The present disclosure provides an actuation system for a flight control surface of an aircraft, having: a support frame for supporting a flight control surface, the support frame being configured to be mounted to an airframe structure of the aircraft for movement between a first position and a seco
The present disclosure provides an actuation system for a flight control surface of an aircraft, having: a support frame for supporting a flight control surface, the support frame being configured to be mounted to an airframe structure of the aircraft for movement between a first position and a second position to operate and move the control surface; an actuation mechanism configured to effect movement of the support frame between the second position and the first position; and a detection device for detecting a fault in the actuation mechanism, the detection device comprising a deflector configured to deflect or skew the support frame away from or out of the first position in the event of a fault in the actuation mechanism.
대표청구항▼
1. An actuation system for a flight control surface of an aircraft, comprising: a support frame for supporting a flight control surface, the support frame being configured to be mounted to an airframe structure of the aircraft for movement between a first position and a second position to move and o
1. An actuation system for a flight control surface of an aircraft, comprising: a support frame for supporting a flight control surface, the support frame being configured to be mounted to an airframe structure of the aircraft for movement between a first position and a second position to move and operate the control surface;an actuation mechanism configured to effect movement of the support frame between the second position and the first position; anda detection device for detecting a problem or a fault in the actuation mechanism, the detection device comprising a deflector configured to deflect or skew the support frame away from or out of the first position in the event of a problem or fault in the operation of the actuation mechanism,wherein the deflector comprises at least one biasing member for generating a biasing force acting against a moving force of the actuation mechanism to deflect or skew the support frame out of the first position. 2. The actuation system according to claim 1, wherein the actuation mechanism is configured and arranged to operate against the biasing force to move the support frame to the first position. 3. The actuation system according to claim 1, wherein the biasing member is resilient. 4. The actuation system according to claim 3, wherein the biasing member comprises a spring member. 5. The actuation system according to claim 1, wherein the detection device comprises one or more sensor for detecting a deflection or skewing of the support frame with respect to the first position. 6. The actuation system according to claim 1, wherein the first position of the support frame corresponds to a retracted position for the control surface and the second position corresponds to an extended position for the control surface. 7. The actuation system according to claim 1, wherein the flight control surface is provided or formed by a movable flap or slat of an aircraft wing structure. 8. The actuation system according to claim 1, wherein the actuation mechanism comprises a drive unit which is operatively connected to the support frame and is drivable through a range of motion to move the support frame between the first position and the second position, wherein the deflection means is configured to deflect or skew the support frame out of the first position in the event of a fault in the operative connection between the drive unit and the support frame of the actuation mechanism. 9. The actuation system according to claim 7, wherein the drive unit is a linear drive unit, and wherein the support frame is configured at least partially to pivot or rotate between the first position and the second position. 10. An aircraft, comprising: an airframe structure;a movable support frame mounted on the airframe structure for movement between a first position and a second position;a flight control surface supported on the support frame, wherein movement of the support frame between the first and second position moves the control surface during aircraft operation;at least two actuation mechanisms provided on the airframe structure for effecting movement of the support frame between the first position and the second position; anda detection device for detecting a fault in either one of the actuation mechanisms, wherein the detection device comprises a deflector configured to deflect or skew the support frame with respect to, or out of, the first position in the event of a fault in any one of the actuation mechanisms,wherein the deflector includes at least one biasing member for generating a biasing force acting to deflect or skew the support frame out of or away from the first position. 11. The aircraft according to claim 10, wherein the detection device comprises one or more sensors for detecting, measuring and/or assessing a deflected or skewed position of the support frame supporting the flight control surface. 12. The aircraft according to claim 10, wherein each actuation mechanism comprises a drive unit operatively connected to the support frame and drivable through a range of motion to move the support frame between the first position and the second position, or a non-linear actuator, such as a rotary actuator. 13. The aircraft according to claim 12, wherein the non-linear actuator is electrically or hydraulically activated. 14. The aircraft according to claim 10, wherein at least two actuation mechanisms are provided for independent operation in parallel with one another laterally spaced apart on the airframe structure to effect movement of the support frame between the first position and the second position, wherein the detection device comprises a separate deflector respectively associated with each actuation mechanism to generate the said deflection or skew in the event of a problem or fault in an operative connection of that actuation mechanism with the support frame. 15. A method of detecting a problem or fault in a system for actuation of a flight control surface of an aircraft on the ground, the method comprising: providing a support frame supporting a flight control surface of an aircraft, the support frame mounted on an airframe structure of the aircraft for movement between a first position and a second position to move the flight control surface;providing an actuation mechanism for effecting movement of the support frame between the first position and the second position;generating a biasing force that acts against the moving force of the actuation mechanism to deflect or skew the support frame with respect to the first position in the event of a problem or fault in an operative connection between the actuation mechanism and the support frame; andsensing or measuring a posture of the support frame on the ground when the actuation mechanism moves the support frame to the first position to detect any deflection or skew with respect to the first position;wherein the flight control surface is provided by a wing flap at a trailing edge of a wing structure.
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이 특허에 인용된 특허 (7)
Recksiek,Martin; Rechter,Harald; Besing,Wolfgang, Adaptive flap and slat drive system for aircraft.
Richter, Martin; Fleddermann, Andreas, 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.
Lindstrom Jeffrey V. ; Reed R. David ; Platin Bradley E. ; Beyer Kevin W. ; Reusch David C., Method and apparatus for detecting skew and asymmetry of an airplane flap.
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