Single boost hydraulic control system with magnetorheological actuator
One embodiment is an aircraft comprising a fuselage; a rotor system connected to the fuselage and comprising at least one rotor blade; a pilot input device; a single hydraulic servo actuator in mechanical communication with the pilot input device and the rotor system for providing force assistance in connection with the pilot input device; and a magnetorheological (MR) actuator in mechanical communication with the pilot input device and the rotor system for providing auto pilot assistance in connection with the pilot input device; wherein subsequent to detection of a failure of the single hydraulic servo actuator, the MR actuator is caused to provide force assistance to the pilot input device.
1. An aircraft comprising:
a fuselage;
a rotor system connected to the fuselage and comprising at least one rotor blade;
a pilot input device;
a single hydraulic servo actuator in mechanical communication with the pilot input device and the rotor system for providing force assistance in connection with the pilot input device; and
a magnetorheological (MR) actuator in mechanical communication with the pilot input device and the rotor system for providing auto pilot assistance in connection with the pilot input device;
wherein subsequent to detection of a failure of the single hydraulic servo actuator, the MR actuator is caused to provide force assistance to the pilot input device.
2. The aircraft of claim 1 , further comprising a flight control computer connected to receive pressure data from the single hydraulic servo actuator indicative of an operational status of the single hydraulic servo actuator.
3. The aircraft of claim 2 , further comprising a load cell configured to provide to the flight control computer information regarding a load required to be applied to the pilot input device to move the pilot input device.
4. The aircraft of claim 2 , wherein the flight control computer controls an operation of the MR actuator.
5. The aircraft of claim 2 , wherein the MR actuator comprises MR fluid comprising ferromagnetic particles dispersed in a carrier fluid.
6. The aircraft of claim 5 , wherein the flight control computer causes an increased magnetic flux to be applied to the MR fluid of the MR actuator to increase a torque output of the MR actuator subsequent to the detection of the failure of the single hydraulic servo actuator.
7. The aircraft of claim 1 , wherein subsequent to detection of the failure of the single hydraulic servo actuator, the MR actuator is caused to cease to provide auto pilot assistance in connection with the pilot input device.
8. A system comprising:
a pilot input device for controlling operation of a rotor system comprising at least one rotor blade;
a single hydraulic servo actuator in mechanical communication with the pilot input device and the rotor system for providing force assistance in connection with the pilot input device;
a magnetorheological (MR) actuator in mechanical communication with the pilot input device and the rotor system for providing auto pilot assistance in connection with the pilot input device; and
a flight control computer for detecting a failure of the single hydraulic servo actuator and subsequent to the detection causing the MR actuator to provide force assistance to the pilot input device.
9. The system of claim 8 , further comprising a pressure switch associated with the single hydraulic servo actuator for indicating a pressure of the single hydraulic servo actuator to the flight control computer.
10. The system of claim 9 , wherein, when the pressure indicated by the pressure switch is zero, the single hydraulic servo actuator is determined to have failed.
11. The system of claim 8 , further comprising a load cell for indicating to the flight control computer a load required to be applied to the pilot input device to move the pilot input device.
12. The system of claim 11 , wherein, when the load indicated by the load cell exceeds a threshold value, the single hydraulic servo actuator is determined to have failed.
13. The system of claim 8 , wherein the MR actuator comprises an MR fluid device including first and second bodies and MR fluid disposed between the first and second bodies, wherein the MR fluid comprises ferromagnetic particles suspended in a carrier fluid.
14. The system of claim 13 , wherein movement between the first and second bodies is more restricted when MR fluid device a first magnetic flux than when the MR fluid device is subject to a second magnetic flux smaller than the first magnetic flux.
15. The system of claim 8 , wherein the flight control computer causes an increased magnetic flux to be applied to MR fluid within the MR actuator to increase a torque output of the MR actuator subsequent to the detection of the failure of the single hydraulic servo actuator.
16. The system of claim 8 , wherein subsequent to detection of the failure of the single hydraulic servo actuator, the MR actuator is caused to cease to provide auto pilot assistance in connection with the pilot input device.
17. A method of boosting pilot flight control input in a rotorcraft including a pilot input device for controlling operation of a rotor system comprising at least one rotor blade, the method comprising:
providing a single hydraulic servo actuator in mechanical communication with the pilot input device and the rotor system for providing force assistance in connection with the pilot input device;
providing a magnetorheological (MR) actuator in mechanical communication with the pilot input device and the rotor system for providing auto pilot assistance in connection with the pilot input device; and
detecting a failure of the single hydraulic servo actuator and subsequent to the detection causing the MR actuator to provide force assistance to the pilot input device.
18. The method of claim 17 , wherein the detecting further comprises providing a pressure switch associated with the single hydraulic servo actuator for indicating a pressure of the single hydraulic servo actuator to the flight control computer, wherein, when the pressure indicated by the pressure switch is zero, the single hydraulic servo actuator is determined to have failed.
19. The method of claim 18 , wherein the detecting further comprises providing a load cell for indicating to the flight control computer a load required to be applied to the pilot input device to move the pilot input device, wherein when the load indicated by the load cell exceeds a threshold value, the single hydraulic servo actuator is determined to have failed.
20. The method of claim 18 , further comprising, subsequent to detection of the failure of the single hydraulic servo actuator, causing the MR actuator to cease to provide auto pilot assistance in connection with the pilot input device.