-
公开(公告)号：US11933420B2
公开(公告)日：2024-03-19
申请号：US17208632
申请日：2021-03-22
申请人： Woodward, Inc.
IPC分类号： F15B13/10 , B64C13/42 , B64F5/60 , F15B18/00 , F15B19/00 , F16K11/07 , F16K31/42 , F15B13/04
CPC分类号： F16K31/426 , B64C13/42 , B64F5/60 , F15B13/10 , F15B18/00 , F15B19/005 , F16K11/07 , F15B2013/0409 , F15B2211/6336 , F15B2211/8757
摘要： Embodiments of the disclosure include a redundant control system for a vehicle. The redundant control system includes first and second actuator pistons mechanically coupled to one another and disposed in respective first and second fluid chambers. The first and second actuator pistons are movable by first and second primary stages. One of the primary stages includes a bypass valve with a pilot valve actuatable in response to movement of the first actuator piston.
-
公开(公告)号：US11926408B2
公开(公告)日：2024-03-12
申请号：US17420432
申请日：2020-01-27
申请人： MOOG INC.
CPC分类号： B64C13/42 , F15B20/002 , F15B20/004 , F15B2013/0409 , F15B2013/0413 , F15B2211/3058 , F15B2211/31547 , F15B2211/31594 , F15B2211/41581 , F15B2211/7058 , F15B2211/7107 , F15B2211/8623 , F15B2211/8633 , F15B2211/8752 , F15B2211/8757
摘要： A failsafe vale provides “Hole-In-The-Wall” failsafe functionality for thin-wing aircraft control surface actuation systems having a geared rotary actuator powered by a hydraulic rotary motor. The failsafe valve is associated with the hydraulic rotary motor and mechanically connected to the control surface, and enables the flight control surface to return to an aerodynamically neutral failsafe position if electrical control and/or hydraulic pressure is lost. When the failsafe valve receives a normal command pressure from the hydraulic system, the valve is inactive and the actuation system operates normally. However, if there is a loss of electrical command capacity to control hydraulic valves and/or a loss of hydraulic pressure, the failsafe valve is activated and connects one of the motor hydraulic control lines to the case return line for the motor if the control surface is away from its failsafe position. Consequently, the control surface will be hydraulically powered or aerodynamically ratcheted to its failsafe position in the failure event.
-
公开(公告)号：US20230174228A1
公开(公告)日：2023-06-08
申请号：US17959600
申请日：2022-10-04
申请人： Microtecnica S.r.l.
发明人： Domenico TAFUNI , Simone ALLEVI
摘要： A Stability and Control Augmentation System (“SCAS”) module includes a SCAS actuator. The SCAS actuator has a substantially cylindrical hydraulic chamber having a first and second regions. A piston is arranged for linear motion in first and second directions along an axis of the hydraulic chamber. The SCAS module also includes a valve system for controlling a flow of a hydraulic fluid into the hydraulic chamber. The valve system has: at least one supply line arranged to provide a first fluid flow path to the first region of the hydraulic chamber and/or a second fluid flow path to the second region of the hydraulic chamber, and a moveable valve member arranged to have a position between a first and second positions.
-
公开(公告)号：US20190217944A1
公开(公告)日：2019-07-18
申请号：US15874545
申请日：2018-01-18
申请人： The Boeing Company
发明人： Neal V. Huynh
CPC分类号： B64C13/42 , B64C9/18 , B64C9/20 , B64C13/16 , B64C13/503 , B64C13/504 , F15B20/004
摘要： Distributed trailing edge wing flap systems are described. An example wing flap system for an aircraft includes a flap and an actuator. The flap is movable between a deployed position and a retracted position relative to a fixed trailing edge of a wing of the aircraft. The actuator is to move the flap relative to the fixed trailing edge. The actuator is hydraulically drivable via first pressurized hydraulic fluid to be supplied by a hydraulic system of the aircraft. The actuator is also hydraulically drivable via second pressurized hydraulic fluid to be supplied by a local power unit. The local power unit is selectively connectable to an electrical system of the aircraft. The electrical system is to power the local power unit to supply the second pressurized hydraulic fluid.
-
公开(公告)号：US09845853B2
公开(公告)日：2017-12-19
申请号：US14601695
申请日：2015-01-21
发明人： Eduardo Chamorro Gonzalez-Tablas , Francisco Jose Aguado Lopez , Esteban Morante Lopez , Andres Jimenez Olazabal
CPC分类号： F16H25/205 , B64C13/28 , B64C13/42 , B64C13/50 , B64C25/20 , B64C25/24 , F16H25/20 , F16H2025/2071 , G01L3/26 , Y02T50/44 , Y10T74/186
摘要： A linear electromechanical actuator with a main screw-nut assembly driven by a main motion device and having a hollow screw with an abutting surface; an anti-jamming piston arranged coaxially within the screw and shiftable between an engaged position in which locking dogs interfere with the abutting surface and a disengaged position in which the piston is free to slide within the screw; and actuating elements configured to shift the piston from the engaged to the disengaged position upon electrical or mechanical failure of the actuator. The actuating elements include a key axially movable between the engaged and disengaged positions and having a locking section, configured to bias the locking dogs into interference with the abutting surface in the engaged position, and an unlocking section, configured to allow free sliding of the piston within the screw in the disengaged position. An anti-jamming device for operating a critical flight control surface.
-
公开(公告)号：US09758244B2
公开(公告)日：2017-09-12
申请号：US15015689
申请日：2016-02-04
发明人： John E. Mercer , Nicolas Albion , Mark Bartel , Marc Feifel , Mark Marvin
IPC分类号： B64C27/57 , B64C27/64 , B64C27/68 , G05D1/08 , B64C27/56 , G05D1/10 , B64C13/18 , B64C13/42 , B64C27/59 , G05D1/00
CPC分类号： B64C27/57 , B64C13/18 , B64C13/42 , B64C27/56 , B64C27/59 , B64C27/64 , B64C27/68 , G05D1/0077 , G05D1/0816 , G05D1/0858 , G05D1/102 , Y02T50/44
摘要： A helicopter autopilot system includes an inner loop for attitude hold for the flight of the helicopter including a given level of redundancy applied to the inner loop. An outer loop is configured for providing a navigation function with respect to the flight of the helicopter including a different level of redundancy than the inner loop. An actuator provides a braking force on a linkage that serves to stabilize the flight of the helicopter during a power failure. The actuator is electromechanical and receives electrical drive signals to provide automatic flight control of the helicopter without requiring a hydraulic assistance system in the helicopter. The autopilot can operate the helicopter in a failed mode of the hydraulic assistance system. A number of flight modes are described with associated sensor inputs including rate based and true attitude modes.
-
公开(公告)号：US20170253318A1
公开(公告)日：2017-09-07
申请号：US15059494
申请日：2016-03-03
申请人： Woodward, Inc.
CPC分类号： F16K31/426 , B64C13/42 , B64F5/60 , F15B18/00 , F15B19/005 , F15B2013/0409 , F15B2211/6336 , F15B2211/8757 , F16K11/07
摘要： A redundant control system for a vehicle includes: one or more actuator housings; a plurality of actuator pistons coupled to the actuator housings, each of the actuator pistons mechanically coupled to one another and a common output device; a plurality of primary stages coupled to the actuator housings, each of the primary stages operatively coupled to move a respective actuator piston relative to at least one of the actuator housings, and each of the primary stages functioning independent of any other primary stage when the control system is operating in a flight-operation mode; and an auxiliary stage operatively coupled to move a first of the plurality of actuator pistons relative to at least one of the actuator housings when the control system is operating in a ground-operation mode, with each of the plurality of primary stages being responsive to movement of the first actuator piston by the auxiliary stage.
-
公开(公告)号：US09732769B2
公开(公告)日：2017-08-15
申请号：US14989105
申请日：2016-01-06
申请人： AIRBUS HELICOPTERS
CPC分类号： F15B11/10 , B64C13/42 , B64C27/12 , F15B9/10 , F15B18/00 , F15B2211/321 , F15B2211/8633 , F15B2211/8752
摘要： A servo-control having at least one movable cylinder that includes a hydraulic directional control valve. The hydraulic valve includes a control shaft that is rotatable about a longitudinal axis, the control shaft being connected to a distributor slide. The servo-control including a stationary abutment member secured to a cylinder and an input lever situated outside the cylinder. The input lever is connected to the control shaft and includes a stop portion arranged in the abutment member. The servo-control includes movement means for moving the input lever longitudinally, a first abutment surface of the abutment member limiting a travel amplitude of the stop portion when the input lever is in a first position.
-
公开(公告)号：US09599212B2
公开(公告)日：2017-03-21
申请号：US13510234
申请日：2009-11-16
申请人： Scott Poster
发明人： Scott Poster
IPC分类号： F16H57/04 , F01M5/00 , F16N39/04 , B64C13/42 , F01M1/18 , F01M11/10 , F16N7/40 , B05B1/20 , B05B9/00 , B05B9/04 , B05B15/04
CPC分类号： F16H57/0442 , B05B1/20 , B05B9/002 , B05B9/0409 , B05B9/0423 , B05B14/00 , B64C13/42 , F01M1/18 , F01M5/001 , F01M11/10 , F16H57/0416 , F16H57/045 , F16N7/40 , F16N39/04 , F16N2260/00 , F16N2260/50 , Y10T137/0318 , Y10T137/8593
摘要： A fluid system includes an emergency subsystem and a main subsystem in fluid communication with a working element. The main subsystem is in fluid communication with the emergency subsystem. The system operates in a standard mode and an emergency mode. During standard mode, both the main and emergency subsystems jointly provide fluid to the working element. During emergency mode, the emergency subsystem is configured for independently providing fluid to the working element.
-
公开(公告)号：US09586675B2
公开(公告)日：2017-03-07
申请号：US14299625
申请日：2014-06-09
申请人： The Boeing Company
摘要： A secondary actuation mechanism for arresting movement of a control surface may include a secondary actuator, a drive link coupled to the secondary actuator, and a secondary connecting rod coupled between the drive link and the control surface, wherein the control surface is movable to a default position in response to actuation of the secondary actuator, and the secondary actuator retains the control surface at the default position.
摘要翻译： 用于阻止控制表面的运动的辅助致动机构可以包括辅助致动器，联接到次级致动器的驱动连杆以及耦合在驱动连杆和控制表面之间的辅助连接杆，其中控制表面可移动到默认 响应于辅助致动器的致动而位置，并且次级致动器将控制表面保持在默认位置。
-
-
-
-
-
-
-
-
-
搜索结果
372 条记录 (耗时 0.023 秒)
