| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 121 | System onboard an aircraft connected with a flight plan | US13015008 | 2011-01-27 | US08694234B2 | 2014-04-08 | Jean-Claude Mere; Julien Dramet |
| An evaluation method and an evaluation system onboard an aircraft in communication with a flight management system to access a flight plan stored in memory of the flight management system, where the flight plan defines a cruising level and a minimum fuel reserve to destination objective. The evaluation system comprises circuitry to calculate a fuel consumption deviation between flight at a selected cruising altitude level and flight at an altitude level initially planned by the flight plan, where the selected altitude level is lower than the altitude level initially planned, and to determine a climb limit point from the selected cruising altitude level as a function of the fuel consumption deviation and the minimum fuel reserve objective, where the climb limit point represents the last climb point respecting the minimum fuel reserve to destination objective; and interface circuitry to provide the climb limit point and anticipative information concerning the climb limit point. | ||||||
| 122 | LOW DRAG PASSENGER-CABIN WINDOW | US13902707 | 2013-05-24 | US20130313366A1 | 2013-11-28 | Thomas S. Hoffa; Kelvin B. Hsieh |
| A low drag passenger-cabin window for use on an aircraft fuselage having a generally cylindrical shape, in which the as-manufactured geometry of the window is modified so that the shape of the window at cruise altitudes is aerodynamically optimized. The window comprises a pane of transparent material. The inner and outer surfaces of the peripheral portion of the pane as manufactured conform to a generally cylindrical shape, while the inner and outer surfaces of the medial portion of the pane as manufactured are depressed inwardly in a prescribed manner relative to the peripheral portion. The surfaces of the medial portion are adapted to deflect outwardly to conform to a generally cylindrical shape in response to a predetermined air pressure differential and/or a predetermined temperature gradient experienced at cruise altitude. | ||||||
| 123 | SITUATIONAL AWARENESS PILOT BRIEFING TOOL | US13784918 | 2013-03-05 | US20130245860A1 | 2013-09-19 | Jennifer COOPER |
| Embodiments of the present invention relate to a system and method for better conveying information to a pilot and/or other members of a flight crew present on the flight deck of an aircraft. Embodiments of the invention are of particular use in the briefings that precede various phases of the flight operations of an aircraft (such as start-up of the engines, take-off, ascent to cruise altitude, descent from cruise altitude and landing). The system and method provide a briefing output relevant to the particular phases of a flight in both of a visual form and an audio form, with the briefing output including data of most relevance to the particular flight phase. | ||||||
| 124 | Aerodynamic sealing member for aircraft | US14592436 | 2015-01-08 | US09394997B2 | 2016-07-19 | Colin John West |
| A sealing member for forming a seal in an aircraft, the sealing member comprising: a sealing material; and a stiffening element which provides structural support to the sealing material and comprises a material with a glass transition temperature below +50° C. The stiffening element is relatively flexible when the aircraft is at low altitude (high temperature) but becomes relatively stiff (increasing resistance to seal flutter) when the aircraft is at cruise altitude (low temperature). | ||||||
| 125 | Aerodynamic sealing member for aircraft | US12349054 | 2009-01-06 | US09004404B2 | 2015-04-14 | Colin John West |
| A sealing member for forming a seal in an aircraft, the sealing member comprising: a sealing material; and a stiffening element which provides structural support to the sealing material and comprises a material with a glass transition temperature below +50° C. The stiffening element is relatively flexible when the aircraft is at low altitude (high temperature) but becomes relatively stiff (increasing resistance to seal flutter) when the aircraft is at cruise altitude (low temperature). | ||||||
| 126 | SYSTEMS AND METHODS FOR FLIGHT MANAGEMENT | US13547878 | 2012-07-12 | US20140018980A1 | 2014-01-16 | Srinivas Bollapragada; Ana Del Amo |
| Systems and methods for flight management are provided. One flight control system is provided that includes a flight management system configured to manage aircraft flight control including at least one of a flight path or an altitude for an aircraft. The flight control system also includes a flight parameter selection module 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. | ||||||
| 127 | AERODYNAMIC SEALING MEMBER FOR AIRCRAFT | US12349054 | 2009-01-06 | US20090184208A1 | 2009-07-23 | Colin John WEST |
| A sealing member for forming a seal in an aircraft, the sealing member comprising: a sealing material; and a stiffening element which provides structural support to the sealing material and comprises a material with a glass transition temperature below +50° C. The stiffening element is relatively flexible when the aircraft is at low altitude (high temperature) but becomes relatively stiff (increasing resistance to seal flutter) when the aircraft is at cruise altitude (low temperature). | ||||||
| 128 | Process and installation for the distribution of air enriched in oxygen to passengers of an aircraft | US10701528 | 2003-11-06 | US06948498B2 | 2005-09-27 | 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. | ||||||
| 129 | Process and installation for the distribution of air enriched in oxygen to passengers of an aircraft | US10068869 | 2002-02-11 | US20020144679A1 | 2002-10-10 | 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. | ||||||
| 130 | Process and installation for the distribution of air enriched in oxygen to passengers of an aircraft | US10701528 | 2003-11-06 | US20040099271A1 | 2004-05-27 | 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. | ||||||
| 131 | Process and installation for the distribution of air enriched in oxygen to passengers of an aircraft | US10068869 | 2002-02-11 | US06701923B2 | 2004-03-09 | 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. | ||||||
| 132 | Adjustable airplane appendages for wave drag reduction | US924641 | 1978-07-14 | US4256276A | 1981-03-17 | Victor R. Ciminera; Ronald H. Hendrickson |
| Movable appendages or stores containers that are positioned controlled in regard to an airplane so as to approximate the cross-sectional area distribution of a minimum drag body of revolution through varied flight regimes of the airplane from take-off to landing and thereby obtain favorable interaction of pressure fields throughout such flight regimes and adjust the store increment on the locus of least drag points in deference to the teaching of the prior art to design the location and shape of such appendages in a compromise position for but one portion of an airplane's flight regime; i.e., normal cruise altitude and speed. | ||||||
| 133 | SYSTEM ONBOARD AN AIRCRAFT CONNECTED WITH A FLIGHT PLAN | US13015008 | 2011-01-27 | US20110208415A1 | 2011-08-25 | Jean-Claude Mere; Julien Dramet |
| The invention relates to a method and an evaluation system onboard an aircraft connected with a flight plan (13) defining a cruising level and a minimum fuel reserve to destination objective, including: calculating means (5) for calculating a fuel consumption deviation between flight at a selected cruising altitude level (15) and flight at an altitude level initially planned (17) by the flight plan, said selected altitude level (15) being lower than the altitude level initially planned (17), calculating means (5) for determining a climb limit point (19) from said selected cruising altitude level (15) as a function of said fuel consumption deviation and said minimum fuel reserve objective, said climb limit point (19) representing the last climb point respecting said minimum fuel reserve to destination objective, and interface means (9) for providing said climb limit point (19) and anticipative information (21) concerning said climb limit point. | ||||||
| 134 | AERODYNAMIC SEALING MEMBER FOR AIRCRAFT | US14592436 | 2015-01-08 | US20150144741A1 | 2015-05-28 | Colin John WEST |
| A sealing member for forming a seal in an aircraft, the sealing member comprising: a sealing material; and a stiffening element which provides structural support to the sealing material and comprises a material with a glass transition temperature below +50° C. The stiffening element is relatively flexible when the aircraft is at low altitude (high temperature) but becomes relatively stiff (increasing resistance to seal flutter) when the aircraft is at cruise altitude (low temperature). | ||||||
| 135 | Aircraft cabin pressure control for ascents and descents | US768505 | 1991-09-30 | US5186681A | 1993-02-16 | Floyd R. Emmons |
| The rate of change of cabin air pressure in an aircraft cabin during aircraft ascent and descent is controlled as a function of a ratio which is equal to (P.sub.ld -P.sub.c)/(P.sub.ld -P.sub.a) during descent, and is equal to (P.sub.cc -P.sub.c)/(P.sub.cr -P.sub.a) during ascent, where P.sub.ld is ambient pressure at the aircraft landing site, P.sub.c is cabin pressure, P.sub.a is external aircraft ambient pressure, P.sub.cc is cabin pressure at cruise altitude, and P.sub.cr is ambient pressure at cruise altitude. A set point value for the ratio is computed throughout aircraft ascent and descent, and compared to the ratio to schedule a variable flow area of an outflow valve in order to drive the difference (i.e., the error) between the ratio and the desired value for the ratio to zero. By using an adjustable value for the desired set point, control of cabin pressure rate of change is improved during ascent and descent, since the cabin pressure rate of change is maintained at a reduced, linear rate, thereby providing a more comfortable environment for passengers. | ||||||
| 136 | Systems and methods for flight management | JP2013143125 | 2013-07-09 | JP2014019431A | 2014-02-03 | SRINIVAS BOLLAPRAGADA; ANA DEL AMO |
| PROBLEM TO BE SOLVED: To provide flight management systems and methods for managing aircraft flight control including a flight path or an altitude taking into account different weather conditions.SOLUTION: A decision support system 30 may be provided to select parameters for an FMS 32. These parameters may be fixed or dynamically changed during flight. The FMS 32 receives initial and optionally updated parameter information from a flight parameter selection module 34. Weather information and/or flight time information (e.g., departure time, current time, and/or estimated arrival time) are received by the flight parameter selection module 34, and the flight parameter selection module 34 outputs control parameters to the FMS 32. For example, a cost index (CI) value, a cruise altitude and/or a traverse flight path may be set or updated using the flight parameter selection module 34. | ||||||
| 137 | Container having lid welded for fluid food, and its manufacturing method | JP29941299 | 1999-10-21 | JP2001122332A | 2001-05-08 | KINTO TETSUAKI |
| PROBLEM TO BE SOLVED: To provide a container for which a lid welded to an opening thereof can be unsealed without allowing a fluid food housed therein to stain hands or clothes and especially without allowing the fluid food to spill out, even though being used in a space such as a cabin of a passenger plane flying at a cruising altitude where the air pressure is set at a level lower than the earth- side atmospheric pressure. SOLUTION: The container is constructed of a container main body 1, a fluid food 9 filled in the container main body, a welded lid 5 for hermetically closing the container main body 1 with a film-like lid member 6 covering the opening of the container main body welded 7 along a rim 2 of the opening, and an air layer 8 provided at the inside of the container main body 1, being in the state of negative pressure under the atmospheric pressure at a normal temperature, and the air pressure in the air layer 8 is set so as to become the same as or lower than the air pressure in a cabin of a passenger plane flying at a cruising altitude. | ||||||
| 138 | Systems and methods for flight management | EP13175881.5 | 2013-07-10 | EP2685292A2 | 2014-01-15 | 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.
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| 139 | SOLAR HOT-AIR BALLOON | PCT/FR1995001381 | 1995-10-19 | WO1996012642A1 | 1996-05-02 | |
| 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. | ||||||
| 140 | METHOD FOR PROVIDING A WARNING OF RADIATION-DOSE-RELEVANT SPACE-WEATHER EVENTS AT CRUISING ALTITUDES | US14532206 | 2014-11-04 | US20150123004A1 | 2015-05-07 | Matthias Meier; Daniel Matthia |
| The method for providing a warning of radiation-dose-relevant space-weather events at cruising altitudes comprises the steps of detecting radiation data of the atmospheric radiation, particularly of the ionized radiation in the atmosphere, and providing a radiation model for 3D-spatially resolved estimation of a radiation field at cruising altitudes of the earth's atmosphere by use of a radiation dose rate scale based on a continuous range of values. Moreover, the 3D-spatially resolved rates of the effective radiation dose on the basis of the detected radiation data and the radiation model will be estimated. The radiation dose rate scale is divided, based on a continuous range of values, into a discrete, i.e. graduated radiation dose rate scale comprising individual successive ranges of values of increasing radiation dose rates, and respectively one index will be assigned to each range of values, wherein a first range of values is between a radiation dose rate of zero and a presettable first upper limit, a second range of values is between the first upper limit and a second upper limit which is equal to a presettable multiple of the first upper limit, and each further range of values is between the upper limit of the next smaller range of values and an upper limit which is equal to the presettable multiple of the upper limit of the next smaller range of values. As a warning, there is indicated the index of that range of values within which is situated the estimated radiation dose rate for a presettable range in the earth's atmosphere. | ||||||
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