초록 ▼

A rotorcraft control system is provided and includes a rotor blade having a moving surface operatively connected for movement among various positions, an actuator receptive of a modified control signal and operatively connected to move the surface among the various positions, a sensor operably coupl

A rotorcraft control system is provided and includes a rotor blade having a moving surface operatively connected for movement among various positions, an actuator receptive of a modified control signal and operatively connected to move the surface among the various positions, a sensor operably coupled to the actuator to generate a sensor response signal reflective of a response of the actuator to the modified control signal and a controller to output the modified control signal to the actuator, the controller including a control loop to generate the modified control signal from an initial control signal that is modified by relating the initial control signal and the sensor response signal and by accounting for actuator inaccuracies, sensor sensitivities and noise.

대표청구항 ▼

1. A rotorcraft control system, comprising: a rotor blade having a moving surface operatively connected for movement among various positions;an actuator receptive of a modified control signal and operatively connected to move the surface among the various positions;a sensor operably coupled to the a

1. A rotorcraft control system, comprising: a rotor blade having a moving surface operatively connected for movement among various positions;an actuator receptive of a modified control signal and operatively connected to move the surface among the various positions;a sensor operably coupled to the actuator to generate a sensor response signal reflective of a response of the actuator to the modified control signal; anda controller to output the modified control signal to the actuator, the controller including a control loop to generate the modified control signal from an initial control signal that is modified by relating the initial control signal and the sensor response signal and by accounting for actuator inaccuracies, sensor sensitivities and noise,wherein the controller comprises a Kalman filter that outputs for summation with the initial control signal an inverse value of a linear sensor sensitivity to actuator commands and a value of sensor sensitivity to external disturbances. 2. The rotorcraft control system according to claim 1, wherein the moving surface comprises at least one of a primary surface and a secondary surface. 3. The rotorcraft control system according to claim 1, wherein the actuator performs primary flight control. 4. The rotorcraft control system according to claim 1, wherein the actuator performs higher harmonic control and/or primary flight control. 5. The rotorcraft control system according to claim 1, wherein the actuator is at least one of a primary actuator and a secondary actuator. 6. The rotorcraft control system according to claim 1, wherein the controller accounts for sensor sensitivity to the actuator and external disturbances. 7. The rotorcraft control system according to claim 1, further comprising a harmonic estimator, which is receptive of the sensor response signal and configured to generate a harmonic sensor response signal to be outputted to the Kalman filter. 8. A rotorcraft control system, comprising: a rotor blade having a moving surface operatively connected for movement among various positions;an actuator receptive of a modified control signal and operatively connected to move the surface among the various positions;a sensor operably coupled to the actuator to generate a signal reflective of a response of the actuator to the modified control signal;a harmonic estimator, which is receptive of the signal reflective of the actuator response and configured to generate a harmonic sensor response signal accordingly; anda controller to output the modified control signal to the actuator, the controller including a control loop to generate the modified control signal from an initial control signal that is modified by relating the initial control signal and the harmonic sensor response signal and by accounting for actuator inaccuracies, sensor sensitivities and noise,wherein the controller comprises a Kalman filter that outputs for summation with the initial control signal an inverse value of a linear sensor sensitivity to actuator commands and a value of sensor sensitivity to external disturbances. 9. The rotorcraft control system according to claim 8, wherein the moving surface comprises at least one of a primary surface and a secondary surface. 10. The rotorcraft control system according to claim 8, wherein the actuator performs primary flight control. 11. The rotorcraft control system according to claim 8, wherein the actuator performs higher harmonic control and/or primary flight control. 12. The rotorcraft control system according to claim 8, wherein the actuator is at least one of a primary actuator and a secondary actuator. 13. The rotorcraft control system according to claim 8, wherein the controller accounts for sensor sensitivity to the actuator and external disturbances. 14. The rotorcraft control system according to claim 8, wherein the harmonic estimator outputs the harmonic sensor response signal to the Kalman filter. 15. A method of operating a controller of a rotorcraft, the method comprising: outputting at a Kalman filter a modified control signal to an actuator for moving a moving surface on a rotor blade;sensing an actuator response to the modified control signal while accounting for actuator inaccuracies, sensor sensitivity to noise and external forces;generating an actuator response signal from the sensed actuator response;converting the actuator response signal into a harmonic sensor response signal; andgenerating the modified control signal by modifying an initial control signal in accordance with values obtained from the harmonic sensor response signal,the modifying comprising outputting for summation with the initial control signal an inverse value of a linear sensor sensitivity to actuator commands and a value of sensor sensitivity to external disturbances. 16. The method according to claim 15, further comprising inputting the initial control signal into the controller.