| Liebherr-Aerospace Lindenberg GmbH Patent applications |
| Patent application number | Title | Published |
|---|
| 20130032054 | Actuator Providing Multiple Actuation - Disclosed is an actuator, in particular for a rail vehicle, comprising a fluidic first actuator unit and a control device having a first control unit, wherein the first actuator unit is connected to the first control unit and can be supplied with power from a fluidic power source under the control of the first control unit. Furthermore, a fluidic second actuator unit is provided, and the control device comprises a second control unit, wherein the second actuator unit is connected to the second control unit and can be supplied with power from the fluidic power source under the control of the second control unit. The invention further relates to a vehicle, in particular a rail vehicle, having an actuator according to the invention. | 02-07-2013 |
| 20120161512 | METHOD FOR SUPPLYING ENERGY TO AN AIRCRAFT - The present invention relates to an energy supply system of an aircraft comprising a fuel cell and having one or more consumers which are or can be connected to the fuel cell such that they are supplied with energy directly or indirectly from the fuel cell in emergency operation as well has having at least one active energy store which is or can be connected to at least one of the consumers such that the consumer(s) is/are supplied with energy from the active energy store at least at times. | 06-28-2012 |
| 20120083345 | HIGH-LIFT SYSTEM OF AN AIRCRAFT - The present invention relates to a high-lift system of an aircraft having at least one drive unit, having at least one load station as well as having one or more transmissions for transmitting the drive energy of the drive unit to the at least one load station, wherein one or more of the transmission are made as transmission shafts which consist of a material containing titanium or comprise a material containing titanium. | 04-05-2012 |
| 20120056039 | CONTROL SYSTEM FOR AN AIRCRAFT - This invention relates to a control system for an aircraft consisting of at least two active inceptor units and at least one coupling means, wherein the coupling means generates or influences at least one setpoint for the control of at least one of the active inceptor units, wherein the generated setpoint corresponds to a movement setpoint for a movement controller. | 03-08-2012 |
| 20110284696 | Control column system - The present invention relates to an active control column system for controlling an aircraft, comprising a control member architecture and a control architecture, wherein the control member architecture has at least one mechanically movable control column, at least one actuator for controlling the control column and at least one detection means for detecting at least one state variable of the control column, and the control architecture includes at least one movement regulator for controlling at least one actuator, a feeling generation means for generating at least one desired movement parameter, wherein the feeling generation means is indirectly/directly connected to at least one movement regulator and the generated desired parameter can be supplied to the movement regulator, and wherein at least one detection means is indirectly or directly connected to the feeling generation means for the supply of at least one state variable. | 11-24-2011 |
| 20110147514 | APPARATUS AND METHOD FOR STEERING ANGLE MEASUREMENT OF AN AIRCRAFT LANDING GEAR AND AIRCRAFT LANDING GEAR - The present disclosure relates to a method and an apparatus for the contactless measurement of the steering angle of an aircraft landing gear, in particular of a nose landing gear. Furthermore, this present disclosure relates to an aircraft landing gear, in particular a nose landing gear, which allows a contactless measurement of the steering angle. | 06-23-2011 |
| 20110079297 | Servo Valve - The present invention relates to a two-stage electrohydraulic servo valve with a first stage, which operates as pilot stage and includes a movable nozzle tube, and a second stage which operates as power stage, wherein the nozzle tube of the pilot stage is guided by means of a torsion element and the oil supply of the movable nozzle tube is integrated in the torsion element. | 04-07-2011 |
| 20100307268 | Spindle drive - The present invention relates to a spindle drive having a first load path which is formed by the spindle and having a second load path which is formed by a torsion bar which is exposed to torsion, which is arranged in the spindle and is connected to it such that a rotary movement is exerted onto the spindle in at least one state of the threaded drive by the torsion bar, with the spindle drive having a sensor unit which is made such that it detects a relative movement between the spindle and the torsion bar. | 12-09-2010 |
| 20100300224 | Spindle Drive - The present invention relates to a spindle drive with a first load path which is formed by a first nut which meshes with a threaded bolt and a second load path which is formed by a second nut which likewise meshes with the threaded bolt and which is arranged such that it is movable relative to the first nut in the axial direction of the threaded bolt in at least one state of the spindle drive, with the spindle drive having a sensor unit which is made such that it detects a relative movement between the first nut and the second nut. | 12-02-2010 |
| 20100288886 | Aircraft High Lift System and Method for Determining an Operating Condition of an Aircraft High Lift System - The present disclosure relates to an aircraft high lift system with at least one load station for actuating a flap of a wing, preferably a landing flap and/or a leading-edge flap, at least one transmission with transmission portions located between branch transmissions, wherein by means of the branch transmissions actuating energy can be branched off from the transmission to the load station, and to a method for determining an operating condition of an aircraft high lift system. | 11-18-2010 |
| 20100064823 | Sensor System for Monitoring the Synchronism of Control Surfaces of an Aircraft - The present invention relates to a sensor system for monitoring the synchronism of control surfaces of an aircraft with two transmission links for the mechanical transmission of the movements of one or more control surfaces to at least one sensor, wherein the two transmission links are coupled with each other mechanically and/or via the at least one sensor, whereby a difference between the movements transmitted by the transmission links can be monitored. | 03-18-2010 |
