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Небесная энциклопедия

Космические корабли и станции, автоматические КА и методы их проектирования, бортовые комплексы управления, системы и средства жизнеобеспечения, особенности технологии производства ракетно-космических систем

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Мониторинг СМИ

Мониторинг СМИ и социальных сетей. Сканирование интернета, новостных сайтов, специализированных контентных площадок на базе мессенджеров. Гибкие настройки фильтров и первоначальных источников.

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16-03-2020 дата публикации

Фюзеляж беспилотного летательного аппарата, включающий основной отсек и отделяемый

Номер: RU0000196780U1
Автор: Антон Игоревич Иванченко, Валерий Анатольевич Щеглов, Владимир Васильевич Обрезчиков, Владимир Данилович Матрусов, Николай Анатольевич Птуха
Принадлежит: Акционерное Общество "Государственное Машиностроительное Конструкторское Бюро "Радуга" Имени А.Я. Березняка"

Фюзеляж беспилотного летательного аппарата, включающий основной отсек и отделяемый, может найти применение в авиационной технике для беспилотных летательных аппаратов (далее - БПЛА) с разгонными и отделяемыми отсеками и многоступенчатых ракет. Устройство состоит из корпуса с электродетонатором, основного отсека и отделяемого отсека БПЛА и пластины с набором тупиковых полостей, например набором концентрических канавок, закрепленной на основном отсеке. Предлагаемым устройством решается задача снижения виброударных ускорений при срабатывании электродетонаторов для разделения отсеков БПЛА. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 196 780 U1 (51) МПК B64F 5/00 (2006.01) B64G 1/64 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ПОЛЕЗНОЙ МОДЕЛИ К ПАТЕНТУ (52) СПК B64G 1/64 (2019.08); B64F 5/00 (2019.08) (21)(22) Заявка: 2019126160, 20.08.2019 (24) Дата начала отсчета срока действия патента: Дата регистрации: 16.03.2020 (45) Опубликовано: 16.03.2020 Бюл. № 8 (54) Фюзеляж беспилотного летательного аппарата, включающий основной отсек и отделяемый (57) Реферат: Фюзеляж беспилотного летательного и отделяемого отсека БПЛА и пластины с аппарата, включающий основной отсек и набором тупиковых полостей, например набором отделяемый, может найти применение в концентрических канавок, закрепленной на авиационной технике для беспилотных основном отсеке. Предлагаемым устройством летательных аппаратов (далее - БПЛА) с решается задача снижения виброударных разгонными и отделяемыми отсеками и ускорений при срабатывании электродетонаторов многоступенчатых ракет. Устройство состоит из для разделения отсеков БПЛА. корпуса с электродетонатором, основного отсека R U 1 9 6 7 8 0 (56) Список документов, цитированных в отчете о поиске: RU 2064655 С1, 27.07.1996. SU 254657 A1, 17.10.1969. RU 94030247 A1, 20.06.1996. US 4869170 A1, 26.09.1989. US 9194668 B2, 24.11.2015. Стр.: 1 U 1 U 1 Адрес для переписки: 141980, Московская обл., г. Дубна, ул. Жуковского, 2а, АО "ГМКБ " ...

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Номер записи: 1
08-11-2021 дата публикации

Поворотная платформа испытательной установки авариестойкой топливной системы вертолета

Номер: RU0000207621U1
Автор: Денис Игоревич Смагин, Николай Владимирович Микрюков, Роман Сергеевич Савельев, Сергей Васильевич Грачев
Принадлежит: Акционерное общество "Опытное конструкторское бюро "Кристалл", Федеральное государственное бюджетное образовательное учреждение высшего образования "Московский авиационный институт (национальный исследовательский университет)"

Полезная модель относится к испытательной технике и может быть использована при проведении стендовых испытаний для полноразмерной имитации режимов работы в ожидаемых условиях эксплуатации топливной системы вертолетов во время выполнения ими маневров в течение полета. Поворотная платформа испытательной установки авариестойкой топливной системы вертолета включает основание с опорами, на которых закреплена прямоугольной формы поворотная рама, для имитации наклона по тангажу, привод для поворота рамы, топливные трубопроводы и датчики углов поворота рамы. Согласно полезной модели, опоры расположены на продольных сторонах основания симметрично друг другу и выполнены в виде блока балок, включающие вертикальную балку, в верхней части связанную с раскосами и, и косую балку одним концом закрепленную на поперечной балке основания, а сверху связанную с вертикальной балкой опоры. Поворотная рама для имитации наклона по тангажу смонтирована в подшипниковых узлах и закрепленных в плоскости поперечной оси симметрии поворотной платформы, образуя внешнюю поворотную раму, на поперечных сторонах которой, в точках пересечения ее с продольной осью симметрии поворотной платформы и в ее плоскости, смонтированы подшипниковые узлы, и для установки в них внутренней поворотной рамы для возможности имитации наклона по крену. С внутренней стороны внутренней поворотной рамы по периметру расположены элементы крепления для испытуемых компонентов топливной системы вертолета. Внутренняя и внешняя поворотные рамы смонтированы таким образом, что их оси и вращения взаимно перпендикулярны и лежат в одной плоскости. Техническим результатом полезной модели является повышение достоверности полученных экспериментальных данных работы топливной системы вертолета при эволюциях последнего. 4 з.п. ф-лы, 6 ил. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 207 621 U1 (51) МПК F02M 65/00 (2006.01) G01M 13/00 (2006.01) G01M 15/00 (2006.01) B64F 5/00 (2006.01) B64F 5/60 (2017.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ ...

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Номер записи: 2
28-06-2012 дата публикации

Method of designing natural laminar flow wing for reynolds numbers equivalent to actual supersonic aircraft

Номер: US20120166148A1
Автор: Hiroaki Ishikawa, Kenji Yoshida, Kisa Matsushima, Yoshine Ueda
Принадлежит: Japan Aerospace Exploration Agency JAXA

In designing supersonic aircrafts, a method of designing a natural laminar flow wing is provided which reduces friction drag by delaying boundary layer transition under flight conditions of actual aircrafts. A target Cp distribution on wing upper surface, suited to natural laminarization in which boundary layer transition is delayed rearward in desired Reynolds number states, is defined by a functional type having as coefficients parameters depending on each spanwise station, a sensitivity analysis employing a transition analysis method is applied to the parameters, and a search is performed for the optimum combination of parameters to delay transition rearward.

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Номер записи: 3
16-08-2012 дата публикации

Panel for acoustic treatment comprising a junction between two parts and process for the reparation of a panel for acoustic treatment

Номер: US20120205192A1
Автор: Veronique Bornert-Dano
Принадлежит: AIRBUS OPERATIONS SAS

An acoustic treatment panel includes two portions with edges spaced in one direction, and from the outside to the inside, a first acoustically resistive layer, a first alveolar structure, and a reflective layer, and a block inserted between the two edges which includes, from the outside to the inside, a second acoustically resistive layer arranged at the first acoustically resistive layer and a second alveolar structure. The block includes at least one sector of alveolar structures with sloped pipes whose height is less than that of the first alveolar structure, whereby the pipes are sloped in a direction such that the ends of the pipes are close to one of the edges of the portions at the first acoustically resistive layer, and the opposite ends of the pipes are moved away from the edge and the reflective layer so as to house connecting elements between the block and the panel.

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Номер записи: 4
27-12-2012 дата публикации

System and method for determining cumulative tow gap width

Номер: US20120328159A9
Автор: Eric Rector, Jeffrey Haywood, Reed Hannebaum, Roger W. Engelbart
Принадлежит: Boeing Co

A system for determining cumulative tow gap width includes an in-process vision system having at least one camera adapted to record images of a composite material and a data analysis computer communicating with and adapted to receive image data from the in-process vision system. The data analysis computer may be adapted to calculate a cumulative gap width of tow gaps in the composite material. A user interface may communicate with and be adapted to receive data analysis results from the data analysis computer. A method for determining cumulative tow width gap of tow gaps in a composite structure is also disclosed.

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Номер записи: 5
04-04-2013 дата публикации

Aircraft thermal insulation

Номер: US20130082144A1
Автор: Matthew Lang, Ruben James Joseph Fernandes
Принадлежит: BAE SYSTEMS plc

The invention provides an arrangement and methods for thermally insulating aircraft, particularly but not exclusively for when the aircraft is operating in extremely hot or cold conditions, and describes an aircraft skin construction including a foam-stiffened CFC sandwich panel forming part of the aircraft outer skin mounted to an underlying load bearing aircraft structure, wherein the panel at the mounting to the structure includes two outer layers of CFC material with an inner layer of foam material sandwiched therebetween.

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Номер записи: 6
23-05-2013 дата публикации

SYSTEM AND METHOD FOR ASSESSING THE PERFORMANCE OF AN ATTITUDE CONTROL SYSTEM FOR SMALL SATELLITES

Номер: US20130125667A1
Автор: Fitz-Coy Norman G., Nagabhushan Vivek
Принадлежит: UNIVERSITY OF FLORIDA RESEARCH FOUNDATION, INC.

Various embodiments of the present invention include systems and methods for assessing the performance of an actuator of an attitude control system (ACS), such as a control moment gyroscope (CMG). In one embodiment, a system includes a support bracket assembly coupled to an actuator, wherein the actuator is configured to generate an output torque. The system also includes at least one sensor assembly that includes a sensor configured to measure the output torque about at least one axis of the support bracket assembly while the support bracket assembly remains substantially motionless. 1. A system for assessing the performance of an actuator of an attitude control system (“ACS”) comprising:a support bracket assembly coupled to an actuator of an ACS, the actuator configured to generate an output torque; andat least one sensor assembly comprising a sensor configured to measure the output torque about at least one axis of the support bracket assembly while the support bracket assembly remains substantially motionless.2. The system of claim 1 , further comprising a data acquisition system in communication with the at least one sensor assembly and configured to receive the measured output torque.3. The system of claim 1 , wherein the support bracket assembly comprises a pitch axis gimbal coupled to the actuator.4. The system of claim 3 , wherein the support bracket assembly comprises a roll axis gimbal pivotably coupled to the pitch axis gimbal.5. The system of claim 4 , wherein the pitch axis gimbal and the roll axis gimbal extend in perpendicular planes with respect to one another.6. The system of claim 4 , wherein the at least one sensor comprises a pitch axis sensor coupled to the pitch axis gimbal and configured to measure torque on the pitch axis gimbal.7. The system of claim 6 , wherein the sensor assembly further comprises a shaft extending through the roll axis gimbal and coupling the pitch axis gimbal and the pitch axis sensor.8. The system of claim 6 , wherein ...

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Номер записи: 7
23-05-2013 дата публикации

Automated Cleaning System and Method for an Aircraft Fuselage Interior

Номер: US20130125926A1
Автор: Robert Neth, Todd S. Tiffany
Принадлежит: Boeing Co

An automated cleaning system for an aircraft fuselage interior is provided. The system has a movable assembly designed to fit within an aircraft fuselage interior to be cleaned. The movable assembly has a removable track assembly and an automated transport mechanism mounted on the removable track assembly, the automated transport mechanism being a guided cart that travels on the removable track assembly. The movable assembly further has a manifold and frame assembly mounted on the automated transport mechanism and a fluid dispensing assembly coupled to the manifold and frame assembly for dispensing fluids onto an aircraft fuselage interior surface. The system further has a fluid management system coupled to the movable assembly for supplying the fluids to the fluid dispensing assembly. The system further has a control system that communicates with and controls the movable assembly and the fluid management system.

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Номер записи: 8
23-05-2013 дата публикации

RAIL SYSTEM AND METHOD AND SYSTEM FOR MOUNTING A COMPONENT IN AN AIRCRAFT

Номер: US20130126673A1
Автор: Blees Christoph, Halfmann Niklas, Koblitz Ralf, Krause Dieter, Umlauft Sebastian
Принадлежит: AIRBUS OPERATIONS GMBH

A rail system for use when assembling a component in an aircraft comprises a first rail element having a securing device which is designed to be complementary to a first securing device provided in the region of a floor of an aircraft fuselage element and is adapted to cooperate with the first securing device in order to releasably secure the first rail element in the region of the floor of the aircraft fuselage element, wherein a section of the first rail element projects beyond an edge of the floor of the aircraft fuselage element in the connected state of the first rail element and the aircraft fuselage element. The first rail element furthermore comprises a guide device, which is designed to be complementary to a first guide device provided on an assembly aid, which is to be introduced into the aircraft fuselage element, and is adapted to cooperate with the first guide device to enable a guided displacement of the assembly aid to be introduced into the aircraft fuselage element relative to the rail system. The rail system furthermore comprises a second rail element having a securing device which is designed to be complementary to a second securing device provided in the region of the floor of the aircraft fuselage element and is adapted to cooperate with the second securing device in order to releasably secure the second rail element in the region of the floor of the aircraft fuselage element, wherein a section of the second rail element projects beyond an edge of the floor of the aircraft fuselage element in the connected state of the second rail element and the aircraft fuselage element. The second rail element furthermore comprises a guide device, which is designed to be complementary to a second guide device provided on an assembly aid, which is to be introduced into the aircraft fuselage element, and is adapted to cooperate with the second guide device to enable a guided displacement of the assembly aid to be introduced into the aircraft fuselage element ...

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Номер записи: 9
23-05-2013 дата публикации

DURABLE AIRSHIP HULL AND IN SITU AIRSHIP HULL REPAIR

Номер: US20130126675A1
Автор: Heppe Stephen B.
Принадлежит: STRATOSPHERIC AIRSHIPS, LLC

A system for airship hull reinforcement and in-situ repair includes a sensor for detecting a leak in the airship hull of a lighter-than-air airship and a repair mechanism inside lighter-than-air airship for dispensing repair material to seal the leak. A durable airship hull includes an inner gas barrier, an outer gas barrier, and a microlattice layer sandwiched between the inner gas barrier and the outer gas barrier. 1. A system for airship hull reinforcement and in-situ repair comprising:a sensor for detecting a leak in the airship hull of a lighter-than-air airship; anda repair mechanism inside the airship for dispensing repair material to seal the leak.2. The system of claim 1 , in which the hull comprises an inner gas barrier claim 1 , a spacer layer claim 1 , and an outer gas barrier.3. The system of claim 2 , in which the spacer layer is a microlattice having a density of less than 10 milligrams per cubic centimeter.4. The system of claim 3 , in which the microlattice has a density of less than 1 milligram per cubic centimeter.5. The system of claim 2 , in which the repair material comprises a sealant injected into the spacer layer.6. The system of claim 1 , in which the repair material comprises tape or an adhesively applied patch.7. The system of claim 1 , in which the sensor comprises a vacuum pump and vacuum line gas sensor.8. The system of claim 7 , in which the vacuum line gas sensor comprises a spectrometer.9. The system of claim 1 , in which the sensor comprises an infrared camera and radiant heat source.10. The system of claim 1 , further comprising:a plurality of ballonets disposed inside the airship hull; anda hollow passageway connecting the ballonets.11. The system of claim 10 , further comprising a plurality of hatches in the passageway providing access to an interior of each of the said plurality of ballonets.12. The system of claim 11 , in which the repair mechanism can access the interior of each of the said plurality of ballonets through the ...

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Номер записи: 10
30-05-2013 дата публикации

Fire Resistance For Optically Transparent Thermoplastics

Номер: US20130133202A1
Автор: HARRIS John N.
Принадлежит: The Boeing Company

A fire retardant, transparent panel and method of making the panel, that is especially well suited for use on mobile platforms, and particularly on aircrafts. The panel is a composite of a transparent matrix and a plurality of fire-retardant nanoparticles. The nanoparticles have a diameter less than the visible spectrum of light, and in one form between about 0.1 nm to about 400 nm in diameter. The nanoparticles may be arranged randomly or in predetermined patterns within the matrix during manufacturing of the panel. The panel is lightweight, transparent and yet highly fire retardant. 1. A method of manufacturing an aircraft , comprising:forming a fuselage having an opening; providing a transparent matrix;', 'integrating a plurality of fire-retardant nanoparticles, each having a diameter less than the wavelength of visible light, within the transparent matrix; and, 'forming a fire-retardant window adapted to be placed within the opening bysecuring the fire-retardant window within the opening in the fuselage.2. The method of claim 1 , wherein integrating the fire-retardant nanoparticles within the transparent matrix comprises integrating the fire-retardant nanoparticles selected from the group consisting of alumina trihydrate claim 1 , magnesium hydroxide claim 1 , calcium carbonate claim 1 , ferrocene claim 1 , and combinations thereof.3. The method of claim 1 , wherein the integrating a plurality of fire-retardant nanoparticles comprises integrating a plurality of fire-retardant fibers each having a length of between 10 nm and 500 nm integrated within the transparent matrix.4. The method of claim 3 , wherein the integrating a plurality of fire-retardant fibers comprises integrating a plurality of fire-retardant fibers each having a diameter less than about 600 nm.5. The method of claim 4 , wherein the integrating a plurality of fire-retardant fibers comprises integrating the fire-retardant fibers such that the fire-retardant fibers are distributed at outer surface ...

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Номер записи: 11
13-06-2013 дата публикации

METHOD FOR PRODUCING AN ACOUSTIC TREATMENT PANEL

Номер: US20130146393A1
Автор: Albet Grégory, Casse Nicolas, Porte Alain
Принадлежит: AIRBUS OPERATIONS SAS

A method for producing an acoustic treatment panel, including: 1. A method for producing an acoustic treatment panel , the method comprising:assembling first and second plates, at least one of which is deformed so as to separate the plates locally to form a plurality of cavities of a cellular structure between the first and second plates, said cavities being delimited by a plurality of facets and a plurality of partitions formed by at least one of the deformed plates,producing at least one opening on the facets of one of the first and second plates, andpressing an acoustically resistive plate against the surface of the cellular structure including the openings.2. The method for producing an acoustic treatment panel according to claim 1 , further comprising deforming the plate in contact with the acoustically resistive layer so as to form a plurality of grooves with a flared shape to delimit channels with said acoustically resistive layer configured for channeling hot air for frost treatment.3. The method for producing an acoustic treatment panel according to claim 1 , further comprising:forming the first and second plates so as to form first and second cellular half-structures each with a set of co-planar facets separated by a grid of grooves, the first and second cellular half-structures having identical grids of grooves, andassembling the first and second cellular half-structures by pressing the ends of the grooves of the first and second half-structures against each other.4. The method for producing an acoustic treatment panel according to claim 1 , further comprising assembling the first and second plates following a grid of junction lines claim 1 , then deforming the first and second plates between first and second dies by injecting a pressurized fluid between the first and second plates.5. The method for producing an acoustic treatment panel according to claim 3 , wherein the plates are formed by superplastic forming using a die with a grid of grooves.6. The ...

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Номер записи: 12
20-06-2013 дата публикации

AIRCRAFT WING ASSEMBLY

Номер: US20130153712A1
Автор: GLEAVE John, HADLEY Paul, Wilson James
Принадлежит: AIRBUS OPERATIONS LIMITED

An aircraft wing assembly, comprising a wing having a fixed leading edge, a slat mounted upon a slat deployment mechanism for moving the slat between a retracted position and an extended position with respect to the fixed leading edge, the fixed leading edge having an aperture to accommodate the slat deployment mechanism, and a closing plate mounted off the slat deployment mechanism for closing a gap between a lower trailing edge of the slat and a lower edge of the aperture when the slat is retracted. The closing plate can include a first portion and a second portion, and a hinge connecting the first and the second portions. The closing plate can include a plurality of integrally formed spacer elements for positioning the closing plate with respect to the slat deployment mechanism. Also, a method of removing an access panel in an aircraft wing assembly. 1. An aircraft wing assembly , comprising a wing having a fixed leading edge , a slat mounted upon a slat deployment mechanism for moving the slat between a retracted position and an extended position with respect to the fixed leading edge , the fixed leading edge having an aperture to accommodate the slat deployment mechanism , and a closing plate mounted off the slat deployment mechanism for closing a gap between a lower trailing edge of the slat and a lower edge of the aperture when the slat is retracted , wherein the closing plate includes a first portion and a second portion , and a hinge connecting the first and the second portions.2. An aircraft wing assembly according to claim 1 , wherein the hinge is a mechanical hinge or a strip of increased flexibility within the closing plate construction.3. An aircraft wing assembly according to claim 1 , wherein the fixed leading edge includes a removable access panel adjacent the aperture claim 1 , and a portion of the closing plate overlaps the access panel when the slat is retracted.4. An aircraft wing assembly according to claim 3 , wherein the normally overlapping ...

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Номер записи: 13
27-06-2013 дата публикации

SYSTEM AND METHOD FOR CONVERTING A PASSENGER AIRCRAFT TO A CARGO AIRCRAFT

Номер: US20130161448A1
Автор: Wagner William J.
Принадлежит: PRECISION CONVERSIONS, LLC

An aircraft-conversion method of converting a passenger aircraft to a cargo aircraft, includes selecting a passenger aircraft, and converting the aircraft to a cargo aircraft by changing a door of the aircraft to accommodate loading and unloading of cargo. The selecting step may involve an all-passenger aircraft, and the converting step may include removing all seats from the aircraft. A system for converting a passenger aircraft with a passenger door for passenger entry and exit to a cargo aircraft includes aircraft-door conversion structure constructed to replace the passenger door with a cargo door that allows loading and unloading of cargo on the aircraft via the cargo door. A converted cargo aircraft includes an aircraft body, and aircraft-door conversion structure constructed to replace the passenger door with a cargo door that allows loading and unloading of cargo on the aircraft via the cargo door. 1. An aircraft-conversion method of converting a passenger aircraft to a cargo aircraft , comprising:selecting a passenger aircraft; andconverting the aircraft to a cargo aircraft by changing a door of the aircraft to accommodate loading and unloading of cargo.2. The method of claim 1 , wherein the selecting step involves an all-passenger aircraft.3. The method of claim 1 , wherein the converting step includes removing all seats from the aircraft.4. A system for converting a passenger aircraft with a passenger door for passenger entry and exit to a cargo aircraft claim 1 , comprising:aircraft-door conversion structure constructed to replace the passenger door with a cargo door that allows loading and unloading of cargo on the aircraft via the cargo door.5. A converted cargo aircraft claim 1 , comprising:an aircraft body;aircraft-door conversion structure constructed to replace the passenger door with a cargo door that allows loading and unloading of cargo on the aircraft via the cargo door. This application is a continuation of U.S. patent application Ser. No. 13/ ...

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Номер записи: 14
27-06-2013 дата публикации

DIAGNOSTICS FOR AIRCRAFT

Номер: US20130166135A1
Автор: Dunsdon Jonathan Mark
Принадлежит:

A system for automatically analysing aircraft systems data is described. The system comprises a data acquisition module operable to acquire aircraft systems data, a data archiving module operable to store aircraft systems data and a data analysis module operable to analyse the aircraft systems data to identify non-predetermined troubleshooting procedures for fault rectification. Automated identification of improved maintenance techniques can thus be provided, with the added benefit that maintenance manuals and procedures may thereby be automatically adapted over time. A related method is also described. 1. A system for automatically analysing aircraft systems data , comprising:a data acquisition module operable to acquire aircraft systems data;a data archiving module operable to store aircraft systems data; anda data analysis module operable to analyse the aircraft systems data to identify non-predetermined troubleshooting procedures for fault rectification.2. The system of claim 1 , wherein the data acquisition module is further operable to acquire the aircraft systems data from a plurality of aircraft.3. The system of claim 1 , wherein the data archiving module is further operable to access a maintenance manual storage module to identify predetermined troubleshooting procedures.4. The system of claim 3 , wherein the data analysis module is further operable to automatically update a maintenance manual stored in the maintenance manual storage module so that it includes maintenance procedures corresponding to the identified non-predetermined troubleshooting procedures.5. The system of claim 1 , further comprising a maintenance task data capture module operable to capture at least one actual maintenance step undertaken during a maintenance procedure.6. The system of claim 5 , wherein the maintenance task data capture module is further operable to capture the steps in sequence.7. The system of claim 6 , wherein the data analysis module is operable to identify the non- ...

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Номер записи: 15
04-07-2013 дата публикации

RAPID STORE LOAD SYSTEM FOR AIRCRAFT AND METHOD OF OPERATION THEREOF

Номер: US20130168499A1
Автор: Grossman Victor A.
Принадлежит:

A method to load stores on an aircraft, the method may be controlled by one or more controller and may include one or more acts of loading stores onto corresponding lift portions; determining a relative position of the aircraft; positioning the stores relative to the determined position of the aircraft; and securing the stores to corresponding hardpoints (HPs) of the aircraft. 1. A method to load stores on an aircraft using plurality of lift portions , the method controlled by a controller , the method comprising acts of:receiving the stores at corresponding lift portions of the plurality of lift portions;determining positions of each of a of plurality of hardpoints (HPs) of the aircraft;controlling corresponding, lift, portions to position the received stores relative to corresponding HPs of the plurality of HPs of the aircraft; andsecuring the stores to corresponding HPs of the plurality of HPs.2. The method of claim 1 , further comprising an act of selecting the stores to be received by the corresponding lift portions in accordance with one or more of an identification (ID) of the aircraft and an identification of the stores.3. The method of claim 1 , wherein the act of selecting the stores further comprises acts of determining a configuration of the aircraft; andcontrolling one or more of the lift portions in accordance with the determined configuration of the aircraft.4. The method of claim 3 , wherein the configuration of the aircraft comprises information related to one or more of aircraft type claim 3 , aircraft identification (ID) claim 3 , aircraft block number claim 3 , selected stores claim 3 , flight data link (FDL) type claim 3 , hardpoint configuration claim 3 , HP type claim 3 , HP location claim 3 , HP rack unit (RU) claim 3 , RU location claim 3 , pylon information claim 3 , launcher information.5. The method of claim 1 , wherein the act of securing the stores comprises attaching the stores to corresponding HPs of the plurality of HPs in accordance ...

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Номер записи: 16
18-07-2013 дата публикации

Self-stiffened composite panel and process for making same

Номер: US20130180642A1
Автор: Bernard Duprieu, Cyrille Collart, Jean-Pierre Cabanac, Laurent Giuseppin, Philippe Blot, Sébastien ALBY
Принадлежит: AIRBUS OPERATIONS SAS

The invention provides a self-stiffened composite panel including an external skin, an internal skin superposed on the external skin, which covers an internal face of the external skin and at least one stiffener protruding inwards relatively to the internal skin which extends along a longitudinal direction, characterised in that the stiffener is made as one piece with the internal skin and consists of a portion of the internal skin which is located at distance from the external skin. The invention also provides a process for making such a self-stiffened panel.

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Номер записи: 17
18-07-2013 дата публикации

Device and method for assembling two sections of aircraft fuselage

Номер: US20130181092A1
Автор: Alain Depeige, Bruno Cacciaguerra, Helene Cazeneuve, Jean-Claude Lacombe, Marc-Antoine Castanet
Принадлежит: AIRBUS OPERATIONS SAS

Device for assembling two aircraft fuselage sections each comprising a skin and longitudinal stiffeners, the device comprising fishplates fishing couples of mutually aligned longitudinal stiffeners belonging respectively to said sections, each fishplate comprising two fishplate pieces each comprising at least one longitudinal sole plate intended to be fixed to a longitudinal stiffener, and a transverse support head, and at least one demountable connecting member able to mutually clamp the respective support heads of said fishplate pieces to allow a transmission of longitudinal forces between these fishplate pieces. Set of fuselage sections assembled by means of a device of the type described above. Method of assembling two fuselage sections by means of a device of the type described above.

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Номер записи: 18
25-07-2013 дата публикации

METHOD OF CALCULATING DYNAMIC PRESSURE AT THE LEVEL OF AN AIRCRAFT SURFACE

Номер: US20130191087A1
Автор: CALMELS Benoit
Принадлежит: AIRBUS OPERATIONS SAS

The invention is aimed at a method simulating the aerodynamic flow around an aircraft, so as to detect the aerodynamic loads exerted on a predetermined surface of the aircraft. The method includes a phase of determining a value denoted QA of global dynamic pressure at the level of the predetermined surface of the aircraft. The method includes steps of carrying out simulations of aerodynamic flow around the predetermined surface of the aircraft for given environmental conditions, on the basis of a mesh produced around the shape of the aircraft, determining a local dynamic pressure qA around the predetermined surface of the aircraft, and then calculating the global dynamic pressure QA. 3. Method according to claim 1 , characterized in that the structure element considered being a horizontal tailplane claim 1 , the step of flow simulations is carried out for predetermined values of incidence of the flow denoted á and for a given trim iH of the tailplane.4400. Method according to claim 3 , characterized in that in step claim 3 , the static pressure at infinity p0 determined beforehand is taken as value of the local static pressure in the presence of the aeroplane without tail pA claim 3 , at any point of the mesh.5500300. Method according to claim 3 , characterized in that in step claim 3 , the value claim 3 , determined during step claim 3 , of the total pressure denoted ptH around the horizontal tailplane is used as approximation of the total pressure without tailplane claim 3 , denoted ptA claim 3 , for the mesh points situated outside of the boundary layer of the tailplane.8. Method of designing an aircraft surface claim 1 , characterized in that it comprises a method for calculating the aerodynamic loads exerted on the said surface claim 1 , according to claim 1 , and a step of verifying the compatibility of the calculated loads with a predefined specification. The present invention pertains to the field of aircraft design methods. It applies to aircraft ...

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Номер записи: 19
08-08-2013 дата публикации

Method and a device for performing a check of the health of a turbine engine of an aircraft provided with at least one turbine engine

Номер: US20130199204A1
Автор: Emmanuel Camhi, Guido Borchers
Принадлежит: Eurocopter SA

A method of automatically performing an engine health check for checking the health of at least one turbine engine of an aircraft. During flight, the stability of at least one monitoring parameter is verified by acquiring a measurement signal, by performing first filtering of each signal by a high-pass filter over a long first duration (TPS 1 ) and by verifying that a first amplitude (A 1 ) of the signal filtered in this way does not exceed a first threshold defined by the manufacturer, by performing second filtering of each signal by a high-pass filter over a short second duration (TPS 2 ) in parallel with said first filtering by a high-pass filter, and by verifying that a second amplitude (A 2 ) of the signal filtered in this way does not exceed a second threshold defined by the manufacturer, the second duration (TPS 2 ) being less than the first duration (TPS 1 ), and the second amplitude (A 2 ) being less than the first amplitude (A 1 ).

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Номер записи: 20
15-08-2013 дата публикации

JIG FOR THE MODELLING OF AT LEAST ONE SECTION OF AN AIRCRAFT FUSELAGE

Номер: US20130206710A1
Автор: Halfmann Niklas, Krause Dieter, ROSCHAT Bernd
Принадлежит: AIRBUS OPERATIONS GMBH

Disclosed is a jig for the modelling of at least one section of an aircraft fuselage, with a framework structure and with a multiplicity of adapters for the connection of stiffening elements to the framework structure, which can be moved relative to the framework structure, and/or with a multiplicity of adapters for the modelling of profiles of stiffening elements, which can be moved relative to the framework structure. 1. A jig for the modelling of at least one section of an aircraft fuselage comprising:a framework structure; anda multiplicity of adapters for connection of stiffening elements to the framework structure, which can be moved relative to the framework structure.2. The jig in accordance with claim 1 , further comprising:a multiplicity of adapters for modelling of profiles of stiffening elements, which can be moved relative to the framework structure.3. The jig in accordance with claim 1 , wherein the multiplicity of adapters on the framework structure can be moved in a radial direction.4. The jig in accordance with claim 1 , wherein the multiplicity of adapters on the framework structure can be moved in a circumferential direction.5. The jig in accordance with claim 1 , wherein the multiplicity of adapters on the framework structure are mounted such that they can be pivoted.6. The jig in accordance with claim 2 , wherein the multiplicity of adapters on the framework structure can be moved in a radial direction.7. The jig in accordance with claim 2 , wherein the multiplicity of adapters on the framework structure can be moved in a circumferential direction.8. The jig in accordance with claim 2 , wherein the multiplicity of adapters on the framework structure are mounted such that they can be pivoted.9. The jig in accordance with claim 2 , wherein the multiplicity of adapters for modelling of profiles of stiffening elements includes sections for a connection of structural elements to the framework structure.10. The jig in accordance with claim 2 , wherein ...

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Номер записи: 21
15-08-2013 дата публикации

INTEGRATED GALLEY AND BIN MONUMENT

Номер: US20130206905A1
Автор: Gee Kyle, SAVIAN Scott
Принадлежит: C&D ZODIAC, INC.

A galley monument assembly that is configured to be positioned in the interior of an aircraft. The galley monument assembly includes a lower storage section that is adapted to receive at least one trolley cart and that includes a vertically oriented rear wall and two opposing side walls. The lower storage section defines a first storage depth. The galley monument assembly also includes an upper storage section that defines a second storage depth. The second storage depth is deeper than the first storage depth. 1. A galley monument assembly configured to be positioned in the interior of an aircraft , the galley monument assembly comprising:a lower storage section that is adapted to receive at least one trolley cart, the lower storage section including a vertically oriented rear wall and two opposing side walls, wherein the lower storage section defines a first storage depth, andan upper storage section, wherein the upper storage section defines a second storage depth, wherein the second storage depth is deeper than the first storage depth.2. The galley monument assembly of further comprising a floor footprint that defines a depth claim 1 , wherein the depth of the upper storage section is greater than the depth of the floor footprint.3. The galley monument assembly of further comprising a transition section disposed between the lower storage section and the upper storage section claim 2 , wherein the transition section defines a gradually increasing storage depth.4. The galley monument assembly of wherein the gradually increasing storage depth is greater than the depth of the floor footprint.5. The galley monument assembly of further comprising an overhanging portion that defines at least a portion of the upper storage section and that includes a rear wall that has a contoured inboard edge claim 4 , wherein when the galley monument assembly is positioned in the interior of an aircraft claim 4 , the rear wall abuts a wall of an overhead stowage bin and the contoured ...

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Номер записи: 22
19-09-2013 дата публикации

SMOOTH SURFACE FORMING TOOL AND MANUFACTURE THEREOF

Номер: US20130240110A1
Автор: Grankäll Tommy, Hallander Per, Nordin Pontus, Petersson Mikael, Strindberg Göte, Weidmann Björn
Принадлежит: SAAB AB

An aircraft article composite forming tool and a method for producing the tool. The aircraft article to be formed includes a composite material including an outer surface. The aircraft article composite forming tool includes a matrix laminate made of at least an upper ply including a forming surface for forming the aircraft article and outer surface. The upper ply includes a nano filament structure embedded therein. 1293111729115. An aircraft article composite forming tool , the aircraft article () to be formed comprises a composite material including an outer surface () , the aircraft article composite forming tool () comprises a matrix laminate () made of at least an upper ply (P) including a forming surface () for forming said aircraft article () and outer surface () , characterized by that the upper ply (P) comprises a nano filament structure () embedded therein.2157. The aircraft article composite forming tool according to claim 1 , wherein the nano filament structure () comprises a portion being exposed in the forming surface ().3151515151. The aircraft article composite forming tool according to or claim 1 , wherein the nano filament structure comprises nano filaments (′ claim 1 , ″ claim 1 , ′″ claim 1 , ″″) claim 1 , which are transversally oriented relative the extension of the plane (P) of the upper ply (P).4311815. The aircraft article composite forming tool according to any of to claims 1 , wherein the matrix laminate () further comprises a bottom ply (P) including a nano filament structure ().51519715151515. The aircraft article composite forming tool according to any of the preceding claims claims 1 , wherein at least a portion of the nano filament structure () is coupled to an energy supply () for heating the forming surface () claims 1 , wherein the nano filaments (′ claims 1 , ″ claims 1 , ′″ claims 1 , ″″) have such a distance between each other so that the electrical resistance increases.61915. The aircraft article composite forming tool ...

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Номер записи: 23
03-10-2013 дата публикации

NOVEL SYSTEMS AND METHODS FOR NON-DESTRUCTIVE INSPECTION OF AIRPLANES

Номер: US20130261876A1
Автор: Froom Douglas Allen, Manak William T.
Принадлежит: AEROBOTICS, Inc.

A method for managing an airplane fleet is described. The method includes: (i) developing a gold body database for an airplane model for each non-destructive inspection system implemented to detect defects; (ii) inspecting, over a period of time, a plurality of candidate airplanes of the airplane model, using different types of non-destructive inspection systems and the gold body database associated with each of the different types of non-destructive inspection systems, to identify defects present on the plurality of candidate airplanes; (iii) repairing or monitoring defects detected on the plurality of candidate airplanes; (iv) conducting a trend analysis by analyzing collective defect data obtained from inspecting of plurality of candidate airplanes; and (v) maintaining the airplane fleet, which includes plurality of candidate airplanes, by performing predictive analysis using results of trend analysis. 1. A method for managing an airplane fleet , said method comprising:developing a gold body database for an airplane model for each non-destructive inspection system implemented to detect defects;inspecting, over a period of time, a plurality of candidate airplanes of said airplane model, using different types of non-destructive inspection systems and said gold body database associated with each of said different types of non-destructive inspection systems, to identify defects present on said plurality of candidate airplanes;repairing or monitoring defects detected on said plurality of candidate airplanes;conducting a trend analysis by analyzing collective defect data obtained from said inspecting of said plurality of candidate airplanes; andmaintaining said airplane fleet, which includes said plurality of candidate airplanes, by performing predictive analysis using results of said trend analysis.2. The method of claim 1 , wherein said non-destructive inspection systems is at least one system selected from a group consisting of X-ray inspection system claim 1 , N- ...

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Номер записи: 24
10-10-2013 дата публикации

Aircraft frame and method for obtaining the same

Номер: US20130264422A1
Автор: Enrique Vera Villares, José Maria Pina López
Принадлежит: AIRBUS OPERATIONS SL

An aircraft frame and a method for obtaining an aircraft frame, which frame is made of composite material, and which frame comprises several partitions ( 20 ) that form, when joined, the aforementioned frame in its entirety, with these partitions ( 20 ) comprising sections ( 1 ) with a length ( 2 ), and sections ( 1 ) that are being arranged on the inside of the skin ( 3 ) that forms the fuselage of the aircraft. This fuselage is integrally embodied in a single piece, with the length ( 2 ) of the sections ( 1 ) being the maximum possible, In such a way that the maximum separation ( 5 ) between the frame section ( 1 ) and the skin ( 3 ), with the separation ( 5 ) being measured by the inside of the aforementioned skin ( 3 ), is lower than the limit value permitted for the use of a liquid sealant.

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Номер записи: 25
10-10-2013 дата публикации

DETECTION SYSTEM FOR DETECTION OF DAMAGES ON ROTATING COMPONENTS OF COMPONENTS OF AIRCRAFT AND METHOD OF OPERATING SUCH A DETECTION SYSTEM

Номер: US20130268154A1
Автор: Kreitmair-Steck Wolfgang
Принадлежит: EUROCOPTER DEUTSCHLAND GMBH

A detection system and method for detection of damages on at least one rotating component (. . . N) of an air vehicle caused by at least one solid, comprising measuring means (S, S, S . . . Sn) for measuring vibration and/or sound of said rotating components ( . . . N), to acquire the time signal of vibration and/or sound of any of said rotating components ( . . . N), and processing means (PRO) for comparing said measured vibration and/or sound with a maximum value or an envelope of standard vibration and/or sound stored in a memory (EM, EM, . . . EMn) and warning means (WS) for issuing a warning signal when the measured vibration and/or sound exceeds said standard vibration and/or sound. The air vehicle is an airplane or a helicopter, the solid is a projectile, stones, ice-crystals or bird strike, and the measuring means are vibration sensors (S, S, S . . . Sn) and/or acoustic sensors (S, S, S . . . Sn). The reference maximum value/envelope is related to/dependent on relevant actual flight parameter values. 1. A detection system for detection of damages on at least one rotating component of an air vehicle caused by at least one solid , comprising measuring means for measuring vibration and/or sound of said rotating components of the air vehicle , in order to acquire data related to the amplitude versus time of vibration and/or sound of any of said rotating components , and processing means for comparing said measured vibration and/or sound with at least one maximum value or an envelope of standard vibration and/or sound stored in a memory and warning means for issuing a warning signal in/to the air vehicle when the measured vibration and/or sound exceeds said standard vibration and/or sound , wherein the air vehicle is a propeller airplane or a helicopter , the at least one solid is a projectile , stones , ice-crystals or bird strike , the measuring means are vibration sensors at bearings of a propeller or a rotor drive and/or acoustic sensors at an upper area of ...

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Номер записи: 26
17-10-2013 дата публикации

Method, devices and program for computer-aided analysis of the failure tolerance of an aircraft system, using critical event charts

Номер: US20130274991A1
Автор: Cheriere Vincent, Genata Ioana, Roger Jeremy, Vilata Estrada Laia
Принадлежит: AIRBUS OPERATIONS (SAS)

Aided analysis of the failure tolerance of an aircraft system, comprising a plurality of subsystems at least one of which comprises a monitoring unit and notification of a detected event, using critical event charts. After selecting at least one receivable notification message represented by a node of the critical event chart, elements of the minimal diagnostic set capable of resulting in the generation of the at least one selected notification message are identified, the identified elements forming part of the failure tolerance report. 1. A method for the computer-aided preparation of a failure tolerance report for a complex system of an aircraft comprising a plurality of subsystems , at least one subsystem of said plurality of subsystems comprising means of monitoring and notification of at least one detected event , the method comprising: a plurality of nodes each representing a notification message capable of being received;', 'at least one node representing a critical event; and,', 'a plurality of nodes each representing an element of said complex system, each element represented by a node being liable to failure;, 'implementing a critical event chart at least partially modelling said complex system, said critical event chart comprising a plurality of nodes, each node of said plurality of nodes being linked by a logical implication relation to at least one other node of said plurality of nodes, said plurality of nodes comprisingreceiving at least one message notifying the occurrence of said at least one detected event;creating a minimal diagnostic set relative to said at least one detected event, comprising a plurality of elements suspected of resulting in said at least one detected event, each element of said minimal diagnostic set being represented by a node of said critical event chart and determined according to at least one logical implication relation of said critical event chart with a node representing said at least one received notification message; ...

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Номер записи: 27
17-10-2013 дата публикации

Method, devices and program for computer-aided preventive diagnostics of an aircraft system, using critical event charts

Номер: US20130274992A1
Автор: Chantal Philippe, Cheriere Vincent, Debray Vincent, Fabre Benjamin, Roger Jeremy
Принадлежит:

Aided preventive diagnostics of an aircraft system, comprising a plurality of subsystems at least one of which comprises a subsystem configured for monitoring and notifying a detected event, using critical event charts. After receiving a message notifying the occurrence of said detected event, a minimal diagnostic set relative to said at least one detected event, comprising a plurality of elements each represented by a node of said critical event chart is created, each element of said minimal diagnostic set being determined according to at least one logical implication relation of said critical event chart with a node representing said at least one received notification message. At least some of the elements of said minimal diagnostic set are then ranked, said ranked elements forming part of said diagnostic report. 1. A method for the computer-aided preparation of a diagnostic report for a complex system of an aircraft comprising a plurality of subsystems , at least one subsystem of said plurality of subsystems comprising a subsystem configured for monitoring and notification of at least one detected event , the method comprising: a plurality of nodes each representing a notification message capable of being received;', 'at least one node representing a critical event; and,', 'a plurality of nodes each representing an element of said complex system, each element represented by a node being liable to failure;, 'implementing a critical event chart at least partially modelling said complex system, said critical event chart comprising a plurality of nodes, each node of said plurality of nodes being linked by a logical implication relation to at least one other node of said plurality of nodes, said plurality of nodes comprisingreceiving at least one notification message of the occurrence of said at least one detected event;creating a minimal diagnostic set relative to said at least one detected event, comprising a plurality of elements each represented by a node of said ...

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Номер записи: 28
17-10-2013 дата публикации

Centralized Maintenance Device for Aircraft

Номер: US20130274994A1
Автор: Christian Albouy, Xavier Chazottes
Принадлежит: Thales SA

A centralized maintenance device installed on-board an aircraft notably carries out the following functions: correlation of data relating to failures, warnings, configurations, operational contexts, flags and the logbook, received by the on-board maintenance system; storage of the data received by the on-board maintenance system in a first database; management of a historical record of the data received and of their correlation; transmission to a man-machine interface of the data received, of their correlation and of a date associated with each item of data; display of the received data, their correlation and the date associated with each item of data, by a man-machine interface of the on-board maintenance system.

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Номер записи: 29
24-10-2013 дата публикации

DEVICE FOR CLEANING AERONAUTICAL PARTS

Номер: US20130276256A1
Автор: GARCIA Honore
Принадлежит:

Device for cleaning aeronautical parts after machining or piercing includes an element for spraying a liquid on the part to be cleaned and an element for aspirating the oil-soiled liquid, chips and/or dust. 1. A pneumatic device for cleaning aeronautical parts after machining or piercing , said device comprising a pneumatic means for spraying a solvent on the part to be cleaned and a pneumatic means for aspirating the oil-soiled liquid , chips and/or dust , the control of the device being pneumatic.2. The cleaning device as claimed in claim 1 , wherein the solvent has a flash point below or equal to 300° C. claim 1 , preferably below or equal to 110° C.3. The cleaning device as claimed in claim 1 , said cleaning device comprising a means for filtering the soiled liquid allowing the filtration of the soiled liquid before it is stored.4. Cleaning device according to claim 3 , said device comprising a closed circuit allowing the soiled liquid claim 3 , once retreated by filtration claim 3 , to be reused by the spraying means.5. The cleaning device as claimed in claim 1 , wherein the spraying means comprises a gun fitted with a trigger (G) claim 1 , the actuation of the trigger (G) allowing the spraying of the liquid.6757. The cleaning device as claimed in claim 5 , wherein the gun comprises a plurality of bristles () forming a brush () claim 5 , the jet of liquid originating from the gun being directed toward the bristles ().795. The cleaning device as claimed in claim 5 , wherein the aspiration means comprises a duct () provided on the gun fitted with the brush ().8. The cleaning device as claimed in claim 1 , wherein the aspiration means comprises a venturi-effect vacuum system.9. The cleaning device as claimed in claim 1 , wherein the air expelled from the device is filtered before it is discharged into the atmosphere.10. The cleaning device as claimed in claim 1 , wherein it comprises a control claim 1 , situated in the vicinity of the trigger claim 1 , making it ...

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Номер записи: 30
24-10-2013 дата публикации

SUPER-RIGID HYBRID AIRSHIP, ITS STRUCTURAL CHARACTERISTICS AND A METHOD OF PRODUCING THEREOF

Номер: US20130277496A1
Автор: Kraus Hans Georg
Принадлежит:

A super-rigid hybrid airship having a modular structure with a central tube having a diameter of between 5 to 10% of the diameter of the airship, structural rings surrounding and preferably concentric with the central tube and connected to the tube by bolts; an external cover made from thin metal sheets, interspersed with composite resins and fibbers which is pressurized and pre-stressed by light gases and which is rigid, conductive, non-combustible and impermeable to gases; balloons filed with hydrogen and disposed in structural sections defined by neighboring structural rings; at least two interconnected cuffs inflated by atmospheric air serving as operational ballast and ensuring weight, pressure and volume balance of the airship. Preferably the airship has a blower system for dispersing air, arranged on the centerline of the top layer, wings arranged at each side of the fixed sections, and thrust means. 11234627. A super-rigid hybrid airship , wherein said airship has a modular structure and comprises a central tube () having a diameter of between 5 to 10% of the diameter of the airship , structural rings () surrounding and preferably concentric with the central tube and connected to the tube by bolts () , an external cover () made from thin metal sheets , interspersed with composite resins and fibbers which is pressurized and pre-stressed by light gases and which is rigid , conductive , non-combustible and impermeable to gases , balloons () filed with hydrogen and disposed in structural sections defined by neighboring structural rings () , at least two interconnected cuffs () inflated by atmospheric air serving as operational ballast and ensuring weight , pressure and volume balance of the airship , wherein the dimensions and quantity of airship components depend on the size of the airship of such a modular design.244. The hybrid airship according to claim 1 , wherein the external cover () is made from aluminium and/or duralumin claim 1 , extremely thin rolled ...

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Номер записи: 31
24-10-2013 дата публикации

METHOD AND DEVICE FOR DEVELOPMENT OF A SYSTEM FOR MANAGEMENT OF THE WARNINGS AND PROCEDURES ON AN AIRCRAFT

Номер: US20130280679A1
Автор: CHAZOTTES Xavier, DESEURE Chris, GAUTHERON Didier, SERROT Patrick
Принадлежит: THALES

A method to develop a system for management of warnings and electronic procedures for an aircraft, comprising a database of parameters relating to the warnings and to logic and procedures, the aircraft comprising ATA equipment, comprises definition and calculation of maturity criteria for development of the system, which comprises, in order: A) verification of warnings in the database with respect to predefined lists of warnings and calculation of a maturity criterion, B) if the criterion of A>predetermined threshold, verification of the coherence of the logic for the warnings then definition and calculation of a maturity criterion, C) if the criterion of B>predetermined threshold, verification of the existence of the procedures and, for each warning, analysis of its logic with respect to its procedure, then definition and calculation of a maturity criterion, the system being fully set up when the latter criterion>predetermined threshold. 1. A method for development of a system for management of warnings and electronic procedures for an aircraft , the system comprising a database of parameters relating to warnings and to logic and procedures associated with these warnings , the aircraft comprising several types of equipment being ATA equipment , the method comprising a step for definition and for calculation of maturity criteria for the development of the system for management of warnings and procedures , which comprises , in order , the following sub-steps:A1) verification of the warnings in the database for each unit of ATA equipment with respect to a predefined list of indispensible warnings, then definition and calculation of a maturity criterion C1 for this sub-step,A2) if C1>first predetermined threshold, verification that these warnings are complete with respect to a predetermined list of warnings for each unit of ATA equipment, then definition and calculation of a maturity criterion C2 for this sub-step,A3) if C2>second predetermined threshold, verification ...

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Номер записи: 32
31-10-2013 дата публикации

Ballistic Protection Systems and Methods

Номер: US20130284339A1
Автор: Bouldin Danny, Cellarius Mark Raymond
Принадлежит:

Embodiments of the present disclosure generally pertain to lightweight, environmentally durable, structurally rigid ballistic protection methods. An exemplary method of fabricating the ballistic protection system comprises the steps of assembling the sections separately and curing each section at a specific temperature and pressure. Once the sections are individually assembled and cured, the sections are joined together and cured at a separate temperature and pressure. 1. A method of fabricating a ballistic protection panel , comprising the steps of:assembling a first section having at least one tile positioned between layers of material;curing the first section at a specific temperature and pressure;assembling a second section having at least one ply of material;curing the second section at a specific temperature and pressure;bonding the first section and the second section to a third section, the third section comprising a honeycomb panel;wrapping the first section, the second section, and the third section in an outer covering thereby forming an assembled ballistic protection panel; andcuring the assembled ballistic protection panel at a specific temperature and pressure.2. The method of claim 1 , wherein the at least one tile comprises silicon carbide.3. The method of claim 1 , wherein the honeycomb panel has a plurality of hexagonal-shaped cells.4. The method of claim 1 , wherein the outer covering comprises a flame retardant material.5. The method of claim 1 , further comprising the step of coupling the assembled ballistic protection panel to a surface of an aerial vehicle. This application claims priority to U.S. provisional patent application no. 61/308,373, entitled “Ballistic Protection Systems and Methods” and filed on Feb. 26, 2010 and to U.S. patent application Ser. No. 13/035,195, entitled “Ballistic Protection Systems and Methods” and filed on Feb. 25, 2011, each of which is incorporated herein by reference in its entirety.Ballistic protection systems ...

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Номер записи: 33
31-10-2013 дата публикации

AIRCRAFT SYSTEM COMPONENT CARRIER MODULE AND SYSTEM, AND MOUNTING METHOD

Номер: US20130284868A1
Автор: Humfeldt Dirk, MOJE Sabrina
Принадлежит:

An aircraft system component carrier module includes a carrier element which is arc-shaped at least in sections and is configured, when the module is mounted in an aircraft, to extend at least in some sections substantially in the direction of the ribs of an aircraft structure over at least a section of a crown area of an aircraft cabin. The module includes a transverse carrier element which is configured, when the module is mounted in an aircraft, to extend in the crown area of an aircraft cabin substantially perpendicularly to a longitudinal axis of the cabin. The module further includes a structure holder for fastening the module to the aircraft structure, an aircraft system component holder for fastening at least one of the aircraft system components to the module and an attaching device, connected to the transverse carrier element, for attaching an aircraft luggage compartment to the module. 1. Aircraft system component carrier module having:a carrier element which is arc-shaped at least in some sections and is configured, when the aircraft system component carrier module is mounted in an aircraft, to extend at least in some sections substantially in the direction of the ribs of an aircraft structure over at least a section of a crown area of an aircraft cabin,a transverse carrier element which is configured, when the aircraft system component carrier module is mounted in an aircraft, to extend in the crown area of an aircraft cabin substantially perpendicularly to a longitudinal axis of the aircraft cabin,a structure holder for fastening the aircraft system component carrier module to the aircraft structure,an aircraft system component holder for fastening at least one aircraft system component to the aircraft system component carrier module andan attaching device, connected to the transverse carrier element, for attaching an aircraft luggage compartment to the aircraft system component carrier module.2. Aircraft system component carrier module according to ...

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Номер записи: 34
07-11-2013 дата публикации

Method for repairing at least a portion of an accoustic panel

Номер: US20130292202A1
Автор: Emmanuel Anfray, Franck Maze, Herve Simon, John Moutier
Принадлежит: Aircelle SA

The present disclosure relates to a method for repairing a portion of an acoustic panel for a nacelle of an aircraft turbojet engine. The panel includes an acoustic skin in which a plurality of acoustic holes are drilled, a solid skin, and a cellular acoustic structure. The cellular acoustic structure, being arranged between the acoustic skin and the solid skin, has a plurality of cells, each of which has one or more drainage openings arranged in one or more of the walls forming each cell. The method includes a step of: defining a part of the acoustic panel to be cut; forming a cutting area closed by the acoustic skin; injecting a resin through the acoustic holes; positioning a replacement cellular acoustic structure in the cutting area and on the acoustic skin; forming a solid replacement skin on the replacement cellular acoustic structure.

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Номер записи: 35
14-11-2013 дата публикации

ACTUATING SYSTEM OF SECTORS OF A DEVICE FOR PRODUCING AN AIRPLANE FUSELAGE

Номер: US20130298365A1
Автор: Iovine Giuseppe, Mostarde Ettore, SIBONA Guido
Принадлежит:

An actuating system of sectors of a device for producing an airplane fuselage in which a lamination mandrel comprises a plurality of sectors angularly spaced about the axis and mobile along guides between: an expanded lamination position and a contracted disassembling position. Each sector is provided with an actuating system of the screw—nut screw type in which a threaded element is rotated about a rotation axis by a motor. The threaded element comprises an internal shaft made of a first material and extending along the rotation axis and an external tubular portion made of a second material, mounted axially on a portion of the shaft and provided externally with a thread. 1245745. An actuating system of sectors of a device () for producing an airplane fuselage in which a lamination mandrel () is defined by an external surface () which defines a rotation solid with respect to a symmetry axis (); said lamination mandrel () is adapted to receive and support a band of impregnated synthetic material which is deposited and wound on the external surface () forming a plurality of overlapping layers which are subjected to a high temperature polymerisation process under vacuum for forming a structural section of the airplane;{'b': 4', '12', '7, 'claim-text': [{'b': 12', '13', '7', '12', '7', '5, 'an expanded lamination position in which the sectors () have greater rectilinear edges () parallel to the axis () and arranged side by side and the external surfaces of the sectors () opposite to the axis () define together said external surface (); and'}, {'b': 12', '7', '5', '4, 'a contracted disassembling position in which at least part of said sectors () approaches the axis () moving away from the trace of the surface () to reduce the radial dimensions of the mandrel and allow the extraction of the mandrel itself () from the structural section of the airplane;'}], 'the lamination mandrel () comprises a plurality of sectors () angularly spaced about the axis () and mobile along ...

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Номер записи: 36
14-11-2013 дата публикации

CELLULAR CORE COMPOSITE LEADING AND TRAILING EDGES

Номер: US20130299061A1
Автор: Rodman William L.
Принадлежит:

A complex-shaped, three-dimensional fiber reinforced composite trailing edge structure may be formed by using counteracting pressures applied to a structural lay-up of wetted fibers placed onto pressurizable members to form continuous fore and aft loops. In turn, the loops may be structurally functional to transfer loads from the trailing edge structure to a wing center section. The trailing structure may include may include fillers and/or a metallic insert, wherein the metallic insert may provide a lightening strike capability for the trailing edge structure. 1arranging a plurality of pressurizable members within a tool, each of the pressurizable members having an outer surface and an inner surface defining a volumetric region, each of the pressurizable members further having an opening to permit internal pressurization thereof, wherein the arranged pressurizable members have an approximate configuration of a trailing edge feature;arranging a plurality of fore and aft fiber plies onto at least one surface of the arranged pressurizable members, wherein the aft fiber plies form a continuous first loop and the fore fiber plies form a continuous second loop, and further wherein an intersection of the first and second loops is functionable as a load transferring spar, where a combination of the pressurizable members and fiber plies comprise a pre-cured assembly;pressurizing an outer surface of the pre-cured assembly with a first pressure; andpressurizing the inner surface of at least some of the pressurizable members with a second pressure, wherein the first pressure and the second pressure operate to compress the fiber plies between the pressurizable members and tool to form the trailing edge structure.. A method of manufacturing a trailing edge structure, the method comprising: This application claims priority from U.S. Provisional Patent Application No. 61/619,000 filed on Apr. 2, 2012, and the subject matter of which is incorporated herein by reference in its ...

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Номер записи: 37
14-11-2013 дата публикации

METHOD AND DEVICE FOR REQUIREMENT CAPTURE FOR A SYSTEM FOR CENTRALIZED MAINTENANCE FOR AIRCRAFT

Номер: US20130304303A1
Автор: Albouy Christian, LAVAL Laurent, MARESTIN Pascal
Принадлежит: THALES

A requirement capture device for a centralized maintenance system for aircraft is composed of a means for capturing and parametrizing the various characteristics of the centralized maintenance system. It allows the various parties to the fine tuning of the CMS system to define the data set specific to their domain in a common framework. User profiles are defined for each of the users affording them configuration possibilities specific to their domain. After validation of the parameters input, a configuration file is generated. 1. A requirement capture device for a centralized maintenance system (CMS) for aircraft , the device comprising:a module for inputting parameters relating to configuration domains for the CMS;a verification module coupled to the input module for verifying the compliance of the parameters input with the configuration domains for the CMS;a generating module coupled to the input module for generating requirement capture files; anda storage module for storing the requirement capture files generated.2. The device according to claim 1 , further comprising a module for defining the configuration domains.3. The device according to claim 1 , further comprising a user profiles management module coupled to the input module.4. The device according to claim 1 , wherein the input module further comprises a Man-Machine Interface.5. The device according to claim 1 , wherein the input module further comprises means of interaction with a user.6. The device according to claim 1 , wherein the storage module comprises a first module for storing the data relating to the definition of the configuration domain and a second module for storing the requirement capture files generated.7. The device according to claim 1 , comprising six configuration domains for defining:information characterizing the Member Systems connected to the CMS system;links between the CMS system and all the connected Member Systems and the interfaces with the systems providing the aircraft's ...

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Номер записи: 38
28-11-2013 дата публикации

STRINGER, AIRCRAFT WING PANEL ASSEMBLY, AND METHOD OF FORMING THEREOF

Номер: US20130316147A1
Автор: DOUGLAS Paul, Petitt David Patrick Stephane
Принадлежит: AIRBUS OPERATIONS LIMITED

Embodiments of the invention relate to a stringer () adapted to transport fluid in an aircraft wing (). For example, the stringer may be adapted to provide venting to one or more fuel tanks () in the aircraft wing, or may be adapted to provide fuel to the one or more fuel tanks. To perform this function, the stringer comprises a duct member () providing a duct and a structural member () providing an attachment surface for attachment of the stringer to a wing panel (). Typically, the stringer is formed from a composite material such as carbon fibre reinforced plastic. A method of manufacturing the stringer is also disclosed. 1. An aircraft wing panel assembly comprising: a wing panel with an inner surface; a stringer comprising a duct member and a structural member providing an attachment surface which attaches the stringer to the inner surface of the wing panel; and a packer between the duct member and the inner surface of the wing panel which caters for deviations of the inner surface of the wing panel.2. An assembly according to claim 1 , wherein the packer caters for deviations of the inner surface of the wing panel by varying in thickness along its length.3. An assembly according to claim 2 , wherein the packer caters for deviations of the inner surface of the wing panel by varying in thickness along its length such that its maximum thickness is more than 50% greater than its minimum thickness.4. (canceled)5. (canceled)6. (canceled)7. (canceled)8. (canceled)9. (canceled)10. (canceled)11. (canceled)12. (canceled)13. An assembly according to claim 1 , wherein the wing panel has thickness variations which cause the deviations in its inner surface claim 1 , such that thicker regions of the wing panel correspond with thinner regions of the packer claim 1 , and vice versa.14. An assembly according to claim 13 , wherein the wing panel varies in thickness such that its maximum thickness claim 13 , which corresponds with a minimum thickness of the packer claim 13 , is ...

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Номер записи: 39
05-12-2013 дата публикации

Procedure and device for the determination of airspeeds of a rotorcraft in stationary flight and/or at low speeds

Номер: US20130325220A1
Автор: Jean-Paul Pinacho, Jerome Gardes, Philippe Gaulene
Принадлежит: Eurocopter SA

A procedure and a device for the determination of current airspeeds [ 13 ] of a rotorcraft [ 2 ] in a stationary flight regime and/or at low speeds. A calculation system [ 1 ] incorporates two pairs of polynomial calculation laws [ 9] [10 ] that are executable successively by pairs. A pair of first polynomial laws [ 9 ] calculates estimated airspeeds [ 11 ], consisting respectively of longitudinal and lateral airspeeds, and is constructed through multilinear regression based on parameters relating to simulated flight points [ 17 ] defined by means of a flight simulator [ 18 ]. A pair of second polynomial laws [ 10 ] calculates the current airspeeds based on the estimated airspeeds [ 11 ], and is constructed through multilinear regression based on parameters relating to test-flight points defined by means of test flights [ 25].

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Номер записи: 40
05-12-2013 дата публикации

METHOD AND DEVICE FOR DETECTING OSCILATORY FAILURES IN A POSITION SERVOCONTROL SUBSYSTEM OF AN AIRCRAFT CONTROL SURFACE

Номер: US20130325254A1
Автор: Babando Olivier, CAZAURANG Franck, Goupil Philippe, LAVIGNE Loïc, SIFI Mohcine
Принадлежит:

Method and device for detecting oscillatory faults in a positional servocontrol arrangement for an aircraft control surface. The detection device comprises means for estimating a reference position of the control surface, with the aid of a model in which at each iteration a residual value of the previous iteration, multiplied by a dynamic gain, is injected, and means for detecting an oscillatory fault with the aid of this reference position. 1. A method for detecting at least one oscillatory fault in at least one positional servocontrol arrangement of at least one control surface of an aircraft , said servocontrol arrangement forming part of a system of electric flight controls of the aircraft , the system including said control surface which is mobile , and whose position with respect to the aircraft is adjusted by at least one actuator , said actuator which adjusts the position of said control surface , as a function of at least one actuation order received , at least one sensor which measures the actual position of said control surface , and a computer which calculates a control surface control order , which receives said measured actual position and which deduces therefrom an actuation order which is transmitted to said actuator , and the method comprises:a) estimating a theoretical position corresponding to a reference position of said control surface in the absence of any fault with the aid of said control surface control order which feeds a model of said actuator;b) computing the difference between said theoretical position estimated in step a) and the actual position measured by said sensor so as to form a residual value; andc) comparing the residual value with at least one predetermined threshold value; andcounting all the successive and alternate oversteppings of said predetermined threshold value by said residual value, and, as soon as the number resulting from said counting becomes greater than a predetermined number, an oscillatory fault is detected ...

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Номер записи: 41
19-12-2013 дата публикации

METHOD FOR OPTIMISING THE DESIGN OF MANHOLE OPENINGS ON AN AIRCRAFT

Номер: US20130338973A1
Автор: Blanco Pacios Carlos, Delgado Jareño Jose Luis
Принадлежит: AIRBUS OPERATIONS S.L.

Method for optimising the design of sealing rings of internal manhole covers which close the manhole openings over the inner surface of the skin of an aircraft structure, the surface that is in contact with the inner surface of the skin being the optimized surface of said sealing rings, the method including dividing the outer contour and the inner contour of the optimised surface into n points; grouping into families Fthe sealing rings of each manhole opening; generating the curves that are best adapted to the set of points taken for the outer contour and for the inner contour of each sealing ring for each one of the families F; generating a ruled surface among the curves generated for each one of the families F. 1. A method for optimising the design of the sealing rings of internal manhole covers which close the manhole openings over the inner surface of the skin of an aircraft structure , the surface that is in contact with the inner surface of the skin being the optimised surface of said sealing rings , characterized in that said method comprises the following steps:a) Dividing the outer contour of the optimized surface of each sealing ring into n points.b) Dividing the inner contour of the optimized surface of each sealing ring into n points.c) Measuring the distance between each one of the n points of the outer contour of step a) and the inner surface of the skin.d) Measuring the distance between each one of the n points of the inner contour of step b) and the inner surface of the skin.{'sub': 'i', 'e) Grouping into families Fthe different sealing rings of each manhole opening.'}{'sub': 'i', 'f) Taking the minimum measurement of each point ni of each family Ffor the outer contour of each sealing ring in step c), and also for the inner contour of each sealing ring in step d).'}g) Generating the curves which are best adapted to the set of points taken in step f) for the outer contour and for the inner contour of each sealing ring for each one of the families ...

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Номер записи: 42
26-12-2013 дата публикации

SYSTEM AND METHOD FOR GROUND VIBRATION TESTING AND WEIGHT AND BALANCE MEASUREMENT

Номер: US20130340511A1
Автор: Davis George V., Miller Mark E.
Принадлежит: The Boeing Company

An apparatus for lifting an aircraft may include a plurality of lifting mechanisms mounted on a supporting surface. Each lifting mechanism may be configured to impart an upward force on a component of the aircraft for lifting the aircraft off the supporting surface. The apparatus may include a beam structure configured to be mounted to the lifting mechanisms. The apparatus may also include a lifting beam suspended from the beam structure. A measurement device may be mounted to the lifting beam and may be configured to engage a jack point associated with the component to determine a weight of the aircraft when the aircraft is lifted off the supporting surface. 1. An apparatus for supporting an aircraft during ground vibration testing , comprising:a plurality of lifting mechanisms mounted on a supporting surface, each lifting mechanism being configured to impart an upward force on a component of the aircraft for lifting the aircraft off of the supporting surface;a beam structure configured to be mounted to the plurality of lifting mechanisms;a lifting beam suspended from the beam structure; anda measurement device mounted to the lifting beam and being configured to engage a jack point associated with a component of the aircraft and determine a weight of the aircraft when the aircraft is lifted off the supporting surface.2. The apparatus of claim 1 , wherein:the jack point is associated with a landing gear of the aircraft.3. The apparatus of claim 1 , wherein:the beam structure comprises a pair of generally parallel hanger beams mounted to the lifting mechanism and arranged in spaced relation to one another;each one of the hanger beams having a hanger rod extending downwardly therefrom; andthe lifting beam having opposing ends coupled to a hanger rod.4. The apparatus of claim 3 , wherein:the hanger rod is comprised of an upper portion joined to a lower portion by a threaded sleeve; andthe threaded sleeve being adjustable to adjust a total length of the hanger rod.5. ...

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Номер записи: 43
26-12-2013 дата публикации

Device for exciting a landing gear of an aircraft while on the ground

Номер: US20130340528A1
Автор: Bruno Lagarde, Nicolas Botargues
Принадлежит: AIRBUS OPERATIONS SAS

A device for exciting a landing gear of an aircraft while it is on the ground. The device includes an oblong bracing foot, a movable support on which the oblong foot is mounted and an arrangement for setting the gear into vibration.

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Номер записи: 44
09-01-2014 дата публикации

System and method for rigging a control surface of an aircraft

Номер: US20140007397A1
Автор: Denis OEGRETICI, Frank DIERENFELDT, Gerd Stahl
Принадлежит: AIRBUS OPERATIONS GMBH

A system for rigging a control surface of an aircraft, wherein the control surface is movable relative to a reference structure of the aircraft by means of at least one actuator, comprises a mobile control unit having being connectable to at least one actuator, an input means for commanding a deflection of the control surface, and an optical rigging apparatus having a first rigging component and a second rigging component. The first rigging component is adapted for being mounted on a reference structure to which the control surface is swivably attached and the second rigging component is adapted for being mounted on the control surface itself. Thereby an accurate rigging may be conducted with a clearly reduced number of personnel and a clearly reduced time for completion.

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Номер записи: 45
09-01-2014 дата публикации

METHOD FOR PERFORMING DIAGNOSTICS OF A STRUCTURE SUBJECT TO LOADS AND SYSTEM FOR IMPLEMENTING SAID METHOD

Номер: US20140012461A1
Автор: IANNONE Michele
Принадлежит:

A method for performing diagnostics of a structure subject to loads, in particular an aircraft structure, is implemented by an arrangement of sensors located at relevant points of the structure and corresponding neural networks. The method includes training the neural network in order to establish an associative relationship between the state of the structure in a subset of relevant points and the state of the structure in at least one residual relevant point. The state of the structure is detected in a plurality of relevant points under operating conditions. The state of the structure is estimated in at least one residual relevant point by the associated neural network on the basis of the pre-established associated relationship. The state of the estimated structure is compared with the detected state at the residual relevant point, such that an intact state of the structure is determined if the expected and detected values of the state parameter match, or a defective state of the structure is determined if these values differ. 2. Method according to claim 1 , wherein the comparison between the estimated and the detected values of the state parameter is carried out for each relevant detection point.3. Method according to claim 1 , wherein said learning step and said operating step are carried out in a plurality of different load conditions claim 1 , whereby a defective state of the structure is determined when a condition of mismatch exists between the estimated and detected values of the state parameter in a plurality of load conditions claim 1 , while occasional signalling occurs when a condition of mismatch exists between the estimated and detected values of the state parameter in only one load condition or in a plurality of conditions where a load is less than a threshold.4. Method according to claim 1 , wherein the learning step includes collecting a plurality of training data in the form of vectors comprising the values assumed by at least one predetermined ...

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Номер записи: 46
13-02-2014 дата публикации

AUTOMATED INSPECTION OF AIRCRAFT LANDING GEAR INTERNAL FLUID LEVELS

Номер: US20140046533A1
Автор: Nance C. Kirk
Принадлежит:

A system for use in monitoring, measuring, computing and displaying the volumes of internal gas within a telescopic aircraft landing gear strut. Pressure sensors and temperature sensors and motion sensors are mounted in relation to each of the landing gear struts to monitor, measure and record the impact movement and rates of internal landing gear strut fluids; experienced by landing gear struts, as the aircraft landing gear initially come into contact with the ground. The computer of this system measures the compression experienced by each landing gear strut and determines if the landing gear strut is improperly serviced with either excess or deficient volumes of nitrogen gas. Additional features include automating the inspections required to aircraft landing gear, prior to flight, during flight and during landing events. 1. A method of monitoring internal fluid levels in a landing gear on an aircraft , the landing gear comprising a telescopic strut , the internal fluids comprising a compressible fluid and a non-compressible fluid , which telescopic strut is capable of extension , comprising the steps of:a) allowing the strut to fully extend under no load while the aircraft is in flight;b) determining a temperature-compensated pressure of the fluids in the strut while the strut is fully extended under no load;c) comparing the no load temperature compensated pressure of the fluids in the strut, to a predetermined pressure of a properly serviced strut;d) monitoring the temperature-compensated pressure of the strut over elapsed time after the landing gear makes contact with the ground;e) if the no load pressure is below the predetermined pressure, determining from the temperature-compensated pressure of the strut over elapsed time after the landing gear makes contact with the ground the amount of compressible fluid in the strut.2. The method of claim 1 , further comprising the steps of:a) providing a look up table of pressures and corresponding ratio amounts of ...

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Номер записи: 47
27-02-2014 дата публикации

THREE-PIECE AIRCRAFT BRAKE ASSEMBLY CONTAINER AND METHOD OF USING SAME

Номер: US20140054188A1
Автор: Ordonez Jose, Waldron Neil
Принадлежит:

An aircraft brake assembly container having a base or container portion with feet extending therefrom. A further base portion is provided and mounted atop the base portion. A spacing is provided between the base and further base portions and this spacing is filled by a spacing container portion or member. The spacing container portion allows for lower profile base and further base portions while accommodating larger diameter new and used brake assemblies. A method of using same is also provided. 1. An aircraft brake assembly container , comprising:a first container portion of an at least three container portions having an at least one channel therein and releasably securing an at least one cradle member therein with an at least one portion extending from the at least one cradle member to engage and move within said at least one channel and having an at least one void section;a second container portion having an at least one void section such that said second container portion forms a mirror image of said first container portion, said first and second container portions of an at least three container portions fittingly engaging with a third container portion of an at least three container portions said third container portion of an at least three container portions coupling to each of the first and second container portions to form said aircraft brake assembly container;an at least one securement device for securing said first portion and second portion to said third portion, wherein the at least one cradle member is moved along the respective at least one channel in the respective at least one container portion to accommodate an aircraft brake assembly wherein the aircraft brake assembly is in a horizontal orientation relative to the container, wherein the at least one void portion provided on said first or second of the at least three container portions allows an aircraft undercarriage or brake axle to penetrate the container.2. The aircraft brake assembly ...

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Номер записи: 48
27-02-2014 дата публикации

METHOD AND APPARATUS FOR AUTOMATED LAUNCH, RETRIEVAL, AND SERVICING OF A HOVERING AIRCRAFT

Номер: US20140054415A1
Автор: Heavey, III Robert Joseph, McGeer Brian Theodore, McMillan Damon Lucas, Stafford John William
Принадлежит: AEROVEL CORPORATION

An aircraft capable of thrust-borne flight can be automatically retrieved, serviced, and launched. In one embodiment, for retrieval, the aircraft drops a tether and pulls the tether at low relative speed into contact with a horizontal guide. The tether is pulled across the guide until the guide is captured b an end effector. The tether length is adjusted as necessary, and the aircraft swings on the guide to hang in an inverted position. Translation of the tether along the guide then brings the aircraft to a docking carriage, in which the aircraft parks for servicing. For launch, the carriage is swung upright, the end effector is released from the guide, and the aircraft thrusts into free flight. A full ground-handling cycle can thus be accomplished automatically with a simple, economical apparatus. It can be used with low risk of damage and requires moderate accuracy in manual or automatic flight control. 1. An apparatus comprising:(a) a suspension support;(b) a docking carriage supported by the suspension support and configured to receive a flying object:(c) a flying object capturer suspended by the suspension support, the flying object capturer including at least two teeth configured to capture a portion of the fling object therebetween; and(d) a motor operatively coupled to the flying object capturer and configured to move the flying object capturer relative to the suspension support.2. The apparatus of claim 1 , wherein the flying object capturer includes a first set of two teeth and a second different set of two teeth claim 1 , wherein the teeth of the first set are configured to capture the portion of the flying claim 1 , object therebetween and the teeth of the second set are configured to capture the portion of the flying object therebetween.3. The apparatus of claim 1 , which includes a guide supported by the suspension support claim 1 , the guide supporting the flying object capturer.4. The apparatus of claim 3 , wherein the motor is configured to move the ...

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Номер записи: 49
27-02-2014 дата публикации

Aircraft Environmental Sensors and System

Номер: US20140058594A1
Автор: Brian E. Tucker, Charles E. Covington, Larry Plowman
Принадлежит: BELL HELICOPTER TEXTRON INC

According to one embodiment, an aircraft part environmental stress analysis system includes a part failure repository, a part history repository, and a failure analysis engine. The part failure repository is configured to store a plurality of failure records, each failure record identifying a failed aircraft part. The part history repository is configured to store a plurality of part records, each part record storing, for a failed aircraft part, at least one measurement of an aspect of a natural environment of which the failed aircraft part was subject to. The failure analysis engine is operable to compare the plurality of failure records to the plurality of part records and identify at least one potential environmental cause of failure for a plurality of failed aircraft parts based on the comparison.

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Номер записи: 50
27-02-2014 дата публикации

Method and device for counting the number of landings performed by an aircraft tyre

Номер: US20140058621A1
Автор: Lionel Fagot-Revurat
Принадлежит: Compagnie Generale des Etablissements Michelin SCA, Michelin Recherche et Technique SA Switzerland

A number of landings of an aircraft tyre is counted according to a method that includes: measuring a physical quantity of air contained inside the tyre, the measuring taking place in a discontinuous mode; determining at least one indicator relating to the physical quantity; comparing the at least one indicator with a predetermined threshold associated with the tyre; and, if the at least one indicator is greater than the predetermined threshold associated with the tyre, incrementing the number of landings of the tyre.

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Номер записи: 51
06-03-2014 дата публикации

AIRCRAFT MAINTENANCE UNIT

Номер: US20140060589A1
Автор: Amcoff Henrik, Nordlund Sebastian, Nyberg Helena
Принадлежит: EcoServices, LLC

The disclosure relates to a maintenance unit for servicing aircraft during stand-still, comprising electrically powered service and/or maintenance equipment. There is a power input for connecting the unit to an electrical power supply operating at 200/115VAC at 400 Hz. The unit further comprises a transformer and conversion unit (TCU) for transforming the 200/115 VAC/400 Hz power to standard grid voltage at 400/23OVAC at 50 Hz and at least one frequency converter enabling variable frequency of the output voltage, for powering said service and/or maintenance equipment. The maintenance equipment may be a gas turbine engine washing equipment and comprises a water delivery member for supplying water from a water source, a high pressure pump coupled to the water providing means for providing pressurized water, and a high pressure water outlet. 1. An aircraft maintenance and/or servicing unit , comprising: electrically powered equipment; a power input adapted to be connected to an electrical power supply operating at 200/115VAC and 400 Hz; a transformer and conversion unit (TCU) adapted to transform the 200/115 VAC/400 Hz power to standard voltage of 400/230VAC/ at selected frequency and to deliver power to said equipment.2. An aircraft maintenance and/or servicing unit as claimed in claim 1 , wherein the TCU comprises a transformer adapted for transforming the input voltage to a higher voltage claim 1 , and at least one frequency converter adapted for converting the frequency of the input voltage to a lower frequency.3. An aircraft maintenance and/or servicing unit as claimed in claim 2 , wherein the transformer is adapted to transform the voltage from 200/115VAC to 400/230VAC claim 2 , and the frequency converter is adapted to convert the frequency from 400 Hz to between 2 and 50 Hz.4. An aircraft maintenance and/or servicing unit as claimed in claim 1 , further comprising a control unit and a control panel (CP) coupled to the control unit (CU) for enabling controlling ...

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Номер записи: 52
06-03-2014 дата публикации

METHOD AND APPARATUS FOR RETRIEVING A HOVERING AIRCRAFT

Номер: US20140061378A1
Автор: McGeer Brian T., Roeseler Corydon C., von Flotow Andreas H.
Принадлежит: AEROVEL CORPORATION

For retrieval of a hovering aircraft, a cable, bar, or similar fixture is suspended in an approximately horizontal orientation across the retrieval area between two well-separated supports. The aircraft slowly flies into this fixture, which then slides along the aircraft in a direction approximately parallel with the aircraft's thrust line. This leads to the aircraft becoming fastened to the fixture by an interceptor or aircraft capturer, which in alternative embodiments are respectively on the aircraft or the fixture or both. Thrust is then reduced, and the aircraft comes to rest hanging from the fixture for subsequent removal. Retrieval is thus accomplished with simple and economical apparatus, light and unobtrusive elements on the aircraft, low risk of damage, and only moderate piloting accuracy. 1. An apparatus for capturing a flying object , said apparatus comprising:(a) a fixture;(b) a suspension support configured to suspend the fixture; and(c) a docking fixture attached to the suspension support, the docking fixture including an arm configured to engage a portion of the flying object, (i) a member connected to a body of the flying object may contact the fixture by motion of the flying object relative to the fixture,', '(ii) the flying object may translate relative to the fixture toward the docking fixture, and', '(iii) the docking fixture receives the flying object., 'wherein the suspension support is configured to suspend the fixture such that2. The apparatus of claim 1 , wherein the suspension support is configured to suspend the fixture such that the member may contact the fixture such that the member removably attaches to the fixture.3. The apparatus of claim 1 , wherein the docking fixture is configured to enable the flying object to be stowed.4. The apparatus of claim 1 , wherein the docking fixture is configured to enable the flying object to be serviced.5. The apparatus of claim 4 , which is configured to automatically service the flying object.6. ...

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Номер записи: 53
06-03-2014 дата публикации

Long and Short Range Storage and Transmission System on Aircraft Parts

Номер: US20140061382A1
Автор: Tucker Brian E.
Принадлежит: Bell Helicopter Textron Inc.

According to one embodiment, an aircraft part storage system includes a first storage device and a second storage device. The first storage device is configured to be coupled to an aircraft part and operable to store and transmit a first set of information about the aircraft part. The second storage device is configured to be coupled to the same aircraft part and operable to store and transmit a second set of information about the aircraft part. The second storage device has a larger storage capacity than the first storage device but a shorter transmission range than the first storage device. 1. A rotorcraft , comprising:a body;a power train coupled to the body and comprising a power source and a drive shaft coupled to the power source;a hub;a rotor blade coupled to the hub;an aircraft part; and a first storage device coupled to the aircraft part and operable to store and transmit a first set of information identifying the aircraft part; and', 'a second storage device coupled to the same aircraft part and operable to store and transmit a second set of information about the aircraft part, the second storage device having a larger storage capacity than the first storage device but a shorter transmission range than the first storage device., 'an aircraft part storage system comprising2. The rotorcraft of claim 1 , wherein the first storage device comprises a radio-frequency identification tag.3. The rotorcraft of claim 1 , wherein the second storage device comprises a contact memory button.4. The rotorcraft of claim 3 , wherein the first set of information identifying the aircraft part comprises a part number unique to a category of parts.5. The rotorcraft of claim 3 , wherein the first set of information identifying the aircraft part comprises a serial number unique to the individual aircraft part.6. The rotorcraft of claim 1 , wherein the second set of information about the aircraft part comprises a maintenance history of the aircraft part.7. The rotorcraft of claim ...

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Номер записи: 54
06-03-2014 дата публикации

Bonded Composite Aircraft Wing

Номер: US20140061385A1
Автор: Dan-Jumbo Eugene
Принадлежит: The Boeing Company

A unitized composite aircraft wing includes upper and lower composite laminate wing skins that have differing stiffnesses and are bonded to a composite grid structure. The grid structure includes grid spars extending in a span-wise direction, and cross beams extending in a chord-wise direction of the wing. The grid spars include caps bonded to the upper and lower wing skins. 1. An aircraft wing , comprising:upper and lower composite wing skins respectively having differing stiffnesses; anda wing-grid structure located between and attached to each of the upper and lower wing skins.2. The aircraft wing of claim 1 , wherein:the wing-grid structure includes a plurality of intersecting composite support members bonded together.3. The aircraft wing of claim 2 , wherein:the composite support members include wing-grid spars extending in a span-wise direction of the wing and bonded to each of the upper and lower composite wing skins, andthe upper and lower composite wing skins and the wing-grid structure form a unitized bonded wing structure.4. The aircraft wing of claim 1 , wherein:the upper composite wing skin has a stiffness less than the stiffness of the lower composite wing skin.5. The aircraft wing of claim 1 , wherein:each of the upper and lower wing skins is orthotropic and has an interlaminar fracture toughness, andwherein the interlaminar fracture toughness of the upper composite wing skin is less than the interlaminar fracture toughness of the lower composite wing skin.6. The aircraft wing of claim 5 , wherein:{'sup': 2', '2, 'the upper composite wing skin has an interlaminar fracture toughness in Mode I of between approximately 3.0 in-lbs/inand approximately 5.0 in-lbs/in, and'}{'sup': 2', '2, 'the lower composite wing skin has an interlaminar fracture toughness in Mode I between approximately 4.5 in-lbs/inand approximately 6.5 in-lbs/in.'}7. The aircraft wing of wherein the upper and lower composite wing skins having at least one differing characteristic ...

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Номер записи: 55
06-03-2014 дата публикации

Aircraft Engine Stand

Номер: US20140061559A1
Автор: Paul Spinazze, Sherry Drake
Принадлежит: Tronair Inc

This mobile, aircraft engine stand provides mobility and ease of operation by one person. The stand includes a frame, a pair of vertical jack screws vertically mounted on the frame and a precision rail system configured to allow for stable and efficient linear motion. A pair of quick change, engine lifting arms are attached to the pair of vertical jack screws; and an electrical control and control panel make unloading, transporting, assembling and moving an engine a one person operation. A plurality of casters allows for easy swiveling of the stand.

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Номер записи: 56
20-03-2014 дата публикации

METHOD OF FORMING A WINDOW CUTOUT IN AN AIRFRAME

Номер: US20140076477A1
Автор: Kismarton Max U.
Принадлежит: The Boeing Company

A method of forming cutouts in an aircraft fuselage may include forming a first cutout and a second cutout in side-by-side relation to one another in a side region of the fuselage. The method may further include configuring the first cutout and the second cutout such that a direct load path extends along the side region substantially continuously from a lower portion of the side region generally under the first cutout to an upper portion of the side region generally over the second cutout. 1. A method of forming cutouts in an aircraft fuselage , comprising the steps of:forming a first cutout and a second cutout in side-by-side relation to one another in a side region of a fuselage; andconfiguring the first cutout and the second cutout such that a direct load path extends along the side region substantially continuously from a lower portion of the side region generally under the first cutout to an upper portion of the side region generally over the second cutout.2. The method of claim 1 , further comprising the steps of:determining a bending moment on the fuselage;determining a shear load generated in the side region in response to the bending moment; andconfiguring the first cutout and the second cutout such that a path of the shear load extends along the side region substantially continuously from the lower portion under the first cutout to the upper portion over the second cutout.3. The method of claim 2 , further comprising the steps of:determining a cabin pressurization load on the fuselage;determining a hoop tension load generated in the side region by the cabin pressurization load;determining a path of a resultant of the shear load and the hoop tension load; andconfiguring the first cutout and the second cutout such that the resultant load path extends along the side region substantially continuously from the lower portion under the first cutout to the upper portion over the second cutout.4. The method of claim 1 , wherein the side region includes a skin ...

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Номер записи: 57
20-03-2014 дата публикации

METHOD AND APPARATUS FOR RETRIEVING A HOVERING AIRCRAFT

Номер: US20140077028A1
Автор: McGeer Brian T., Roeseler Corydon C., von Flotow Andreas H.
Принадлежит:

For retrieval of a hovering aircraft, a cable bar, or similar fixture is suspended in an approximately horizontal orientation across the retrieval area between two well-separatod supports. The aircraft slowly flies into this fixture, which then sides along the aircraft in a direction approximately parallel with the aircraft's thrust. line.. This leads to the aircraft becoming fastened to the fixture by an interceptor or aircraft capturer, which in alternative embodiments are respectively on the aircraft or the fixture or both. Thrust is then reduced, and the aircraft comes to rest hanging from the fixture for subsequent removal. Retrieval is thus accomplished with simple and economical apparatus, light unobtrusive elements on the aircraft, low risk of damage, and only moderate piloting accuracy. 1. A method for capturing a flying object , said method comprising:(a) causing a member connected to a body of the flying object to contact a fixture by motion of the flying object relative to the fixture;(b) thereafter, translating the flying object relative to the fixture toward a docking fixture;(c) receiving the flying object in the docking fixture; and(d) engaging a portion of the flying object with an arm of the docking fixture.2. The method of claim 1 , wherein causing the member to contact the fixture includes causing the member to contact the fixture such that the member removably attaches to the fixture.3. The method of claim 1 , which includes stowing the flying object after the docking fixture receives the flying object.4. The method of claim 1 , which includes servicing the flying object after the docking fixture receives the flying object.5. The method of claim 4 , wherein said servicing is performed automatically.6. The method of claim 1 , which includes facilitating launch of the flying object after the docking fixture receives the flying object.7. The method of claim 1 , which includes holding said portion of the flying object with the arm.8. The method of ...

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Номер записи: 58
27-03-2014 дата публикации

METHOD FOR MANUFACTURING A SOUND ATTENUATION PANEL

Номер: US20140083798A1
Автор: Maze Franck, MOUTIER John
Принадлежит: AIRCELLE

The present disclosure provides a method for manufacturing a sound attenuation panel having a first cellular core structure and a second cellular core structure joined in a junction area (J), the first and second cellular core structures. The method includes: a) a joining edge of the first cellular core structure is joined to a corresponding joining edge of the second cellular core structure, thereby forming the junction area; b) the first cellular core structure and the second cellular core structure are placed between an inner skin and an outer skin of the panel. 1. A method for manufacturing a sound attenuation panel comprising a first cellular core structure and a second cellular core structure joined in a junction area (J) , the first and second cellular core structures each comprising at least one cellular core layer ,wherein:a) a joining edge of the first cellular core structure having a cellular core is joined to a corresponding joining edge of the second cellular core structure having a cellular core, thereby forming the junction area;b) the first cellular core structure and the second cellular core structure are placed between an inner skin and an outer skin of the panel,wherein the method further comprises:a step prior to step a), in which at least one junction reinforcement is inserted between the joining edge of the first cellular core structure and the corresponding joining edge of the second cellular core structure in the junction area, said junction reinforcement extending in a plane transverse to the first and the second cellular core structures, anda subsequent step in which the first and second cellular core structures and the junction reinforcement are secured together using a connecting means.2. The method according to claim 1 , wherein the junction reinforcement is indexed and fixed on a mold.3. The method according to claim 1 , wherein the junction reinforcement is not pierced.4. The method according to claim 1 , wherein the height of the ...

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Номер записи: 59
03-04-2014 дата публикации

System and method for manufacturing a wing panel

Номер: US20140090252A1
Автор: Antonio C. Micale, Azita N. NAMDARAN, Chris G. COUEVAS, Clayton L. Munk, Daniel R. Smith, Darrell D. Jones, Donald A. MOTTAZ, Edward John BATT, Farahnaz Tanni SISCO, James N. Buttrick, Jayson J. AQUINO, Mario RAMOS, Noman S. NOOR
Принадлежит: Boeing Co

A system and method are provided to automate the assembly of a wing panel, such as utilized by commercial aircraft. In the context of a system, a tacking cell is provided that is configured to tack one or more stringers to a skin plank. The system also includes a riveting cell configured to receive a tacked plank from the tacking cell and to rivet the one or more stringers to the skin plank. The system also includes a splicing cell configured to receive a plurality of riveted planks from the riveting cell and to attach one or more splice stringers to the plurality of riveted planks. Further, the system includes a side of body cell configured to receive a spliced panel from the splicing cell and to attach a side of body chord thereto to produce a wing panel.

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Номер записи: 60
03-04-2014 дата публикации

METHOD AND APPARATUS FOR AUTOMATED LAUNCH, RETRIEVAL, AND SERVICING OF A HOVERING AIRCRAFT

Номер: US20140091176A1
Автор: McGeer Brian T., von Flotow Andreas H.
Принадлежит:

Various embodiments of the present disclosure provide an apparatus configured to automatically retrieve, service, and launch an aircraft. For retrieval, the aircraft drops a weighted cable, and pulls it at low relative speed into a broad aperture of the apparatus. In certain instances, the cable is dragged along guiding surfaces of the apparatus into and through a slot until its free end is captured. The aircraft becomes anchored to the apparatus, and is pulled downward by the cable into a receptacle. Guiding surfaces of the receptacle adjust the position and orientation of a probe on the aircraft, directing the probe to mate with a docking fixture of the apparatus. Once mated, the aircraft is automatically shut down and serviced. When desired, the aircraft is automatically started and tested in preparation for launch, and then released into free flight. A full ground-handling cycle is thus accomplished with a simple, economical apparatus. 1. An apparatus for retrieving a flying object from free flight , said apparatus comprising:(a) a base; and (i) a member holder configured to receive a member connected to a body of the flying object and hold the member after receiving the member, and', '(ii) a member mover configured to move the member relative to the docking station to cause the flying object to move toward the docking station., '(b) a docking station supported by the base and configured to receive a portion of the flying object, the docking station including2. The apparatus of claim 1 , wherein the member mover is configured to move the member relative to the docking station until the docking station receives the portion of the flying object.3. The apparatus of claim 2 , wherein the docking station includes a sensor configured to detect when the docking station receives the portion of the flying object claim 2 , and wherein the member mover is configured to stop moving the member relative to the docking station when the sensor detects that the docking station ...

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Номер записи: 61
03-04-2014 дата публикации

METHOD AND APPARATUS FOR AUTOMATED LAUNCH, RETRIEVAL, AND SERVICING OF A HOVERING AIRCRAFT

Номер: US20140091177A1
Автор: McGeer Brian T., von Flotow Andreas H.
Принадлежит:

Various embodiments of the present disclosure provide an apparatus configured to automatically retrieve, service, and launch an aircraft. For retrieval, the aircraft drops a weighted cable, and pulls it at low relative speed into a broad aperture of the apparatus. In certain instances, the cable is dragged along guiding surfaces of the apparatus into and through a slot until its free end is captured. The aircraft becomes anchored to the apparatus, and is pulled downward by the cable into a receptacle. Guiding surfaces of the receptacle adjust the position and orientation of a probe on the aircraft, directing the probe to mate with a docking fixture of the apparatus. Once mated, the aircraft is automatically shut down and serviced. When desired, the aircraft is automatically started and tested in preparation for launch, and then released into free flight. A full ground-handling cycle is thus accomplished with a simple, economical apparatus. 1. A method for retrieving a flying object from free flight , said method comprising:(a) causing a member connected to a body of the flying object to be received by a member holder of a docking station, the docking station supported by a base and configured to receive a portion of the flying object;(b) thereafter, causing the member holder to hold the member; and(c) causing a member mover of the docking station to move the member relative to the docking station to cause the flying object to move toward the docking station.2. The method of claim 1 , which includes causing the member mover to move the member relative to the docking station until the docking station receives the portion of the flying object.3. The method of claim 2 , which includes detecting when the docking station receives the portion of the flying object using a sensor and stopping the movement of the member relative to the docking station when the sensor detects that the docking station receives the portion of the flying object.4. The method of claim 1 , which ...

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Номер записи: 62
07-01-2016 дата публикации

METHOD AND APPARATUS FOR AUTOMATED MULTI-DRILLING AND MULTI-RIVET MACHINE

Номер: US20160001350A1
Автор: Amirehteshami David Hassan, IV John W., Pringle, Wright Rodney Stephen
Принадлежит:

Method and apparatus for assembling, with fasteners, components of a structure having an outboard side, an inboard side, and a supporting frame. The components are placed together on the frame. An electromagnet having a core with multiple openings is positioned on the outboard side. A magnetically attractive member is placed against the inboard side opposite and aligned with the electromagnet. When activated, the electromagnet is attracted towards the magnetically attractive member and the two hold the components together. Multiple drill members pass through the openings in the core of the electromagnet and multiple openings are drilled simultaneously through the components. Subsequently, multiple rivets or huck bolts are simultaneously inserted into the drilled openings. 1. An apparatus for performing at least one step for assembling first and second unassembled components of a structure with fasteners , said structure having a preexisting frame supporting said first and second unassembled components , said frame having an outboard side and an inboard side , said first and second unassembled components having a combined fastener-receiving zone , said apparatus comprising:a first robotic member positioned adjacent said outboard side;an electromagnet mounted on said first robotic member for moving said electromagnet between an operative position and an inoperative position;said operative position being against said combined fastener-receiving zone on said outboard side;said electromagnet having a central magnetizable core with multiple openings in said central magnetizable core and an electrical coil surrounding said central magnetizable core;a second robotic member positioned adjacent said outboard side;a tool carrier operatively mounted on said second robotic member for operative passage of tools through said multiple openings in said central magnetizable core of said electromagnet;a magnetically attractive member mounted on said inboard side aligned with said ...

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Номер записи: 63
05-01-2017 дата публикации

Method, device and system for assembly of a plurality of panels

Номер: US20170001734A1
Автор: Franck Darras, Yannick Wattier
Принадлежит: Stelia Aerospace SAS

The invention relates to a device for assembling a plurality of panels of an aircraft fuselage, said device comprising at least one anvil body, comprising a surface for supporting the said plurality of panels, the said anvil body comprising at least one anvil rail mounted movably in a cavity of the anvil body and configured to move between a top position in which the upper surface of the anvil rail extends into the extension of the support surface and a bottom position in which a workspace is created between the upper surface of the anvil rail and the support surface so as to allow a machining and/or stripping tool to pass through.

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Номер записи: 64
05-01-2017 дата публикации

METHOD AND SYSTEM FOR ASSEMBLY OF A PLURALITY OF PANELS

Номер: US20170001735A1
Автор: Darras Franck, Wattier Yannick
Принадлежит:

The invention relates to a system for assembling a plurality of panels of an aircraft fuselage, said system comprising at least one anvil body, at least one first panel and one second panel, and movement means mounted on the said anvil body, the said movement means being arranged to move the first panel in relation to the second panel between a first machining position in which one edge of the first panel and one edge of the second panel are spaced a machining distance apart so as to allow a machining tool to pass between the said edges in order to machine them simultaneously and a second welding position in which the said edge of the first panel and the said edge of the second panel are adjacent and resting on the said anvil body. 115.-. (canceled)16. A system for assembling a plurality of panels of an aircraft fuselage , the plurality of panels comprising at least one first panel and at least one seond panel , the system comprising:at least one anvil body comprising a support surface supporting the plurality of panels;at least one anvil rail movably mounted in a cavity of the at least one anvil body and configured to move between a top position in which an upper surface of the at least one anvil rail extends into an extension of the support surface and a bottom position in which a workspace is created between the upper surface of the at least one anvil rail and the support surface so as to enable the passage of a tool; the at least one anvil rail comprising a structural beam extending along the at least one anvil body and a guide bar for the tool; andmovement means mounted on the at least one anvil body, the movement means being arranged to move the at least one first panel in relation to the at least one second panel between a first machining position in which an edge of the at least one first panel and an edge of the at least one second panel are spaced a machining distance apart so as to allow the tool to pass between the edges of the at least one first panel ...

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Номер записи: 65
07-01-2016 дата публикации

BRIDGE ADAPTED FOR ACCESSING AN AIRCRAFT COMPARTMENT VIA A MANHOLE

Номер: US20160002869A1
Автор: Matignon Mickaël
Принадлежит:

A bridge configured to allow access by an operative to an aircraft compartment via a manhole formed in a wall. The bridge comprises an overlapping section which includes at least one plate, a transverse runner beneath the plate or plates with at least one groove configured to receive a lower edge of the manhole, at least a first support configured to rest on one side of the wall and at least a second support configured to rest on the other side of the wall. 1. A bridge configured to allow an operative to access an aircraft compartment via a manhole formed in a wall , said bridge comprising:an overlapping section including at least one plate,a transverse runner beneath the at least one plate with at least one groove configured to receive a lower edge of the manhole,at least a first support configured to rest on a first side of the wall, andat least a second support configured to rest on a second side of the wall.2. The bridge according to claim 1 , further comprising at least one fixing member for hooking a ladder to the bridge.3. The bridge according to claim 1 , further comprising a platform positioned in an extension of the overlapping section on the second side of the wall and a detachable connection which assures a junction between the platform and the overlapping section.4. The bridge according to claim 3 , further comprising a suspension to support the platform claim 3 , at least one cable attaching said platform to said suspension and a detachable fixing to attach said suspension to an aircraft structure above the bridge.5. The bridge according to claim 4 , wherein the suspension comprises a bar and two cables claim 4 , each attached to one end of said bar claim 4 , and wherein the platform comprises a supporting cross member that extends on either side of the platform claim 4 , the ends of said cross member being attached to the cables.6. The bridge according to claim 5 , wherein the suspension comprises claim 5 , in addition to the bar claim 5 , a first arm ...

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Номер записи: 66
03-01-2019 дата публикации

FRANGIBLE FASTENERS WITH FLEXIBLE CONNECTORS FOR UNMANNED AIRCRAFT, AND ASSOCIATED SYSTEMS AND METHODS

Номер: US20190003511A1
Автор: Leon Michael Matthew, Rubesh Kristian
Принадлежит:

Frangible fasteners with flexible connectors for unmanned aircraft, and associated systems and methods are disclosed. A representative aircraft includes a fuselage portion, a wing portion, a winglet carried by the wing portion, and a frangible fastener coupling the winglet portion to the wing portion. The frangible fastener can include an outer body with a first portion in contact with the wing portion, a second portion in contact with the winglet portion, and a frangible portion between the first and second portions. A flexible member is positioned at least partially within the outer body and is connected to the first portion so as to extend through and out of the second portion. A stop element is carried by the flexible member. 1. An unmanned aircraft , comprising:a fuselage portion;a wing portion;a winglet carried by the wing portion; and an outer body with a first portion in contact with the wing portion, a second portion in contact with the winglet portion, and a frangible portion between the first and second portions;', 'a flexible member positioned at least partially within the outer body, connected to the first portion, and extending through and out of the second portion; and', 'a stop element carried by the flexible member., 'a frangible fastener coupling the winglet portion to the wing portion, the frangible fastener including2. The aircraft of wherein the flexible member is crimped to the first portion.3. The aircraft of wherein the flexible member includes a cable.4. The aircraft of wherein the flexible member includes a solid wire.5. The aircraft of wherein the stop element is crimped to the flexible member.6. The aircraft of wherein the outer body has a hollow internal cavity with an opening toward one end of the outer body claim 1 , and wherein the flexible member includes a cable having a first end positioned within the hollow cavity and fixedly attached to the outer body claim 1 , the cable extending through the opening and away from the outer body ...

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Номер записи: 67
01-01-2015 дата публикации

METHOD FOR DETECTING A FAILURE OF AT LEAST ONE SENSOR ONBOARD AN AIRCRAFT IMPLEMENTING AN ANEMO-INERTIAL LOOP, AND ASSOCIATED SYSTEM

Номер: US20150006019A1
Автор: DARBONNEAU Francois-Xavier
Принадлежит:

A method for detecting a failure of at least one sensor on board an aircraft is provided. The method includes implementing an anemo-inertial loop including obtaining a computed horizontal speed, based on an integration of a measured horizontal acceleration and obtainment of a short-term anemo-inertial speed from the computed horizontal speed; developing at least one intermediate loop parameter based on a deviation between the short-term anemo-inertial speed and the anemometric speed or the airspeed; and observing a failure detection parameter obtained from an intermediate parameter of the anemo-inertial loop and determining the presence of a failure on one of the sensors of the aircraft, based on the value of the observed failure detection parameter. 1. A method for detecting a failure of at least one sensor on board an aircraft comprising:measuring a horizontal acceleration;measuring an anemometric speed or an airspeed; obtaining a computed horizontal speed, based on an integration of the measured horizontal acceleration and obtaining a short-term anemo-inertial speed from the computed horizontal speed;', 'developing at least one intermediate loop parameter based on a deviation between the short-term anemo-inertial speed and the anemometric speed or the airspeed; and', 'looping on the measured horizontal acceleration, before integration, according to the value of at least one intermediate parameter;, 'implementing an anemo-inertial loop in a computer, the anemo-inertial loop comprisingobserving at least one failure detection parameter obtained from the at least one intermediate loop parameters of the anemo-inertial loop; anddetermining the presence of a failure on one of the sensors of the aircraft based on the value of the observed failure detection parameter.2. The method as recited in wherein the determining includes comparing the value of the observed failure detection parameter and a given predetermined threshold.3. The method as recited in wherein the anemo- ...

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Номер записи: 68
01-01-2015 дата публикации

Method for detecting a failure of at least one sensor onboard an aircraft implementing a baro-inertial loop, and associated system

Номер: US20150006020A1
Автор: Francois-Xavier D'ARBONNEAU
Принадлежит: Dassault Aviation SA

A method for detecting a failure of at least one sensor onboard an aircraft implementing a baro-inertial loop is provided. The method includes implementing a baro-inertial loop including obtaining a computed vertical speed, then a short-term baro-inertial altitude, based on a double integration of the measured vertical acceleration; and developing at least one intermediate loop parameter based on a deviation between the short-term baro-inertial altitude and the pressure altitude. The method also includes observing at least one failure detection parameter obtained from one of the intermediate parameters of the baro-inertial loop; and determining the presence of a failure on one of the sensors of the aircraft based on the value of the observed failure detection parameter.

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Номер записи: 69
03-01-2019 дата публикации

Computing Techniques for Three-Dimensional Modeling and Design Analysis

Номер: US20190005185A1
Автор: "DAntuono Raymond P.", Mukundakrishnan Bharath, Pavanaskar Sushrut S., Rajnarayan Dev G.
Принадлежит:

Techniques and systems for creating and performing analysis on three-dimensional computer models are described. The model creation and analysis may be specified using an un-compiled script that includes a set of instructions. The set of instructions may implement a computer-aided design (CAD) kernel using a bridge layer that includes compiled bridge code. The instructions may be used to create a job set having a group of tasks. Using the job set, a processing queue may be constructed, the processing queue having a subset of common tasks prioritized within the processing queue. Subsets or groups of tasks or instructions may also be executed in parallel using multiple distinct processors or a multi-threaded processor. 1. A computer-implemented method for analyzing a computer model of an airplane assembly , the method comprising:obtaining an un-compiled script having a set of instructions for analyzing the computer model of the airplane assembly, the airplane assembly including a set of components that defines at least a portion of an aeronautical surface; constructing a nominal solid model for each component of the set of components by implementing a computer-aided design (CAD) kernel using a compiled bridge layer;', 'constructing a nominal mesh of discrete elements for each nominal solid model;', 'constructing a delta solid model for at least one component of the set of components, the delta solid model having at least one parameter that is incrementally varied with respect to the nominal solid model;', 'constructing a delta mesh of discrete elements for the delta solid model and at least one nominal solid model; and', 'performing an analysis using either or both the nominal mesh and/or the delta mesh;, 'creating a job set comprising a group of tasks specified by the set of instructions, the group of tasks comprising tasks foridentifying a subset of common tasks within the group of tasks;generating a task order by prioritizing the subset of common tasks with respect ...

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Номер записи: 70
08-01-2015 дата публикации

System and method of rotorcraft usage monitoring

Номер: US20150007666A1
Автор: Allen Altman, Bang Nguyen, Brian Tucker, Robert Wardlaw, Tom Wood
Принадлежит: BELL HELICOPTER TEXTRON INC

A method of monitoring usage of a component of an aircraft can include: monitoring a usage of the component by using a torque measurement system to calculate torque events in a time period; categorizing the usage of the component by assigning a usage value based upon whether the number of torque events in the period of time is above or below a threshold; and determining a life used of the component.

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Номер записи: 71
12-01-2017 дата публикации

MACHINING APPARATUS AND MACHINING METHOD

Номер: US20170008102A1
Автор: Ishikawa Yuichi, MIYASHITA Yasushi, RIHEI Atsushi, YAMASHITA Saichiro
Принадлежит:

According to one implementation, a machining apparatus includes an electromotive saw and an attaching structure. The electromotive saw cuts off a workpiece to be machined. The attaching structure attaches the saw to an arm of a robot. Further, according to one implementation, a machining method is provided. In the machining method, a machined product is manufactured by processing a composite material or a honeycomb structure with a cutting tool attached to an arm of a robot. Further, according to one implementation, a machining method is provided. In the machining method, a machined product is manufactured by processing a workpiece to be machined with a cutting tool attached to an arm of a robot. The workpiece is processed along a shape of a jig for setting the workpiece. The workpiece is processed with contacting a guide with the jig. The guide is attached to the arm. 1. A machining apparatus comprising:an electromotive saw that cuts off a workpiece to be machined; andan attaching structure that attaches the saw to an arm of a robot.2. The machining apparatus according to claim 1 , further comprising:a guide for copying processing along a shape of a jig for setting the workpiece to be machined, the copying processing being performed by contacting the guide with the jig.3. The machining apparatus according to claim 1 , further comprising the robot.4. The machining apparatus according to claim 2 , further comprising the robot.5. The machining apparatus according to claim 2 , further comprising:the robot;a sensor that measures a force applied on the guide from the jig; anda control circuit that performs a feedback control of the robot, based on a measurement result by the sensor, to make the force applied on the guide from the jig be constant.6. A machining method claim 2 ,wherein a machined product is manufactured by processing a composite material or a honeycomb structure with a cutting tool attached to an arm of a robot.7. A machining method claim 2 ,wherein a ...

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Номер записи: 72
12-01-2017 дата публикации

System for Developing Composite Repair Patches on Aircraft or Other Composite Structures

Номер: US20170008184A1
Автор: Brown Brian M., Salah Lamia, Tomblin John
Принадлежит:

A system for generating a repair patch for a damaged area of a composite structure may include a scanning module, a repair patch model generator and a cutting tool. The scanning module may be deployed at the location of the damaged composite structure. The scanning module may be configured to scan the damaged area to generate scanned data indicative of a shape, size and/or contours of the damaged area. The repair patch model generator may include processing circuitry configured to obtain the scanned data, obtain parent ply information of the damaged composite structure, and generating a patch model of a repair patch including size and shape definition for each of a plurality of plies based on the scanned data and the parent ply information. The cutting tool may be configured to receive cutting files based on the patch model to generate a plurality of cut plies that combine to form the repair patch. 16-. (canceled)7. A system for generating a repair patch for a damaged area of a composite structure , the system comprising:a scanning module deployable on-site at a location of the composite structure, the scanning module being configured to scan the damaged area to generate scanned data indicative of a shape, size and/or contours of the damaged area; obtain the scanned data;', 'obtain parent ply information of the composite structure; and', 'generate a patch model of a repair patch including size and shape definition for each of a plurality of plies based on the scanned data and the parent ply information, wherein the patch model is generated on-site at the location of the composite structure; and, 'a repair patch model generator comprising processing circuitry configured toa cutting tool located remote from the location of the composite structure and configured to receive cutting files based on the patch model to generate a plurality of cut plies that are separately cut and assembled remote from the location of the composite structure to form the repair patch for ...

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Номер записи: 73
12-01-2017 дата публикации

REPAIR APPARATUS AND METHOD FOR COMPOSITE PANELS HAVING A CONDUCTIVE LAYER

Номер: US20170008268A1
Автор: Ackerman Patrice K., Anderson Weston K., Heeter Russell J.
Принадлежит:

A repair apparatus for an electrically conductive layer of a composite structure includes a dielectric layer, having a perimeter, secured to the composite structure, a first adhesive layer, and a conductive layer, secured over the dielectric layer and to the composite structure via the first adhesive layer around an entirety of the perimeter of the dielectric layer, the first adhesive layer being scored along a perimeter region thereof to improve a conductive path between the conductive layer and the composite structure. 1. A repair apparatus for an electrically conductive layer of a composite structure , comprising:a dielectric layer, having a perimeter, secured to a composite structure;a first adhesive layer;a conductive layer, secured over the dielectric layer and to the composite structure via the first adhesive layer around an entirety of the perimeter of the dielectric layer, the first adhesive layer being scored along a perimeter region thereof to improve a conductive path between the conductive layer and the composite structure.2. The repair apparatus of claim 1 , wherein the dielectric layer has a thickness of 2-8 mils and a dielectric constant of about 2 to 5.3. The repair apparatus of claim 1 , wherein the conductive layer has a thickness of 8-12 mils and an equivalent conductivity of aluminum having a thickness of 8-12 mils.4. The repair apparatus of claim 1 , wherein the electrically conductive layer of the composite structure comprises a copper foil grid layer that is integrally included in the composite structure.5. The repair apparatus of claim 1 , where in the composite structure comprises a portion of an aircraft.6. The repair apparatus of claim 5 , wherein the composite structure comprises a skin panel of the aircraft.7. The repair apparatus of claim 1 , further comprising a sealing composition claim 1 , applied around a perimeter of the conductive layer.8. The repair apparatus of claim 1 , wherein the dielectric layer comprises polyester.9. The ...

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Номер записи: 74
03-01-2019 дата публикации

INTEGRATED WIRING SYSTEM FOR COMPOSITE STRUCTURES

Номер: US20190008065A1
Автор: Dalal Hardik, Duce Jeffrey Lynn, Merriweather Breana K., Robbins Brent A., Rosillo Yelina
Принадлежит:

A composite part comprising an electronic device and method for making the same. A primer is deposited on a surface of the composite part. An electronic device comprising a group of conductive elements is deposited on the primer. Power may be supplied to a device connected to the composite part through current flowing through the group of conductive elements. 1. An apparatus comprising:a composite part;a primer deposited on a surface of the composite part; andan electronic device comprising a group of conductive elements deposited on the primer, wherein power is supplied to a device connected to the composite part through current flowing through the group of conductive elements.2. The apparatus of claim 1 , wherein the primer comprises:a layer of metallic material sprayed on the surface of the composite part using a thermal plasma spray; anda layer of ceramic material sprayed on the layer of metallic material using the thermal plasma spray.3. The apparatus of claim 1 , wherein conductive material is sprayed on the primer using a thermal plasma spray to form the group of conductive elements.4. The apparatus of claim 3 , wherein the conductive material is selected from at least one of copper claim 3 , copper alloy claim 3 , carbon claim 3 , graphene claim 3 , titanium claim 3 , nickel claim 3 , or silver.5. The apparatus of claim 1 , wherein the composite part is an aircraft part.6. The apparatus of claim 5 , wherein the composite part is selected from one of a skin panel claim 5 , an interior panel claim 5 , a stringer claim 5 , a frame claim 5 , a spar claim 5 , a wing claim 5 , a winglet claim 5 , a fuselage claim 5 , an empennage claim 5 , and a control surface.7. The apparatus of claim 1 , wherein the group of conductive elements comprises at least one of an electrical trace claim 1 , an interconnect claim 1 , a wire claim 1 , a transistor claim 1 , an integrated circuit claim 1 , or a conductive connector.8. The apparatus of claim 1 , wherein the device ...

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Номер записи: 75
12-01-2017 дата публикации

Body Fuel Tank Critical Gap Measurement and Validation Template

Номер: US20170008645A1
Автор: Pham Rosemary D., Taylor John W.
Принадлежит: The Boeing Company

A tank is coupled to a body assembly of the fuselage of an aircraft with a lug of the tank mounted on a pin coupled to a body assembly. The pin is marked using a special tool with a first location mark and a second location mark. The lug of the tank may be mounted on the pin. To verify that the tank is correctly located on the pin, the position of the lug may be compared to two marks disposed on the pin. When the respective marks are visible on either side of the lug, the tank is properly aligned on the pin and the tank can be secured to the body assembly. The process is particularly helpful when the pin is located in an area that is inaccessible for direct observation or measurement after the tank is in place. 1. A method of attaching a tank with a lug onto a pin of a body assembly of an aircraft fuselage , the method comprising:disposing a first location mark on the pin;disposing a second location mark on the pin;mounting the lug onto the pin between the first location mark and the second location mark;determining that the lug has no overlap with the first location mark;determining that the lug has no overlap with the second location mark; andattaching the tank to the body assembly.2. The method of claim 1 , further comprising adjusting a location of the tank relative to the body assembly when the lug overlaps one of the first location mark or the second location mark.3. The method of claim 1 , further comprising attaching a tool to the pin claim 1 , the tool having a first aperture and a second aperture.4. The method of claim 3 , wherein disposing the first location mark comprises marking the pin at the first aperture claim 3 , and wherein disposing the second location mark comprises marking the pin at the second aperture.5. The method of claim 4 , further comprising removing the tool prior to installation of the tank and after disposing the first and second location marks on the pin.6. The method of claim 3 , wherein attaching the tool to the pin comprises: ...

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Номер записи: 76
12-01-2017 дата публикации

EXTERIOR INDEXING PROCESS AND TOOLING

Номер: US20170008646A1
Автор: CHARLTON Craig, HUCKEY Andrew Michael, NESTLEROAD Mark Edward, WHORTON William Shawn, WILSON Jake Aspen
Принадлежит:

Method and apparatus for aligning fastener holes of two components. An alignment fixture includes two mating fixtures. Each mating fixture includes a reference plate that is aligned to the fastener holes of one of the components. Each mating fixture also includes an alignment device. The alignment devices can be aligned with the respective reference plates such that the alignment between the reference plates and the fastener holes are transferred to the alignment devices. Once aligned, the alignment devices can be temporarily attached to the respective components at locations away from the fastener holes. The reference plates can then be removed. Thereafter, the components can be brought together such that mating features on the alignment devices engage. Engagement of the mating features aligns the two components such that the fastener holes on the components are aligned. 1. A method for aligning a first component and a second component , wherein the first component includes a first plurality of fastener holes , wherein the second component includes a second plurality of fastener holes , and wherein the first plurality of fastener holes and the second plurality of fastener holes are alignable to receive fasteners that join the first component and the second component , the method comprising:attaching a first reference plate to at least two of the fastener holes of the first plurality of fastener holes in the first component;aligning mating features of a first alignment device with cooperating mating features of the first reference plate, thereby placing the at least two fastener holes and the first alignment device in a predefined relative arrangement;having placed the at least two fastener holes and the first alignment device in the predefined relative arrangement, attaching the first alignment device to the first component;attaching a second reference plate to at least two of the fastener holes of the second plurality of fastener holes in the second component; ...

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Номер записи: 77
12-01-2017 дата публикации

LANDING GEAR SHOCK ABSORBER SERVICING

Номер: US20170008647A1
Автор: POUNTNEY Oliver, SHEPHERD Alan
Принадлежит:

A method and apparatus for servicing a shock absorber on a landing gear assembly of an aircraft in a weight-on-wheels state is disclosed. The shock absorber includes at least one chamber containing both hydraulic fluid and a gas in fluid communication with each other. The apparatus includes a source of gas and a source of hydraulic fluid. The amount of hydraulic fluid in the chamber is corrected, preferably such that the chamber is then filled with a known amount of degassed hydraulic fluid. The process may be at least semi-automatically performed, for example under the control of a control unit. By delivering a pre-set mass of gas into the chamber, there is no need to rely on a measure of gas pressure or H-dimension (h) when servicing the shock absorber, and more accurate servicing of a shock absorber may thus be provided. 1. A portable apparatus for servicing a shock absorber on a landing gear assembly of an aircraft when the aircraft is in a weight on wheels configuration , the shock absorber comprising at least one chamber containing both hydraulic fluid and a gas in fluid communication with each other , wherein the apparatus comprises:a source of gas,a source of hydraulic fluid, anda gas delivery system for delivering a pre-set mass of gas into the shock absorber, the gas delivery system including a tank that is arranged both to receive gas from a shock absorber and to deliver gas to the shock absorber.2. An apparatus according to claim 1 , wherein the tank has a variable volume.3. An apparatus according to claim 2 , wherein the apparatus includes an actuator which is arranged to effect a change in the volume of the variable volume tank.4. An apparatus according to claim 1 , wherein the apparatus comprises a control unit configured to control the delivery by the gas delivery system of the pre-set mass of gas into the shock absorber.5. An apparatus according to claim 4 , wherein the control unit is configured to receive an input from an input device that reads ...

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Номер записи: 78
12-01-2017 дата публикации

SERVICING OF LANDING GEAR SHOCK ABSORBERS

Номер: US20170008648A1
Автор: POUNTNEY Oliver, SHEPHERD Alan
Принадлежит:

A method and portable apparatus for servicing a shock absorber on a landing gear assembly of an aircraft in a weight-on-wheels state is disclosed. The shock absorber includes at least one chamber containing both hydraulic fluid and a gas in fluid communication with each other. The apparatus includes a source of gas and a source of hydraulic fluid. The amount of hydraulic fluid in the chamber is corrected, preferably such that the chamber is then filled with a known amount of degassed hydraulic fluid. A pre-set mass of gas is then delivered into the chamber under the control of a gas delivery system of the portable apparatus. More accurate servicing of a shock absorber may thus be provided since account is additionally taken of gas dissolved in hydraulic fluid. By delivering a pre-set mass of gas into the chamber, there is no need to rely on a measure of gas pressure or H-dimension (h) when servicing the shock absorber. 1. A method of servicing a shock absorber on a landing gear assembly of an aircraft , the shock absorber comprising at least one chamber containing both hydraulic fluid and a gas in fluid communication with each other , wherein the method comprises the following steps all conducted whilst the weight of the aircraft is at least partially supported by the landing gear assembly:exhausting all gas from the chamberdegassing at least some dissolved gas from the hydraulic fluidensuring that one or more set criteria, which depend on the amount of hydraulic fluid in the chamber are met, including if so required adjusting the amount of hydraulic fluid in the chamber anddelivering a pre-set mass of gas into the chamber.2. A method according to claim 1 , wherein during the step of exhausting all gas from the chamber claim 1 , the volume of the chamber reduces so that the shock absorber contracts claim 1 , and the method further includes a step of using a stop which is arranged to resist further contraction of the shock absorber.3. A method according to claim 1 , ...

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Номер записи: 79
14-01-2016 дата публикации

Wheel Mounting System

Номер: US20160009155A1
Автор: Do Quang T., Gudzinski Gregory, IV Richard Griffith, Kozak Michael J., Miller Jeffrey Lawrence, Oberoi Harinder S., Reese
Принадлежит:

A method and apparatus for installing a wheel arm assembly for an autonomous vehicle. The wheel arm assembly may be inserted into a base of the autonomous vehicle from the exterior of the base. A number of fasteners may be installed at the exterior of the base to attach the wheel arm assembly to the base of the autonomous vehicle. 1. An apparatus comprising:a retaining structure associated with a base of a vehicle; anda wheel arm assembly coupleable to the retaining structure at an exterior of the base.2. The apparatus of claim 1 , wherein the wheel arm assembly is coupleable to the retaining structure from a first end of the retaining structure located at the exterior of the base.3. The apparatus of claim 1 , wherein the wheel arm assembly is coupleable from the exterior of the base without requiring disassembly of any portion of the base.4. The apparatus of claim 1 , wherein the retaining structure has a first channel.5. The apparatus of claim 1 , wherein the retaining structure comprises:a first end that faces externally with respect to the vehicle; anda second end that faces internally with respect to the vehicle.6. The apparatus of claim 5 , wherein the retaining structure has a first channel that extends from the first end to the second end and wherein the wheel arm assembly is located within the first channel when the wheel arm assembly is coupled to the retaining structure.7. The apparatus of claim 4 , wherein the wheel arm assembly comprises:a retainer bushing.8. The apparatus of claim 7 , wherein the retainer bushing enables coupling and decoupling of the wheel arm assembly from the exterior of the base.9. The apparatus of claim 7 , wherein the retainer bushing comprises a first end claim 7 , a second end claim 7 , and a second channel that extends from the first end of the retainer bushing to the second end of the retainer bushing.10. The apparatus of claim 7 , wherein the retainer bushing comprises:a flange at a first end of the retainer bushing.11. The ...

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Номер записи: 80
14-01-2016 дата публикации

EXPANDED AIRLINER CONFIGURED SYMMETRICALLY REAR TO FRONT OR REAR TO REAR

Номер: US20160009415A1
Автор: Uitdenbogerd Brian Lee
Принадлежит:

Currently the world's largest airplane is Airbus A380, can carry 525 people in a normal three-class configuration. It can travel nonstop 15,700 kilometers (8,500 nmi; 9,800 mi), at a speed of Mach 0.85 (about 900 Km/h or 560 mph; 490 kn at cursing altitude). To carry twice as many passengers and fly the same distance with the similar performance or better can achieved by joining the two same types of airplanes in the rear to front, (FIG. ), or rear to rear (FIG. ), can have the equivalent or better effect, and have similar or better performance than keep on building larger, fatter, airplanes such as A380. For example, Airbus, A350 can carry 350 passengers in a three-class setting, if the two A350s are jointed, it can carry, 700 passengers instead of only 350. This will work on other makers with the two same types of large airplanes. 145. Two in one. Two airliners joined together to one airliner. It pears to be one long airliner but it is not. It is two separate airliner joined rear to front to have one cockpit. Two in one but all the parts and functions will work as one airliner. No changes in the production of the airliners except for the last part where the two airliners are joined. All the parts and functions are to work together as one. Except for the Tail end may need a larger vertical and horizontal stabilizers to better control the longer weight and load in the front. As indicated in . Airliners are extended almost the twice of its length. By joining two same type of airliners rear to the front to make its appearance to look like one long airliner but it is two airliners joined rear to front to work together as one airliner , , . , is where it is joined and it would be the center of gravity , make this point a point of perfect balance and strongest part of the fuselages of the aircraft. The two fuselages will be attached using a newly designed large bulkhead frame and skin splice at each intersection.245. As indicated in . Airliners are extended almost the ...

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Номер записи: 81
14-01-2016 дата публикации

Mobile Platforms for Performing Operations Inside a Fuselage Assembly

Номер: US20160009416A1
Автор: Barrick Kevin Marion, Do Quang T., Draper Alan S., Gudzinski Gregory, IV Richard Griffith, Miller Jeffrey Lawrence, Oberoi Harinder S., Reese
Принадлежит:

A method and apparatus for performing an assembly operation. A tool may be macro-positioned within an interior of a fuselage assembly. The tool may be micro-positioned relative to a particular location on a panel of the fuselage assembly. An assembly operation may be performed at the particular location on the panel using the tool. 1. A method for performing an assembly operation , the method comprising:macro-positioning a tool within an interior of a fuselage assembly;micro-positioning the tool relative to a particular location on a panel of the fuselage assembly; andperforming the assembly operation at the particular location on the panel using the tool.2. The method of claim 1 , wherein macro-positioning the tool comprises:moving a platform base of an internal mobile platform carrying the tool with at least one degree of freedom relative to a floor inside the fuselage assembly.3. The method of claim 2 , wherein micro-positioning the tool comprises:moving the tool with the at least one degree of freedom relative to the platform base.4. The method of claim 2 , wherein micro-positioning the tool comprises:commanding at least one of an internal robotic device or a movement system associated with the internal mobile platform to move the tool with the at least one degree of freedom relative to the platform base to the particular location.5. The method of claim 1 , wherein macro-positioning the tool comprises:driving an internal mobile platform carrying the tool across a floor within the interior of the fuselage assembly.6. The method of claim 2 , wherein driving the internal mobile platform comprises:driving the internal mobile platform carrying the tool across the floor within the interior of the fuselage assembly to an internal position relative to the panel of the fuselage assembly.7. The method of claim 2 , wherein driving the internal mobile platform comprises:driving the internal mobile platform across the floor inside the fuselage assembly using a track system.8 ...

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Номер записи: 82
14-01-2016 дата публикации

Dual-Interface Coupler

Номер: US20160009417A1
Автор: Do Quang T., Draper Alan S., IV Richard Griffith, Kozak Michael J., Miller Jeffrey Lawrence, Oberoi Harinder S., Reese, Stojanoski Vanco
Принадлежит:

A method for coupling a number of utilities between a first system and a second system is provided. A first interface that couples the number of utilities between the first system and the second system is created between the first system and a utilities unit. The first interface is activated. A second interface between the second system and the utilities unit is deactivated, while the first interface remains activated. 1. A method for coupling a number of utilities between a first system and a second system , the method comprising:creating a first interface between the first system and a utilities unit that couples the number of utilities between the first system and the second system;activating the first interface; anddeactivating a second interface between the second system and the utilities unit while the first interface remains activated.2. The method of claim 1 , wherein creating the first interface comprises:creating the first interface autonomously.3. The method of claim 1 , wherein creating the first interface comprises:mating a first coupling unit associated with the utilities unit with a first corresponding coupling unit associated with the first system to create the first interface.4. The method of further comprising:creating the second interface that mechanically couples the utilities unit to the second system prior to the first interface being created; andactivating the second interface prior to the first interface being created.5. The method of claim 4 , wherein creating the second interface comprises:mating a second coupling unit associated with the utilities unit with a second corresponding coupling unit associated with the second system to create the second interface.6. The method of claim 1 , wherein activating the first interface comprises:activating the first interface autonomously.7. The method of claim 1 , wherein deactivating the second interface comprises:deactivating the second interface autonomously.8. The method of claim 1 , wherein ...

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Номер записи: 83
14-01-2016 дата публикации

Clamping Feet for an End Effector

Номер: US20160009418A1
Автор: Arriaga Jorge Alberto, Draper Alan S., Findlay Melissa Ann, Oberoi Harinder S., Sarh Branko
Принадлежит:

An attachment for an end effector. The attachment may include a clamp and a foot adhesively bonded to an edge of the clamp and having a set of interlocking features that form a mechanical interlock with the clamp. 1. An apparatus comprising:a clamp; anda foot adhesively bonded to an edge of the clamp and having a set of interlocking features that form a mechanical interlock with the clamp.2. The apparatus of claim 1 , wherein the set of interlocking features increase a cohesive strength of an interface between a first element and a second element.3. The apparatus of claim 2 , wherein the set of interlocking features give the interface between the first element and the second element cohesive strength to resist bending forces.4. The apparatus of claim 1 , wherein the set of interlocking features is a set of projections.5. The apparatus of claim 2 , wherein the second element further comprises:a base portion, wherein the set of interlocking features extend from the base portion.6. The apparatus of claim 5 , wherein an interlocking feature in the set of interlocking features comprises:an elongated portion that extends from the base portion of the second element.7. The apparatus of claim 6 , wherein the interlocking feature further comprises:a locking portion located at an end of the elongated portion and having a first width greater than a second width of the elongated portion.8. The apparatus of claim 7 , wherein the locking portion is a circular portion having a diameter greater than the second width of the elongated portion.9. The apparatus of claim 6 , wherein the elongated portion extends from the base portion of the second element at an angle relative to an interface between the base portion and the edge of the first element.10. The apparatus of claim 9 , wherein the angle is between about 5 degrees and about 85 degrees relative to the interface.11. The apparatus of claim 6 , wherein the elongated portion extends substantially perpendicularly from the base ...

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Номер записи: 84
14-01-2016 дата публикации

Towers for Accessing an Interior of a Fuselage Assembly

Номер: US20160009419A1
Автор: Barrick Kevin Marion, Do Quang T., Draper Alan S., Gerosa Alfredo Jose, Hu Yuanxin Charles, IV Richard Griffith, Kozak Michael J., Oberoi Harinder S., Reese
Принадлежит:

A method and apparatus for accessing an interior of a fuselage assembly. A tower having a number of platform levels may be driven into a selected tower position within an assembly area. The interior of the fuselage assembly may be accessed using the number of platform levels. 1. A method for accessing an interior of a fuselage assembly , the method comprising:driving a tower having a number of platform levels into a selected tower position within an assembly area; andaccessing the interior of the fuselage assembly using the number of platform levels.2. The method of claim 1 , wherein driving the tower comprises:driving the tower autonomously into the selected tower position.3. The method of further comprising:building an assembly fixture proximate to the tower.4. The method of further comprising:engaging a plurality of panels with the assembly fixture to build the fuselage assembly.5. The method of claim 3 , wherein accessing the interior comprises:accessing the interior of the fuselage assembly while the fuselage assembly is being supported by the assembly fixture.6. The method of further comprising:accessing at least one of a number of floors within the interior of the fuselage assembly from the number of platform levels of the tower.7. The method of further comprising:mating the number of platform levels of the tower to a number of floors of the fuselage assembly.8. The method of claim 7 , wherein mating the number of platform levels of the tower to the number of floors of the fuselage assembly comprises:aligning a ramp system associated with one of the number of platform levels to a corresponding one of the number of floors.9. The method of claim 7 , wherein mating the number of platform levels of the tower to the number of floors of the fuselage assembly comprises:aligning the number of platform levels to the number of floors using at least one of a plurality of stabilizing members or a ramp system.10. The method of claim 9 , wherein aligning the number of ...

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Номер записи: 85
14-01-2016 дата публикации

Assembly Fixture for Supporting a Fuselage Assembly

Номер: US20160009420A1
Автор: Barrick Kevin Marion, Do Quang T., Draper Alan S., Gerosa Alfredo Jose, Gudzinski Gregory, IV Richard Griffith, Oberoi Harinder S., Reese, Sarh Branko
Принадлежит:

A method and apparatus for building an assembly fixture for holding a fuselage assembly. A number of cradle fixtures may be driven across a floor to an assembly area. The number of cradle fixtures may be configured to form the assembly fixture. 1. A method for building an assembly fixture , the method comprising:driving a number of cradle fixtures across a floor to an assembly area; andconfiguring the number of cradle fixtures to form the assembly fixture.2. The method of further comprising:engaging a plurality of fuselage sections with the assembly fixture to build a fuselage assembly.3. The method of further comprising:supporting the fuselage assembly using the assembly fixture such that the fuselage assembly meets outer mold line requirements and inner mold line requirements within selected tolerances.4. The method of claim 1 , wherein configuring the number of cradle fixtures comprises:micro-positioning a number of retaining structures associated with each of the number of cradle fixtures.5. The method of claim 4 , wherein micro-positioning the number of retaining structures comprises:micro-positioning each of the number of retaining structures associated with the each of the number of cradle fixtures using data acquired from a laser tracking system.6. The method of further comprising:driving, autonomously, the number of cradle fixtures into a number of selected cradle positions.7. The method of claim 6 , wherein driving claim 6 , autonomously claim 6 , the number of cradle fixtures comprises:driving, autonomously, the number of cradle fixtures into the number of selected cradle positions relative to a tower.8. The method of claim 7 , wherein driving claim 7 , autonomously claim 7 , the number of cradle fixtures into the number of selected cradle positions comprises:macro-positioning the number of cradle fixtures using a number of radar sensors.9. The method of claim 7 , wherein driving claim 7 , autonomously claim 7 , the number of cradle fixtures into the ...

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Номер записи: 86
14-01-2016 дата публикации

Adjustable Retaining Structure for a Cradle Fixture

Номер: US20160009421A1
Автор: Alfredo Jose Gerosa, Branko Sarh, Gregory Gudzinski, Harinder S. Oberoi, Kevin Marion Barrick, Quang T. Do, Richard Griffith Reese, Iv, Yuanxin Charles Hu
Принадлежит: Boeing Co

A method and apparatus for adjusting an adjustable retaining structure. The adjustable retaining structure may be rotated, passively, about a spherical interface as a panel applies a load to the adjustable retaining structure.

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Номер записи: 87
14-01-2016 дата публикации

Autonomous Flexible Manufacturing System for Building a Fuselage

Номер: US20160009422A1
Автор: Arriaga Jorge Alberto, Barrick Kevin Marion, Do Quang T., Draper Alan S., Findlay Melissa Ann, Gerosa Alfredo Jose, Hu Yuanxin Charles, IV Richard Griffith, Kozak Michael J., Miller Jeffrey Lawrence, Oberoi Harinder S., Reese, Sarh Branko
Принадлежит:

A method and apparatus for building a fuselage assembly for an aircraft. A number of fixtures may be drive across a floor to an assembly area to form an assembly fixture. The fuselage assembly may be built on the assembly fixture. 1. A method for building a fuselage assembly for an aircraft , the method comprising:driving a number of fixtures across a floor to an assembly area to form an assembly fixture; andbuilding the fuselage assembly on the assembly fixture.2. The method of claim 1 , wherein building the fuselage assembly comprises:building the fuselage assembly on the assembly fixture using a plurality of mobile platforms.3. The method of further comprising:distributing a number of utilities to the plurality of mobile platforms through a distributed utility network.4. The method of claim 1 , wherein driving the number of fixtures comprises:driving a number of cradle fixtures into a number of selected cradle positions to form the assembly fixture.5. The method of claim 4 , wherein driving the number of cradle fixtures comprises:driving the number of cradle fixtures autonomously into the number of selected cradle positions to form the assembly fixture.6. The method of further comprising:driving a tower into a selected tower position relative to a utility fixture located in the assembly area.7. The method of claim 6 , wherein driving the number of fixtures comprises:driving a number of cradle fixtures into a number of selected cradle positions relative to the tower to form the assembly fixture.8. The method of further comprising:coupling a number of utilities between a tower and a utility fixture.9. (canceled)10. The method of claim 8 , wherein coupling the number of utilities between the tower and the utility fixture comprises:coupling the tower to the utility fixture autonomously to enable a flow of the number of utilities from the utility fixture to the tower.11. The method of further comprising:coupling the number of utilities between the tower and the ...

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Номер записи: 88
14-01-2016 дата публикации

METHOD OF DETECTING A LEAK PAST A DYNAMIC SEAL IN AIRCRAFT LANDING GEAR

Номер: US20160009423A1
Автор: Steel Graeme
Принадлежит: MESSIER-BUGATTI-DOWTY

A leak detection method for detecting a leak past a dynamic seal in aircraft landing gear () comprising: a strut (); a rod () slidably mounted in the strut; and a bearing () fitted to an end () of the strut to guide the rod (). The bearing includes a bushing () having a seal () arranged to rub against the rod () to provide sealing between the strut and the rod, defines a fluid chamber (), and a stop nut () for preventing the bushing from moving relative to the strut. The method includes a step of installing a test nut () without a wiper seal in the place of the stop nut (), the step of putting the hydraulic fluid in the landing gear under pressure, and the step of verifying the existence of a leak of hydraulic fluid on the outside surface () of the rod (). 1100. A leak detection method for detecting a leak past a dynamic seal in aircraft landing gear () comprising at least:{'b': '10', 'a strut ();'}{'b': '20', 'a rod () slidably mounted in the strut; and'}{'b': 70', '11', '20', '50', '62', '20', '2', '40', '64, 'a bearing () fitted to an end () of the strut to guide the rod (), said bearing including at least one bushing () having at least one dynamic seal () arranged to rub against the rod () in order to provide sealing between the strut and the rod, thereby defining a chamber () filled with hydraulic fluid between the strut and the rod, and a stop nut () for preventing the bushing from moving in translation relative to the strut and provided with at least one wiper seal () arranged to wipe hydraulic fluid on the rod;'}{'b': 3', '40', '22, 'the method being characterized in that it includes a step of installing a test nut () without a wiper seal in the place of the stop nut (), the step of putting the hydraulic fluid in the landing gear under pressure, and the step of verifying the existence of a leak, if any, of hydraulic fluid on the outside surface () of the rod.'}210062. A method according to for detecting a leak in aircraft landing gear () claim 1 , wherein ...

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Номер записи: 89
14-01-2016 дата публикации

THREE-PIECE AIRCRAFT BRAKE ASSEMBLY CONTAINER AND METHOD OF USING SAME

Номер: US20160009424A1
Автор: Ordonez Jose, Waldron Neil
Принадлежит: Bill Thomas Associates, Inc.

An aircraft brake assembly container having a base or container portion with feet extending therefrom. A further base portion is provided and mounted atop the base portion. A spacing is provided between the base and further base portions and this spacing is filled by a spacing container portion or member. The spacing container portion allows for lower profile base and further base portions while accommodating larger diameter new and used brake assemblies. A method of using same is also provided. 1. An aircraft brake assembly container , comprising:a first container portion of an at least three container portions having an at least one channel therein and releasably securing an at least one cradle member therein and with an at least one void section;a second container portion having an at least one channel therein and releasably securing an at least one cradle member therein and with an at least one void section such that said second container portion is identical to said first container portion,an at least one load spreading protrusion extending from at least one of the first or and second of an at least three container portions to spread the load of the brake assembly when stacked and providing lifting cavities in said first or second of an at least three container portionsa third of the at least three container portions, said first and second container portions of an at least three container portions fittingly engaging with said third container portion of an at least three container portions, said third container portion of an at least three container portions coupling to each of the first and second container portions and filling the void section in each portion with a corresponding tab portion extending from both a top and a bottom of the third container portion into the identical first and second container portions and said second of an at least three container portions is stacked atop said third container portion which is stacked atop said first of the at ...

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Номер записи: 90
11-01-2018 дата публикации

Interior component carrier system and method for mounting an interior component carrier system

Номер: US20180009520A1
Автор: Benthien Hermann, HINRICHS Marcus, METTEN Martin, MUELLER Florian, TELKAMP Michael, TINCANI Tancredi
Принадлежит:

An interior component carrier system comprises a first and second installation rail. Each rail includes at least one connecting portion connectable to an associated primary structure component to fasten the rail to the component, and a carrier portion extending from the connecting portion in a direction along a longitudinal axis of the system. The system further comprises a first carrier element having a first end connected to a first carrier rod extending in a direction along the longitudinal axis and a second end connectable to a first interior component, wherein the first carrier rod is fastened to the carrier portion of the first rail, and a second carrier element having a first end connected to a second carrier rod extending in the longitudinal axis direction and a second end connected to the first carrier element, wherein the second carrier rod is fastened to the second rail carrier portion. 1. An interior component carrier system comprising: at least one connecting portion being connectable to an associated primary structure component in order to fasten the installation rail to the primary structure component, and', 'a carrier portion extending from the connecting portion in a direction along a longitudinal axis of the interior component carrier system,, 'a first and a second installation rail, each of the first and the second installation rails including'}a first carrier element having a first end connected to a first carrier rod extending in a direction along the longitudinal axis of the interior component carrier system and a second end which is connectable to a first interior component, wherein the first carrier rod is fastened to the carrier portion of the first installation rail, anda second carrier element having a first end connected to a second carrier rod extending in a direction along the longitudinal axis of the interior component carrier system and a second end connected to the first carrier element, wherein the second carrier rod is fastened to ...

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Номер записи: 91
12-01-2017 дата публикации

METHODS FOR USE IN COVERING A PORTION OF A FASTENER PROTRUDING FROM A SURFACE

Номер: US20170009797A1
Автор: Cameron Michael Scott, Rawdon Blaine Knight
Принадлежит:

A system for use in covering a portion of a fastener protruding from a surface is provided. The system includes a cap that includes an interior, a base that at least partially delimits the interior, and pawls on the interior. The system may also include a tooth configured to be associated with the fastener and configured to positively engage the pawls. 120-. (canceled)21. A method of covering a portion of a fastener protruding from a surface , said method comprising:providing a cap that comprises a wall, a base, an interior at least partially delimited by the wall and the base, and pawls located in the interior of the cap, the wall having an interior surface, each of the pawls comprising a first end, proximal to the interior surface, and a second end, distal from the interior surface, wherein the second ends of all the pawls are equidistant from the base;coupling a tooth to the fastener;covering the portion of the fastener with the cap; andpositively engaging the pawls with the tooth.22. The method in accordance with claim 21 , wherein positively engaging the pawls with the tooth comprises loading the pawls in compression against the tooth.23. The method in accordance with claim 21 , wherein positively engaging the pawls with the tooth comprises loading the pawls in tension against the tooth.24. The method in accordance with claim 21 , wherein positively engaging the pawls with the tooth comprises elastically deforming the pawls relative to the tooth prior to positively engaging the pawls with the tooth.25. The method in accordance with claim 21 , wherein positively engaging the pawls with the tooth comprises biasing the pawls against the tooth.26. (canceled)27. The method in accordance with claim 21 , wherein coupling the tooth to the fastener comprises threadably engaging a nut claim 21 , which comprises the tooth claim 21 , with the fastener.28. The method in accordance with claim 21 , wherein coupling the tooth to the fastener comprises coupling the tooth to the ...

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Номер записи: 92
08-01-2015 дата публикации

ASSEMBLY INSPECTION SYSTEM AND METHOD

Номер: US20150012171A1
Автор: BERNDT Dirk, GARMANN Daniel, RICHTER Ingo, SAUER Steffen, SCHOMACKER Michael, SCHWANZAR Sebastian, TROSTMANN Erik
Принадлежит:

A method for inspecting assembly of components in a structure includes acquiring a visual representation of at least a portion of the structure, and saving an electronic file of the visual representation on a computer readable medium. A three-dimensional design of the structure, which contains information on a proper position of the components within the structure, is accessed. The visual representation is compared with the three-dimensional design using a computer, and a feedback indicating a result of the comparison is generated. 1. A method for inspecting assembly of components in an aircraft structure , comprising:acquiring a visual representation of at least a portion of the structure;saving an electronic file of the visual representation on a computer readable medium;accessing a three-dimensional design of the structure, the three dimensional design containing information on a proper position of the components within the structure;comparing the visual representation with the three-dimensional design using a computer; andgenerating a feedback indicating a result of the comparison.2. The method of claim 1 , further comprising automatically compiling a list of inspection stations relative to the structure based on the three-dimensional design.3. The method of claim 2 , further comprising compiling a list of inspection stations that are inaccessible for acquisition of the visual representation.4. The method of claim 2 , wherein the acquiring of the visual representation is performed using an optical sensor.5. The method of claim 4 , wherein the optical sensor is a stereoscopic sensor having at least two digital cameras.6. The method of claim 4 , wherein the method further comprises developing an inspection path for a conveyance device configured to selectively position the visual sensor at each inspection station in response to commands provided by the controller.7. The method of claim 1 , wherein comparing the visual representation with the three-dimensional ...

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Номер записи: 93
15-01-2015 дата публикации

METHOD FOR MOUNTING A PYLON TO AN AIRCRAFT

Номер: US20150013142A1
Автор: West Randall Ray
Принадлежит:

An assembly and method for attaching an engine pylon to an aircraft wing. The method may include attaching a first forward wing-mounted fitting to the pylon at a first side of the pylon between upper and lower spars of the pylon and attaching a second forward wing-mounted fitting to the pylon at a second side of the pylon between the upper and lower spars of the pylon. The second side of the pylon is located opposite of the first side of the pylon. Mechanical attachment devices may be inserted through holes on the sides of the pylon aligned with holes formed through the forward wing-mounted fittings. The mechanical attachment devices may be made of steel and the forward wing-mounted fittings may be made of composite or aluminum material. 1. A method of attaching an engine pylon to an aircraft wing , the method comprising:attaching a first forward wing-mounted fitting to the pylon at a first side of the pylon between upper and lower spars of the pylon; andattaching a second forward wing-mounted fitting to the pylon at a second side of the pylon between the upper and lower spars of the pylon, wherein the second side of the pylon is located opposite of the first side of the pylon.2. The method of claim 1 , further comprising attaching a rear wing-mounted fitting to a rear end of the pylon.3. The method of claim 1 , further comprising a step of attaching the forward wing-mounted fittings to a front spar of the wing.4. The method of claim 1 , further comprising attaching a center wing-mounted fitting located between the first and second forward wing-mounted fittings to the pylon at or proximate to the first and second sides of the pylon via center attachment links such that the center attachment links angle toward each other at ends attached to the center wing-mounted fitting.5. The method of claim 1 , further comprising attaching at least one brace to the pylon and the wing claim 1 , providing an alternate failsafe load path should any of the wing-mounted fittings fail. ...

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Номер записи: 94
11-01-2018 дата публикации

Computer-implemented method for space frame design, space frame construction kit and space frame

Номер: US20180011965A1
Автор: Dale Zhao, Damon Lau, Danil Nagy, David Benjamin
Принадлежит: Autodesk Inc

A computer-implemented method for space frame design involves constructing a load stress map in a geometrical boundary representation of a design space, defining attachment points and load application points in the design space, creating a starting network of interconnecting lines between each two of the attachment points and load application points in the design space, assigning load application factors to each line of the starting network of interconnecting lines based on values of the load stress map, generating potential space frame designs by culling different subsets of lines of the starting network of interconnecting lines for each potential space frame design according to variable culling parameters, evaluating the potential space frame designs with respect to optimization parameters, combining the culling parameters for the potential space frame designs the performance score of which is above a predefined performance threshold, and iterating the steps of generating potential space frame designs and evaluating the potential space frame designs on the basis of the combined culling parameters.

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Номер записи: 95
19-01-2017 дата публикации

METROLOGY SYSTEM FOR GENERATING MEASUREMENTS OF FUSELAGE SECTIONS

Номер: US20170015440A1
Автор: Hunt Jeffrey H., Saint Clair Jonathan M., Walls Stephen A., Whelan David Arthur
Принадлежит:

Methods and an apparatus for processing fuselage sections. Measurements of a first fuselage section are generated using a scanning system. The scanning system includes a first scanner and a second scanner. The first scanner generates measurements of a first portion of the first fuselage section and the second scanner generates measurements of a second portion of the first fuselage section. The first fuselage section is held in a cradle system. The measurements of the first portion of the first fuselage section are combined with the measurements of the second portion of the first fuselage section to generate an ensemble of measurements of the first fuselage section. Using the cradle system, one or more of the first fuselage section or a second fuselage section are shaped based on the ensemble of measurements. Using the cradle system, the first fuselage section is joined with the second fuselage section. 1. A method for joining fuselage sections , the method comprising:generating measurements of a first fuselage section using a scanning system, wherein the scanning system includes a first scanner and a second scanner, wherein the first scanner generates measurements of a first portion of the first fuselage section and the second scanner generates measurements of a second portion of the first fuselage section, wherein the first fuselage section is held in a cradle system;combining the measurements of the first portion of the first fuselage section with the measurements of the second portion of the first fuselage section to generate an ensemble of measurements of the first fuselage section;shaping, using the cradle system, one or more of the first fuselage section or a second fuselage section based on the ensemble of measurements; andjoining, using the cradle system, the first fuselage section to the second fuselage section.2. The method of further comprising:placing targets on an exterior surface of the first fuselage section.3. The method of claim 2 , wherein the ...

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Номер записи: 96
18-01-2018 дата публикации

Aircraft Monument Floor Mounting System

Номер: US20180016008A1
Автор: Davidson Merv, Payne Elizabeth M.
Принадлежит:

In an illustrative embodiment, a system for mounting an aircraft monument partition to an aircraft cabin surface such as a floor may include a mounting structure fitted within and attached to a floor-abutting edge of the monument partition, the mounting structure including a mounting opening. A securement apparatus for securing the monument partition to cabin surface via the mounting structure may include a threaded fastener for extending through the mounting opening of the mounting structure and through a corresponding opening in a track mounted to the cabin surface, and a bridging washer for mating with the mounting opening; where, to secure the monument partition to the floor of the cabin area, the threaded fastener is provided through the mounting opening of the mounting structure and threaded to a mating fixture on a bottom side of the track. 1. A system for adjustably mounting a partition of an aircraft monument to a cabin surface , the system comprising:a mounting structure fitted within and attached to an edge of the partition abutting the cabin surface, the mounting structure comprising a mounting aperture; and a threaded fastener for extending through the mounting aperture of the mounting structure and through a corresponding opening in a track mounted to the cabin surface,', 'a head member for applying rotational force to the threaded fastener,', 'a bridging washer for mating with the mounting opening, and', 'a threaded sleeve;, 'a securement apparatus for securing the partition to the cabin surface via the mounting structure, the securement apparatus comprising'} the bridging washer is pressed against the monument opening, and', 'the head member is secured to an upper side of the bridging washer to fixedly retain the partition to the track;', 'and wherein, to adjust a vertical distance between the monument partition and the cabin surface, the threaded sleeve is configured for rotating relative to an internal sleeve fixed to the mounting structure., ' ...

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Номер записи: 97
18-01-2018 дата публикации

Modular Aircraft Galley Systems, Apparatus and Methods for Configuration

Номер: US20180016014A1
Автор: Allan Coombs, Donna Charlene Brownlie, Elizabeth M. Payne, Merv Davidson, Neil R. Elshaw, Peter John Leslie BURD, Sam Foster, Venkata Prasanth Suman Neti
Принадлежит: BE Aerospace Inc

In a preferred embodiment, a modular galley monument for an aircraft cabin includes a first side panel, a second side panel, and an upper surface connecting the first side panel and the second side panel. The modular galley monument may include dividers partitioning the monument into a number of compartments. The monument may include an upper monument portion and a lower monument portion connected at a periphery via a seal allowing for vertical deflection between the first monument portion and the second monument portion of at least one inch while maintaining contact with both. The monument may include an integrated heating appliance for a compartment, including an insulation shell, a heated compartment positioned within the insulation shell, an electrical heating unit disposed within the insulation shell and configured to provide heat energy to the heated compartment. and a door assembly rotatably connected about an opening of the heated compartment.

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Номер записи: 98
19-01-2017 дата публикации

CALIBRATION OF TRANSDUCERS

Номер: US20170016792A1
Автор: HEALEY Mark, SHEPHERD Alan
Принадлежит:

A load measuring sensor set on an aircraft is used under the control of a control unit on the aircraft. The load measuring sensor set is calibrated and there is calibration data associated with it. A code is retrieved which identifies uniquely the sensor set, so that a remote database can be interrogated using the code to retrieve the correct calibration data for the sensor set, for use by the control unit. The sensor set may utilise an optical-fibre having a Fibre Bragg Grating arrangement which provides optical signature characteristics that provide the unique code and having a Fibre Bragg Grating arrangement configured to measure loads. 1. A method of setting up a load measuring sensor on an aircraft , whereinthe loads are to be measured using a calibrated sensor set under the control of a control unit which uses calibration data associated with the calibrated sensor set,the sensor set and the control unit are both located on the aircraft, andwherein the method includes the following steps:retrieving a code that identifies uniquely the calibrated sensor set located on the aircraft;interrogating a remote database using the code to retrieve calibration data that is associated with the calibrated sensor set located on the aircraft; andtransmitting the retrieved calibration data to the control unit.2. A method according to claim 1 , wherein the method includes a step of calibrating the sensor set to produce the calibration data that is associated with the calibrated sensor set.3. A method according to claim 1 , wherein the method includes a step of providing a unique code and physically associating the code with the calibrated sensor set.4. A method according to claim 1 , wherein the step of retrieving a code includes retrieving electronically the code from the sensor set or something that is physically associated with the sensor set.5. A method according to claim 1 , wherein the method includes the steps of:calibrating the sensor set to produce the calibration data ...

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Номер записи: 99
21-01-2016 дата публикации

STANCHION SAFETY NET SUPPORT ARRAY WITH ANCHORAGE SYSTEM AND METHOD OF USING THE SAME

Номер: US20160017618A1
Автор: White Lawrence G., White Mathew E., White Randy A.
Принадлежит:

A safety net support system is provided. The system includes a plurality of support members having a material positioned there between to create a barrier between neighboring support members. The system further includes a pneumatic anchorage member functionally coupled to a source of pressurized air. An anchorage member is configured to sustain a corresponding support member. Each anchorage member includes a vacuum cup and a control input that can transition the anchorage member between an engaged state and a disengaged state. In the engaged state, the anchorage member utilizes the pressurized air to establish a vacuum between the vacuum cup and a surface in contact with the vacuum cup. In the disengaged state, the anchorage member utilizes the pressurized air to establish an air cushion between the vacuum cup and the surface. 1. A safety net support system comprising:a plurality of support members;a material coupled to the plurality of support members, wherein the support members supports the material between the support members; andan anchorage member coupled to each support member, the anchorage member having configured thereon a sealing member, the sealing member being configured to transition between an engaged state and a disengaged state,wherein in the engaged state the sealing member is pneumatically coupled to a surface in contact therewith, and wherein in the disengaged state the sealing member is released from the surface.2. The safety net support system of claim 1 , wherein a positive compressed-air supply powers the anchorage member.3. The safety net support system of claim 1 , further comprising a control input operable between a first position and a second position claim 1 , the control input being biased in the first position.4. The safety net support system of claim 3 , wherein with the control input in the first position the sealing member is in the engaged state claim 3 , and wherein with the control input in the second position the sealing member ...

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Номер записи: 100