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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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Форма поиска

Поддерживает ввод нескольких поисковых фраз (по одной на строку). При поиске обеспечивает поддержку морфологии русского и английского языка
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Применить Всего найдено 4419. Отображено 100.
27-10-2016 дата публикации

Обод тормозного колеса под бескамерную шину с приводными шипами для вращающихся дисков

Номер: RU0000165708U1
Автор: Иван Кузьмич Бобылев
Принадлежит: Открытое акционерное общество "Авиационная корпорация "Рубин"

Обод колеса под бескамерную шину с приводными шипами для тормозных дисков, содержащий ступицу с подшипниками, дисковую часть, соединяющую ступицу с ободом, и продольные выступы по внутреннему контуру обода с продольными в них канавками, боковые стенки которых контактируют с ответными боковыми поверхностями прямоугольных силовых направляющих накладок с цилиндрическими концевыми частями, размещенными в ответных цилиндрических отверстиях дисковой части обода колеса для зацепления с вращающимися тормозными дисками, отличающийся тем, что на торцевых поверхностях продольных выступов внутреннего контура обода с противоположной от съемной реборды стороны закреплены винтами замковые элементы в виде Г-образных пластин, продольные выступы которых входят в поперечные ответные Г-образные пазы прямоугольных силовых направляющих накладок. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (51) МПК B64C 25/42 B60B 25/00 B60B 21/08 B60B 3/04 (13) 165 708 U1 (2006.01) (2006.01) (2006.01) (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ТИТУЛЬНЫЙ (21)(22) Заявка: ЛИСТ ОПИСАНИЯ ПОЛЕЗНОЙ МОДЕЛИ К ПАТЕНТУ 2016105399/11, 18.02.2016 (24) Дата начала отсчета срока действия патента: 18.02.2016 (72) Автор(ы): Бобылев Иван Кузьмич (RU) (73) Патентообладатель(и): Открытое акционерное общество "Авиационная корпорация "Рубин" (RU) R U Приоритет(ы): (22) Дата подачи заявки: 18.02.2016 (45) Опубликовано: 27.10.2016 Бюл. № 30 1 6 5 7 0 8 R U (57) Формула полезной модели Обод колеса под бескамерную шину с приводными шипами для тормозных дисков, содержащий ступицу с подшипниками, дисковую часть, соединяющую ступицу с ободом, и продольные выступы по внутреннему контуру обода с продольными в них канавками, боковые стенки которых контактируют с ответными боковыми поверхностями прямоугольных силовых направляющих накладок с цилиндрическими концевыми частями, размещенными в ответных цилиндрических отверстиях дисковой части обода колеса для зацепления с вращающимися тормозными дисками, отличающийся тем, ...

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Номер записи: 1
23-07-2019 дата публикации

Блок бортового поворота снегоболотохода

Номер: RU0000191091U1
Автор: Андрей Викторович Иванов
Принадлежит: Общество с ограниченной ответственностью "Лесник"

Полезная модель относится к области самоходных транспортных средств, а более конкретно к транспортным средствам типа вездехода, предназначенным для движения по заболоченной местности и слабонесущим грунтам, льду рек и озер, пересеченной местности, а также преодоления водных преград, и может быть использована для создания и производства малогабаритной транспортной техники различного назначения. Задачей полезной модели является разработка более легкого блока бортового поворота снегоболотохода за счет упрощения конструкции. Для выполнения поставленной задачи блок бортового поворота снегоболотохода содержит центральный редуктор с ведомым валом, на котором симметрично с обеих сторон жестко установлены фрикционные механизмы, включающие диски фрикциона. Ведомый вал выполнен составным из трех частей: центральной части, являющейся частью центрального редуктора, правого вала бортового поворота и левого вала бортового поворота. С обеих сторон относительно центрального редуктора на ведомом валу также установлены тормозные механизмы, ведущие звездочки передних и задних колес и ротационные муфты левого и правого борта. Причем тормозные механизмы выполнены из поочередно установленных на ведомом валу тормозных дисков и тормозных суппортов. А во фрикционные механизмы включены суппорта фрикциона. Техническим результатом является то, что выполнение ведомого вала составным из трех частей и установка на нем указанных деталей позволяет отказаться от сложных по конструкции механизмов, как в прототипе, заменив их на более простые и не такие тяжелые, что требуется при конструкции снегоболотоходов. Указанный блок может использоваться в трансмиссиях транспортных средств с бортовым поворотом. 1 н.п. ф-лы,1 ил. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 191 091 U1 (51) МПК B62D 11/08 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ПОЛЕЗНОЙ МОДЕЛИ К ПАТЕНТУ (52) СПК B62D 11/08 (2019.05) (21)(22) Заявка: 2019110881, 11.04.2019 (24) Дата начала отсчета срока действия ...

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Номер записи: 2
31-05-2012 дата публикации

Brake system and method

Номер: US20120133200A1
Автор: Hiroki Oyama, Michael Joseph Boland
Принадлежит: Honda Patents and Technologies North America LLC

A hydraulic system for an aircraft includes a brake operation device, a pressure supply, a reservoir, a shut-off valve, and a wheel brake. The shut-off valve is in fluid communication with and is disposed between the pressure supply and the brake valve. The shut-off valve can include a poppet, a first valve seat and a second valve seat. Movement of the poppet is controlled by operation of the brake operation device. The poppet is movable between a first position where the poppet acts against the first valve seat and a second position where the poppet acts against the second valve seat. In the first position, fluid flow is blocked between the pressure supply and the brake valve through the shut-off valve. In the second position, fluid flow is allowed between the pressure supply and the brake valve through the shut-off valve. The wheel brake is in fluid communication with and downstream from the shut-off valve.

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Номер записи: 3
11-10-2012 дата публикации

System and method for aircraft braking system usage monitoring

Номер: US20120259500A1
Автор: Garrett H. DeVlieg
Принадлежит: Hydro Aire Inc

The system and method for monitoring wear of one or more aircraft parts, such as an aircraft brake, an aircraft tire, a standby system, and landing gear, utilize one or more sensors to sense a parameter of usage, and an estimate of usage of the part can be determined based upon the signal indicating the sensed value of the parameter of usage of the aircraft part. A plurality of sensors can be provided for sensing usage of a plurality of parts of the aircraft, and the estimate of usage of the part can be stored for access of the estimate by ground personnel.

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Номер записи: 4
01-11-2012 дата публикации

Method and device of calculating aircraft braking friction and other relating landing performance parameters based on the data received from aircraft's on board flight data management system

Номер: US20120277937A1
Автор: Zoltán Iván Radó
Принадлежит: Aviation Safety Technologies LLC

This invention relates to a method and apparatus for the calculation of aircraft braking friction and other relating landing parameters, including but not limited to aircraft braking action, aircraft takeoff distance, aircraft landing distance, runway surface conditions and runway surface friction based on the data collected by and available in the aircraft Flight Data Recorder (FDR) or other flight data management system, for example, the Quick Access Recorder (QAR), to provide all involved personnel in the ground operations of an airport and airline operations, including but not limited to aircraft pilots, airline operation officers and airline managers as well as airport operators, managers and maintenance crews, with the most accurate and most recent information on the true aircraft landing performance parameters to help better and more accurate safety and economical decision making.

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Номер записи: 5
22-11-2012 дата публикации

Method for controlling the deceleration on the ground of a vehicle

Номер: US20120296498A1
Автор: Malika Essadouni, Xavier Dal Santo
Принадлежит: AIRBUS OPERATIONS SAS

The invention relates to a method for controlling the deceleration on the ground of a vehicle. The method obtains, from the crew of the vehicle or from an outside operator, parameters relating to its current position and its current speed. Then it determines a reference position and speed of the vehicle, the reference position being a theoretical position to be reached by the vehicle. Finally it determines, from indicated parameters and from reference parameters, a deceleration command with a view to ending up at a target position at a preselected speed.

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Номер записи: 6
13-12-2012 дата публикации

Disengageable interface mechanism between a motorization system of an aircraft landing gear assembly and a wheel

Номер: US20120312112A1
Автор: Laurent Tizac
Принадлежит: AIRBUS OPERATIONS SAS

A motorization mechanism for a wheel of a landing gear assembly, including an input gear driven by a motor-reducer unit; a pendulum element, carrying two intermediate gear wheels driven in rotation by this element, with the intermediate gear wheels having synchronized rotation blocking mechanisms such that the two intermediate gear wheels can be simultaneously engaged or simultaneously released. The angular displacement of the pendulum element around its rotation axis is limited by a first and a second adjustable stop. These adjustable stops are set so that when the pendulum element comes into contact with an adjustable stop, the blocking mechanism of the intermediate gear wheels is freed, whereas it is engaged when the pendulum element is in the neutral position. This pendulum assembly faces a cog wheel that is capable of driving the hub of the said wheel.

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Номер записи: 7
03-01-2013 дата публикации

Method of reducing fuel carried by an aircraft in flight

Номер: US20130001355A1
Автор: Isaiah W. Cox, Joseph Cox
Принадлежит: Borealis Technical Ltd

A method for reducing the amount of fuel required to be carried in flight by an aircraft is provided that substantially reduces the taxi margin amount of fuel required by an aircraft, thereby reducing the aircraft's weight and producing significant increases in fuel use efficiency and savings in fuel costs. The substantially reduced taxi margin amount of fuel is produced by equipping an aircraft with at least one drive wheel powered by at least one onboard drive means that cooperatively drive the aircraft on the ground during taxi between takeoff and landing without reliance on the operation of the aircraft main engines.

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Номер записи: 8
24-01-2013 дата публикации

Method of Extending and Improving Aircraft Life and Efficiency

Номер: US20130020430A1
Автор: Isaiah W. Cox, Joseph J. Cox, Rodney T. Cox
Принадлежит: Borealis Technical Ltd

A method for extending the useful and economic life of an aircraft and improving aircraft efficiency is provided. This method produces significant fuel savings on the ground and in flight as well as cost-effective and efficient operation of and reduced maintenance requirements for older aircraft. The increased economic viability of the continued use of older aircraft is achieved by equipping an aircraft with at least one onboard drive wheel assembly controllably powered to drive the aircraft during ground travel independently of aircraft engines or external tow vehicles. The substantial elimination of damage to an aircraft's airframe, brakes, landing gear, and engine components resulting from tow vehicle attachment, brake application during ground travel with operating aircraft engines, or by FOD produces cleaner, more efficient engine operation during flight. Significant and substantial potential cost savings realized by the present method makes the continued use of older aircraft a viable option.

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Номер записи: 9
18-04-2013 дата публикации

Device for connecting a gearmotor to an aircraft wheel in order to enable the wheel to be driven selectively by the gearmotor

Номер: US20130091969A1
Автор: Daniel Bucheton
Принадлежит: Messier Bugatti Dowty SA

A device for connecting a gear motor to an aircraft wheel, the device comprising: a casing rotatably carrying a shaft that is to be driven by the gear motor, and on which a pinion is mounted idle by means of a rolling bearing; a toothed ring for being constrained in rotation with the aircraft wheel and arranged to mesh permanently with the idle pinion; and rotation securing means for selectively constraining the idle pinion in rotation with the shaft. With this structure, a smooth bearing is interposed between the shaft and the rolling bearing of the idle pinion.

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Номер записи: 10
18-04-2013 дата публикации

Means to improve the performance of high energy brakes such as in aircraft landing gear.

Номер: US20130092787A1
Автор: Polubinski Michal
Принадлежит:

The invention provides means to prevent high-performance brakes from overheating by delivering coolant to the heat-generating brake components. As a result of implementing the invention, the brakes can then be used more effectively to control an aircraft during aborted landing after touchdown. After the aircraft completed the braking action, the risk of damaging tire explosions and undercarriage fires is minimized. The aircraft does not require an extensive post-incident overhaul and can be back in service much faster than when and if the invention is not implemented. 1. An apparatus for self-propelling aircraft undercarriage components , comprising: at least one self-propelled aircraft undercarriage wheel; at least one drive means for propelling said undercarriage wheel; said drive means comprising a rotor; whereby said drive means utilizes the external airflow to propel the said wheel.2. The apparatus of wherein the rotor is coupled to the said wheel.3. The apparatus of wherein the rotor comprises a plurality of vanes shaped to propel the wheel by the airflow around aircraft undercarriage components of .4. The apparatus of wherein the wheel rotates before and on the touch down in the desired direction to minimize the generation of heat on touch-down.5. An apparatus for cooling a brake system claim 3 , comprising: at least one moving member claim 3 , one static member wherein the heat generated during breaking action is absorbed and dissipated by cooling means other than the air claim 3 , called “coolant” hereinafter.6. The apparatus of wherein said coolant comprises additional substances such as solid particles claim 5 , corrosion inhibitors claim 5 , anti-freezing agents—mixed at variable claim 5 , time-depending rates.7. The apparatus of or of claim 5 , wherein said coolant is delivered to the heat-generating zone through a fluid conveyance such as but not limited to a tube claim 5 , a pipe claim 5 , or a hose.8. The apparatus of claim 5 , or of claim 5 , ...

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Номер записи: 11
09-05-2013 дата публикации

METHOD FOR REDUCING REQUIREMENTS FOR AIRCRAFT BRAKE SIZE, COMPLEXITY, AND HEAT DISSIPATION

Номер: US20130112805A1
Автор: Cox Isaiah W.
Принадлежит: BOREALIS TECHNICAL LIMITED

A method is provided for optimizing requirements for brake size, complexity, and heat dissipation capability in an aircraft, wherein the aircraft is powered during ground travel by an onboard wheel drive assembly, including controllable drive means, mounted on at least one aircraft wheel, and ground travel is controlled by the pilot to move the aircraft on the ground without relying on the operation of the aircraft engines, while substantially minimizing brake use between landing and takeoff. Brakes can be optimally sized and configured to meet landing and taxi requirements, resulting in reduced brake size and complexity and increased effective heat dissipation. Substantially minimizing brake use during taxi produces improved brake cooling, substantially eliminating delays caused by slow brake heat shedding and enables rapid aircraft turnaround between landing and takeoff. 1. A method for reducing the requirements for aircraft brake size and heat dissipation capability comprising equipping an aircraft with at least one onboard wheel drive assembly with drive means , wherein said wheel drive assembly is controllably mounted on at least one aircraft wheel so that said drive means is controllable to power the aircraft wheel and move said aircraft independently on the ground without reliance on the aircraft main engines; and providing brakes selected for optimal size and heat dissipation capability during said independent aircraft ground movement.2. The method of claim 1 , wherein said brakes are selected for optimal size and heat dissipation capability based on aircraft taxi brake load.3. The method of claim 2 , wherein said aircraft is equipped with at least one wheel drive assembly mounted on at least one nose landing gear wheel.4. The method of claim 2 , wherein said aircraft is equipped with at least one wheel drive assembly mounted on at least one main landing gear wheel.5. The method of claim 1 , wherein said drive means comprises a drive means selected from the ...

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Номер записи: 12
09-05-2013 дата публикации

Drive system with harmonic drive for self-propelled aircraft wheel

Номер: US20130112806A1
Автор: Hans Walitzki, Isaiah W. Cox, Jonathan Edelson, Rodney T. Cox
Принадлежит: Borealis Technical Ltd

A drive system with harmonic drive designed to meet the high power and torque requirements required to drive an aircraft independently on the ground is provided. The drive system includes an electric motor driven by a harmonic drive assembly that may be configured to be integral with the motor. This drive system with harmonic drive can be effectively installed in an existing aircraft nose wheel or main wheel without changes to other components.

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Номер записи: 13
09-05-2013 дата публикации

Apparatus for Pre-Rotating Aircraft Tires

Номер: US20130112809A1
Автор: Anis Khal, Sami KHAL
Принадлежит: Anis Khal, Sami KHAL

A disc-shaped accessory having radially-hinged flaps is adapted to be attached to an aircraft wheel. The flaps open no more than 90° (preferably 45-70°) in an airstream to exert a rotational torque on the wheel, causing the wheel to spin. The rotation helps reduce tire wear and damage during aircraft landing.

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Номер записи: 14
09-05-2013 дата публикации

AUTOBRAKING INTERLOCK FOR AN AIRCRAFT ELECTRIC BRAKE SYSTEM

Номер: US20130116862A1
Автор: Griffith T. Todd, Uta Andreea D., Yamamoto David T.
Принадлежит: The Boeing Company

An electric autobrake interlock system for an aircraft includes an autobrake power interlock mechanism that prevents inadvertent (uncommanded) application of brakes. The autobrake power interlock removes operating power from the brake actuators whenever the autobrake actuation data does not indicate a legitimate autobrake application condition. The interlock processing occurs in parallel with the autobrake command processing such that even if an inadvertent autobrake command is generated, the brake actuators will be enable to act upon the inadvertent autobrake command. In this regard, the brake actuators are unable to apply brakes automatically unless the following two actions happen concurrently: the operating power is provided to enable the electric brake actuators and autobrake actuation control is commanded in response to the legitimate autobrake application condition. 1. A control arrangement for an autobrake interlock for an electric brake system of an aircraft , the control arrangement comprising:an autobrake actuator power control architecture configured to enable/disable operating power for a brake mechanism of the electric brake system; andan autobrake actuator command architecture in parallel with the autobrake actuator power control architecture, the autobrake actuator command architecture being configured to process brake mechanism commands for the brake mechanism; whereinthe autobrake actuator power control architecture is capable of preventing actuation of the brake mechanism independently of the autobrake actuator command architecture; andthe autobrake actuator command architecture is capable of preventing actuation of the brake mechanism independently of the autobrake actuator power control architecture.2. A control arrangement according to claim 1 , wherein the autobrake actuator power control architecture comprises an interlock decision module configured to process autobrake actuation data and to generate claim 1 , in response to the autobrake ...

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Номер записи: 15
30-05-2013 дата публикации

METHOD OF MANAGING PARKING BRAKING IN A BRAKING SYSTEM FOR A VEHICLE FITTED WITH ELECTRIC BRAKES

Номер: US20130138317A1
Автор: COLIN Emmanuel, MUDRY Stephane, Ragot Frédéric, VANEY Jean-Baptiste
Принадлежит: MESSIER-BUGATTI

The invention relates to a method of managing parking braking in a braking system for a vehicle fitted with at least one electric brake including at least one electric actuator having a pusher actuated by an electric motor for selectively applying a force against friction elements of the brake, the method comprising the steps of: 1. A method of managing parking braking in a braking system for a vehicle fitted with at least one electric brake including at least one electric actuator having a pusher actuated by an electric motor for selectively applying a force against friction elements of the brake , the method comprising the steps of:establishing a series of direct adjustment tables for parking braking, corresponding to braking situations at different energy levels;when applying parking braking, selecting a direct adjustment table corresponding to a braking situation preceding the application of parking braking; anddirectly adjusting a parking braking force in application with the selected direct adjustment table;wherein the method comprises the steps of:selecting a first direct adjustment table and applying it for a predetermined initial application time;making a first adjustment;comparing a real change in position of the pusher with a theoretical change in position of the pusher obtained from the direct adjustment tables after an application time equal to the initial application time; andselecting a second direct adjustment table for which the theoretical change in position of the pusher is the closest to the real change in position.2. A method according to claim 1 , wherein the first direct adjustment table is a high energy level table.3. A method according to claim 2 , wherein the first direct adjustment table is the table having the highest energy level.4. A method according to claim 1 , comprising the steps of:establishing for each braking energy level different direct adjustment tables as a function of ambient temperature; andselecting the direct adjustment ...

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Номер записи: 16
13-06-2013 дата публикации

METHOD AND APPARATUS FOR PROVIDING POWER IN AN AIRCRAFT TO ONE OR MORE AIRCRAFT SYSTEMS

Номер: US20130146707A1
Автор: LYNAS Christopher, MORGAN Iain
Принадлежит: AIRBUS OPERATIONS LIMITED

A method and apparatus is disclosed in which an aircraft system such as the landing gear system or braking system is operated at least partially under power provided by a generator driven by the wheels of the landing gear. 1. Apparatus for providing power in an aircraft to an aircraft braking system , said apparatus comprising:a generator associated with a set of landing gear for an aircraft, said generator being coupled to one or more wheels of said landing gear for extracting kinetic energy from the or each said wheel and to convert said kinetic energy into a first power type for use by an aircraft braking system;an aircraft braking system arranged to utilise said first power type; anda control system operable to controllably supply said first power type from said generator to said aircraft braking system for operating one or more brakes for said aircraft.2. Apparatus according to in which said braking system is associated with said set of landing gear.3. Apparatus according to in which said control system is operable to supply said first power type to said braking system for operation of said braking system during landing of said aircraft.4. Apparatus according to in which said control system comprises an energy storage device arranged to be charged with energy from said generator for powering said braking system when the output of said generator is below a predetermined threshold.5. Apparatus according to in which said aircraft braking system is powered by a second power type and said control system is operable to convert said first power type from said generator to said second power type.6. Apparatus according to in which said first or second power type is hydraulic claim 5 , pneumatic or electric.7. A method for providing power in an aircraft to an aircraft braking system claim 5 , said method comprising the steps of:receiving a command to operate an aircraft braking system arranged to utilise a first power type;directing power from a generator associated with ...

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Номер записи: 17
11-07-2013 дата публикации

METHOD AND DEVICE FOR DRIVING AT LEAST ONE LANDING GEAR WHEEL OF AN AIRCRAFT BY MEANS OF A WHEEL MOTOR

Номер: US20130175388A1
Автор: Bulin Guillaume, Cros Christophe
Принадлежит: AIRBUS OPERATIONS SAS

The invention relates to a device for driving at least one landing gear wheel of an aircraft by means of a wheel motor, which is intended to be used in the stage when the aircraft is traveling on the ground, said aircraft having turbojet engines () attached to the main wing. The device comprises at least one power source (), and one power transmission line between the power source and the wheel motor. The power source () is arranged adjacently to a turbojet engine () attached to the main wing of the aircraft, and comprises disengageable means () enabling the power source to be mechanically connected to the rotating portion of the turbojet engine (), the power source being sufficient to act as a starter for the turbojet engine (). 11. A device for driving at least one landing gear wheel of an aircraft by means of a wheel motor , said device being intended to be used in the taxiing phase of an aircraft , said aircraft being of the type comprising jet engines () attached to the main wing unit ,the device comprising at least one power source, and a power transmission line between the power source and the wheel motor,{'b': 6', '8', '1', '7', '1', '1, 'characterized in that the power source (, ) is arranged in the vicinity of a jet engine () attached to the main wing unit of the aircraft, and comprises disengageable means () to be mechanically linked to the rotating part of the jet engine (), the power source being sufficient to serve as starter for the jet engine ().'}2681. The device as claimed in claim 1 , intended to be used to drive a wheel train arranged under the main wing unit claim 1 , characterized in that the power source ( claim 1 , ) is arranged in the vicinity of the jet engine () closest to said wheel train.368. The device as claimed in claim 1 , characterized in that the power source comprises a microturbine () driving a generator ().4689. The device as claimed in claim 3 , characterized in that the microturbine () drives the generator () via a free wheel ...

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Номер записи: 18
18-07-2013 дата публикации

AIRCRAFT VERSATILE POWER SYSTEM

Номер: US20130181088A1
Автор: CASADO MONTERO Carlos, RUIZ JIMENEZ Alfredo
Принадлежит: AIRBUS OPERATIONS, S.L.

An aircraft versatile power system () comprises an air breathing engine (), a power converter (), and a motor (). 212. An aircraft versatile power system () claim 1 , according to claim 1 , wherein the air breathing engine () operates in three different modes:{'b': '11', '1) providing only power through a mechanical drive (),'}{'b': 11', '25, '2) providing power through a mechanical drive (), and also thrust through its nozzle (),'}{'b': '25', '3) providing only thrust through its nozzle ().'}3162. An aircraft versatile power system () according to or claim 1 , wherein the power converter () transforms shaft motion from the air breathing engine () into electric energy.4162. An aircraft versatile power system () according to or claim 1 , wherein the power converter () transforms shaft motion from the air breathing engine () into hydraulic energy.5162. An aircraft versatile power system () according to or claim 1 , wherein the power converter () transforms shaft motion from the air breathing engine () into pneumatic energy.614. An aircraft versatile power system () according to claim 1 , or wherein the motor () is an electric motor claim 1 , a hydraulic motor or a pneumatic motor.7162. An aircraft versatile power system () according to any previous to claims 1 , wherein the air breathing engine () is a turbojet.8162. An aircraft versatile power system () according to any previous to claims 1 , wherein the air breathing engine () is a turbofan.9129109. An aircraft versatile power system () according to any previous claim claims 1 , wherein the air breathing engine () has at least an air intake () that provides air supply () when open claims 1 , and the air intake () presents no aerodynamic drag when it is closed.1111. A method to operate an aircraft using a versatile power system () according to claim 10 , wherein during the boarding claim 10 , parking and disembarking phases the versatile power system () works in mode 1 claim 10 , providing power supply to the ...

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Номер записи: 19
08-08-2013 дата публикации

SYSTEM AND METHOD FOR MAINTAINING AIRCRAFT GROUND TRAVEL SPEED AND DIRECTION

Номер: US20130200209A1
Автор: Cox Isaiah W., Cox Rodney T., Goldman Joseph
Принадлежит: BOREALIS TECHNICAL LIMITED

A system and method for setting, controlling, or maintaining a selected taxi speed and route for one or more aircraft equipped with an onboard non-engine powered drive means powering one or more aircraft wheels to move the aircraft during taxi is provided. Taxi speed and/or route can be set, maintained, or controlled by the aircraft pilot or ground traffic control in conjunction with taxi speed and travel of other aircraft and ground vehicles. A pilot activates a speed control to set and control taxi speed. The aircraft will automatically travel on the ground at that speed without input from the pilot until it is necessary to change the speed manually or automatically. Airport ground traffic control can generate taxi profiles for all non-engine driven aircraft to automatically control, subject to pilot capability to override, the taxi of multiple aircraft at an airport in conjunction with ground vehicle movement. 1. A system for setting , controlling , and maintaining ground travel speed or direction in an aircraft equipped with onboard non-engine drive means for driving the aircraft on the ground , wherein said system comprises:a. an aircraft equipped with one or more drive means drivingly connected to one or more aircraft wheels;b. a source of power to power said drive means;c. drive means activation and control means in communication with said drive means for operating said drive means during aircraft ground travel;d. speed hold control means in communication with said drive means for setting a speed for aircraft ground travel and maintaining a set speed during aircraft ground travel;e. sensor means in communication with said drive means and said speed hold control means for sensing speed of said aircraft and communicating information relating to the sensed speed to said speed hold control means; andf. speed adjustment means in communication with said speed hold control means for receiving information relating to the sensed speed and adjusting the power supplied ...

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Номер записи: 20
08-08-2013 дата публикации

DRIVE UNIT FOR AIRCRAFT RUNNING GEAR

Номер: US20130200210A1
Автор: Heeg Manfred, Oswald Johann
Принадлежит: L-3 Communications Magnet-Motor GmbH

A drive unit () for an aircraft running gear () having at least a first wheel () and a second wheel () on a common wheel axis (A) is characterized in that the drive unit () is drivingly coupleable to the first and second wheels () such that a direction of longitudinal extension (C) of the drive unit () is in a plane orthogonal to the common wheel axis (A). 1. A drive unit for an aircraft running gear having at least a first wheel and a second wheel on a common wheel axis , characterized in that the drive unit is drivingly coupleable to the first and second wheels such that a direction of longitudinal extension of the drive unit is in a plane orthogonal to the common wheel axis.2. The drive unit according to claim 1 , comprising:a first motor drivingly coupleable to the first wheel via a first gear structure, anda second motor drivingly coupleable to the second wheel via a second gear structure,wherein the first and second motors are arranged in tandem along the direction of longitudinal extension of the drive unit.3. The drive unit according to claim 2 , wherein:the first motor in operation drives a first bevel gear, with the first bevel gear being drivingly coupleable to the first wheel via the first gear structure, andthe second motor in operation drives a second bevel gear, with the second bevel gear being drivingly coupleable to the second wheel via the second gear structure.4. The drive unit according to claim 2 , wherein the first and second motors are arranged in a coaxial manner.5. The drive unit according to any of claim 2 , wherein the first motor has a first motor shaft and the second motor has a second motor shaft claim 2 , with the first motor shaft being hollow and being arranged around the second motor shaft.6. The drive unit according to claim 2 , wherein the first and second motors are electric motors or hydraulic motors.7. The drive unit according to claim 2 , whereinthe first gear structure comprises a first gear element having a third bevel gear ...

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Номер записи: 21
22-08-2013 дата публикации

METHOD FOR IMPROVING GROUND TRAVEL CAPABILITY AND ENHANCING STEALTH IN UNMANNED AERIAL VEHICLES

Номер: US20130214089A1
Автор: Cox Isaiah W., Cox Joseph, Cox Rodney T.
Принадлежит: BOREALIS TECHNICAL LIMITED

A method for improving ground movement capability and enhancing stealth in unmanned aerial vehicles is provided. The present method comprises providing, in an unmanned aerial vehicle equipped with wheels, one or more onboard drive means capable of translating torque through the vehicle wheels and controllable to move the unmanned aerial vehicle on the ground without reliance on the unmanned aerial vehicle main motive power source. The onboard drive means is controllably powered by a power source with substantially no acoustic signature to move the unmanned aerial vehicle quietly on the ground with only a minimal audible or visible footprint. This method provides a significant expansion of ground movement capability and expands the potential ground uses of unmanned aerial vehicles, particularly in military applications. The present method can also be applied to move any manned aerial vehicle or aircraft on the ground with only minimal audible or visible footprints.

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Номер записи: 22
05-09-2013 дата публикации

ELECTRIC BRAKE FOR AN AIRCRAFT WHEEL, THE BRAKE INCLUDING AN ELECTROMECHANICAL ACTUATOR FITTED WITH A TEMPERATURE SENSOR

Номер: US20130230075A1
Автор: COLIN Emmanuel, SELLES Franck, VANEY Jean-Baptiste
Принадлежит: MESSIER-BUGATTI-DOWTY

An electric brake for an aircraft wheel comprising a support formed by a torsion tube and by an actuator-carrier , a stack of disks mounted around the torsion tube , electromechanical actuators carried by the actuator-carrier , each actuator comprising an electric motor and a pusher , the electric motor being adapted to move the pusher facing the stack of disks in order to apply a braking force selectively to the stack of disks; and temperature measurement means for measuring a temperature representative of a temperature that exists in the stack of disks. The temperature measurement means comprises at least one temperature sensor arranged in the pusher of one of the electromechanical actuators so as to be located in the immediate proximity of the stack of disks when the pusher is brought into contact therewith. 1. An electric brake for an aircraft wheel , the brake comprising:{'b': 4', '5', '6, 'a support () that may be formed by a torsion tube () and by an actuator-carrier ();'}{'b': 7', '5, 'a stack () of disks mounted around the torsion tube ();'}{'b': 8', '6', '12', '14', '12', '14', '7', '7, 'at least one electromechanical actuator () carried by the actuator-carrier (), each actuator comprising an electric motor () and a pusher (), the electric motor () being adapted to move the pusher () facing the stack () of disks in order to apply a braking force selectively to the stack () of disks; and'}{'b': '7', 'temperature measurement means for measuring a temperature representative of a temperature that exists in the stack () of disks;'}{'b': 18', '14', '8', '7', '14, 'the electric brake being characterized in that the temperature measurement means comprise at least one temperature sensor () arranged in the pusher () of one of the electromechanical actuators () so as to be located in the immediate proximity of the stack () of disks when the pusher () is brought into contact therewith.'}281814. An electric brake according to claim 1 , wherein each actuator () is ...

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Номер записи: 23
12-09-2013 дата публикации

Movable bushing interface and taxi drive system

Номер: US20130233969A1
Автор: David Lane Charles, Donald Jeffrey Christensen, Douglas Wise
Принадлежит: Honeywell International Inc

A drive ring may be configured to receive a drive key from a wheel rim in a bushing on the ring. The bushing may include a slot with clearance to allow movement of the drive key within the slot during axial or rim flexure events. The axial or rim flexure events may occur for example, during taxiing of a vehicle and the loads of the vehicle can impart flexure forces on the connection between the wheel rim and the drive system. In one exemplary embodiment, the bushing may be movable on the drive ring to accommodate movement of the drive key during flexure.

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Номер записи: 24
19-09-2013 дата публикации

METHOD FOR DETERMINING RELATIONAL SPEED AND POSITION IN AN AIRCRAFT EQUIPPED WITH A LANDING GEAR DRIVE WHEEL

Номер: US20130240664A1
Автор: Cox Isaiah W., Cox Rodney T.
Принадлежит: BOREALIS TECHNICAL LIMITED

A method is provided for determining a relational speed and position of two moving components, preferably an aircraft landing gear drive wheel, a component of the drive wheel, a drive means driving the landing gear drive wheel, or a component of the drive means, using fiber optic technology. Speed and positional information relating to the relative positions of a part of a landing gear drive wheel and a part of a drive means driving the drive wheel can be obtained to ensure their proper engagement or interaction. A single optical fiber preferably provides information relating to drive wheel speed, drive means speed, drive wheel position, and drive means position, therefore enabling efficient autonomous ground travel of an aircraft equipped with this system. The present method can also be employed to monitor aircraft wheel speed in aircraft that use thrust from the engines to move an aircraft on the ground. 1. A method for determining relational speed and position in an aircraft equipped with one or more landing gear drive wheels driven by onboard non-engine drive means , comprising:a. providing an aircraft with one or more landing gear drive wheels driven by one or more onboard non-engine drive means to move the aircraft autonomously on the ground;b. providing control means including a light source and at least one optical fiber to sense and control speed or position of said one or more drive wheels and said one or more drive means; andc. directing light through said control means optical fiber to one or more selected targets operatively associated or linked with said one or more drive wheels or a component of said drive wheels and said one or more onboard drive means or a component of said drive means while said drive wheel said drive wheel component, said drive means, or said drive means component is in motion to move said aircraft, wherein light reflected from said drive wheel, drive wheel component, drive means, or drive means component through said optical ...

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Номер записи: 25
19-09-2013 дата публикации

METHOD FOR IMPROVING EFFICIENCY OF AIRPORT DEICING OPERATIONS

Номер: US20130240665A1
Автор: Cox Isaiah W., Cox Rodney T.
Принадлежит: BOREALIS TECHNICAL LIMITED

A method for improving the efficiency of airport deicing operations is provided. The present method equips aircraft using an airport with onboard non-engine drive means powered to drive one or more landing gear wheels to move the aircraft on the ground autonomously during taxi without reliance on the aircraft's engines. Decreasing or substantially eliminating the operation of aircraft engines during taxi substantially eliminates the likelihood that ice, snow, slush, and other runway contaminants moved by the jet blast produced by aircraft engine operation during taxi will be sprayed from the runway onto surfaces of taxiing aircraft, both prior to deicing and after deicing. Deicing operations can be conducted more quickly, and repeated deicing operations on a single aircraft can be avoided. 1. A method comprising increasing the efficiency of airport deicing operations by substantially reducing time required for deicing operations and substantially avoiding a need to conduct repeat deicing procedures on aircraft required by the presence of wet or frozen runway contaminants sprayed by operating engines of adjacent aircraft , wherein each of a plurality of aircraft using airport facilities is equipped with onboard non-engine drive means powered to drive one or more landing gear wheels to move each aircraft autonomously on the ground during taxi without operating aircraft engines; andwherein the presence of airborne wet or frozen runway contaminants within a jet blast danger zone area of each of said plurality of aircraft driven autonomously on the ground by non-engine drive means is eliminated.2. The method described in claim 1 , wherein said onboard non-engine drive means is selected from the list comprising electric induction motors claim 1 , permanent magnet brushless DC motors claim 1 , switched reluctance motors claim 1 , hydraulic pump/motor assemblies claim 1 , and pneumatic motors.3. The method described in claim 1 , wherein said one or more landing gear wheels ...

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Номер записи: 26
26-09-2013 дата публикации

Electromechanical braking system for an aircraft

Номер: US20130253736A1
Автор: DAVID Frank
Принадлежит: Messier Bugatti Dowty SA

The invention relates to an aircraft braking system having brakes with electromechanical braking actuators (103) adapted to press selectively against associated stacks of disks in order to generate a braking torque on associated wheels of the aircraft; at least one control module (130) receiving braking setpoints and responding by generating a braking command (121); and at least one power module (120) responding to the braking command by delivering AC power to the motors of actuators connected to the power module so that the motors develop a braking force corresponding to the braking setpoints. According to the invention, the control module includes a digital processor stage (131) and an analog processor unit (135).

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Номер записи: 27
03-10-2013 дата публикации

DRIVING DEVICE FOR WHEEL OF AIRPLANE

Номер: US20130256452A1
Автор: Tawara Akihiko, Ushiyama Izumi
Принадлежит:

The device of this invention comprises a revolution drive disc which has a rubber ringed plate and plural fins The fins are obliquely attached on the outside surface of the ringed plate so that torque by the fin at the lower side of the tire in the direction same as the revolution of the wheel after landing is larger than the torque by the fin at the upper side of the tire in the direction reverse to the revolution of the wheel after landing. The revolution drive disc is adhered on the side surface of the tire through the rubber group adhesive. The wheel of the airplane, drawn out from the body, rotates in the direction same as the revolution of the wheel after landing due to the atmospheric air flow by the flight before landing. Thus the change of the number of the revolution at the moment of touch down on landing is reduced or gone, resulting in the reduction of the wear and damage of the tire and the reduction or prevention of the adhere of the remnant or residue of the tire on the runway. 1. A driving device for wheel of airplane driving the wheel in such a direction same as the revolution of the wheel after landing by utilizing the relative atmospheric air flow the airplane receives before landing , comprising;a ringed flat plate constituting the attaching means to attach on the side surface of the tire,fins arranged at the predetermined pitch in the peripheral direction on the ringed plate, the fins being obviously arranged on the ringed plate so that the torque by the fin at the lower side of the tire in the direction same as the revolution of the wheel after landing is larger than the torque by the fin at the upper side of the tire reverse to the revolution of the wheel after landing,wherein, the ringed plate is attached to the side surface of the tire.2. A driving device for wheel of airplane according to claim 1 , wherein claim 1 , the fins at the upper side of the tire receives force to close the fin by the atmospheric air flow due to the flight before ...

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Номер записи: 28
03-10-2013 дата публикации

METHOD AND SYSTEM FOR CONTROLLING AIRCRAFT BRAKING ON A RUNWAY

Номер: US20130261920A1
Автор: JOURNADE Jerome, LIGNEE Robert, Morin Rémi, PICAUT Stephane
Принадлежит:

A method to control braking of an aircraft on a landing runway including: selecting a dummy runway state corresponding to a level of adhesion of wheels of the aircraft to a runway which is lower, over an entire speed range of the aircraft while braking on a runway, than an adhesion level of the wheels of the aircraft to the landing runway; calculating a set point of a deceleration value for the aircraft on the landing runway based on the landing runway for the selected dummy runway state, wherein the calculated set point corresponds to maximum braking value of the aircraft, and controlling the braking of the aircraft using the set point. 1. A method to control braking of an aircraft on a landing runway comprising:selecting a dummy runway state corresponding to a level of adhesion of wheels of the aircraft to a runway which is lower, over an entire speed range of the aircraft while braking on a runway, than an adhesion level of the wheels of the aircraft to the landing runway;calculating a set point of a deceleration value for the aircraft on the landing runway based on the landing runway for the selected dummy runway state, wherein the calculated set point corresponds to maximum braking value of the aircraft, andcontrolling the braking of the aircraft using the set point.2. The method according to wherein the calculation of the set point includes applying a function having as a parameter at least one of an aerodynamic drag force exerted on the aircraft claim 1 , a thrust of the aircraft claim 1 , and a braking force exerted on the aircraft.4. The method according to wherein the calculation of the set point includes calculating an aerodynamic force exerted on the aircraft using at least one of the following formulae:{'br': None, 'i': ×Ps×S', '×Cz, 'sup': '2', 'Lift=0.7ref×Mach'}{'br': None, 'i': ×Ps×S', '×Cx, 'sup': '2', 'Drag=0.7ref×Mach'} Ps is static air pressure;', 'Mach is a Mach number of a speed of the aircraft;', 'Sref is a reference surface area of the ...

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Номер записи: 29
24-10-2013 дата публикации

SYSTEM AND METHODS FOR DYNAMICALLY STABLE BRAKING

Номер: US20130282251A1
Автор: Cahill Eric D.
Принадлежит:

Systems and methods tbr dynamically stable braking are disclosed. A first electromechanical brake actuator controller may be placed in communication with a second electromechanical brake actuator controller, wherein each of the first electromechanical brake actuator controller and second electromechanical brake actuator controller are in communication with electromechanical brake actuators that are associated with the same wheel. The first electromechanical brake actuator controller and second electromechanical brake actuator controllers may then communicate electromechanical brake actuator status information and take corrective measures in accordance with the status information. 120-. (canceled)21. A system comprising:a first electromechanical brake actuator controller;a second electromechanical brake actuator controller;a first communication channel in communication with the first electromechanical brake actuator controller and the second electromechanical brake actuator controller;a first electromechanical brake actuator associated with a plate in electrical communication with the first electromechanical brake actuator controller;a second electromechanical brake actuator associated with the plate in electrical communication with the second electromechanical brake actuator controller;wherein the first electromechanical brake actuator controller transmits status information pertaining to the first electromechanical brake actuator to the second electromechanical brake actuator controller via the first communication channel; andwherein the second electromechanical brake actuator controller commands the second electromechanical brake actuator responsive to the status information pertaining to the first electromechanical brake actuator.22. The system of claim 21 , wherein the status information comprises at least one of a commanded force or a brake actuator position.23. The system of claim 21 , thither comprising a first brake system controller in electrical ...

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Номер записи: 30
31-10-2013 дата публикации

COMPACT ELECTRIC TAXI ASSEMBLY FOR INSTALLATION ON AN AIRCRAFT

Номер: US20130284854A1
Автор: CHARLES DAVID LANE, CHRISTENSEN DONALD J., DEMPSTER JOHN BRIAN, GAINES LOUIE TIMOTHY
Принадлежит:

A method of taxing an aircraft with an electric taxi system (ETS) comprising of drive units producing airflow through rotors to pre-cool drive motors and produce rotation of aircraft wheels. The drive motors may be used to produce reverse motion of the aircraft and of operating the drive motors independently of one another so one can operate at a rate of speed and/or direction that is different from the second one of the drive units which may provide enhanced maneuverability of the aircraft during taxing. The drive motors may be controlled to produce regenerative power producing a deceleration of the aircraft that does not shift a center of gravity of the aircraft. 1. A method for taxiing an aircraft with an ETS comprising the steps of:producing airflow through rotors of wheel-mounted drive motors to pre-cool the drive motors;applying controlled current to the drive motors; anddriving the drive motors to rotate wheels of the aircraft.2. The method of wherein the step of applying controlled current comprises applying overcurrent to the drive motors.3. The method of wherein the step of applying controlled current to the drive motors produces clockwise rotation of a first one of the drive motors and counterclockwise rotation of a second one of the drive motors.4. The method of further comprising the step of:producing cooling airflow through a brake assembly of the wheels after an aircraft has landed and has stopped; andwherein the airflow through the brake assembly is produced by rotation of the drive motors and an integral fan assembly with a clutch assembly disengaged.5. The method of further comprising the steps of:rotating the drive motors to produce reverse motion of the aircraft; andcontrolling the drive motors to produce regenerative power in order to stop the reverse motion of the aircraft.6. The method of wherein the step of controlling the drive motors to produce regenerative power produces a deceleration of the aircraft that does not shift a center of ...

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Номер записи: 31
07-11-2013 дата публикации

AIRCRAFT ELECTRIC BRAKE ACTUATION SYSTEM AND METHOD

Номер: US20130297101A1
Автор: Blunt Allan, Hanlon Casey, Quitmeyer James Neil
Принадлежит: HONEYWELL INTERNATIONAL INC.

A system and method of controlling aircraft brakes in an aircraft that includes a brake pedal and an electric brake actuator. An aircraft operational state is determined and an application force that is supplied to the brake pedal is determined When the determined aircraft operational state is a ground-idle state and the determined application force is greater than a set force magnitude, an actuator brake is moved to engage the electric brake actuator and the electric brake actuator is de-energized. 1. A method comprising:determining an aircraft operational state;measuring an application force supplied to a brake pedal of an aircraft; andmoving an actuator brake to engage an electric brake actuator and de-energizing the electric brake actuator when (i) the determined aircraft operational state is a ground-idle state, wherein the ground-idle state is a state in which the aircraft is moving, and (ii) the measured application force is greater than a set force magnitude.2. The method of claim 1 , further comprising:disengaging the actuator brake and re-energizing the electric brake actuator when the application force is less than a reset force magnitude.3. The method of claim 1 , wherein determining the aircraft operational state comprises measuring aircraft wheel speed.4. The method of claim 1 , wherein determining the aircraft operational state comprises detecting that the aircraft is on a surface.5. The method of claim 1 , wherein the aircraft further includes an engine throttle claim 1 , and wherein determining the aircraft operational state comprises determining an engine throttle position of the engine throttle.6. An electric brake control system for an aircraft claim 1 , the electric brake control system comprising:an electric brake actuator configured to be controllably energized and, upon being controllably energized, to move to a brake position;an actuator brake configured to move between an engage position, in which the actuator brake prevents movement of the ...

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Номер записи: 32
14-11-2013 дата публикации

BRAKE FOR AN AIRCRAFT WHEEL

Номер: US20130299286A1
Автор: TANTY Fabien
Принадлежит: MESSIER-BUGATTI-DOWTY

A brake for an aircraft wheel comprising an actuator-carrier that carries at least one electromechanical actuator having a pusher that is movable along a direction parallel to an axis of rotation X of the wheel and facing friction elements in order to apply a braking force selectively against the friction elements The actuator-carrier and the actuator include guide means for guiding the actuator while being installed on the actuator-carrier in a radial direction Y until it reaches a service position. The guide means forms a bearing surface for transmitting braking forces from the actuator to the actuator-carrier. Position-holder means holds the position of the actuator in its service position and comprises a strap fastened to the actuator-carrier to prevent the actuator from moving on the actuator-carrier in the service position. 11415192710710141525321514373737141514. A brake for an aircraft wheel , the brake comprising an actuator-carrier () that carries at least one electromechanical actuator () having a pusher () that is movable along a direction parallel to an axis of rotation (X) of the wheel () and facing friction elements ( , ) in order to apply a braking force selectively against the friction elements ( , ) , the actuator-carrier () and the actuator () including guide means ( , ) for guiding the actuator () while it is being installed on the actuator-carrier () in a radial direction (Y) until it reaches a service position , said guide means forming a bearing surface suitable for transmitting braking forces from the actuator to the actuator-carrier , and position-holder means () for holding the position of the actuator in its service position , the brake being characterized in that the position-holder means () comprise a strap () fastened to the actuator-carrier () in order to prevent the actuator () from moving on the actuator-carrier () in the service position.237143939. A brake according to claim 1 , wherein the strap () is removable radially and is ...

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Номер записи: 33
12-12-2013 дата публикации

DEVICE FOR BRAKING AND ROTATING AN AIRCRAFT WHEEL

Номер: US20130327884A1
Автор: Yiu Jean-Marc
Принадлежит: MESSIER-BUGATTI-DOWTY

The invention relates to a device for braking and driving rotation of a wheel () mounted to rotate on an aircraft landing gear axle, the device comprising: a torsion tube () adapted to be mounted to rotate on the axle that carries the wheel; a stack of disks () including first disks having means for constraining them in rotation with the wheel and second disks arranged in alternation with the first disks and including means for constraining them in rotation with the torsion tube; a ring () carrying braking actuators () that are adapted to act selectively to press the disks against one another, the ring being constrained in rotation with the torsion tube in order to form a rotary portion () of the device; a rotary drive member () for driving rotation of the rotary portion (); and finally blocking means () for selectively blocking rotation of the rotary portion, which means are independent of the rotary drive member. 11. A device for braking and driving rotation of a wheel () mounted to rotate on an aircraft landing gear axle , the device comprising:{'b': '26', 'a torsion tube () adapted to be mounted to rotate on the axle that carries the wheel;'}{'b': '30', 'a stack of disks () including first disks having means for constraining them in rotation with the wheel and second disks arranged in alternation with the first disks and including means for constraining them in rotation with the torsion tube;'}{'b': 23', '24', '20, 'a ring () carrying braking actuators () that are adapted to act selectively to press the disks against one another, the ring being constrained in rotation with the torsion tube in order to form a rotary portion () of the device; and'}{'b': 40', '20, 'a rotary drive member () for driving rotation of the rotary portion ();'}{'b': 51', '52, 'the device being characterized in that it also includes blocking means (, ) for selectively blocking rotation of the rotary portion, which means are independent of the rotary drive member.'}2202040. A device ...

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Номер записи: 34
16-01-2014 дата публикации

AIRCRAFT BRAKE SYSTEM

Номер: US20140014447A1
Автор: "OConnell Charles T.", Oyama Hiroki
Принадлежит: Honda Patents & Technologies North America, LLC

An aircraft emergency brake system includes a modulating emergency/parking brake valve in fluid communication with and disposed between a pressure source and a wheel brake and a lever assembly operatively connected with the brake valve. The emergency brake system is operative in first and second stages. The lever assembly includes a handle, a lock mechanism and an unlock mechanism. The handle is movable between a non-actuated position and a fully-actuated position. The brake pressure provided to the wheel brake through the brake valve depends on a position of the handle. The lock mechanism is operatively connected with the handle to obstruct the handle from moving from the first stage to the second stage. The unlock mechanism is disposed on the handle to unlock the lock mechanism allowing movement of the handle to the second stage position from the first stage position. 1. An emergency brake system for an aircraft comprising:a modulating emergency/parking brake valve in fluid communication with and disposed between a pressure source and a wheel brake, the emergency brake system being operative in a first stage to provide a moderate amount of brake pressure to the wheel brake and a second stage to provide a greater brake pressure to the wheel brake; and a handle being movable between a non-actuated position where the wheel brake is disengaged and a fully-actuated position where the wheel brake is fully engaged, wherein the brake pressure provided to the wheel brake through the brake valve is provided according to a position of the handle;', 'a lock mechanism operatively connected with the handle to obstruct the handle from moving from a first stage to a second stage; and', 'an unlock mechanism disposed on the handle to unlock the lock mechanism to allow the handle to move to the second stage from the first stage., 'a lever assembly operatively connected with the brake valve, the lever assembly including'}2. The system of claim 1 , wherein the handle is movable from ...

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Номер записи: 35
30-01-2014 дата публикации

WRAPAROUND STRAIN GAGE ASSEMBLY FOR BRAKE ROD

Номер: US20140027570A1
Автор: Tilman James Erik
Принадлежит: The Boeing Company

An apparatus comprises a brake rod and a flexible dielectric membrane wrapped around the brake rod. The membrane has a plurality of substrate cutouts at precise locations for strain gage substrates. 1. Apparatus comprising:a brake rod; anda flexible dielectric strip wrapped around the brake rod, the strip having a plurality of substrate cutouts at precise locations for strain gage substrates.2. The apparatus of claim 1 , further comprising strain gage substrates mounted in the substrate cutouts.3. The apparatus of claim 2 , wherein the strain gage substrates include elements of a Wheatstone bridge.4. The apparatus of claim 3 , further comprising a plurality of terminals on the dielectric strip claim 3 , and wires and traces connecting the terminals to the strain gage elements in the configuration of the Wheatstone bridge.5. The apparatus of claim 4 , wherein a first portion of the dielectric strip holds the substrates and is configured for sensing strain claim 4 , and a second portion is configured to carry the terminals.6. The apparatus of claim 2 , further comprising a protective coating on the substrates.7. The apparatus of claim 1 , wherein the dielectric strip includes marks for precisely aligning ends of the dielectric strip when wrapped around the brake rod claim 1 , and marks for precisely positioning the dielectric strip along a length and circumference of the brake rod claim 1 , the substrates attached to the dielectric strip at precise locations relative to the marks.8. The apparatus of claim 1 , wherein the brake rod is an aircraft brake rod.9. A strain gage assembly comprising:a strain gage including a plurality of substrates; anda flexible dielectric strip having a plurality of cutouts for the substrates, the substrates mounted in the cutouts.10. The assembly of claim 9 , wherein the strip includes marks for precisely aligning ends of the dielectric strip when wrapped around the brake rod claim 9 , and marks for precisely positioning the dielectric ...

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Номер записи: 36
30-01-2014 дата публикации

METHOD OF MAINTAINING OPTIMAL BRAKING AND SKID PROTECTION FOR A TWO-WHEELED VEHICLE HAVING A SPEED SENSOR FAILURE ON A SINGLE WHEEL

Номер: US20140032076A1
Автор: Raby Ronald, Silberling Jordan
Принадлежит: HYDRO-AIRE, INC.

The method of maintaining optimal braking and skid protection for a two-wheeled vehicle wheel with a wheel speed sensor failure involves providing pulsed braking pressure to the affected wheel with the wheel speed sensor failure. If an incipient or initial skid on another wheel with a functioning wheel speed sensor has occurred, the pulsed braking pressure to the affected wheel is limited to the brake pressure command that caused the last incipient or initial skid on the other wheel, scaled by a factor for safety. Otherwise the pulsed braking pressure to the affected wheel is limited to be no greater than the greatest commanded brake pressure to the other wheel. The pulsed braking pressure is also limited to be less than the brake pressure commanded to the affected wheel. 1. A method for controlling antiskid braking of a plurality of wheels in a group of wheels of an aircraft , said plurality of wheels having a corresponding plurality of wheel speed sensors associated therewith , respectively , said plurality of wheel speed sensors configured to generate wheel speed signals of said corresponding plurality of wheels , respectively , for antiskid control of said plurality of wheels , based upon said wheel speed signals , when a first wheel speed sensor of said plurality of wheel speed sensors of the corresponding first wheel has failed and a second wheel speed sensor of said plurality of wheel speed sensors of the corresponding second wheel is functioning , the method comprising the steps of:determining a commanded braking pressure of the second wheel;determining whether an incipient or initial skid of the second wheel associated with said commanded braking pressure of the second wheel has occurred, based upon said wheel speed signals from the second wheel speed sensor;storing said commanded braking pressure of the second wheel as a brake pressure limit of the first wheel if said skid of the second wheel associated with said commanded braking pressure has occurred; ...

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Номер записи: 37
20-02-2014 дата публикации

Free Spinning Wheel for Airplanes

Номер: US20140048648A1
Автор: Karl Winter
Принадлежит:

The landing gear wheels of an aircraft include modified tires mounted on the rim of the wheel include a plurality of fins integral with the sidewall of the tires and configured to catch the wind created by movement of the aircraft through the air for spinning the wheel in a forward motion direction when the landing gear has been deployed and before the aircraft touches down, thereby reducing the friction between the runway and the tire upon touchdown. 1. A device for spinning a landing gear wheel of an aircraft once the landing gear has been deployed and before the aircraft touches down on a runway , the device comprising:a. A tire mounted on the wheel, the tire having a sidewall;b. A plurality of fins integral with the sidewall of the tire and configured to catch the wind created by movement of the aircraft through the air for spinning the wheel in a forward motion direction.2. The device of claim 1 , wherein the fins are crescent shaped to control the direction of rotation of the wheel.3. The device of claim 1 , wherein the length of the fins are sized to control the speed of rotation of the wheel relative to air speed.4. The device of claim 1 , wherein the fins are on the interior sidewall of the tire.5. The device of claim 1 , wherein the fins are on the outer sidewall of the tire.6. The device of claim 1 , wherein the fins are on both the inner and the outer sidewalls of the tire.7. A modified tire for a landing gear wheel of an aircraft claim 1 , the tire adapted to be mounted on the wheel and adapted to promote spinning of the wheel in a controlled direction when the landing gear has been deployed and before the aircraft touches down for spinning the wheel in the direction of forward motion claim 1 , thereby reducing the friction between the runway and the tire upon touchdown claim 1 , the modified tire comprising:a. A tire mounted on the wheel, the tire having a sidewall;b. A plurality of fins integral with the sidewall of the tire and configured to catch ...

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Номер записи: 38
06-03-2014 дата публикации

METHOD FOR INCREASING LANDING GEAR EFFECTIVE LIFE AND AIRCRAFT LANDING CYCLES

Номер: US20140061374A1
Автор: Cox Isaiah W., Cox Rodney T., Vana Jan
Принадлежит:

A method for reducing maintenance and increasing the effective life of an aircraft's landing gear, thereby increasing the aircraft's flight and landing cycles is provided. The present method eliminates adverse stresses and forces produced on landing gear components by the operation of a tow vehicle to tow the aircraft on the ground by providing an onboard wheel driver that is powered to drive at least one of the aircraft's nose wheels or main wheels to move the aircraft on the ground. Movement of the aircraft on the ground is controlled by the operation of the driver-powered drive wheel, eliminating the possibility of damage to landing gear components associated with tug operation. 1. A method comprising reducing damage to aircraft landing gear caused by external tow vehicles comprising providing onboard wheel drive means capable of translating torque through aircraft wheels and controllable to move the aircraft on the ground without said tow vehicles.2. The method of claim 1 , wherein the aircraft is moved on the ground by onboard wheel drive means comprising any motor capable of producing the torque required to move a commercial sized aircraft at an optimum speed for ground movement.3. The method of claim 2 , wherein the onboard wheel drive means is selected from the group consisting of electric induction motors claim 2 , permanent magnet brushless DC motors claim 2 , switched reluctance motors claim 2 , hydraulic pump/motor assemblies claim 2 , and pneumatic motors.4. The method of claim 1 , wherein the onboard wheel drive means is mounted on at least one aircraft nose wheel or on at least one aircraft main wheel.5. The method of claim 1 , wherein said onboard wheel drive means is powered by a power source selected from the group consisting of an aircraft's auxiliary power unit claim 1 , an aircraft's main engines claim 1 , batteries claim 1 , fuel cells claim 1 , solar power claim 1 , POWER CHIPS® claim 1 , and burn boxes.6. The method described in claim 3 , ...

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Номер записи: 39
20-03-2014 дата публикации

METHOD OF FASTENING AN AIRCRAFT WHEEL DRIVE MEMBER ON AN UNDERCARRIAGE CARRYING A WHEEL

Номер: US20140075739A1
Автор: Blanpain Thierry, Campbell Edouard, REMOND Sébastien, TOVAR Alexis
Принадлежит: MESSIER-BUGATTI-DOWTY

The invention provides a method of mounting an aircraft wheel drive member () on an undercarriage having an axle () that carries the wheel and that is provided with a torque plate () having an outside face against which a brake can be fitted, the method comprising the steps of fitting a support () that bears against an inside face of the torque plate opposite from its outside face against which a brake () is fitted, and of fitting the drive member on the support. 1301310110210. A method of mounting an aircraft wheel drive member () on an undercarriage having an axle () that carries the wheel and that is provided with a torque plate () having an outside face against which a brake can be fitted , the method comprising the steps of fitting a support (; ; ) that bears against an inside face of the torque plate opposite from its outside face , and of fitting the drive member on the support.210. A mounting method according to claim 1 , wherein the support () comprises two half-supports claim 1 , each of which is fitted against the inside face of the torque plate in order to be bolted thereto.320212225. A mounting method according to claim 1 , wherein the support is fastened on the torque plate by using at least one bolt () inserted in an orifice of the torque plate and having a threaded bolt shank () on which a nut () is fitted to clamp together the support and the torque plate between a head () of the shank and the nut.423. A mounting method according to claim 3 , wherein the bolt shank includes a smooth portion () for centering it in the orifice of the torque plate.525. A mounting method according to claim 4 , wherein the head () of the bolt is received in the spot face of the brake with a small amount of circumferential clearance in order to position the brake relative to the torque plate.6110210. A mounting method according to claim 1 , wherein the support is made as a single piece (; ) and has an opening to enable it to be put into place against the inside face of ...

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Номер записи: 40
03-04-2014 дата публикации

AIRCRAFT WHEEL WITH A UNIVERSAL DRIVE DOG

Номер: US20140091173A1
Автор: BARBU Mirca, REMOND Sébastien
Принадлежит: MESSIER-BUGATTI-DOWTY

The invention relates to an aircraft wheel comprising a rim adapted to receive a tire, and a hub connected to the rim () in order to receive bearings for guiding the wheel in rotation about an axis of rotation (X) on an axle of the aircraft, the wheel including at least one dog () that projects laterally from the rim in order to present two parallel faces () and that is pierced by an orifice () extending from one face to the other along a generally orthoradial direction (Y). 12101112. An aircraft wheel comprising a rim adapted to receive a tire , and a hub connected to the rim () in order to receive bearings for guiding the wheel in rotation about an axis of rotation (X) on an axle of the aircraft , the wheel being characterized in that it includes at least one dog () that projects laterally from the rim in order to present two parallel faces () and that is pierced by an orifice () extending from one face to the other along a generally orthoradial direction (Y).2101010. An aircraft wheel according to claim 1 , having three dogs ( claim 1 , claim 1 , ) that are circumferentially spaced apart at 120° from one another.3100203343. A method of driving a wheel according to in rotation claim 1 , wherein the aircraft is fitted with a rotary drive member () provided with drive means (; ; ) suitable for co-operating with the dog(s).420. The method according to claim 3 , wherein the drive member is provided with one or more drive forks () suitable for fitting astride a respective dog in order to transmit rotary torque by the fork bearing against one of the parallel faces of the dog.5100333010. The method according to for driving a wheel in rotation claim 3 , wherein the rotary drive member () is provided with a drive link () having one end coupled to a lug () fitted to the dog ().631. The method according to claim 5 , wherein the lug is fitted with a shank () having a threaded end claim 5 , the shank being engaged in the orifice of the dog in order to fasten the lug to the dog ...

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Номер записи: 41
10-04-2014 дата публикации

Electromechanical braking system architecture

Номер: US20140100719A1
Автор: Julien Thibault
Принадлежит: Messier Bugatti Dowty SA

The invention relates to a braking system architecture for an aircraft having wheels 1 braked by means of respective brakes 2, each brake having a plurality of electromechanical actuators 3 a, 3 b, the braking system having controllers 8 a, 8 b for distributing electric power Ps to the actuators 3 a, 3 b in response to a braking setpoint, each controller 8 a, 8 b being associated with some of the actuators of any given brake. According to the invention, each controller 8 a, 8 b has an input Ev for receiving information about the rotary speed of the wheel 1 braked by the actuators associated with said controller, the controller including processor means 13 for modulating the power transmitted to the actuators as a function of the speed of rotation of the wheel in order to provide anti-skid protection.

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Номер записи: 42
01-01-2015 дата публикации

SYSTEM AND METHOD FOR BRAKE DISK ASSEMBLY

Номер: US20150001008A1
Автор: Kirkpatrick Christopher T.
Принадлежит:

Systems and methods disclosed herein may be useful for use in a disk brake assembly. In this regard, a disk brake system may comprise a combination of split friction disk assemblies and solid disk assemblies. These split friction disk assemblies and/or solid disk assemblies may be arranged together in any suitable pattern or position.

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Номер записи: 43
01-01-2015 дата публикации

METHOD OF USING AND RENOVATING A DISK FROM A STACK OF DISKS

Номер: US20150001009A1
Автор: CHAMBARD Pierre, VANEY Jean-Baptiste
Принадлежит: MESSIER-BUGATTI-DOWTY

The invention relates to a method of using and renovating a brake disk (), the method comprising steps of using the disk in a plurality of lives and compensating for a reduction in the thickness of the disk after each life by assembling the disk with a complementary portion or by associating the disk with another disk of rotor or stator type if the disk is itself respectively of stator or rotor type.

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Номер записи: 44
01-01-2015 дата публикации

KEYED BRAKE DISK ASSEMBLY

Номер: US20150001017A1
Автор: Kirkpatrick Christopher T.
Принадлежит:

Friction disks, such as rotors and stators, including keyed wear liners are disclosed. The friction disks may include a core and a replaceable wear liner coupled to each side of the core. The wear liners may include a plurality of keys which engage key notches in the core. The key notches may prevent the wear liners from rotating with respect to the core in response to a shear force, such as a force applied during braking. 1. A stator comprising: a spine;', 'an inner core having a thickness greater than the spine;', 'a lug in the inner core; and', 'a key notch recessed into an outer portion of the inner core; and, 'a core comprisinga first wear liner coupled to the spine, the first wear liner comprising an annular ring and a stator key, wherein the stator key mates with the key notch in the inner core.2. The stator of claim 1 , further comprising a second wear liner coupled to the spine opposite the first wear liner.3. The stator of claim 2 , wherein a combined thickness of the first wear liner claim 2 , the spine claim 2 , and the second wear liner is greater than the thickness of the inner core.4. The stator of claim 1 , wherein the first wear liner comprises a coned disc shape.5. The stator of claim 1 , wherein the first wear liner is at least one of bonded to the core and riveted to the core.6. The stator of claim 1 , wherein the core comprises a first material claim 1 , the first wear liner comprises a second material claim 1 , and wherein the first material is different than the second material.7. The stator of claim 1 , wherein the stator key engages a core key in the inner core to prevent rotation of the first wear liner.8. The stator of claim 1 , wherein the first wear liner comprises a first remanufactured wear liner bonded to a second remanufactured wear liner.9. A rotor comprising:a core comprising a spine and a plurality of lugs, wherein at least one lug comprises a recessed key notch; anda wear liner comprising an annular ring having a wear surface and ...

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Номер записи: 45
07-01-2021 дата публикации

SELECTIVE BRAKING OF CARBON BRAKES TO IMPROVE LIFE

Номер: US20210001823A1
Автор: Georgin Marc, Kordik Michael
Принадлежит: GOODRICH CORPORATION

A method for active brake selection, in accordance with various embodiments is disclosed. The method comprises detecting an outbound taxiing event for an aircraft. The method further comprises determining whether an inboard or outboard brake has less wear than a respective inboard or outboard brake on a respective landing gear. The method may further comprise selecting an inboard or outboard brake to use during the outbound taxiing event. 1. A method for active brake selection , comprising:detecting, by a brake control unit (BCU), an outbound taxiing event in an aircraft;determining, by the BCU, a first inboard wear state of a left landing gear inboard brake and a first outboard wear state of a left landing gear outboard brake;selecting, by the BCU, the left landing gear inboard brake or the left landing gear outboard brake as a selected left landing gear brake for exclusive use during the outbound taxiing event;determining, by the BCU, a second inboard wear state of a right landing gear inboard brake and a second outboard wear state of a right landing gear outboard brake;selecting, by the BCU, at least one of the right landing gear inboard brake or the right landing gear outboard brake as a selected right landing gear brake for exclusive use during the outbound taxiing event.2. The method of claim 1 , further comprising:monitoring, by the BCU, a first temperature of the selected left landing gear brake and a second temperature of the selected right landing gear brake during the outbound taxiing event.3. The method of claim 2 , further comprising:alternating, by the BCU, the selected left landing gear brake to an unselected left landing gear brake if at least one of the first temperature exceeds a predetermined temperature threshold or the selected right landing gear brake to an unselected right landing gear brake if the second temperature exceeds the predetermined temperature threshold.4. The method of claim 1 , wherein the first inboard wear state claim 1 , the ...

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Номер записи: 46
07-01-2016 дата публикации

APPARATUS AND SYSTEM FOR POWER DISTRIBUTION TO BRAKE SYSTEMS

Номер: US20160001753A1
Автор: Georgin Marc, Pant Albert Keith
Принадлежит:

A low voltage DC power system for powering an aircraft brake actuator assembly. The brake actuator assembly may comprise an electric actuator motor system with a park brake and/or a hybrid electric hydraulic system with a park brake. The brake actuator assembly may also comprise a load cell and one or more sensors. The load cell and sensors may be configured to operate with low voltage DC power. Moreover, by employing a low voltage DC power system, the wiring of an aircraft brake system may be reduced and/or simplified. 1. (Proposed amended) A brake power distribution system , comprising:a control system;a park brake configured to receive power at a first voltage level from the control system via a first power line;a sensor configured to receive power at a second voltage level from the control system via a second power line; anda load cell configured to receive power at the second voltage level from the control system via the second power line, wherein the park brake, the sensor, and the load cell are configured to receive power via a single power line comprising the first power line and the second power line as at least one of a segment, junction, and portion of the single power line.2. The brake power distribution system of claim 1 , further comprising a conditioning circuit in electrical communication with the control system and configured to condition power from the control system to the first voltage level and the second voltage level.3. The brake power distribution system of claim 1 , wherein the park brake is configured to control hydraulic fluid.4. The brake power distribution system of claim 1 , wherein the park brake and the sensor are part of a brake actuator assembly.5. The brake power distribution system of claim 4 , wherein the conditioning circuit is a portion of at least one of the brake actuator assembly or the control system.6. The brake power distribution system of claim 1 , further comprising a fluid reservoir in fluid communication with the park ...

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Номер записи: 47
05-01-2017 дата публикации

ELECTROMECHANICAL BRAKING SYSTEMS AND METHODS WITH POWER DEMAND CONTROL

Номер: US20170001610A1
Автор: SINGH SAMEEP
Принадлежит: GOODRICH CORPORATION

A controller for an electromechanical brake actuator (EBA) is provided. EBA has a motor driven in response to a motor drive signal generated by controller. Controller includes a velocity limiter and a current limiter. Velocity limiter limits a velocity command in response to a measured braking force signal output. Limited velocity command has a positive velocity limit boundary defined between a positive maximum velocity limit setpoint and a positive minimum velocity limit setpoint and a negative velocity limit boundary defined between a negative maximum velocity limit setpoint and a negative minimum velocity limit setpoint. Current limiter limits a current command in response to the measured braking force signal output. Limited current command has a positive current limit boundary defined between a positive maximum current limit setpoint and a positive minimum current limit setpoint and a negative current boundary defined between a negative maximum current limit setpoint and a negative minimum current limit setpoint. 1. A controller for an electromechanical brake actuator having a motor that is driven in response to a motor drive signal generated by the controller comprising:a velocity limiter for limiting a velocity command to a limited velocity command in response to a measured braking force signal output, the limited velocity command having a positive velocity limit boundary defined between a positive maximum velocity limit setpoint and a positive minimum velocity limit setpoint and a negative velocity limit boundary defined between a negative maximum velocity limit setpoint and a negative minimum velocity limit setpoint; anda current limiter for limiting a current command to a limited current command in response to the measured braking force signal output, the limited current command having a positive current limit boundary defined between a positive maximum current limit setpoint and a positive minimum current limit setpoint and a negative current boundary ...

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Номер записи: 48
05-01-2017 дата публикации

LANDING GEAR DRIVE SYSTEM AND METHOD

Номер: US20170001718A1
Автор: DIDEY Arnaud
Принадлежит:

A drive system for an aircraft landing gear is disclosed having a wheel rotatable about a wheel axis, a driven gear arranged to be attached to the wheel and capable of rotating the wheel about the wheel axis, a drive train comprising an input gear rotatable by an input shaft, an intermediate gear meshed with the input gear and rotatable by an intermediate shaft, and a support member arranged to support the input shaft and intermediate shaft. The support member is arranged to pivot about the input shaft between a neutral configuration in which the drive train is disengaged from the driven gear and a driven configuration in which the drive train is engaged with the driven gear to enable the drive train to rotate the driven gear. The drive system includes brake capable of being engaged with the input shaft to prevent rotation of the input shaft relative to the support member and of being disengaged from the input shaft to permit rotation of the input shaft relative to the support member. 1. A drive system for an aircraft landing gear having a wheel rotatable about a wheel axis , the drive system including:a driven gear arranged to be attached to the wheel so as to be capable of rotating the wheel about the wheel axis;a drive train comprising an input gear rotatable by an input shaft, an intermediate gear meshed with the input gear and rotatable by an intermediate shaft, and a support member arranged to support the input shaft and intermediate shaft and arranged to pivot about the input shaft between a neutral configuration in which the drive train is disengaged from the driven gear and a driven configuration in which the drive train is engaged with the driven gear to enable the drive train to rotate the driven gear;a brake capable of being engaged with the input shaft to prevent rotation of the input shaft relative to the support member and of being disengaged from the input shaft to permit rotation of the input shaft relative to the support member, wherein the support ...

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Номер записи: 49
05-01-2017 дата публикации

LANDING GEAR DRIVE SYSTEM AND METHOD

Номер: US20170001719A1
Автор: DIDEY Arnaud, WILSON Fraser
Принадлежит:

A drive system for a landing gear is disclosed having a wheel rotatable about a wheel axis, the a drive assembly comprising an input gear rotatable about an input axis by an input shaft, an engagement assembly comprising a first intermediate gear meshed with the input gear and rotatable about a first intermediate axis by a first intermediate shaft, and a first drive pinion mounted on the first intermediate shaft and arranged to rotate in tandem with the first intermediate gear, the engagement assembly being pivotable about the input shaft relative to the drive assembly. A locking device is engageable to prevent rotation of the first intermediate gear about the first intermediate axis. The drive system also comprises a driven gear is configured to be attached to the wheel so as to be capable of rotating the wheel about the wheel axis. 1. A drive system for a landing gear having a wheel rotatable about a wheel axis , the drive system including:a drive assembly comprising an input gear rotatable about an input axis by an input shaft;an engagement assembly comprising a first intermediate gear meshed with the input gear and rotatable about a first intermediate axis by a first intermediate shaft, and a first drive pinion mounted on the first intermediate shaft and arranged to rotate in tandem with the first intermediate gear, the engagement assembly being pivotable about the input shaft relative to the drive assembly;a locking device which is engageable to prevent rotation of the first intermediate gear about the first intermediate axis; anda driven gear configured to be attached to the wheel so as to be capable of rotating the wheel about the wheel axis,wherein:the drive system is arranged to move from a neutral configuration, in which the first drive pinion is not meshed with the driven gear and the locking device is engaged, to a first driven configuration, in which the first drive pinion is meshed with the driven gear and the locking device is disengaged, upon ...

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Номер записи: 50
05-01-2017 дата публикации

WHEEL AND GEAR ASSEMBLY

Номер: US20170001720A1
Автор: DIDEY Arnaud, WILSON Fraser
Принадлежит:

A wheel assembly is disclosed, in which a ring gear is movably mounted to the rim of the wheel, so that torque can be transmitted between wheel and rim, while the ring gear is isolated from deformations induced in the wheel rim. 1. A wheel assembly , comprising:a wheel;a ring gear, mounted to and rotatable with the wheel; andan interface for connecting the wheel hub to the ring gear to transmit a torque therebetween; an array of substantially radially oriented openings, arranged in a substantially circular array around an axis of rotation of the assembly; and', 'a plurality of connecting members disposed in the openings, each connector having a substantially radially oriented longitudinal axis, the connecting members being free to move relative to at least one of the wheel hub and the ring gear, to permit relative radial movement between the ring gear and the wheel hub;, 'the interface comprisingsuch that torque applied to one of the ring gear or the wheel is transmitted to the other via the connecting members, and the ring gear is substantially isolated from radial deformation of the wheel rim.2. A wheel hub assembly according to claim 1 , wherein the interface provides a radial clearance on a connection path between the wheel hub and the ring gear.3. A wheel hub assembly according to claim 1 , wherein the interface comprises a lateral extension to the wheel rim or ring gear claim 1 , extending in a direction of the axis of rotation of the wheel or ring gear on which it is provided.4. A wheel hub assembly according to claim 3 , wherein the lateral extension comprises a grow-out provided on at least one of the wheel and the ring gear.5. A wheel hub assembly according to claim 3 , wherein the lateral extension comprises a series of laterally extending tabs provided on one of the wheel or the ring gear.6. A wheel assembly according to claim 3 , wherein the interface is provided between the lateral extensions and a plurality of tabs provided on one of the wheel rim and ...

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Номер записи: 51
02-01-2020 дата публикации

Braking System For a Dual Landing Gear Aircraft

Номер: US20200001984A1
Автор: David T. Yamamoto, Taylor R. Hubbard
Принадлежит: Boeing Co

A braking system for use with a dual landing gear aircraft. The braking system pairs outboard brake control into an outboard brake system control unit (BSCU) and inboard brake control into a second inboard brake system control unit (BSCU). Each BSCU is designed with two independent control lanes in which the forward wheel set is paired in one control lane and the aft wheels are paired onto the other. Alternate braking is provided via an alternate brake module installed in a fore-aft wheel pairing.

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Номер записи: 52
04-01-2018 дата публикации

AIRCRAFT INCLUDING PARALLEL HYBRID GAS TURBINE ELECTRIC PROPULSION SYSTEM

Номер: US20180002025A1
Автор: Hardin Larry W., Lents Charles E., Rheaume Jonathan
Принадлежит:

A gas turbine engine includes a core having a compressor section with a first compressor and a second compressor, and a turbine section with a first turbine and a second turbine. The first compressor is connected to the first turbine via a first shaft and the second compressor is connected to the second turbine via a second shaft. An electric motor is connected to the first shaft such that rotational energy generated by the electric motor is translated to the first shaft. An electric energy storage component is electrically connected to the electric motor, and electrically connected to at least one aircraft taxiing system. The gas turbine engine is configured such that the gas turbine engine requires supplemental power from the electric motor during at least one mode of operations. 1. A gas turbine engine comprising:a core including a compressor section having a first compressor and a second compressor, a turbine section having a first turbine and a second turbine;the first compressor is connected to the first turbine via a first shaft;the second compressor is connected to the second turbine via a second shaft;an electric motor connected to the first shaft such that rotational energy generated by the electric motor is translated to the first shaft;an electric energy storage component electrically connected to said electric motor, and electrically connected to at least one aircraft taxiing system; andwherein the gas turbine engine is configured such that the gas turbine engine requires supplemental power from the electric motor during at least one mode of operations.2. The gas turbine engine of claim 1 , wherein the aircraft taxiing system is a traction drive.3. The gas turbine engine of claim 2 , wherein the traction drive is drivably connected to at least one of an aircraft landing gear wheels and transmission.4. The gas turbine engine of claim 1 , wherein the aircraft taxiing system is a fan connected to said first shaft via at least one gearing system.5. The gas ...

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Номер записи: 53
03-01-2019 дата публикации

DRIVE SYSTEM FOR AIRCRAFT LANDING GEAR

Номер: US20190002090A1
Автор: DIDEY Arnaud, WILSON Fraser
Принадлежит:

A drive system for rotating a wheel of an aircraft landing gear is disclosed including a motor operable to rotate a drive pinion via a drive path; and a driven gear adapted to be attached to the wheel so as to be capable of rotating the wheel. The drive system has a drive configuration in which the drive pinion is capable of meshing with the driven gear to permit the motor to drive the driven gear via the drive path. The drive path includes a first compensating gear mounted on a common drive shaft with the drive pinion so as to be capable of rotating in tandem with the drive pinion, and a second compensating gear which is meshed with the first compensating gear. 1. A drive system for rotating a wheel of an aircraft landing gear , the drive system including:a motor operable to rotate a drive pinion via a drive path; anda driven gear adapted to be attached to the wheel so as to be capable of rotating the wheel, wherein:the drive system has a drive configuration in which the drive pinion is capable of meshing with the driven gear to permit the motor to drive the driven gear via the drive path;the drive path comprises a first compensating gear and a second compensating gear which is meshed with the first compensating gear;one of the drive pinion and the driven gear comprises a roller gear having a series of rollers arranged to form a ring, each roller being rotatable about a roller axis, and the other of the drive pinion and the driven gear comprises a sprocket; andone of the first compensating gear and the second compensating gear comprises a roller gear having a series of rollers arranged to form a ring, each roller being rotatable about a roller axis, and the other of the first compensating gear and the second compensating gear comprises a sprocket.2. A drive system according to claim 1 , wherein either:the drive pinion and the first compensating gear each comprise a roller gear having a series of rollers arranged to form a ring, each roller being rotatable about a ...

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Номер записи: 54
03-01-2019 дата публикации

AIRCRAFT LANDING GEAR ASSEMBLY

Номер: US20190002092A1
Автор: THOMPSON Robert Ian
Принадлежит:

An aircraft landing gear assembly () including a shock absorber strut (), a bogie (), a link assembly (), and a movement detector (). The shock absorber strut includes an upper and a lower telescoping parts (), the upper part being connectable to the airframe of an aircraft and the lower part being connected to the bogie. The link assembly extends between the upper and lower telescoping parts. The movement detector detects movement of the link assembly relative to the bogie. The movement detector includes: a piston () arranged such that relative movement between the link assembly and the bogie causes relative movement of the piston within a cylinder (); fluid which flows as a result of relative movement between the piston and the cylinder; and a flow sensor () arranged to sense a change in flow due to movement of the piston within the cylinder. 1. An aircraft landing gear assembly comprising:a shock absorber strut, a bogie, a link assembly, and a movement detector;wherein the shock absorber strut comprises an upper telescoping part and a lower telescoping part, the upper telescoping part being connectable to the airframe of an aircraft and the lower telescoping part being connected to the bogie such that the bogie may adopt different pitch angles;the link assembly extends between the upper and lower telescoping parts, such that relative movement between the upper and lower telescoping parts causes relative movement between parts of the link assembly;the movement detector is arranged to detect movement of the link assembly relative to the bogie; and a piston slidably received within a cylinder, arranged such that relative movement between the link assembly and the bogie causes relative movement of the piston within the cylinder,', 'fluid which flows as a result of relative movement between the piston and the cylinder, and', 'a flow sensor arranged to sense a change in flow of the fluid, and, 'wherein the movement detector compriseswherein relative movement between ...

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Номер записи: 55
05-01-2017 дата публикации

ROLLER-BASED DRIVE SYSTEMS

Номер: US20170002896A1
Автор: Christensen Donald Jeffrey, Mitchell Robert
Принадлежит: HONEYWELL INTERNATIONAL INC.

An electric taxi system (ETS) for an aircraft includes rollers attached circumferentially to a wheel of the aircraft, and a sprocket with circumferentially distributed teeth attached to a sprocket-tooth ring. The sprocket has a hub with an axis of rotation that is parallel to an axis of rotation of the wheel of the aircraft. The sprocket includes a flexible member interposed between the hub and the sprocket-tooth ring. A radial axis of at least one tooth of the sprocket is substantially perpendicular with an axis of rotation of at least one of the rollers even if the at least one of the rollers is non-parallel to the axis of rotation of the wheel of the aircraft. 1. An electric taxi system (ETS) for an aircraft comprising:driven elements attached circumferentially to a wheel of the aircraft, anda driving member with circumferentially distributed driving elements attached to driving-element support ring;wherein the driving member has an inner hub with an axis of rotation that is parallel to an axis of rotation of the wheel of the aircraft;wherein the driving member includes a flexible member interposed between the inner hub and the driving-element support ring; andwherein the driving elements properly align with and successively engage with the driven elements upon rotation of the driving member even when distortion of the wheel results in the driven elements being misaligned relative to the axis of rotation of the driving member.2. The ETS ofwherein the flexible member comprises a plurality of annular discs;wherein first spacers are interposed between outer portions of the annular discs;wherein second spacers are interposed between inner portions of the annular discs;wherein the first spacers and the outer portions of the annular discs are metallurgically bonded together; andwherein the second spacers and the inner portions of the annular discs are metallurgically bonded together.3. The ETS of wherein the annular discs have an undulating cross-sectional ...

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Номер записи: 56
20-01-2022 дата публикации

CROSS-CONNECTION TEST FOR AIRCRAFT LANDING GEAR

Номер: US20220017237A1
Автор: HAYES Alexander
Принадлежит:

A method of testing an aircraft landing gear is disclosed including: a) generating a test signal with the first tachometer, wherein the first wheel is not rotating during the generation of the test signal; b) receiving the test signal via one of the tachometer output lines; c) issuing a braking command in response to the receipt of the test signal, wherein the braking command is issued via the braking command line which is associated with the one of the tachometer output lines; and d) monitoring a response of the first or second braking system to the braking command to test for a cross-connection between the first and second braking systems. The landing gear includes first and second wheels; a first braking system having a first tachometer mounted to the first wheel and configured to generate a first tachometer signal indicating rotation of the first wheel, and a first brake configured to brake the first wheel. 1. A method of testing an aircraft landing gear , the aircraft landing gear comprising:first and second wheels;a first braking system comprising a first tachometer mounted to the first wheel and configured to generate a first tachometer signal indicating rotation of the first wheel, and a first brake configured to brake the first wheel;a second braking system comprising a second tachometer mounted to the second wheel and configured to generate a second tachometer signal indicating rotation of the second wheel, and a second brake configured to brake the second wheel;first and second tachometer output lines;a first braking command line associated with the first tachometer output line; anda second braking command line associated with the second tachometer output line; a) generating a test signal with the first tachometer, wherein the first wheel is not rotating during the generation of the test signal;', 'b) receiving the test signal via one of the tachometer output lines;', 'c) issuing a braking command in response to the receipt of the test signal, wherein the ...

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Номер записи: 57
12-01-2017 дата публикации

BRAKING CONTROL SYSTEM FOR AN AIRCRAFT

Номер: US20170008503A1
Автор: DAMIANI Andrea, GAMA Miguel Angel, ROMANA Louis-Emmanuel
Принадлежит:

A braking control system for an aircraft having braking wheels, the braking control system being configured to receive input of signals from sensors representative of a plurality of measured aircraft parameters, and to output a plurality of brake commands to brakes associated with the braking wheels, wherein the braking control system includes a health monitoring system for determining the operability and/or reliability of the sensor signals and/or of the braking wheels, and a task manager for automatically self-reconfiguring the braking control system so as to change the manner in which the braking control system utilises the input signals in the event that the health monitoring system judges a failure of one or more of the braking wheels or sensor signals. Also a method for operating an aircraft having a plurality of braking wheels. 1. A braking control system for an aircraft having a plurality of braking wheels , the braking control system being configured to receive input of sensor signals from sensors representative of a plurality of measured aircraft parameters , and to output a plurality of brake commands to brakes associated with the braking wheels according to a brake torque distribution , wherein the braking control system includes:a health monitoring system configured to determine an operability and/or a reliability of the sensor signals and/or of the braking wheels, anda task manager configured to automatically reconfigure the braking control system so as to change the manner in which the braking control system utilizes the sensor signals in the event that the health monitoring system judges a failure of one or more of the braking wheels or sensor signals and to control a prioritization of the brake torque distribution among the available braking wheels in response to detected events under normal and failure conditions.2. The braking control system according to claim 1 , wherein the aircraft parameters include one or more of: aircraft speed claim 1 , ...

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Номер записи: 58
12-01-2017 дата публикации

DEVICE FOR MEASURING A RELATIVE ROTATION SPEED AND/OR A RELATIVE ANGULAR POSITION BETWEEN A FIRST ROTATING ELEMENT AND A SECOND ROTATING ELEMENT MOUNTED TO ROTATE RELATIVE TO A STATIC PART

Номер: US20170008617A1
Автор: DURAND Guillaume, LEYNAERT Francois-Noel, QUENERCH`DU Marc
Принадлежит: SAFRAN LANDING SYSTEMS

A device for measuring a relative rotation speed and/or a relative angular position between a first rotating element () and a second rotating element (). The device includes a structure for generating a magnetic field rotating at a magnetic rotation speed representing a rotation speed of the first rotating element and a sensor () mounted to rotate and adapted to produce from the rotating magnetic field a measurement signal representing the relative rotation speed and/or the relative angular position. The device also has a processor () positioned on the static part and intended to acquire the measurement signal. A transmitter is adapted to transmit the measurement signal to the processor from the sensor. 121023103. A measuring device for measuring a relative rotation speed and/or a relative angular position between a first rotating element (; ) and a second rotating element (; ) mounted to rotate relative to a static part , the device including:means for generating a magnetic field rotating at a magnetic rotation speed representing a rotation speed of the first rotating element;{'b': 5', '105, 'a sensor (; ) mounted to rotate at the rotation speed of the first rotating element or at a rotation speed of the second rotating element and sensitive to the rotating magnetic field, the sensor being adapted to produce from the rotating magnetic field a measurement signal representing the relative rotation speed and/or the relative angular position;'}{'b': 11', '111, 'processing means (; ) positioned on the static part and intended to acquire the measurement signal;'}first transmission means adapted to transmit the measurement signal to the processing means from the sensor.2. The measuring device according to claim 1 , wherein the sensor is mounted on the second rotating element.313. The measuring device according to claim 1 , wherein the generation means include a permanent magnet () or a winding positioned directly on the first rotating element to influence the sensor.4717. ...

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Номер записи: 59
12-01-2017 дата публикации

OPTIMIZING GROUND MOVEMENT IN AIRCRAFT EQUIPPED WITH NON-ENGINE DRIVE MEANS

Номер: US20170008618A1
Автор: Cox Isaiah W., Cox Joseph J., Cox Rodney T., Vana Jan
Принадлежит: BOREALIS TECHNICAL LIMITED

A method is provided for maximizing efficiency of ground travel in aircraft equipped with landing gear wheel-mounted non-engine drive motors for autonomous ground travel. Selective operation of the non-engine drive motors and selective operation of the aircraft's engines are integrated to power aircraft movement when different ground travel speeds or airport ground travel conditions require operation of engines or non-engine drive motors for optimal efficiency of aircraft ground travel. The non-engine drive motors may be specifically designed to move aircraft at lower speeds optimal for ground maneuvers in a ramp area or elsewhere, and one or more of the aircraft's engines may be operated at a thrust level that moves the aircraft efficiently at higher taxi speeds. 1. A method for increasing efficiency of aircraft ground travel from an aircraft landing location , into and out of an airport terminal parking location , and then to a takeoff location in aircraft equipped with non-engine drive motors for autonomous ground movement , comprising:a. equipping both wheels of an aircraft nose landing gear in an aircraft powered by one or more engines with non-engine drive motors mounted completely within each of the nose landing gear wheels and controllable by a pilot of the aircraft to drive the aircraft autonomously without operation of the one or more engines at an optimal ground speed for selected ground travel locations and operations;b. selectively controlling only the non-engine drive motors and driving the aircraft at the optimal ground speed during ground travel at the selected ground travel locations and during the selected ground travel operations; andc. selectively controlling operation of the one or more engines to move the aircraft on an airport ground surface only at an airport taxi speed during other selected ground travel taxi operations and at other selected ground travel locations without operation of the non-engine drive motors.2. The method of claim 1 , ...

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Номер записи: 60
12-01-2017 дата публикации

AIRCRAFT STEERING SYSTEM CONTROLLER

Номер: US20170008619A1
Автор: GAMA Miguel Angel, ROMANA Louis-Emmanuel
Принадлежит:

A controller for an aircraft steering system, the controller being configured to receive a steering input representative of a desired direction of travel of a steerable nose landing gear, and to receive one or more force-based inputs representative of lateral forces acting upon the nose landing gear, wherein the controller is adapted to automatically adjust the steering input based upon the force-based input(s) so as to output an adjusted steering command for a steering actuator of the nose landing gear. 1. A controller for an aircraft steering system , the controller being configured to receive a steering input representative of a desired direction of travel of a steerable nose landing gear , and to receive one or more force-based inputs representative of lateral forces acting upon the nose landing gear , wherein the controller is adapted to automatically adjust the steering input based upon the one or more force-based inputs and output an adjusted steering command for a steering actuator of the nose landing gear.2. The controller according to claim 1 , wherein the one or more force-based inputs include a closed-loop feedback signal representative of actual lateral force acting upon the nose landing gear.3. The controller according to wherein the one or more force-based inputs include an open-loop estimate of lateral force acting upon the nose landing gear.4. The controller according to claim 3 , wherein the controller is configured to calculate the estimated lateral force estimate based upon one or more aircraft parameters and a pre-defined model stored in the controller.5. The controller according to wherein the one or more force-based inputs include an open-loop estimate of lateral force acting upon the nose landing gear and wherein the controller is configured to automatically revert to the open-loop estimate of lateral force when the closed-loop signal of actual lateral force is unavailable or is unreliable.6. The controller according to claim 1 , wherein the ...

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Номер записи: 61
14-01-2016 дата публикации

DRIVE UNIT FOR AIRCRAFT RUNNING GEAR

Номер: US20160009383A1
Автор: Heeg Manfred, Oswald Johann
Принадлежит: L-3 Communications Magnet-Motor GmbH

A drive unit () for an aircraft running gear () having at least a first wheel () and a second wheel () on a common wheel axis (A) is characterized in that the drive unit () is drivingly coupleable to the first and second wheels () such that a direction of longitudinal extension (C) of the drive unit () is in a plane orthogonal to the common wheel axis (A). 1. A drive unit for an aircraft running gear having at least a first wheel and a second wheel on a common wheel axis , the drive unit comprising:a differential gear; anda motor drivingly coupleable to the first and second wheels via the differential gear,wherein the drive unit is drivingly coupleable to the first and second wheels such that a direction of longitudinal extension of the drive unit is in a plane orthogonal to the common wheel axis.2. The drive unit according to claim 1 , wherein the motor comprises a bevel gear for engaging with the differential gear.3. The drive unit according to claim 1 , wherein the differential gear is coupleable to the first and second wheels by first and second gear structures claim 1 , respectively.4. The drive unit according to claim 1 , wherein the differential gear is a bevel differential or planetary differential or ball differential.5. The drive unit according to claim 1 , wherein the motor is an electric motor or a hydraulic motor.6. The drive unit according to claim 1 , further comprising:a first output stage gear engageable with a first wheel axis gear, which is coupled to the first wheel, for driving the first wheel, anda second output stage gear engageable with a second wheel axis gear, which is coupled to the second wheel, for driving the second wheel,wherein the first and second output stage gears are aligned on a common output stage axis, which is substantially orthogonal to the direction of longitudinal extension of the drive unit.7. The drive unit according to claim 3 , wherein the first and second gear structures comprise a planetary gear claim 3 , respectively ...

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Номер записи: 62
14-01-2016 дата публикации

PARKING BRAKE CONTROL SYSTEM FOR AN AIRCRAFT

Номер: US20160009384A1
Автор: DI ZAZZO Marco, PLANTE Bertrand
Принадлежит:

A system for providing control to a parking brake for an aircraft () having a power source includes a panel () accessible from an exterior of the aircraft () and a parking brake switch () disposed on the panel () providing control over the engagement and disengagement of the parking brake on the aircraft (), a method operating such a system for providing control to a parking brake is also disclosed. 1. A system for providing control to a parking brake for an aircraft having a power source during a towing operation of the aircraft , comprising:a panel of the aircraft accessible from an exterior of the aircraft;a parking brake switch disposed on the panel and configured to provide control over the engagement and disengagement of the parking brake on the aircraft; anda tow status indicator configured to provide an indication to the exterior of the aircraft as to whether or not the aircraft may be towed.2. The system of claim 1 , wherein the panel is proximate to a landing gear of the aircraft.3. The system of claim 1 , wherein the panel is proximate to the nose of the aircraft.4. The system of claim 1 , wherein the parking brake is an electric brake.5. The system of claim 1 , further comprising:a power switch disposed on the panel, to provide power to the system from the power source.6. The system of claim 1 , wherein the power source is at least one battery on the aircraft.7. The system of claim 1 , further comprising:a navigation lights switch, wherein the navigation lights switch permits activation and deactivation of navigation lights on the aircraft when power is provided to the electric brakes.8. The system of claim 5 , wherein navigation lights are activated when power is provided to the system from the power source.9. The system of claim 7 , wherein the navigation lights are powered by the power source.10. The system of claim 9 , wherein the beacon lights are powered by the power source.11. The system of claim 1 , wherein:the tow status indicator is disposed on ...

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Номер записи: 63
14-01-2016 дата публикации

Vehicle Braking System Having Braking Control and Skid Reduction Functions

Номер: US20160009385A1
Автор: Godo Erik L., Van Deventer Bruce
Принадлежит: The Boeing Company

Methods and means for reducing wear in electric or electro-hydraulic braking systems utilizing an adjustable (adaptive) filter, wherein the adaptive filter provides for rapid response during anti-skid operation and a smooth and filtered response during non-anti-skid operation. 1. A method for braking comprising:(a) receiving a sequence of unfiltered braking command values comprising merged brake command values and anti-skid command values;(b) adaptively filtering said sequence of braking command values to form filtered braking command values; and(c) controlling a brake in accordance with said adaptively filtered braking command values,wherein said adaptive filtering changes from a first mode to a second mode in response to the content of anti-skid command values exceeding a specified threshold.2. The method as recited in claim 1 , wherein said second mode is a pass-through mode.3. The method as recited in claim 1 , wherein said second mode is a fast response mode.4. The method as recited in claim 1 , wherein step (b) comprises:selecting a first set of filter coefficients in response to a transition in said sequence of braking command values from predominantly brake command values to predominantly anti-skid command values;configuring a filter with said first set of selected filter coefficients; andfiltering subsequently received braking command values using the filter configured with said first set of selected filter coefficients.5. The method as recited in claim 4 , wherein step (b) further comprises:determining a signature of braking command values of said sequence received within a time window; anddetermining whether said signature is indicative of said transition.6. The method as recited in claim 5 , wherein said signature comprises a number of matched pairs of braking command values of said sequence received within said time window claim 5 , and said step of determining whether said signature is indicative of said transition comprises determining whether said ...

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Номер записи: 64
27-01-2022 дата публикации

LANDING GEAR OF AN AIRCRAFT AND METHOD FOR COOLING AN ELECTRIC TAXIING MOTOR AND BRAKES OF SUCH A LANDING GEAR

Номер: US20220024567A1
Автор: Blanco Loic, Cassagnet Christophe, CHALLAS Florent, FONTALBAT Thierry, Galy Quentin, JABER Sylvain, WISSEMER Eric
Принадлежит:

Aircraft landing gears include at least one wheel, an electric taxiing system including an electric taxiing motor, brakes capable of slowing down or stopping the rotation of the wheel, and a cooling system for cooling the electric taxiing motor and the brakes. The cooling system includes ventilation means capable of mixing a first air flow originating from the brakes and a second air flow originating from outside the landing gear and of ventilating the electric taxiing motor with a mixture of the two air flows. 1. A landing gear of an aircraft comprising:at least one wheel;an electric taxiing system comprising an electric taxiing motor, said electric taxiing motor being configured to rotate said at least one wheel;a braking system comprising brakes configured to reduce a rotational rate of said at least one wheel; anda cooling system for cooling said electric taxiing motor and said brakes, the cooling system comprising ventilation means configured to mix a first air flow originating from said brakes and a second air flow originating from outside said landing gear to create a mixed third air flow, and configured to ventilate said electric taxiing motor with the mixed third air flow, wherein said ventilation means comprise a ventilation wheel configured to suck said mixed third air flow and a motor configured to rotate said ventilation wheel.2. The landing gear according to claim 1 , wherein said ventilation means comprise at least one series of fins positioned along a path of said mixed third air flow.3. The landing gear according to claim 2 , wherein the fins of said at least one series of fins are arranged in a staggered pattern.4. The landing gear according to claim 1 , further comprising a cowl surrounding said braking system claim 1 , and wherein said ventilation means are arranged with a clearance with respect to said cowl.5. The landing gear according to claim 1 , further comprising a gearbox connected to said electric taxiing motor and to said at least one ...

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Номер записи: 65
14-01-2021 дата публикации

BRAKE ACTUATOR

Номер: US20210009259A1
Автор: Kielczykowski Piotr, Kielczykowski Przemyslaw
Принадлежит:

A brake actuator for an aircraft braking system includes a housing having an internal bore, a sleeve mounted for axial movement within the bore of the housing that has a plurality of ratchet teeth on an external surface thereof, a latching mechanism comprising at least one latch mounted for radial movement for engagement with the ratchet teeth of the sleeve. The latching mechanism further includes a latch spring mounted externally of the internal bore for biasing the at least one latch radially inwardly to engage with the ratchet teeth of the sleeve, and a hydraulic brake piston slidably mounted within the internal bore of the housing and extending axially through the sleeve, the piston having a piston head at a first end thereof, and a second opposite end for operative engagement with a brake element, the piston being mounted so as to be movable axially relative to the sleeve. 1. A brake actuator for an aircraft braking system , the brake actuator comprising:a housing having an internal bore;a sleeve mounted for axial movement within the bore of the housing, the sleeve having a plurality of ratchet teeth on an external surface thereof;a latching mechanism comprising at least one latch mounted for radial movement for engagement with the ratchet teeth of the sleeve, the latching mechanism further comprising a latch spring mounted externally of the internal bore for biasing the at least one latch radially inwardly to engage with the ratchet teeth of the sleeve; anda hydraulic brake piston slidably mounted within the internal bore of the housing and extending axially through the sleeve, the piston having a piston head at a first end thereof, and a second opposite end for operative engagement with a brake element, the piston being mounted so as to be movable axially relative to the sleeve between a first position in which the piston is drivingly engaged with the sleeve for urging the sleeve in a first direction along the internal bore of the housing, and a second ...

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Номер записи: 66
10-01-2019 дата публикации

AIRCRAFT AUTONOMOUS PUSHBACK

Номер: US20190009891A1
Автор: COLOSIMO Antonio, Morris James
Принадлежит:

The invention provides methods and systems for controlling speed of an aircraft during an autonomous pushback manoeuvre, i.e. under the aircraft's own power without a pushback tractor. The method includes applying a torque to at least one landing gear wheel of the aircraft, the torque being in a direction opposite to the backwards rolling direction of rotation of the landing gear wheel. The torque applied does not exceed a limit for ensuring aircraft longitudinal stability. For longitudinal stability the torque applied should not cause the aircraft to risk a tip-over event. 1. A method of controlling speed of an aircraft during backwards motion of the aircraft when in contact with the ground , the method comprising:applying a torque to at least one landing gear wheel of the aircraft, the torque being in a direction opposite to the backwards rolling direction of rotation of the landing gear wheel,wherein the torque applied does not exceed a limit for ensuring aircraft longitudinal stability.2. A method according to claim 1 , wherein the torque applied does not exceed a limit at which aircraft longitudinal stability is ensured such that the aircraft cannot tip back onto its tail.3. A method according to wherein the torque applied does not exceed a limit at which aircraft longitudinal stability is ensured such that a nose landing gear of the aircraft does not part contact with the ground.4. A method according to wherein the torque applied does not exceed a limit at which aircraft longitudinal stability is ensured such that a substantially vertical load through a nose landing gear wheel does not fall below a threshold at which a steering centring device maintains the wheel of the nose landing gear straight.5. A method according to claim 1 , wherein the torque limit is based upon one or more of the following instantaneous aircraft parameters when the torque is applied: a slope angle of the ground over which the aircraft is moving; the centre of gravity of the aircraft; ...

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Номер записи: 67
09-01-2020 дата публикации

DRIVE SYSTEM FOR AIRCRAFT LANDING GEAR

Номер: US20200010180A1
Автор: DIDEY Arnaud, WILSON Fraser
Принадлежит:

A drive system for rotating a wheel of an aircraft landing gear is disclosed. The drive system includes a motor operable to rotate a drive pinion via a drive path, and a driven gear adapted to be mounted to the wheel. The drive system has a first configuration in which the drive pinion is capable of meshing with the driven gear to permit the motor to drive the driven gear via the drive path. The drive path has a plurality of shafts rotatable about respect shaft axes, including an output shaft. The output shaft is operable to pivot about the axis of rotation of another shaft axis spaced from the output shaft axis. Also, an aircraft landing gear having a wheel and the drive system, where the driven gear of the drive system is mounted to the wheel. 1. A drive system for rotating a wheel of an aircraft landing gear , the drive system including a motor operable to rotate a drive pinion via a drive path , and a driven gear adapted to be mounted to the wheel , wherein the drive system has a first configuration in which the drive pinion is capable of meshing with the driven gear to permit the motor to drive the driven gear via the drive path , wherein the drive path has an input shaft having an axis of rotation spaced from an axis of rotation of an output shaft , and wherein the output shaft is operable to pivot about the axis of rotation of the input shaft.2. A drive system according to claim 1 , wherein the drive path is mounted within a housing having a pivot with a pivot axis coaxial with the axis of rotation of the input shaft for pivotally mounting the housing to the aircraft landing gear.3. A drive system according to claim 2 , further comprising an actuator for coupling between the housing and the aircraft landing gear so that extension and retraction of the actuator causes rotation of the housing about the pivot.4. A drive system according to claim 1 , wherein the drive path is a single stage torque transmission arrangement.5. A drive system for rotating a wheel of ...

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Номер записи: 68
08-01-2015 дата публикации

BRAKE CONTROL SYSTEM COMPRISING TIRE/RUNWAY FRICTION PROPERTY ESTIMATION MAPPING

Номер: US20150012153A1
Автор: JR. Richard Paul, KOLK RICHARD, Metzger
Принадлежит: GOODRICH CORPORATION

Systems and methods for a tire/runway friction property estimation method based on measured wheel speed, calculated acceleration, wheel reference and tire normal force estimation are disclosed. Based on the resulting estimations, a map and/or function of position for the friction properties may be formed and transmitted to external systems after an aircraft stop is completed. 1. A method for determining coefficients of friction along a portion of a runway comprising:measuring, by a brake control unit, a first axle reference speed for a braked wheel of an aircraft;establishing, by the brake control unit, a wheel reference speed for the braked wheel of the aircraft;determining, by the brake control unit, a slip ratio of the braked wheel;estimating, by the brake control unit, a weight of the aircraft associated with the first braked wheel;mapping, by the brake control unit, position data to the measured values; andestimating, by the brake control unit, coefficients of friction associated with locations along the portion of the runway.2. The method of claim 1 , wherein the establishing the wheel reference speed of the first braked wheel comprises measuring a wheel speed of a wheel.3. The method of claim 2 , further comprising transmitting the measured wheel speed from a wheel speed sensor to the brake control unit.4. The method of claim 1 , wherein the estimating the weight of the aircraft comprises determining a tire pressure of a tire of the first braked wheel claim 1 , and calculating the weight of the aircraft based on the determined change tire pressure from a known reference value.5. The method of claim 1 , further comprising calculating position data from a location sensor.6. The method of claim 5 , wherein the location sensor is a global positioning unit.7. The method of claim 1 , further comprising estimating claim 1 , by the brake control unit claim 1 , a slip ratio peak associated with locations along the runway.8. The method of claim 1 , further comprising ...

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Номер записи: 69
08-01-2015 дата публикации

SYSTEM AND METHOD FOR DETECTING AN ON GROUND CONDITION OF AN AIRCRAFT

Номер: US20150012195A1
Автор: Georgin Marc, Metzger Richard
Принадлежит:

Systems and methods for detecting an on ground condition of an aircraft are disclosed. A weight on wheel system may determine that an aircraft is on the ground. Wheel speed sensors may measure the speed of the aircraft wheels. Axle reference speeds may be calculated for each landing gear based on the speed of the aircraft wheels. A brake control unit may determine that the axle reference speed for each axle of the landing gears is above an on ground threshold speed, and the brake control unit may allow braking to be applied. 1. A method for determining an on ground condition of an aircraft comprising:calculating a first axle reference speed for a first landing gear of an aircraft;calculating a second axle reference speed for a second landing gear of the aircraft; andin response to both the first axle reference speed and the second axle reference speed being greater than an on ground threshold, permitting, by a brake control unit, a braking force to be applied to at least one of the first landing gear and the second landing gear.2. The method of claim 1 , wherein the calculating the first axle reference speed comprises measuring a wheel speed of a wheel on the first landing gear.3. The method of claim 1 , further comprising determining that an axle reference acceleration is below an acceleration threshold.4. The method of claim 2 , further comprising transmitting the first wheel speed from a wheel speed sensor to the brake control unit.5. The method of claim 1 , further comprising calculating a third axle reference speed for a third landing gear of the aircraft.6. The method of claim 1 , wherein the calculating the first axle reference speed comprises averaging a wheel reference speed of a plurality of wheels on the first landing gear.7. The method of claim 1 , further comprising determining claim 1 , using a weight on wheel system claim 1 , that the aircraft is on the ground.8. The method of claim 1 , further comprising:measuring, using a wheel speed sensor coupled ...

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Номер записи: 70
08-01-2015 дата публикации

BRAKE CONTROL SYSTEM COMPRISING RUNWAY FRICTION PROPERTY ESTIMATION MAPPING

Номер: US20150012201A1
Автор: KOLK RICHARD, Metzger Richard Paul
Принадлежит:

Systems and methods for detecting the onset of wheel skids and controlling brake torque to achieve efficient and smooth braking performance are described herein. A brake control system may utilize an algorithm, along with substantially real-time measured values to assist with controlling brake torque to achieve efficient and smooth braking performance. A history of wheel speed information, such as wheel speed information associated with one or more landing event, may also be used to iteratively estimate tire/runway friction properties. 1. A method for determining coefficients of friction along a portion of a runway comprising:measuring, by a flight control processor, a first gear reference speed for a first landing gear of an aircraft;measuring, by the flight control processor, a first gear instantaneous speed for the first landing gear of the aircraft;determining, by the flight control processor, a slip ratio of the first landing gear;estimating, by the flight control processor, a weight of the aircraft associated with the first landing gear;mapping, by the flight control processor, position data to the measured values; andestimating, by the flight control processor, coefficients of friction associated with locations along the portion of the runway.2. The method of claim 1 , wherein the calculating the first gear reference speed comprises measuring a wheel speed of a wheel on the first landing gear.3. The method of claim 1 , wherein the estimating the weight of the aircraft comprises determining a tire pressure of a tire of the first landing gear claim 1 , and calculating the weight of the aircraft based on the determined change tire pressure from a known reference value.4. The method of claim 1 , further comprising transmitting the first gear reference speed from a wheel speed sensor to the flight control processor.5. The method of claim 1 , further comprising calculating position data from a location sensor.6. The method of claim 5 , wherein the location sensor ...

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Номер записи: 71
12-01-2017 дата публикации

DATA PROCESSING UNIT FOR AIRCRAFT UNDERCARRIAGE PERFORMANCE MONITORING

Номер: US20170011568A1
Автор: GAMA Miguel Angel, ROMANA Louis-Emmanuel
Принадлежит:

A data processing unit for monitoring the performance of at least one undercarriage which is used for braking and/or steering an aircraft, wherein the data processing unit is configured to: receive data representative of operating characteristics of the undercarriage(s) and use that data to calculate a maximum achievable braking force and/or yaw moment to be generated by the undercarriage(s). Also a method for monitoring the performance of at least one aircraft undercarriage which is used for braking and/or steering an aircraft, the method including: receiving data representative of operating characteristics of the undercarriage(s); and using that data to calculate a maximum achievable braking force and/or yaw moment to be generated by the undercarriage(s). 1. A data processing unit for monitoring the performance of at least one undercarriage which is used for braking and/or steering an aircraft , wherein the data processing unit is configured to receive data representative of operating characteristics of the at least one undercarriage and use the data to calculate a maximum achievable braking force and/or yaw moment to be generated by the at least one undercarriage.2. The data processing unit according to claim 1 , wherein the maximum achievable braking force and/or yaw moment represents an instantaneous performance envelope of the undercarriage.3. The data processing unit according to which is configured to use the data representative of the operating characteristics of the at least one undercarriage to calculate a total braking force and/or yaw moment being generated by the at least one undercarriage.4. The data processing unit according to claim 1 , wherein the data representative of the operating characteristics of the at least one undercarriage comprises data output by at least one sensor configured to measure the operating characteristics of the at least one undercarriage.5. An aircraft braking and/or steering system for controlling braking and/or steering of ...

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Номер записи: 72
09-01-2020 дата публикации

ANTIVIBRATION CENTERING RING FOR THE FOOT OF A TORQUE TUBE OF AN AIRCRAFT BRAKE, AND A BRAKE FITTED WITH SUCH A RING

Номер: US20200011388A1
Автор: Le Floch Romain, Vitti Joseph
Принадлежит: SAFRAN LANDING SYSTEMS

An antivibration centering ring for centering a foot of the torque tube of an aircraft brake on an axle of the aircraft includes alternating bearing zones that are arranged to bear in alternation on the axle and on the torque tube foot. The bearing zones are offset on their non-bearing sides by functional clearance so that no bearing zone bears simultaneously on the axle and on the foot of the torque tube. The bearing zones are connected to one another by flexible ligaments. 1. An aircraft brake , comprising a torque tube having a foot configured to be centered on an aircraft axle , the brake comprising an antivibration centering ring configured to center the foot of the torque tube on the axle of the aircraft , wherein the centering ring includes alternating bearing zones arranged to bear in alternation on the axle and on the torque tube foot , the bearing zones being offset on their non-bearing sides by functional clearance so that no bearing zone bears simultaneously on the axle and on the foot of the torque tube , the bearing zones being connected to one another by flexible ligaments.2. The aircraft brake according to claim 1 , wherein the flexible ligaments are centered in a zone extending between the foot and the torque tube claim 1 , the bearing zones projecting in both directions from the flexible ligaments.3. The aircraft brake according to claim 1 , wherein the flexible ligaments are of a thickness that is less than 25% of a thickness of the bearing zones.4. The aircraft brake according to claim 1 , wherein the functional clearance is in the range of 0.2 mm to 0.8 mm.5. The aircraft brake according to claim 1 , comprising a circularly repeating pattern in succession of a bearing zone for bearing on the axle claim 1 , a first flexible ligament claim 1 , a bearing zone for bearing on the foot of the torque tube claim 1 , and a second flexible ligament. The disclosure relates to an antivibration centering ring for the foot of a torque tube in an aircraft ...

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Номер записи: 73
14-01-2016 дата публикации

SMART ELECTRIC TAXI PATH CONTROL

Номер: US20160012736A1
Автор: Jackson Patrick, Nutaro Joseph, Sims Jay
Принадлежит: HONEYWELL INTERNATIONAL INC.

An aircraft taxi control system may include a motor connected to drive a landing gear wheel of the aircraft. A motor controller may be connected to control speed of the motor. The system may also include an aircraft taxi route database, an aircraft position determination unit; an aircraft performance database and a processor configured to a) integrate signals from the aircraft taxi route database, the aircraft position determination unit and aircraft performance database, and b) produce a motor deceleration signal to the motor controller when the aircraft arrives at a predetermined distance from a predetermined location so that the aircraft arrives at the location traveling at a desired speed 1. An aircraft taxi control system comprising:at least one motor connected to drive at least one landing gear wheel of the aircraft;a motor controller connected to control speed of the at least one motor;an aircraft taxi route database;an aircraft position determination unit;an aircraft performance database; a) integrate signals from the aircraft taxi route database, the aircraft position determination unit and aircraft performance database, and', 'b) produce a motor deceleration signal, based on the signals integrated in step (a), to the motor controller when the aircraft arrives at a predetermined distance from a predetermined location so that the aircraft arrives at the predetermined location traveling at a desired speed without a need for manual speed adjustment by a pilot of the aircraft., 'a processor configured to,'}2. The taxi control system of wherein the predetermined location is a turning location.3. The taxi control system of wherein the predetermined location is a hold location.4. The taxi control system of further comprising a regenerative braking system wherein the processor is configured to produce a regenerative braking command in addition to the motor deceleration signal on an as needed basis so that the aircraft arrives at the predetermined location traveling ...

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Номер записи: 74
09-01-2020 дата публикации

INTELLIGENT AIRPORT RAMP AND ELECTRIC TAXI-DRIVEN AIRCRAFT GROUND MOVEMENT MONITORING SYSTEM

Номер: US20200013301A1
Автор: Cox Isaiah W., Cox Joseph J., Vana Jan
Принадлежит: BOREALIS TECHNICAL LIMITED

A monitoring system and method are provided to monitor ground movement of aircraft driven with electric taxi drive systems and movement of ground service vehicles and equipment and personnel within airport ramp areas. Monitor and sensor devices, including those that are intelligent and employ scanning technology to generate image, positional, and other data may be mounted in locations on aircraft, ground service vehicles and equipment, passenger loading bridges, an airport terminal, and other ramp locations to generate a constant stream of data as the aircraft moves into, within, and out of an airport ramp area. The data stream is transmitted to an artificial intelligence-based processing system to identify and communicate possible safety hazards to multiple locations so that the aircraft's ground travel or a ground vehicle's travel may be altered to avoid identified safety hazards and to avoid collisions. 1. A monitoring system that provides a maximal amount of information about an airport ramp area environment from a constant stream of data generated during the ground movement of electric taxi system-driven aircraft within the airport ramp area to improve safety of ramp operations , comprising:a. an airport ramp area at an airport terminal with a plurality of gates, passenger loading bridges attached to said terminal at said gates, moving ground service vehicles and equipment, and nonmoving structures within said ramp area;b. aircraft equipped with landing gear wheel-mounted electric taxi drive systems to drive said aircraft within said airport ramp area and a display screen in a cockpit of said aircraft visible to a pilot and crew of said aircraft;c. a plurality of monitoring devices mounted in exterior locations on said electric taxi system-driven aircraft and at least on said ground service vehicles and equipment and on said nonmoving structures within said ramp area operative to provide fields of view of said aircraft exterior and said ramp area from said ...

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Номер записи: 75
03-02-2022 дата публикации

PISTON ENGAGING MEMBER

Номер: US20220033070A1
Автор: Pacak Pawel, Stras Karol, Wyszowski Adam
Принадлежит: GOODRICH CORPORATION

A piston engaging member of a piston assembly for engaging a pressure plate of an aircraft brake system, the engaging member comprising a body having a first side configured to selectably engage with the pressure plate, and a mount on a second side of the body configured to mount the piston engaging member with a piston of the piston assembly wherein the body comprises a cellular structure between the first and second sides. 1. A piston engaging member of a piston assembly for engaging a pressure plate of an aircraft brake system , the engaging member comprising:a body having a first side configured to selectably engage with the pressure plate; anda mount on a second side of the body configured to mount the piston engaging member with a piston of the piston assembly;wherein the body comprises a cellular structure between the first and second sides.2. The piston engaging member of claim 1 , wherein the cellular structure comprises a plurality of walls and a plurality of cavities defined by the walls.3. The piston engaging member of claim 2 , wherein the plurality of walls are arranged in a regular pattern.4. The piston engaging member of claim 2 , wherein the angle between intersecting walls in at least one cavity is 90 degrees and/or 45 degrees.5. The piston engaging member of any of claims 2 , wherein the plurality of walls comprise a first wall and a second wall claims 2 , wherein a thickness of the first wall is greater than a thickness of the second wall.6. The piston engaging member of claim 5 , wherein the second wall is disposed radially outwardly of the first wall.7. The piston engaging member of claim 2 , wherein the spacing between adjacent walls varies in at least one of an axial claim 2 , radial and circumferential direction.8. The piston engaging member of claim 1 , wherein the cellular structure is a first portion of the body claim 1 , and the body comprises a second portion claim 1 , wherein the density of the second portion is greater than the ...

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Номер записи: 76
19-01-2017 дата публикации

AIRCRAFT LANDING GEAR

Номер: US20170015408A1
Автор: IORDANIDIS George, REES John, Yates Michael
Принадлежит:

A aircraft landing gear for an aircraft, comprising a plurality of wheels, an electrically powered drive system comprising a drive motor arranged to drive at least one of the plurality of wheels, and an electrically powered braking system comprising a brake arranged to brake at least one of the plurality of wheels. A power supply unit is arranged to provide a supply of power to the electrically powered drive system, and also to the electrically powered braking system. 2. An aircraft landing gear as claimed in claim 1 , wherein the power supply unit is arranged to receive a supply of power generated from the engines of the aircraft.3. An aircraft landing gear as claimed in claim 1 , wherein the power supply unit is arranged to receive a supply of power from a battery.4. An aircraft landing gear as claimed in claim 1 , wherein the electrically powered braking system comprises a brake control unit arranged to operate the brakes of the electrically powered braking system claim 1 , wherein the brake control unit is arranged to receive a DC voltage power supply from the power supply unit.5. An aircraft landing gear as claimed in claim 1 , wherein the electrically powered drive system comprises a drive control unit arranged to operate the drive motor of the electrically powered drive system claim 1 , wherein the drive control unit is arranged to receive a DC voltage power supply from the power supply unit.6. An aircraft landing gear as claimed in claim 1 , wherein the electrically powered drive system is arranged to receive a multi-phase AC voltage power supply from the power supply unit to operate the drive motor of the electrically powered drive system.7. An aircraft landing gear as claimed in claim 5 , wherein the power supply unit is arranged to be switchable between a first mode in which it supplies a DC voltage power supply to the electrically powered braking system claim 5 , and a second mode in which it supplies a multi-phase AC voltage power supply to the ...

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Номер записи: 77
19-01-2017 дата публикации

ROLLER-BASED DRIVE SYSTEMS WITH COMPLIANCE FOR ACCOMMODATING NON-CONJUGATE MESHING

Номер: US20170015409A1
Автор: Christensen Donald Jeffrey, Mitchell Robert
Принадлежит: HONEYWELL INTERNATIONAL INC.

A gearbox for driving a sprocket includes a gear train and an output shaft assembly positioned between the gear train and a power output end of the gearbox. The output shaft assembly includes, a first shaft segment extending to the power output a second shaft segment coupled to the gear train and a torsion spring interposed between the first shaft segment and the second shaft segment. Upon non-conjugate meshing of the sprocket, the torsion spring expands and contracts so that the angular velocity of the second shaft segment differs from the angular velocity of the first shaft segment. 1. An electric taxi system (ETS) for an aircraft comprising:a roller-based drive system; and a first shaft segment coupled to a driving element of the roller-based drive system,', 'a second shaft segment coupled to a gear train of the gearbox, and', 'a torsion spring,', 'wherein the torsion spring interposed between and coupled to the first shaft segment and the second shaft segment, to form a first torque-transmitting path through the output shaft assembly, 'a gearbox having an output shaft assembly, the output shaft assembly including;'}2. The ETS of wherein the roller-based drive system includes a chain attached circumferentially around a wheel of the aircraft.3. The ETS of wherein the chain is a roller chain.4. The ETS of : includes rollers attached directly to a wheel of the aircraft.5. The ETS of further comprising;a spring-load limiting system;wherein the gearbox has a second torque-transmitting path in which the first shaft segment is connected to the second shaft segment through the spring-load limiting system.6. The ETS of wherein the spring-load limiting system comprises:a flange of the first shaft segment;at least one slot in the flange;at least one key coupled to the second shaft segment and to the torsion spring;wherein the at least one slot is larger than the at least one key;wherein the at least one key is engageable with a side of the at least one slot upon occurrence ...

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Номер записи: 78
19-01-2017 дата публикации

METHODS AND CONTROL SYSTEMS FOR CONTROLLING A DRIVE SYSTEM OF AN AIRCRAFT

Номер: US20170015410A1
Автор: COLOSIMO Antonio, Guery Xavier, SZNAJDER Lukasz
Принадлежит:

A method of controlling a drive system of an aircraft. The drive system comprised a drive motor arranged to drive at least one wheel of an aircraft landing gear. A power signal indicative of a power level for the drive motor and a speed signal indicative of a rotation speed of the drive motor are received. A torque level for the drive motor is determined using the power signal and the speed signal. The drive motor is then driven such that the torque generated by the drive motor is at the determined torque level. 1. A method of controlling a drive system of an aircraft , wherein the drive system comprises a drive motor arranged to drive at least one wheel of the aircraft landing gear , the method comprising the steps of:receiving a power signal indicative of a power level for the drive motor;receiving a speed signal indicative of a rotation speed of the drive motor;determining a torque level for the drive motor using the power signal and the speed signal;driving the drive motor such that the torque generated by the drive motor is at the determined torque level.2. A method as claimed in claim 1 , wherein the torque level is determined by dividing the power level indicated by the power signal by the rotation speed indicated by the speed signal.3. A method as claimed in claim 1 , wherein the torque level is at most a predefined maximum torque level.4. A method as claimed in claim 1 , wherein the torque level is claim 1 , if non-zero claim 1 , at least a predefined minimum torque level.5. A method as claimed in claim 1 , wherein the torque level is increased over time by at most a predefined maximum torque rate.6. A method as claimed in claim 1 , wherein if the rotation speed indicated by the speed signal is below a predefined minimum rotation speed claim 1 , the torque level is determined using the predefined minimum rotation speed.7. A method as claimed in claim 1 , wherein the power level indicated by the power signal is a percentage of a predefined maximum power ...

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Номер записи: 79
21-01-2016 дата публикации

ELECTRIC BRAKING SYSTEM AND METHOD RELYING ON VOLTAGE HYSTERESIS FOR APPLIED BRAKE POWER CONTROL

Номер: US20160016563A1
Автор: DI ZAZZO Marco, PLANTE Bertrand
Принадлежит:

A method of operating electric brakes for a vehicle including monitoring at least a voltage in a power system of the vehicle, and adjusting a power provided to the electric brakes based on at least the monitored voltage to control a current according to a predetermined behavior.

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Номер записи: 80
21-01-2016 дата публикации

Determining integrity of braking control system

Номер: US20160016576A1
Автор: George Howell, Matthieu DELLA NAVE
Принадлежит: Airbus Operations Ltd

A method of determining the integrity of an electric or hydraulic braking control system. A reduction rate of a voltage or hydraulic pressure in the braking control system is determined, and the integrity of the braking control system is determined by comparing the reduction rate with a threshold. The braking control system may be an aircraft braking control system, and the method may be performed during flight of the aircraft—typically during cruise.

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Номер записи: 81
21-01-2016 дата публикации

Aircraft Auxiliary Drive Wheel Taxi System

Номер: US20160016658A1
Автор: Luk Wing S., Walitzki Hans J.
Принадлежит: BOREALIS TECHNICAL LIMITED

An auxiliary drive wheel taxi system for driving an aircraft autonomously without reliance on engine operation during ground travel is designed for installation in an aircraft location other than on nose or main landing gear components. The auxiliary drive wheel taxi system may be mounted in an integral housing located internally or externally on an aircraft's body at a selected location relative to main or nose landing gears and includes one or more auxiliary drive wheels mounted on an extensible strut adapted to extend from and retract into the housing. An electric, hydraulic, or pneumatic non-engine drive means controllable to provide torque required to rotate the drive wheel and drive the aircraft at desired taxi speeds may be mounted in a selected location to drive the auxiliary drive wheel. The manually or automatically controllable auxiliary taxi system is operable only to drive the aircraft during taxi.

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Номер записи: 82
21-01-2016 дата публикации

METHOD FOR ADDING VALUE TO OPERATION OF LONG HAUL AIRCRAFT

Номер: US20160016659A1
Автор: Cox Isaiah W., Cox Joseph J., Cox Rodney T.
Принадлежит: BOREALIS TECHNICAL LIMITED

A method is provided for adding value to operation of long haul aircraft when aircraft designed for long haul flight are moved quietly and efficiently on the ground without operation of aircraft engines. The number of long haul aircraft at airports with slot controls, including airports that are constrained from operation at certain times by curfews that limit hours when long haul aircraft are able to operate, can be increased significantly. Long haul aircraft powered by onboard non-engine drive means or moved manually or automatically by tugs, tow vehicles, or other transfer apparatus have the capability to move quietly and efficiently to a runway to be ready for takeoff as soon as curfew is lifted and to move without engines to an airport arrival location after landing right before curfew starts, effectively expanding and increasing the number of available long haul slots and the value of operating long haul aircraft.

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Номер записи: 83
21-01-2016 дата публикации

Force Command Update Rate Detection

Номер: US20160016660A1
Автор: Abbott Michael, Ayichew Efrem E.
Принадлежит:

The present disclosure relates to rate detection components, and more particularly, to a rate detection system that determines the update rate of commands. The update rate of the commands may be determined in response to the incidence of similarities and differences among samples of the commands.

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Номер записи: 84
21-01-2016 дата публикации

DIFFERENTIAL BRAKING OF AIRCRAFT LANDING GEAR WHEELS

Номер: US20160016661A1
Автор: BEN Livier, HOWELL George, ROMANA Louis-Emmanuel
Принадлежит:

A method of braking left and right landing gear wheels on respective left and right sides of an aircraft. A desired left braking parameter (L) is received for the left wheel and a desired right braking parameter (R) is received for the right wheel. The left wheel is braked with a reduced left braking parameter (L′) which is less than the desired left braking parameter (L), and the right wheel is braked with a reduced right braking parameter (R′) which is less than the desired right braking parameter (R). A difference between the braking parameters is maintained so that L′−W=L−R.

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Номер записи: 85
18-01-2018 дата публикации

WHEEL REFERENCE BALANCE ESTIMATOR

Номер: US20180015910A1
Автор: Georgin Marc
Принадлежит: GOODRICH CORPORATION

Systems and methods are disclosed herein for controlling braking systems. In this regard, a method for controlling brakes may comprise receiving, by an antiskid control (ASK), a first wheel speed, calculating, by the ASK, a first wheel reference speed (WRS), and calculating, by the ASK, a first wheel reference estimate (WRE). In various embodiments, the method may further comprise determining if the first WRS is within a threshold value of the first WRE. In various embodiments, the method may further comprise calculating an ASK desired pressure. The ASK desired pressure may be calculated using the first WRS in response to the first WRS being within the threshold value of the first WRE. The ASK desired pressure may be calculated using the first WRE in response to the first WRS being outside the threshold value of the first WRE. 1. A method for controlling brakes , comprising:receiving, by an antiskid controller (ASK), a first wheel speed;calculating, by the ASK, a first wheel reference speed (WRS);calculating, by the ASK, a first wheel reference estimate (WRE); anddetermining, by the ASK, if the first WRS is within a threshold value of the first WRE.2. The method of claim 1 , further comprising:calculating, by the ASK, an ASK desired pressure, wherein, in response to the first WRS being within the threshold value of the first WRE, the ASK desired pressure is calculated using the first WRS.3. The method of claim 1 , further comprising:calculating, by the ASK, an ASK desired pressure, wherein, in response to the first WRS being outside the threshold value of the first WRE, the ASK desired pressure is calculated using the first WRE.4. The method of claim 1 , further comprising:receiving, by the ASK, a second wheel speed; andcalculating, by the ASK, a second WRS, wherein the first WRE is calculated using the first WRS and the second WRS.5. The method of claim 4 , further comprising:receiving, by the ASK, a third wheel speed;receiving, by the ASK, a fourth wheel speed; ...

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Номер записи: 86
18-01-2018 дата публикации

Antiskid brake control system with minimum disruption autobrake function

Номер: US20180015911A1
Автор: Marc Georgin
Принадлежит: Goodrich Corp

A method for controlling brakes may comprise detecting, by a brake control unit (BCU), an aircraft speed, determining, by the BCU, that the aircraft speed is at least one of at or above a threshold value, determining, by the BCU, that an auto-brake control has been enabled, receiving, by the BCU, an antiskid desired pressure that is output from an antiskid control, the BCU comprising a brake control executive (BKX), the antiskid desired pressure being received by the BCU, and receiving, by the BCU, a desired pressure comprising at least one of a deceleration control desired pressure from a deceleration control (DK) or a pilot desired pressure from a manual brake control, the desired pressure being received by the BKX.

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Номер записи: 87
18-01-2018 дата публикации

USE OF AUTOMATIC PITCH CONTROL TO IMPROVE BRAKING PERFORMANCE

Номер: US20180015997A1
Автор: DA COSTA Tiago Francisco Gomes, PAVÃO Fernando Antonio, ZAMBRANO Gustavo José
Принадлежит:

A flight control law enhances braking efficiency through the operation of aircraft elevators (or another pitch control system) using measured longitudinal acceleration and/or pedal position as references to the control law. Through this solution, it is possible to increase the vertical load in the main landing gear and consequently enhance braking efficiency. 1. A system for improving braking efficiency of an aircraft having an elevator or other rear pitch control surface , the system comprising:an acceleration sensor that measures longitudinal acceleration of the aircraft;a brake pedal sensor that measures position of a brake pedal; anda controller coupled to the acceleration sensor and/or the brake pedal sensor, the controller implementing a flight control law that enhances braking efficiency of the aircraft through the operation of the elevator or other pitch control surface by using measured longitudinal acceleration and/or pedal position as references to the control law, to thereby selectively increase the vertical load in the main landing gear and consequently enhance the braking efficiency of the aircraft.2. The system of wherein the aircraft includes a nose wheel that has no associated brakes.3. The system of wherein the acceleration sensor comprises a linear accelerometer.4. The system of wherein the controller outputs a signal to change the position of the elevator or other pitch control surface in response to the measured longitudinal acceleration and/or brake pedal position.5. The system of wherein the controller produces an output that controls the control surface to at least partially counteract the nose-down moment generated by main landing gear brakes claim 1 , the nose-down moment having the effect of decreasing the local load on the main landing gear and increasing the load on nose landing gear.6. The system of wherein the controller adjusts the relationship between acceleration and/or brake pedals with control surface deflection to always keep at ...

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Номер записи: 88
18-01-2018 дата публикации

LANDING GEAR ARRANGEMENT

Номер: US20180016001A1
Автор: BERNARD James, Ganis Rony Giovanni
Принадлежит: GOODRICH CORPORATION

An arrangement for landing gear comprises a piston, a bogie beam and forward and rear brake rods. The piston has an attachment portion with a pivot connection for the bogie beam at its lower end. The bogie beam is mounted to the attachment portion at the pivot connection. The bogie beam supports forward and rear brake assemblies on forward and rear sides of the piston. The forward brake rod is connected to the forward brake assembly at a location for acting under tension during braking and the rear brake rod is connected to the rear brake assembly at a location for acting under tension during braking. The rear end of the forward brake rod is connected to the attachment portion forward of the pivot connection of the bogie beam, and a forward end of the rear brake rod is connected to the attachment portion. 1. An arrangement for landing gear comprising:a piston having an attachment portion with a pivot connection for a bogie beam at a lower end;a bogie beam mounted to the attachment portion at the pivot connection, the bogie beam supporting forward and rear brake assemblies on forward and rear sides of the piston respectively;a forward brake rod connected to the forward brake assembly at a location for acting under tension during braking; anda rear brake rod connected to the rear brake assembly at a location for acting under tension during braking;characterised in that a rear end of the forward brake rod is connected to the attachment portion forward of the pivot connection of the bogie beam, and a forward end of the rear brake rod is connected to the attachment portion, at a position rearward of the pivot connection.2. The arrangement for landing gear of claim 1 , wherein the forward brake rod has been formed of a fibre composite material comprising fibres placed with an axial orientation (within ±25° of an axial direction of the forward brake rod) claim 1 , wherein the axially orientated fibres follow a helical path inclined at an angle of 5° or more to an axial ...

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Номер записи: 89
17-01-2019 дата публикации

BRAKE HANDLE FOR EMERGENCY ELECTRIC BRAKING

Номер: US20190016326A1
Автор: Georgin Marc, Kordik Michael
Принадлежит: GOODRICH CORPORATION

A brake handle for emergency braking in an emergency electric brake system is disclosed. The emergency electric brake system may comprise a brake control unit (BCU), an electric braking actuating controller (EBAC), and one or more electromechanical brake actuators (EBA). The brake handle may be in direct electronic communication with the EBAC to allow an independent emergency braking input to the EBAC, thus bypassing the BCU in the event of an emergency braking situation. 1. An emergency electric brake system for an aircraft , comprising:a brake handle comprising a displacement sensor configured to detect and measure the displacement of the brake handle, wherein the brake handle is configured to generate a displacement distance data related to the displacement of the brake handle; and a conditioning module configured to receive the displacement distance data from the brake handle, wherein in response to receiving the displacement distance data, the conditioning module is configured to generate an emergency brake signal based on the displacement distance data, and wherein the emergency brake signal comprises a specified brake force; and', 'a control module configured to transmit the emergency brake signal to apply the specified brake force., 'an electric braking actuating controller (EBAC) in direct electronic communication with the brake handle, the EBAC comprising2. The emergency electric brake system of claim 1 , further comprising an electromechanical brake actuator (EBA) in electronic communication with the EBAC.3. The emergency electric brake system of claim 2 , wherein in response to receiving the emergency brake signal from the control module of the EBAC claim 2 , the EBA is configured to apply a braking force in an aircraft brake based on the specified brake force.4. (canceled)5. The emergency electric brake system of claim 1 , wherein the displacement sensor comprises at least one of a linear variable differential transformer (LVDT) sensor or a rotary ...

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Номер записи: 90
17-01-2019 дата публикации

Powered Clutch for Aircraft Wheel Drive System

Номер: US20190016446A1
Автор: Isaiah W. Cox, John Hanson, Jonathan S. Edelson, Joseph J. Cox, Yonatan Rotenberg
Принадлежит: Borealis Technical Ltd

A powered clutch assembly is provided for an aircraft landing gear or other vehicle wheel drive system equipped with wheel drive motors controllable to move the aircraft or vehicle during ground travel. Electric power for the clutch assembly is transferred to clutch actuation elements by a rotary power transfer assembly mounted between stationary and rotating elements within the landing gear wheel drive system to clutch actuation elements. Actuation elements are powered to securely lock clutch rotating elements when required to improve the reliability of failsafe operation of the clutch assembly when torque should not be transferred and to unlock clutch rotating elements when torque should be transferred when the landing gear wheel drive system is used to drive the aircraft during ground travel. Power transferred from the rotary power transfer assembly may also be used to operate components associated with the aircraft drive wheel other than the powered clutch assembly.

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Номер записи: 91
16-01-2020 дата публикации

AIRCRAFT LANDING GEAR ASSEMBLY

Номер: US20200017201A1
Автор: Coq Marie, PRICE NEIL
Принадлежит:

An aircraft landing gear assembly comprising: an axle having an axis, a wheel rotatably mounted on the axle to rotate about the axis, a brake arranged to selectively exert a braking torque on the wheel about the axis, a brake anchor structure having a substantially fixed position relative to the axle, a brake reaction linkage that mechanically couples the brake to the brake anchor structure, and a sensor comprising a sensor element arranged to detect a change in one or more physical properties of a component of the brake reaction linkage in order to determine a stress in the component due to the braking torque, wherein the sensor element does not contact the component. 1. An aircraft landing gear assembly comprising:an axle having an axis;a wheel rotatably mounted on the axle to rotate about the axis;a brake arranged to selectively exert a braking torque on the wheel about the axis;a brake anchor structure having a substantially fixed position relative to the axle;a brake reaction linkage that mechanically couples the brake to the brake anchor structure; anda sensor comprising a sensor element arranged to detect a change in one or more physical properties of a component of the brake reaction linkage in order to determine a stress in the component due to the braking torque, wherein the sensor element does not contact the component.2. The landing gear assembly of claim 1 , wherein the sensor element is arranged to convert an electromagnetic property to an electrical signal.3. The landing gear assembly of claim 2 , wherein the sensor element is a light transducer.4. The landing gear assembly of claim 2 , wherein the sensor element is arranged to detect a magnetic field.5. The landing gear assembly of claim 1 , wherein the sensor is an interferometer.6. The landing gear assembly of claim 1 , wherein the component is a torque tube claim 1 , which surrounds and extends along the axle claim 1 , and stationary brake discs are coupled to the torque tube.7. The landing gear ...

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Номер записи: 92
16-01-2020 дата публикации

ARCHITECTURE FOR LOCKED WHEEL AND ANTISKID PERFORMANCE

Номер: US20200017202A1
Автор: Georgin Marc, Kordik Michael
Принадлежит: GOODRICH CORPORATION

Braking control systems and methods, such as for an aircraft, use a dump valve to rapidly decrease hydraulic pressure applied to a brake actuator during a wheel skid condition. In response to the wheel speed recovering, the dump valve is commanded closed and the brake control system returns to normal braking. The dump valve and a servo-valve may work harmoniously for locked wheel brake control. 1. A brake control system , comprising:a non-transitory memory configured to store instructions; and control a servo valve;', 'determine whether a locked wheel condition is detected;', 'command a dump valve to open in response to the locked wheel condition being detected to release the hydraulic fluid from the hydraulic line;', 'determine whether a wheel speed has recovered; and', 'command the dump valve closed in response to the wheel speed being recovered., 'a controller in electronic communication with the memory, the controller configured to2. The brake control system of claim 1 , further comprising a brake control module claim 1 , comprising:a shutoff valve configured to receive a hydraulic fluid;the servo valve configured to receive the hydraulic fluid from the shutoff valve and configured to provide the hydraulic fluid to apply braking force to a wheel via a hydraulic line; andthe dump valve, wherein the dump valve is in fluid communication with the hydraulic line.3. The brake control system of claim 2 , wherein the controller determines whether the locked wheel condition is detected by determining whether a rotational velocity of the wheel has decreased below a first pre-determined threshold value.4. The brake control system of claim 3 , wherein the controller determines whether the wheel speed has recovered by determining whether the rotational velocity of the wheel has increased above a second pre-determined threshold value.5. The brake control system of claim 2 , wherein the controller commands the dump valve open by sending a dump valve control signal to the dump ...

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Номер записи: 93
21-01-2021 дата публикации

AIRCRAFT TOW POINT

Номер: US20210016898A1
Автор: Douglass Daniel B.
Принадлежит:

An aircraft is presented. The aircraft comprises a tow point positioned on a body of the aircraft and forward of main landing gear of the aircraft, wherein the tow point is connected to an airframe of the aircraft to accept and distribute forces forward, aft, and normal to the aircraft. 1. An aircraft comprising:a tow point positioned on a body of the aircraft and forward of main landing gear of the aircraft, wherein the tow point is connected to an airframe of the aircraft to accept and distribute forces forward, aft, and normal to the aircraft.2. The aircraft of claim 1 , wherein the tow point is positioned at approximately a center of gravity of the aircraft.3. The aircraft of claim 1 , wherein the tow point comprises a receptacle configured to receive a connector of an aircraft tow vehicle.4. The aircraft of claim 1 , wherein the tow point is connected to a keel beam of the airframe.5. The aircraft of further comprising:an actuated door covering the tow point.6. The aircraft of further comprising:reinforced skin surrounding the tow point, the reinforced skin configured to provide support for forces received through the tow point.7. A method of towing an aircraft comprising:coupling a connector of an aircraft tow vehicle to a tow point of the aircraft to form an interface, the tow point positioned on skin of the aircraft and forward of main landing gear of the aircraft;applying an upward force to the tow point of the aircraft by the aircraft tow vehicle; andtowing the aircraft at least one of forward or aft by driving the aircraft tow vehicle while the connector is coupled to the tow point.8. The method of further comprising:steering the aircraft laterally using aircraft controls of the aircraft as the aircraft is towed by the aircraft tow vehicle.9. The method of further comprising:maintaining lateral placement of the aircraft tow vehicle within a tolerance as the aircraft is towed.10. The method of claim 7 , wherein applying the upward force to the tow point ...

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Номер записи: 94
21-01-2016 дата публикации

CONTROL ACTUATION SMOOTHING

Номер: US20160020928A1
Автор: Abbott Michael, Ayichew Efrem E.
Принадлежит:

The present disclosure relates to control actuation smoothing, and more particularly, to a control actuation smoothing system that smoothes brake actuation. The smoothing may be determined in response to a filter. In various embodiments, the smoothing may enhance brake component performance. 1. A method of control actuation smoothing comprising:receiving, by an aircraft brake and steering controller (“ABSC”) comprising a processor and a non-transitory memory, target performance data;receiving, by the ABSC, a force command comprising a braking instruction;comparing, by the ABSC, the force command to an expected brake behavior;determining, by the ABSC, an error between the force command and the expected brake behavior;filtering, by the ABSC, the force command in response to the error and target performance data; andoutputting, by the ABSC, a smoothed force command in response to the filtering.2. The method according to claim 1 , wherein the target performance data comprises a precedent force command.3. The method according to claim 2 , wherein the precedent force command comprises a smoothed brake instruction output by the ABSC earlier in time than the force command.4. The method according to claim 1 , wherein the target performance data comprises brake assembly position data.5. The method according to claim 1 , wherein the braking instruction comprises an approximate step function claim 1 , and wherein the smoothed force command comprises a first-order approximation.6. The method according to claim 5 , wherein filtering comprises reshaping the first-order approximation based on at least one of: target performance data claim 5 , expected brake system response claim 5 , and safety aspects.7. A control actuation smoothing system comprising:a filter;a target performance data input comprising a logical input in communication with target performance data and the filter;a control data input comprising a logical input in logical communication with a control data source and ...

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Номер записи: 95
16-01-2020 дата публикации

HYBRID ELECTRIC AND HYDRAULIC BRAKE SYSTEM

Номер: US20200018368A1
Автор: Poisson Richard A.
Принадлежит: GOODRICH CORPORATION

A braking system is provided. The braking system may comprise a brake stack and an electromechanical actuator mechanically coupled to the brake stack. A first hydraulic chamber may also be mechanically coupled to the brake stack and in fluid communication with a first piston of the electromechanical actuator. A second piston may be in fluid communication with the first hydraulic chamber. The second piston may also be configured to translate towards the brake stack in response to a translation of the first piston. 1. A hybrid actuation system , comprising:a first electromechanical actuator comprising a first piston;a first hydraulic chamber mechanically coupled to the first electromechanical actuator with the first piston in fluid communication with the first hydraulic chamber;a second piston in fluid communication with the first hydraulic chamber, the second piston configured to translate in response to a translation of the first piston;a second hydraulic chamber in fluid communication with the first hydraulic chamber;a second electromechanical actuator comprising a third piston, the second electromechanical actuator mechanically coupled to the second hydraulic chamber with the third piston in fluid communication with the second hydraulic chamber.2. The hybrid actuation system of claim 1 , wherein the first hydraulic chamber comprises a hydraulic manifold.3. The hybrid actuation system of claim 2 , further comprising a fourth piston in fluid communication with the hydraulic manifold claim 2 , wherein the second piston and the fourth piston are configured to apply an equalized force.4. The hybrid actuation system of claim 1 , further comprising a conduit coupled between the first hydraulic chamber and the second hydraulic chamber.5. The hybrid actuation system of claim 1 , further comprising a valve configured to disable fluid communication between the first hydraulic chamber and the second hydraulic chamber in response to the valve closing.6. The hybrid actuation ...

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Номер записи: 96
22-01-2015 дата публикации

METHOD FOR ACCELERATED POWERED SELF PUSH BACK OF AN AIRCRAFT

Номер: US20150021431A1
Автор: Cox Isaiah W., Cox Joseph J., Kracht Stefan, Vana Jan
Принадлежит:

A method for accelerated power push back of an aircraft equipped with a pilot-controlled engines-off taxi system that drives the aircraft without reliance on the aircraft's main engines or tugs is provided. An aircraft is quickly and efficiently moved out of a gate where it is positioned in a nose-in orientation. The pilot controls the taxi system to drive the aircraft in reverse along a perpendicular path away from the terminal to a location where there is sufficient space for the aircraft to stop and turn, and the aircraft is turned and driven in a forward direction to a takeoff runway. Pilot reliance on ground personnel guidance during push back maneuvers is minimized by providing a monitoring system designed to monitor gate and ramp areas around the aircraft in any visibility or environmental conditions and provide feedback to the pilot. 1. A method for accelerated power push back of an aircraft equipped with an engines-off taxi system for autonomous ground movement , comprising controlling operation of an engines-off taxi to push back an aircraft parked in a nose-in position at an airport terminal , whereby a pilot of said aircraft first controls said engines-off taxi system to drive said aircraft in a reverse direction away from said terminal along a path perpendicular to said terminal to a location a selected distance away from said terminal where said aircraft is positioned parallel to the terminal in said location and may be safely turned around; and the pilot further controls said engines-off taxi system to turn said aircraft through a selected angle and to then drive said aircraft in a forward direction to a takeoff runway.2. The method of claim 1 , further comprising said pilot controlling the engines-off taxi system to drive the aircraft in reverse a selected distance away from the terminal comprising 15 to 20 meters.3. The method of claim 1 , further comprising said pilot controlling the engines-off taxi system to drive the aircraft in reverse a ...

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Номер записи: 97
22-01-2015 дата публикации

Apparatus for causing an aircraft wheel to rotate

Номер: US20150021435A1
Автор: Abbasszadeh Mehrdad, Abbasszadeh Mohammad Taghi
Принадлежит:

A rotator assembly for rotating an aircraft landing wheel by the action of the airstream flowing thereby has a circular plate mounted on the wheel and a plurality of independently movable cone shape connected to the outer surface of the plate in circumferentially spaced relation. Each cone shape member has a circle leading edge facing generally in the direction in which the wheel is to be rotated. As the wheel rotates, the members, which were previously pivoted outward, become engaged by the airstream and are sequentially forced inward against the plate. 1a circular plate adapted to be mounted on an aircraft-landing wheel;a plurality of independently movable cone shape members connected to an outer surface of said plate in circumferentially spaced relation about the axis of rotation of the wheel and each having an opening facing generally in the direction in which the wheel is to be rotated,wherein all of said cone shaped members are maintained inward against said plate outer surface and a pivoting condition allowing each one of said cone shaped members to pivot independently relative to said plate outer surface; andthe airstream engaging said cone shaped members which face generally toward the airstream; and whereinas the wheel rotates, said cone shaped members are sequentially forced inward against said plate outer surface.. A rotator assembly for rotating an aircraft-landing wheel by the action of the airstream flowing thereby comprising: This application claims priority to U.S. Provisional Application No. 61/672,886 entitled “ Mechanism of reduce horizontal friction in airplane landing” filed Jul. 18, 2012 by Mohammad Taghi Abbasszadeh.1. Field of the InventionThis invention relates generally to aircraft landing wheels, and more particularly to an aircraft landing wheel rotator having a plurality of independently movable outwardly pivoting air cone shape members which can be selectively extended outward relative to the landing wheel surface to expose a much ...

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Номер записи: 98
26-01-2017 дата публикации

SYSTEMS AND METHODS FOR AIRCRAFT BRAKING AND TAXIING

Номер: US20170021920A1
Автор: Drennen David, Rehfus Kevin
Принадлежит: GOODRICH CORPORATION

Systems and methods are disclosed for aircraft braking and taxiing systems for use in, for example, an aircraft. In this regard, a system may comprise an electric motor and a clutch. The electric motor may include a first output shaft and a second output shaft. The clutch may selectively engaging the motor to at least one of a driver transmission and a brake transmission, wherein, in response to engagement with the driver transmission, the electric motor drives, exclusively, an aircraft wheel via the first output shaft, wherein, in response to engagement with the brake transmission, the electric motor drives, exclusively, a brake clamping system via the second output shaft to apply force to an aircraft brake disk stack. 1. A braking and taxiing system comprising:an electric motor, wherein said electric motor comprises a first output shaft and a second output shaft,a clutch for selectively engaging the electric motor to at least one of a driver transmission and a brake transmission,wherein, in response to engagement with the driver transmission, the electric motor drives, exclusively, an aircraft wheel via the first output shaft,wherein, in response to engagement with the brake transmission, the electric motor drives, exclusively, a brake clamping system via the second output shaft to apply force to an aircraft brake disk stack.2. The system of claim 1 , wherein the brake clamping system comprises the brake transmission claim 1 , a ballscrew and a ram.3. The system of claim 1 , wherein the first output shaft and the second output shaft are in concentric alignment.4. The system of claim 1 , wherein the driver transmission is located on the opposite side of the electric motor as the brake transmission claim 1 , wherein the electric motor claim 1 , the driver transmission claim 1 , and the brake transmission are in concentric alignment.5. The system of claim 1 , wherein the clutch includes a neutral position claim 1 , wherein claim 1 , in response to engagement in the ...

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Номер записи: 99
26-01-2017 дата публикации

Powered Clutch for Aircraft Wheel Drive System

Номер: US20170021921A1
Автор: Cox Isaiah W., Cox Joseph J., Edelson Jonathan S., Hanson John, Rotenberg Yonatan
Принадлежит: BOREALIS TECHNICAL LIMITED

A powered clutch assembly is provided for an aircraft landing gear or other vehicle wheel drive system equipped with wheel drive motors controllable to move the aircraft or vehicle during ground travel. Electric power for the clutch assembly is transferred to clutch actuation elements by a rotary power transfer assembly mounted between stationary and rotating elements within the landing gear wheel drive system to clutch actuation elements. Actuation elements are powered to securely lock clutch rotating elements when required to improve the reliability of failsafe operation of the clutch assembly when torque should not be transferred and to unlock clutch rotating elements when torque should be transferred when the landing gear wheel drive system is used to drive the aircraft during ground travel. Power transferred from the rotary power transfer assembly may also be used to operate components associated with the aircraft drive wheel other than the powered clutch assembly. 1. A powered clutch assembly automatically or manually controllable to selectively transfer driving torque in an aircraft landing gear drive wheel drive system , comprising:a. a clutch comprising cooperating selective torque transfer elements mounted within a defined volume inside an aircraft landing gear drive wheel in selective torque transfer contact with a drive system and a drive motor;b. rotary power transfer means for transferring electric power from a source of electric power to an aircraft landing gear wheel drive system structure to be powered and for connecting a stationary component of said aircraft landing gear wheel and a rotating component of said aircraft landing gear wheel;c. an electric power transfer system interposed between said rotary power transfer means and a clutch actuation system located on said rotating component; andd. one or more clutch actuation elements in said clutch actuation system in electric power transfer communication with said rotary power transfer means ...

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Номер записи: 100