• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    APPARATUS FOR DETERMINING AIRCRAFT FUEL MILEAGE PERFORMANCE, SYSTEM, METHOD IMPLEMENTED ON COMPUTER AND COMPUTER PROGRAM PRODUCT A computer apparatus and method for determining aircraft fuel mileage performance. Computer apparatus including a memory and a processor arranged in communication with the memory and configured to issue a plurality of instructions stored in memory. The instructions issue signals to receive real-time aircraft data during aircraft flight and process the real-time data to determine real-time aircraft mass data. A calculation is performed to determine real-time fuel mileage performance for the aircraft based on real-time aircraft mass data.
    公开号:BR102013002536B1
    申请号:R102013002536-4
    申请日:2013-02-01
    公开日:2021-08-31
    发明作者:Thomas Horsager；Michael Haukom；William Baumgarte；Matt Hansen；Ken Freeman
    申请人:Rosemount Aerospace Inc.；
    IPC主号:
    专利说明:

    REFERENCE REFERENCE TO RELATED ORDERS
    [001] This application claims priority from US patent application 61/594,761 filed February 3, 2012 which is incorporated herein by reference in its entirety. FIELD OF THE INVENTION
    [002] The present invention relates to a system and method for real-time aircraft performance monitoring, and more particularly, to fuel mileage performance optimization. BACKGROUND OF THE INVENTION
    [003] Fuel usage is one of the major operating costs for the aviation industry and therefore optimizing fuel mileage performance, ie fuel efficiency, is a priority. Fuel efficiency can be increased during the manufacture of new aircraft and includes more efficient engine design, lighter design materials and improved aerodynamics, however, for aircraft that currently exist, increasing fuel efficiency proved difficult.
    [004] Existing aircraft, using conventional techniques to increase fuel efficiency, typically fly in specified flight envelopes that depend on an aircraft's actual gross weight or mass, ambient data, and performance parameters, eg, speed and altitude. Specifically, pilots adjust the aircraft's altitude and cruise speed as mass decreases due to fuel consumption, which in turn optimizes fuel efficiency. Optimal cruising speeds are determined according to cost programs derived from fuel efficiency. Cost programs have a cost index that is calculated by the airlines, and balance time and fuel costs. For example, as fuel costs increase, the cost index decreases and results in lower optimal cruising speeds, that is, slower.
    [005] However, conventional techniques that calculate fuel mileage performance are often inaccurate due to inaccurate calculations of mass variations and assumptions of environmental data. For example, flight crews typically derive a preflight mass for an aircraft from combinations of estimated and effective mass. This pre-flight mass is input into a flight computer that adjusts the flight profile according to pre-programmed algorithms, which can account for weight variations due to in-flight fuel consumption. However, these pre-programmed algorithms are based on statistical models that often result in variances between calculated and actual conditions, including environmental and mass conditions.
    [006] Other conventional techniques that attempt to calculate fuel mileage performance occur post-flight. For example, some airlines manually track fuel consumed at the end of each flight. However, this approach fails to aid in-flight fuel efficiency optimization as it only measures post-flight fuel mileage performance.
    [007] Evidently, there is a need in the art for improved systems and methods that increase fuel efficiency for aircraft, through real-time aircraft performance monitoring. In addition, there is a need to more accurately determine mass using real-time aircraft performance monitoring, which in turn increases fuel mileage performance, eg fuel efficiency. Still additionally, there is a need to more accurately monitor other factors, in real time, that affect fuel mileage performance, eg environmental conditions. SUMMARY OF THE INVENTION
    [008] The purpose and advantages of the invention will be set forth in and evident from the description that follows. Additional advantages of the invention will be realized and obtained by the apparatus, systems and methods indicated in the written description and claims herein, as well as from the accompanying drawings.
    [009] To obtain these and other advantages and in accordance with the purpose of the invention, as incorporated, the invention includes, in one aspect, a computer apparatus and method for determining aircraft fuel mileage performance in which an aspect of the invention includes receiving real-time aircraft data during aircraft flight and processing the real-time data to determine real-time aircraft mass data. A calculation is performed to determine real-time fuel mileage performance for the aircraft based on real-time aircraft mass data.
    [010] Additional aspects of the invention include transmitting a warning signal that indicates degradation of fuel mileage performance when the fuel mileage performance falls below a predetermined threshold. Another aspect includes adjusting the aircraft's altitude and cruise speed based on calculated real-time fuel mileage performance. Other aspects include storing fuel mileage performance as a record in a database having previously stored records and calculating a performance trend for fuel mileage performance based on the record and at least one of the previously stored records. Additional aspects include determining a fuel mileage performance degradation in accordance with the calculated performance trend and performing maintenance on the aircraft when the fuel mileage performance degradation falls below a predetermined threshold. BRIEF DESCRIPTION OF THE DRAWINGS
    [011] In order that those with common knowledge in the art, to which the present invention relates, more fully understand how to employ the novel system and methods of the present invention, the embodiments thereof will be described in detail below with reference to the drawings, in what:
    [012] Figure 1 is a system diagram for performing real-time aircraft performance monitoring methods; and
    [013] Figure 2 is a block diagram according to an illustrated embodiment. DETAILED DESCRIPTION OF CERTAIN MODALITIES
    [014] The present invention is now more fully described with reference to the accompanying drawings, in which an illustrated embodiment of the present invention is shown. The present invention is in no way limited to the illustrated embodiment as the illustrated embodiment described below is merely exemplary of the invention, which may be embodied in various forms as recognized by a person skilled in the art. Therefore, it is to be understood that any structural and functional details disclosed herein are not to be construed as limiting, but merely as a basis for the claims and as representative of teaching a person skilled in the art to variously employ the present invention. Furthermore, the terms and phrases used herein are not intended to be limiting but rather to provide an understandable description of the invention.
    [015] Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by a person of ordinary skill in the art to which this invention belongs. While any methods and materials similar or equivalent to those described herein may also be used in the practice or testing of the present invention, exemplary methods and materials are now described. All publications mentioned herein are hereby incorporated by reference to disclose and describe the methods and/or materials with respect to which the publications are cited.
    [016] It should be noted that as used herein and in the appended claims, the singular forms "a", "an" and "o, a" include several referents unless the context clearly dictates otherwise. Thus, for example, reference to "a stimulus" includes a plurality of such stimuli and reference to "the signal" includes reference to one or more signs and equivalents thereof known to those skilled in the art, and so on.
    [017] The publications discussed herein are provided solely for your disclosure prior to the filing date of this application. Nothing herein should be construed as an admission that the present invention is not entitled to predate such publication by virtue of a prior invention. In addition, the publication dates provided may differ from the actual publication dates which may need to be independently confirmed.
    [018] It should be recognized that embodiments of the present invention as discussed below are preferably a software algorithm, program or code that resides on computer usable media having control logic to allow execution on a machine having a computer processor. The machine typically includes memory storage configured to provide program execution output or computer algorithm.
    [019] As used herein, the term "software" is intended to be synonymous with any code or program that may be on a host computer processor, regardless of whether the implementation is in hardware, firmware or as an available computer software product on a disk, a memory storage device, or for downloading from a remote machine. The modalities described here include such software for implementing the equations, relations and algorithms described above. A person skilled in the art will recognize additional aspects and advantages of the invention based on the above-described embodiments. Therefore, the invention is not to be limited by what has been particularly shown and described, except as indicated by the appended claims. All publications and references cited herein are expressly incorporated herein by reference in their entirety.
    [020] With reference to the modalities illustrated below, the present invention is directed to systems and methods for real-time aircraft performance monitoring. More particularly, the present invention is directed to determining a real-time aircraft mass and determining performance parameters based on real-time aircraft mass.
    [021] Real-time aircraft performance monitoring allows pilots to make more accurate and effective decisions that maximize aircraft performance and optimize an aircraft's flight profile. These decisions include adjusting the altitude and cruising speed of an aircraft. For example, an autopilot system or a pilot can initiate a step climb to a higher altitude for improved fuel mileage performance based on a real-time mass that accounts for weight decreases due to burning fuel with the passing time. In addition, the aircraft's cruise speed can be adjusted according to more accurate costing programs that are derived in part from real-time mass calculations. Cost programs can be additionally derived from real-time evaluation of fuel mileage performance factors.
    [022] With reference to the figures, and in particular to figure 1, a diagram of a system, i.e. system 100, for real-time aircraft performance monitoring is provided. System 100 preferably includes a computer 105 coupled to a network 130, for example, aircraft digital buses and/or aircraft radio networks. Computer 105 preferably includes a user interface 110, a processor 115, and a memory 120. Although computer 105 is represented herein as a stand-alone device, it is not limited thereto, but rather can be coupled to other devices (not shown). ) in a distributed processing system.
    [023] The user interface 110 preferably includes an input device, such as a keyboard, a touch screen or a speech recognition subsystem, that allows the pilot to communicate information and command selections to the processor 115. The interface User 110 also includes an output device such as a display, eg a heads up display or a multi-function display. User interface 110 may further include an input device such as a mouse, TrackBall, or joystick, which allows the pilot to manipulate the display to communicate additional information and command selections to processor 115.
    [024] Processor 115 is preferably an electronic device configured with logical circuitry that responds to and executes instructions. Memory 120 is preferably computer readable media encoded with a computer program. In this regard, memory 120 stores data and instructions that are readable and executable by processor 115 to control the operation of processor 115. Memory 120 can be implemented in a random access memory (RAM), a hard drive, a memory only. (ROM), or a combination thereof. One of the memory components 120 is a program module 125.
    [025] Program module 125 contains instructions for controlling processor 115 to execute the methods described here. For example, under the control of program module 125, processor 115 executes the processes described for the EFB processor above. It should be recognized that the term "module" is used herein to indicate a functional operation that can be incorporated as an independent component or as an integrated configuration of a plurality of subordinate components. Thereby, the program module 125 can be implemented as a single module or as a plurality of modules that operate in cooperation with each other. further, although program module 125 is described herein as being installed in memory 120, and therefore being implemented in software, it could be implemented in any of hardware (e.g., electronic circuitry), firmware, software, or a combination of the same.
    [026] The processor 115 transmits, to the user interface 110, a result of an execution of the methods described here. Alternatively, processor 115 could direct output to a remote device (not shown), for example, refer to a flight operations center 225 in Figure 2, via network 130. It should also be recognized that although the program module 125 is indicated as already loaded into memory 120, may be configured on storage medium 135 for subsequent loading into memory 120. Storage medium 135 is also computer readable media encoded with a computer program, and may be any medium. conventional storage that stores program module 125 therein in tangible form. Examples of storage media 135 include a floppy disk, a compact disk, a magnetic tape, a read-only memory, an optical storage media, universal serial bus (USB) flash drive, a solid state storage (SSD), a compact flash card, or a digital versatile disc. Alternatively, storage medium 135 may be random access memory, or other type of electronic storage, located in a remote storage system and coupled to computer 105 via network 130.
    [027] It should be further recognized that although the systems and methods described here can be implemented in software, they can be implemented in any hardware (eg, electronic circuitry), firmware, software, or a combination thereof.
    [028] In the illustrated modalities, a method for real-time aircraft performance is provided. In particular, the method includes the steps of receiving real-time data from an aircraft having in-flight sensors of the aircraft, processing the real-time data to calculate mass data, and calculating a fuel mileage performance based on the mass data. . It should be understood that real-time data encompasses any data relating to an aircraft's attributes and performance at a given measurement time. For example, real-time data includes (and is not limited to): aircraft loaded weight, thrust, drag, elevation, speed, altitude, and atmospheric conditions in which the aircraft is traveling.
    [029] The method may further include transmitting an alert that indicates degradation of fuel mileage performance, transmitting fuel mileage performance to an aircraft cabin, and automatic adjustment of aircraft altitude and cruise speed based on performance of measured fuel mileage, for example, when a performance threshold fuel mileage is exceeded.
    [030] In some embodiments, the method includes storing fuel mileage performance as a record in a database having previously stored records, and calculating a performance trend based on the record and at least one of the previously stored records. Figure 2 illustrates a system diagram, ie, system diagram 200, for real-time aircraft performance monitoring. Typically, system 200 employs all or part of system 100 in accordance with the present invention.
    [031] System 200 includes aircraft digital data buses 205, an aircraft interface device 210, a cockpit display 215, an aircraft radio 220, and a flight operations center 225. The aircraft digital buses 205 relay sensor data in real time to aircraft interface device 210. Aircraft interface device 210 is preferably part of an electronic flight bag (EFB) system. Aircraft interface device 210 receives and processes sensor data in real time and provides processed data relating to aircraft performance. Subsequently, the aircraft interface device typically transmits the processed data to the cockpit display 215 (which may also be part of the EFB system), aircraft radio(s), for example, ACARS and broadband, and aircraft operations center. flight 225, for example, ground stations, via aircraft radios.
    [032] Preferably, the EFB includes a processor, and a memory having instructions that are executable by the processor, for example, processor 115. For example, the instructions, when read by the processor can cause the processor to receive data in real time during aircraft flight, and process the data in real time to calculate fuel mileage performance factors as aircraft mass data. The processor can further communicate with, and receive real-time data from, various aircraft sensors, e.g., inertial sensors, pitot sensors, and position sensors, via aircraft digital data buses 205. In addition, the processor can calculate a fuel mileage performance based on the mass data, and transmit an indication of that fuel mileage performance from the EFB, eg aircraft interface device 210, to cockpit display 215, aircraft radio 220, or flight operations center 225 (via aircraft radio 220). Additionally, the aircraft, in response to fuel mileage performance, can adjust an altitude or a cruise speed by manual pilot input or autopilot controls. Also, in some modalities, the processor communicates with a database. The processor stores fuel mileage data in a database record. Through a compilation of stored records, the processor generates performance trend data. Still additionally, the processor generates and transmits an alert that indicates degraded fuel mileage performance. This alert can be transmitted to cockpit display 215, aircraft radio 220 or flight operations center 225.
    [033] The present invention facilitates aircraft fuel efficiency maximization through real-time data. Maximizing fuel efficiency translates into a cost reduction. In addition, calculating and tracking aircraft performance trends facilitates advanced monitoring of an aircraft's condition and can provide an indication of required maintenance.
    [034] The techniques described herein are exemplary, and should not be construed as indicating any specific limitation on the present disclosure. It should be understood that various alternatives, combinations and modifications can be devised by those skilled in the art. For example, steps associated with the processes described here can be performed in any order unless otherwise specified or determined by the steps themselves.
    [035] The present disclosure is intended to cover all such alternatives, modifications and variances that fall within the scope of the appended claims. While the systems and methods of the present invention have been described with respect to the embodiments disclosed above, those skilled in the art will readily recognize that changes and modifications can be made thereto without departing from the spirit and scope of the present invention as defined by the appended claims.
    权利要求:
    Claims (13)
    [0001]
    1. SYSTEM FOR CONTROLLING AN AIRCRAFT, comprising: a memory (120); an electronic flight packet processor (115) communicated with said memory, said memory having instructions stored therein which, when read by said processor, cause the processor (115) to: receive, at said packet processor. electronic flight, real-time aircraft data by aircraft sensors in communication with said electronic flight packet processor during aircraft flight; characterized in that instructions stored in memory (120) when read by said processor further cause processor (115) to: process, by said electronic flight packet processor, said data in real time to determine mass data of the aircraft in real time; calculate, by said electronic packet processor, a real-time fuel mileage performance for the aircraft based on determined aircraft mass data, automatically adjust, by means of an aircraft autopilot control in communication with said processor of electronic flight package, at least one of an aircraft altitude and cruise speed based on calculated real-time fuel mileage performance; determine the degradation of fuel mileage performance, according to a trend in calculated real-time fuel mileage performance; and service the aircraft when fuel mileage performance degradation drops below a predetermined threshold.
    [0002]
    2. SYSTEM according to claim 1, characterized in that it further comprises aircraft sensors that transmit data in real time to said processor.
    [0003]
    3. SYSTEM according to claim 1, characterized in that said real-time data are selected from a group consisting of: drag, survey, speed and altitude.
    [0004]
    A SYSTEM according to claim 3, characterized in that said instructions stored in memory (120) further cause said processor to transmit an alert signal indicating the degradation of a fuel mileage performance.
    [0005]
    The system of claim 3, characterized in that said instructions stored in memory (120) further cause said processor (115) to transmit said fuel mileage performance to the cockpit of an aircraft.
    [0006]
    6. SYSTEM according to claim 3, characterized in that said aircraft adjusts both said altitude and said cruise speed based on said fuel mileage.
    [0007]
    The SYSTEM of claim 3, wherein said processor (115) calculates said fuel mileage performance based on said aircraft mass data, wherein said system is further comprising: a base of data having records, and wherein said memory further causes said processor to store said fuel mileage performance data as a record of said records in said database, and compare at least said one record with at least minus one previously stored record to produce performance trending data.
    [0008]
    8. The system of claim 1, characterized in that said instructions stored in memory (120) further cause said processor to calculate a fuel mileage performance based on said mass data and at least one group parameter of parameters consisting of: an environmental parameter and a performance parameter, and where the performance parameter includes speed data, altitude data, temperature data, pressure data, and angle of attack data.
    [0009]
    9. SYSTEM according to claim 6, characterized in that said instructions further cause the processor to obtain a cost schedule using real-time mass determination; and adjust aircraft altitude and cruise speed based on cost schedules.
    [0010]
    10. COMPUTER IMPLEMENTED METHOD, comprising: receiving, in an electronic flight packet processor (115), real-time data by aircraft sensors during aircraft flight; processing, by said electronic flight packet processor, said real-time data to determine real-time aircraft mass data; characterized by further comprising: calculating, by said electronic flight packet processor, the real-time fuel mileage performance of the aircraft based on said determined aircraft mass data; automatically adjust, through an aircraft autopilot control, at least one of an aircraft's altitude and cruise speed based on calculated real-time fuel mileage performance; storing said fuel mileage performance as a record in a database having previously stored records: calculating a performance trend for said fuel mileage performance based on the record and at least one of the previously stored records; determine a fuel mileage performance degradation in accordance with the calculated performance trend; and perform aircraft maintenance when fuel mileage performance degradation falls below a predetermined threshold.
    [0011]
    11. The method according to claim 10, further comprising transmitting an alert signal indicating the degradation of said fuel mileage performance when said fuel mileage performance is below a predetermined threshold.
    [0012]
    12. The method according to claim 10, further comprising transmitting a signal indicative of said fuel mileage performance to the cockpit of an aircraft.
    [0013]
    13. The method of claim 10, further comprising adjusting an altitude and cruising speed of said aircraft based on said calculated real-time fuel mileage performance.
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    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US2968031A|1955-02-24|1961-01-10|North American Aviation Inc|Electronic micrometer|
    US3783496A|1968-12-19|1974-01-08|J Siler|Method of assembling members having misaligned holes|
    US4110605A|1977-02-25|1978-08-29|Sperry Rand Corporation|Weight and balance computer apparatus for aircraft|
    US4277041A|1978-09-11|1981-07-07|Lockheed Corporation|Aircraft cruise speed control system|
    US4269070A|1979-09-28|1981-05-26|Weico Corporation|Strain/deflection sensitive variable reluctance transducer assembly|
    US4312042A|1979-12-12|1982-01-19|Sundstrand Data Control, Inc.|Weight, balance, and tire pressure detection systems|
    US4480480A|1981-05-18|1984-11-06|Scott Science & Technology, Inc.|System for assessing the integrity of structural systems|
    DE3273648D1|1981-08-14|1986-11-13|Atomic Energy Authority Uk|Extensometers|
    US4494210A|1981-12-21|1985-01-15|Sperry Corporation|Enroute weight computer for aircraft|
    DE3239877A1|1982-10-27|1984-05-03|Interatom Internationale Atomreaktorbau Gmbh, 5060 Bergisch Gladbach|Device for strain measurement|
    FR2545170B1|1983-04-29|1986-02-21|Sfena|METHOD FOR PRODUCING ELEMENT SUPPORT BEARING RING FOR HOLLOW OR FULL CYLINDRICAL PARTS AND BEARING RING THUS OBTAINED|
    US4590475A|1983-10-24|1986-05-20|The United States Of America As Represented By The Secretary Of The Army|Stall avoidance system for aircraft|
    JPH01503530A|1987-04-29|1989-11-30|
    SU1469339A1|1987-09-09|1989-03-30|Сибирский государственный научно-исследовательский институт метрологии|Capacitive transducer of movements with variable interelectrode gap|
    IT1224034B|1988-12-23|1990-09-26|Marelli Autronica|CAPACITIVE DEFORMATION SENSOR|
    US5358637A|1989-02-18|1994-10-25|Herman Finckh Maschinenfabrik Gmbh & Co.|Apparatus for sorting and deflaking fibrous suspensions|
    FR2645259B1|1989-04-04|1994-02-11|Thomson Csf|CAPACITIVE SENSOR FOR DISPLACEMENTS AND TORSION ANGLE SENSOR COMPRISING AT LEAST ONE SUCH CAPACITIVE SENSOR|
    DE4035197A1|1990-07-07|1992-01-09|Vdo Schindling|Inductive force sensor mounted on aircraft landing gear - has two mounting elements, one carrying measurement tongue between them, on carrying sensor coils, produces high useful signal level|
    DE4112675A1|1990-10-20|1992-04-23|Vdo Schindling|ARRANGEMENT OF AT LEAST ONE SENSOR ON THE UNDERCARRIAGE OF AN AIRPLANE FOR MEASURING ITS WEIGHT AND FOCUS|
    CA2113619A1|1992-05-22|1993-12-09|Michael John Arnold|Closure default indicator|
    US5314115A|1992-05-27|1994-05-24|Bombardier Inc.|Rail cross-tie for LIM transit system|
    JP3144173B2|1993-08-26|2001-03-12|株式会社明電舎|Vehicle drive system test equipment|
    ES2115382T5|1994-05-14|2004-12-01|Synaptics Limited|POSITION CODING|
    US5446666A|1994-05-17|1995-08-29|The Boeing Company|Ground state-fly state transition control for unique-trim aircraft flight control system|
    US6691004B2|1995-07-31|2004-02-10|Honeywell International, Inc.|Method for determining a currently obtainable climb gradient of an aircraft|
    US5955972A|1995-09-26|1999-09-21|William G. Wade|Gear position indicator|
    US6354152B1|1996-05-08|2002-03-12|Edward Charles Herlik|Method and system to measure dynamic loads or stresses in aircraft, machines, and structures|
    FR2772342B1|1997-12-16|2000-02-18|Aerospatiale|PROPELLER ASSEMBLY WITH BLOWER HOODS PROVIDED WITH HOLDING AND POSITIONING SAFETY DEVICES FOR AIRCRAFT|
    US6289289B1|1998-12-10|2001-09-11|Honeywell International Inc.|Aircraft structural fatigue monitor|
    FR2787587B1|1998-12-18|2001-10-05|Sextant Avionique|PROCESS FOR THE REAL-TIME DEVELOPMENT OF TRAJECTORIES FOR AN AIRCRAFT|
    US6134500A|1999-06-03|2000-10-17|United Air Lines, Inc.|System and method for generating optimal flight plans for airline operations control|
    DE10023196C2|2000-05-11|2003-04-03|Orenstein & Koppel Ag|Device for detecting the angle of rotation between two components|
    AU7858201A|2000-08-04|2002-02-18|Dunlop Aerospace Ltd|Brake condition monitoring|
    US6865690B2|2001-06-21|2005-03-08|Northrop Grumman Corporation|Voltage conditioner with embedded battery backup|
    US6676075B2|2001-08-30|2004-01-13|The Boeing Company|Airplane hard landing indication system|
    US20030176954A1|2001-10-12|2003-09-18|Jaw Link C.|Tracking and control of gas turbine engine component damage/life|
    GB0126014D0|2001-10-30|2001-12-19|Sensopad Technologies Ltd|Modulated field position sensor|
    US6745153B2|2001-11-27|2004-06-01|General Motors Corporation|Data collection and manipulation apparatus and method|
    GB2387912A|2002-04-26|2003-10-29|Messier Dowty Inc|Monitoring parameters in structural components|
    US7131672B2|2002-05-03|2006-11-07|Hartwell Corporation|Latch mechanism|
    US6807853B2|2002-05-10|2004-10-26|Michelin Recherche Et Technique S.A.|System and method for generating electric power from a rotating tire's mechanical energy using piezoelectric fiber composites|
    AU2003260831C1|2002-07-31|2010-01-14|Sap Ag|Tagging with maintenance related information|
    WO2004028902A1|2002-09-25|2004-04-08|Goodrich Corporation|Aircraft shock strut having a fluid level monitor|
    US7490793B2|2002-10-18|2009-02-17|The Boeing Company|Wireless landing gear monitoring system|
    US6909985B2|2002-11-27|2005-06-21|Lockheed Martin Corporation|Method and apparatus for recording changes associated with acceleration of a structure|
    GB2414809A|2003-01-23|2005-12-07|Jentek Sensors Inc|Damage tolerance using adaptive model-based methods|
    US6951145B2|2003-03-24|2005-10-04|Siemens Vdo Automotive Corporation|Non-contact thrust force sensor assembly|
    US6880784B1|2003-05-08|2005-04-19|Supersonic Aerospace International, Llc|Automatic takeoff thrust management system|
    US7031811B2|2003-05-30|2006-04-18|The Boeing Company|Fuel efficient airspeed trim|
    US7578199B2|2003-08-27|2009-08-25|Airbus Uk Limited|Apparatus and method suitable for measuring the displacement or load on an aircraft component|
    US7252311B2|2003-09-17|2007-08-07|Hartwell Corporation|Motor driven latch|
    US20060004499A1|2004-06-30|2006-01-05|Angela Trego|Structural health management architecture using sensor technology|
    US7702427B1|2004-07-30|2010-04-20|The United States Of America As Represented By The National Aeronautics And Space Administration |Air traffic management evaluation tool|
    CA2487704A1|2004-11-18|2006-05-18|R. Kyle Schmidt|Method and system for health monitoring of aircraft landing gear|
    GB0428378D0|2004-12-24|2005-02-02|Airbus Uk Ltd|Apparatus and method for measuring loads sustained by a bearing pin|
    US7274310B1|2005-03-29|2007-09-25|Nance C Kirk|Aircraft landing gear kinetic energy monitor|
    CA2509742A1|2005-06-10|2006-12-10|Messier-Dowty Inc.|System and method for determining aircraft hard landing events from inertial and aircraft reference frame data|
    US7606641B2|2005-08-04|2009-10-20|The Boeing Company|Fuel consumption data tracking/collection and aircraft/route optimization|
    US7874521B2|2005-10-17|2011-01-25|Hoshiko Llc|Method and system for aviation navigation|
    US20070150123A1|2005-12-08|2007-06-28|The Boeing Company|System and method for controlling the airspeed of an aircraft|
    EP1839984B1|2006-03-29|2016-02-24|Meggitt SA|Power measurement device for vehicle chassis|
    US7843363B2|2007-07-12|2010-11-30|Rosemount Aerospace Inc.|Mechanical latch locking detection sensors|
    US20090173823A1|2008-01-07|2009-07-09|Rohr, Inc.|Method and component for determining load on a latch assembly|
    DE102008048275B4|2008-09-22|2014-07-24|Airbus Operations Gmbh|Fuel management system|
    US8838298B2|2008-09-25|2014-09-16|The Boeing Company|Methods and systems for active wing and lift surface control using integrated aeroelasticity measurements|
    US8935174B2|2009-01-16|2015-01-13|The Boeing Company|Analyzing voyage efficiencies|
    US9330573B2|2009-06-25|2016-05-03|Honeywell International Inc.|Automated decision aid tool for prompting a pilot to request a flight level change|
    CN101989363B|2009-07-30|2014-07-16|中国商用飞机有限责任公司|System and method for processing digital air data|
    CN101881969B|2009-09-03|2012-03-14|中国航空无线电电子研究所|Flight management system and method thereof based on multi-task parallel processing|
    CN101692315B|2009-09-25|2011-08-10|民航总局空管局技术中心|Method for analyzing high precision 4D flight trajectory of airplane based on real-time radar data|
    US20110118908A1|2009-11-18|2011-05-19|The Boeing Company|Methods and systems for management of airplane speed profile|
    CN201726066U|2010-05-25|2011-01-26|广州科易光电技术有限公司|Hardware structure of airborne system of power line patrol-inspection helicopter|
    US8286508B2|2010-07-19|2012-10-16|Goodrich Corporation|Systems and methods for measuring angular motion|
    US8359932B2|2010-07-19|2013-01-29|Goodrich Corporation|Systems and methods for mounting landing gear strain sensors|
    US8627727B2|2010-07-19|2014-01-14|United Technologies Corporation|Sensor for measuring large mechanical strains with fine adjustment device|
    CN102741884B|2010-07-27|2016-06-08|松下知识产权经营株式会社|Moving body detecting device and moving body detection method|
    CN101923739B|2010-08-19|2012-09-05|北京航空航天大学|Integrated display system for aircraft engine parameters and air service information and construction method thereof|
    US20120078450A1|2010-09-27|2012-03-29|Honeywell International Inc.|Display information to support climb optimization during cruise|
    US9567097B2|2012-02-03|2017-02-14|Rosemount Aerospace Inc.|System and method for real-time aircraft performance monitoring|
    US8509968B1|2012-03-20|2013-08-13|The Boeing Company|System and method for real-time aircraft efficiency analysis and compilation|
    US20120218127A1|2012-05-10|2012-08-30|Christopher Finley Kroen|Terminal Intelligent Monitoring System|
    US10665114B2|2014-03-28|2020-05-26|The Boeing Company|Aircraft fuel optimization analytics|
    US9811950B2|2014-09-18|2017-11-07|Honeywell International Inc.|Aircraft electric taxi system diagnostic and prognostic evaluation system and method|US8768607B2|2010-09-21|2014-07-01|The Boeing Company|Managing fuel in aircraft|
    US9432611B1|2011-09-29|2016-08-30|Rockwell Collins, Inc.|Voice radio tuning|
    US9567097B2|2012-02-03|2017-02-14|Rosemount Aerospace Inc.|System and method for real-time aircraft performance monitoring|
    US10502584B1|2012-12-28|2019-12-10|Sean Patrick Suiter|Mission monitor and controller for autonomous unmanned vehicles|
    US9037320B1|2014-01-29|2015-05-19|The Boeing Company|Unscheduled maintenance disruption severity and flight decision system and method|
    US20150269861A1|2014-03-24|2015-09-24|Rebecca Rose Shaw|System and Method for Using Pilot Controllable Discretionary Operational Parameters to Reduce Fuel Consumption in Piloted Aircraft|
    US10339828B2|2014-03-24|2019-07-02|Steven E. Shaw|Operator training and maneuver refinement system for powered aircraft|
    CN103995874A|2014-05-22|2014-08-20|北京航空航天大学|EFB system based on Windows modern UI|
    US9665345B2|2014-07-29|2017-05-30|Honeywell International Inc.|Flight deck multifunction control display unit with voice commands|
    US9922651B1|2014-08-13|2018-03-20|Rockwell Collins, Inc.|Avionics text entry, cursor control, and display format selection via voice recognition|
    US9916701B2|2014-09-10|2018-03-13|The Boeing Company|Vehicle auditing and control of maintenance and diagnosis for vehicle systems|
    US10553120B2|2014-09-15|2020-02-04|L3 Technologies, Inc.|Fail safe aircraft monitoring and tracking|
    EP3065020B1|2015-03-04|2017-10-18|The Boeing Company|Method for calculating the optimum economy cruise speed in an aircraft|
    EP3065019B1|2015-03-04|2017-09-13|The Boeing Company|Method for optimum maximum range cruise speed in an aircraft|
    CN104986347B|2015-06-03|2017-02-22|中国民航大学|Real-time detection method for civil aircraft airline pilot operation errors|
    US9745052B2|2015-10-30|2017-08-29|Ge Aviation Systems Llc|Determining enhanced operating state for aircraft|
    US9911339B2|2015-11-05|2018-03-06|Ge Aviation Systems Llc|Experimental real-time performance enhancement for aircraft|
    CN105371895B|2015-11-25|2017-12-08|中山市厚源电子科技有限公司|A kind of audible alarm system for space shuttle based on Internet of Things|
    WO2017162197A1|2016-03-23|2017-09-28|冯春魁|Aircraft data acquisition, processing and flight status monitoring method and system|
    US10297162B2|2016-12-28|2019-05-21|Honeywell International Inc.|System and method to activate avionics functions remotely|
    US10991255B2|2018-04-05|2021-04-27|Ge Aviation Systems Llc|Providing an open interface to a flight management system|
    US11042150B2|2018-04-17|2021-06-22|Massachusetts Institute Of Technology|Aircraft fuel efficiency tunnel display for pilots and dispatchers|
    US11176832B2|2019-04-25|2021-11-16|Honeywell International Inc.|Systems and methods to integrate real-time internet-connected aircraft data for cargo planning|
    CN110503349A|2019-09-10|2019-11-26|深圳市瑞达飞行科技有限公司|Processing method, processing unit and the electronic equipment of flight fuel consumption data|
    CN111696389B|2020-05-29|2021-07-02|航科院中宇（北京）新技术发展有限公司|Aircraft fuel estimation method and system based on flight plan|
    CN111785095B|2020-07-31|2021-06-01|北京航空航天大学|Method for forming monitoring performance evaluation index|
    法律状态:
    2015-06-30| B03A| Publication of a patent application or of a certificate of addition of invention [chapter 3.1 patent gazette]|
    2018-12-04| B06F| Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette]|
    2019-11-12| B06U| Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 patent gazette]|
    2021-02-17| B06A| Patent application procedure suspended [chapter 6.1 patent gazette]|
    2021-05-11| B06A| Patent application procedure suspended [chapter 6.1 patent gazette]|
    2021-05-25| B06I| Publication of requirement cancelled [chapter 6.9 patent gazette]|Free format text: ANULADA A PUBLICACAO CODIGO 6.1 NA RPI NO 2627 DE 11/05/2021 POR TER SIDO INDEVIDA. |
    2021-05-25| B09A| Decision: intention to grant [chapter 9.1 patent gazette]|
    2021-08-24| B09X| Republication of the decision to grant [chapter 9.1.3 patent gazette]|
    2021-08-31| B16A| Patent or certificate of addition of invention granted [chapter 16.1 patent gazette]|Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 01/02/2013, OBSERVADAS AS CONDICOES LEGAIS. |
    优先权:
    申请号 | 申请日 | 专利标题
    US201261594761P| true| 2012-02-03|2012-02-03|
    US61/594,761|2012-02-03|
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