Nabtesco Corporation

Bae Systems Controls Inc.

Atsushi Fukui

Shingo Nakagawa

Atsushi Mori

Masahiko Maruoka

Koji Ito

Kazuyuki Suzuki

Yasuyuki Shirai

Toshiaki Ogawa

Gary P Ellsworth

Dino A Gianisis

Steven Bessette

Norimasa Takagi

A fluid pressure pump and a fluid pressure system in which leakage of fluid and ablation of a cylinder block and a port plate can be prevented by pressing the cylinder block to the port plate with an appropriate pressing force. A hydraulic pump includes a cylinder block that has a cylinder chamber that may be in communication with an oil passage of a port plate and in which a piston is housed; and a cylinder block pressing means imparting, to the cylinder block, a pressing force that presses the cylinder block to the port plate. The cylinder block pressing mechanism has a changing means that changes the force that presses the cylinder block to the port plate.

Fluid pressure pump and fluid pressure system

A rotary actuator includes an output shaft, a housing, a piston, and a friction reducer. The housing includes an arcuate bore that extends around the output shaft. The piston is coupled to the output shaft and moved in the arcuate bore. Pressure fluid acts to move the piston. The friction reducer is configured to reduce friction between a peripheral surface of the piston and an inner circumferential surface of the housing forming the arcuate bore.

Rotary actuator

A rotational shaftreceives input of torque that is output from an electric motor. A housingrotatably supports the rotational shaft. A cylinder blockinside the housingrotates with the rotational shaft. The pistonsare supported relative to the respective cylinder chambersin the cylinder blockso as to be slidably displaceable. A swash plateis provided so as to come into contact with ends of the pistonsand be rotatable around the rotational shaftwith the pistons, and be rotatable about a rotation centerline that is obliquely inclined relative to the rotational shaft. A caseinside the housingis pivotably supported relative to the housing. A bearing portionholds the swash platerelative to the caseso as to be rotatable around the rotation centerline.

Hydraulic pump

An electric motor drives a variable capacity 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. A power source unit rectifies electric power supplied from a variable frequency supply. A driver supplies the electric power from the power source unit, and drives the electric motor so as to rotate the pump at a predetermined constant rotational speed. The constant rotational speed is set, based on the change in the efficiency of each of the pump, the electric motor, and the driver with respect to the rotational speed of the pump, such that the overall efficiency, obtained as a product of these efficiencies, has a maximum value.

Hydraulic system for aircraft actuators

An operation control apparatus includes a command generation portion that generates a command signal for commanding operation of a control surface, and first and second monitoring portions that monitor an abnormality of operation of first and second control portions, respectively, of the actuator control apparatus. The actuator control apparatus includes first and second control portions that generate a control signal for an actuator for driving the control surface and that are different in design, and a switching unit that switches the connection to the actuator from one of the first and second control portions to the other, when an abnormality is detected by the first and second monitoring portions. Accordingly, it is possible to monitor a generic failure, and realize redundancy enabling control of the overall operation of the actuator, from start to finish, when a generic failure has occurred, thus realizing further simplification and streamlining of the configuration.

Actuator control system

A plurality of control channels each include a power supply, an interface that receives a manipulation signal, an arithmetic processing portion that calculates and generates an operation command signal for actuators based on the manipulation signal, and a signal determination unit that determines a control signal for finally controlling the operation of the actuators and outputs the control signal. The arithmetic processing portions respectively provided in the plurality of control channels have designs different from one another. Each of the signal determination units determines the control signal by receiving a first operation command signal generated by the arithmetic processing portion of the control channel in which that signal determination unit is provided, and a second operation command signal generated in the arithmetic processing portion of another of the control channels, and comparing the first operation command signal and the second operation command signal, and outputs the control signal.

Aircraft control apparatus and aircraft control system

The control apparatus acquires an ideal velocity characteristic of a control surface, and the temperature of pressure oil of the actuator to be tested and the operating speed of the control surface when the actuator is attached to the control surface. The control apparatus corrects the ideal velocity characteristic of the control surface by using the pressure oil temperature and the control surface operating speed. The control apparatus sets an upper limit and a lower limit by using a predicted value for a fluctuation range for a fluctuation factor that causes a fluctuation of the control surface operating speed, with reference to the corrected ideal velocity characteristic, measures the pressure oil temperature and the operating speed by actuating the control surface, with the actuator to be tested placed in a damping mode, and determines whether the measured value falls within the range between the upper limit and the lower limit.

Damping test method, control apparatus, hydraulic system, and computer readable recording medium

A hydraulic pump is installed inside a wing at which a control surface is provided, and supplies pressure oil to an actuator when a loss or degradation occurs in the function of aircraft central hydraulic power sources. An electric motor is installed inside the wing and drives the backup hydraulic pump. A driver is installed inside the wing and drives the electric motor. A cooling device is installed inside the wing and simultaneously cools the backup hydraulic pump, the electric motor, and the driver.

Aircraft actuator hydraulic apparatus

A first actuator drives a control surface by being operated by supply of pressure oil from a first aircraft central hydraulic power source including a first aircraft central hydraulic pump. A second actuator drives the control surface by being operated by supply of pressure oil from a second aircraft central hydraulic power source including a second aircraft central hydraulic pump. A backup hydraulic pump is installed inside a wing of the aircraft and is provided so as to be able to supply pressure oil to the first actuator when a loss or degradation in a function of at least one of the first aircraft central hydraulic power source and the second aircraft central hydraulic power source occurs. A maximum discharge pressure of the backup hydraulic pump is set to be greater than maximum discharge pressures of the first aircraft central hydraulic pump and the second aircraft central hydraulic pump.

Aircraft actuator hydraulic system

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.

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.

A backup system is provided that has a local electric motor and pump for some or all of hydraulic actuators. A local backup hydraulic actuator has two power sources, hydraulic as primary and electrical as backup. During normal operation, the hydraulic actuator receives pressurized fluid from a hydraulic system and the fluid flow to the chambers is controlled by a servo valve. If the hydraulic system fails, the electronic controller detects the failure by observing the signal indicative of the pressure from the pressure sensor, and the controller powers the local hydraulic pump to provide high pressure hydraulic fluid to the hydraulic actuator via the servo valve.

Local backup hydraulic actuator for aircraft control systems

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.

Growing community of inventors

Gifu, Japan

Atsushi Fukui