Actuator for an aircraft flight control surface

• US 6,082,672 A
• Filed: 12/08/1998
• Issued: 07/04/2000
• Est. Priority Date: 12/08/1997
• Status: Expired due to Term

• Current Assignee: Sagem SA (Safran SA)
• Original Assignee: Sfim Industries
• Inventors: Audren, Jean Thierry
• Primary Examiner(s): Barefoot, Galen L.
• Application Number:
  US09/207,032
• Time in Patent Office: 574 Days
• Field of Search: 244/75 R, 244/228, 244/76 R, 244/178, 244/177, 310/328, 310/331, 310/330, 310/323.03
• US Class Current: 244/99.8
• CPC Class Codes: B64C 13/50 using electrical energy

Abstract

An actuator for a primary control surface of an air-craft, the actuator comprising at least one motor of the vibration type mounted in series with at least a second motor which is a piezoelectric, electrostrictive, or magnetostrictive actuator of the direct type, and further including control means causing one or both of the motors to operate in such a manner that the second motor drives movements of the control surface of the type used for stabilizing the aircraft, while the vibration drives movements of greater amplitude.

Claims

1. An actuator for a primary control surface of an air-craft, the actuator comprising at least one motor of the vibration type mounted in series with at least a second motor which is a piezoelectric, electrostrictive, or magnetostrictive actuator of the direct type, and further including control means causing one or both of the motors to operate in such a manner that the second motor drives movements of the control surface of the type used for stabilizing the aircraft, while the vibration drives movements of greater amplitude.

2. An actuator according to claim 1, wherein the control means comprise an electronic circuit controlling both of the motors as a function firstly of an external set point signal and secondly of signals output by two detectors, one providing information concerning the position of the control surface, and the other providing information concerning the relative angular position between the outlets of the two motors mounted in series.

3. An actuator according to claim 2, wherein the motor is an actuator of the direct type and is controlled by a servo-control loop designed to maintain the position of the control surface on the flight set point.

4. An actuator according to claim 2, wherein the control means apply speed control to the vibration motor as a function of the relative angle between the outlets of the two motors and in application of a non-linear control law.

5. An actuator according to claim 4, wherein the control law is such that:

the vibration motor is not caused to rotate so long as said relative angle is less than a given threshold;

the motor is caused to rotate at a given speed when the absolute value of said relative angle exceeds the threshold; and

rotation of the motor is stopped when said relative angle becomes zero.

6. An actuator according to claim 4, further including filter means at the outlet of the non-linear control.

7. An actuator according to claim 1, comprising a plurality of vibration motors and a plurality of direct type motors in series.