| Entries |
| Document | Title | Date |
|---|
| 20080223987 | Rib element and composite flange for aircraft - A rib element for aircraft and a composite flange for use in aircraft. The rib element ( | 09-18-2008 |
| 20080245927 | METHODS AND SYSTEMS FOR COMPOSITE STRUCTURAL TRUSS - Methods and structures for a composite truss structure are provided. The structure includes an upper chord member, a lower chord member, and a plurality of web members extending therebetween. Each of the upper chord member, the lower chord member, and the plurality of web members are formed of a continuous composite fiber positioned in each of the upper chord member, the lower chord member, and each of the plurality of web members wherein each of the upper chord member, the lower chord member, and the plurality of web members includes a predetermined number of passes of the continuous composite fiber corresponding to a predetermined load. The composite truss structure also includes at least a first gusseting plate coupled to the upper chord member, the lower chord member, and the plurality of web members. | 10-09-2008 |
| 20080245928 | METHODS AND SYSTEMS FOR COMPOSITE STRUCTURAL TRUSS - Methods and structures for a composite truss structure are provided. The structure includes a web formed of a plurality of sheets of composite material, each sheet including a first face and an opposing second face and each face including a length and a width. Each of the plurality of sheets are coupled to at least one other of the plurality of sheets face to face such that the length and width of each face substantially match the length and width of a face of an adjacent sheet. The plurality of sheets are formed to include an upper chord member, a lower chord member, and a plurality of web members extending therebetween. The structure also includes at least a first flange plate coupled to the web proximate an outer periphery of the web. | 10-09-2008 |
| 20080265094 | Structural Element and Method of Manufacture - In a method for manufacturing a structural element intended for aeronautical construction, at least a first and second metal block are made available, the limit of elasticity under compression of the first metal block being greater than that of the second metal block. The first metal block is machined in such a manner as to obtain a first machined monolithic part which has a first web portion and at least one stringer element whose height is such that a stringer portion extends beyond the first web portion. There is prepared, by shaping the second metal block, at least one second part having at least a second web portion capable of co-operating with the first web portion to form the web. The first monolithic part and the second part are assembled by placing the first and second web portions end-to-end over their entire common length. | 10-30-2008 |
| 20090026316 | SOLAR POWERED AERIAL VEHICLE - A solar powered aerial vehicle includes an elongated airframe incorporating lifting and control surfaces, a mechanism for propelling the airframe through the air such that lift developed by the lifting surface is equal to or greater than the weight of the aerial vehicle, a planar solar sail coupled to the airframe and having at least one surface adapted to collect solar energy during the day and to power the propelling mechanism with a first portion of the energy collected, and an apparatus such as a fuel cell/electrolyzer for storing a second portion of the solar energy collected by the solar sail during the day and for powering the propelling mechanism with the second portion of energy during the night. The vehicle is capable of continuous operation at northern latitudes and during the winter months for extended periods without landing or refueling. | 01-29-2009 |
| 20090065644 | Device and method for non-symmetrical mixed carbon-metal assembly - The invention concerns an assembling device including a splice bar ( | 03-12-2009 |
| 20090078825 | METHOD FOR MANUFACTURING AND ATTACHMENT OF WING FAIRINGS - A method and apparatus for manufacturing and installing a fairing on an aircraft. In one advantageous embodiment, a composite fairing is installed on the aircraft. A composite sheet having a form of the composite fairing is formed. A plurality of cured composite tiles is created from the composite sheet, wherein spaces are present between the plurality of composite tiles. The plurality of composite tiles is cured to form the composite fairing. The composite fairing is attached to a surface of the aircraft. The spaces between the plurality of composite tiles are filled with a flexible filler. | 03-26-2009 |
| 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 |
| 20090114771 | Split Return Wing - The present invention concerns a sort of split return wing. The split return wing contains main wing body, which connects with the fuselage main support frame, and the tilting-able segments of main wing-spar are installed on the fuselage main support frame actively. Two ends of the tilting-able segments of main wing-spar connect with the fixed segments of main wing-spar actively. Two split return wing sector wing-pieces are installed on the right and the left tilting-able segment of main wing-spar separately. There is one group tilting-able dynamic device in front of every split return sector wing-piece. The split return sector wing-pieces can be in the perforation spaces of the main wing body, and their shapes are same. And two big wingspan outer-wings are set on the right and left of the main wing body separately. The Split return wing will decrease unbalanced moment of aircraft to the minimum when the aircraft is taking off & landing vertically. They also will decrease the air resistance of the whole wing to the minimum when the aircraft flies transitionally. At the same time, the whole wing, especially the big wingspan outer-wings still keep horizontally from beginning to end. In this case, it will ensure that the aircraft is taking off & landing vertically, and will fly transitionally toward horizontal high-speed flight smoothly, so, the wing could satisfy the demand of persons. | 05-07-2009 |
| 20090121082 | Method of locally reinforcing a composite element and reinforced aircraft wing structure central box section - A method of locally reinforcing an element made of composite material having a longest dimension, such as a composite beam, which is intended to bear multidirectional forces. To do that, at least one metal reinforcing piece is secured to the composite element, at a point on the composite element that is intended to bear vertical forces. The same may be done at each of those points on the composite element that is intended to bear vertical forces. | 05-14-2009 |
| 20090189019 | RIB FOR AIRCRAFT WING AND METHODS FOR THE MANUFACTURE THEREOF - There is provided a method of manufacturing a rib for an aircraft wing, the method comprising providing a billet of material for forming the rib, machining away material from all sides of the billet to form a rib for use in an aircraft, the rib including a web that extends between first and second flanged portions, each flanged portion having a flange that facilitates fixing of the rib to another component of the aircraft, wherein the material that forms the web extends diagonally across the billet, the web having a first face on a first side and a second face on a second side opposite to the first side of the web, and the first flanged portion extends more to the first side of the web than to the second side and the second flanged portion extends more to the second side of the web than to the first side. | 07-30-2009 |
| 20090200423 | WING COVER PANEL ASSEMBLY AND WING COVER PANEL FOR AN AIRCRAFT WING AND A METHOD OF FORMING THEREOF - A wing cover panel assembly, wing cover and method of forming thereof are disclosed in which an attachment surface of the wing cover panel is provided with a locating channel into which a wing structural element such as a stringer or spar is captured so as to fix the wing structural element to the wing cover panel. | 08-13-2009 |
| 20090277996 | Wing and empennage leading edge structure made of thermoplastic material with a stiffened double shell configuration - A leading edge structure is described for wing structures and empennage, comprising an outer shell suitable to define a front portion of a airfoil. The outer shell is formed by a bent plate of fiber-reinforced thermoplastic resin composite material. The structure further comprises | 11-12-2009 |
| 20090294589 | METHODS AND APPARATUS FOR AN INTEGRATED AERODYNAMIC PANEL - An integrated aerodynamic panel—e.g., for a trailing edge or leading edge of an aircraft aerodynamic surface—includes a first panel region defining inner and outer mold lines, and a second panel region contiguous with and extending from the first panel region in a tapering fashion. A splice plate region extends from the second panel region and includes an edge band region configured to accept a fastener. A filler region (e.g., a SYNCORE or fiberglass structure) adjacent the second panel region has an exposed surface substantially flush with the outer mold line. | 12-03-2009 |
| 20090314892 | AIRPLANE WING STRUCTURE - A rib of an airplane wing is prevented from deforming due to a machining load when machining a rivet hole in parts where the rib and a skin are joined. With regard to a rib that provides a connection between first and second spars of the airplane wing, the rib is formed with mounting flanges secured to a skin via a rivet, a stringer through hole for a stringer to be positioned through, and first and second cutouts facing parts where the first and second spars and the skin are connected. Since reinforcing beads are formed along the mounting flanges and reinforcing flanges are formed so as to extend in the span direction from the edges of the stringer through hole and the first and second cutouts and be connected integrally to the mounting flanges, the stiffness of the rib toward a load in the vertical direction when drilling a rivet hole can be enhanced. | 12-24-2009 |
| 20100006700 | AIRCRAFT WINGS HAVING CONTINUOUSLY TAILORED STRUCTURAL STRENGTH - The structural strength of an aircraft wing is continuously tailored along its length to closely match continuously varying imposed wing loads. The wing comprises upper and lower skins each formed from panels joined together. Each of the skin panels includes a stiffening web sandwiched between and joined to the inner and outer facesheets. The web has a repeating pattern and at least one dimension that continuously varies along the length of the panel. | 01-14-2010 |
| 20100044511 | Aircraft structure - An aircraft wing ( | 02-25-2010 |
| 20100108810 | Integration system for lifting surfaces semi-parts in aircrafts - The lifting surface consists of a torsion box capable of bearing aerodynamic and inertial loads, and the semi-parts ( | 05-06-2010 |
| 20100116937 | COLLAPSIBLE WING BEAMS AND METHOD - A wing, such as a wing for an unmanned aerial vehicle (UAV), includes a beam or box that can be selectively expanded from a collapsed condition, to increase the thickness of the wing. The beam may include a pair of plates that are close together when the beam is in a collapsed condition, and separate from one another to put the beam in an expanded condition. The plates may be substantially parallel to each other, and may have shape memory foam and/or resilient devices, such as coil springs, between them, in order to provide a force to separate the plates before, during, and/or after deployment of the wing. The expandable/collapsible beam may have a lock mechanism to lock it into place when the beam is in an expanded condition. | 05-13-2010 |
| 20100140404 | Composite wing panel - A composite wing panel is disclosed. In one embodiment, a wing panel for an aircraft includes an external skin having a substantially smooth laminar surface, the external skin including multiple layers of a cured material; a sealed core material located within the external skin, the core material having first and second side opposing sides and having been substantially evacuated of air; and a support element disposed within the external skin, the external skin and support element being co-bonded or co-cured together. | 06-10-2010 |
| 20100148007 | Cover for an aircraft structure - A cover for an aircraft structure, in particular for nose parts of the vertical tail, horizontal tail or the wing, including a skin and support structure. The skin is arranged on the support structure and the support structure includes a plurality of ribs and a plurality of stringers. The plurality of stringers are arranged on the plurality of ribs to support the skin. Also provided is an aircraft having such a cover. | 06-17-2010 |
| 20100170989 | ELONGATE COMPOSITE STRUCTURAL MEMBERS AND IMPROVEMENTS THEREIN - A composite material elongate structural member, such as a spar, for use in an aerospace structure, comprises a web disposed between upper and lower flanges. The web may include a clockwise twist about an axis parallel to the length L at a first portion towards the wing-root-end of the spar and a counter-twist in the anticlockwise direction at a second portion towards the wing-tip-end of the spar. The geometry of the spar may vary non-linearly along its length (L) so that the developed width of the spar as measured from a distal edge of the upper flange via the web to a distal edge of the lower flange varies linearly with increasing distance along the length (L). The risk of causing, during fabrication of the spar, undesirable creasing, stressing or stretching of composite material layers in a region in which the geometry of the member varies non-linearly may be reduced by means of such an arrangement. | 07-08-2010 |
| 20100193635 | COMPOSITE WING SLAT FOR AIRCRAFT - An aircraft wing slat is formed from composite materials using lay-up and vacuum bagging techniques. The slat lay-up comprises a central honeycomb core sandwiched between upper and lower composite skins, a pre-cured spar and pre-cured stiffeners. After the lay-up is cured and removed from a lay-up mold, leading edge strengthening ribs and a preformed composite nose skin are installed to complete the slat. | 08-05-2010 |
| 20100193636 | METHOD OF MANUFACTURING AN INTEGRAL PROFILE MONOLITHIC WING STRUCTURE - A method of manufacturing a wing structure includes laying a plurality of layers of preimpregnated material on a first mould half and on a second mold half so as to form a first fresh skin and a second fresh skin of the wing structure. A plurality of layers of preimpregnated material are laid in succession on a shaped apparatus to form a fresh leading edge skin of the wing structure. Fresh spars of preimpregnated material are formed. A wedgelike body of expanded plastics material is formed, this body being designed to be interposed between the first and second skins at the trailing edge of the wing structure. The fresh spars are positioned in a coordinated way on the first fresh skin, removable support members also positioned next to the spars. The second mold half is turned over on to the first mold half so as to position the second fresh skin on the spars and the supports, to produce a fresh wing structure. The fresh wing structure is subjected to a polymerization cycle, using a vacuum bag. | 08-05-2010 |
| 20100230541 | Integrated composite skin for aircraft mid-box lifting surfaces - A composite skin ( | 09-16-2010 |
| 20100230542 | 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 form a single piece of material and has differential strength along its length. | 09-16-2010 |
| 20100243808 | SHAPE-CHANGE MATERIAL AND METHOD - A shape-change material includes a shape memory material layer with an electrically conductive layer on a surface of the shape memory material layer. The conductive material may be used to heat the shape memory material by electrical resistance heating. The conductive material may be a primary heater, providing the heating to cause softening or shape change in the shape memory material, or may be a secondary heater in conjunction with a greater amount of heating from a primary heater, such as a conductive plate that provides electrical resistance heating to a surface of the shape memory material on an opposite side of the shape memory material from the conductive material. One use for the shape-change material is as the skin material for a shape changing material. | 09-30-2010 |
| 20100258674 | TRACK CONTAINER - An aircraft wing assembly comprising: a spar; a fuel tank; a track container which is attached to the spar and extends into the fuel tank; a track which extends through the spar and into the track container; and a high-lift device, such as a slat or flap, carried by the track. The track container comprises a stiffening element encased in an elastomeric sheath. The track container is manufactured by placing a stiffening element and elastomeric material together in a mould; and compressing and heating them to cure and shape the elastomeric material. | 10-14-2010 |
| 20100276542 | REINFORCED BLOCK MADE FROM COMPOSITE MATERIAL AND METHOD FOR REINFORCING A COMPOSITE BLOCK - A block including at least one glass ply at least partially covering an outer surface of a core made from composite material. A method for reinforcing a block made from a composite material, including a glass ply placed in a mould, such as to cover the base of the mould; the block is positioned in the mould; the edges of the glass ply are folded such that the glass ply is moulded to the outer edge of the block; the mould is closed with a cover; the block housed inside the mould is cured in an oven such as to polymerize the glass ply; and the glass-ply-covered block is recovered. | 11-04-2010 |
| 20100282906 | MULTI-LAYER METAL/SHAPE MEMORY POLYMER ROLL-UP WING STRUCTURES FOR FITMENT-CONSTRAINED AIR VEHICLES - A laminated wing structure includes at least one layer of metal material and at least one layer of a shape memory polymer (SMP) material. The SMP is heated to a temperature in its glass transition band Tg to roll the wing around the air vehicle into a stored position. The metal layer(s) must be thin enough to remain below its yield point when rolled up. In preparation for launch, the SMP material is thermally activated allowing the strain energy stored in the layer of metal material to return the wing to its deployed position at launch. Once deployed, the SMP cools to its glassy state. The SMP material may be reinforced with fiber to form a polymer matrix composite (PMC). SMP may be used to provide shear strain relief for multiple metal layers. By offloading the motive force required to return the wing to its original deployed position from the SMP to the metal, the polymer does not acquire a permanent set and the wing may be deployed accurately. | 11-11-2010 |
| 20100327114 | METHOD OF MANUFACTURING A STRUCTURE - A method of manufacturing a structure, the method comprising: forming a panel assembly by bonding a stack of thickness control plies of composite material to a laminar composite panel, the stack of thickness control plies having a first edge proximate an edge of the laminar composite panel, a second edge opposite the first edge, and a ramp where the thickness of the stack of thickness control plies decreases towards the first or second edge; measuring the thickness of the laminate composite panel or the panel assembly; controlling the number of thickness control plies in accordance with the measured thickness; attaching a first component to the panel assembly, the first component having a surface which engages the laminar composite panel and a ramp which engages the ramp in the stack of thickness control plies; and attaching the laminar composite panel at or near its edge to a further component. | 12-30-2010 |
| 20110031349 | Pinned lug joint - A pinned lug joint comprising: a first part comprising two first lugs projecting from a bridge which extends between them; a second part pivotally coupled to the first part, the second part comprising a second lug positioned between the first lugs; and a sealing member, the sealing member being mounted to the first lugs and extending between them to seal an air gap between the second lug and the bridge at least when the second part is in a first position. The pinned lug joint may be used to attach a panel assembly to part of an aircraft. | 02-10-2011 |
| 20110049297 | AEROFOIL WITH EROSION RESISTANT LEADING EDGE - The present invention relates to an aerofoil having an erosion resistant leading edge. The aerofoil comprises an aerofoil main body portion and a leading edge portion. The leading edge portion comprises a plurality of functionally distinct parts, including at least; a first part for resisting abrasion of the leading edge portion, and a second part for resisting a bending force applied to the leading edge portion, and located behind the first part. | 03-03-2011 |
| 20110095133 | COVER TRAILING EDGE PROFILE - An aircraft wing assembly, comprising a front spar, a rear spar, and upper and lower wing covers extending between the front and rear spars, wherein the upper and/or lower wing cover overhangs the rear spar and has a non-linear trailing edge profile forming an array of tabs and cut-outs. Also, a method of assembling the aircraft wing. | 04-28-2011 |
| 20110147522 | METHOD OF STIFFENING A RIB - A method of stiffening a rib ( | 06-23-2011 |
| 20110147523 | PIPE COUPLING DEVICE FOR AIRCRAFT WING - An aircraft wing comprising first and second fuel pipe segments which are coupled together with a pipe coupling device comprising a corrugated tube formed from an elastomer filled with conductive material. The pipe coupling device is particularly useful for connecting together fuel pipe segments in an aircraft wing as it removes the need to attach bonding leads between fuel pipe segments to dissipate lightning currents and static. | 06-23-2011 |
| 20110174927 | AIRCRAFT COMPONENT WITH PANELS STIFFENED WITH STRINGERS - Aircraft component with panels ( | 07-21-2011 |
| 20110215201 | STRUT SYSTEM FOR THE STABILIZATION OF THE SHELL OF AN AERODYNAMIC AIRCRAFT COMPONENT FOR A COMMERCIAL AIRCRAFT - The invention relates to a strut system for the stabilisation of the shell ( | 09-08-2011 |
| 20110260004 | Parachute with One-Way Valve Device - A multi-celled ram-air parachute possessing one or more internal one-way valved air passages between at least two parachute cells to maintain positive air pressure within the parachute for the purpose of maintaining shape and rigidity when less than optimal airspeed is present thereby increasing a user's control and safety. | 10-27-2011 |
| 20110278397 | ALUMINUM-COPPER-LITHIUM ALLOY FOR A LOWER WING SKIN ELEMENT - The present disclosure relates to an alloy containing aluminum including, as a % by weight, 2.1 to 2.4% of Cu, 1.3 to 1.6% of Li, 0.1 to 0.5% of Ag, 0.2 to 0.6% of Mg, 0.05 to 0.15% of Zr, 0.1 to 0.5% of Mn, 0.01 to 0.12% of Ti, optionally at least one element chosen from among Cr, Sc, and Hf, the quantity of the element, if it is chosen, being from 0.05 to 0.3% for Cr and Sc, 0.05 to 0.5% for Hf, a quantity of Fe and Si each less than or equal to 0.1 and inevitable impurities at a rate of less than or equal to 0.05 each and 0.15 in total. The alloy can be used to produce extruded, rolled and/or forged products particularly suitable for the manufacture of elements for the lower wing skin of aircrafts. | 11-17-2011 |
| 20120037755 | WING STRUCTURE - A wing structure is provided, wherein the wing structure comprises; an upper covering, a lower covering, and a spar, the spar comprising; a spar web, an upper spar cap attached to the upper covering, and a lower spar cap attached to the lower covering, the wing structure also comprising a face spaced apart from the spar web extending between the upper and lower spar caps. The wing structure is arranged to contain fuel in a fuel containment area between the upper and lower coverings on one side of the spar web. The upper and lower spar caps extend from the spar web only on the other side of the spar web to the fuel containment area. | 02-16-2012 |
| 20120043422 | Multi-Spar Port Box Joint - A method for connecting a wing. A frame for a wing may be positioned relative to a fuselage of an aircraft. The frame may have bays and comprise a front spar, a rear spar, and a number of spars located between the front and rear spars. A first number of skin panels may be on a first side of the frame, and a second number of skin panels may be on a second side of the frame. The first side may be opposite to the second side. Openings may be in the first and second numbers of skin panels. The openings may be in locations such that each bay has an opening and such that the openings may alternate between the first side and the second side between adjacent bays in the bays. The frame may be attached to the fuselage using the openings to access an interior of the frame. | 02-23-2012 |
| 20120061515 | COMPOSITE STRUCTURING PANEL FOR THE TRAILING EDGE OF AN AIRCRAFT ELEMENT - The invention relates to a composite structuring panel ( | 03-15-2012 |
| 20120104168 | MANUFACTURING PROCEDURE OF A PART MADE OUT OF A COMPOSITE MATERIAL INTRODUCING A GEOMETRIC CHANGE IN ONE OF ITS FACES - A manufacturing procedure of a composite material part ( | 05-03-2012 |
| 20120112005 | Wing tip device attachment apparatus and method - A winglet ( | 05-10-2012 |
| 20120138746 | OBLIQUE PANEL AT THE REAR OF A CENTRAL BOX OF AN AIRCRAFT FUSELAGE - An aircraft structure includes a wing spar ( | 06-07-2012 |
| 20120153083 | OPTIMIZATION OF STRUCTURES SUBJECTED TO HOT GAS STREAMS - Optimisation of structures subjected to hot gas streams. The invention refers to a fairing ( | 06-21-2012 |
| 20120187246 | VENT STRINGER AND AIRCRAFT MAIN WING - A vent stringer | 07-26-2012 |
| 20120211603 | WING PANEL AND AIRCRAFT MAIN WING - There is provided a wing panel having improved formability at the time when the wing panel is curvedly formed by the peen forming method, and an aircraft main wing provided with the said wing panel. For a stringer member | 08-23-2012 |
| 20120273617 | REINFORCED AIRFOIL SHAPED BODY - The present invention relates to an airfoil shaped body with a leading edge and a trailing edge extending along the longitudinal extension of the body and defining a profile chord, the airfoil shaped body comprising an airfoil shaped facing that forms the outer surface of the airfoil shaped body and surrounds an internal volume of the body, a distance member that is connected to the facing inside the body and extends from the facing and into the internal volume of the body, and at least one reinforcing member that operates in tension for reinforcing the facing against inward deflections and that is connected to the facing inside the internal volume of the body at the same side of the profile chord as the connection of the distance member to the facing and to the distance member at a distance from the facing. | 11-01-2012 |
| 20130001360 | BRACKET - An integrated bracket assembly for attachment to a convex outer corner surface of a torsion box of an aerofoil structure, the bracket assembly comprising a bracket strip having a plurality of brackets arranged spaced side by side, and connected by an infill rail integrally formed with the bracket strip, wherein the infill rail has a concave surface for mating with the convex surface of the torsion box. The torsion box may be of a “U-box” construction where a front spar and a rear spar are integrally formed with either an upper or lower torsion box cover to form an omega-shaped unitary component, and the other cover is attached to the omega-shaped component to provide an enclosed volume. The bracket strip may be used for attaching a leading/trailing edge structure of the aerofoil to the torsion box. | 01-03-2013 |
| 20130026294 | MANUFACTURING PROCEDURE OF A COMPOSITE PART OF A CLOSED COMPARTMENT WITH AN INTEGRATED ACCESS ASSEMBLY - Procedure for the manufacture of a composite part ( | 01-31-2013 |
| 20130062467 | AIRCRAFT WING BOX JOINT - An aircraft wing box spanwise joint, comprising a rib having a web, and a pair of rib fittings joined together, each rib fitting forming a closed loop around the periphery of the rib, wherein the rib is integrally formed with one of the rib fittings. Also, an aircraft wing including two or more of the joints. Also, a method of forming an aircraft wing box spanwise joint, the method comprising forming a pair of rib fittings, wherein one of the rib fittings is integrally formed with a rib having a web, each rib fitting forming a closed loop around the periphery of the rib, bringing the rib fittings together, and joining the rib fittings together. | 03-14-2013 |
| 20130075526 | Multi-Layer Metallic Structure and Composite-to-Metal Joint Methods - A composite structure comprises stacked sets of laminated fiber reinforced resin plies and metal sheets. Edges of the resin plies and metal sheets are interleaved to form a composite-to-metal joint connecting the resin plies with the metal sheets. | 03-28-2013 |
| 20130082142 | TAIL CAPABLE OF IMPROVING ANTI-BIRD STRIKE PERFORMANCE OF AIRCRAFT - The present invention relates to a tail for improving anti-bird strike performance of an aircraft. A leading edge reinforcement having a shape of an isosceles triangle is located inside a tail leading edge. The leading edge reinforcement is spanwisely fixed in sections between respective spans formed by the wing rib inside the tail leading edge along the tail of the aircraft. An apex angle of the leading edge reinforcement is the same as an apex angle or arc transition of the tail leading edge skin. The leading edge reinforcement is fixedly connected with the small front beam by a leading edge reinforcement fixed surface. The present invention additionally installs a leading edge reinforcement in the original tail of the aircraft. | 04-04-2013 |
| 20130099058 | AIRCRAFT WING COVER COMPRISING A SANDWICH PANEL AND METHODS TO MANUFACTURE AND DESIGN THE SAID WING COVER - An aircraft wing cover ( | 04-25-2013 |
| 20130105629 | Multi-Spar Port Box Joint | 05-02-2013 |
| 20130146711 | AIRCRAFT RIB ASSEMBLY - A spoiler rib assembly ( | 06-13-2013 |
| 20130233972 | AIRCRAFT WING AND FIBER METAL LAMINATE FORMING PART OF SUCH AN AIRCRAFT WING - Fiber metal laminate ( | 09-12-2013 |
| 20130277499 | AIRCRAFT AIRFOIL, AND AN AIRCRAFT PROVIDED WITH SUCH AN AIRFOIL - An airfoil ( | 10-24-2013 |
| 20130299636 | KEEL BEAM OF AN AIRCRAFT - A keel beam connected to a central wing box of an aircraft and ensuring the connection between a front structure and a rear structure of an aircraft is characterized in that it includes, on the one hand, a U-shaped body with a horizontal base and two solid lateral walls, and on the other hand, a cover which has a U shape oriented in the same manner as the body, with a base in the lower portion and curved edges, the ends of which are oriented upward so that each curved edge includes an outer surface flattened against and fixed to the inner surface of the lateral walls in order to define, with the body, a closed section, the cover including openings for accessing the inside of the keel beam. | 11-14-2013 |
| 20130320141 | SEAL ASSEMBLY FOR AN AIRCRAFT WING - A wing assembly for an aircraft comprising a spar, a wing cover and a rib; wherein the spar has a web portion and a flange portion joined by a radius corner; wherein a gap is formed at an interface between the spar, the wing cover and the rib; wherein the assembly further comprises a seal member which substantially covers the gap, and sealant provided between the seal member and the rib and/or the wing cover and/or the spar so as to seal the gap. Also a method for sealing a gap in an aircraft wing assembly. | 12-05-2013 |
| 20140048651 | RIB FOR AN AIRCRAFT WING - A method of installing fuel system components in an aircraft wing is disclosed. An aircraft wing having a plurality of structural elements such as ribs which are joined together during assembly. The method includes the step of attaching at least some of the fuel system components to at least one of the structural elements prior to joining said structural elements together to assemble a wing. Also disclosed is a structural rib for an aircraft wing, configured to receive one or more fuel system components, and a combined structural rib and fuel system assembly. | 02-20-2014 |
| 20140048652 | HIGHLY INTEGRATED INNER STRUCTURE OF A TORSION BOX OF AN AIRCRAFT LIFTING SURFACE - The invention provides a method for manufacturing a monolithic torsion box inner structure ( | 02-20-2014 |
| 20140054420 | PASSIVE LOAD ALLEVIATION FOR A FIBER REINFORCED WING BOX OF AN AIRCRAFT WITH A STIFFENED SHELL STRUCTURE - Awing box of an aircraft with a stiffened shell structure, consisting of fiber reinforced material includes a skin for absorbing shear loads, and several stringers arranged on the inner side of the wing box for absorbing axial loads, in which at least 60% of the mass of the stiffened shell structure is concentrated in the stringers, wherein the stringers provide at least 80% of the axial stiffness of the stiffened shell structure. In the specific case of wing structure, this embodiment allows the use of unbalanced laminates for the skin to induce higher nose-down twist of the wing box without any loss in bending stiffness and so envisaging higher weight saving capability. | 02-27-2014 |
| 20140061385 | Bonded Composite Aircraft Wing - A unitized composite aircraft wing includes upper and lower composite laminate wing skins that have differing stiffnesses and are bonded to a composite grid structure. The grid structure includes grid spars extending in a span-wise direction, and cross beams extending in a chord-wise direction of the wing. The grid spars include caps bonded to the upper and lower wing skins. | 03-06-2014 |
| 20140117158 | AIRCRAFT WING WITH WING TIP DEVICE - An aircraft wing assembly comprising a wing ( | 05-01-2014 |
| 20140138485 | MODULAR STRUCTURAL ASSEMBLY - A modular structural assembly to form part of an aircraft wing that has an outer skin and a plurality of stringers is disclosed. The assembly includes a plurality of panels, each panel having a portion that forms part of the outer skin and at least one stringer integrally formed with said portion. | 05-22-2014 |
| 20140138486 | OPTIMIZED TORSION BOX FOR AN AIRCRAFT - The invention provides an aircraft lifting surface with a torsion box ( | 05-22-2014 |
| 20140145032 | Multi-Box Wing Spar And Skin - Apparatus and methods provide for the construction of wing sections having multi-box wing spars. According to one aspect of the disclosure provided herein, an aircraft wing may be constructed by applying one or more layers of composite material onto a plurality of wing mandrels. The wing mandrels, when placed together, form the shape of the wing. After the layers of composite material are applied to each individual mandrel, the mandrels are abutted together. Thereafter, the mandrels are compressed using wing surface tooling applied to the plurality of wing mandrels. The composite material is thereafter cured. After curing, the wing surface tooling and mandrels are removed, resulting in a wing having multi-box wing spars and skin. | 05-29-2014 |
| 20140151505 | MAIN SUPPORTING STRUCTURE OF AN AIRCRAFT LIFTING SURFACE - An aircraft lifting surface with a main supporting structure comprising upper and lower faces defining its aerodynamic profile, front and rear faces oriented towards, respectively, the leading and trailing edges, a first set of transverse ribs extended from the front face to the rear face and a second set of transverse ribs crossing the front face and/or the rear face. The integration of leading and trailing edge ribs in the main supporting structure allows a weight and cost reduction of aircraft lifting surfaces. A manufacturing method of said main supporting structure is also disclosed. | 06-05-2014 |
| 20140151506 | HIGHLY INTEGRATED STRUCTURE INCLUDING LEADING AND TRAILING EDGE RIBS FOR AN AIRCRAFT LIFTING SURFACE - The invention provides an aircraft lifting surface with a monolithic main supporting structure ( | 06-05-2014 |
| 20140209744 | Box Structures for Carrying Loads and Methods of Making the Same - There is provided a box structure for carrying load having upper and lower composite integrated sandwich panels. The panels have facesheets sandwiching one or more core portions and adjacent dense packs oriented in an axial direction. The box structure further has a plurality of spars. Each spar has a web and web attachments and has a spar length in the axial direction. The plurality of spars are connected to the panels with the web attachments located at the dense packs. The facesheets are configured to carry primarily torsion and pressure loads in shear and no significant axial loads. The dense packs are configured to carry all significant box bending in axial tension and compression loads. | 07-31-2014 |
| 20140209745 | AIRFRAME PANEL FOR AIRCRAFT AND AIRCRAFT WING - In order to provide an airframe panel for aircraft having stringers and ribs which enables reduction of the workload of the shimming operation, an airframe panel for aircraft of the present invention includes a plurality of stringers | 07-31-2014 |
| 20140284424 | COMPONENT HAVING A BOX STRUCTURE FOR AN AIRPLANE AIRFOIL - The present invention relates to a panel, especially for a component having a box structure in an airplane airfoil, comprising a surface shaped body and grid-like reinforcement bars protruding from the body on one side of the body, and the body and the grid-like reinforcement bars are integral molded. Since the body and the grid-like reinforcement bars of the panel are integral molded, no additional connecting process is required, so that the disconnection phenomenon as happened between the skin and the stiffener or stringer of the prior art would not occur, and the assembly complexity can be decreased. | 09-25-2014 |
| 20140299713 | VENT MEMBER, WING PANEL, AND MAIN WING FOR AIRCRAFT - An opening portion of a vent member is prevented from being blocked, and thus ventilation is reliably performed. A plurality of opening portions ( | 10-09-2014 |
| 20150041590 | AIRFOIL WITH A TRAILING EDGE SUPPLEMENT STRUCTURE - An airfoil includes a main portion formed of a base material and having an inner core comprising a hollow region. Also included is a trailing edge region of the main portion. Further included is a trailing edge supplement structure comprising a low-melt superalloy operatively coupled to the base material proximate the trailing edge region. Yet further included is at least one cooling passage fluidly coupling the inner core of the main portion to an inner region of the trailing edge region. Also included is a trailing edge region exhaust path disposed in the inner region and configured to route a cooling airflow in a span-wise direction of the airfoil. | 02-12-2015 |
| 20150298790 | SYMMETRIC WING RIB WITH CENTER PLANE FASTENED SHEAR TIES - A symmetrical rib structure and methods are presented. A structural web comprises a web center plane and a plurality of web stiffeners, and is symmetrical about the web center plane. A flange is configured on a periphery of the symmetrical rib structure, and a fastener hole is configured in the flange and comprises a fastener hole centerline aligned with the web center plane. A cutout is configured in the structural web around the fastener hole, and two support columns are coupled to the flange on opposite sides of the cutout. | 10-22-2015 |
| 20150336656 | VENT STRINGER FITTING - A fitting for a vent stringer of a type having an open end and an outer edge defining the open end. The fitting may include a fitting body receivable along the open end of the vent stringer, the fitting body having a groove that generally corresponds with the outer edge of the vent stringer, the groove of the fitting body shaped to receive the outer edge of the vent stringer to create a tongue and groove joint with the outer edge; and a connection between the fitting and the stringer to prevent slidable movement of the fitting relative to the stringer. | 11-26-2015 |
| 20150343702 | METHOD FOR MANUFACTURING AN AERONAUTICAL TORSION BOX, TORSION BOX AND TOOL FOR MANUFACTURING AN AERONAUTICAL TORSION BOX - Method for manufacturing a base structure ( | 12-03-2015 |
| 20150375846 | LEADING EDGE FOR AN AIRCRAFT LIFTING SURFACE AND MANUFACTURING METHOD THEREOF - A method for manufacturing a leading edge of an aircraft lifting surface, the leading edge having a leading edge skin and a supporting structure including at least two spars span-wise arranged and fixed internally to the leading edge skin. In the method of the invention, the supporting structure is obtained from a single laminate of plies of composite material, which is conformed in such that in a cross-sectional view, the laminate includes a trapezoidal configuration which forms a front spar and a rear spar of the supporting structure. A leading edge obtained by the above-described method is disclosed. Since the supporting structure of the leading edge is obtained from a single component, namely the laminate, the manufacturing method is simplified and production costs are significantly reduced. | 12-31-2015 |
| 20160009365 | STRUCTURE | 01-14-2016 |
| 20160009366 | STRUCTURE | 01-14-2016 |
| 20160068250 | AIRFOIL PORTION WITH A CHAMBER - An airfoil portion includes an outer skin member and an inner stiffening member. Either the outer skin member or the inner stiffening member or both are arranged to delimit a chamber. The chamber is configured to contain an inner pressure, wherein the inner pressure differs from a pressure external to the chamber. In an embodiment, an aircraft includes such an airfoil portion. A method for providing such an airfoil portion with a chamber is also described. | 03-10-2016 |
| 20160099363 | USING SOLAR CELLS AS BYPASS DIODE HEAT SINKS - A solar panel includes a plurality of solar cells, a bypass diode unit, and a heat spreader. The bypass diode unit includes a bypass diode coupled in an electrical shunting configuration across at least a first solar cell of the plurality of solar cells to bypass current around at least the first solar cell in an event of failure of the first solar cell. The heat spreader is disposed over a portion of one or more of the solar cells. The bypass diode unit is disposed on a first side of the heat spreader with the bypass diode in thermal contact with the heat spreader. A second side of the heat spreader is mounted in thermal contact with the one or more of the solar cells to dissipate heat generated in the bypass diode to the one or more of the solar cells. | 04-07-2016 |
| 20160146022 | HIGH-MODULUS COATING FOR LOCAL STIFFENING OF AIRFOIL TRAILING EDGES - An airfoil is disclosed. The airfoil may comprise a leading edge, a body portion and a trailing edge formed from a high-modulus plating. The body portion of the airfoil may be formed from a material having a lower elastic modulus than the high-modulus plating. The high-modulus plating may improve the stiffness of the trailing edge, allowing for thinner trailing edges with improved fatigue life to be formed. | 05-26-2016 |
| 20160176499 | AIRCRAFT WING TORSION BOX, AIRCRAFT WING, AIRCRAFT AND SUPPORTING MEMBER FOR USE THEREIN | 06-23-2016 |
| 20160176501 | DEVICE FOR PROTECTING THE FRONT SPAR STRUCTURE OF A CENTRAL CASING OF AN AIRCRAFT WING AND AT LEAST ONE PIECE OF EQUIPMENT LOCATED IN SAID WING | 06-23-2016 |
| 20160194070 | VENTILATED AERO-STRUCTURES, AIRCRAFT, AND ASSOCIATED METHODS | 07-07-2016 |
| 20170232662 | METHOD FOR ASSEMBLING A SET OF COMPOSITE PARTS AND ASSEMBLY OBTAINED BY SUCH A METHOD | 08-17-2017 |
| 20180022438 | THERMOPLASTIC MOULDED INJECTED TIP STRUCTURE FOR AN AIRCRAFT | 01-25-2018 |
