturing techniques such that the seat can be economically produced for use as an economy class seat. | 11-27-2008 |
20080308224 | Flexible Shape Low Volume Autoclave - Techniques and apparatus for providing a flexible shape low volume autoclave are disclosed. In one embodiment, an autoclave includes an elongated pressure vessel that is sealed on both ends and has a circumferential joint between a first portion and a second portion. The autoclave further includes the portions defining an interior configured for accepting an elongated part, the joint being configured to create an angle between the portions and further creating an opening with a seal, the opening facilitating an insertion of the part into the interior, and the seal enabling pressurization of the interior. | 12-18-2008 |
20090061144 | Process for Marking Composite Panel - A process for marking a composite panel prior to curing for subsequent identification. An illustrative embodiment of the process includes applying a label strip made of a resin-permeable material to a composite panel formed of a resin and curing the panel to an elevated temperature such that the resin at least partially permeates the label strip. A marked composite panel is also disclosed. | 03-05-2009 |
20090084899 | COMPOSITE WING-BODY JOINT - Embodiments of integral composite panels and joints for composite structures are described In one implementation, an integrated panel spanning substantially the entire wingspan of an aircraft, includes at least a center portion and a pair of outwardly projecting wing portions. The portions may include a skin formed from successive layers or plies of composite material which overlap and offset at the joint between respective sections creating a pad-up area to carry loads between the portions. In a particular implementation, the skin is laid over one or more structural stringers which are transitioned into the joints between sections such as by tapering of the thickness and/or stiffness of the stringer. | 04-02-2009 |
20090084925 | COMPOSITE LEG STRUCTURE FOR A LIGHTWEIGHT AIRCRAFT SEAT ASSEMBLY - A lightweight leg assembly for an aircraft seat assembly includes a leg frame comprising at least one leg attachment bracket and a main frame member carried by the at least one leg attachment bracket and comprising a thermoplastic material. At least one track fitting may be carried by the leg frame. A method of fabricating a leg assembly for an aircraft seat assembly is also disclosed. | 04-02-2009 |
20090104398 | COMPOSITE ARTICLE HAVING REINFORCING FIBERS ORIENTED TO SUPPRESS OR DELAY PLY SPLITTING - A composite article comprises a plurality of reinforcing fibers embedded in a matrix. The fibers have a fiber orientation of ±α with respect to an axis of loading, where α=2 to 8 degrees to suppress or delay ply splitting. | 04-23-2009 |
20090277992 | Composite leg for landing gear assembly - A composite leg for a landing gear assembly includes a composite compression cap including reinforcing fibers that provide strength in compression, and a tension cap including reinforcing fibers that provide strength in tension. The composite leg further includes a torque box including carbon reinforcing fibers for providing torsional rigidity of the leg and carrying shear flow between the caps. The carbon fibers in the torque box are oriented at +θ and −θ with respect to a longitudinal axis of the leg, where θ is between 35 and 55 degrees. | 11-12-2009 |
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 |
20100187894 | Composite Seat Pan Structure For A Lightweight Aircraft Seat Assembly - An aircraft passenger seat configured in accordance with an embodiment of the invention utilizes composite materials to achieve significant weight savings relative to conventional seat designs. The seat includes one or more lightweight composite support legs, a lightweight composite seat pan, and a lightweight composite seat back structure. The support legs are coupled to the seat pan, which is in turn coupled to the seat back structure. The support legs utilize composite frame elements that are formed as continuous compression molded composite extrusions. The seat pan includes composite fore and aft cross beams that are also formed as continuous compression molded composite extrusions. The aft cross beam includes a rear flange that serves as a flexible “hinge” for the seat back structure. The seat can leverage producible and relatively inexpensive composite manufacturing techniques such that the seat can be economically produced for use as an economy class seat. | 07-29-2010 |
20100187895 | Composite Seat Back Structure for a Lightweight Aircraft Seat Assembly - An aircraft passenger seat configured in accordance with an embodiment of the invention utilizes composite materials to achieve significant weight savings relative to conventional seat designs. The seat includes one or more lightweight composite support legs, a lightweight composite seat pan, and a lightweight composite seat back structure. The support legs are coupled to the seat pan, which is in turn coupled to the seat back structure. The support legs utilize composite frame elements that are formed as continuous compression molded composite extrusions. The seat pan includes composite fore and aft cross beams that are also formed as continuous compression molded composite extrusions. The aft cross beam includes a rear flange that serves as a flexible “hinge” for the seat back structure. The seat can leverage producible and relatively inexpensive composite manufacturing techniques such that the seat can be economically produced for use as an economy class seat. | 07-29-2010 |
20100219294 | COMPOSITE BEAM CHORD BETWEEN REINFORCEMENT PLATES - A composite beam chord is between first and second reinforcement plates. The beam chord includes a first ply of reinforcing fibers with a fiber orientation of +α degrees with respect to a longitudinal axis of the beam chord and a second ply of reinforcing fibers with a fiber orientation of −α degrees with respect to the longitudinal axis. The angle α is between 2 and 12 degrees for suppression or delay of ply splitting. | 09-02-2010 |
20100276541 | Method of Absorbing Energy in an Aircraft Passenger Seat Assembly - An aircraft seat assembly configured in accordance with an example embodiment of the invention offers a light weight and comfortable seat cushioning system that also provides energy-absorption and enhanced passenger maneuverability in extreme conditions such as may be experienced in a hard landing situation. The cushioning system includes a crushable, energy-absorbing layer, a main cushioning layer, a smaller ishial insert layer which may be the same as the main cushioning material and a semi-dynamic pneumatic cell which uses a dual action breather valve to vary its inflation with changes in cabin pressure. The seat cushion may be finished with a covering of cloth or upholstery. | 11-04-2010 |
20100282904 | AIRCRAFT HAVING A FORWARD-FACING SECTION THAT DEFLECTS ELASTICALLY UNDER IMPACT LOADS - An aircraft comprises a forward-facing aircraft section including composite aircraft skin and a substructure for the skin. The substructure includes a plurality of hoop-shaped composite frames. The frames are designed to deflect elastically under bird impact loads. | 11-11-2010 |
20100320320 | AEROPSPACE STRUCTURE INCLUDING COMPOSITE BEAM CHORD CLAMPED BETWEEN REINFORCEMENT PLATES - A structure for an aerospace vehicle includes a composite beam chord clamped between first and second metal plates. The beam chord is clamped at a force that precludes or reduces beam chord delamination under axial loading during operation of the vehicle. | 12-23-2010 |
20110045232 | COMPOSITE STIFFENERS FOR AEROSPACE VEHICLES - An aerospace vehicle includes a plurality of composite stiffeners. Each stiffener of the plurality has a stack of plies of reinforcing fibers. At least some of the plies in the stack have reinforcing fibers oriented at ±α with respect to an axis of primary loading, where a is between 2 and 12 degrees. At least some of the plies in the stack have reinforcing fibers oriented at ±β with respect to the axis of primary loading, where β is between 50 and 85 degrees. | 02-24-2011 |
20120067513 | COMPOSITE LEG STRUCTURE FOR A LIGHTWEIGHT AIRCRAFT SEAT ASSEMBLY - An aircraft passenger seat configured in accordance with an embodiment of the invention utilizes composite materials to achieve significant weight savings relative to conventional seat designs. The seat includes one or more lightweight composite support legs, a lightweight composite seat pan, and a lightweight composite seat back structure. The support legs are coupled to the seat pan, which is in turn coupled to the seat back structure. The support legs utilize composite frame elements that are formed as continuous compression molded composite extrusions. The seat pan includes composite fore and aft cross beams that are also formed as continuous compression molded composite extrusions. The aft cross beam includes a rear flange that serves as a flexible “hinge” for the seat back structure. The seat can leverage producible and relatively inexpensive composite manufacturing techniques such that the seat can be economically produced for use as an economy class seat. | 03-22-2012 |
20120121866 | METHOD OF LAYING UP PREPREG PLIES ON CONTOURED TOOLS USING A DEFORMABLE CARRIER FILM - Composite prepreg is laid up over a tool by placing prepreg material on a carrier film and using the carrier film to apply the prepreg material to the tool. The prepreg is conformed to contours of the tool by deforming the carrier film. | 05-17-2012 |
20120223187 | DIAMOND SHAPED WINDOW FOR COMPOSITE AND/OR METALLIC AIRFRAME - An aircraft fuselage may include a barrel section having a side region. The fuselage may include a first cutout and a second cutout formed in the side region in side-by-side relation to one another. The fuselage may provide a direct load path extending along the barrel section. The load path may extend substantially continuously from a lower portion of the side region generally under the first cutout to an upper portion of the side region generally over the second cutout. | 09-06-2012 |
20120234972 | Composite leg for landing gear assembly - A composite leg for a landing gear assembly includes a composite compression cap including reinforcing fibers that provide strength in compression, and a tension cap including reinforcing fibers that provide strength in tension. At least some of the fibers are oriented at +α and −α with respect to a longitudinal axis of the leg, where α is between 2 and 8 degrees. | 09-20-2012 |
20130214586 | COMPOSITE FIBER BICYCLE WHEELS - Carbon fiber bicycle wheels are formed from parts cut from carbon fiber cloth and then joined together to form a rim, sidewalls, spokes, flanges and a center tunnel on which the flanges are mounted. The parts are then assembled, bonded together, and cured to form a wheel. During assembly, the spokes and the wheel are placed in tension by moving the flanges outwardly on the center tunnel after assembly and then bonding them in place to stiffen and strengthen the wheel. The spokes of the drive side of the rear wheel are specially shaped to accommodate torque transfer forces generated by pedaling. | 08-22-2013 |
20130330503 | Optimized Cross-Ply Orientation in Composite Laminates - A composite laminate has a primary axis of loading and comprises a plurality resin plies each reinforced with unidirectional fibers. The laminate includes cross-plies with fiber orientations optimized to resist bending and torsional loads along the primary axis of loading. | 12-12-2013 |
20140001820 | BICYCLE WHEEL WITH UNITARY SIDE CONSTRUCTION | 01-02-2014 |
20140027048 | METHOD OF LAYING UP PREPREG PLIES ON CONTOURED TOOLS USING A DEFORMABLE CARRIER FILM - A method is presented. The method comprises identifying a desired shape of a ply on a tool, in which the ply has a fiber orientation; identifying a cut shape for the ply, in which the cut shape is different than the desired shape; cutting a composite prepreg ply to have the cut shape, the composite prepreg ply having the fiber orientation; using a deformable carrier to apply the composite prepreg ply having the cut shape to the tool such that the composite prepreg ply has the desired shape on the tool. | 01-30-2014 |
20140070053 | PASSIVE LOAD ALLEVIATION FOR AERODYNAMIC LIFT STRUCTURES - An aerodynamic lift structure comprises unbalanced composite skin that couples twist and bending. | 03-13-2014 |
20140076477 | METHOD OF FORMING A WINDOW CUTOUT IN AN AIRFRAME - A method of forming cutouts in an aircraft fuselage may include forming a first cutout and a second cutout in side-by-side relation to one another in a side region of the fuselage. The method may further include configuring the first cutout and the second cutout such that a direct load path extends along the side region substantially continuously from a lower portion of the side region generally under the first cutout to an upper portion of the side region generally over the second cutout. | 03-20-2014 |
20140352451 | Apparatus and Method for Load Testing a Coupon - An apparatus for load testing a coupon may include a test frame and a pair of spaced apart load balancing assemblies connected to the test frame, each load balancing assembly of the pair of load balancing assemblies including a load leveling mechanism connected to the test frame and a plurality of spaced apart load plates, each load plate of the plurality of load plates having a first end pivotably connected to the load leveling mechanism and a second end, the second end of each load plate including a friction holder configured to frictionally engage an end of the coupon, wherein at least one load balancing assembly of the pair of load balancing assemblies is movable along an axis of movement with respect to an opposed load balancing assembly to communicate a load to the coupon. | 12-04-2014 |
20150017362 | Thermoplastic and Titanium Sandwich Structures - A method and apparatus for forming a sandwich structure is presented. A sandwich structure comprises a metallic core layer and a thermoplastic layer on a first side of the metallic core layer. The thermoplastic layer is consolidated against the first side of the metallic core layer. | 01-15-2015 |
20150020603 | Apparatus, System and Method for Compression Testing of Test Specimens - There is provided an apparatus for compression testing. The apparatus has a base assembly having an end load element attached to the base assembly, the base assembly being rigid. The apparatus has a support assembly attached to the base assembly, and having a plurality of window portions. The apparatus has a core assembly installed within the support assembly, the core assembly being crushable and configured to protect the support assembly and the base assembly from fracture loads generated during compression testing. The base assembly, the support assembly, and the core assembly together form an apparatus for compression testing of a test specimen having a notch portion. The apparatus is configured for use with an optical strain measurement system. When the test specimen is installed in the support assembly, the test specimen and the notch portion are visible to the optical strain measurement system through the plurality of window portions. | 01-22-2015 |