| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 244053000 | Air intakes | 73 |
| 20080237404 | Hydrogen powered aircraft - Disclosed is an aircraft, configured to have a wide range of flight speeds, consuming low levels of power for an extended period of time, while supporting a communications platform with an unobstructed downward-looking view. The aircraft includes an extendable slat at the leading edge of the wing, and a reflexed trailing edge. The aircraft comprises a flying wing extending laterally between two ends and a center point. The wing is swept and has a relatively constant chord. The aircraft also includes a power module configured to provide power via a fuel cell. The fuel cell stores liquid hydrogen as fuel, but uses gaseous hydrogen in the fuel cell. A fuel tank heater is used to control the boil-rate of the fuel in the fuel tank. The fuel cell compresses ambient air for an oxidizer, and operates with the fuel and oxidizer at pressures below one atmosphere. The aircraft of the invention includes a support structure including a plurality of supports, where the supports form a tetrahedron that affixes to the wing. | 10-02-2008 |
| 20080245930 | HIGH INTENSITY LASER POWER BEAMING RECEIVER FOR SPACE AND TERRESTRIAL APPLICATIONS - Systems and methods are described that facilitate refueling a vehicle with electrical energy by targeting receiver thereon and pointing a high-intensity laser source at the receiver. Vertical multi-junction (VMJ) photocells receive the laser energy and convert the laser energy into electrical energy. The laser source can operate at a range of output power levels depending on the vehicle's energy needs. The laser source can be pulsed or continuous near-infrared laser source. A heat exchanger can be coupled to the receiver to dissipate laser energy not converted into electrical energy. If the vehicle has a propeller, the heat exchanger can be mounted to the vehicle in the propeller wash path. | 10-09-2008 |
| 20080258016 | NACELLE ASSEMBLY WITHOUT LOWER BI-FI SPLITTER - A nacelle assembly provides thrust reverser doors and core cowl doors with separate thrust reverser door hinge lines and core cowl doors hinge lines for independent operation to eliminate the requirement of a lower bi-fi splitter. The removal of the lower Bi-Fi splitter provides improved aerodynamic packaging with improved performance by reducing drag in the bypass fan stream. | 10-23-2008 |
| 20080308685 | SOLAR POWERED WING VEHICLE USING FLYWHEELS FOR ENERGY STORAGE - A solar powered air vehicle that can stay aloft for indefinite periods of time. The vehicle employs photovoltaic solar cells for primary power and high speed counter-rotating flywheels for energy storage and steering of the vehicle. The flywheels are placed in the wing to reduce airfoil drag. A control law provides three-axis stabilized control of the vehicle by controlling propeller pitch to vary the speeds of the flywheels. | 12-18-2008 |
| 20090032648 | LONG ENDURANCE AIRCRAFT - A long endurance powered aircraft includes a fuselage, a propeller coupled to the fuselage, a wing coupled to the fuselage, and an energy storage system disposed within the fuselage. The wing includes an adjustable surface area including solar cells configured to collect incident solar energy and convert the collected incident solar energy to electrical energy for powering the aircraft during daylight flight. The energy storage system is configured to convert excess electrical energy converted from collected incident solar energy to chemical energy, store the chemical energy, and convert the stored chemical energy to electrical energy for powering the aircraft during night flight. | 02-05-2009 |
| 20090045292 | ENGINE HAVING POWER BUS FAULT SHORT CIRCUIT CONTROL WITH A DISCONNECTION SWITCH - An aircraft electrical system comprises a generator to be driven as part of a gas turbine engine. The generator supplies electrical power to a plurality of accessories associated with the gas turbine engine, and to an aircraft power bus in parallel to the supply to the accessories. A control detects a short circuit on the aircraft power bus. When a short circuit is detected on the aircraft power bus, a switch is driven open to disconnect the aircraft power bus from the generator. In this manner, the power will continue to be delivered to the plurality of accessories. In a separate feature, a control voltage is provided by an auxiliary permanent magnet generator to a voltage regulator for the main generator. | 02-19-2009 |
| 20090045293 | GENERATOR FOR GAS TURBINE ENGINE HAVING DC BUS FAULT SHORT CIRCUIT CONTROL USING A BATTERY - An aircraft electrical system comprises a generator to be driven as part of a gas turbine engine. The generator supplies electrical power to a plurality of accessories associated with the gas turbine engine, and to an aircraft DC bus in parallel to the supply to the accessories. A battery supplies voltage to a control circuit for the generator through a selectively opened and closed switch. A control detects a short circuit on the aircraft DC bus. The battery switch allows power from the battery to flow to provide control voltage for the generator when the control detects a short circuit on the aircraft DC bus. | 02-19-2009 |
| 20090065652 | Aircraft combination engines exhaust thrust recovery - A gas turbine engine with a turbine with an exhaust manifold thereabout from which fluids can be transferred to the turbine and an air compressor having an air transfer duct extending therefrom so as to be capable to provide compressed air in that air transfer duct at one end thereof to the air intake of an internal combustion engine provided as an intermittent combustion engine. The air intake and an exhaust outlet are each coupled to combustion chambers therein and a rotatable output shaft is also coupled to those combustion chambers for generating force. The exhaust outlet has an exhaust transfer duct extending therefrom so as to have the intermittent combustion engine be capable to provide exhaust therefrom in that exhaust transfer duct at one end thereof, and the exhaust transfer duct being connected at an opposite end thereof to the exhaust manifold to be capable of transferring intermittent combustion engine exhaust thereto. | 03-12-2009 |
| 20090072095 | SMOKE GENERATION DEVICE FOR AIRCRAFT AND AIRCRAFT FITTED WITH SUCH A DEVICE - The invention relates to a smoke generation device for an aircraft ( | 03-19-2009 |
| 20090101760 | Aircraft engine protection unit (A.E.P.U) - My present invention relates to a Protective Screen specifically designed to be mounted, anchored or fitted at the front intake of a jet engine nacelle aircraft to prevent the ingestion of birds and other foreign airborne objects of substantial amount(s), size(s), and quantities from entering the engine. The external front view of the Aircraft Engine Protection Unit (AEPU) screen, is a Radial Dome-Shaped Screen with interlocking mesh wires, rods and bars braced or welded together. This screen is anchored to the front external nacelle of the aircraft engine, attached with the aid of I-Bar (Arm) structures fastened on the outside panels securing the AEPU Screen in the front position. A De-icing mechanism is installed to enable defrosting by means of electrical and/or avionics systems incorporated in the AEPU system. Since my invention is at its conceptual stage, the exact dimension(s) of materials and parts produced shall be determined during manufacturing. | 04-23-2009 |
| 20090272854 | ELECTRIC PROPULSION SYSTEM USEFUL IN JET-TYPE MODEL AIRPLANES AND UAVS - A power plant for a jet-type model airplanes and UAVs includes an electric motor and a cover. The cover receives a portion of the electric motor and a sleeve into which the electric motor is inserted. The sleeve has a plurality of fins to dissipate heat and create openings into the cover. Air from the fan rotor passes through the openings to cool an electronic speed control member and exits a rear opening in the cover. The cover may also have additional openings for air to enter into the cover. | 11-05-2009 |
| 20100019102 | GAS TURBINE ENGINE NACELLE - An initial geometry for a nacelle provides an intake at the upstream end of the nacelle and an exhaust at the downstream end of the nacelle. The intake has, in flow series/an intake lip and a diffuser. The intake lip has a highlight defining the boundary between the inner and outer surfaces of the intake lip. On all longitudinal sections containing the axis of the engine (i) the inner and outer surfaces are tangency matched at the highlight, and (ii) the inner and outer surfaces have their maximum curvatures at the highlight. | 01-28-2010 |
| 20100065691 | MODULAR EXTERNALLY ACCESSIBLE BATTERIES FOR AN AIRCRAFT - An aircraft comprises an airframe, an electric propulsion system, a number of battery pods, and an engagement system. The number of battery pods has a physical connector system. The engagement system is attached to the airframe and is capable of engaging the physical connector system to connect the number of battery pods to the airframe. | 03-18-2010 |
| 20100072324 | NACELLE FOR DOUBLE FLOW ENGINE - A nacelle for double-flow engine with a cowling and at least one thrust reverser, the thrust reverser having an internal door and an external door arranged in the cowling, and means for simultaneously shifting these doors between a stable retracted position in which the doors are integrated in the cowling and a stable deployed position in which the internal and external doors are positioned at least partially inside and outside of the nacelle, respectively, to deflect the secondary flow and to generate a thrust reversal. The means for simultaneously shifting the doors comprise an actuator, one extremity of which is linked to one of the doors to shift this door between the extreme positions, and at least one linkage element linked to the doors to pivot by its extremities, so that the shifting of the door entails the shifting of the other door between these extreme positions. | 03-25-2010 |
| 20100288890 | WING-ENGINE COMBINATION, AN AIRCRAFT, AND A WING SECTION OF AN AIRCRAFT COMPRISING AN ENGINE BLEED-AIR DUCT ARRANGEMENT - A wing-engine combination includes: a wing with a main wing and an engine with a premixing chamber, a combustion chamber and a hot-air space, which includes: an engine bleed-air duct, which extends along the wingspan direction and along the leading edge of the main wing, including an engine bleed-air inlet device that is coupled to an engine hot-air space, and including an engine bleed-air outlet device having a discharge orifice on the main wing or a connecting part for coupling the engine bleed-air duct to a consumer of the engine bleed-air, an ambient-air duct, which extends along the engine bleed-air duct, including an ambient-air inlet device which is arranged on an aircraft component of the aircraft, which aircraft component faces the intended flow-around direction of the aircraft and includes an aperture for letting ambient air into the ambient-air duct, and including an ambient-air outlet device with a passage between the ambient-air duct and a premixing chamber of the engine so that the arrangement including the engine bleed-air duct and the ambient-air duct forms a heat exchanger device for cooling the air flowing in the engine bleed-air duct and so that the ambient air conveyed in the ambient-air duct is supplied for combustion in the engine; and an aircraft and a wing section of an aircraft including an engine bleed-air duct arrangement. | 11-18-2010 |
| 20110073717 | AIRCRAFT WITH A HYBRID ENERGY SUPPLY - An aircraft with a hybrid power supply, the aircraft comprising:
| 03-31-2011 |
| 20110155862 | JET ENGINE NOZZLE EXIT CONFIGURATIONS AND ASSOCIATED SYSTEMS AND METHODS - Nozzle exit configurations and associated systems and methods are disclosed. An aircraft system in accordance with one embodiment includes a jet engine exhaust nozzle having an internal flow surface and an exit aperture, with the exit aperture having a perimeter that includes multiple projections extending in an aft direction. Aft portions of individual neighboring projections are spaced apart from each other by a gap, and a geometric feature of the multiple can change in a monotonic manner along at least a portion of the perimeter. | 06-30-2011 |
| 20110192938 | WIND POWER GENERATION SYSTEM FOR LIGHTER THAN AIR (LTA) PLATFORMS - An apparatus includes a lighter than air platform, a reversible propulsive/wind turbine, a deployable anchor to constrain movement of the lighter than air platform with respect to an anchor point allowing wind to drive the turbine, and a generator/motor coupled to the turbine to produce electrical power when movement of the lighter than air platform is constrained. A method performed by the apparatus is also provided. | 08-11-2011 |
| 20120025032 | ELECTRICAL ARCHITECTURE FOR A ROTARY WING AIRCRAFT WITH A HYBRID POWER PLANT - A hybrid power plant ( | 02-02-2012 |
| 20120261522 | MODULAR EXTERNALLY ACCESSIBLE BATTERIES FOR AN AIRCRAFT - An aircraft comprises an airframe, an electric propulsion system, a number of battery pods, and an engagement system. The number of battery pods has a physical connector system. The engagement system is attached to the airframe and is capable of engaging the physical connector system to connect the number of battery pods to the airframe. | 10-18-2012 |
| 20130026301 | NACELLE FOR VARIABLE SECTION NOZZLE PROPULSION UNIT - The invention relates to a nacelle for a variable area nozzle propulsion unit comprising a nacelle, hosting a turbofan jet engine, of dual-flow type. The propulsion unit includes: a fixed part, carried by the inboard half-nacelle defined by a vertical plane of symmetry of the nacelle; and a movable part carried by the outboard half-nacelle. The moving part containing or releasing part of the secondary flow, depending on its open or closed position. The moving part being able to move to a discrete number of positions including a closed position, an open position, and one or more intermediate positions so as to provide variable area nozzle configurations for the turbofan engine. | 01-31-2013 |
| 20130140405 | Integral Powered Wing Aircraft Utilizing Full Rotary Disc Stacking With Aeronautical Enhancements - In prior embodiments of the IPWA was configured as concentric contra-rotating discs. In this patent the IPWA is configured as a stack of contra-rotating discs. The top disc may be a single disc, or several concentric discs rotating within one another in the same direction of rotation. There may be one or more discs below the top disc. Each lower disc rotates in the same direction and opposite the rotation of the top disc or discs. | 06-06-2013 |
| 20140061391 | TWO-STROKE, FUEL INJECTED INTERNAL COMBUSTION ENGINES FOR UNMANNED AIRCRAFT AND ASSOCIATED SYSTEMS AND METHODS - Two-stroke, fuel injected internal combustion engines for unmanned aircraft and associated systems and methods are disclosed herein. Engines configured in accordance with embodiments of the disclosure can include, for example, (a) an electronic fuel injection system configured to provide a desired low fuel rate by injecting fuel every nth compression cycle rather than every cycle (so-called “skip-cycle” operation), (b) one or more pressure sensors configured to measure fluctuations in peak crankcase pressure and use such fluctuations to control fuel injection delivery, and (c) a multi-cylinder configuration having a common crankcase with a fuel injection arrangement configured to mitigate or eliminate problems with mixed redistribution. | 03-06-2014 |
| 20140263852 | SPOOLER FOR UNMANNED AERIAL VEHICLE SYSTEM - In an aspect, in general, a spooling apparatus includes a filament feeding mechanism for deploying and retracting filament from the spooling apparatus to an aerial vehicle, an exit geometry sensor for sensing an exit geometry of the filament from the spooling apparatus, and a controller for controlling the feeding mechanism to feed and retract the filament based on the exit geometry. | 09-18-2014 |
| 20140263853 | Methods Utilizing Cold Spray Techniques for Repairing and Protecting Rotary Components of Aviation Propulsion Systems - A method of repairing a component comprises identifying a non-compliant surface of the component, wherein the non-compliant surface is not within an allowable tolerance, cold spraying a powder comprising a metal onto the non-compliant surface, and forming a coating comprising the metal over the non-compliant surface, wherein an outer surface of the coating is within an allowable tolerance. In an embodiment, the method of repairing an outer component further comprises machining the outer surface of the coating. In an embodiment, the component is a shaft, a rotor mast, an input quill, or a bearing. In an embodiment, the component contains electronic equipment during the cold spraying, and wherein the cold spraying does not damage the electronic equipment. In an embodiment, the component is repaired without subjecting the component to a hydrogen embrittlement bake. | 09-18-2014 |
| 20140339371 | Long Range Electric Aircraft and Method of Operating Same - Electric aircraft, including in-flight rechargeable electric aircraft, and methods of operating electric aircraft, including methods for recharging electric aircraft in-flight, through the use of unmanned aerial vehicle (UAV) packs flying independent of and in proximity to the electric aircraft. | 11-20-2014 |
| 20140367525 | AIRCRAFT USING TURBO-ELECTRIC HYBRID PROPULSION SYSTEM - An air vehicle incorporating a hybrid propulsion system. The system includes a gas turbine engine as a first motive power source, and one or more battery packs as a second motive power source. Through selective coupling to a DC electric motor that can in turn be connected to a bladed rotor or other lift-producing device, the motive sources provide differing ways in which an aircraft can operate. In one example, the gas turbine engine can provide operation for a majority of the flight envelope of the aircraft, while the battery packs can provide operation during such times when gas turbine-based motive power is unavailable or particularly disadvantageous. In another example, both sources of motive power may be decoupled from the bladed rotor such that the vehicle can operate as an autogyro. | 12-18-2014 |
| 20150021442 | SOLAR RELAY AIRCRAFT POWERED BY GROUND BASED SOLAR CONCENTRATOR MIRRORS IN DUAL USE WITH POWER TOWERS - A solar relay aircraft system includes a solar relay aircraft having an upper surface, and a lower surface, and equipped with a solar radiation receiver on said lower surface and capable of converting solar energy to electrical energy. An electric motor in electrical connection with said solar radiation receiver to receive the electrical energy and drives a propeller to propel the solar relay aircraft. A number of ground-based reflector arrays include a plurality of reflecting mirrors for receiving solar radiation from the sun and direct the solar radiation from the sun towards the solar relay aircraft. | 01-22-2015 |
| 20150041598 | AERIAL PLATFORM SYSTEM, AND RELATED METHODS - An aerial platform receives power in the form of light, for example laser light, transmitted via an optical fiber from a remote optical power source. The platform comprises a receiver which converts at least a portion of the light to a different form of power, for example electric power. The platform also comprises a propulsion element which consumes the different form of power to generate propulsive thrust. Supplying power to the aerial platform from a remote source enables the platform to remain aloft longer than a battery or fuel tank carried by the platform would allow. Transmitting the power in the form of light is preferable in many cases to transmitting electric power, because electrical conductors are generally heavier than optical fibers, and are hazardous in the presence of lightning or a high-voltage power line. | 02-12-2015 |
| 20150115108 | Aircraft Electric Motor System - A method and apparatus for controlling an electric aircraft is presented. An apparatus comprises a controller. The controller is configured to identify a state for an electric aircraft. The controller is further configured to identify a group of recharging parameters for a group of electric motors in an electric propulsion system. The electric propulsion system is configured to move the electric aircraft based on the state for the group of electric motors for the electric aircraft. The controller is still further configured to recharge a power source for the electric aircraft using the group of recharging parameters to control recharging of the power source with the group of electric motors when a recharge state is present for the electric aircraft. | 04-30-2015 |
| 20160009377 | POSITIONABLE EJECTOR MEMBER FOR EJECTOR ENHANCED BOUNDARY LAYER ALLEVIATION | 01-14-2016 |
| 20160009402 | SOLAR RELAY AIRCRAFT POWERED BY GROUND BASED SOLAR CONCENTRATOR MIRRORS IN DUAL USE WITH POWER TOWERS | 01-14-2016 |
| 20160032761 | AIRCRAFT ENGINE CLEANING SYSTEM - A cleaning system for performing a cleaning cycle on a turbine engine mounted to an airframe includes a mobile supply unit. The mobile supply unit includes a cleaning agent supply that introduces cleaning agent into the turbine engine. The aircraft includes at least one valve configured to block cleaning agent from moving from the turbine engine into a passenger cabin of the aircraft. | 02-04-2016 |
| 20160036071 | COOLING CONCEPT FOR A FUEL CELL SYSTEM FOR A VEHICLE AND AIRCRAFT HAVING SUCH A FUEL CELL SYSTEM - A fuel cell system for a vehicle comprises at least one fuel cell, at least one fuel cell heat exchanger arranged in or at the at least one fuel cell for receiving heat of the at least one fuel cell, at least one thermal dissipation unit, at least one additional heat exchanger and a cooling loop having a plurality of fluid line segments for conveying a coolant. The at least one fuel cell heat exchanger is coupled with the at least one thermal dissipation unit through the cooling loop, and the additional heat exchanger is arranged in the cooling loop and is adapted for receiving heat from an external source and for raising the temperature of a coolant flowing in the cooling loop. | 02-04-2016 |
| 20160068266 | ROTARY PROPELLER DRONE WITH INTEGRATED POWER STORAGE - An electrically powered unmanned aircraft system (UAS or drone) including a propeller including a core formed by battery material layers as a power source and integrated as a structural component of the drone. The battery material layers can be a graphene super capacitor or a nanopore battery structure. Power available from the integrated battery material layers can be used to power an electric motor included with the drone and operating to rotate the propeller. | 03-10-2016 |
| 20160090185 | ALIGNMENT AND SAFETY DEVICE FOR THE COWLS OF AIRCRAFT ENGINE NACELLES - The disclosure herein provides an alignment and safety device for the cowls of the nacelle of an aircraft engine formed by first and second parts to be arranged opposite of each other at the lower edges of the cowls that include first and second alignment arms configured with a portion arranged to enter inside the inner space of the nacelle covered by the opposite cowl. One of the parts includes a blocking member configured to be interposed between the cowls after being unlatched to facilitate their opening operation and also when they return to the closed position from an open position if they are misaligned to facilitate its alignment and subsequent latching applying a force F on the blocking member. | 03-31-2016 |
| 20160200445 | AIRCRAFT SAFETY DEVICE SYSTEMS | 07-14-2016 |
| 20160251085 | METHOD OF ATTACHING NACELLE STRUCTURE TO MINIMIZE FATIGUE LOADING | 09-01-2016 |
| 20190145273 | Drive System for an Aircraft | 05-16-2019 |
| 20080277533 | Aircraft combination engines inlet airflow control system - A power generation system for propelling, and generating electrical power in, an aircraft, having a gas turbine engine in an engine compartment in the aircraft with an air inlet in the aircraft that is curved along its extent in leading to an air compressor in the gas turbine engine having a compressor air transfer duct extending therefrom to an internal combustion engine provided as an intermittent combustion engine at an air intake thereof. An inlet duct manifold is positioned against the duct wall of the inlet duct to cover a perforated portion thereof on the air compressor side of a curve therein with the inlet duct manifold having an inlet air transfer duct extending therefrom that is coupled to the intermittent combustion engine air intake. | 11-13-2008 |
| 20080283676 | VARIABLE CONTRACTION RATIO NACELLE ASSEMBLY FOR A GAS TURBINE ENGINE - A nacelle assembly includes an inlet lip section having a highlight diameter and a throat diameter. One of the highlight diameter and the throat diameter is fixed and the other of the highlight diameter and the throat diameter is selectively adjustable in each of a first direction and a second direction relative to the inlet lip section to influence a contraction ratio associated with the inlet lip section. | 11-20-2008 |
| 20080296440 | FLOW DISTRIBUTION SYSTEM FOR INLET FLOW CONTROL - A nacelle structure for a gas turbine engine includes an inlet aft of an exit guide vane for supplying air flow to a forward plenum. Air is exhausted from the plenum into an air intake opening and over an inner surface of the nacelle for controlling air flow characteristics within the nacelle. | 12-04-2008 |
| 20080308684 | NACELLE WITH ARTICULATING LEADING EDGE SLATES - A nacelle includes leading edge slates movable to modify inlet shape and area airflow into the nacelle. The articulating leading edge slats are movable for tailoring incoming airflow to current aircraft operating conditions. An actuator disposed within a thickness of the nacelle drives leading edge slates to a desired position to vary the inlet area and shape. | 12-18-2008 |
| 20080315042 | THRUST GENERATOR FOR A PROPULSION SYSTEM - A thrust generator is provided. The thrust generator includes an air inlet configured to introduce air within the thrust generator and a plenum configured to receive exhaust gas from a gas generator and to provide the exhaust gas over a Coanda profile, wherein the Coanda profile is configured to facilitate attachment of the exhaust gas to the profile to form a boundary layer and to entrain incoming air from the air inlet to generate thrust. | 12-25-2008 |
| 20080315043 | Emergency Ram Air Inlet Valve of an Aircraft - The present invention relates to an emergency ram air inlet valve, also designated as an ERAI valve, of an aircraft comprising an actuating element ( | 12-25-2008 |
| 20090008508 | VARIABLE CONTOUR NACELLE ASSEMBLY FOR A GAS TURBINE ENGINE - A gas turbine engine includes a compressor section, a combustor section, a turbine section and a nacelle assembly which at least partially surrounds the compressor section, the combustor section and the turbine section. At least a portion of the nacelle assembly includes an adjustable contour. The portion of the nacelle assembly including the adjustable contour is selectively moveable between a first portion and a second position to influence the adjustable contour of the nacelle assembly. A controller identifies an abnormal aircraft operating condition and selectively moves the portion of the nacelle assembly including the adjustable contour between the first position and the second position in response to detecting the abnormal aircraft operating condition. | 01-08-2009 |
| 20090008509 | AIRCRAFT ENGINE NACELLE INLET HAVING ACCESS OPENING FOR ELECTRICAL ICE PROTECTION SYSTEM - An aircraft engine nacelle inlet is provided with an inlet cowling. The inlet cowling includes an inner lip, an outer lip, and a leading edge portion connecting the inner and outer lips. Heating elements are provided proximate the leading edge, either on an inside surface of the cowling or on an outside surface. An inner barrel portion and an outer barrel portion of the nacelle inlet define a space therebetween. Ice protection-related equipment such as controllers, cables, switches, connectors, and the like, may reside in this space. One or more access openings are formed in the outer barrel to enable an operator to gain access to this equipment. The inlet cowling attaches to the inner and outer barrels with its outer lip extending sufficiently far in the aft direction to cover the access opening. When the cowling is removed, the access opening is uncovered, thereby permitting access to the equipment. | 01-08-2009 |
| 20090014597 | Supersonic aircraft jet engine - Jet engine inlet structure of a supersonic aircraft comprising the structure having an inlet ramp and an cowl lip spaced outwardly of the ramp so that entering air flows between the ramp and lip, the lip and ramp configured to produce a first oblique shock that extends outwardly from a forward portion of the ramp to pass ahead of the lip, and a terminal shock that extends outwardly from a rearward portion of the ramp to one of the following
| 01-15-2009 |
| 20090014598 | AIRCRAFT ENGINE NACELLE INLET HAVING ACCESS OPENING FOR ELECTRICAL ICE PROTECTION SYSTEM - An aircraft engine nacelle inlet is provided with an inlet cowling. The inlet cowling includes an inner lip, an outer lip, and a leading edge portion connecting the inner and outer lips. Heating elements are provided proximate the leading edge, either on an inside surface of the cowling or on an outside surface. An inner barrel portion and an outer barrel portion of the nacelle inlet define a space therebetween. Ice protection-related equipment such as controllers, cables, switches, connectors, and the like, may reside in this space. One or more access openings are formed in the outer barrel to enable an operator to gain access to this equipment. The inlet cowling attaches to the inner and outer barrels with its outer lip extending sufficiently far in the aft direction to cover the access opening. When the cowling is removed, the access opening is uncovered, thereby permitting access to the equipment. | 01-15-2009 |
| 20090114774 | Multi-path inlet for aircraft engine - An inlet for an aircraft, missile or other high speed airborne mobile platform, to receive intake air and compress the intake air for delivery to an engine of the mobile platform. The inlet has an array of inlet elements placed in side-by-side arrangement. Each inlet element has a passage for delivery of intake air. The array provides for compact volume and effective aerodynamic performance. The inlet may be mounted for rotation to start the inlet when at a supersonic speed. The inlet is shorter in length than traditional inlets and can be integrated into a wider variety of airframes, or at locations on existing airframes that would be difficult or impossible to integrate a traditional inlet on. | 05-07-2009 |
| 20090140104 | TURBOJET NACELLE AND METHOD FOR CONTROLLING SEPARATION IN A TURBOJET NACELLE - An aircraft turbojet nacelle comprising blowing means intended to inject a tangential airflow (F | 06-04-2009 |
| 20090152406 | ROTATING AUXILIARY POWER UNIT AIR INLET DOOR - An inlet door assembly includes an inlet door rotatable about an axis of rotation. | 06-18-2009 |
| 20090261208 | AIRCRAFT ENGINE INLET PIVOTABLE BARRIER FILTER - An inlet barrier filter system for an aircraft engine includes a filter panel ( | 10-22-2009 |
| 20090314899 | STRUCTURAL ELEMENT OF AN AIRCRAFT - A rear frame of an air intake of a nacelle of an aircraft, is made in part of composite material that is based on a fiber-reinforced geopolymer resin and includes at least one part ( | 12-24-2009 |
| 20090321585 | NACELLE INLET LIP - A nacelle inlet lip has a simplified geometry. The nacelle inlet lip has a constant cross-section all along a circumference thereof and is wholly concentric relative to the engine centerline, thereby allowing for the use of simple and economical manufacturing processes. | 12-31-2009 |
| 20100019100 | GAS TURBINE ENGINE NACELLE - An initial geometry for a nacelle provides an intake at the upstream end of the nacelle and an exhaust at the downstream end of the nacelle. The intake has in flow series, an intake lip and a diffuser. The intake lip has a highlight defining the boundary between the inner and outer surfaces of the intake lip. On all longitudinal sections containing the axis of the engine (i) the inner and outer surfaces are tangency matched at the highlight, and (ii) the inner and outer surfaces have their maximum curvatures at the highlight. | 01-28-2010 |
| 20100019101 | GAS TURBINE ENGINE NACELLE - A nacelle for a gas turbine engine has an intake at the upstream end of the nacelle and an exhaust at the downstream end of the nacelle. The intake has, an intake lip and a diffuser. The diffuser has a main diffuser section and an optional shorter straight wall diffuser section. The main diffuser section is bounded by an inner wall of the nacelle, the inner wall curving in the airflow direction of the engine. On each longitudinal section containing the engine axis, at the downstream end of the main diffuser section the inner wall has a non zero curvature. Thus each circumferential position on the inner wall at the downstream end of the main diffuser section has a curvature defined by a respective radius of curvature. However, one or more of the radii of curvature differ from the others of the radii of curvature. | 01-28-2010 |
| 20100025542 | MULTI-PATH INLET FOR AIRCRAFT ENGINE - An inlet for an aircraft, missile or other high speed airborne mobile platform, to receive intake air and compress the intake air for delivery to an engine of the mobile platform. The inlet has an array of inlet elements placed in side-by-side arrangement. Each inlet element has a passage for delivery of intake air. The array provides for compact volume and effective aerodynamic performance. The inlet may be mounted for rotation to start the inlet when at a supersonic speed. The inlet is shorter in length than traditional inlets and can be integrated into a wider variety of airframes, or at locations on existing airframes that would be difficult or impossible to integrate a traditional inlet on. | 02-04-2010 |
| 20100044522 | AIR INLET FOR A VEHICLE - The invention relates to an air inlet for a vehicle comprising an opening with an opening contour in an outer skin of the vehicle; at least one bottom element; one or several walls between the opening contour and the bottom element; and an air guide channel with a longitudinal axis, wherein the bottom element extends from the outer skin of the vehicle to an interior region of the vehicle underneath a border edge of the opening, and the air guide channel adjoins from between the bottom element and the border edge, wherein at least one transition region between the opening contour and the walls at least in some regions comprises an essentially convex-shaped profile that essentially extends parallel to the air guide channel. The air inlet according to the invention is in a position to remove air from a flow boundary layer and to provide said air to air-consuming systems. | 02-25-2010 |
| 20100051756 | SYSTEM, METHOD, AND APPARATUS FOR THROAT CORNER SCOOP OFFTAKE FOR MIXED COMPRESSION INLETS ON AIRCRAFT ENGINES - A system, method, and apparatus for throat corner scoop offtake for mixed compression inlets for high speed aircraft engine applications is disclosed. The throat corner scoops are small air intakes located inside the large mixed compression inlet. They are positioned in a region otherwise prone to generate low pressure airflow. The throat corner scoops capture and remove the low pressure airflow from the bulk stream that is passed on to the engine. This location also provides inlet stability enhancement, and the airflow is used on the auxiliary systems. | 03-04-2010 |
| 20100059634 | LOCKING SYSTEM FOR A MOVABLE NACELLE COWL - The present invention relates to a locking system ( | 03-11-2010 |
| 20100140418 | Air Induction Control - Air induction control systems and methods for aircraft are provided. A particular aircraft includes a fuselage, a pair of wings and an engine. The aircraft also includes an inlet defining an aperture to receive air for delivery to the engine. The inlet has a longitudinal axis generally aligned with a direction of flow of the air as the air approaches the inlet. The aircraft also includes at least one first dielectric barrier discharge generator positioned to apply a first force to the air prior to the air being received by the engine. The first force acts in a first direction. The aircraft further includes at least one second dielectric barrier discharge generator positioned to apply a second force to the air prior to the air being received by the engine. The second force acts in a second direction that is non-parallel to the first direction. | 06-10-2010 |
| 20100148012 | AIRCRAFT ENGINE NACELLE WITH TRANSLATING INLET COWL - A nacelle for a turbofan aircraft engine having a fan case with a fan case forward edge includes an inlet inner barrel having an inner barrel forward edge and an inner barrel aft edge. The inner barrel aft edge is configured to be affixed to the fan case forward edge in a stationary position on the engine. The nacelle also includes a translating inlet cowl having an inlet lip with an aft inlet lip edge and an outer skin with rear edge. The translating inlet cowl is configured to be movably attached to one or more stationary portions of the engine such that the inlet cowl is selectively movable between a stowed flight position and an extended service position. | 06-17-2010 |
| 20100176250 | FAIRING FOR A PYLON VIA WHICH A TURBINE ENGINE IS SUSPENDED FROM A WING OF AN AIRCRAFT - Fairing for a pylon via which a turbine engine is suspended from a wing of an aircraft. According to the invention, the forward attachment ( | 07-15-2010 |
| 20100181436 | RELATING TO AIR-BREATHING FLIGHT VEHICLES - An air intake for a supersonic air-breathing flight vehicle introduces or injects fluid in order to create predetermined regions of separated flow and an attendant fluid shear layer. This shear layer forms an aerodynamic boundary for the capture flow with a profile determined and optimised by appropriate injection of fluid. The aerodynamic boundary so generated replaces mechanically moveable solid surfaces used to vary the geometry of prior-art intakes. Use of an introduced or injected fluid can provide an advantage of a variable geometry, but with reduced weight and reduced mechanical complexity. In some embodiments, the injection of fluid has the effect of re-energising any ingested boundary layer, thus obviating the conventional requirement for a bleed system to provide boundary layer control. | 07-22-2010 |
| 20100237200 | Turbojet engine for aircraft, propulsion unit comprising such a turbojet engine and aircraft comprising such a propulsion unit - A propulsion unit comprises a turbojet engine and a thermal exchanger, situated above the turbojet engine. The turbojet engine comprises a regulation device to regulate an air flow-rate in a cooling air lead-in conduit conveying a stream of cooling air into a thermal exchanger, The regulation device regulates the air flow-rate upstream with respect to the cooling air lead-in conduit | 09-23-2010 |
| 20100252689 | AIRCRAFT NACELLE GUIDANCE SYSTEM INSTALLATION - The present invention relates to a turbojet engine nacelle ( | 10-07-2010 |
| 20100276548 | ACOUSTIC PROCESSING STRUCTURE PARTICULARLY ADAPTED TO THE AIR INLET OF AN AIRCRAFT NACELLE - An acoustic treatment structure related to a leading edge onto which an aerodynamic stream flows, in particular at an air intake of an aircraft nacelle, includes—from the outside to the inside—at least one acoustically resistive substructure ( | 11-04-2010 |
| 20100314501 | LOCKING SYSTEM FOR AIR INTAKE STRUCTURE FOR TURBOJET ENGINE NACELLE - The invention relates to a nacelle for a turbojet engine that includes an air intake structure ( | 12-16-2010 |
| 20110001019 | RAM DOOR ASSEMBLIES - A ram door assembly is provided for an intake opening of an intake duct of an auxiliary power unit of an aircraft. The ram door assembly includes a ram door hingeably mounted adjacent to the intake opening and moveable between an open position to a closed position. The ram door has an interior surface and an exterior surface. The ram door assembly further includes a fairing positioned on the interior surface of the ram door. | 01-06-2011 |
| 20110062290 | Supersonic aircraft jet engine installation - Jet engine inlet structure of a supersonic aircraft comprising the structure having an inlet ramp and an cowl lip spaced outwardly of the ramp so that entering air flows between the ramp and lip, the lip and ramp configured to produce a first oblique shock that extends outwardly from a forward portion of the ramp to pass ahead of the lip, and a terminal shock that extends outwardly from a rearward portion of the ramp to one of the following
| 03-17-2011 |
| 20110073716 | Ram Air Duct Flap Arrangement And Ram Air Duct - A ram air duct flap arrangement ( | 03-31-2011 |
| 20110108676 | AIR INLET FOR AN AIRCRAFT TURBINE ENGINE, AN AIRCRAFT PROVIDED WITH SUCH AN AIR INLET, AND A METHOD OF OPTIMIZING THE OPERATION OF AN AIRCRAFT TURBINE ENGINE WITH THE HELP OF AN AIR INLET - The present invention relates to an air inlet ( | 05-12-2011 |
| 20110114796 | DEVICE FOR SHROUDING AN AIRCRAFT NACELLE - An aircraft nacelle includes an air intake ( | 05-19-2011 |
| 20110139940 | WAVE ATTENUATION PANEL INSERTED BETWEEN THE MOTOR AND AIR INLET OF AN AIRCRAFT NACELLE - An aircraft nacelle includes an air intake for channeling air flow in the direction of a power plant. The air intake includes an inside pipe that forms an aerodynamic surface in contact with the air flow and is extended toward the rear by an aerodynamic surface of a pipe of the power plant. The nacelle includes a wave attenuation panel which limits or prevents the propagation of at least one wave produced during the pumping of the power plant and includes a layer that is in contact with the air flow that can allow passage of the at least one wave, at least one alveolar structure, and a reflective or impermeable layer, wherein the wave attenuation panel is inserted between the air intake and the power plant, and the layer that is in contact with the air flow ensures the continuity of the aerodynamic surfaces that are arranged downstream and upstream and the wave attenuation panel includes inserts that can be inserted between the air intake and the power plant so as not to crush the wave attenuation panel. | 06-16-2011 |
| 20110147534 | MEASUREMENT INSTRUMENT SUPPORT INTERPOSED BETWEEN A DRIVE UNIT AND AN AIR INTAKE OF AN AIRCRAFT NACELLE - An aircraft nacelle includes an air intake ( | 06-23-2011 |
| 20110163207 | AIRPLANE HAVING ENGINES PARTIALLY ENCASED IN THE FUSELAGE - An airplane provided with dual-flow turbojet engines having nacelles at least partially encased in the fuselage, wherein the air intake of each engine is connected to the fuselage by two boundary layer guiding walls, the walls extending towards the upstream side of the air intake and being spaced apart towards the upstream side. | 07-07-2011 |
| 20110168852 | METHOD OF DEPOSITING A COATING FOR IMPROVING LAMINAR FLOW - A process for deposition of a coating whose purpose is to improve the laminar flows at a junction between a first panel ( | 07-14-2011 |
| 20110215204 | SYSTEM AND METHOD FOR GENERATING THRUST - A thrust generator includes an air inlet configured to introduce air within the thrust generator and a plenum having a plurality of fluid injection devices. The plenum is configured to receive an exhaust gas from a gas generator and direct the exhaust gas via the plurality of fluid injection devices radially into the thrust generator and along a Coanda profile surface configured to facilitate attachment of the exhaust gas to the profile surface to form a boundary layer and to entrain incoming air from the air inlet to generate thrust. The thrust generator has a non-circular shape. | 09-08-2011 |
| 20110253843 | Air Intake Arrangement For An Aircraft - The invention relates to an arrangement ( | 10-20-2011 |
| 20110272533 | JET ENGINE NACELLE INTENDED TO EQUIP AN AIRCRAFT - The invention relates to a jet engine nacelle intended to equip an aircraft, comprising a forward air inlet section, a mid-section intended to surround a fan of the jet engine, and an aft section formed from at least first and second half-shells ( | 11-10-2011 |
| 20110309203 | METHODS AND APPARATUS FOR MISSILE AIR INLET - Methods and apparatus for delivering a missile may operate in conjunction with a missile comprising an outer skin. The missile may be configured in a closed position and an open position. In the open position, an aperture is opened in the outer skin, for example to supply air to an air-breathing engine. In the closed position, the aperture is closed. | 12-22-2011 |
| 20120091285 | AIRCRAFT NACELLE INCLUDING A CONTINUE JOINT AREA BETWEEN AN OUTER WALL AND A FRONT FRAME - An aircraft nacelle includes a lip that is extended inside the nacelle by an inside wall that delimits a pipe that empties at a power plant and outside of the nacelle by an outside wall, a first frame called a front frame that connects the inside wall and the outside wall, delimiting an annular pipe with the lip, and a second frame called a rear frame that connects the inside wall and the outside wall close to the power plant, characterized in that it includes at least one junction zone—at at least one cross-section of the nacelle along a plane that contains the longitudinal axis of the nacelle—an element that constitutes at least one part of the outside wall and at least one part of the front frame and that includes an offset whose shapes are suitable for accommodating a panel that forms the lip. | 04-19-2012 |
| 20120091286 | ISENTROPIC COMPRESSION INLET FOR SUPERSONIC AIRCRAFT - A supersonic inlet employs relaxed isentropic compression to improve net propulsive force by shaping the compression surface of the inlet. Relaxed isentropic compression shaping of the inlet compression surface functions to reduce cowl lip surface angles, thereby improving inlet drag characteristics and interference drag characteristics. Supersonic inlets in accordance with the invention also demonstrate reductions in peak sonic boom overpressure while maintaining performance. | 04-19-2012 |
| 20120181389 | PASSIVE CONTROL OF ICE SHEDDING - A plate including a body with an aft face at an aft portion of the body, which is attachable to a leading edge of an ice accretion surface such that the body protrudes substantially in a forward direction from the leading edge, and a forward face opposite the aft face, which extends between opposing surfaces of the body and which is oriented substantially perpendicularly with respect to the forward direction and a predominant flow direction of air flowing past the leading edge. | 07-19-2012 |
| 20120261521 | NACELLE INCORPORATING AN ELEMENT FOR CONNECTING A LIP AND AN ACOUSTIC ATTENUATION PANEL TOGETHER - An aircraft nacelle includes a first subassembly consisting of a pipe ( | 10-18-2012 |
| 20120280090 | CONNECTING DEVICE PARTICULARLY ADAPTED FOR THE CONNECTION BETWEEN AN AIR INTAKE AND AN ENGINE OF AN AIRCRAFT NACELLE - A connecting device between two cylindrical parts that are connected at a junction plane, more particularly suited for connecting an air intake and a power plant of an aircraft nacelle, includes—at the parts to be connected—a large number of through holes that are perpendicular to the junction plane and that empty out at the junction plane, arranged facing one another and connecting elements housed in the through holes, each including a rod with supports at each end that make it possible to keep the parts to be connected flattened. The through holes include—for each—at least one small cross-section that is adjusted to the rod of the connecting element close to the corresponding support and a cross-section with significant play at the junction plane so that the rod only undergoes very weak shear forces at the junction plane during the relative deformation of the assembled parts. | 11-08-2012 |
| 20120292455 | AUXILIARY POWER UNIT INLET DUCT SCREEN ASSEMBLY - An example inlet duct screen assembly includes a grid portion having a plurality of apertures and a frame portion circumscribing the grid portion. The grid portion and the frame portion are formed from a single sheet of material. An example method of making an auxiliary power unit inlet duct screen includes machining apertures in a sheet of material to establish a grid portion of an inlet duct screen. | 11-22-2012 |
| 20120325978 | NACELLE FLOW ASSEMBLY - A nacelle assembly for a turbine engine has a cowl for a turbine engine. The cowl has a first surface spaced from a second surface. The second surface defines defining a bypass flow passage. A flow volume is spaced between the first surface and the second surface. A plurality of holes are disposed on the cowl. Each of the plurality of holes are configured to alter local air pressure about one of the first surface and the second surface of the cowl. The plurality of holes are in communication with the flow volume. | 12-27-2012 |
| 20130001369 | AUXILIARY POWER UNIT INLET - An aircraft auxiliary power unit assembly includes an aircraft skin providing a cavity. The aircraft skin is secured to a structure in an assembled condition and provides an opening. An auxiliary power unit is arranged within the cavity and secured to the structure. The aircraft skin substantially covers the auxiliary power unit in the assembled condition. An inlet duct is removably secured within the opening and is selectively connected to the auxiliary power unit between installed and service positions. The installed and service positions are with the aircraft skin in the assembled condition. A method of servicing the auxiliary power unit includes removing the auxiliary power unit inlet duct from the opening in the aircraft skin. The auxiliary power unit that is arranged within the cavity of the aircraft skin is exposed. A portion of the auxiliary power unit is serviced through the opening. | 01-03-2013 |
| 20130075539 | COMPOSITE AEROSPACE STRUCTURE WITH INTEGRATED CONVEYANCE ELEMENT - A composite structure for aerospace applications includes a structural member having multiple composite layers providing a longitudinally extending cavity. A conveyance element is arranged between and integral with the layers. In one example, the structural member provides a gas turbine engine duct or an airframe component. A composite structural assembly is manufactured by providing a first composite layer on a form that corresponds to a cavity. A second form, which may be a conveyance element in one example, is positioned along the first layer. A second composite layer is laid onto the second form and the first composite layer to provide a composite structural member with an integrated conveyance element. | 03-28-2013 |
| 20130087663 | SELF-ALIGNING INLET PLENUM SYSTEM FOR ROTORCRAFT - An inlet system for a rotorcraft includes a cowl door assembly and a plenum assembly. The cowl door assembly includes a door member, a cowl inlet opening, and a cowl inlet duct. The plenum assembly is configured to free float in relation to the cowl door. The plenum assembly includes a plenum duct with a plenum band configured to attach the plenum assembly to an inlet opening. An aft seal is located between the aft plenum flange and a firewall, the aft seal being configured to provide a compressive contact between the plenum assembly and the firewall. | 04-11-2013 |
| 20130168502 | AIRCRAFT AIR INLET DIVERTER ASSEMBLIES WITH IMPROVED AERODYNAMIC CHARACTERISTICS - Diverter assemblies for aircraft air inlets include a diverter structure at least substantially surrounding the air inlet, and a fairing mounted to an upper edge of the diverter structure forwardly of the air inlet. | 07-04-2013 |
| 20130206920 | Driven Aircraft, in Particular to an Aircraft Designed as a Flying Wing and/or Having a Low Radar Signature - An aircraft is provided includes at least one drive flow passage, which runs from an air inlet directed forward on the body surface via a jet engine through the body to a jet nozzle that opens towards the rear on the body surface. At least a part of the jet engine is arranged upstream of the air inlet seen in the flight direction of the aircraft and the drive flow passage has curvature sections embodied and arranged for this in a suitable manner. | 08-15-2013 |
| 20130248657 | DEPLOYABLE INLET SCOOP FOR AN INBOARD RAM AIR TURBINE - An aircraft includes a fuselage that has an exterior contour with an opening and a duct that is arranged interiorly of the exterior contour and extends from the opening. A ram air turbine is arranged within the duct. A deployable inlet scoop is mounted on the fuselage and is configured to be moveable between stowed and deployed positions. The stowed position blocks the opening into the duct and the deployed position exposes the opening and permits airflow through the duct. A method of providing electrical power includes identifying an electrical power demand condition, deploying an inlet scoop from an aircraft fuselage, and driving a ram air turbine with an airflow through the inlet scoop into the fuselage. | 09-26-2013 |
| 20130313371 | ENGINE INLET - An inlet duct for an engine or multiple engines includes two or more joining duct legs and a pressure relief pathway located at each duct leg to condition inlet airflow from the duct legs. A method of operating an aircraft includes urging an inlet airflow into two or more duct openings disposed at a fuselage of the aircraft. The inlet airflow is urged through two or more converging inlet duct legs extending from the two or more duct openings toward an engine inlet. A portion of the inlet airflow is flowed from at least one inlet duct leg of the two or more inlet duct legs into a pressure relief pathway. An inlet duct for an engine or multiple engines includes one or more inlet duct legs and a bypass leg extending from an inlet duct leg of the one or more inlet duct legs through a bypass opening. | 11-28-2013 |
| 20140158833 | AIR INLET COMBINING A FILTER AND A BYPASS DEVICE FOR USE WITH A TURBINE ENGINE - An air inlet ( | 06-12-2014 |
| 20150034771 | DEVICE FOR SUPPLYING AIR TO AN AUXILIARY POWER UNIT OF AN AIRCRAFT AND ASSOCIATED AIRCRAFT - A device for supplying air to an auxiliary power unit for aircraft, including the auxiliary power unit; a turbocharger, and a cabin, the auxiliary power unit including a diesel engine coupled to the turbocharger in such a way that: the turbocharger includes a first air inlet in a compressor of the turbocharger coming from the cabin for its intake into a combustion chamber of the diesel engine, the diesel engine including: a first outlet carrying the air burnt by the combustion chamber to the turbocharger, the diesel engine delivering a power making it possible to supply an electric alternator and pressurising compressor, intended to pressurise a second air inlet, wherein the first air inlet is supplied by a fraction of pressurised air from the cabin of an aircraft. | 02-05-2015 |
| 20150090844 | HELICOPTER WITH ENGINE AIR INTAKES - A helicopter with a fuselage, at least two engines substantially inside said fuselage, an air intake for each of said two engines and at least two separate lateral air inlet ports for said at least two engines in said fuselage. Said separate lateral air inlet ports being arranged on sides opposed to each other relative to an essentially vertical midplane of said fuselage and oriented with their respective cross section substantially parallel to a forward flight direction of the helicopter. At least one frontal air inlet port with a forward portion is provided separate from said lateral air inlet ports, said frontal air inlet port being located on a gear cowling of the fuselage oriented with its cross section substantially perpendicular to the forward flight direction of the helicopter. | 04-02-2015 |
| 20150122952 | GAS TURBINE ENGINE INLET WALL DESIGN - A gas turbine engine has an inlet duct formed to have a shape with a first ellipse in one half and a second ellipse in a second half. The second half has an upstream most end which is smaller than the first ellipse. The inlet duct has a surface defining the second ellipse which curves away from the first ellipse, such that the second ellipse is larger at an intermediate location. The second ellipse is even larger at a downstream end of the inlet duct leading into a fan. | 05-07-2015 |
| 20150291288 | ENGINE INLET CONFIGURATION - An engine inlet assembly includes an inlet duct having a first inlet duct leg and a second inlet duct leg, the first inlet duct leg and the second inlet duct leg extending toward a common inlet duct outlet located at an engine inlet. The first inlet duct leg and the second inlet duct leg are fixedly secured to an airframe of an aircraft at an air inlet. The duct outlet has a floating interface with the engine inlet. | 10-15-2015 |
| 20150314883 | Intake for an Engine of an Aircraft - An intake for feeding air to an engine of an aircraft includes an opening for sucking in air, which opening faces in the direction of movement of the aircraft; and an air duct between the opening and the engine, which air duct is curved such that an impact region is arranged in the air duct after the opening in relation to the direction of movement of the aircraft. An object flying into the opening contacts the impact region. The impact region has a penetration region, which is designed to be penetrated by the impinging object. | 11-05-2015 |
| 20150360790 | AIRCRAFT NACELLE COMPRISING AN IMPROVED AIR INTAKE - An aircraft nacelle comprising an air intake configured to channel an air flow in the direction of an engine assembly which comprises a fan with an axis of rotation, said air intake comprising, according to a flow direction of the air flow, a lip with a leading edge and an internal conduit which extends said lip towards the fan, wherein the air intake comprises a plurality of protrusions distributed over the circumference of the air intake and following each protrusion, a concave form configured in order to achieve compression of the air flow. | 12-17-2015 |
| 20160017844 | REVERSE CORE ENGINE WITH THRUST REVERSER - An engine system has a gas generator, a bi-fi wall surrounding at least a portion of the gas generator, a casing surrounding a fan, and the casing having first and second thrust reverser doors which in a deployed position abut each other and the bi-fi wall. | 01-21-2016 |
| 20160039477 | ZERO AERODYNAMIC DRAG VEHICLES - A vehicle for transporting people as well as goods that moves with minimal aerodynamic drag loss because the energy in the aerodynamic drag is transferred to the propulsive thermal engine. The high dynamic air pressure in front of the vehicle ( | 02-11-2016 |
| 20160075439 | AIRCRAFT WITH AN AIR INTAKE FOR AN AIR BREATHING PROPULSION ENGINE - An aircraft with a fuselage that accommodates at least one air breathing propulsion engine, the fuselage having a maximum fuselage width determined in the region of the at least one air breathing propulsion engine and comprising at least one front fuselage cowling and at least one rear fuselage cowling that are each covering the at least one air breathing propulsion engine at least partly, the at least one front and rear fuselage cowlings being spaced apart from each other in a direction transverse to a longitudinal axis of the at least one air breathing propulsion engine by a predetermined cowling offset to define a dynamic air intake through which an intake air stream is supplied to the at least one air breathing propulsion engine in operation. | 03-17-2016 |
| 20160122005 | EMBEDDED ENGINES IN HYBRID BLENDED WING BODY - A hybrid wing aircraft has an engine embedded into a body of the hybrid wing aircraft. The embedded engine has a fan that is received within a nacelle. The body of the aircraft provides a boundary layer over a circumferential portion of a fan. A system delivers additional air to correct fan stability issues raised by the boundary layer. | 05-05-2016 |
| 20160144949 | METHOD OF CONTROLLING BOUNDARY LAYER FLOW - An aircraft inlet comprising an annular air intake structure defined by an inner surface and an outer surface, a plurality of perforations formed in the outer surface of the aircraft inlet, a plenum chamber situated within the aircraft inlet and configured to receive air entering the plurality of perforations, and/or a plurality of sensors disposed about the outer surface of the aircraft inlet, each sensor associated with a region of the plurality of perforations. Each sensor may comprise a hot film anemometer. The aircraft inlet may further comprise a regulator coupled at one end to the plenum chamber and at another end to a pump, wherein the regulator regulates a suction produced by the pump. | 05-26-2016 |
| 20160144972 | Blended Wing Body Boundary Layer Ingesting Inlet Design Integration - An inlet for a propulsion system has an upper wall and a lower wall and a throat extending between the upper wall and the lower wall. The lower wall has a bump edge located immediately after the throat. | 05-26-2016 |
| 20160375988 | MULTI-ZONE ACTIVE LAMINAR FLOW CONTROL SYSTEM FOR AN AIRCRAFT PROPULSION SYSTEM - A nacelle is provided for an aircraft propulsion system. The nacelle may include an outer barrel and an active laminar flow control system. The active laminar flow control system may include a plurality of suction sources and a plurality of arrays of perforations in the outer barrel. The active laminar flow control system may be configured with a plurality of zones. Each of the zones may include a respective one of the suction sources which is fluidly coupled with a respective one of the arrays of perforations in the outer barrel. | 12-29-2016 |
| 20160376018 | SWEPT GRADIENT BOUNDARY LAYER DIVERTER - A swept gradient air boundary layer diverter for an aircraft. The aircraft includes a fuselage and an air inlet for an engine of the aircraft, where the air inlet includes a cowl at a leading edge of the inlet. The diverter includes a V-shaped ramp portion formed in the fuselage in an area proximate to and in front of the cowl where the ramp portion extends downward away from an outer surface of the fuselage towards an inside of the aircraft. The diverter also includes a V-shaped trough portion formed into the fuselage and being positioned adjacent to and integral with the ramp portion between the ramp portion and the air inlet. Air flowing over the fuselage towards the cowl is expanded and compressed by the ramp portion and the trough portion so as to create pressure gradients that generate vortices to redirect boundary layer airflow around the air inlet. | 12-29-2016 |
| 20190144126 | Air Management Systems for Stacked Motor Assemblies | 05-16-2019 |
| 20080315041 | POWER STARTER FOR MICRO AIR VEHICLES - A manual starter for an engine includes a main housing, an output shaft, a spring housing, a spring, and an attachment unit. The output shaft is disposed at least partially inside the main housing, and is configured to supply a starting torque to the engine. The spring housing is disposed in the main housing. This spring is disposed in the spring housing, and is configured to receive an initial force from a starter cord and to supply the starting torque to the output shaft. The attachment unit is configured to selectively couple the spring to the output shaft before the engine has started and decouple the spring from the output shaft after the engine has started. | 12-25-2008 |
| 20100252688 | DEVICE AND METHOD FOR CONVERTING SUPPLIED ELECTRICAL POWER INTO MECHANICAL POWER TO START AT LEAST ONE ENGINE - The present invention relates in to a device for supplying mechanical power to start at least one engine, with a power supply device for supplying electrical power with an alternating voltage and constant frequency; and with a number, N1, of conversion devices for the conversion of the supplied electrical power to a respective mechanical power for a respective engine, wherein a respective conversion device has a cascade starter generator for direct conversion of the supplied electrical power to mechanical power, wherein the cascade starter generator has a first stator, a second stator, a first rotor and a second rotor, the first stator being integrally formed with the second stator and the first rotor being integrally formed with the second rotor. The present invention further relates to an aircraft comprising such a power distribution network and a method for supplying mechanical power to start at least one engine in an aircraft. | 10-07-2010 |
| 20130233977 | Engine Starting System For Rotorcraft In Flight - A rotorcraft engine starting system includes a starting system controller in communication with a flight control computer; an electric engine starter; an electronic engine controller in communication with the electric engine starter; an electrical power distributor; and a plurality of power sources coupled to the electrical power distributor; the starting system controller selecting at least one of the plurality of power sources and instructing the electrical power distributor to use the at least one of the plurality of power sources to power the electric engine starter. | 09-12-2013 |
