Настройки

Укажите год
-

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

Подробнее
-

Мониторинг СМИ

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

Подробнее

Форма поиска

Поддерживает ввод нескольких поисковых фраз (по одной на строку). При поиске обеспечивает поддержку морфологии русского и английского языка
Ведите корректный номера.
Ведите корректный номера.
Ведите корректный номера.
Ведите корректный номера.
Укажите год
Укажите год
Применить Всего найдено 24. Отображено 24.
08-11-2016 дата публикации

Variable area fan nozzle systems with improved drive couplings

Номер: US0009488130B2
Автор: Kevin K. Chakkera, Ron Vaughan, CHAKKERA KEVIN K, VAUGHAN RON, Chakkera Kevin K., Vaughan Ron
Принадлежит: HONEYWELL INTERNATIONAL INC., HONEYWELL INT INC

A VAFN system is provided for a fan case of an engine. The system includes a motor; a gearbox; an actuator; a nozzle; and a drive coupling extending between the gearbox and the actuator and configured to transmit the mechanical torque from the motor to the actuator. The drive coupling includes an external tube extending from a first one of the gearbox or the actuator, the external tube defining first and second slots extending in a longitudinal direction, and an internal tube extending from a second one of the gearbox or the actuator and at least partially extending within the external tube, the internal tube including a pin with first and second ends respectively positioned within the first and second slots such that the internal tube is configured to translate within the external tube and to be rotatably coupled to the external tube.

Подробнее
Номер записи: 1
02-03-2017 дата публикации

ACTUATOR INCLUDING HANDLING-PROOF POSITION FEEDBACK MECHANISM

Номер: US20170059020A1
Автор: Ron Vaughan, Kevin K. Chakkera, Paul T. Wingett, VAUGHAN RON, CHAKKERA KEVIN K, WINGETT PAUL T, Vaughan Ron, Chakkera Kevin K., Wingett Paul T.
Принадлежит: HONEYWELL INTERNATIONAL INC.

An actuator includes a housing assembly, an actuator shaft, an actuation member, and an anti-rotation rod. The actuator shaft is rotationally mounted in the housing assembly, is adapted to receive a drive torque, and is configured, upon receipt of the drive torque, to rotate. The actuation member is mounted on the actuator shaft, and is configured to translate in response to rotation of the actuator shaft. The anti-rotation rod is coupled to the actuator housing and extends therefrom. The anti-rotation is rod configured to at least selectively engage, and thereby prevent rotation of, the actuation member. 1. An actuator , comprising:a housing assembly;an actuator shaft rotationally mounted in the housing assembly, the actuator shaft adapted to receive a drive torque and configured, upon receipt thereof, to rotate;an actuation member mounted on the actuator shaft, the actuation member configured to translate in response to rotation of the actuator shaft;a rod engagement structure extending from the actuation member and translatable therewith; andan anti-rotation rod connected to the housing assembly and extending therefrom, the anti-rotation rod configured to only selectively and non-continuously engage the rod engagement structure, the anti-rotation rod includes a first end and a second end;', 'the first end is coupled to the actuator housing;', 'the second end is adapted to be coupled to a fixed structure; and', 'rotation of the actuation member is prevented when the anti-rotation rod engages the rod engagement structure., 'wherein2. The actuator of claim 1 , wherein:the actuator shaft comprises a ball screw; andthe actuation member comprises a ball nut.3. The actuator of claim 1 , wherein:the rod engagement structure comprises a first arm and a second arm, the first arm and the second arm spaced apart from each other to define a rod passageway; andthe anti-rotation rod extends through the rod passageway.4. The actuator of claim 1 , wherein the anti-rotation rod is ...

Подробнее
Номер записи: 2
27-10-2016 дата публикации

LOCKING MANUAL DRIVE UNIT FOR AIRCRAFT ENGINE NACELLE DOOR OPERATING SYSTEM

Номер: US20160312511A1
Автор: Kevin K. Chakkera, Timm E. Hartman, Ron Vaughan, Stephen Birn, CHAKKERA KEVIN K, HARTMAN TIMM E, VAUGHAN RON, BIRN STEPHEN, Chakkera Kevin K., Hartman Timm E., Vaughan Ron, Birn Stephen
Принадлежит: HONEYWELL INTERNATIONAL INC.

An aircraft engine nacelle door operating system locking manual drive unit includes a housing, an input drive shaft, an output drive shaft, a lock shaft, and a lock spring. The input drive shaft, the output drive shaft, and the lock shaft are all rotationally mounted in the housing. The output drive shaft continuously engages and mates with the input drive shaft, and he lock shaft extends at least partially into and engages the input drive shaft. The lock shaft is movable between a lock position, in which it engages and mates with the output drive shaft, and an unlock position, in it is disengaged from the output drive shaft. The lock spring supplies a bias force to the lock shaft that urges the lock shaft toward the lock position. 1. An aircraft engine nacelle door operating system locking manual drive unit , the manual drive unit comprising:a housing;an input drive shaft rotationally mounted in the housing, the input drive shaft including a first end, a second end, an inner surface, and an input drive gear, the inner surface defining an axial bore between the first and second ends;an output drive shaft rotationally mounted in the housing, the output drive shaft including an output drive gear that continuously engages and mates with the input drive gear;a lock shaft rotationally mounted in the housing and extending at least partially into the axial bore and engaging the inner surface of the input drive shaft, the lock shaft including a lock gear and movable between a lock position, in which the lock gear engages and mates with the output drive gear, and an unlock position, in which the lock gear is disengaged from the output drive gear; anda lock spring mounted in the housing and engaging the housing and the lock shaft, the lock spring supplying a bias force to the lock shaft that urges the lock shaft toward the lock position.2. The manual drive unit of claim 1 , wherein the input drive shaft and the lock shaft are configured such that the lock shaft is indexed to ...

Подробнее
Номер записи: 3
16-05-2017 дата публикации

Rotary hydraulic motor driven hybrid thrust reverser actuation system with end-of-stroke snubbing

Номер: US0009650993B2
Автор: Kevin K. Chakkera, Ron Vaughan, Steve Abel, CHAKKERA KEVIN K, VAUGHAN RON, ABEL STEVE, Chakkera Kevin K., Vaughan Ron, Abel Steve
Принадлежит: HONEYWELL INTERNATIONAL INC., HONEYWELL INT INC

An aircraft thrust reverser actuation system includes a plurality of actuator assemblies that are each configured, upon receipt of a drive torque, to move to a position. The rotary hydraulic motor is coupled to each of the actuator assemblies and is configured, upon receipt of hydraulic fluid, to rotate and supply the drive torque to each of the actuator assemblies. The control valve is in fluid communication with the rotary hydraulic motor and is configured, upon receipt of electrical current, to move to a valve position based on the magnitude of the received electrical current, to thereby control the direction and flow of hydraulic fluid to the hydraulic motor. The valve control is configured, upon receipt of thrust reverser commands, to supply the electrical current to the control valve and selectively vary the magnitude of the electrical current based on the positions of the actuator assemblies.

Подробнее
Номер записи: 4
13-06-2013 дата публикации

CASE ASSEMBLY WITH FUEL OR HYDRAULIC DRIVEN VAFN ACTUATION SYSTEMS

Номер: US20130145768A1
Автор: Ron Vaughan, Michael McGill, Kevin K. Chakkera, Larry Portolese, Mark Behnke
Принадлежит: HONEYWELL INTERNATIONAL INC.

A variable area fan nozzle (VAFN) system for an aircraft is provided. The VAFN system includes a fluid-driven motor configured to receive a fluid; one or more actuators coupled to the fluid-driven motor; and a nozzle assembly coupled to the actuators such that the motor drives the nozzle assembly during operation. 1. A variable area fan nozzle (VAFN) system for an aircraft , comprising:a fluid-driven motor configured to receive a fluid;one or more actuators coupled to the fluid-driven motor; anda nozzle assembly coupled to the actuators such that the motor drives the nozzle assembly during operation.2. The VAFN system of claim 1 , wherein the fluid-driven motor is a fuel-driven motor and the fluid is fuel claim 1 , and wherein the fluid-driven motor is configured to receive the fuel from a fuel system of the aircraft.3. The VAFN system of claim 2 , wherein the fuel-driven motor is configured to output a torque.4. The VAFN system of claim 3 , wherein the one or more actuators includes a linear actuator driven by the torque provided by the fuel-driven motor.5. The VAFN system of claim 4 , wherein the linear actuator is a ballscrew actuator.6. The VAFN system of claim 4 , wherein the linear actuator has a first portion and a second portion claim 4 , and wherein the linear actuator has a first position in which the first portion is decoupled from the second portion to prevent transmission of the torque between the first and second portions claim 4 , and a second position in which the first portion is coupled to the second portion to transmit the torque between the first and second portions.7. The VAFN system of claim 1 , wherein the fluid-driven motor is a hydraulic-driven motor and the fluid is hydraulic fluid claim 1 , and wherein the hydraulic-driven motor is configured to receive the hydraulic fluid from a hydraulic system of the aircraft.8. The VAFN system of claim 7 , wherein the hydraulic-driven motor is configured to output a torque.9. The VAFN system of claim 8 ...

Подробнее
Номер записи: 5
22-10-2015 дата публикации

ROTARY HYDRAULIC MOTOR DRIVEN HYBRID THRUST REVERSER ACTUATION SYSTEM WITH END-OF-STROKE SNUBBING

Номер: US20150300294A1
Автор: Kevin K. Chakkera, Ron Vaughan, Steve Abel
Принадлежит: HONEYWELL INTERNATIONAL INC.

An aircraft thrust reverser actuation system includes a plurality of actuator assemblies that are each configured, upon receipt of a drive torque, to move to a position. The rotary hydraulic motor is coupled to each of the actuator assemblies and is configured, upon receipt of hydraulic fluid, to rotate and supply the drive torque to each of the actuator assemblies. The control valve is in fluid communication with the rotary hydraulic motor and is configured, upon receipt of electrical current, to move to a valve position based on the magnitude of the received electrical current, to thereby control the direction and flow of hydraulic fluid to the hydraulic motor. The valve control is configured, upon receipt of thrust reverser commands, to supply the electrical current to the control valve and selectively vary the magnitude of the electrical current based on the positions of the actuator assemblies.

Подробнее
Номер записи: 6
28-03-2013 дата публикации

VAFN SYSTEMS WITH IMPROVED DRIVE COUPLING ASSEMBLIES AND BRAKES

Номер: US20130078081A1
Автор: Kevin K. Chakkera, Ron Vaughan, Michael McGill, Stephen Birn
Принадлежит: HONEYWELL INTERNATIONAL INC.

An actuation system is provided for a variable area fan nozzle assembly of an aircraft. The actuation system includes a motor configured to generate a torque; a nozzle; and a drive coupling assembly coupled to the motor and the nozzle. The drive coupling assembly includes a first position in which the torque from the motor is transferred to the nozzle to translate the nozzle and a second position in which the torque from the motor is not transferred to the nozzle. The drive coupling assembly includes a first end portion and a second end portion, the first and second end portions mating with one another in the first position and disengaged from one another in the second position. 1. An actuation system for a variable area fan nozzle assembly of an aircraft , the system comprising:a motor configured to generate a torque;a nozzle; anda drive coupling assembly coupled to the motor and the nozzle, the drive coupling assembly having a first position in which the torque from the motor is transferred to the nozzle to translate the nozzle and a second position in which the torque from the motor is not transferred to the nozzle,wherein the drive coupling assembly comprises a first end portion and a second end portion, the first and second end portions mating with one another in the first position and disengaged from one another in the second position.2. The actuation system of claim 1 , wherein the drive coupling assembly is mounted on a transcowl such that the drive coupling is in the first position when the transcowl is stowed and in the second position when the transcowl is deployed.3. The actuation system of claim 2 , wherein the drive coupling assembly comprisesa first drive shaft coupled to the first end portion;a second drive shaft coupled to the second end portion; anda nozzle actuator coupled to the second drive shaft and mounted on the transcowl such that deployment of the transcowl moves the nozzle actuator and the second drive shaft away from the first drive shaft ...

Подробнее
Номер записи: 7
18-02-2016 дата публикации

THRUST REVERSER ACTUATOR WITH PRIMARY LOCK

Номер: US20160047334A1
Автор: Paul T. Wingett, Kevin K. Chakkera, Ron Vaughan, Dan Birchak, Albert Kang, Rich Gockel, Bill Ryan, Brent Bristol
Принадлежит: HONEYWELL INTERNATIONAL INC.

Actuator assembly includes a housing assembly, a ball screw, a ball nut, and a lock. The ball screw is rotationally mounted on and extends from the housing assembly, is coupled to receive an actuator drive torque, and is configured, upon receipt thereof, to rotate. The ball nut is rotationally supported on the ball screw and is configured, in response to rotation of the ball screw, to translate thereon between a stowed position and a deployed position. The lock is disposed at least partially within the housing assembly and is configured to move between a lock position and an unlock position. The lock prevents the ball nut from translating out of the stowed position when the lock is in the lock position and the ball nut is in the stowed position. 1. An actuator assembly , comprising:a housing assembly;a ball screw rotationally mounted on and extending from the housing assembly, the ball screw coupled to receive an actuator drive torque and configured, upon receipt thereof, to rotate;a ball nut rotationally supported on the ball screw and configured, in response to rotation of the ball screw, to translate thereon between a stowed position and a deployed position; anda lock disposed at least partially within the housing assembly and configured to move between a lock position and an unlock position, the lock comprising a lock pin adapted to receive a lock actuation force and configured, upon receipt thereof, to translate between the lock and unlock position,wherein the lock prevents the ball nut from translating out of the stowed position when (i) the lock is in the lock position and (ii) the ball nut is in the stowed position.2. The actuator assembly of claim 1 , wherein the lock does not prevent the ball nut from translating when the lock is in the unlock position.3. The actuator assembly of claim 1 , further comprising a lock pin opening formed in the ball nut for receiving the lock pin therein.4. The actuator assembly of claim 1 , wherein the lock further comprises: ...

Подробнее
Номер записи: 8
10-10-2013 дата публикации

THRUST REVERSER ACTUATOR WITH PRIMARY LOCK

Номер: US20130264399A1
Автор: Paul T. Wingett, Kevin K. Chakkera, Ron Vaughan, Dan Birchak, Albert Kang, Rich Gockel, Bill Ryan, Brent Bristol
Принадлежит: HONEYWELL INTERNATIONAL INC.

Actuator assembly includes a housing assembly, a ball screw, a ball nut, and a lock. The ball screw is rotationally mounted on and extends from the housing assembly, is coupled to receive an actuator drive torque, and is configured, upon receipt thereof, to rotate. The ball nut is rotationally supported on the ball screw and is configured, in response to rotation of the ball screw, to translate thereon between a stowed position and a deployed position. The lock is disposed at least partially within the housing assembly and is configured to move between a lock position and an unlock position. The lock prevents the ball nut from translating out of the stowed position when the lock is in the lock position and the ball nut is in the stowed position. 1. An actuator assembly , comprising:a housing assembly;a ball screw rotationally mounted on and extending from the housing assembly, the ball screw coupled to receive an actuator drive torque and configured, upon receipt thereof, to rotate;a ball nut rotationally supported on the ball screw and configured, in response to rotation of the ball screw, to translate thereon between a stowed position and a deployed position; anda lock disposed at least partially within the housing assembly and configured to move between a lock position and an unlock position,wherein the lock prevents the ball nut from translating out of the stowed position when (i) the lock is in the lock position and (ii) the ball nut is in the stowed position.2. The actuator assembly of claim 1 , wherein the lock does not prevent the ball nut from translating when the lock is in the unlock position.3. The actuator assembly of claim 1 , wherein the lock comprises:a main body having an actuation end and an engagement end, and rotationally mounted on the housing assembly between the actuation end and the engagement end, the main body adapted to receive a lock actuation force on the actuation end and configured, upon receipt thereof, to rotate between the lock and ...

Подробнее
Номер записи: 9
12-05-2020 дата публикации

Aircraft thrust reverser system with hydraulic assist device

Номер: US0010648428B2
Автор: Steve Abel, James Wawrzynek, Patrick Hinke, Ron Vaughan, ABEL STEVE, WAWRZYNEK JAMES, HINKE PATRICK, VAUGHAN RON, Abel, Steve, Wawrzynek, James, Hinke, Patrick, Vaughan, Ron
Принадлежит: HONEYWELL INTERNATIONAL INC., HONEYWELL INT INC

A thrust reverser system for a gas turbine engine includes a support structure, a transcowl, an actuator, and a hydraulic assist mechanism. The actuator is configured to supply an actuation force to the transcowl to thereby move the transcowl between the stowed and deployed positions. The hydraulic assist mechanism is coupled to the transcowl and is configured to react reverse thrust loads on the transcowl at least when the transcowl is translating between the stowed position and the deployed position.

Подробнее
Номер записи: 10
14-11-2017 дата публикации

Locking manual drive unit for aircraft engine nacelle door operating system

Номер: US0009816586B2
Автор: Kevin K Chakkera, Timm E Hartman, Ron Vaughan, Stephen Birn, CHAKKERA KEVIN K, HARTMAN TIMM E, VAUGHAN RON, BIRN STEPHEN, Chakkera Kevin K, Hartman Timm E, Vaughan Ron, Birn Stephen
Принадлежит: HONEYWELL INTERNATIONAL INC., HONEYWELL INT INC

An aircraft engine nacelle door operating system locking manual drive unit includes a housing, an input drive shaft, an output drive shaft, a lock shaft, and a lock spring. The input drive shaft, the output drive shaft, and the lock shaft are all rotationally mounted in the housing. The output drive shaft continuously engages and mates with the input drive shaft, and he lock shaft extends at least partially into and engages the input drive shaft. The lock shaft is movable between a lock position, in which it engages and mates with the output drive shaft, and an unlock position, in it is disengaged from the output drive shaft. The lock spring supplies a bias force to the lock shaft that urges the lock shaft toward the lock position.

Подробнее
Номер записи: 11
17-11-2015 дата публикации

Thrust reverser actuator with primary lock

Номер: US0009188081B2
Автор: Paul T. Wingett, Kevin K. Chakkera, Ron Vaughan, Dan Birchak, Albert Kang, Rich Gockel, Bill Ryan, Brent Bristol, WINGETT PAUL T, CHAKKERA KEVIN K, VAUGHAN RON, BIRCHAK DAN, KANG ALBERT, GOCKEL RICH, RYAN BILL, BRISTOL BRENT, WINGETT PAUL T., CHAKKERA KEVIN K.
Принадлежит: HONEYWELL INTERNATIONAL INC., WINGETT PAUL T, CHAKKERA KEVIN K, VAUGHAN RON, BIRCHAK DAN, KANG ALBERT, GOCKEL RICH, RYAN BILL, BRISTOL BRENT, HONEYWELL INT INC, WINGETT PAUL T., CHAKKERA KEVIN K.

Actuator assembly includes a housing assembly, a ball screw, a ball nut, and a lock. The ball screw is rotationally mounted on and extends from the housing assembly, is coupled to receive an actuator drive torque, and is configured, upon receipt thereof, to rotate. The ball nut is rotationally supported on the ball screw and is configured, in response to rotation of the ball screw, to translate thereon between a stowed position and a deployed position. The lock is disposed at least partially within the housing assembly and is configured to move between a lock position and an unlock position. The lock prevents the ball nut from translating out of the stowed position when the lock is in the lock position and the ball nut is in the stowed position.

Подробнее
Номер записи: 12
25-06-2019 дата публикации

Thrust reverser actuator with primary lock

Номер: US0010330046B2
Автор: Paul T. Wingett, Kevin K. Chakkera, Ron Vaughan, Dan Birchak, Albert Kang, Rich Gockel, Bill Ryan, Brent Bristol, WINGETT PAUL T, CHAKKERA KEVIN K, VAUGHAN RON, BIRCHAK DAN, KANG ALBERT, GOCKEL RICH, RYAN BILL, BRISTOL BRENT, Wingett, Paul T., Chakkera, Kevin K., Vaughan, Ron, Birchak, Dan, Kang, Albert, Gockel, Rich, Ryan, Bill, Bristol, Brent
Принадлежит: HONEYWELL INTERNATIONAL INC., HONEYWELL INT INC

Actuator assembly includes a housing assembly, a ball screw, a ball nut, and a lock. The ball screw is rotationally mounted on and extends from the housing assembly, is coupled to receive an actuator drive torque, and is configured, upon receipt thereof, to rotate. The ball nut is rotationally supported on the ball screw and is configured, in response to rotation of the ball screw, to translate thereon between a stowed position and a deployed position. The lock is disposed at least partially within the housing assembly and is configured to move between a lock position and an unlock position. The lock prevents the ball nut from translating out of the stowed position when the lock is in the lock position and the ball nut is in the stowed position.

Подробнее
Номер записи: 13
13-06-2013 дата публикации

CASE ASSEMBLY WITH FUEL DRIVEN ACTUATION SYSTEMS

Номер: US20130145743A1
Автор: Ron Vaughan, Michael McGill, Kevin K. Chakkera, Larry Portolese, Mark Behnke
Принадлежит: HONEYWELL INTERNATIONAL INC.

A thrust reverser actuation system (TRAS) for a case assembly of an aircraft is provided. The TRAS includes a fuel-driven motor; one or more actuators coupled to the fuel-driven motor; and a transcowl coupled to the actuators such that the fuel-driven drives the transcowl during operation. 1. A thrust reverser actuation system (TRAS) for a case assembly of an aircraft , comprising:a fuel-driven motor;one or more actuators coupled to the fuel-driven motor; anda transcowl coupled to the actuators such that the fuel-driven drives the transcowl during operation.2. The TRAS of claim 1 , further comprising an electrical control unit configured to control the fuel-driven motor.3. The TRAS of claim 2 , wherein the electrical control unit is an 110V electrical control unit.4. The TRAS of claim 1 , further comprising a fuel control unit configured to provide fuel to the fuel-driven motor.5. The TRAS of claim 1 , wherein the fuel-driven motor is configured to output a torque.6. The TRAS of claim 5 , wherein the one or more actuators includes a linear actuator driven by the torque provided by the fuel-driven motor.7. The TRAS of claim 6 , wherein the linear actuator is a ballscrew actuator.8. The TRAS of claim 1 , wherein the fuel-driven motor is approximately 10-70 horsepower.9. The TRAS of claim 1 , wherein the fuel-driven motor is approximately 14-16 horsepower.10. An engine system for an aircraft claim 1 , comprising:an engine assembly having an inlet and an outlet;a thrust reverser actuation system (TRAS) configured to selectively block the outlet; anda fuel system configured to supply a first portion of fuel to the engine system and a second portion of fuel to the TRAS.11. The engine system of claim 10 , wherein the TRAS comprises a fuel-driven motor;one or more actuators coupled to the fuel-driven motor; anda transcowl coupled to the actuators such that the fuel-driven drives the transcowl during operation.12. The engine system of claim 11 , further comprising an ...

Подробнее
Номер записи: 14
11-07-2017 дата публикации

Aircraft engine cowl door movement control system and method

Номер: US0009701414B2
Автор: Ron Vaughan, Leroy Allen Fizer, James Wawrzynek, Kevin K. Chakkera, Mohamed A. Salam, William Warr, Stephen Birn, VAUGHAN RON, FIZER LEROY ALLEN, WAWRZYNEK JAMES, CHAKKERA KEVIN K, SALAM MOHAMED A, WARR WILLIAM, BIRN STEPHEN, Vaughan Ron, Fizer Leroy Allen, Wawrzynek James, Chakkera Kevin K., Salam Mohamed A., Warr William, Birn Stephen
Принадлежит: HONEYWELL INTERNATIONAL INC., HONEYWELL INT INC

A system and method are provided for controlling the movement of an aircraft engine cowl door between an open position and a closed position. The system includes an electric motor, at least one actuator, and an electrically operated brake. The actuator is coupled to the motor and is operable to move the cowl door between the closed and the open position. The electrically operated brake is coupled to the electric motor and the at least one actuator and is configured, upon being energized, to supply a unidirectional resisting torque load to the electric motor that does not prevent motor rotation.

Подробнее
Номер записи: 15
01-03-2018 дата публикации

AIRCRAFT THRUST REVERSER SYSTEM WITH HYDRAULIC ASSIST DEVICE

Номер: US20180058374A1
Автор: Steve Abel, James Wawrzynek, Patrick Hinke, Ron Vaughan
Принадлежит: HONEYWELL INTERNATIONAL INC.

A thrust reverser system for a gas turbine engine includes a support structure, a transcowl, an actuator, and a hydraulic assist mechanism. The actuator is configured to supply an actuation force to the transcowl to thereby move the transcowl between the stowed and deployed positions. The hydraulic assist mechanism is coupled to the transcowl and is configured to react reverse thrust loads on the transcowl at least when the transcowl is translating between the stowed position and the deployed position.

Подробнее
Номер записи: 16
21-08-2014 дата публикации

ACTUATOR INCLUDING HANDLING-PROOF POSITION FEEDBACK MECHANISM

Номер: US20140230583A1
Автор: Ron Vaughan, Kevin K. Chakkera, Paul T. Wingett, VAUGHAN RON, CHAKKERA KEVIN K, WINGETT PAUL T, CHAKKERA KEVIN K., WINGETT PAUL T.
Принадлежит: HONEYWELL INTERNATIONAL INC.

An actuator includes a housing assembly, an actuator shaft, an actuation member, and an anti-rotation rod. The actuator shaft is rotationally mounted in the housing assembly, is adapted to receive a drive torque, and is configured, upon receipt of the drive torque, to rotate. The actuation member is mounted on the actuator shaft, and is configured to translate in response to rotation of the actuator shaft. The anti-rotation rod is coupled to the actuator housing and extends therefrom. The anti-rotation is rod configured to at least selectively engage, and thereby prevent rotation of, the actuation member.

Подробнее
Номер записи: 17
28-03-2013 дата публикации

VAFN SYSTEMS WITH NOZZLE LOCKING ASSEMBLIES

Номер: US20130075494A1
Автор: Ron Vaughan, Kevin K. Chakkera
Принадлежит: HONEYWELL INTERNATIONAL INC.

A nozzle locking assembly is provided for an aircraft with a thrust reverser actuation system (TRAS) having a transcowl and a variable area fan nozzle (VAFN) system having a nozzle. The nozzle locking assembly includes a rod coupled to a fixed structure of the aircraft; and a locking mechanism mounted on the transcowl and configured to, when the transcowl is in a first position, engage the rod to unlock the nozzle locking assembly and to, when the transcowl is in a second position, disengage from the rod to lock the nozzle locking assembly 1. A nozzle locking assembly for an aircraft with a thrust reverser actuation system (TRAS) having a transcowl and a variable area fan nozzle (VAFN) system having a nozzle , the nozzle locking assembly comprising:a rod coupled to a fixed structure of the aircraft; anda locking mechanism mounted on the transcowl and configured to, when the transcowl is in a first position, engage the rod to unlock the nozzle locking assembly and to, when the transcowl is in a second position, disengage from the rod to lock the nozzle locking assembly.2. The nozzle locking assembly of claim 1 , wherein the locking mechanism is mounted on the transcowl with a torsion spring with a spring force counter to the rod.3. The nozzle locking assembly of claim 2 , wherein the locking mechanism has a first end and a second end claim 2 , the first end engaging the rod in the first position and the second end engaging the nozzle in the second position.4. The nozzle locking assembly of claim 3 , wherein the locking mechanism is pivotably mounted on the transcowl with the torsion spring such that claim 3 , when the transcowl is transitioning between the first position and the second position claim 3 , the first end of the locking mechanism disengages from the rod and the torsion spring pivots the second end of the towards the nozzle to engage the nozzle.5. The nozzle locking assembly of claim 4 , wherein the locking mechanism is pivotably mounted on the transcowl ...

Подробнее
Номер записи: 18
06-12-2016 дата публикации

Actuator including handling-proof position feedback mechanism

Номер: US0009512910B2
Автор: Ron Vaughan, Kevin K. Chakkera, Paul T. Wingett, VAUGHAN RON, CHAKKERA KEVIN K, WINGETT PAUL T, Vaughan Ron, Chakkera Kevin K., Wingett Paul T.
Принадлежит: HONEYWELL INTERNATIONAL INC., HONEYWELL INT INC

An actuator includes a housing assembly, an actuator shaft, an actuation member, and an anti-rotation rod. The actuator shaft is rotationally mounted in the housing assembly, is adapted to receive a drive torque, and is configured, upon receipt of the drive torque, to rotate. The actuation member is mounted on the actuator shaft, and is configured to translate in response to rotation of the actuator shaft. The anti-rotation rod is coupled to the actuator housing and extends therefrom. The anti-rotation is rod configured to at least selectively engage, and thereby prevent rotation of, the actuation member.

Подробнее
Номер записи: 19
19-03-2015 дата публикации

AIRCRAFT ENGINE COWL DOOR MOVEMENT CONTROL SYSTEM AND METHOD

Номер: US20150078879A1
Автор: Ron Vaughan, Leroy Allen Fizer, James Wawrzynek, Kevin K. Chakkera, Mohamed A. Salam, William Warr, Stephen Birn, VAUGHAN RON, FIZER LEROY ALLEN, WAWRZYNEK JAMES, CHAKKERA KEVIN K, SALAM MOHAMED A, WARR WILLIAM, BIRN STEPHEN, CHAKKERA KEVIN K., SALAM MOHAMED A.
Принадлежит:

A system and method are provided for controlling the movement of an aircraft engine cowl door between an open position and a closed position. The system includes an electric motor, at least one actuator, and an electrically operated brake. The actuator is coupled to the motor and is operable to move the cowl door between the closed and the open position. The electrically operated brake is coupled to the electric motor and the at least one actuator and is configured, upon being energized, to supply a unidirectional resisting torque load to the electric motor that does not prevent motor rotation. 1. A system for controlling movement of an aircraft engine cowl door between an open position and a closed position , comprising:an electric motor;at least one actuator coupled to the motor and operable to move the cowl door between the closed and the open position; andan electrically operated brake coupled to the electric motor and the at least one actuator and configured, upon being energized, to supply a resisting torque load to the electric motor that does not prevent motor rotation.2. The system of claim 1 , further comprising:a second electrically operated brake coupled to the electric motor and configured to selectively supply a braking torque to the motor that prevents motor rotation.3. The system of claim 1 , wherein the actuator comprises:a rotationally mounted ball screw shaft, the ball screw shaft coupled to receive torque supplied by the electric motor and configured, upon receipt thereof, to rotate; anda ball nut rotationally supported on the ball screw shaft, the ball nut configured to translate in response to rotation of the ball screw shaft.4. The system of claim 1 , further comprising:a controller coupled to the electric motor and the electrically operated brake, the controller configured to (i) controllably energize the electric motor and (ii) controllably energize the electrically operated brake.5. The system of claim 4 , wherein:the controller is further ...

Подробнее
Номер записи: 20
06-10-2016 дата публикации

FLUID-POWERED THRUST REVERSER ACTUATION SYSTEM WITH ELECTROMECHANICAL SPEED CONTROL

Номер: US20160290283A1
Автор: Ron Vaughan, Kevin K. Chakkera, James Wawrzynek, Leroy Allen Fizer, VAUGHAN RON, CHAKKERA KEVIN K, WAWRZYNEK JAMES, FIZER LEROY ALLEN, Vaughan Ron, Chakkera Kevin K., Wawrzynek James, Fizer Leroy Allen
Принадлежит: HONEYWELL INTERNATIONAL INC.

A fluid-powered thrust reverser actuation system includes electromechanical speed control to implement multiple mid-stroke speeds. The system may also be configured to implement two different operational modes—a normal operational mode and a rejected take-off operational mode. 1. An aircraft thrust reverser actuation system , comprising:a plurality of actuator assemblies, each actuator assembly coupled to receive a drive torque and configured, upon receipt of the drive torque, to move to a position;a fluid-powered motor coupled to each of the actuator assemblies and adapted to selectively receive fluid at a fluid flow rate, the fluid-powered motor configured, upon receipt of the fluid, to rotate and supply the drive torque to each of the actuator assemblies;a position sensor coupled to at least one of the actuator assemblies, the position sensor configured to sense actuator position and supply a position feedback signal representative thereof;a motor speed sensor configured to sense rotational speed of the fluid-powered motor and supply a speed feedback signal representative thereof;a control valve in fluid communication with the fluid-powered motor and coupled to receive valve control signals, the control valve configured, in response to the valve control signals, to move to a commanded valve position, to thereby control the direction and flow of fluid to the fluid-powered motor, and thereby control movement direction and movement speed of the actuator assemblies; anda control coupled to receive thrust reverser commands, the position feedback signal, and the speed feedback signal, the control configured, in response to the thrust reverser commands, the position feedback signal, and the speed feedback signal, to supply valve control signals to the control valve that selectively cause the actuator assemblies to move at a plurality of movement speeds.2. The system of claim 1 , wherein:the actuator assemblies are each configured to move between a fully stowed position ...

Подробнее
Номер записи: 21
03-10-2017 дата публикации

Actuator including handling-proof position feedback mechanism

Номер: US0009777812B2
Автор: Ron Vaughan, Kevin K. Chakkera, Paul T. Wingett, VAUGHAN RON, CHAKKERA KEVIN K, WINGETT PAUL T, Vaughan Ron, Chakkera Kevin K., Wingett Paul T.
Принадлежит: HONEYWELL INTERNATIONAL INC., HONEYWELL INT INC

An actuator includes a housing assembly, an actuator shaft, an actuation member, and an anti-rotation rod. The actuator shaft is rotationally mounted in the housing assembly, is adapted to receive a drive torque, and is configured, upon receipt of the drive torque, to rotate. The actuation member is mounted on the actuator shaft, and is configured to translate in response to rotation of the actuator shaft. The anti-rotation rod is coupled to the actuator housing and extends therefrom. The anti-rotation is rod configured to at least selectively engage, and thereby prevent rotation of, the actuation member.

Подробнее
Номер записи: 22
23-04-2015 дата публикации

VARIABLE AREA FAN NOZZLE SYSTEMS WITH IMPROVED DRIVE COUPLINGS

Номер: US20150107220A1
Автор: Kevin K. Chakkera, Ron Vaughan, CHAKKERA KEVIN K, VAUGHAN RON, CHAKKERA KEVIN K.
Принадлежит: HONEYWELL INTERNATIONAL INC.

A VAFN system is provided for a fan case of an engine. The system includes a motor; a gearbox; an actuator; a nozzle; and a drive coupling extending between the gearbox and the actuator and configured to transmit the mechanical torque from the motor to the actuator. The drive coupling includes an external tube extending from a first one of the gearbox or the actuator, the external tube defining first and second slots extending in a longitudinal direction, and an internal tube extending from a second one of the gearbox or the actuator and at least partially extending within the external tube, the internal tube including a pin with first and second ends respectively positioned within the first and second slots such that the internal tube is configured to translate within the external tube and to be rotatably coupled to the external tube. 1. A variable area fan nozzle (VAFN) system for a fan case of an engine , comprising:a motor configured to provide mechanical torque;a gearbox coupled to the motor to receive the mechanical torque from the motor;an actuator coupled to the gearbox to receive the mechanical torque from the gearbox;a nozzle coupled to the actuator and configured to be driven based on the mechanical torque; and an external tube extending from a first one of the gearbox or the actuator, the external tube defining first and second slots extending in a longitudinal direction, and', 'an internal tube extending from a second one of the gearbox or the actuator and at least partially extending within the external tube, the internal tube including a pin with first and second ends respectively positioned within the first and second slots such that the internal tube is configured to translate within the external tube and to be rotatably coupled to the external tube., 'a drive coupling extending between the gearbox and the actuator and configured to transmit the mechanical torque from the motor to the actuator, the drive coupling comprising'}2. The VAFN system of ...

Подробнее
Номер записи: 23
13-06-2013 дата публикации

CASE ASSEMBLIES WITH COMMON CONTROLS

Номер: US20130146708A1
Автор: Ron Vaughan, Larry Portolese, Michael McGill, Kevin K. Chakkera, Mark E. Behnke, John Taft Morris
Принадлежит: HONEYWELL INTERNATIONAL INC.

A case assembly for an aircraft is provided. The assembly includes a thrust reverser actuation system (TRAS) configured to provide braking assistance to the aircraft; a variable area fan nozzle (VAFN) system configured to adjust an engine exhaust of the aircraft; and a common control group coupled to the TRAS and the VAFN system for controlling operation of the TRAS and the VAFN system. 1. A case assembly for an aircraft , comprising:a thrust reverser actuation system (TRAS) configured to provide braking assistance to the aircraft;a variable area fan nozzle (VAFN) system configured to adjust an engine exhaust of the aircraft; anda common control group coupled to the TRAS and the VAFN system for controlling operation of the TRAS and the VAFN system.2. The case assembly of claim 1 , wherein the common control group includes a Full Authority Digital Engine Controller (FADEC).3. The case assembly of claim 2 , wherein the FADEC is configured to provide deploy and retract commands to the TRAS and the VAFN system.4. The case assembly of claim 3 , wherein the common control group further includes a low voltage controller.5. The case assembly of claim 4 , wherein the low-voltage controller is a 28VDC controller.6. The case assembly of claim 4 , wherein the low-voltage controller includes a common EMI filter associated with the TRAS and the VAFN system.7. The case assembly of claim 4 , wherein the TRAS includes a first motor and the VAFN system includes a second motor claim 4 , and wherein low voltage controller is configured to provide motor command signals based on deploy and retract commands from the FADEC.8. The case assembly of claim 7 , wherein the first motor is a first fuel-driven motor and the second motor is a second fuel-driven motor claim 7 , and wherein the common control group further includes a fuel control unit configured to provide fuel to the first fuel-driven motor and the second fuel-driven motor based on motor commands from the low voltage controller.9. ...

Подробнее
Номер записи: 24