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WO/2011/107066A2 |
The invention relates to a component, comprising a first section, a second section, and a third section, of which at least one of the sections is made of a titanium material and at least one further section is made of an aluminum materia...
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WO/2011/105345A1 |
Disclosed is a vibration reduction device provided with actuators which apply forces to beams supporting a cabin, in such a way as to bend the beams; acceleration sensors which measure accelerations of the cabin; and a control device whi...
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WO/2011/101050A1 |
The invention relates to a multi-layer flame-retardant film, comprising at least one upper layer made of a thermoplastic polyurethane, which contains halogen-free flameproofing agent and is adhesively bound at least to a layer of textile...
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WO/2011/101513A1 |
The invention relates to a method for producing a stringer from a pair of angular half-stringers, the webs of which are joined with the insertion therebetween of laminar half-bodies that are in contact with one another, said half-bodies ...
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WO/2011/099275A1 |
Provided is a highly lightning-resistant, inexpensive-to-produce closure member for an opening. In the disclosed door body (30), the outer surface (31a) of the plate section (31) is made of a composite material layer (60), and the inner ...
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WO/2011/099274A1 |
Provided is a highly lightning-resistant, inexpensive-to-produce closure member for an opening. With the disclosed closure member, a door body (30), a clamp ring (40) made of a composite material, and an opening (12) in a wing surface pa...
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WO/2011/099396A1 |
Disclosed is a shock absorber structure that absorbs a shock when the shock occurs in an envisioned shock direction. The shock absorber structure comprises a plurality of shock absorbing members, which are cylindrical bodies positioned w...
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WO/2011/095491A1 |
The invention relates to an insulating packet (24, 50, 60) for thermally and acoustically insulating a vehicle cab (2), comprising an aperture (18, 26) for feeding a mounting device (12, 42, 62) therethrough. An insulating piece (28, 38,...
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WO/2011/062682A9 |
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WO/2011/095834A1 |
A system and method for fabricating a composite material assembly. The components of the assembly originate from more than one mold while providing curing or solidifying under heat and vacuum in one step only, preferably with a composite...
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WO/2011/087389A1 |
The invention relates to a device for modifying a counter-acting force and provided in an area of force transfer from one object to another, e.g. on a load-lifting cable or on a thrust transmission line from a thruster to a body, such as...
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WO/2011/087189A1 |
Disclosed are a door control device for a flight vehicle and a flight vehicle having the same, the door control device including, an opening formed at a main body of the flight vehicle and allowing a corresponding wing to be deployed fro...
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WO/2011/081635A1 |
A multi-wing, airfoil fuselage aircraft (1) that is capable of flying in a ground- effect mode includes a main airfoil fuselage wing (2), a fin (8) that extends vertically from this wing, a pivot mount (26) that is affixed to the fin, an...
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WO/2011/080320A2 |
The invention relates to an aircraft or spacecraft casing, comprising a composite shell made of first rod elements or sandwich core elements and first skin elements, which are connected to the first rod elements or sandwich core elements...
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WO/2011/080286A2 |
The invention relates to a fuselage (2) for an aircraft, which fuselage is produced of a fiber-reinforced composite material and comprises a skin (4) and a plurality of peripheral reinforcements (12) and only a small number of longitudin...
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WO/2011/081830A2 |
A fireproof, bi-directional decompression panel includes a frame member and a pressure relief panel member that is releasably retained to the frame member to removably cover a decompression vent opening of an aircraft partition, such as ...
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WO/2011/077030A1 |
The device intended for double glazing comprising at least one outer glazing (1) and one inner glazing (2), which glazings are separated by a gas-filled intermediate space (3), used for insulating an interior environment against an exter...
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WO/2011/073315A1 |
The invention relates to a structural element (2) capable of recovering static compressive forces along an axis Z. Said structural element comprises two profile members (21, 22) made of fibrous composite material that extend along the ax...
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WO/2011/071939A2 |
A wing spar joint is provided for coupling the inboard ends of a right wing spar and a left wing spar. The wing spar joint comprises a forward fitting, an aft fitting, a spar cap a lower chord fitting and a strap member. A first pluralit...
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WO/2011/066950A1 |
The invention relates to an aircraft fuselage component (4) having an exterior wall (5) with reinforcing elements and having an opening (3, 9) in the exterior wall (5). The aircraft fuselage component (4) is designed as an integral fibre...
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WO/2011/068445A1 |
The invention relates to an unmanned aerial vehicle (UAV) helicopter comprising a dismountable tail section including a torque compensating rotor, wherein power transmission from the motor to the torque compensating rotor is accomplished...
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WO/2011/064261A1 |
The invention relates to a structural stiffener made of a layered composite material comprising a head (11) held at a distance from a sole plate by means of which said stiffener is intended to be attached to a panel. The head (11) compri...
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WO/2011/064519A2 |
The invention relates to an aircraft comprising a structural element, such as a fuselage, a wing or a tail unit, including: a wall separating the inside and the outside of the element and including portions jointly defining an inner volu...
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WO/2011/064436A1 |
Joining of elements (1) that are part of aeronautical structures, said elements (1) being made of composite material, with other thermoplastic or reinforced thermoplastic elements (2) also belonging to aeronautical structures, said eleme...
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WO/2011/064520A1 |
The invention relates to a method for creating a sealed joint (118) between elongate parts (14, 116) of an aircraft extending locally in main directions that are not mutually parallel; a plurality of parts of a mould are assembled on the...
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WO/2011/064356A2 |
The invention relates to a cargo hold floor for a cargo hold of an aircraft. The cargo hold floor comprises a plurality of panels for forming the cargo hold floor, wherein the panels have rail segments for forming rails extending over a ...
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WO/2011/064263A2 |
The invention relates to a structural element made of a layered composite material in the form of an elongate profile section and comprising, in a thickness of the layering, three cores consisting of an electrically conductive material c...
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WO/2011/062677A1 |
A blended wing body cargo aircraft is disclosed. A body section defines a cargo volume, where an outer surface of the body section is shaped to provide an aerodynamic lifting surface. A cargo door and ramp structure (306,308) is located ...
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WO/2011/061260A2 |
The invention relates to nose parts of the fairing of vertical and horizontal tails and wings of an aircraft with a skin and a support structure, the skin being disposed on the support structure. The support structure is provided with a ...
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WO/2011/061234A1 |
The invention relates to a supporting structure for an aircraft floor panel, which consists of a three-dimensional truss (1) consisting of a single part made of a composite material comprising a plurality of long-fibre plies arranged sub...
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WO/2011/059571A1 |
An adaptive structural core includes a plurality of core members arranged in a repeating pattern, a plurality of actuator attachment points provided on the plurality of core members and at least one actuator engaging the plurality of act...
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WO/2011/055524A1 |
Provided is a bladder type of jig for manufacture of a composite material structure. The jig is particularly useful for manufacture of a stiffened panel structure employing a hat-type stringer and is sufficiently durable to withstand rep...
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WO/2011/054683A2 |
The present invention relates to an aircraft or spacecraft, comprising a cargo space (8) for receiving cargo and at least one wall element (10) disposed between the cargo space (8) and an area (2, 16) adjacent thereto and comprising at l...
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WO/2011/055097A2 |
The invention relates to a front section (1) of the fuselage of an aircraft comprising secure access between the cockpit (2) and the passenger cabin (3) while being compact. For this purpose, the front section (1) comprises a separation ...
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WO/2011/051697A1 |
A curable flexible electromagnetic hazard resistance laminate, comprising a layer of electrically conductive metal material and thermosetting resin, wherein an external face of the laminate comprises a releasable backing sheet in contact...
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WO/2011/051698A1 |
A curable flexible electromagnetic hazard resistance laminate, comprising a layer of electrically conductive metal material and thermosetting resin, wherein a first external face of the laminate comprises a releasable backing sheet in co...
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WO/2011/046923A2 |
An aircraft elevator system includes a fixed frame, a floating frame coupled to the fixed frame, and a cabin coupled to the floating frame. The floating frame can move with respect to the fixed frame and the cabin can move with respect t...
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WO/2011/046142A1 |
Disclosed is a stringer manufacturing method such that the operational efficiency is increased, that the operators’ work environment is improved, and that the manufacturing cost is reduced. The stringer manufacturing method comprises m...
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WO/2011/042511A2 |
The invention relates to a pressure fuselage of an aircraft, said pressure fuselage being composed of several fuselage sections (1a-1f) in the longitudinal direction, wherein at least one tail-face pressure calotte (2) is provided for fo...
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WO/2011/044476A2 |
Embodiments of the present invention provide a system that provides a cohesive, harmonized look to aircraft galleys and other aircraft areas. The system allows airlines to easily change the decorative front fascia of galley (and other) a...
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WO/2011/043346A1 |
Provided is a wing the weight of which can be reduced, with consideration given to stress concentrations in areas around access holes. A wing (1) on which a tensile load is imposed in the longitudinal direction is provided with a center ...
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WO/2011/039402A2 |
Joining of a structural aircraft element (1 ) that has a section in an omega shape, to another structural aircraft element (10) with a differently shaped section, with the aforementioned joint of these structural elements (1, 10) with a ...
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WO/2011/039399A2 |
Aircraft ring frame and method for the production thereof, said ring frame being produced from composite material, said ring frame comprising a number of partitions (20) that, when connected together, form said ring frame in its entirety...
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WO/2010/140082A9 |
A UAV with an engine (34) attached to rear (38) of its fuselage by an engine mounting assembly with the rotational axis of the engine generally parallel with the axis (45) of the fuselage. The engine mounting assembly includes a fuselage...
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WO/2011/034531A1 |
An easily removable and lightweight horizontal stabilizer configured to provide aerodynamic stability for a rotorcraft. The horizontal stabilizer comprising a spar removably coupled to a tailboom with a removable spar attachment means, t...
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WO/2011/032641A1 |
The invention relates to a braking device for braking freight objects in the freight loading area of aircraft. The braking device comprises a braking roller (10), which is rotatably accommodated in a housing (12). A divided friction ring...
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WO/2011/032996A2 |
The invention relates to a covering device (2) for an interior (4) of an aircraft, comprising at least one material web (6), at least one guide unit (10), and at least one tensioning element. The guide unit (10) is set up for being attac...
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WO/2011/030078A1 |
The invention relates to a radome (1) for an aircraft and, specifically, to a device for connecting said radome to the structure of said aircraft. The radome that is the subject matter of the invention includes a plurality of locking uni...
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WO/2011/022137A1 |
A laminated composite rod (16) includes a rod body having a generally circular or oval cross-section and comprising a plurality of laminated composite plies (1) disposed at various orientations with respect to each other.
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WO/2011/017727A2 |
The invention relates to a method for producing a hollow body (1), in particular an aircraft fuselage (2), designed as a sandwich construction, wherein an inner layer (3) comprises a specifiable number of plies (4) of a specifiable, at l...
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