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| Number | Title | Issue Date |
| 8146865 | Leading edge for aircraft made of reinforced composite material The present invention relates to a leading edge (1) for aircraft made of composite material, characterized in that it comprises on its inner face a metallic-type reinforcement (2) firmly adhered to the mentioned inner face of the leading edge (1... | 04/03/2012 |
| 8042770 | Structural element, method for producing such a structural element, and aircraft having such a structural element A multilayer structural element, such as a skin panel for an aircraft fuselage, comprises a plurality of metal webs and a plurality of fiber webs arranged as layers in a sandwich structure, where the metal webs of neighbouring layers form stepped connecting regions.... | 10/25/2011 |
| 7963483 | Stiffening element carbon-glass layered foot section The present invention provides a stiffening element for stiffening a step-like substructure, in particular in an aircraft or spacecraft, having a foot section which is composed of a fiber composite material and is shaped in the form of a step such that it essentiall... | 06/21/2011 |
| 7429015 | Acoustic absorption blanket mounting system for an aircraft cabin An acoustic absorption blanket mounting system includes a blanket mounting strip (BMS) attached to a fastener strip mounted to an airframe member. The BMS is generally of a shape to removably capture a sound proofing blanket between opposed pair of wings. At least ... | 09/30/2008 |
| 7358466 | Localized heat treating apparatus for blisk airfoils The present invention is a BLISK airfoil heat treating apparatus and method for heat treating the leading and/or trailing edge section(s) of a BLISK airfoil using the BLISK airfoil heat treating apparatus. The apparatus comprises a pair of hingedly connected heat tr... | 04/15/2008 |
| 7338694 | Method for an integral composite forward flange in a composite The present invention is directed toward a laminate composite structure and a method for fabricating a laminate composite structure, wherein the laminate composite structure comprises a solid laminate and a composite sandwich structure. The solid laminate includes a... | 03/04/2008 |
| 7325771 | Splice joints for composite aircraft fuselages and other structures Structures and methods for joining composite fuselage sections and other panel assemblies together are disclosed herein. In one embodiment, a shell structure configured in accordance with the present invention includes a first panel portion positioned adjacent to a ... | 02/05/2008 |
| 7318619 | Method and apparatus for reducing drag and noise for a vehicle A body part including a surface having a fluid flow thereover. The body part also includes flocking coupled to at least a portion of the surface that adjusts an aerodynamic characteristic relative to the surface that is devoid of the flocking. ... | 01/15/2008 |
| 7291373 | Thermally insulated structure—full depth sandwich joint concept Provided is a composite joint comprising a pair of composite panels each defining a composite panel thickness and having an inner face sheet and an outer face sheet sandwiching a core panel therebetween. The core panel defines a constant thickness portion and a ramp... | 11/06/2007 |
| 7284726 | Self extinguishing composite primary structure A helicopter with one or more components formed from a self extinguishing composite primary structure material to provide increased passenger safety. The self extinguishing composite primary structure material has a core formed from a fire retardant material, which ... | 10/23/2007 |
| 7258303 | Aircraft partition designed to separate a cargo part from a cockpit or from a passenger compartment An aircraft includes a partition designed to separate a cargo part from a cockpit or a passenger compartment. The partition includes a corrugated structure, defining several corrugations with an approximately omega section extending along the direction of the height... | 08/21/2007 |
| 7255916 | Metallic layer material, reinforced with basalt fibers, as well as products made thereof A metallic layer material includes at least two metal sheets. Each sheet has a thickness of less than 1.5 mm. Between the sheets, a plastic layer is disposed, which is bonded to the metal sheets. The plastic layer comprises a plastic material and basalt fibers, and ... | 08/14/2007 |
| 7223318 | Method for forming a laminate with a rebate A method for the production of a laminate consisting of metal layers as well as at least one fibre-reinforced bonding layer (5–7) that is located between the metal layers (1–4), which laminate has at least one region (9) that has a smaller n... | 05/29/2007 |
| 7198691 | Fastenerless internal support for hollow structures A reinforced structural member having a tubular member and a support structure. The tubular member has a sidewall that defines a hollow interior portion. The support structure is formed from a composite material and bonded to the sidewall in at least two predetermin... | 04/03/2007 |
| 7115323 | Titanium foil ply replacement in layup of composite skin Laminate structures and methods for forming same are disclosed. In one embodiment, a laminate structure includes a metal-polymer composite lamina. The metal-polymer composite lamina has a first face and a second face spaced apart, and extends to a terminal edge. The... | 10/03/2006 |
| 7108227 | Insulation package and use thereof An insulation package to reduce the transmission of heat and/or noise between the outer skin and the cabin lining of an aircraft composed of an insulating material enclosed by an encapsulating membrane. The encapsulating material has a vapor diffusion resistance (s | 09/19/2006 |
| 7087317 | Composite laminated aluminum-glass fiber sandwich panels A Glare type composite laminated sandwich panel comprising (i) aluminum (ii) glass fibre with adhesive (iii) aluminum is disclosed. According to the present invention, at least one of the aluminum sheets is preferably made of an aluminum non-heat treatable alloy typ... | 08/08/2006 |
| 7074474 | Composite material-stiffened panel and manufacturing method thereof A composite material-stiffened panel has a skin obtained by molding a fiber-reinforced resin composite material into a flat skin, stiffeners arranged in rows on one surface of the skin, and a fiber-reinforced resin-composite material stitched on the skin covering th... | 07/11/2006 |
| 6992640 | Radome A radome has a structure in which core portions are laminated to opposite side surfaces of a high relative-dielectric-constant layer, respectively, and skin portions are additionally laminated to opposite side surfaces of the laminate, respectively. Furthermore, the... | 01/31/2006 |
| 6986929 | Composite preform structural panel having electrically conductive stitching A structural panel comprised of a composite preform having an electrically conductive stitching. The stitching forms an electrically conductive grid-like network on the structural panel to better dissipate electrical energy received in a lightning strike throughout ... | 01/17/2006 |
| 6949282 | Contoured crushable composite structural members and methods for making the same The present invention provides contoured crushable composite structural members and methods for making the same. The contoured structural members comprise composite materials sandwiching a support or stabilizing structure. The contoured structure can be provided by ... | 09/27/2005 |
| 6935594 | Composite components with integral protective casings Methods and compositions for fabricating composite parts including at least one structural material and at least one protective material that are integrally bonded without the use of secondary bonding operations. One or more of the materials forming the layers of th... | 08/30/2005 |
| 6871821 | Cockpit door of aircraft The cockpit door has a hinge on one side and a latch device on the other side that can be operated only from the cockpit side. To the inner side of the door panel is mounted a reinforcement member 100 having a body formed by laminating layers of aromatic poly... | 03/29/2005 |
| 6837464 | Lox-compatible composite tank for aerospace applications Composite tanks are desirable for aerospace applications since they are much lighter than comparable metal tanks. Various polymeric compositions satisfy the requirements to make a Lox compatible tank. ... | 01/04/2005 |
| 6827312 | Method and system of thermal protection A method and system for assembly and attachment of high temperature materials used as thermal protection systems (TPS) for applications such as re-entry or hypersonic vehicles are disclosed. The attachment system comprises a fastener that passes through an aperture ... | 12/07/2004 |
| 6779757 | Preforms for acute structural edges A preform is joined to converging surfaces of a structure, such as an airfoil, to form a structural edge. The preform has a body having an acute-angle edge at one end and connecting areas extending from the opposing end for connecting the preform to converging plana... | 08/24/2004 |
| 6749155 | Composite assembly with integrated composite joints An aircraft composite assembly 10 is provided, including a first composite member 12, at least one first flange joint 26 comprising a first plurality of plies 24 cured to the first composite member 12, a second composite member ... | 06/15/2004 |
| 6746755 | Ceramic matrix composite structure having integral cooling passages and method of manufacture A multi-layer ceramic matrix composite structure (40) having a plurality of fiber-reinforced cooling passages (42) formed therein. The cooling passages are formed by the removal of a fugitive material (24). The fugitive material is part of a wra... | 06/08/2004 |
| 6719870 | Fastenerless internal support for hollow structures A reinforced structural member having a tubular member and a support structure. The tubular member has a sidewall that defines a hollow interior portion. The support structure is formed from a composite material and bonded to the sidewall in at least two predetermin... | 04/13/2004 |
| 6679969 | Method of manufacturing a sandwich panel, made of composite material, and a panel thereby obtained In order to manufacture a sandwich panel using the RTM technique, a stack comprising a core (10) with open cells, a film (12) of intumescent material covering each of the faces of the core (10), a dry barrier fabric (14) covering each of the films (12) an... | 01/20/2004 |
| 6676077 | High temperature resistant airfoil apparatus for a hypersonic space vehicle A ruddervator for an aerospacecraft including a monolithic, one-piece, oxide/oxide-based ceramic matrix composite (Oxide-CMC) shell having a hollowed interior area. A graphite composite structural member is inserted into the hollowed interior area and bon... | 01/13/2004 |
| 6673402 | Fiber-reinforced ceramics in spacecrafts and aerodynes A movable structural component for a thermomechanically stressed assembly at least partially from fiber reinforced ceramic is disclosed, wherein the movable structural component comprises at least one structural element made by an polymer infiltration and... | 01/06/2004 |
| 6655633 | Tubular members integrated to form a structure Integrally stiffened and formed, load carrying structures comprising a plurality of elongated thin-walled tubes placed co-extensively in a complementary side-by-side fashion which together form a hollow structure having a desired external contour. Integra... | 12/02/2003 |
| 6607851 | Multi-layer ceramic fiber insulation tile A multi-layer tile material produced from layers of alumina enhanced thermal barrier material having different densities. The insulation layers are bound together by a high strength, high temperature alumina or silica binder having a coefficient of therma... | 08/19/2003 |
| 6588709 | Apparatus for variation of a wall skin The present invention provides an apparatus and method for varying a wall skin to alter airflow over the skin. The apparatus has a first and second end-plates, a plurality of flexible rods are arranged substantially parallel to substantially define a plan... | 07/08/2003 |
| 6575407 | Subdermally-reinforced elastomeric transitions A subdermally-reinforced elastomeric transition is provided in which an elastomeric skin is attached to a plurality of subdermal supporting members that engage subdermal reinforcing members. The reinforcing members may be rods or support rails which the s... | 06/10/2003 |
| 6494405 | PEAR composites for oxygen systems The development of polymer composite liquid oxygen (LOX) tanks is a critical step in creating the next generation of launch vehicles. A composite LOX tank will weigh significantly less than conventional metal tanks. This benefit of reduced weight is criti... | 12/17/2002 |
| 6460807 | Missile components made of fiber-reinforced ceramics The missile comprises a nose, fixed fins or movable fins, gas rudders, propelling nozzles and blast pipe inserts, combustion chamber liners, tail cone, grid fins, fluid elements and radome or subcomponents of these made of carbon fiber-reinforced silicon ... | 10/08/2002 |
| 6450450 | Low cost structural fabrication that resists catastrophic failure under rapid thermal loading Provided is a fabrication that is simple to make and cost effective in optimizing performance for moderately extended high velocity missions of high performance airborne vehicles. To counter rapid thermal loading while providing a relatively low cost stru... | 09/17/2002 |
| 6375122 | Reinforced elastomer panel A reinforced elastomer panel (100) has a first rigid member (104) with an edge (116) attached to a first end of an elastomer panel (114). The first rigid member (104) has a removable plate (106) that provides access to a cavity (108). Attached to the firs... | 04/23/2002 |
