| Patent application number | Description | Published |
|---|
| 20090065648 | COMPENSATION ACTUATOR FOR A ROTORCRAFT FLIGHT CONTROL - The invention relates to an actuator ( | 03-12-2009 |
| 20090283642 | BREAKABLE COUPLING DEVICE, AND AN ASSOCIATED TRIM ACTUATOR - A breakable coupling device for coupling together first and second main transmission shafts stationary in translation along a longitudinal axis of rotation of the device comprises a blocking device having a discontinuous first housing and a continuous second housing forming a closed loop; a compression device; at least one drive device connecting the blocking device and the compression device together in rotation about the longitudinal axis below a predetermined torque, wherein the discontinuous first housing is configured to receive the at least one drive device below the predetermined torque; and a shifting device configured to shift the at least one drive device non-reversibly from the discontinuous first housing towards the continuous second housing when the torque exerted on the at least one drive device is greater than the predetermined torque. | 11-19-2009 |
| 20100127121 | ROTARY ACTUATOR INCORPORATING A FORCE RELATIONSHIP, AND A METHOD OF REDUCING ANGULAR SLACK IN SUCH A ROTARY ACTUATOR - A rotary actuator incorporating a three relationship includes a twistably-deformable structure having a first and a second end plate and a helical spring with a first and a second terminal end secured on the first and the second end plate, respectively, and wherein the first and the second end plate have a first and a second notch, respectively, and wherein the first and the second notch have a first and a second contact zone, respectively. The rotary actuator further includes an outlet shaft and a motor assembly having an outlet gear configured to drive the twistably-deformable structure so as to drive the outlet shaft in rotation, wherein, the motor assembly, the twistably-deformable structure and the outlet shaft are disposed in succession. The rotary actuator has a first finger constrained to rotate with the outlet gear and a second finger constrained to rotate with the outlet shaft. | 05-27-2010 |
| 20100308154 | METHOD OF CONTROLLING A HYBRID HELICOPTER IN YAW, AND A HYBRID HELICOPTER PROVIDED WITH A YAW CONTROL DEVICE SUITABLE FOR IMPLEMENTING SAID METHOD - A method of controlling the yaw attitude of a hybrid helicopter including a fuselage and an additional lift surface provided with first and second half-wings extending from either side of the fuselage, each half-wing being provided with a respective first or second propeller. The hybrid helicopter has a thrust control suitable for modifying the first pitch of the first blades of the first propeller and the second pitch of the second blades of the second propeller by the same amount. The hybrid helicopter includes yaw control elements for generating an original order for modifying the yaw attitude of the hybrid helicopter by increasing the pitch of the blades of one propeller and decreasing the pitch of the blades of the other propeller, the original order is optimized as a function of the position of the thrust control to obtain an optimized yaw control order that is applied to the first and second blades. | 12-09-2010 |
| 20100308157 | MECHANICAL DEVICE FOR COMBINING FIRST AND SECOND CONTROL ORDERS, AND AN AIRCRAFT PROVIDED WITH SUCH A DEVICE - The present invention relates to a mechanical device ( | 12-09-2010 |
| 20100308178 | VARIABLE RATIO CRANK FOR A MANUAL FLIGHT CONTROL LINKAGE OF A ROTARY WING AIRCRAFT - The present invention relates to a bellcrank ( | 12-09-2010 |
| 20110024551 | VARIABLE DAMPING OF HAPTIC FEEDBACK FOR A FLIGHT-ATTITUDE CHANGING LINKAGE OF AN AIRCRAFT - The present invention relates to haptic feedback for operating at least one manual flight control device ( | 02-03-2011 |
| 20110114798 | LONG-RANGE AIRCRAFT WITH HIGH FORWARD SPEED IN CRUISING FLIGHT - The present invention relates to an aircraft ( | 05-19-2011 |
