Patent application number | Description | Published |
20110264242 | ACTUATOR CONTROL SYSTEM - 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. | 10-27-2011 |
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 |
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 |
20110290353 | HYDRAULIC SYSTEM FOR AIRCRAFT ACTUATORS - 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. | 12-01-2011 |
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 |
20120029859 | DAMPING TEST METHOD, CONTROL APPARATUS, HYDRAULIC SYSTEM, AND COMPUTER READABLE RECORDING MEDIUM - 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. | 02-02-2012 |
20120085860 | AIRCRAFT ACTUATOR HYDRAULIC APPARATUS - 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. | 04-12-2012 |
20120131912 | AIRCRAFT ACTUATOR HYDRAULIC SYSTEM - 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. | 05-31-2012 |
20130124019 | AIRCRAFT CONTROL APPARATUS AND AIRCRAFT 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. | 05-16-2013 |
20130219878 | AIRCRAFT ACTUATOR HYDRAULIC SYSTEM - A plurality of actuators ( | 08-29-2013 |
20130224044 | HYDRAULIC PUMP - A rotational shaft | 08-29-2013 |
20130336816 | AIRCRAFT ACTUATOR HYDRAULIC SYSTEM - A backup hydraulic pump supplies pressure oil to an actuator when a loss or degradation of the function of an aircraft central hydraulic power source occurs. A control valve controls the operation of the actuator by controlling supply and discharge of the pressure oil to/from the actuator. The control valve has a main body provided with a pressure oil port, a spool portion that moves in a sliding manner within the main portion and switches a path of the pressure oil, and a drive portion. The drive portion is connected to an end of the spool portion and drives the spool portion by electromagnetic force so as to control the position of the spool portion based on an electric signal. | 12-19-2013 |