Rotorcraft autopilot and methods

• US 9,758,244 B2
• Filed: 02/04/2016
• Issued: 09/12/2017
• Est. Priority Date: 02/10/2012
• Status: Active Grant

• Current Assignee: Merlin Technologies Incorporated
• Original Assignee: Merlin Technologies Incorporated
• Inventors: Mercer, John E., Albion, Nicolas, Bartel, Mark, Feifel, Marc, Marvin, Mark
• Primary Examiner(s): MARC-COLEMAN, MARTHE Y
• Application Number:
  US15/015,689
• Publication Number:
  US 20160152330A1
• Time in Patent Office: 586 Days
• Field of Search: 701 3, 701 13, 244177, 244192, 244175, 244 1713
• CPC Class Codes: B64C 13/0421 control sticks for primary flight controls
• CPC Class Codes: B64C 13/044 operated by feet, e.g. pedals
• CPC Class Codes: B64C 13/18 using automatic pilot
• CPC Class Codes: B64C 13/341 having duplication or stand-by provisions
• CPC Class Codes: B64C 27/56 characterised by the control initiating means, e.g. manually actuated
• CPC Class Codes: B64C 27/57 automatic or condition responsive, e.g. responsive to rotor speed, torque or thrust
• CPC Class Codes: B64C 27/58 Transmitting means, e.g. interrelated with initiating means or means acting on blades means acting on blades B64C27/72
• CPC Class Codes: B64C 27/59 mechanical
• CPC Class Codes: B64C 27/64 using fluid pressure, e.g. having fluid power amplification
• CPC Class Codes: B64C 27/68 using electrical energy, e.g. having electrical power amplification
• CPC Class Codes: G05D 1/0077 using redundant signals or controls
• CPC Class Codes: G05D 1/0816 to ensure stability
• CPC Class Codes: G05D 1/0858 specially adapted for vertical take-off of aircraft
• CPC Class Codes: G05D 1/102 specially adapted for vertical take-off of aircraft
• CPC Class Codes: Y02T 50/40 Weight reduction

Abstract

A helicopter autopilot system includes an inner loop for attitude hold for the flight of the helicopter including a given level of redundancy applied to the inner loop. An outer loop is configured for providing a navigation function with respect to the flight of the helicopter including a different level of redundancy than the inner loop. An actuator provides a braking force on a linkage that serves to stabilize the flight of the helicopter during a power failure. The actuator is electromechanical and receives electrical drive signals to provide automatic flight control of the helicopter without requiring a hydraulic assistance system in the helicopter. The autopilot can operate the helicopter in a failed mode of the hydraulic assistance system. A number of flight modes are described with associated sensor inputs including rate based and true attitude modes.

Claims

1. As part of an autopilot for providing automatic control of a helicopter by actuating one or more flight controls of the helicopter, an actuator arrangement comprising:

at least one electric motor including an output shaft and a motor coil arrangement for receiving a drive current that produces rotation of the output shaft;

an actuator linkage that is operatively coupled between the output shaft of the motor and the flight controls such that rotation of the output shaft produces a corresponding movement of the actuator linkage and the flight controls; and

a motor drive arrangement that is operable to provide said drive current from a power source during normal operation of the autopilot and at least for shorting the motor coil arrangement responsive to a failure of the power source such that the motor provides a braking force on said actuator linkage that serves to stabilize the flight of the helicopter during said power failure.

2. The actuator arrangement of claim 1 wherein the motor drive arrangement is configured to electrically short the motor coil arrangement.

3. The actuator arrangement of claim 2 wherein the motor drive arrangement includes at least one MOSFET that is arranged to at least momentarily electrically connect the motor coil arrangement to a helicopter ground responsive to the power failure.

4. The actuator arrangement of claim 2 including a power storage capacitor that is charged responsive to normal operation of said power source and the motor drive arrangement is configured to discharge the power storage capacitor responsive to the failure of the power source in a way that biases said MOSFET to an on state to at least momentarily short the motor coil arrangement.

5. The actuator arrangement of claim 2 wherein the electric motor includes a Y-connected stator coil having three branch coils and wherein the motor drive arrangement includes a group of MOSFETs that are arranged to cooperatively momentarily short the branch coils responsive to the failure of the power source.

6. The actuator arrangement of claim 5 wherein the group of MOSFETs is arranged to at least momentarily electrically connect each branch coil to a helicopter ground responsive to the power failure.

7. The actuator arrangement of claim 5 including a power storage capacitor that is charged responsive to normal operation of said power source and the actuator arrangement is configured to discharge the power storage capacitor responsive to the failure of the power source in a way that biases each MOSFET of said group to an on state to at least momentarily short the branch coils.

8. The actuator arrangement of claim 2 wherein the motor drive arrangement includes at least one electromechanical relay that is arranged to electrically short the motor coil arrangement responsive to the power failure.

9. The actuator arrangement of claim 8 wherein the electromechanical relay includes at least one normally closed contact that is arranged to electrically connect the motor coil to a helicopter ground responsive to a failure of the power source.

10. An autopilot system for a helicopter which includes a hydraulic assistance system that receives flight control inputs from a pilot and, in turn, produces mechanical outputs that are mechanically coupled to the helicopter to provide pilot control of the helicopter, said autopilot system comprising:

a sensor arrangement that produces a set of sensor outputs that characterize the flight of the helicopter;

a control arrangement that receives the sensor outputs and generates electrical drive signals; and

an actuator arrangement that is electromechanical and receives said electrical drive signals to generate control outputs responsive thereto that are mechanically coupled to the hydraulic assistance system and which is configured to cooperate with the control arrangement to provide automatic flight control of the helicopter in a first, normal mode with the hydraulic assistance system in a normal operational status and in a second, failed mode with the hydraulic assistance system in a failed operational status to provide automatic flight control of the helicopter in each of the normal mode and the failed mode.

11. The autopilot system of claim 10 wherein said sensor arrangement is configured to sense an operational status of the hydraulic assistance system as one of the normal mode and the failed mode and said control arrangement generates the electrical drive signals based on a first, normal set of parameters responsive to detection of the normal mode and a second, failure set of parameters responsive to detection of the failed mode of the hydraulic system.

12. The autopilot system of claim 11 wherein a failure of the hydraulic assistance system creates a dead zone for mechanical control inputs applied thereto and wherein the failure set of parameters is configured at least to compensate for the dead zone.

13. The autopilot system of claim 10 wherein said actuator arrangement couples the control outputs to a cyclic control of the helicopter in parallel with any pilot actuations that are applied to the cyclic control.

14. The autopilot system of claim 10 wherein said helicopter includes a cyclic control that is controlled by said hydraulic assistance system and wherein said actuator arrangement provides mechanical inputs to actuate the hydraulic assistance system.