Method for automatic piloting of a rotary wing aircraft having at least one thruster propeller, associated automatic autopilot device, and aircraft

• US 10,144,508 B2
• Filed: 11/20/2017
• Issued: 12/04/2018
• Est. Priority Date: 07/12/2011
• Status: Active Grant

• Current Assignee: Airbus Helicopters
• Original Assignee: Airbus Helicopters
• Inventors: Eglin, Paul
• Primary Examiner(s): Badawi, Medhat
• Application Number:
  US15/817,888
• Publication Number:
  US 20180072411A1
• Time in Patent Office: 379 Days
• CPC Class Codes: B64C 27/22 Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
• CPC Class Codes: B64C 27/57 automatic or condition responsive, e.g. responsive to rotor speed, torque or thrust
• CPC Class Codes: B64D 45/00 Aircraft indicators or protectors not otherwise provided for camouflage F41H3/00
• CPC Class Codes: G05D 1/0858 specially adapted for vertical take-off of aircraft

Abstract

An autopilot device and method for automatically piloting a rotary wing aircraft, having at least one propulsion propeller, the rotary wing including at least one rotor with blades, the device including a processor co-operating with at least one collective control system for controlling the collective pitch of the blades. The device includes engagement means connected to the processor for engaging an assisted mode of piloting for maintaining an angle of attack, the processor automatically controlling the collective pitch of the blades when the assisted mode of piloting for maintaining an angle of attack is engaged by controlling the collective control system to maintain an aerodynamic angle of attack (α) of the aircraft at a reference angle of attack (α*).

Claims

1. A method for a rotary wing aircraft having at least one propulsion propeller provided with a plurality of propulsion propeller blades configured to contribute to propulsion of the aircraft, a rotary wing having a main rotor provided with a plurality of main rotor blades, an adjustment mechanism having a servo-control arrangement configured to adjust pitch of the main rotor blades, and a collective control system connected to the adjustment mechanism and configured to control a collective pitch of the main rotor blades via the adjustment mechanism, the method comprising:

during an assisted piloting mode, automatically controlling, by a processor, the collective control system to control the collective pitch of the main rotor blades to maintain an aerodynamic angle of attack (a) of the aircraft equal to a reference angle of attack (a*); and

wherein automatically controlling the collective control system to control the collective pitch of the main rotor blades to maintain the aerodynamic angle of attack (a) of the aircraft equal to the reference angle of attack (a*) includes servo-controlling the collective pitch of the main rotor blades via the servo-control arrangement of the adjustment mechanism so that the aerodynamic angle of attack (a) of the aircraft either tends toward the reference angle of attack (a*) or is equal to the reference angle of attack (a*), whereby when the aerodynamic angle of attack (a) of the aircraft is no longer equal to the reference angle of attack (a*) action is taken on the collective pitch of the main rotor blades to cause the aerodynamic angle of attack (a) of the aircraft to become equal to the reference angle of attack (a*).

2. The method according to claim 1, wherein the collective pitch of the main rotor blades is controlled automatically to control a vertical air speed of the aircraft so as to maintain the aerodynamic angle of attack (α

) of the aircraft equal to the reference angle of attack (α

*) by application of the following relationship;

α

*=θ

−

arcsin(VZ/TAS)

where “

VZ”

represents the vertical air speed of the aircraft, “

TAS”

represents the true air speed of the aircraft, “

θ

”

represents a current longitudinal attitude of the aircraft, and “

α

*”

represents the reference angle of attack.

3. The method according to claim 1, wherein the reference angle of attack (α

*) is equal to a current value of the aerodynamic angle of attack (α

) of the aircraft at the moment that the assisted piloting mode is engaged.

4. The method according to claim 1, further comprising:

modifying the reference angle of attack (α

*) during flight of the aircraft.

5. The method according to claim 1, wherein the aircraft further includes a cyclic control system connected to the adjustment mechanism and configured to control a cyclic pitch of the main rotor blades via the adjustment mechanism, the method further comprising:

during the assisted mode of piloting, automatically controlling, by the processor, the cyclic control system to control the cyclic pitch of the main rotor blades to maintain a longitudinal attitude (q) of the aircraft equal to a reference longitudinal attitude (q*).

6. The method according to claim 5, wherein automatically controlling the cyclic control system to control the cyclic pitch of the main rotor blades to maintain the longitudinal attitude (θ

) of the aircraft equal to the reference longitudinal attitude (θ

*) includes servo-controlling automatically the reference attitude (θ

*) to a current value of the longitudinal attitude (θ

) of the aircraft when a pilot operates the cyclic control system for controlling the cyclic pitch of the main rotor blades so as to modify the longitudinal attitude (θ

) of the aircraft.

7. The method according to claim 5, wherein automatically controlling the cyclic control system to control the cyclic pitch of the main rotor blades to maintain the longitudinal attitude (θ

) of the aircraft equal to the reference longitudinal attitude (θ

*) includes keeping the reference longitudinal attitude (θ

*) constant when a pilot operates the cyclic control system for controlling the cyclic pitch of the main rotor blades so as to modify the longitudinal attitude (θ

) of the aircraft.

8. The method according to claim 1, wherein the reference angle of attack (α

*) is bounded.

9. The method according to claim 1, further comprising:

displaying a first symbol representing a reference air speed vector on an artificial horizon so that a pilot will visualize a reference air-path slope and consequently the reference angle of attack (α

*).

10. The method according to claim 9, further comprising:

displaying a second symbol representing a reference longitudinal attitude (θ

*) on the artificial horizon.

11. The method according to claim 10, further comprising:

displaying a third symbol representing a current air speed vector on the artificial horizon.

12. The method according to claim 11, further comprising:

displaying a fourth symbol representing a current ground speed vector on the artificial horizon.

13. The method according to claim 9, wherein with at least one symbol being displayed on the artificial horizon to illustrate the reference angle of attack, modifying the color of the symbol whenever automatic control of the collective pitch of the main rotor blades to maintain the reference angle of attack (α

*) requires power greater than a threshold power, and modifying automatically the reference angle of attack (α

*) to comply with the threshold power.

14. An autopilot device for automatically piloting a rotary wing aircraft having at least one propulsion propeller provided with a plurality of propulsion propeller blades configured to contribute to propulsion of the aircraft, a rotary wing having a main rotor provided with a plurality of main rotor blades, an adjustment mechanism having a servo-control arrangement configured to adjust pitch of the main rotor blades, and a collective control system connected to the adjustment mechanism and configured to control a collective pitch of the main rotor blades via the adjustment mechanism, the autopilot device comprising:

a processor configured to, during an assisted mode of piloting, automatically control the collective control system to control a collective pitch of the main rotor blades to maintain an aerodynamic angle of attack (a) of the aircraft equal to a reference angle of attack (a*); and

wherein the processor automatically controls the collective control system to control the collective pitch of the main rotor blades to maintain the aerodynamic angle of attack (a) of the aircraft equal to the reference angle of attack (a*) by servo-controlling the collective pitch of the main rotor blades via the servo-control arrangement of the adjustment mechanism so that the aerodynamic angle of attack (a) of the aircraft either tends toward the reference angle of attack (a*) or is equal to the reference angle of attack (a*), whereby when the aerodynamic angle of attack (a) of the aircraft is no longer equal to the reference angle of attack (a*) action is taken on the collective pitch of the main rotor blades to cause the aerodynamic angle of attack (a) of the aircraft to become equal to the reference angle of attack (a*).

15. The autopilot device according to claim 14, wherein the processor automatically controls the collective control system to control the collective pitch of the main rotor blades to control a vertical air speed of the aircraft in such a manner as to maintain the aerodynamic angle of attack (α

) of the aircraft equal to a reference angle of attack (α

*) is in compliance with the following relationship;

α

*=θ

−

arcsin(VZ/TAS)

where “

VZ”

represents the vertical air speed of the aircraft, “

TAS”

represents a true air speed of the aircraft, “

θ

”

represents a current longitudinal attitude of the aircraft, and “

α

*”

represents the reference angle of attack, the device further comprises a set of means connected to the processor to determine the vertical air speed of the aircraft, the true air speed of the aircraft, and the current longitudinal attitude.

16. The autopilot device according to claim 14, wherein the processor is further operable to adjust the reference angle of attack (α

*).

17. The autopilot device according to claim 14, wherein the aircraft further includes a cyclic control system connected to the adjustment mechanism and configured to control a cyclic pitch of the main rotor blades via the adjustment mechanism, wherein the processor is further configured to, during the assisted mode of piloting, automatically control the cyclic pitch of the main rotor blades to maintain a longitudinal attitude (q) of the aircraft equal to a reference longitudinal attitude (q*).

18. The autopilot device according to claim 14, further comprising a display connected to the processor to display at least one symbol illustrating the reference angle of attack (a*).

19. An aircraft comprising:

at least one propulsion propeller provided with a plurality of propulsion propeller blades configured to contribute to propulsion of the aircraft;

a rotary wing having a main rotor provided with a plurality of main rotor blades;

an adjustment mechanism having a servo-control arrangement configured to adjust pitch of the main rotor blades;

a collective control system connected to the adjustment mechanism and configured to control a collective pitch of the main rotor blades via the adjustment mechanism;

an autopilot device for automatically piloting the aircraft, the autopilot device including a processor configured to, during an assisted mode of piloting, automatically control the collective control system to control a collective pitch of the main rotor blades to maintain an aerodynamic angle of attack (a) of the aircraft equal to a reference angle of attack (a*); and

wherein the processor automatically controls the collective control system to control the collective pitch of the main rotor blades to maintain the aerodynamic angle of attack (a) of the aircraft equal to the reference angle of attack (a*) by servo-controlling the collective pitch of the main rotor blades via the servo-control arrangement of the adjustment mechanism so that the aerodynamic angle of attack (a) of the aircraft either tends toward the reference angle of attack (a*) or is equal to the reference angle of attack (a*), whereby when the aerodynamic angle of attack (a) of the aircraft is no longer equal to the reference angle of attack (a*) action is taken on the collective pitch of the main rotor blades to cause the aerodynamic angle of attack (a) of the aircraft to become equal to the reference angle of attack (a*).

20. The aircraft according to claim 19, further comprising:

a cyclic control system connected to the adjustment mechanism and configured to control a cyclic pitch of the main rotor blades via the adjustment mechanism; and

wherein the processor is further configured to, during the assisted mode of piloting, automatically control the cyclic pitch of the main rotor blades to maintain a longitudinal attitude (q) of the aircraft equal to a reference longitudinal attitude (q*).