IP Library Granted Patent US 8,474,752
Granted Patent B2
US 8,474,752 · App. 13/590,078 · Granted Jul 2, 2013

Actuator force equalization controller

Inventor: Douglas B. Kirkland (Mukilteo, WA)
Assignee: The Boeing Company
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Quick Facts
Patent No.
US 8,474,752
App. No.
13/590,078
Granted
Jul 2, 2013
Kind
B2
Abstract

An actuation system including a plurality of actuators; a plurality of position sensors coupled to the actuators, the plurality of position sensors providing rate feedback signals proportional to an actuator rate; a plurality of force sensors coupled to the actuators, the plurality of force sensors providing delta pressure signals; and a feedback control loop configured to receive the rate feedback signals and delta pressure signals and compute a difference in actual actuator rates and sum the difference with a computed difference in actuator forces to generate actuator positioning commands that equalize the actuator forces on a control surface.

Claims (16)

1. An actuation system comprising:

a plurality of actuators;

a plurality of position sensors coupled to the actuators, the plurality of position sensors providing rate feedback signals proportional to an actuator rate;

a plurality of force sensors coupled to the actuators, the plurality of force sensors providing delta pressure signals;

a feedback controller configured to receive the rate feedback signals and delta pressure signals and compute a difference in actual actuator rates and sum the difference with a computed difference in actuator forces to generate actuator positioning commands that equalize the actuator forces on a control surface; and

a multiplication module, wherein a first force fight component is multiplied by a lead-lag factor to generate a factored first force fight component, the lead-lag factor being substantially equal to Kest/Aest and wherein the lead-lag factor accounts for an estimated force fight loop stiffness and for corrective gain factors.

2. The actuation system of claim 1 , wherein said plurality of force sensors comprise linear variable differential transformers (LVDTs), piezoelectric pressure sensors and combinations thereof.

3. The actuation system of claim 1 , wherein the control surface comprises ailerons, flaperons, rudders, elevators, elevons, canards and ruddervators.

4. The actuation system of claim 1 , wherein at least one feedback signal comprises a feedback position signal.

5. The actuation system of claim 4 , wherein a feedback position signal is provided by an electro-hydraulic servo valve.

6. The actuation system of claim 1 , further comprising a signal limiter applied to a predicted force fight in an actuator in the plurality of actuators.

7. The actuation system of claim 6 , wherein the predicted force fight is multiplied by a conversion factor to relate the predicted force fight to an actuator ram position.

8. The actuation system of claim 1 , further comprising a compensation for limit cycles that may result due to actuator friction and digital controller quantization.

9. The actuation system of claim 1 , wherein the predicted force fight is multiplied by a gain factor so as to improve the performance of the equalization.

10. The actuation system of claim 1 , further comprising a low pass filter applied to the predicted force fight so as to limit the creation of limit cycles when an actuator ram hits an endstop.

11. The actuation system of claim 1 , further comprising a summing module that generates a force equalization command by summing the force equalization command with a pilot or autopilot command, to command an actuator to cause a compensating change to an actuator position.

Continuity (2)
Division 12323090 · Nov 25, 2008
Related Publication 20130026298A1 · Jan 31, 2013