Aircraft servoactuator apparatus

• US 4,228,386 A
• Filed: 06/02/1978
• Issued: 10/14/1980
• Est. Priority Date: 06/02/1978
• Status: Expired due to Term

• Current Assignee: Honeywell Incorporated (Honeywell International Inc.)
• Original Assignee: Sperry Corporation (Unisys Corporation)
• Inventors: Griffith, Carl D.
• Primary Examiner(s): Dobeck, B.
• Application Number:
  US05/912,165
• Time in Patent Office: 865 Days
• Field of Search: 318/628, 318/584, 318/586, 318/591, 244/83 D, 74/480
• US Class Current: 318/628
• CPC Class Codes: B64C 13/345 with artificial feel
• CPC Class Codes: B64C 13/38 with power amplification

Abstract

A single actuator unit is installed in an aircraft, for example, a helicopter, and is coupled to the control linkage from the pilot'"'"'s stick to perform the functions of series actuation, trim actuation, artificial feel, control position sensing, control limits and, if needed, force boost. Although the device performs as a series actuator, it is installed in and connected to the vehicle surface control linkages in the conventional parallel actuator manner and therefore greatly simplifies control system installation and reduces problems associated with control rod vibration resonances normally encountered with series actuator installations.

Claims

1. A combined series and trim actuator for aircraft automatic stabilization systems comprising:

a housing adapted to be secured directly to the aircraft airframe and including input and output shafts coupled in the control rigging between the pilot'"'"'s control member and an aircraft control member,

a first coupling means between said input shaft and said output shaft so constructed and arranged to permit resilient, limited relative motion therebetween,

a second coupling means between said input shaft and said output shaft including clutch means so constructed and arranged that in a first state of said clutch means said input and output shafts are directly connected and in a second clutch means state, said input and output shafts are disconnected,

servomotor means having its output connected to drive said output shaft through said second coupling means in said second clutch means state, and

electric signal means repsonsive to the difference in position between said input shaft and said output shaft for controlling said servomotor whereby to position said output shaft in accordance with the position of said input shaft within the authority of said first coupling means.

2. The actuator as set forth in claim 1 further including

resilient feel means connected with said input shaft for providing artificial surface effect feel to the pilot for movements of said pilot'"'"'s control member from an established trim position, and

trim means coupled with said feel means for varying the trim position of said feel means.

3. The actuator as set forth in claim 2 wherein said trim means includes an electromagnetic clutch means and further including

electric signal responsive means for actuating said trim clutch means whereby to provide automatic trim of said artificial feel means.

4. The actuator as set forth in claim 3 wherein said electric signal responsive means includes

signal level detector means and time delay means responsive thereto for actuating said trim means upon the signal from said electric signal means exceeds a predetermined value for a predetermined time period.

5. The actuator as set forth in claim 3 wherein said resilient artificial feel means includes

a torsion spring coupled with said input shaft and said clutch means, and

damper means coupled with said torsion spring means.

6. The actuator as set forth in claim 2 wherein said first coupling means comprises

a resiliently centered sloppy link for determining said authority limit, said link including switch means actuated in accordance with said authority limit, and

logic means responsive to actuation of said switch means for operating said second coupling means clutch means to its first state.

7. The actuator as set forth in claim 1 further including

further electric signal means responsive to an automatic aircraft control system for further controlling said servomotor means.

8. The actuator as set forth in claim 7 wherein said further electric signal means is responsive to an automatic aircraft stability augmentation system.

9. The actuator as set forth in claim 7 wherein said further electric signal means is responsive to an automatic aircraft flight control system.

10. The actuator as set forth in claim 1 wherein said electric signal means comprises

first signal generating means coupled with said input shaft for providing output signal in accordance with the position thereof,

second signal generator means coupled with said output shaft for providing an output signal in accordance with the position of said output shaft, and

servomotor amplifier means responsive to the difference between the outputs of said first and second signal generator means.

11. The actuator as set forth in claim 1 wherein said servomotor means comprises

first and second servomotors and mechanical differential means having its inputs responsive to said first and second servomotors, and its output connected to drive said output shaft,

and wherein said electric signal means comprises

first and second signal generators coupled to said input shaft and first and second signal generators coupled to said output shaft for controlling said first and second servomotors respectively in accordance with the difference between the signals generated by its respective first and second signal generators.

12. The actuator as set forth in claim 1 wherein said servomotor means in response to said differential signal provides a force boost to the said output shaft.