Patent application number | Description | Published |
20130205576 | Joining method and a punching, stamping rivet - A method for the joining of moulded components with a punching, stamping rivet, wherein a punched hole is radially widened in at least certain sections of the moulded components that are to be punched. A punching, stamping rivet is provided which has a deforming section that has a greater external diameter than a punching section. | 08-15-2013 |
20130206910 | EMERGENCY SUPPLY SYSTEM FOR A TRANSPORTATION MEANS, METHOD FOR SUPPLYING ELECTRICAL POWER AND FOR INHIBITING FIRE AND AIRCRAFT WITH AN EMERGENCY SUPPLY SYSTEM - An emergency supply system for a transportation means is provided. The system includes at least one fuel cell, a hydrogen tank, an oxygen tank, an extinguishing agent container, an oxidant supply unit and an extinguishing-agent supply unit. The oxidant supply unit includes an oxygen inlet connectable to the oxygen tank, an air inlet connectable to an air source, and an oxidant outlet connected to an oxidant inlet of the fuel cell. The oxidant supply unit either conveys oxygen from the oxygen inlet or air from the air inlet to the oxidant outlet. The extinguishing-agent supply unit includes a first extinguishing agent inlet connected to an exhaust air outlet of the fuel cell, a second extinguishing agent inlet connected to the extinguishing agent container, and an extinguishing agent outlet that is connectable to an extinguishing-agent inlet unit of at least one space of the transportation means. | 08-15-2013 |
20130206918 | AUXILIARY FLAP ARRANGEMENT AND AERODYNAMIC BODY COMPRISING SUCH AN AUXILIARY FLAP - The invention relates to an auxiliary flap arrangement for modifying the profile of an aerodynamic body, in particular the trailing edge of the aerodynamic body. The auxiliary flap arrangement here exhibits at least two auxiliary flaps that can be adjusted by an adjustment device while coupled to each other. | 08-15-2013 |
20130210248 | EARTH CONNECTION FOR ELECTRICALLY AND MECHANICALLY CONNECTING EARTH WIRES - An earth connection for electrically and mechanically connecting a plurality of earth wires to a structure, in particular to an aircraft structure, comprising an angled element which element is formed in one piece and is made of electrically conductive material, which comprises a first and a second fastening portion. The first fastening portion is fastened to the structure and the second fastening portion comprises a plurality of electrical connections for connecting the earth wires. The electrical connections comprise socket contact elements which are formed so as to receive pin contact elements of the earth wires. | 08-15-2013 |
20130213048 | DIESEL ENGINE/GAS TURBINE COMPOUND ENGINE FOR A MEANS OF TRANSPORT - A compound engine for a means of transportation, includes a diesel engine and a gas turbine with at least one compressor and with at least one turbine. The diesel engine and the gas turbine are interconnected in such a manner that during continuous duty operation the compound engine is configured to be operated only by way of the diesel engine, and the diesel engine is optionally operated on its own or together with a compressor and a turbine of the gas turbine as a turbocharger for the diesel engine. The compound engine is configured to be operated by way of the diesel engine or the gas turbine. | 08-22-2013 |
20130214067 | DEVICE FOR MANUALLY PAINTING A LARGE SURFACE, IN PARTICULAR AN OUTER SURFACE OF AN AIRCRAFT - A device for manually painting a large surface using a spray gun connected to a paint feed line for the supply of an enamel paint and to a pressure line for the provision of compressed air. After the manual actuation of an operating switch arranged on a handle piece, the spray gun sprays the enamel paint by compressed air via a spray head to apply the enamel paint onto the surface. The spray gun includes means such that it can be moved manually along the surface. The means include an extension rod, at one end of which the spray gun is attached by the handle piece and which is configured such that, when held by an operator on an arm holder configured at the opposite end, it extends from the elbow along the forearm of the operator and beyond the distal end of the forearm. | 08-22-2013 |
20130214092 | AERODYNAMIC BODY WITH AN ANCILLARY FLAP - An aerodynamic body with at least one ancillary flap on the aerodynamic body so it can be moved with a guide mechanism, and with a drive device for actuating the ancillary flap. The guide mechanism has a connecting lever, which at its first end is articulated on the aerodynamic body by a first pivotal articulation, and which at its second end is articulated on the ancillary flap by a second pivotal articulation. The second pivotal articulation is located at some distance from a trailing edge of the ancillary flap, and from a leading edge of the ancillary flap. The guide mechanism has an actuation element, which is coupled with the drive device. The actuation element is articulated on the ancillary flap by a third pivotal articulation. The third pivotal articulation is arranged such that it can be moved in the chordwise direction of the aerodynamic body. | 08-22-2013 |
20130216850 | STRUCTURAL COMPONENT FOR AN AIRCRAFT OR SPACECRAFT - A structural component for an aircraft or spacecraft having an outer skin, comprising at least one former element for reinforcing the outer skin. The former element is arcuately curved in accordance with an inner contour of the outer skin | 08-22-2013 |
20130222347 | DEVICE AND METHOD FOR EXCHANGING INFORMATION BETWEEN AT LEAST ONE OPERATOR AND A MACHINE - A device and a method for exchanging information between at least one operator and a machine which comprises the following components: a display means, which is set up so as to display information from the machine to the at least one operator visually and three-dimensionally; an input means, which is set up so as to detect the position of objects, preferably the position of the fingers of at least one operator, in three-dimensional space in relation to the display means, in a time-resolved manner by optical and/or acoustic and/or electromagnetic measurement methods, and to detect at least one operator input from the detected progression over time in accordance with at least one predetermined criterion and to pass said operator input on to the machine. | 08-29-2013 |
20130224443 | REINFORCEMENT DEVICE FOR THE PURPOSE OF REINFORCING A MAIN LOAD-BEARING COVERING PANEL AND MAIN LOAD-BEARING COVERING PANEL - The invention concerns a reinforcement device for the purpose of reinforcing a main load-bearing covering panel, also a corresponding main load-bearing covering panel, a structural component of a flow body, and also a corresponding flow body. Here the reinforcement device serves the purpose of accommodating and transferring forces and/or stresses in the interior of the covering panel. In accordance with the present invention, in addition to forces and/or stress in the normal direction, forces and/or stresses in a crosswise direction, that is to say, for example, transverse stresses and/or shear stresses, can also be accommodated and transferred. | 08-29-2013 |
20130269256 | PNEUMATICALLY CONTROLLED LOCKING SYSTEM FOR THE COCKPIT DOOR OF AN AIRCRAFT - A locking system is disclosed for locking and unlocking a door such as a cockpit door between the cockpit and cabin of an aircraft. The locking system has a door held by hinges on a door frame and movable between an open position and closed position, and at least one closing means that can lock the door when it is in the closed position. The locking system includes a compressed air source that can be coupled to the closing means to move the closing means from an unlocking position to a locking position by supplying compressed air, and at least one venting valve coupled to each of the closing means in order to conduct compressed air away from each closing means when in the open state, in order to move the at least one closing means from the unlocking position to the locking position. | 10-17-2013 |
20130270390 | AIRCRAFT HAVING AN AIRCRAFT FUSELAGE AND AN AIR SUCKING FUSELAGE COMPONENT - An aircraft having an aircraft fuselage that has an outer skin includes an air sucking fuselage component with an outer surface that is perforated at least in some regions, and a suction profile body. The suction profile body is arranged on the outer skin, forms a local bulge in the outer skin, and further includes a suction opening that is arranged at a location at which there is the lowest pressure, for example at a position furthest away from the outer skin. The suction opening is connected to a suction connection of the air sucking fuselage component. In this way laminarization of the flow at the air sucking fuselage component may take place without the use of active air conveying devices. | 10-17-2013 |
20130273301 | LINING SHELL CARRYING A MAIN LOAD AND STRUCTURAL COMPONENT HAVING AT LEAST ONE LINING SHELL CARRYING A MAIN LOAD - The invention relates to a structural component ( | 10-17-2013 |
20130277495 | DEVICE AND METHOD FOR INCREASING THE AERODYNAMIC LIFT OF AN AIRCRAFT - A lift arrangement for an aircraft includes an aircraft fuselage section with an outside, an aerodynamic lift body attached to the aircraft fuselage section and extending from the aircraft fuselage section outwardly, and a pair of movably held add-on bodies arranged upstream of a leading edge of the aerodynamic lift body. The add-on bodies include an aerodynamically effective surface and are equipped with incoming airflow to generate vortices that impinge on the aerodynamic lift body, thus leading to an increase in lift on the aerodynamic lift body. Thus the lift generation on a lift body is effectively influenced, in particular to compensate for loss of lift as a result of icing. The add-on bodies are moveable, and, can be moved to a neutral position in which they do not project into the flow around the aircraft, and are thus not effective from the point of view of fluid dynamics. | 10-24-2013 |
20130277502 | FLOW BODY HAVING A LEADING EDGE, A SURFACE AND AN ACTIVE FLOW CONTROL SYSTEM AND VEHICLE COMPRISING AT LEAST ONE SUCH FLOW BODY AND AN AIR SOURCE - A flow body having a surface, a leading edge has an active flow control system. The active flow control system includes a plurality of openings, at least one control pressure varying device and at least one fluidic actuator with an interaction chamber having an inlet connectable to an air source, at least two outlets and at least two control pressure ports. The openings are distributed along or parallel to the leading edge in a side-by-side relationship and extend through the surface. The control pressure varying device is connected to the at least two control pressure ports in a fluidic manner, wherein the control pressure varying device is adapted to bring about the flow of the fluid at least majoritarily into a respective one of the outlets. Each of the outlets is connected to one individual opening of the plurality of openings. | 10-24-2013 |
20130284855 | GUIDING MECHANISM FOR OPENING AND CLOSING A CARGO DOOR OF AN AIRCRAFT, AIRCRAFT WITH SUCH A GUIDING MECHANISM AND METHOD FOR OPENING AND CLOSING A CARGO DOOR OF AN AIRCRAFT - A guiding mechanism is disclosed for moving a cargo door into extended cargo door positions to open and into a retracted cargo door position to close at least one section of an opening of a loading hatch on a fuselage of an aircraft. A first structural component in the form of the cargo door is pivotably supported on a second structural component on a front lateral edge by a pivot joint arranged in a pivoting axis in order to assume the extended cargo door positions on the loading hatch. The guiding mechanism features at least one actuator for moving the cargo door, a supporting device arranged on an actuating element, and a spring mechanism on the actuator for exerting a compressive force. | 10-31-2013 |
20130291981 | FLUID ACTUATOR FOR INFLUENCING THE FLOW ALONG A FLOW SURFACE, AS WELL AS BLOW-OUT DEVICE AND FLOW BODY COMPRISING A LIKE FLUID ACTUATOR - The invention relates to a fluid actuator for influencing the flow along a flow surface by ejection of a fluid. By means of a like fluid actuator a continuous flow is distributed to at least two outlet openings in order to generate fluid pulses out of these outlet openings. Control of this distribution takes place inside an interaction chamber supplied with fluid flow via a feed line. Into this interaction chamber there merge at least two control lines via control openings to which respective different pressures may be applied. The flow in the interaction chamber is distributed to the individual outlet openings as a function of the pressure difference at the control openings. | 11-07-2013 |
20130304312 | DIAGNOSTIC SYSTEM AND DIAGNOSING METHOD, HOUSING COMPONENT OF A LUBRICANT CONTAINER - Diagnostic system including a sensor device with a sensor for generating signals corresponding to a first operational condition, a control device with a timer and function for performance of measurements, and a signal transmission device. The system includes a device for determination of a second operational condition of the system component and configured where the sensor value of the signal transmission device corresponding to the first operational condition is furnished when the sensor value corresponding to a second operational condition of the transmission mechanism is higher or lower than a comparative value, and housing component of a lubricant container and in particular closure device for sealing an opening of such a housing component from a lubricant which is present in the operational use thereof in an internal space thereof, having arranged therein: at least one sensor device comprising at least one sensor for determining the water content in the lubricant. | 11-14-2013 |
20130306794 | AIRCRAFT STRUCTURAL ASSEMBLY - An aircraft structural assembly includes an area element which has a core and an outer layer. A first surface of the area element is convexly curved, at least in certain sections, relative to an imaginary central area of the area element extending through the core of the area element. By contrast, a second surface of the area element located opposite the first surface is oriented, at least in certain sections, parallel to the imaginary central area of the area element extending through the core of the area element. The area element is configured in the form of a floor panel of a floor system. The first or the second surface of the area element is designed to form a walkable floor surface of the floor system in the state of the aircraft structural assembly when mounted in an aircraft. | 11-21-2013 |
20130306797 | HYDROGEN TANK FOR H2-INJECTION - To save weight and to enhance safety, a hydrogen tank for supplying an engine with hydrogen is attached externally to an aircraft. | 11-21-2013 |
20130307324 | Energy supply network; method and aircraft or spacecraft - An energy supply network, especially for an aircraft or spacecraft, including a first coupling device, the first coupling device being configured to couple the energy supply network to an external energy source, a first high voltage direct current, HVDC, segment, the first HVDC segment being coupled to the first coupling device and a second HVDC segment, the second HVDC segment being coupled to the first coupling device. Also provided is a corresponding method and an aircraft or spacecraft incorporating such an energy supply network. | 11-21-2013 |
20130311112 | METHOD AND APPARATUS FOR DETERMINING THE THRUST ON A VEHICLE - A method for determining the thrust of at least one engine, which is held on a supporting structure of a vehicle, includes the steps of acquiring the elongation of at least one structural element onto which the thrust of the at least one engine acts, by means of at least one strain gage; calculating the force causing the elongation in the at least one structural element, taking into account the materials characteristics of the structural element; and determining the thrust of the at least one engine as an effective force component in the direction of thrust of the vehicle. It is thus not necessary to carry out an estimate of the thrust on the basis of other physical variables such as shaft speeds, pressure or exhaust gas temperature of engines. | 11-21-2013 |
20130320150 | WING FOR AN AIRCRAFT, AIRCRAFT AND METHOD FOR REDUCING AERODYNAMIC DRAG AND IMPROVING MAXIMUM LIFT - A wing for an aircraft includes a leading edge and a wing tip extension extending from an end of a main wing region to a wing tip. The wing tip extension includes an arrangement of openings at least from the end of a main wing region to the wing tip along the leading edge, which openings are connected to an air conveying device for conveying air through the openings. Thereby in flight states with a low flight velocity the flow around a wing tip extension can be harmonized such that the drag is decreased and the lift of the wing is increased. | 12-05-2013 |
20130334289 | MOVABLE JOINING DEVICE FOR CONNECTING STRUCTURAL COMPONENTS OF AN AIRCRAFT - A movable joining device for connecting structural components of an aircraft, with joining means moveably arranged on a guiding device situated on the outside of the structural components so as to fixedly connect joining edges of the structural components positioned adjacent to each other, wherein the joining means includes a welding unit that can move on the rail-like guiding device, and is equipped with a special so-called bobbin tool as a tool for friction stir welding. | 12-19-2013 |
20130343805 | STRUCTURAL ELEMENT FOR AN AIRCRAFT AND/OR SPACECRAFT AND METHOD FOR PRODUCING SUCH A STRUCTURAL ELEMENT - The present invention provides a structural element for an aircraft and spacecraft, having a core which includes core regions which are uncoupled from one another by means of an expansion joint arranged between the core regions. The present invention further provides a method for producing a structural element for an aircraft or spacecraft, including the following method steps: providing a core of the structural element, which core includes core regions; and arranging an expansion joint between the core regions. The present invention relates still further to an aircraft and/or spacecraft having such a structural element. | 12-26-2013 |
20140021304 | PROFILE PLATE PORTION FOR USE AS AN OUTER WALL OF A FLOW BODY, METHOD FOR MANUFACTURING A PROFILE PLATE PORTION AND FLOW BODY COMPONENT COMPRISING A SUCTION-EXTRACTION DEVICE FOR FLUID - A profile plate portion is disclosed for use as an outer wall of a flow body including a first profile plate panel that is fluid permeable, a second profile plate panel extending along the first profile plate panel, and a reinforcing device for supporting the first profile plate panel and the second profile plate panel on one another. Fluid can flow through the reinforcing device, and/or fluid of the flow present at the first profile plate panel, which flows through the first profile plate panel, can flow through the reinforcing device in the local profile plate thickness direction from the first profile plate panel to the second profile plate panel and in some regions can flow through to an inside that is situated opposite the flow side. A method is disclosed for manufacturing a profile plate portion and a flow body component with a suction-extraction device for fluid. | 01-23-2014 |
20140027088 | HEAT EXCHANGER, HEATER AND GALLEY - A heat exchanger for cooling air, with a coolant onward-flow connection for feeding liquid coolant for cooling air and a coolant return-flow connection for discharging liquid coolant. For removing ice by melting accumulated ice in the heat exchanger, a heater is provided that is associated with an electrical heating element. An operational safety device prevents overheating of the heater. The operational safety device comprises a fault-current detection device. Such a heater, with a heating element for heating air for subjecting accumulated ice to heated air, and with such an operational safety device is provided. Also, a galley for a commercial aircraft is provided with a receiving space for trolleys, and a cooling device for cooling the receiving space. The cooling device comprises such a heat exchanger for cooling air. | 01-30-2014 |
20140050884 | STRUCTURAL COMPONENT COMPRISING AT LEAST ONE MAIN-LOAD-BEARING COVERING SHELL AND A CARRIER STRUCTURE FOR FIXING THE MAIN-LOAD-BEARING COVERING SHELL, AND FLOW BODY COMPRISING SUCH A STRUCTURAL COMPONENT - Structural component including at least one covering shell and a carrier structure, the covering shell designed in the form of a sandwich and formed by an inner skin section, an outer skin section and a shear-load absorbing core layer disposed between the two sections and connecting the inner and the outer skin sections to one another in a planar manner. The carrier structure is formed by at least one panel-shaped connecting part extending between and transversely to the inner and outer skin sections and connected along a reference longitudinal direction to the covering shell. The connecting part is located outside the carrier structure and fastened to the inner skin section resting thereon in a planar manner, wherein at least one profiled support extending along the reference longitudinal direction is provided in the covering shell in order to form a reinforcing section in the connecting region of the panel-shaped connecting part. | 02-20-2014 |
20140061387 | SURFACE ELEMENT FOR AN AIRCRAFT, AIRCRAFT AND METHOD FOR IMPROVING HIGH-LIFT GENERATION ON A SURFACE ELEMENT - A surface element, e.g. a wing, of an aircraft includes a leading edge, a high lift device arrangement positioned along the leading edge and at least one add-on body positioned in a leading edge region, wherein the high lift device arrangement is interrupted in the region of at least one add-on body for preventing collision with the add-on body and wherein the surface element includes an arrangement of openings in a region covering the add-on body, which openings are connected to an air conveying device for conveying air through the openings. Thereby an additional flap for harmonizing the flow above a pylon or other add-on body can be eliminated. | 03-06-2014 |
20140084111 | SYSTEM AND METHOD FOR DEPLOYING LOADS OUT OF AN AIRCRAFT - A system for deploying loads out of an aircraft comprises an aerial delivery parachute with an aerial-delivery parachute line and an activation means for placing the aerial delivery parachute in an enveloping flow past the aircraft. Within the aircraft a receiving device can be positioned that receives a tractive force acting on the aerial-delivery parachute line, which tractive force has been determined by a force measuring device and has been transmitted by way of a transmitting device. With the knowledge of the tractive force it is possible both to implement emergency release and to assess whether an aerial delivery parachute has correctly deployed in the flow enveloping the aircraft. | 03-27-2014 |
20140090802 | AIRCRAFT THERMAL CONTROL SYSTEM AND METHOD OF OPERATING AN AIRCRAFT THERMAL CONTROL SYSTEM - An aircraft thermal control system includes a thermal control unit including an internal circuit, an evaporator and a condenser, the evaporator and the condenser being disposed in the internal circuit. The aircraft thermal control system further includes a cooling circuit which is thermally coupled to the evaporator of the thermal control unit, and a heating circuit which is thermally coupled to the condenser of the thermal control unit. | 04-03-2014 |
20140138480 | HIGH LIFT SYSTEM FOR AN AIRCRAFT WITH TWO SEPARATE DRIVE UNITS - A high-lift system on a wing of an aircraft is provided. The wing includes a right-hand and a left-hand wing half with movably held high-lift flaps and the right-hand and left-hand wing half are attached to an aircraft fuselage, thus forming a wing root. Each wing half in a region in close proximity to the wing root, includes a drive unit. In each case this drive unit is joined to a transmission shaft mechanically connected to the respective drive unit, which transmission shaft extends from the drive unit in the direction of the end of the respective wing half and is designed to mechanically move the high-lift flaps arranged in the respective wing half. By means of such an arrangement it is possible to do without deflection gear arrangements from a central drive unit to the individual wing halves. | 05-22-2014 |