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141. Process and installation for the distribution of air enriched in oxygen to passengers of an aircraft

申请号: US10068869

申请日: 2002-02-11

公开（公告）号: US20020144679A1

公开（公告）日: 2002-10-10

发明人: Jean-Michel Cazenave; Jean Dehayes; Olivier Vandroux; Richard Zapata

According to this process, there is supplied to the passengers a first fraction of air enriched in oxygen from independent supply elements, in particular high pressure cylinders (16), during a descent phase of the aircraft between a normal cruising altitude and an intermediate rerouting altitude. There is moreover compressed air taken from a source of compressed air belonging to the aircraft, to produce (in 2) a second fraction of the air enriched in oxygen which is delivered to the passengers, at least during a phase of stabilized flight of the aircraft, adjacent the re-routing altitude, greater than 5,500 meters.

142. Systems and methods for flight management

申请号: EP13175881.5

申请日: 2013-07-10

公开（公告）号: EP2685292A2

公开（公告）日: 2014-01-15

发明人: Bollapragada, Srinivas; Del Amo, Ana

Systems and methods for flight management are provided. One flight control system is provided that includes a flight management system (32) configured to manage aircraft flight control including at least one of a flight path or an altitude for an aircraft (52). The flight control system also includes a flight parameter selection module (34) configured to determine a Cost Index (CI) and cruising altitude for use by the flight management system to manage the aircraft flight control, wherein the determination is based on a flight cost and predicted weather along the flight path.

143. Process and installation for the distribution of air enriched in oxygen to passengers of an aircraft

申请号: US10701528

申请日: 2003-11-06

公开（公告）号: US20040099271A1

公开（公告）日: 2004-05-27

发明人: Jean-Michel Cazenave; Jean Dehayes; Olivier Vandroux; Richard Zapata

According to this process, there is supplied to the passengers a first fraction of air enriched in oxygen from independent supply elements, in particular high pressure cylinders (16), during a descent phase of the aircraft between a normal cruising altitude and an intermediate re-routing altitude. There is moreover compressed air taken from a source of compressed air belonging to the aircraft, to produce (in 2) a second fraction of the air enriched in oxygen which is delivered to the passengers, at least during a phase of stabilized flight of the aircraft, adjacent the re-routing altitude, greater than 5,500 meters.

144. AIRCRAFT

申请号: PCT/CA2002/001571

申请日: 2002-10-17

公开（公告）号: WO2003035470A1

公开（公告）日: 2003-05-01

发明人: LAMONT, John, S.

An aircraft (10) is provided having a rotary lifting system (26) including vanes (36) supported thereon which are movable between a deployed position in which the vanes (36) provide lift to the aircraft (10) when rotated and an undeployed position in which the rotary lifting system (26) is generally in the shape of an airfoil so as to provide lift when propelled in a forward direction. A forward drive system (54) is included to generate forward thrust to propel the housing in the forward direction. The airfoil shape of the rotary lifting system (26) permits the wings (24) of conventional aircraft to be reduced or even eliminated to minimize excessive drag from wings which are larger than necessary for normal cruise on conventional aircraft. Furthermore, the engines(54) of the forward drive system are not required to be any larger or more powerful than appropriate for sustaining flight at normal cruise height.

145. HYBRID ASSEMBLY FOR AN AIRCRAFT

申请号: US13785737

申请日: 2013-03-05

公开（公告）号: US20130227950A1

公开（公告）日: 2013-09-05

发明人: Richard Anderson; Lori Costello; Charles Eastlake; Glenn P. Greiner

A propeller driven aircraft powered by either an internal combustion engine or an electric motor. The parallel system hybrid aircraft can takeoff with the internal combustion engine and climb to a cruising altitude. The internal combustion engine then can be turned off and the electric motor turned on to power the aircraft's propeller. The aircraft is capable of alternating operation between the electric motor and internal combustion engine as often as required at altitude. The aircraft can be landed using either the internal combustion engine or the electric motor. The transition of power from the internal combustion engine to the electric motor and back is performed through a hybrid clutch and pulley assembly that interconnects the internal combustion engine propeller flange to the propeller driveshaft. The electric motor is connected to the hybrid assembly through belts and sheaves. The electric motor throttle is controlled in the cockpit.

146. Flight path optimization using nonlinear programming

申请号: US14844892

申请日: 2015-09-03

公开（公告）号: US09564056B1

公开（公告）日: 2017-02-07

发明人: Reza Ghaemi; Eric Richard Westervelt; Mark Darnell

A method, medium, and system to receive a mathematical model representation of performance characteristics for an aircraft and an engine combination; perform a projection based model order reduction on the mathematical model representation; eliminate, based on the projected model, fast dynamics components of the mathematical model representation; determine a reduced order model, as a differential algebraic equation, wherein algebraic equations replace the fast dynamics; set a flight path angle and a throttle level angle as a control to minimize fuel consumption for the modeled aircraft and engine combination; discretize equations of motion for the modeled aircraft and engine combination and formulate optimization equations as a nonlinear programming problem; and determine an optimal open loop control that minimizes fuel consumption for the modeled aircraft and engine combination to climb to a prescribed cruise altitude and airspeed.

147. Thermopile Generator for Airplanes and Other Applications

申请号: US15256201

申请日: 2016-09-02

公开（公告）号: US20170057654A1

公开（公告）日: 2017-03-02

发明人: Mohamed Ahmed Abdelhalim Elnahhas

An airframe having an integrated thermoelectric generator and a method thereof for providing electricity in an aircraft. A plurality of thermocouple wires is disposed about an aircraft frame to form a thermopile circuit in which electrical current is generated as a result of a temperature difference observed at a cruising altitude. The temperature difference is created by a hot side, interior to the aircraft frame, and a cold side, exterior to the aircraft frame. The thermopile circuit is formed by a first thermoelectric material and a second thermoelectric material that are selected to produce a desired voltage when exposed to the temperature difference. The electric current is harnessed by a transfer cable and directed to an aircraft electrical system to provide power to the desired devices.

148. SOLAR HOT-AIR BALLOON

申请号: PCT/FR1995001381

申请日: 1995-10-19

公开（公告）号: WO1996012642A1

公开（公告）日: 1996-05-02

发明人:

A dark-coloured hot-air balloon (10) with an open bottom end. Said balloon may be made of webs (12-14) of thin black plastic joined together by means of adhesive strips (16-18). The air in the balloon is continuously reheated by solar radiation. This craft is provided with an electric fan (34), powered by a battery (36), mounted in a protective housing (56) and secured to suspension beams (42) connected to the load ring (20) of the balloon. Said fan (34) can quickly inflate or deflate the balloon (10) to alter the cruising altitude. An electronic unit (38) is provided for controlling the speed and direction of rotation of the motor. Unmanned balloons are recoverable. Said balloon may be used for recreational purposes, for high-altitude scientific prospecting, or for launching aircraft or spacecraft.

149. Hybrid assembly for an aircraft

申请号: US13785737

申请日: 2013-03-05

公开（公告）号: US09102326B2

公开（公告）日: 2015-08-11

发明人: Richard Anderson; Lori Costello; Charles Eastlake; Glenn P. Greiner

150. Altitude measurement system and associated methods

申请号: US11197405

申请日: 2005-08-04

公开（公告）号: US07095364B1

公开（公告）日: 2006-08-22

发明人: Blaine K. Rawdon; Zachary C. Hoisington

An altitude measuring system and method for aircraft is provided. The altitude measuring system includes altitude sensors for providing data to an altitude processing unit. The altitude processing unit spatially averages each output to determine a mean altitude. Pitch and roll are accounted for by correction. A method of determining aircraft altitude from a plurality of altitude sensors includes receiving altitude sensor data from each sensor and spatially averaging the altitude sensor outputs to determine aircraft altitude. A method of estimating the maximum height of an ocean surface includes receiving a plurality of altitude sensor data and determining a mathematical description of the ocean surface from the sensor data. The maximum probable wave height of the ocean surface is estimated from the mathematical description. From the maximum wave height, a cruise altitude may be determined.

151. Window element for insertion in a window aperture in an outer skin of a transport

申请号: US11251054

申请日: 2005-10-14

公开（公告）号: US20060123718A1

公开（公告）日: 2006-06-15

发明人: Bernd Paspirgilis

A window element has a cover pane which is substantially flush with an outer skin of an aircraft or other transport, achieving a fluid-dynamically favourable, substantially unbulged exterior surface. As a result of the presence of an additional back-ventilated cover pane 10 arranged in front of the actual outer pane of the window element, a fluid-dynamically favourable integration of the window element into the outer skin of an aircraft fuselage airframe is achieved. Any deformation, such as any buckling or bulging of the outer pane of the window element, as a result of a difference in pressure between the interior of the aircraft fuselage airframe and the exterior space at cruising altitudes, has no fluid-dynamically disadvantageous effect. The outer pane is covered by the cover pane which remains substantially undeformed with respect to the outer skin of the aircraft fuselage airframe, for example. Any deformation of the cover pane is largely eliminated by this back-ventilation.

152. SYSTEM AND METHOD FOR DETERMINING AND DISPLAYING OPTIMIZED AIRCRAFT ENERGY LEVEL

申请号: EP17190225.7

申请日: 2017-09-08

公开（公告）号: EP3296698A2

公开（公告）日: 2018-03-21

发明人: DE VILLELE, Dorothee; PARICAUD, Erwan; CORBEL, Daniel; POLANSKY, Michal; JANCIK, Zdenek

A system and method of displaying optimized aircraft energy level to a flight crew includes processing flight plan data, in a processor, to determine the optimized aircraft energy level along a descent profile of the aircraft from cruise altitude down to aircraft destination, and continuously processing aircraft data, in the processor, to continuously determine, in real-time, an actual aircraft energy level. The actual aircraft energy level of the aircraft is continuously compared, in the processor, to the optimized aircraft energy level. The processor is use to command a display device to render an image that indicates: (i) the optimized aircraft energy level, (ii) how the actual aircraft energy level differs from the optimized aircraft energy level, and (iii) how the actual aircraft energy level is trending relative to the optimized aircraft energy level.

153. Window element for insertion in a window aperture in an outer skin of a transport

申请号: US11251054

申请日: 2005-10-14

公开（公告）号: US08079185B2

公开（公告）日: 2011-12-20

发明人: Bernd Paspirgilis

A window element has a cover pane which is substantially flush with an outer skin of an aircraft or other transport, achieving a fluid-dynamically favorable, substantially unbulged exterior surface. As a result of the presence of an additional back-ventilated cover pane arranged in front of the actual outer pane of the window element, a fluid-dynamically favorable integration of the window element into the outer skin of an aircraft fuselage airframe is achieved. Any deformation, such as any buckling or bulging of the outer pane of the window element, as a result of a difference in pressure between the interior of the aircraft fuselage airframe and the exterior space at cruising altitudes, has no fluid-dynamically disadvantageous effect. The outer pane is covered by the cover pane which remains substantially undeformed with respect to the outer skin of the aircraft fuselage airframe, for example. Any deformation of the cover pane is largely eliminated by back-ventilation.

154. Various energy conservation cycle integrated engine

申请号: JP2012234242

申请日: 2012-10-24

公开（公告）号: JP2014084789A

公开（公告）日: 2014-05-12

发明人: TANIGAWA HIROYASU; TANIGAWA KAZUNAGA

PROBLEM TO BE SOLVED: To improve existing jet engines and gas turbines having the same number of stationary blades and rotor blades of zero power alternately arranged thereto to interrupt the flow of compressed air and combustion gas, and thereby causing the speed and output to be close to zero.SOLUTION: This invention relates to a double inversion type injection engine 2y etc. having substantially all rotor blades. In this engine, bearing loads are integrated and air compression speed and combustion gas expansion speed near 0 and near 1f of a lateral shaft bearing are made maximum through straight line compression and straight line expansion. A high pressure and high temperature combustion chamber 5M is provided with a high pressure and high temperature water heating pipe 5H so as to recover heat and cool it. The same amount of compression air is kept up to a theoretical air-fuel ratio and fuel burning calorie is set to be four times an existing jet engine. Three-fourths or more of the calorie is consumed with a super-heated steam 50 with a pressure of about 20 times that of the combustion gas so as to attain an injection propulsion output and rotational output of 10 times that of the existing jet engine etc. and apply it to electric power generation, automobile drive, marine ship drive, airplane drive and the like. In the case of the airplane drive, existing rocket launch from the ground level is considered to be the worst scenario, and this rocket launch is therefore carried out from the highest airplane cruising altitude so as to provide 16 round-trips a day around the Earth, which allow us a one-day trip and a moon flight from everywhere on the Earth, for example.

155. Skin of an airplane door and method of making door with same

申请号: US09908729

申请日: 2001-07-20

公开（公告）号: US20020043588A1

公开（公告）日: 2002-04-18

发明人: Jens Bold; Guenther Klockow

The skin of an airplane door conforms in use to a surrounding surface contour of an airplane fuselage. The skin is connected with a door frame which has supports arranged in a longitudinal direction of the fuselage and spaced with respect to one another in a circumferential direction. During flight the skin and door frame are exposed to a pressure load direction. To provide the skin of an airplane door with a clearly smaller dimension for the purpose of a light construction thereby avoid displacements on the skin, the skin and door frame are preformed against an in use pressure load direction. During the flight at cruising altitude, the door has essentially no displacements with respect to the surrounding surface contour of the fuselage, and thus essentially no displacements occur which could increase the flow resistance of the skin. Relative to a material, it is possible to thus construct the skin in a smaller thickness than in the case of known doors, but disturbing displacements on the skin are nevertheless essentially avoided while permitting a weight reduction of the door.

156. Method of reducing wind gust loads acting on an aircraft

申请号: US303264

申请日: 1999-04-30

公开（公告）号: US6161801A

公开（公告）日: 2000-12-19

发明人: Roland Kelm; Michael Grabietz

A method of reducing the bending moment effect of wind gust loads acting on the wing of an aircraft involves adjusting the aerodynamic configuration of the wing so as to alter the distribution of lift generated by the wing during phases of flight in which critical wind gusts are expected to occur. Particularly, during climb and descent phases of flight below cruise altitude, the lift generated by outboard portions of the wings is reduced while the lift generated by inboard portions of the wings is increased. Thereby, the 1 g basis load acting on the outboard portions of the wings is reduced, and consequently the total load applied to the outboard portions of the wings, resulting from the 1 g basis load plus the additional wind gust load, is correspondingly reduced. This leads to a reduction of the bending moments effective on the wings, and of any rolling moment effective on the aircraft. The required adjustment of the lift distribution is preferably achieved by deflecting the ailerons of both wings symmetrically upward and/or deflecting the flaps of both wings symmetrically downward during climb and descent. The adjustment of the wing configuration is carried out dependent only on flight parameters such as the altitude, speed and gross weight, and does not require rapid sensing of the occurrence of a wind gust and rapid actuation of control surfaces to try to instantaneously counteract a wind gust as it occurs.

157. Terminal airways traffic control system

申请号: US38793073

申请日: 1973-08-13

公开（公告）号: US3868497A

公开（公告）日: 1975-02-25

发明人: VIETOR CARL W

A system for scheduling aircraft arrivals from cruise to touchdown, and also for scheduling departures from airport to cruise altitude; wherein space considerations are reserved to the aircraft pilot and wherein time considerations are reserved to the control authority. The aircraft is navigated by the pilot along a Terminal Corridor Route (TCR) in conformance to the requirements of a ground based Traffic Control Computer (TCC). The airborne Aircraft Instrumentation Computer (AIC) includes a programmed computer and an instrument panel display that positions the aircraft relative to an optimum time flexible energy path and responsive to in-flight data which is also telemetered to the TCC for processing. The TCC repeatedly processes all in-range aircraft on a time cycle basis and imposes and regulates time intervals between said aircraft by issuing speed-up and slow-down commands thereto as necessary to qualify said aircraft to proceed, and alerts the control authority and pilot as well of aircraft which do not qualify and/or require corrective proceedures. The system identifies all in-range aircraft and sequentially programs the flight paths thereof along the required track and through waypoints; taking into account the kinetic as well as potential energies involved for executing practical and efficient flight to the ends of infallible traffic control and safety, economy, antipollution and noise abatement.

158. Emergency smoke disposal system for pressurized aircraft

申请号: US422934

申请日: 1982-09-24

公开（公告）号: US4552325A

公开（公告）日: 1985-11-12

发明人: Wilhelm A. Bruensicke

The present invention provides a convenient and reliable means to evacuate smoke from an interior cabin (30) of a pressurized aircraft (20) by providing a normally closed smoke evacuation outlet (102) in the skin (108) of the aircraft in fluid communication with a relatively large area smoke disposal chute (114) extending upwardly from the cabin's ceiling (50), whereby upon the activation of the outlet, the smoke (106) (that otherwise would rise to and collect below the ceiling of the cabin until the whole cabin is full of smoke) will be discharged into the external airstream, with the differential pressure between the relatively high pressure in the cabin and the relatively low pressure in the external atmosphere (particularly at the high cruising altitudes associated with the operation of modern transport aircraft) providing the actual motive power. Preferably, the outlet is designed to be opened automatically (110, 124) in response to smoke in the vicinity of the smoke disposal chute being detected by means of a conventional type of smoke detector (120). The chute between the ceiling and the outlet on the skin may also be provided with a manual means (132, 134) for blocking the further outflow of pressurized air through the skin outlet opening in the event that the apparatus has been activated inadvertently or in the event that the emergency is over.