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公开(公告)号：US20210207735A1
公开(公告)日：2021-07-08
申请号：US17208632
申请日：2021-03-22
申请人： Woodward, Inc.
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.
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公开(公告)号：US11008097B2
公开(公告)日：2021-05-18
申请号：US16552405
申请日：2019-08-27
发明人： Jürgen Götte , Uwe Arnold
摘要： An actuator for aviation may include an electromechanical drive unit connected with an output drive via a gearbox. The drive unit may have at least two partial drives that can be operated independently from one another. The gearbox may be located at least partially between the at least two partial drives such that the at least two partial drives are spaced apart from one another.
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公开(公告)号：US10969035B2
公开(公告)日：2021-04-06
申请号：US15059494
申请日：2016-03-03
申请人： Woodward, Inc.
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.
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公开(公告)号：US10926867B2
公开(公告)日：2021-02-23
申请号：US16126671
申请日：2018-09-10
申请人： The Boeing Company
发明人： Neal V. Huynh
摘要： Distributed trailing edge wing flap systems are described. An example wing flap system for an aircraft includes a flap and first and second actuators. 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 first and second actuators are configured to move the flap relative to the fixed trailing edge. The first actuator is actuatable via pressurized hydraulic fluid to be supplied from a hydraulic system of the aircraft to the first actuator via a hydraulic module operatively coupled to the first actuator. The first actuator is operatively coupled to a first shaft. The second actuator is actuatable via an electric motor of the second actuator. The electric motor is operatively coupled to an electrical system of the aircraft. The second actuator is operatively coupled to a second shaft. The first and second shafts are selectively operatively couplable via a clutch operatively positioned between the first and second shafts. The clutch is actuatable between a disengaged position in which the second shaft is operatively uncoupled from the first shaft and an engaged position in which the second shaft is operatively coupled to the first shaft.
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公开(公告)号：US10518870B2
公开(公告)日：2019-12-31
申请号：US15727826
申请日：2017-10-09
申请人： AIRBUS HELICOPTERS
IPC分类号： B64C13/04 , B64D31/04 , B64C13/50 , B64C13/28 , B64C27/26 , B64C27/56 , B64C11/30 , B64C13/42 , B64C27/82
摘要： An electric control device having manipulation means. The electric control device has a first measurement system and a second measurement system respectively taking a first measurement and a second measurement of the current position of the manipulation means. A processor unit compares the first and second measurements in order to generate a control signal as a function of said current position, said processor unit considering that the manipulation means are in a neutral position when the first and second measurements do not correspond to the same position for the manipulation means.
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公开(公告)号：US10196131B2
公开(公告)日：2019-02-05
申请号：US15045237
申请日：2016-02-16
申请人： The Boeing Company
摘要： A hydraulic system of an aircraft may include a system pump configured to provide hydraulic fluid to the hydraulic system at a first working pressure. The hydraulic system may further include a booster pump configured to supply hydraulic fluid to at least one boostable actuator at a second working pressure higher than the first working pressure. The boostable actuator may be operatively coupled to and configured to actuate at least one flight control surface of an aircraft.
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公开(公告)号：US10190608B2
公开(公告)日：2019-01-29
申请号：US15213562
申请日：2016-07-19
发明人： Eric Wildman
摘要： An actuator comprising: an inner cylinder received in an outer cylinder and a piston received in the inner cylinder that extends from the inner cylinder and the outer cylinder, the piston being slideable relative to the inner cylinder and the outer cylinder in response to the application of fluid pressure to cause the piston to extend further from the inner cylinder and the outer cylinder; and an auxiliary drive mechanism operable to cause the inner cylinder to extend from the outer cylinder, wherein the piston moves together with the inner cylinder relative to the outer cylinder.
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公开(公告)号：US20180312240A1
公开(公告)日：2018-11-01
申请号：US16029327
申请日：2018-07-06
申请人： The Boeing Company
发明人： Mark Steven Good , Matthew August Lassen , Michael E. Renzelmann , Mark J. Gardner , Mark William Lesyna , Brian Curtis Hill , Nicholas Seth Tyler
摘要： A system and method for a number of backup systems in an aircraft. The apparatus comprises a movement system; a latch system; a lock system; and at least one of a backup valve, a backup actuator, or a backup power source connected to at least one of the movement system, the latch system, or the lock system. The movement system has a first number of actuators and is connected to a hydraulic power source. The latch system has a second number of actuators and is connected to the hydraulic power source. The lock system has a third number of actuators and is connected to the hydraulic power source.
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公开(公告)号：US10040541B2
公开(公告)日：2018-08-07
申请号：US14626676
申请日：2015-02-19
申请人： The Boeing Company
IPC分类号： B64C13/42 , B64C13/40 , B64C13/48 , B64C25/22 , B64C25/26 , B64C25/28 , F04B23/04 , F04B49/06 , F15B18/00 , F04B49/20
摘要： A method includes receiving pump cycle location data associated with a fluid power system. The fluid power system includes a plurality of pumps (including at least a first pump, a second pump, and a third pump). Based on the pump cycle location data having a first value, the method includes activating the first pump as a primary pump. Based on the pump cycle having a second value, the method includes activating the second pump as the primary pump. The method also includes activating the third pump as a secondary pump when the fluid power system is in a multiple-pump operating mode.
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公开(公告)号：US10040539B2
公开(公告)日：2018-08-07
申请号：US15112668
申请日：2015-01-20
摘要： The invention relates to an actuator (4) for controlling a horizontal stabilizer (3) of an aircraft, including: a primary channel including a screw (6) and a primary nut (7), the primary nut (7) being suitable for engaging with the screw (6), such that a rotation of the screw (6) relative to the primary nut (7) about a rotation axis (X) causes the primary nut (7) to translate relative to the screw (6) along the axis (X), such as to move the horizontal stabilizer (3); a secondary channel including a secondary part (25, 28), and a housing (23, 26), the secondary part (25, 28) being mounted in the housing (23, 26) with play between the secondary part and the housing, in which the secondary channel also includes a play take-up device (27), configured to, in the event of a breakdown of the primary channel causing the secondary part (25, 28) to move relative to the housing, eliminate the play between the secondary part (25, 28) and the housing (23, 26) such as to keep the secondary part (25, 28) in contact with the housing (23, 26).
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