Patent application number | Description | Published |
20090045678 | Method and Device for Redundantly Supplying Several Electric Servomotors or Drive Motors by Means of a Common Power Electronics Unit - A method and a device for redundantly supplying several electric servomotors or drive motors by a common power electronics unit particularly in an aircraft, wherein the power electronics unit contains a number of electronic motor control units, and wherein the electric motors are operated with nominal power if the electronic motor control units are fully functional. The motors are operated with the available residual power of the motor control units if partial failure of the motor control units occurs. The motors may be operated sequentially or simultaneously. | 02-19-2009 |
20100125380 | Method And Device For Fault Detection In The Load Path Of A Spindle Actuator - A method and a device for fault detection in the load path of a spindle actuator which is provided for actuating an aerodynamically active surface, in particular a high-lift flap of an aircraft, wherein the spindle actuator has a redundant load path which is formed by a spindle and a secondary connection which are connected rotationally fixedly to one another on the driven side and are coupled to the surface to be actuated and which are assigned separate load paths on the drive side, whereof the primary load path contains a primary spindle which is driven by a motor and can be fixed in its rotational movement by a primary brake, and the secondary load path contains the secondary inner connection, which is in particular arranged concentrically in the primary spindle, which can be fixed in its rotational movement by a secondary brake, in which output signals representing the turning position of the spindle, which are generated by means of at least one turning position sensor which is coupled to the primary spindle on the drive side, are detected and evaluated, wherein: fixing the secondary connection in its rotational movement is achieved by means of the secondary brake; the redundant load path is put under load, when the primary brake is released, the load being applied via a predefined torque by the motor as far as the secondary brake is fixing the secondary connection; and the detection of a fault is evaluated when a change in the turning position, which lies outside the tolerance range predefined for an intact spindle actuator, is detected at the turning position sensor coupled to the primary spindle. | 05-20-2010 |
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 |
20110255968 | ADJUSTER DEVICE FOR AN AIRCRAFT, COMBINATION OF AN ADJUSTER DEVICE AND AN ADJUSTER DEVICE FAULT RECOGNITION FUNCTION, FAULT-TOLERANT ADJUSTER SYSTEM AND METHOD FOR RECONFIGURING THE ADJUSTER SYSTEM - An adjustment device to be coupled to an adjustment flap of an aircraft, with an actuator, adjustment kinematics, and a gearing, wherein the adjustment device can be coupled to a controller/monitor for purposes of its actuation. The adjustment device includes a first load sensor, on the input side of the actuator for determining the load arising on the input side due to actuation of the adjustment flap, and a second load sensor, on the output side of the actuator for determining the load arising on the output side due to actuation. The first load sensor and second load sensor are functionally linked with a fault-recognition function for receiving sensor values ascertained by the load sensors, to assign a fault state to the adjustment device. A combination of an adjustment device and a fault recognition function, a fault-tolerant adjustment system, and a method for reconfiguring the adjustment system are also provided. | 10-20-2011 |
20120312931 | FLAP ADJUSTING SYSTEM OF AN AIRCRAFT WITH A REGULATING FLAP - Embodiments pertain to a flap adjusting system including a regulating flap mounted on an airfoil using at least two bearing devices and movable relative to the airfoil, and an adjusting device. The adjusting device includes an actuator and adjusting kinematics with a drive rod that couples the actuator to the regulating flap using a first and a second joint, as well as a load sensor. The adjusting kinematics are configured such that, at a maximum adjustment travel of the regulating flap, the second joint between the drive rod and the regulating flap is adjusted by an angle less than 50% of the angle by which the first joint is adjusted. The load sensor is arranged in at least one adjusting device and in the second joint, which couples the drive rod to the regulating flap. The load sensor is configured to measure the forces in this load path. | 12-13-2012 |
20130181089 | ADJUSTMENT SYSTEM OF AN AEROPLANE WITH AN ADJUSTABLE FLAP - An adjustment system of an aeroplane, having: at least one adjustable flap on each of the wing of an aeroplane, adjustable with an adjustment device, a drive device for purposes of driving the adjustment devices, and a load sensor for purposes of recording the load occurring in the load path between the actuator and the adjustable flap of the respective adjustment device. The load sensor is embodied as a sensor for purposes of measuring the longitudinal force occurring in a drive rod along its longitudinal direction. | 07-18-2013 |
20130261852 | MONITORING DEVICE FOR AN ACTUATION SYSTEM OF AN AIRCRAFT, ACTUATION SYSTEM AND METHOD FOR RECONFIGURING THE ACTUATION SYSTEM - A monitoring device is disclosed for an actuation system of an aircraft for monitoring a guiding device of a regulating flap with a load sensor. An actuation system with the monitoring device and a method for reconfiguring such an actuation system are disclosed. The monitoring device includes an interface to the load sensor and an interface to a driving device for adjusting the regulating flap. The monitoring device can determine or receive in-flight information actively signaling a predefined flight attitude and/or a predefined operational state of the aircraft. The monitoring device can compare a load value corresponding to a sensor value acquired by the load sensor and a limiting value corresponding to a minimum operational load for the predefined flight attitude and/or the predefined operational state of the aircraft and a monitoring function. The monitoring function can assign a fault mode to the regulating flap. | 10-03-2013 |
20140027580 | HIGH LIFT SYSTEM FOR AN AIRCRAFT - A high lift system for an aircraft, which extends and retracts the landing flaps of the aircraft in a fully electric manner. In this context, a fully electric drive is used, comprising an electric motor having an internal redundancy, in such a way that the electric motor is configured as a fault-tolerant electric motor. It may thus be possible to do without a coupling gear unit in the electric motor. | 01-30-2014 |