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US20120119030 |
REINFORCEMENT BEAM AS WELL AS METHOD AND FIBER LAMINATE FOR MANUFACTURING THE REINFORCEMENT BEAM
Disclosed is a reinforcement blank, in particular a curved ring frame segment for fuselage cells of aircraft, comprising a synthetic material that is reinforced by at least one fiber laminate. The... |
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US20080302912 |
Bladderless Mold Line Conformal Hat Stringer
Apparatus and techniques for providing a closed hat stringer are disclosed. In one embodiment, a closed hat stringer for stiffening a composite structure includes opposing cavity walls situated... |
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US20150259067 |
MODULE FOR AN AIRCRAFT
A module for an aircraft has a fuselage structure and a floor element defining a floor plane. The module includes a frame device adapted for mounting a functional element and the frame device is... |
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US20110108667 |
Thermoplastic Composite Window Panel for Aircraft Applications
An aircraft trim panel structure includes a thermoplastic resinated quadraxial fiberglass lay-up prepreg first open structure skin layer having at least a 28% open area. A thermoplastic resinated... |
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US20080237442 |
MULTI-RING SYSTEM FOR FUSELAGE BARREL FORMATION
An aircraft fuselage barrel (10) includes a skin (12) and a shear tie (18). The shear tie (18) resides within and is integrally formed with the skin (12). The shear tie (18) is separate from and... |
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US20080099611 |
Tail cone for aircraft with movable fairing and support structure for auxiliary power unit and the ancillary elements thereof
Tail cone (2) for aircraft (1) with a cover (8) housing an auxiliary power unit (3) and the ancillary systems thereof (6,7), and the cover (8) has a fixed forward section (11) by means of which... |
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US20110309187 |
NESTED CORE GAS TURBINE ENGINE
An aircraft, with the ability to cruise at supersonic speeds, designed to increase cruise lift/drag ratio, reduce sonic boom and have greater downward visibility by having an ‘inverted’ nose... |
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US20070138695 |
STIFFENING ELEMENT AND A METHOD FOR MANUFACTURING OF A STIFFENING ELEMENT
The present invention relates to a stiffening element (1) and a method for manufacturing of a stiffening element (1) of composite material, which stiffening element (1) is provided for attachment... |
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US20070210211 |
Airplane body and method for manufacturing it
The invention refers to an airplane body, in particular the fuselage, the fuselage being manufactured from a synthetic structure. The fuselage consists of at least two parts which are connected at... |
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US20080248772 |
Integrated Aviation Rf Receiver Front End and Antenna Method and Apparatus
An aviation radio frequency receiver front end (502) and a corresponding antenna (501) are coupled together. The antenna is configured and arranged to be disposed during use in a fixed position... |
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US20080029644 |
Process for manufacturing composite material structures with collapsible tooling
A process for manufacturing stiffened structures (11) in composite materials formed by an outer skin (13) and a plurality of stiffeners or stringers (15) the cross-section of which has a closed... |
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US20050224630 |
SUPERSONIC AIRCRAFT WITH SPIKE FOR CONTROLLING AND REDUCING SONIC BOOM
Method and arrangement for reducing the effects of a sonic boom created by an aerospace vehicle when said vehicle is flown at supersonic speed. The method includes providing the aerospace vehicle... |
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US20120001023 |
AIRCRAFT FUSELAGE MADE OUT WITH COMPOSITE MATERIAL AND MANUFACTURING PROCESSES
Aircraft fuselage made out with composite material and manufacturing processes. The structure of the fuselage (11) comprises a skin (13), a plurality of frames (17) positioned transversely to the... |
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US20090266936 |
AIRCRAFT FUSELAGE STRUCTURAL COMPONENTS AND METHODS OF MAKING SAME
Aircraft fuselage structures have reinforcement members in the vicinity of the stringer openings formed in frame members and are rigidly lap joined to a surface region of the frame members by a... |
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US20130043344 |
HIGH-STRENGTH AIRCRAFT INTERIOR PANEL WITH EMBEDDED INSERT
An aircraft interior panel for supporting high-weight loads including a core panel sandwiched between structural plies, a panel insert embedded in the panel and passing through and interrupting... |
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US20140175223 |
AIRCRAFT FRONT PORTION HAVING AN IMPROVED LANDING GEAR BAY
An aircraft front portion in which the landing gear storage bay is arranged under a cockpit floor. The landing gear bay is mechanically connected to the fuselage frames of the aircraft front... |
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US20120325326 |
Method of Reducing Resistance of Streamlined Body of A Vehicle and Its Applications
A method of reducing resistance of streamlined body of a vehicle and its applications is provided, wherein one or more raised structures are configured between the widest point and the caudal end... |
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US20070023571 |
Quiet airplane configuration
A blended wing aircraft reduces forward, aft, and sideline flyover noise and heat energy by reflecting it upward using the wing and vertical stabilizers positioned just outboard of the engines.... |
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US20120267472 |
AIR VEHICLE
A sensor/emitter arrangement (M1-M3) is integrated into the fuselage (120) structure of a specially designed air vehicle (100), in which the air vehicle is configured for optimizing operation of... |
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US20100133380 |
SKIN PANEL FOR AN AIRCRAFT FUSELAGE
The invention relates to a skin panel (11) of an aircraft (1), comprising a laminate of at least one first metal sheet (40) and preferably first fiber-reinforced polymer layers (41) connected... |
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US20160185437 |
TAIL CONE OF AN AIRCRAFT
A tail cone of an aircraft, more specifically a tail cone made of composite materials comprising an internal skin, an external skin surrounding the internal skin, longitudinal structural members... |
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US20090145129 |
SPLIT-CYCLE AIRCRAFT ENGINE
A split-cycle aircraft engine includes a crankshaft rotatable about a crankshaft axis. A power piston is slidably received within a power cylinder and is operatively connected to the crankshaft... |
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US20100243806 |
AIRCRAFT PRESSURE BULKHEAD ASSEMBLY STRUCTURE
The structure comprises: a rim angle (22) with a front portion and a rear portion, the latter being slanted upward and backward and connected to the bulkhead (1); a simple frame (18), being... |
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US20080179459 |
Pressure bulkhead made of composite material for an aircraft
The present invention relates to a curved rear pressure bulkhead (1) made of a composite material, comprising three layers: an outer layer (2) and an inner layer (3) symmetrical with one another,... |
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US20120119415 |
Improvements in Aircraft Seats and Related Components
In one aspect, an aircraft seat assembly comprises a plurality of seat skeleton parts (22-26, 36,38) held in juxtaposition with one another by means of an over-moulded polymer material (42). In... |
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US20170129588 |
Truss-Reinforced Radome Crown Structure
A truss-reinforced radome crown structure (TRRCS) that functions in combination with an aircraft and a communication radome or antenna. The TRRCS maintains and protects a radome and antenna... |
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US20160107753 |
SEAT FASTENING SYSTEM, SEAT OR SEAT GROUP, AIRCRAFT CABIN, AND METHOD FOR FASTENING A SEAT OR A SEAT GROUP
In order to reduce weight, simplify the mounting of a seat or a seat group, and increase the flexibility in the cabin, a seat fastening system for a seat or a seat group of an aircraft comprises... |
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US20100163669 |
Super aircraft structrue
An aircraft structure is provided. The aircraft structure for an aircraft includes a fuselage, front wings, rear small wings, vertical winglets, and four levels. The fuselage has a cross-section... |
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US20060237588 |
Composite structural member having an undulating web and method for forming the same
Composite structural members and methods for forming the same are disclosed. In one embodiment, a composite structural member includes a central structural portion that extends in a first... |
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US20170043869 |
PROTECTION ELEMENT AND DEVICE FOR CAMERA DRONE
A protection element and a protection device for a camera drone are disclosed herein. The protection element is installed between a landing gear and a propeller of the camera drone and comprises a... |
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US20100038487 |
FUSELAGE STRUCTURAL COMPONENT OF AN AIRCRAFT OR SPACECRAFT, WITH A FOAM LAYER AS THERMAL INSULATION
The present invention creates a fuselage structural component of an aircraft or spacecraft, with a non-load-bearing outer skin and a load-bearing inner framework structure, wherein a foam layer... |
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US20080308676 |
Aircraft Fuselage
The present invention provides an aircraft fuselage which comprises a bulletproof layer in at least partial areas, an aircraft fuselage being understood as both a primary fuselage structure of an... |
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US20080223986 |
Trussed Structure
The invention provides a trussed structure comprising a frame and at least one strut, wherein the frame is of composite material and includes sockets which are integral with the frame. The... |
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US20160176085 |
METHOD AND SYSTEM FOR PRODUCING COMPOSITE STRUCTURES
The subject matter disclosed herein relates to a method of producing a composite structure, such as an airframe or fuselage of an aircraft. The method comprises the steps of: arranging a first... |
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US20130264422 |
Aircraft frame and method for obtaining the same
An aircraft frame and a method for obtaining an aircraft frame, which frame is made of composite material, and which frame comprises several partitions (20) that form, when joined, the... |
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US20150232165 |
AIRCRAFT PANEL FOR AN INTERIOR OF AN AIRCRAFT AND METHOD FOR MAKING THE AIRCRAFT PANEL
Aircraft panel 1 for an interior of an aircraft, wherein the aircraft panel 1 has a sandwich structure 2, wherein the sandwich structure 2 comprises a core section 4 and a covering section 3 as... |
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US20170183081 |
Multi-Rotor Passenger-Carrying Aircraft with Foldable Aircraft Arm
A multi-rotor passenger-carrying aircraft with foldable aircraft arm is disclosed, including an aircraft body, a fixing mechanism, a connector and an aircraft arm. The fixing mechanism is fastened... |
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US20160046392 |
Method For Assembling An Aircraft Fuselage
A method for assembling an aircraft fuselage includes different steps. In a first step the secondary structural components and interior components are assembled to form a core structure. The core... |
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US20100012773 |
Aircrft Structure
An aircraft structure is provided. The aircraft structure for an aircraft includes a fuselage, front wings, rear delta wings, vertical winglets, and three levels. The fuselage has a cross-section... |
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US20140027573 |
AIRCRAFT FUSELAGE STRUCTURAL ELEMENT WITH VARIABLE CROSS-SECTION
An aircraft fuselage structural element has the general form of an elongated profile and includes a web and at least one flange. The at least one flange has a curved cross-section tangent to the... |
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US20160244142 |
FLAT KINKED REAR PRESSURE BULKHEAD
An aircraft fuselage comprising a pressurized cabin and an unpressurized rear section separated by a rear pressure bulkhead. The bulkhead comprises flat portions forming one or more kinks between... |
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US20160129985 |
AIRCRAFT STRUCTURE HAVING CABLES LOCATED IN STRINGERS
An aircraft structure having cables located in stringers is disclosed. According to one embodiment, the aircraft structure includes a stringer having a hollow channel. Further, one or more cables... |
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US20120074261 |
FUSELAGE ARRANGEMENT, AIRCRAFT OR SPACECRAFT AND METHOD
The present invention provides a fuselage arrangement for an aircraft or spacecraft, comprising: a skin portion which consists substantially of fibre composite material and/or of a... |
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US20080283664 |
Aircraft Fuselage Structure
An aircraft fuselage shell section comprises a skin (11) defining a boundary between a first air pressure and a second air pressure, and a reinforcing structure (13) connected to the skin (11).... |
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US20050067531 |
Apparatus for positioning a cable behind a fixed structure
An apparatus for positioning a cable in a recess behind a fixed structure, e.g. a storage bin, in an aircraft. A portion of the cable is enclosed in a conduit. Panels adjacent the structure are... |
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US20110155850 |
CROSS-BEAM AND AN AIRCRAFT WITH CROSS-BEAMS OF THIS TYPE
A cross-beam for a floor structure of an aircraft includes a web having opposing end sections configured to connect to opposing structural sections of an aircraft fuselage and at least one stepped... |
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US20100230538 |
CLOSED STRUCTURE OF COMPOSITE MATERIAL
The invention relates to a tubular-shaped closed structure (11) of composite material comprising a skin (21) and a plurality of omega-shaped reinforcing longitudinal stringers (23), such as a... |
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US20100090061 |
FUSELAGE OF AN AIRCRAFT OR SPACECRAFT OF CRP/METAL HYBRID CONSTRUCTION WITH A METAL FRAMEWORK
The present invention provides an inherently rigid fuselage of an aircraft or spacecraft comprising shell elements or fuselage barrels of CRP construction, wherein the shell elements or fuselage... |
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US20080210817 |
Energy-absorbing Square Tube Composite Stanchion
An energy absorbing structural strut employs a composite tube bonded to an end fitting with the bond being slightly lower in strength than the crushing strength of the tube in axial compression.... |
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US20140054418 |
DOOR FRAME CONSTRUCTION, FUSELAGE PORTION AND AIRCRAFT OR SPACECRAFT
The present invention provides a door frame construction in particular for an aircraft or spacecraft, including a former; a fibre metal laminate which is connected to the former; and an outer skin... |