飞机制造商相关的专利数据

序号	专利名	申请号	申请日	公开（公告）号	公开（公告）日	发明人
61	一种航空发电机测试设备	CN202220827671.5	2022-04-08	CN217294931U	2022-08-26	王冠华; 董致臻; 刘国强
本实用新型涉及一种航空发电机测试设备，包括：机架，具有工作台；伺服电机，设于工作台上；增速齿轮箱，设于工作台上，具有动力输入端和动力输出端，该增速齿轮箱的动力输出端用来与待检测的发电机的动力输入轴连接；扭矩传感器，设于工作台上，具有位于同一直线上的第一连接轴和第二连接轴，第一连接轴通过第一联轴器与所述伺服电机的输出轴连接，第二连接轴通过第二联轴器与增速齿轮箱的动力输入端连接；负载箱，与待检测的发电机电连接，用于检测发电机的输出电压以及功率；触控屏，与所述伺服电机、扭矩传感器以及负载箱均电信号连接。通过该测试设备对发电机检测，有效减少了发电机在飞机上不能工作的风险和发动机制造商的售后成本。
62	Integrated system and method for supplying identical parts with multiple certifications	US12069243	2008-02-07	US20080189128A1	2008-08-07	Pete Curti
Methods and computer based systems for supplying the same aircraft part under different part certifications comprises a communication link for accepting part orders from an aircraft manufacturer or a third party. A first computer subsystem is included for determining whether the order came from an aircraft manufacturer or a third party. A second computer subsystem is included for generating certification paperwork and statements for the aircraft manufacturer certification corresponding to a part ordered by said aircraft manufacturer. A third computer subsystem generates certification paperwork and statements for a vendor certification corresponding to a part ordered by said third party.
63	UNIVERSAL EXTENSION BELT	PCT/US2017/028911	2017-04-21	WO2017185015A1	2017-10-26	PRATT SMITH, Lori; GRILLIOT, Ron; BLACK, Barrington; MEIR ARNDT, Stefan
The present invention discloses an apparatus, system, and related method that enables an aircraft operator to use the same extension belt component on an aircraft that has been configured with seats having lap belts from more than one manufacturer.
64	Fuel control apparatus	US12707181	2010-02-17	US08746214B2	2014-06-10	Roger Hall
The invention, described herein, is an improved Fuel Injection Servo (“Servo”) for the homebuilt aircraft. The Servo has been designed to allow the manufacturer to more easily fine tune the pressure differential over the air diaphragm. The Servo also provides an idle valve that the manufacturer and homebuilder can easily fine tune. In a second embodiment, the Servo is further adapted to replace the carburetor in smaller aircraft.
65	FUEL CONTROL APPARATUS	US12707181	2010-02-17	US20110197854A1	2011-08-18	Roger Hall
The invention, described herein, is an improved Fuel Injection Servo (“Servo”) for the homebuilt aircraft. The Servo has been designed to allow the manufacturer to more easily fine tune the pressure deferential over the air diaphragm. The Servo also provides an idle valve that the manufacturer and homebuilder can easily fine tune. In a second embodiment, the Servo is further adapted to replace the carburetor in smaller aircraft.
66	METHODS AND APPARATUS PROVIDING AN E-ENABLED GROUND ARCHITECTURE	PCT/US2007/088084	2007-12-19	WO2008127473A2	2008-10-23	SMALL, Gregory J; MYSORE SRINIVASAMURTHY, Jayanth; GOULD, Kim V; HALL, Lee S
A method for integrating airplane operation related services provided by ground-based systems is described. The method includes receiving information from a plurality of airplane service functions, the airplane service functions including airlines, airplanes, regulatory authorities, maintenance repair organizations, and aircraft manufacturers, the received information relating to airplane operation. The method further includes determining which of the received airplane operation information is applicable to each of the airplane service functions, and distributing the applicable airplane operation information to each of the airplane service functions.
67	Maintenance support equipment for aircraft and component procurement support equipment, and maintenance support system for aircraft	JP2011146100	2011-06-30	JP2013014152A	2013-01-24	ISHIOKA MASATO
PROBLEM TO BE SOLVED: To provide maintenance support equipment for an aircraft, which can shorten an inspection and maintenance time by supporting the inspection and maintenance of the aircraft, component procurement support equipment, and a maintenance support system for the aircraft.SOLUTION: A maintenance management device 2 installed on the side of a customer owning an airframe, and the maintenance support equipment 3 for the aircraft are connected to each other through the Internet. The maintenance support equipment 3 for the aircraft has a quality record database in which conforming article inspection data on the aircraft before delivery, carried by an airframe manufacturer delivering the aircraft, are stored in such a manner as to be associated with airframe identification information. When receiving inspection information, in which airframe inspection data and the airframe identification information are associated with each other, from the maintenance management device 2, the maintenance support equipment for the aircraft extracts the corresponding conforming article inspection data from the quality record database, and provides the maintenance management device 2 with the extracted conforming article inspection data.
68	GRADUATED AIRCRAFT DESIGN AND CONSTRUCTION METHOD	PCT/US1986001324	1986-06-20	WO1987003265A1	1987-06-04	FOX BROTHERS LIMITED PARTNERSHIP
In a design and construction method, for a graduated series of aircraft of various sizes, development costs are minimized by maintaining a consistent scale configuration from model to model, and production costs are minimized through the use of a universal tooling concept for the manufacturing of detail parts, subassemblies and components of the airframes. Each model (M11, M12...M1n) of a series size-graduated elements such as the main wing airfoils (31, 32, 33) is designed with similar characteristics and overlapping dimensions. A common set of tools for constructing these elements is built to accommodate the largest dimensions, such as the root chord (34) of the largest airfoil (31), down to the smallest dimension, such as the tip chord (35) of the smallest airfoil (33). The maintaining of a consistent geometric-scaled relationship between the wing, horizontal and vertical airfoils of the various models for specific manufacturer's size-graduated series of aircraft and the maintenance of the structural bending and torsional stiffness coefficients consistent from model to model provides for consistent flying qualities and performance characteristics assuming that the thrust to weight ratios are also maintained constant from one model to another throughout a specific manufacturer's size-graduated series of aircraft. The universal tooling concept provides for a set of tooling to be used by a specific manufacturer for the making of all of the detail parts and the assembly of these parts, materials and components into completed airframes for each model in a specific manufacturer's size-graduated series of aircraft.
69	GRADUATED AIRCRAFT DESIGN AND CONSTRUCTION METHOD	EP86904540.0	1986-06-20	EP0247063A1	1987-12-02	FOX, William, W.
In a design and construction method, for a graduated series of aircraft of various sizes, development costs are minimized by maintaining a consistent scale configuration from model to model, and production costs are minimized through the use of a universal tooling concept for the manufacturing of detail parts, subassemblies and components of the airframes. Each model (M11, M12...M1n) of a series size-graduated elements such as the main wing airfoils (31, 32, 33) is designed with similar characteristics and overlapping dimensions. A common set of tools for constructing these elements is built to accommodate the largest dimensions, such as the root chord (34) of the largest airfoil (31), down to the smallest dimension, such as the tip chord (35) of the smallest airfoil (33). The maintaining of a consistent geometric-scaled relationship between the wing, horizontal and vertical airfoils of the various models for specific manufacturer's size-graduated series of aircraft and the maintenance of the structural bending and torsional stiffness coefficients consistent from model to model provides for consistent flying qualities and performance characteristics assuming that the thrust to weight ratios are also maintained constant from one model to another throughout a specific manufacturer's size-graduated series of aircraft. The universal tooling concept provides for a set of tooling to be used by a specific manufacturer for the making of all of the detail parts and the assembly of these parts, materials and components into completed airframes for each model in a specific manufacturer's size-graduated series of aircraft.
70	METHODS AND APPARATUS PROVIDING AN E-ENABLED GROUND ARCHITECTURE	US11617903	2006-12-29	US20080162155A1	2008-07-03	Gregory John Small; Jayanth Mysore-Srinivasamurthy; Kim Van Wyck Gould; Lee S. Hall
A method for integrating airplane operation related services provided by ground-based systems is described. The method includes receiving information from a plurality of airplane service functions, the airplane service functions including airlines, airplanes, regulatory authorities, maintenance repair organizations, and aircraft manufacturers, the received information relating to airplane operation. The method further includes determining which of the received airplane operation information is applicable to each of the airplane service functions, and distributing the applicable airplane operation information to each of the airplane service functions.
71	Methods and apparatus providing an E-enabled ground architecture	US11617903	2006-12-29	US08645148B2	2014-02-04	Gregory John Small; Jayanth Mysore Srinivasamurthy; Kim Van Wyck Gould; Lee S. Hall
A method for integrating airplane operation related services provided by ground-based systems is described. The method includes receiving information from a plurality of airplane service functions, the airplane service functions including airlines, airplanes, regulatory authorities, maintenance repair organizations, and aircraft manufacturers, the received information relating to airplane operation. The method further includes determining which of the received airplane operation information is applicable to each of the airplane service functions, and distributing the applicable airplane operation information to each of the airplane service functions.
72	Method for Automated Calculation of the Center of Gravity and the Weight of Aircraft on the Ground	US14549669	2014-11-21	US20160144975A1	2016-05-26	KIRIL LLIEV TOMOV
The method is to be applied by the aircraft manufacturing companies for the purpose of passenger and cargo aircraft design. The result of applying the method by aircraft manufacturers will be to increase the precision of the passenger and cargo weight calculation.Two of the most important characteristics in aircraft design are the Centre of Gravity (CG) and the Total Aircraft Load (G) as they are directly related to its balance, stability and safety in flight. This is why it is mandatory that CG and G are calculated before every take off. The currently used calculations are based on the classic method: multiplying the weights of the passengers and the cargo by the distance to a fixed point in the aircraft, then divided to the total sum of the weights. There are software solutions and charts developed on the basis of the classic method and they are widely used by aircraft producers and airlines. However they are mainly relying on a manual data input. The presented method is based on an alternative approach, allowing for the automated calculation of fluctuations in the CG while the aircraft is being loaded. The same method could also be used to calculate the CG of an empty aircraft.The presented method is based on automated data reception from sensors positioned in specific locations in the aircraft. This information goes directly to the cockpit onboard computer. The calculated CG and G results are then available on a cockpit display.
73	Graduated aircraft design and construction method	US879485	1986-06-27	US4741497A	1988-05-03	William W. Fox
A design and construction method, for a graduated series of aircraft of various sizes, in which development costs are minimized by maintaining a consistent scale configuration from model to model, and production costs are minimized through the use of a universal tooling concept for the manufacturing of detail parts, subsassemblies and components of the airframes. For each model (M11, M12 . . . M1n) of a series size-graduated elements such as the main wing airfoils (31, 32, 33) are designed with similar characteristics and overlapping dimensions. A common set of tools for constructing these elements is built to accommodate the largest dimension, such as the root cord (34) of the largest airfoil (31) down to the smallest dimension, such as the tip cord (35) of the smallest airfoil (33). The maintaining of a consistent geometric-scaled relationship between the wing, horizontal and vertical airfoils of the various models for a specific manufacturer's size-graduated series of aircraft and the maintenance of the structural bending and torsional stiffness coefficients consistent from model to model provides for consistant flying qualities and performance characteristics assuming that the thrust to weight ratios are also maintained constant from one model to another throughout a specific manufacturer's size-graduated series of aircraft. The universal tooling concept provides for a set of tooling to be used by a specific manufacturer for the making of all of the detail parts and the assembly of these parts, materials and components into completed airframes for each model in a specific manufacturer's size-graduated series of aircraft.
74	INTEGRATED FIRE AND FLIGHT CONTROL SYSTEM FOR CONTROLLING THE ANGLE OF ATTACK OF A ROTARY WING AIRCRAFT	PCT/US1999/005113	1999-03-09	WO99050611A1	1999-10-07
An integrated fire and flight control system (10) of the type which controls (200) aircraft flight dynamics to referenced values defined by a weapon launch solution to provide optimum aircraft to target orientation, further optimizes the aircraft's angle of attack (AOA) (47) to the target by controlling the aircraft's vertical speed to modify the aircraft's rate of climb or descent as necessary to produce an actual pitch attitude that is within a range of AOA values corresponding to the range of permissive weapon launch vertical speeds recommended by the weapons manufacturer.
75	항공기 성능의 최적화 방법, 장치, 및 항공기	KR1020130013617	2013-02-06	KR1020130090848A	2013-08-14	에브라트,장-필리프; 코프론,알반
PURPOSE: An apparatus, method and aircraft for optimizing the performance of the aircraft are provided to optimize vehicle performance by health check of a turbine engine in order to maximize power margin. CONSTITUTION: A method for optimizing performance of an aircraft comprises following steps. Each turbine engine (2) comprises a gas generator (2') and a turbine assembly with one or more turbines (2", 2"'), and manufacturers determine the first minimum performance level and the second maximum performance level of an aircraft (1). Current power transferred to each turbo engine (2) is determined during a health check step. Current temperature and rotary speed of gas are measured in the turbine assembly. The first power margin is determined to ensure the first performance level at the current rotary speed. The health check for each turbine engine is performed by determining a second power margin and second minimum power in order to ensure the first performance level.
76	Aircraft part and subassembly damage reporting method, system and mobile computer software application	US14046282	2013-10-04	US09446860B2	2016-09-20	Mudler Alexandre; Barizza Laurent
A preferred method of the invention is executed by code stored on a non-transient medium to control a portable computing device with a touchscreen. The code generates graphical interfaces includes an application that allows a user to capture necessary data for reporting data to permit quick and efficient diagnoses of repairs by a repair service to a part or sub-assembly of an aircraft. The data acquisition is controlled and guided with reference to actual aircraft specifications that are updated by an aircraft part supplier, such as an aircraft manufacturer.
77	AIRCRAFT PART AND SUBASSEMBLY DAMAGE REPORTING METHOD, SYSTEM AND MOBILE COMPUTER SOFTWARE APPLICATION	US14046282	2013-10-04	US20150100201A1	2015-04-09	Mudler Alexandre; Barizza Laurent
A preferred method of the invention is executed by code stored on a non-transient medium to control a portable computing device with a touchscreen. The code generates graphical interfaces includes an application that allows a user to capture necessary data for reporting data to permit quick and efficient diagnoses of repairs by a repair service to a part or sub-assembly of an aircraft. The data acquisition is controlled and guided with reference to actual aircraft specifications that are updated by an aircraft part supplier, such as an aircraft manufacturer.
78	Process for use with aircraft repairs	US493471	1995-06-22	US5828969A	1998-10-27	Lyle James Chamney; Garry Steve Lynchuk
The process provides for improved control of the repair of aircraft damage. The process involves: photographing aircraft damage using a digital camera; inputting the digital visual data and descriptive information into a computer database to produce a record; and electronically transmitting the record into a compatible database at a facility of the manufacturer of the aircraft, so that the recipient may produce the record, visually assess the damage and prepare instructions for the best possible repair according to relevant regulations and send them to the operator. In an additional embodiment, digital photographs and records of a repair are similarly produced and electronically transmitted so that the manufacturer may ensure operator's compliance with the instructions.
79	Integrated fire and flight control system for controlling the angle of attack of a rotary wing aircraft	US52463	1998-03-31	US6145428A	2000-11-14	Phillip J. Gold; Donald L. Fogler, Jr.
An integrated fire and flight control system of the type which controls aircraft flight dynamics to referenced values defined by a weapon launch solution to provide optimum aircraft to target orientation, further optimizes the aircraft's angle of attack (AOA) to the target by controlling the aircraft's vertical speed to modify the aircraft's rate of climb or descent as necessary to produce an actual pitch attitude that is within a range of AOA values corresponding to the range of permissive weapon launch vertical speeds recommended by the weapons manufacturer.
80	DIMENSIONALLY STABLE FABRIC	PCT/US2004043915	2004-12-29	WO2005065369A2	2005-07-21	SCOTT DONALD E
A method of producing a dimensionally stable, fire-resistant fabric including the steps of spinning yarn from wool and fire-resistant synthetic fibers, weaving the yarn to form a fabric, and dimensionally stabilizing the fabric to produce a textile that passes aircraft manufacturer specifications.

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