Class / Patent application number | Description | Number of patent applications / Date published |
244990400 | Redundant arrangements | 10 |
20080265091 | SENSING LOAD RELIEF BY A SECONDARY PATH OF A FLIGHT CONTROL ACTUATOR - Device for sensing load relief by a secondary path of a flight control actuator having a primary path and a secondary path capable of relieving the load of the primary path in the event of a breakdown thereof, the primary path comprising a screw, the screw terminating in a fastener of the primary path, the secondary path comprising an emergency load relief rod passing through the screw, this rod terminating in a male shape which, when the primary path is carrying the load, is accommodated inside of a female shape of a fastener of the secondary path,
| 10-30-2008 |
20090289145 | ELECTROMECHANICAL ACTUATING ASSEMBLY - An electromechanical actuating assembly ( | 11-26-2009 |
20100032520 | CONTROL SURFACE FAILSAFE DROP LINK - An aircraft control surface failsafe hinge configuration is disclosed. The arrangement comprises a drop link configuration which is adapted to attach a control surface to an aircraft structure where the drop link additionally incorporates a failsafe hinge means which provides a backup hinge connection between the control surface and the aircraft structure to which it is attached. The improved failsafe hinge construction may be applied to any aircraft control surface such as an aileron, elevator, vertical tail plane and the like. | 02-11-2010 |
20100116929 | HYBRID ELECTROMECHANICAL/HYDROMECHANICAL ACTUATOR AND ACTUATION CONTROL SYSTEM - A hybrid actuator assembly includes an actuator housing, an electromechanical actuator, and a hydraulic actuator. The electromechanical actuator is disposed at least partially within the actuator housing and is adapted to be controllably energized. The electromechanical actuator is configured, upon being controllably energized, to supply a first drive force. The hydraulic actuator is disposed at least partially within the actuator housing and is adapted to receive pressurized hydraulic fluid. The hydraulic actuator is configured, upon receipt of pressurized hydraulic fluid, to supply a second drive force. | 05-13-2010 |
20100213311 | ELECTROMECHANICAL ACTUATING ASSEMBLY - An electromechanical actuating assembly ( | 08-26-2010 |
20110062282 | FAULT-TOLERANT ACTUATING SYSTEM FOR ADJUSTING FLAPS OF AN AIRCRAFT, COMPRISING ADJUSTMENT KINEMATICS WITH A FIXED PIVOT, AND A METHOD FOR MONITORING AN ACTUATING SYSTEM - A fault-tolerant actuating system with at least one flap, adjustable on a respective wing of an aircraft, and with a control and monitoring device, includes: drive devices that are functionally connected to the control and monitoring device, with one of these drive devices in each case being associated with a flap, where each flap in each case is associated with a drive device, in each case including: two drive motors, two brake mechanisms, where each drive motor is associated with a brake mechanism for stopping rotation of the output of the respective drive motor, a differential that couples the outputs of the aforesaid to the aforesaid in a summing manner, an output shaft for coupling the output of the differential to drive connections, and a differential lock that is functionally connected to the control and monitoring device, which differential lock is coupled to the control and monitoring device in this manner, where each of the brake mechanisms as well as the differential lock can be operated by way of a command signal from the control and monitoring device; adjustment devices, that are coupled to the respective drive device associated with the flap, where each adjustment device in each case includes: a transmission gear unit, an adjustment mechanism and a position sensor that is functionally connected to the control and monitoring device for acquiring the adjustment state of the flap; where the control and monitoring device includes: an actuating function for generating command signals for the drive motors for adjusting the flap, a monitoring function by way of which a command signal is transmitted to both brake mechanisms and to the differential lock for operating the aforesaid when the control and monitoring device based on a comparison of sensor values of the position sensors on two different adjustment devices of a flap determines different adjustment states that exceed a predetermined extent, and a method for monitoring an actuating system. | 03-17-2011 |
20110290938 | ACTUATOR CONTROL APPARATUS - Herein disclosed is an actuator control apparatus, comprising primary control means for producing a control signal used to control an operation of an actuator in accordance with an instruction signal indicative of an operation of the actuator, secondary control means for producing a control signal in accordance with the instruction signal; and switching means for selectively switching one of the primary control means and the secondary control means to the other, and in which the secondary control means is less in the number of functions than the primary control means, and each of components constituting the secondary control means is easier in fault verification than a component constituting the primary control means the most difficult in fault verification among all of components constituting the primary control means. | 12-01-2011 |
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 |
20130001357 | HORIZONTAL STABILIZER TRIM ACTUATOR FAILURE DETECTION SYSTEM AND METHOD USING POSITION SENSORS - An actuator assembly having a primary load path for tightly coupling an actuated surface to a reference structure and a secondary load path having a backlash portion for coupling the actuated surface to the reference structure with backlash, wherein the secondary load path is unloaded during an operative state of the primary load path and loaded during a failure state of the primary load path. The actuator assembly includes at least one sensor configured to sense the failure state of the primary load path when a relative displacement between a portion of the primary load path and a portion of the secondary load path exceeds a predetermined value or is within a predetermined range of values. | 01-03-2013 |
20130105623 | DEVICE FOR DETECTING BREAKAGE OF A PRIMARY PATH IN A FLIGHT CONTROL ACTUATOR | 05-02-2013 |