Class / Patent application number | Description | Number of patent applications / Date published |
244058000 | Auxiliary | 64 |
20080203218 | Systems And Methods For Reducing Pressure Loss Of Air Flowing From A First Area To A Second Area - Systems and methods are provided for reducing pressure loss of air flowing from a first area in a first direction to a second area in a second direction. The systems include a flow surface, first and second fence walls, an opening, and a flow path. The flow surface defines a portion of the first area. The fence walls extend substantially parallel to each other along the flow surface in the first direction. The opening is formed in the flow surface and is disposed between the first and second fence walls. The flow path defines at least a portion of the second area and is in flow communication with the opening to receive a portion of the airflow and to direct the airflow in the second direction. Methods of using and manufacturing the systems are also provided. | 08-28-2008 |
20090072080 | ON BOARD SECONDARY PROPULSION SYSTEM FOR AN AIRCRAFT - An on board secondary propulsion system for an aircraft provides the capability of taxiing the aircraft on the ground without using the main aircraft engine(s). The power system includes a small driver mounted on the aircraft. In one embodiment of the invention, the driver may be mounted at any desirable location on the aircraft and is designed to provide sufficient thrust to taxi the aircraft. Such a suitable system may be provided as original equipment to an aircraft or retrofitted to existing aircraft. In a further embodiment of the invention, the on board secondary propulsion system, in addition to the taxiing function, may be incorporated with an alternator to provide electrical power, an environmental control unit, and an emergency power unit as desired. The system may also be used to supplement the main aircraft engines as necessary during takeoff and climb to further reduce fuel consumption, noise, engine emissions, maintenance costs and extend the life of the main aircraft engines. Additionally the thrust provided by the secondary propulsion system could essentially reduce the required takeoff distance of an aircraft, thus allowing the use of shorter runways. | 03-19-2009 |
20090108128 | GROUND SUPPORT SYSTEM - A ground support system configured to support servicing of aircraft may include a main body housing one or both of an engine and/or a blower, a control panel that is used to control operation of one or both of the engine and/or blower, and at least one acoustic wave engagement member positioned on the control panel. The acoustic wave member(s) is configured to selectively activate and deactivate an engine or blower function when touched by an operator. The acoustic wave engagement member(s) operates in the presence of moisture and debris. | 04-30-2009 |
20090121077 | Method and apparatus for operating an aircraft landing system - A method and apparatus is disclosed in which an aircraft landing system is at least partly primarily powered by power provided by a ram air turbine (RAT). | 05-14-2009 |
20090152394 | METHOD OF FEEDING ENERGY TO ACTUATORS ASSOCIATED WITH AN AIRCRAFT UNDERCARRIAGE - The invention relates to a method of feeding energy to actuators associated with the undercarriages forming the landing gear of an aircraft, the aircraft comprising:
| 06-18-2009 |
20090230239 | ICE PROTECTION POWER SUPPLY - There is disclosed an electrical system for an aircraft comprising: at least one generator ( | 09-17-2009 |
20090294581 | Configuration of the pneumatic installation in the tail zone of an aircraft - Which comprises an auxiliary power unit ( | 12-03-2009 |
20090302152 | Engine arrangement - There is a necessity to provide power for some aircraft service functions whilst the main engines ( | 12-10-2009 |
20090308973 | AIRCRAFT TAIL CONE - In a rear cone of a fuselage of an airplane a pressurized space is arranged in the rear cone and extends up to an impervious strong wall, placed on a rear portion of the length covered by a fin. The pressurized space constitutes an area accessible to individuals and is able to constitute, in particular, a rest and service area for the crew. | 12-17-2009 |
20100001124 | CONTROLLABLE DROGUE - A refueling drogue assembly including a refueling drogue receptacle, a control unit including a duct, and a refueling hose connector adapted to rigidly couple the control unit to an aerial refueling hose. In some embodiments, the control unit is flexibly coupled to the refueling drogue receptacle. In some embodiments, the control unit is adapted to change an orientation of at least a portion of the duct relative to a longitudinal axis of the control unit. | 01-07-2010 |
20100044504 | REAR PROPULSION SYSTEM WITH LATERAL AIR INLETS FOR AN AIRCRAFT WITH SUCH SYSTEM - A propulsive system for an aircraft including an auxiliary jet engine is integrated within a tail cone of a fuselage. Lateral air intakes include each one a scoop movable between a closed position and an opened position are associated with aerodynamic channels to supply with air the auxiliary jet engine. The aerodynamic channels meet at a common channel including a movable flap to balance air flows coming from the air intakes when the operation is not symmetrical. | 02-25-2010 |
20100170981 | ENERGY STORAGE AERODYNAMIC BRAKING DEVICE AND METHOD - In order to generate an efficient aerodynamic braking force, whatever the speed of a vehicle such as an airplane flying in the air, the method includes a step for the production of energy by the vehicle, a step of storage of the energy produced and a step of utilisation of such energy to drive a propeller which generates a force opposing the forward motion of the vehicle. Energy is produced by using the displacement of the vehicle with respect to air using a propeller driving a generator, or using the displacement with respect to the ground, using wheels driving a generator, or using generators driven by motors of the vehicle. The energy can be stored in the pneumatic, electric or kinetic form and the generation and driving means are selected according to the technology used for the storage means. | 07-08-2010 |
20100193629 | LOCALIZED UTILITY POWER SYSTEM FOR AIRCRAFT - The disclosure provides for an aircraft galley and lavatory energy system capable of independent operation from a separate aircraft energy generating system. The galley and lavatory energy system comprises an energy source providing electrical energy, heat energy, and at least one by-product; a plurality of galley and lavatory devices for receiving the electrical energy, the heat energy, and the at least one by-product; and, a plurality of connectors for connecting the electrical energy, the heat energy, and the at least one by-product to the galley and lavatory devices. The energy source comprises a fuel cell, a fuel module, and optionally, a supplemental fuel source. | 08-05-2010 |
20100193630 | SYSTEM FOR ELECTRICAL GENERATION, CONVERSION, DISTRIBUTION, AND STARTING ON BOARD AN AIRCRAFT - A system for electrical generation, conversion, distribution and starting on board an aircraft, of “bleedless” type, that is, with an electrical power architecture with no pneumatic circuits. The electrical distribution channels for high power loads specific to aircraft of “bleedless” type, and the electrical distribution channels for conventional loads, including technical loads, such as avionics, lighting, fuel pumps and commercial loads are separated, and are supplied with power by separate generators driven by the aircraft's engines. | 08-05-2010 |
20100193631 | Hydraulic Drive, Hydraulic Supply Device, Airplane with a Hydraulic Supply Device and Method for Configuring a Hydraulic Supply Device - A hydraulic drive for an aircraft includes: a gear, a first hydraulic pump and a second hydraulic pump, wherein the gear is installed in a gear housing and wherein the first hydraulic pump and the second hydraulic pump in each case are installed in a pump housing that is affixed to the gear housing, or the two together are installed in a pump housing that is affixed to the gear housing; a hydraulic supply device including a first and a second hydraulic system for operating actuators of the aircraft; and a monitoring and drive device, with the hydraulic supply device including a first hydraulic drive for coupling the latter to a first engine, and a second hydraulic drive for coupling the latter to a second engine, wherein each hydraulic drive includes: a gear drive shaft for coupling the respective hydraulic drive to an engine output shaft of the respective associated engine; two hydraulic pumps that are coupled to a gear output shaft, in each case with a connection device for connecting the hydraulic pump to the pressure line and to the suction line of a hydraulic system; an aircraft comprising such a hydraulic supply device; as well as a method for configuring a hydraulic supply device. | 08-05-2010 |
20100200692 | Aircraft electric generation system - This invention provides an aircraft electric generation system, which can achieve significantly increased capacity of electric generation, while adequately suppressing unwanted increase of a front face area of an aircraft engine as well as successfully dealing with considerably large changes of an engine spool speed. This electric generation system is driven by the engine and includes: a continuously variable transmission (CVT) connected with a rotation shaft of the engine; an electric generator located above the CVT and driven by an output of the CVT; and a lubricating oil pump unit located below the CVT and also driven by the output of the CVT. | 08-12-2010 |
20100264261 | AIRCRAFT DRAG MANAGEMENT STRUCTURE - Drag management structure. The structure includes a tube having an entrance and exit along a longitudinal axis. At least one row of stationary swirl generating vanes is provided at the entrance, the swirl vanes disposed at an angle with respect to the longitudinal axis selected to produce a steady streamwise vortex in a fluid at the tube exit. A fan rotor may be disposed upstream of the stationary vanes. | 10-21-2010 |
20110001003 | FILTERING DEVICE WITH INTEGRATED BYPASS FOR AN AIR INLET - A filtering device for an engine or a for power unit with a radial air intake, includes a ring-shaped filter for covering the radial air intake, characterised in that the ring-shaped filter includes a first fixed part and a second mobile part which is movable with respect to the first fixed part through actuator elements, from a filtering position in which the whole radial air intake is covered by the ring-shaped filter, to a bypass position in which the second mobile part uncovers at least partly the radial air intake. | 01-06-2011 |
20110062280 | ELECTROMAGNETIC LANDING GEAR BRAKES - An electromagnetic control for the landing gear of an aircraft includes a hub to be fixed to a frame of an aircraft landing gear. A rotor rotates with a tire on the aircraft landing gear. Permanent magnetic disks are associated with the rotor, and interspersed with disks on the hub. Some of the disks on the hub are electromagnetic disks supplied with electric power, and some of the plurality of disks on the hub are made of high electric conductivity material. | 03-17-2011 |
20110127372 | AUTOMATIC CONTROL SYSTEMS FOR AIRCRAFT AUXILIARY POWER UNITS, AND ASSOCIATED METHODS - Systems and methods for operating aircraft power systems are disclosed. A power system in accordance with one embodiment of the invention includes an aircraft auxiliary power unit and a controller coupled to the aircraft auxiliary power unit, with the controller being configured to automatically stop the auxiliary power unit while the auxiliary power unit is functioning normally. The controller can also be configured to automatically start the auxiliary power unit in-flight when power supplied or expected to be supplied to a subsystem of the aircraft has a non-zero value at or below a threshold value. The controller may also be configured to start the auxiliary power unit when a load or expected load on the subsystem meets or exceeds a threshold value. | 06-02-2011 |
20110240795 | EMERGENCY POWER SYSTEM FOR AN AIRCRAFT - The present invention relates to an emergency power system for an aircraft having at least one fuel cell unit for producing electric power, wherein the fuel cell unit is cooled via at least one cooling circuit which includes at least one heat exchanger, and wherein the heat exchanger is connected to at least one air distribution system of the aircraft cabin so that exhaust air heated by the heat exchanger in the operation of the emergency power system can be distributed via the air distribution system in the aircraft cabin. | 10-06-2011 |
20110315815 | MULTI-SOURCE EMERGENCY POWER OPTIMIZATION - A disclosed emergency power system includes multiple emergency power devices that are each sized to provide partial power during emergency operation and/or full power for a portion of emergency operation. | 12-29-2011 |
20120006938 | POWER GENERATING SYSTEM FOR INTEGRATION INTO AN AIRCRAFT SYSTEM - A power generation system for integration into an aircraft system, including a secondary power supply device having a generator turbine arranged in a duct running between a forward opening and a rearward opening on the fuselage of the aircraft. An electromagnetic unlocking device locks and unlocks a covering device on the forward opening, depending on a signal strength supplied to the unlocking device. The system also includes an actuation device that generates an opening or closing signal for an opening and closing device, and an opening function switching device that activates the unlocking device electrically with a signal strength that locks the covering device in an initial state, and on receipt of a power requirement signal from a power generation monitoring device, activates the unlocking device with a second signal strength that unlocks the covering device. | 01-12-2012 |
20120056034 | VARIABLE CYCLE VTOL POWERPLANT - A VTOL aircraft powerplant choosing between a low-power, turbofan mode during cruise flight and a high-power, lift fan mode during vertical flight. Turbofan mode is a gas turbine engine's shaft power driving a remote front fan. Its fan flow goes to thrust for cruising flight. During VTOL, front fan output enters a boost compressor. It produces the compressed air for a combustion chamber which feeds a large lift-fan turbine. That is the implementation of lift-fan mode. The boost compressor has more stages than the front fan and is a big added load. The gas turbine engine is supercharged to turn that added load: Part of the boost compressor output is taken during VTOL. This is a new version of the supercharging. During cruise flight, a low pressure turbine stage is bypassed to match the lesser load. That completes the apparatus for a variable-cycle VTOL engine. | 03-08-2012 |
20120068008 | Aircraft Provided With A Fuel Cell System - According to the invention, a rear portion ( | 03-22-2012 |
20120119020 | AIRCRAFT, PROPULSION SYSTEM, AND SYSTEM FOR TAXIING AN AIRCRAFT - One embodiment of the present invention is a unique aircraft. Another embodiment is a unique aircraft propulsion system. Still another embodiment is a unique system for taxiing an aircraft without starting one or more main aircraft propulsion engines. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aircraft taxiing and propulsion systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith. | 05-17-2012 |
20120119021 | AIRCRAFT AND PROPULSION SYSTEM - One embodiment of the present invention is a unique aircraft. Another embodiment is a unique propulsion system for an aircraft. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aircraft and aircraft propulsion systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith. | 05-17-2012 |
20120138737 | AIRCRAFT POWER DISTRIBUTION ARCHITECTURE - An aircraft power distribution architecture including an Auxiliary Power Unit, a power distributor, and an electric generator distributes power to multiple aircraft systems. | 06-07-2012 |
20120153076 | AIRCRAFT, PROPULSION SYSTEM, AND SYSTEM FOR TAXIING AN AIRCRAFT - One embodiment of the present invention is a unique aircraft. Another embodiment is a unique aircraft propulsion system. Still another embodiment is a unique system for taxiing an aircraft without starting one or more main aircraft propulsion engines. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aircraft taxiing and propulsion systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith. | 06-21-2012 |
20120160958 | POWER AND COOLING ARRANGEMENT - A vehicle is described having an engine to provide motive transportation and a work producing device used to provide power and thermal conditioning to a payload aboard the vehicle. In one form the work producing device provides power to the payload separate from a network powered by the engine that provides motive transportation. The payload can be a directed energy device in one embodiment. The vehicle can take the form of an aircraft which can be configured to receive the work producing device in a cargo bay/payload bay and/or a pod. | 06-28-2012 |
20120248242 | AIRCRAFT AND AIRBORNE ELECTRICAL POWER AND THERMAL MANAGEMENT SYSTEM - One embodiment of the present invention is a unique airborne electrical power and thermal management system. Another embodiment is a unique aircraft. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aircraft and electrical power and thermal management systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith. | 10-04-2012 |
20120292437 | METHOD FOR POWERING AUTONOMOUS DRIVE MOTORS FOR AN AIRCRAFT - The invention relates to a method for powering an autonomous drive device (4) in an aircraft comprising a certain number of drive motors (5) for the wheels (6) when the jet engines of the aircraft are not activated, the aircraft comprising an auxiliary power unit or APU (2) driving a first generator (1) for supplying power to devices on the aircraft that need to be powered when the jet engines are not activated, characterized in that the method comprises the use of a second generator (8) dedicated to the power supply of the autonomous drive device, the second generator being disposed in parallel with the first generator so as to be driven by the APU and, when it operates as a motor under the action of power recovered by the autonomous drive device, so as to help the APU drive at least the first generator. | 11-22-2012 |
20120318912 | DEAERATOR AND CONDUIT ASSEMBLY - An example deaerator assembly includes a housing having a housing inlet and a housing outlet. A conduit configured to communicate a deaerated coolant is located within the housing. A mixture of coolant and air is deaerated as the mixture is communicated from the housing inlet to the housing outlet within the housing and outside the conduit. | 12-20-2012 |
20120318913 | ON-BOARD AIRCRAFT AUXILIARY POWER SYSTEMS HAVING DUAL AUXILIARY POWER UNITS - Aircraft are provided with a pair of auxiliary power units (APUs) adjacently mounted in parallel relative to one another within the tail cone section of the aircraft's fuselage. In some embodiments, the APUs are mounted generally vertically adjacent to one another. Alternatively, the APUs may be mounted generally horizontally adjacent to one another. The aircraft fuselage may include a pair of downwardly and outwardly oriented strakes adjacent the tail cone having lower edges which establish a maximum take-off pitch angle of the fuselage and define a spatial zone therebetween. The APUs are positioned within such a spatial zone defined between the strakes so that the maximum take-off pitch angle is not required to be changed when modifying an existing single APU aircraft with dual APUs. | 12-20-2012 |
20120318914 | AIRCRAFT POWER SYSTEMS AND METHODS - One embodiment of the present application is directed to a unique method for powering one or more critical loads in an aircraft. Another embodiment is a unique apparatus for powering one or more critical loads upon failure of one or more engines. Other embodiments include unique methods, systems, devices, and apparatus' for powering power loads in an aircraft. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith. | 12-20-2012 |
20120318915 | SUPPLEMENTARY POWER SUPPLY APPARATUS FOR A VEHICLE, IN PARTICULAR A FLYING MACHINE - A supplementary power supply apparatus for electric onboard consumers of a vehicle, in particular flying machines. The apparatus includes openly disposed visible solar surfaces of several solar cells that are arranged in areas on the surface of an outer skin of the vehicle or integrated in the latter in the manner of a layer. Each of the solar cells includes at least two electric terminals by means of which the solar cells may be interconnected to form a solar generator, and several ones of the electric terminals are configured as generator terminals of the solar generator for one or several predetermined voltages between two respective ones of these generator terminals. | 12-20-2012 |
20130008999 | TANKER AIRCRAFT WITH A REFUELING DEVICE FOR REFUELING WITH A HOSE AND AN ELECTRIC POWER GENERATOR DROGUE - A tanker aircraft that comprises at least two hose ( | 01-10-2013 |
20130009000 | METHOD AND APPARATUS FOR OPERATING AN AIRCRAFT LANDING SYSTEM - A method and apparatus is disclosed in which an aircraft landing system is at least partly primarily powered by power provided by a ram air turbine (RAT). | 01-10-2013 |
20130214091 | AUXILIARY POWER SYSTEM - This invention relates to an aircraft having an auxiliary power system, the auxiliary power system, including: a reciprocating engine having an air inlet and an exhaust system; a compressed air source for providing compressed air to the air inlet; and, an electrical generator for providing electrical power. | 08-22-2013 |
20130228648 | AUXILIARY POWER UNIT INLET - An aircraft auxiliary power unit assembly includes an aircraft skin that provides a cavity. It is secured to a structure in an assembled condition and it provides an opening. An auxiliary power unit is arranged within the cavity and is secured to the structure. The aircraft skin substantially covers the auxiliary power unit in the assembled condition. An inlet duct that is removable is secured within the opening and is selectively connected to the auxiliary power unit between the installed and service positions. The installed and service positions are with the aircraft skin in the assembled condition. | 09-05-2013 |
20130256454 | RAM AIR TURBINE PUMP LEAKAGE CONTROL - An example ram air turbine drive shaft assembly includes a drive shaft that rotates about an axis to drive a hydraulic pump and a generator. The drive shaft has an interruption that redirects a fluid flowing from the hydraulic pump to the generator when the drive shaft is rotated. | 10-03-2013 |
20130292509 | RAT ACTUATOR FINE ADJUSTMENT ASSEMBLY - A ram air turbine system includes an actuator having a threaded portion, a rod having a threaded region at or near one end and an eyelet at an opposite end, and a bushing. The bushing has a first thread engaged with the threaded portion of the actuator, and a second thread engaged with the threaded region of the rod, such that an actuation force can be transmitted between the actuator and the rod through the bushing. The first and second threads of the bushing have different pitches. | 11-07-2013 |
20130292510 | FLUID TRANSFER TUBE FOR SEVERE MISALIGNMENT APPLICATIONS - A hydraulic system for a ram air turbine includes a hydraulic pump having a high pressure fluid outlet port, a housing, a pivot post arranged to pass through the housing and defining a mechanical pivot relative to the housing about an axis, a transfer tube positioned between the high pressure fluid outlet port of the hydraulic pump and a port in the housing for the high pressure fluid outlet path, and seal elements positioned at or near opposite ends of the transfer tube. A fluid inlet path and a high pressure fluid outlet path pass through the housing and the pivot post. The transfer tube has a crowned end. | 11-07-2013 |
20130306790 | HYBRID POWER SYSTEM ARCHITECTURE FOR AN AIRCRAFT - A hybrid power distribution system for an aircraft generates hydraulic power from one of a plurality of power sources based on which power source provides energy most efficiently. Power sources includes an electric power distribution bus that distributes electrical energy onboard the aircraft, a pneumatic distribution channel that distributes pneumatic energy onboard the aircraft, and mechanical power provided by one or more engines associated with the aircraft. | 11-21-2013 |
20130320136 | SYSTEM AND METHOD FOR PROVIDING ELECTRICAL POWER - An electrical power unit provides electrical power to an electrical component on-board an aircraft. The electrical power unit includes a hydrogen generation system configured to be positioned on-board the aircraft. The hydrogen generation system is further configured to generate hydrogen using a reaction between water and metal. The electrical power unit also includes a fuel cell configured to be positioned on-board the aircraft. The fuel cell is operatively connected to the hydrogen generation system such that the fuel cell receives hydrogen from the hydrogen generation system. The fuel cell is further configured to generate electrical power from the hydrogen received from the hydrogen generation system and to be electrically connected to the electrical component for supplying the component with electrical power. | 12-05-2013 |
20140027568 | METHOD FOR GENERATING HYDRAULIC POWER IN AN AIRCRAFT, USE OF A HYBRID POWER CONTROL UNIT AND DRIVE SYSTEM - A method for generating hydraulic power in an aircraft, the aircraft having a drive system comprising at least one transmission shaft connected to a power control unit, the power control unit having an electric motor and a hydraulic displacement machine connected to a differential gear unit for driving a common output shaft. The method includes switching the hydraulic displacement machine into a pump mode, arresting the output shaft, rotating the electric motor such that the hydraulic displacement machine is driven due to the arrested output shaft and supplying the fluid flow into a hydraulic system. A drive system of an aircraft may thereby be used for either moving control surfaces or for generating hydraulic power in an aircraft. This hydraulic power may be used to cover hydraulic load peaks during aircraft operation or to power hydraulic devices without the need of additional hydraulic power generation components. | 01-30-2014 |
20140070049 | Ram Air Turbine Release Cable Assembly - A ram air turbine assembly is provided including a release cable coupled at a first end to a turbine release pin and coupled at a second end to a release lever. Aluminum tubing surrounds a portion of the release cable. An upper cable bracket supports the aluminum tubing adjacent the first end of the release cable. A lower cable bracket supports the aluminum tubing adjacent the second end of the release cable. The lower cable bracket includes a threaded bushing having an axial bore for receiving the release cable. The threaded bushing is in direct contact with an end fitting coupled to the aluminum tubing. | 03-13-2014 |
20140084107 | Flexible and fireproof APU drainage device - An aircraft auxiliary power unit (APU) flexible and fireproof drainage device including a bellows which receives leakage fluids from an APU engine; a drain pipe which transfers leakage fluids outside the aircraft from the bellows, and a support piece surrounding the drain pipe. The bellows connects the APU engine with the drain pipe. The support piece provides stability to the bellows and the drain pipe. | 03-27-2014 |
20140145028 | METHOD AND A ROTARY WING AIRCRAFT HAVING THREE ENGINES - An aircraft ( | 05-29-2014 |
20140183299 | AN AIRCRAFT COMPRISING A COCKPIT DELOCALIZED OUTSIDED THE NOSE - The invention concerns an aircraft comprising a cockpit situated outside the nose of the aircraft. The cockpit is situated in a lower part of a fin, the latter advantageously extending to a front end of the aircraft. Preferably, the aircraft has a lancet-shaped nose. | 07-03-2014 |
20140263824 | GENERATOR FOR FLIGHT VEHICLE - A flight vehicle includes a fuselage and a gas turbine engine. The gas turbine engine is coupled to the fuselage to provide thrust when air surrounding the flight vehicle is admitted to the gas turbine engine and combusted with fuel. The flight vehicle further includes a generator coupled to the gas turbine engine to provide power to equipment included in the vehicle. | 09-18-2014 |
20140332623 | TRANSFER TUBE FOR A RAM AIR FAN (RAF) ASSEMBLY - A transfer tube including a tube member extends from a first end to a second end through an intermediate portion having an outer surface and an inner surface. The outer surface has an outside diameter. A flange is mounted at one of the first and second ends of the tube member. The flange includes a flange body extending from a first end portion to a second end portion through an intermediate section having an outer surface and an inner surface. The inner surface defines an inside diameter. The outside diameter of the tube member is between about 0.010-inch (0.0254-cm) and about 0.030-inch (0.0762-cm) smaller than the inside diameter of the flange. | 11-13-2014 |
20140332624 | INLET DUCT SCREEN ASSEMBLY - An example inlet duct screen assembly includes a grid portion including 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. | 11-13-2014 |
20150014479 | INDEPENDENT POWER GENERATION IN AIRCRAFT - A method includes generating thrust at one or more engines of an aircraft. The method includes generating first electricity at a first power unit concurrently with generating second electricity at a second power unit. The first power unit and the second power unit are independent of the one or more engines of the aircraft. The first electricity has a first set of electrical characteristics and the second electricity has a second set of electrical characteristics, where the first set of electrical characteristics is different than the second set of electrical characteristics. | 01-15-2015 |
20150115099 | AUXILIARY POWER UNIT INLET DOOR HAVING OPENINGS FORMED THEREIN - An inlet door system includes a duct, an inlet door, and a plurality of openings. The duct is configured to extend from the auxiliary power unit (APU) to an intake opening formed in an outer surface of an aircraft. The duct includes an inlet port, an outlet port, and a duct sidewall extending between the inlet port and the outlet port. The inlet door includes an inner surface, an outer surface, and an outer peripheral edge between the inner and outer surfaces. The door is rotationally coupled to the duct, and is configured to selectively rotate between a closed position and a plurality of open positions. The openings extend through the inlet door between the inner surface and outer surface, and each opening is disposed adjacent to the outer peripheral edge. | 04-30-2015 |
20150122944 | METHOD AND ARCHITECTURE FOR THE OPTIMIZED TRANSFER OF POWER BETWEEN AN AUXILIARY POWER MOTOR AND THE MAIN ENGINES OF A HELICOPTER - A method and architecture to optimize an entire traction system available on a helicopter by using an auxiliary engine to provide energy to equipment and accessories of the helicopter connected to the engines. Main engines and an APU unit, as an auxiliary engine, include a gas generator connected to, for the main engines, a reduction gearbox and an accessory gearbox for mechanical, electrical, and/or hydraulic power take-off and connected to, for the APU unit, at least one power conversion member. The power conversion member of the APU unit is connected to the equipment and accessories by the reduction gearbox and/or the accessory gearbox of the main engines. | 05-07-2015 |
20150307201 | ENERGY RECOVERY OF AN AIRCRAFT - An apparatus for energy recovery of an aircraft, an aircraft comprising the apparatus and a method of energy recovery are disclosed. The apparatus comprises a turbine having a body and rotor blades. The turbine is adapted to be mounted to the exterior of an aircraft, such that the body receives an air stream flowing at the exterior of the aircraft. The rotor blades are selectively movable between a stowed position and a deployed position, wherein at the deployed position the rotor blades are rotated by the air stream so as to generate electricity. The blades may be deployed during descent of the aircraft to recover energy normally irretrievably dissipated as the aircraft descends and slows. The blades are stowed when not in use, such as during take-off and cruise. | 10-29-2015 |
20150367952 | STRUCTURE FOR FEEDING AIR TO AN AUXILIARY POWER UNIT IN AN AIRCRAFT - The invention concerns a structure ( | 12-24-2015 |
20160075442 | AUXILLIARY POWER AND THRUST UNIT DRIVE SYSTEM - An aircraft auxiliary power and thrust unit includes at least one blade mounted to a fan shaft which are mounted to a tail cone of the aircraft and rotatable relative to the tail cone. Also included is an air intake assembly which includes an opening defined by the tail cone and a channel in fluid communication with the opening and the at least one blade. A first drive shaft positioned to extend in a direction transverse to the fan shaft and engageable to rotate with the fan shaft and first drive shaft engaged and the first drive shaft engageable to a second drive shaft positioned transverse to the first drive shaft such that the second drive shaft rotates with the first drive shaft with the first and second drive shafts engaged. The second drive shaft is positioned outside of the channel of the air intake. | 03-17-2016 |
20160152344 | FIRE EXTINCTION DESIGN FOR AN AUXILIARY POWER UNIT COMPARTMENT OF AN AIRCRAFT | 06-02-2016 |
20160159489 | FIRE CONTAINMENT APPARATUSES FOR AIRCRAFT DUCT ASSEMBLIES - An intake duct assembly for an auxiliary power unit system is provided. A first inlet adapter includes at least one hole through the duct wall. A fire containment apparatus forms a first passage to direct intake air between exterior wall of the aircraft and the enclosure. An inner duct mounted on the first inlet adapter at a first position downstream of the at least one hole and mounted on the second inlet adapter. An outer sheath is mounted on the first inlet adapter at a second position upstream of the at least one hole and mounted on the second inlet adapter. The outer sheath circumscribes the inner duct to form at least a portion of a barrier annulus between the inner duct and outer sheath in fluid communication with the first passage via the at least one hole in the first inlet adapter. | 06-09-2016 |
20160159492 | AUTONOMOUS AIRCRAFT FUEL CELL SYSTEM - Embodiments of the present disclosure relate generally to systems and methods for providing improved aircraft fuel cell systems. In one embodiment, the system provides separate zones, maintaining various equipment components in separate controlled hydrogen concentration zones. In one embodiment, the fuel cell system provided may be simpler such that it functions without a power converter and autonomous such that it functions without need for power from any aircraft supply. | 06-09-2016 |
20160176529 | AIRCRAFT AND AIRBORNE ELECTRICAL POWER AND THERMAL MANAGEMENT SYSTEM | 06-23-2016 |
20160185461 | INTEGRATED AUXILIARY POWER UNIT, STARTER-GENERATOR-MOTOR, AND VAPOR CYCLE COOLING SYSTEM FOR AN AIRCRAFT - A system for an aircraft includes a compressor for a vapor cycle cooling system (VCCS) for providing cabin air conditioning; an APU for mechanically driving the VCCS compressor; and a starter-generator-motor (SGM) apparatus operable in any of a starter mode, a generator mode, or a motor mode. The SGM apparatus includes: (i) a first coupling element for coupling the SGM apparatus to the APU such that, in the starter mode, the SGM apparatus is used in driving and starting the APU, (ii) a second coupling element for coupling the SGM apparatus to the VCCS compressor such that, in the motor mode, the SGM apparatus mechanically drives the VCCS compressor, and (iii) a set of electrical power terminals at which, in the generator mode, the SGM apparatus provides electrical output power for powering the aircraft electrical system (including the VCCS condenser fan and VCCS evaporator fans) and, in the starter mode and motor mode, the SGM apparatus receives electrical input power from an external electrical power source. | 06-30-2016 |