Class / Patent application number | Description | Number of patent applications / Date published |
244990500 | Fluid | 25 |
20080203224 | Load optimized redundant flight control surface actuation system and method - An aircraft flight surface control system and method simultaneously provides the benefits of both an active/active system architecture and in active/standby system architecture. The system is preferably implemented using hydraulic actuator assemblies and electromechanical actuator assemblies coupled to the same flight control surface. During normal system operations the electromechanical actuator assemblies are energized to supply a relatively minimal force to associated flight control surfaces. In effect, the electromechanical actuators, although energized, may be pulled along by the associated hydraulic actuator assemblies, until needed. Thus, the electromechanical actuator assemblies are controlled in a manner that closely resembles the active/standby architecture. | 08-28-2008 |
20090050734 | FLOW CONTROL ACTUATORS - A flow control actuator | 02-26-2009 |
20090266934 | HYDRAULIC FLUID SUPPLY DEVICE AND ELECTRIC ACTUATOR - An electric actuator of the present invention includes a hydraulic fluid supply device and an actuator actuated in response to an input of hydraulic fluid from a variable-volume pump. The hydraulic fluid supply device includes an adjustable-speed motor, the variable-volume pump which is driven by the adjustable-speed motor and ejects hydraulic fluid, an electric motor control unit which controls the adjustable-speed motor so as to achieve an intended rotation speed, and a pump control unit which controls the variable-volume pump so that the ejection volume of the variable-volume pump decreases with an increase in the ejection pressure of the variable-volume pump. | 10-29-2009 |
20100282899 | System for Actuating at least One Positioning Flap of an Aircraft and a Method for Monitoring the System. - A method for actuating at least one positioning flap on each wing of an aircraft, which positioning flap is actuated by at least two flap coupling devices each including a flap actuator device, where at least on one flap actuator device for each positioning flap a brake mechanism is arranged by means of whose actuation an adjustment state of the respective flap actuator device can be locked, including the steps of: actuating each brake mechanism of a positioning flap individually, subsequently actuating the flap actuator device by means of the drive motor, in the case of a change in the adjustment state of the positioning flap by a predetermined extent, terminating actuation of the positioning flap concerned, and a system for implementing the method. | 11-11-2010 |
20110006156 | HYDRAULIC ACTUATOR WITH END POSITION DAMPING - A hydraulic actuator includes, but is not limited to a first outflow and a second inflow and outflow as well as a closure device for closing the second inflow and outflow in the direction of outflow. The first outflow an outflowing hydraulic fluid is subjected to flow resistance. When a switching position is reached, the second inflow and outflow is closed in the direction of outflow so that the hydraulic fluid has to be discharged through the first outflow while overcoming the flow resistance. This damps the movement of the hydraulic actuator in the region of an end position. | 01-13-2011 |
20110068221 | Control System for a Hydraulically Actuatable Horizontal Stabilizer and Test Method for Testing the Integrity of a Control System - An actuation system for a hydraulically operable aircraft elevator, includes: two actuators, supplied from at least one hydraulic supply system, of which each is coupled to a load-bearing structural component, and to an elevator, displaceable relative to the load-bearing structural component, for the operation of the elevator, a first control valve device, hydraulically connected to the first actuator to control the latter, and a second control valve device, hydraulically connected to the second actuator to control the latter, which devices are respectively supplied from an hydraulic system, a control and monitoring unit functionally connected with the control valve devices, which determines appropriate command signals for the control valve devices and transmits the signals to the latter to execute appropriate control movements for the operation of the actuators, a locking device, coupled to the first actuator, with a locking mechanism to secure the extended position of the pushrod of the first actuator in its locked state, which is hydraulically connected with the first hydraulic system and with the second hydraulic system via an hydraulic OR-circuit, such that in normal operation of at least one of the hydraulic systems the locking mechanism is in its unlocked state, and in the event of the failure of both hydraulic systems the locking mechanism under a minimum pressure secures the extended position of the pushrod of the first actuator, and/or a lock activation device, which is functionally connected with the control and monitoring unit, and which upon the receipt of an activation signal activates the locking mechanism, and also a test method to check the integrity of an actuation system. | 03-24-2011 |
20110215195 | AIRCRAFT CONTROL SURFACE METHODS - A control surface drive system having a plurality of actuator assemblies are coupled to first and second supply lines and to a return line. The first and second supply lines are connected to a source of hydraulic fluid. At least one of the actuator assemblies has a hydraulic actuator movably connectable to an aircraft control surface. A flow control assembly is connected to the return line and to at least one of the first and second supply lines. A bypass line is in fluid communication with the first and second supply lines and positioned to recycle the hydraulic fluid from one of the first and second supply lines back into the other one of the first and second supply lines when the hydraulic actuator moves toward the first position. A computer controller operatively interconnects the plurality of actuator assemblies and the flow control assembly. It is emphasized that this abstract is provided to comply with the rules requiring an abstract. It is submitted with the understanding that it will not be used to interpret or limit the scope or meaning of the claims 37 C.F.R. ยง1.72(b)). | 09-08-2011 |
20110266390 | HYDRAULIC APPARATUS FOR AIRCRAFT ACTUATORS - A pump unit installed inside a wing, and a panel body constituting part of a wing structure portion forming a surface structure of the wing are provided. The pump unit includes a backup hydraulic pump that can supply pressure oil to an actuator when a loss or reduction occurs in the function of an aircraft central hydraulic power source and an electric motor that drives this pump. Except for at least the panel body, the wing structure portion is formed from fiber reinforced plastics. The panel body is formed of a metallic material. | 11-03-2011 |
20110266391 | Fluidic Artificial Muscle Actuation System For Trailing-Edge Flap - An actuation system for trailing-edge flap control suitable for use in reducing vibration in rotorcraft blades as well as primary flight control and noise mitigation employing an antagonistic pair of fluidic artificial muscles (FAMs) located and operated inside the rotor blade. The FAMs are connected to a force transfer mechanism such as an inboard bellcrank and engaged to an outboard bellcrank by one or more linkages running spanwise out through the spar. The outboard mechanism translates the spanwise linkage motion into chordwise motion of a flap control rod which is connected to the trailing-edge flap. A torsion rod flexure (TRF) device is included connecting the trailing-edge flap to the blade. The actuation system can produce large flap deflections at relatively high operating frequencies for vibration reduction and noise cancellation and is capable of larger flap deflections at lower operating frequencies for embedded primary control of the rotorcraft. | 11-03-2011 |
20110284687 | Structural assembly for an aircraft - A structural assembly for an aircraft comprising a cover with outer and inner faces, an inner support element and urging means on the inner support element, wherein opposing edges of the cover are fixedly mounted relative to the inner support element, and the urging means acts on the inner face of the cover to urge the cover to distend outwardly and locate in a predetermined position. Another aspect of the invention relates to a method of forming a structural assembly for an aircraft comprising an cover with outer and inner faces, an inner support element and urging means on the inner support element, the method comprising the steps of fixedly mounting opposing edges of the cover relative to the inner support element and operating the urging means to act on the inner face of the cover so that the cover is urged to distend outwardly into a predetermined position. | 11-24-2011 |
20120006939 | BEARING ASSEMBLY - A bearing assembly for mounting a pair of spaced parallel actuators ( | 01-12-2012 |
20120168560 | FLOW REGULATION IN AIRCRAFT SYSTEMS - The present invention relates generally to flow regulation in aircraft systems. More particularly, the present invention relates to a flow regulator | 07-05-2012 |
20120181383 | HYDRAULIC ACTUATOR SYSTEM - A hydraulic actuator system | 07-19-2012 |
20120305701 | AIRCRAFT CONTROL SURFACE DRIVE MECHANISM - An actuator includes a plurality of cylinder units each including a cylinder and a rod, and is pivotably attached, at a first end thereof, to a control surface. A reaction link is pivotably attached, at a first end thereof, to a fulcrum shaft rotatably supporting the control surface. The reaction link is pivotably attached, at a second end thereof, to a second end of the actuator between the plurality of cylinder units. | 12-06-2012 |
20140312170 | ACTUATOR DEVICE FOR AIRCRAFT, AND AIRCRAFT - The present invention provides an actuator device which can prevent a rapid change in deflection angle when an active actuator and a standby actuator are switched. A first actuator | 10-23-2014 |
20150314851 | METHOD FOR GENERATING HYDRAULIC POWER IN AN AIRCRAFT, USE OF A HYBRID POWER CONTROL UNIT AND DRIVE SYSTEM - A method for generating hydraulic power in an aircraft, the aircraft having a drive system comprising at least one transmission shaft connected to a power control unit, the power control unit having an electric motor and a hydraulic displacement machine connected to a differential gear unit for driving a common output shaft. The method includes switching the hydraulic displacement machine into a pump mode, arresting the output shaft, rotating the electric motor such that the hydraulic displacement machine is driven due to the arrested output shaft and supplying the fluid flow into a hydraulic system. A drive system of an aircraft may thereby be used for either moving control surfaces or for generating hydraulic power in an aircraft. This hydraulic power may be used to cover hydraulic load peaks during aircraft operation or to power hydraulic devices without the need of additional hydraulic power generation components. | 11-05-2015 |
20170233064 | HYDRAULIC SYSTEM AND METHOD FOR AN AIRCRAFT FLIGHT CONTROL SYSTEM | 08-17-2017 |
20220135209 | AN ACTUATOR APPARATUS COMPRISING A POSITIONING ACTUATOR - Provided is an actuator apparatus including a positioning actuator device configured to position a first carrier member of the actuator apparatus. The positioning actuator device includes a first hydraulic fluid actuator having a first clamping means and a second hydraulic fluid actuator having a second clamping means, wherein the first and second hydraulic fluid actuator are configured to alternately clamp around a guide arrangement for moving the positioning actuator device along the guide arrangement. The first carrier member is provided with a first coupling member configured to be releasable coupled to the positioning actuator device. A method of positioning a first carrier member by means of the positioning actuator device is provided. | 05-05-2022 |
244990600 | Fluid pressure source arrangement | 6 |
20090242694 | HYDRAULIC SYSTEM FOR AIRCRAFT - A hydraulic system for aircraft operating devices provides a secondary pressure source for direction and deceleration control in case of loss of pressure from a primary pressure source. The system includes multiple pressure accumulators that include a primary accumulator, which supplies pressurized fluid to a first actuator, and first and second secondary accumulators, which supply pressurized fluid to second and third actuators, respectively. If the primary accumulator is disabled, the first secondary accumulator will supply pressurized fluid to the first actuator. If the first secondary accumulator is disabled, the second secondary accumulator will supply pressurized fluid to the second actuator. By providing multiple, substantially independent accumulators, direction and deceleration control is maintained even in the event of loss of the primary accumulator. | 10-01-2009 |
20110278392 | HYDRAULIC APPARATUS FOR AIRCRAFT ACTUATORS - A pump unit installed inside a wing includes a backup hydraulic pump that can supply pressure oil to an actuator when a loss or reduction occurs in the function of an aircraft central hydraulic power source and an electric motor that drives the pump. A wing structure portion forming the surface structure of the wing is provided with an inlet port and an exhaust port that are formed therethrough. The inlet port is provided so as to be opened and closed by an inlet port opening/closing portion, and the exhaust port is provided so as to be opened and closed by an exhaust port opening/closing portion. | 11-17-2011 |
20120001021 | AIRCRAFT ACTUATOR HYDRAULIC SYSTEM - When a loss or degradation in the function of one of a first aircraft central hydraulic power source and a second aircraft central hydraulic power source occurs, a controller performs a control so as to operate the other backup hydraulic pump, out of a first backup hydraulic pump and a second backup hydraulic pump, which is connected downstream of the other hydraulic power source, which is the other of the first and second aircraft central hydraulic power sources. Oil flowing through the other backup hydraulic pump is cooled by an oil cooler of the other hydraulic power source by operation of the other backup hydraulic pump in a state where the other hydraulic power source is being operated. | 01-05-2012 |
20120025015 | AIRCRAFT ACTUATOR CONTROL APPARATUS - A plurality of hydraulically operated actuators that drive a control surface and a plurality of control systems that respectively control the operation of the actuators are included. Each of the control systems includes a control valve, a state switching valve and a test orifice circuit. The test orifice circuit includes a test orifice used for testing the performance of an orifice. The state switching valve is provided such that its position can be switched between an actuator connection position, a damping position and a test orifice position. | 02-02-2012 |
20180022440 | HORIZONTAL STABILIZER TRIM ACTUATOR SYSTEMS AND METHODS | 01-25-2018 |
20180022441 | Electronically Controlled Rotary Actuator for an Aircraft Control Surface | 01-25-2018 |
244990700 | Nonlinear fluid actuator | 1 |
20100270426 | AIRCRAFT ACTUATOR - An aircraft actuator is provided that can achieve a significant weight reduction, while securing a sufficient tensile strength and a sufficient buckling strength, even if it is provided with a reaction link in which large bent portions are formed. A reaction link is made of fiber reinforced plastic, and includes a pair of linear portions, a coupling portion, and a pair of bent portions. The cross section at the pair of linear portions, the coupling portion, and the pair of bent portions is formed as a hollow cross section. The outer cross sectional area of the hollow cross section at each of the pair of bent portions is configured to be larger than the outer cross sectional area of the hollow cross section at each of the pair of linear portions. | 10-28-2010 |