GOVERNOR FOR A ROTOR WITH A VARIABLE MAXIMUM COLLECTIVE PITCH

• US 20080243313A1
• Filed: 03/26/2007
• Published: 10/02/2008
• Est. Priority Date: 03/26/2007
• Status: Active Grant

• Current Assignee: Bell Helicopter Textron Incorporated (Textron Inc)
• Original Assignee: Bell Helicopter Textron Incorporated (Textron Inc)
• Inventors: Schaeffer, Joseph Mathew
• Granted Patent: US 7,873,445 B2
• Time in Patent Office: Days
• US Class Current: 701/3
• CPC Class Codes: B64C 11/303 characterised by comprising a governor
• CPC Class Codes: B64C 29/0033 the propellers being tiltable relative to the fuselage

Abstract

A governor configured to regulate the rotational velocity of one or more rotors of an aircraft by adjusting a collective blade pitch of the one or more rotors. In one embodiment, the governor comprises a control monitor, a maximum pitch module, a rotor module, and a pitch adjustment module. The control monitor is configured to monitor one or more flight control inputs that are controllable by an operator of the aircraft. The maximum pitch module is configured to dynamically determine a maximum collective blade pitch based on the one or more flight control inputs monitored by the control monitor. The rotor module is configured to monitor information related to the rotational velocity of the one or more rotors. The pitch adjustment module is configured to (i) receive information related to the rotational velocity of the one or more rotors from the rotor module and (ii) adjust the collective blade pitch of the one or more rotors to regulate the rotational velocity of the one or more rotors.

Claims

1. A governor configured to regulate the rotational velocity of one or more rotors of an aircraft by adjusting a collective blade pitch of the one or more rotors, the governor comprising:

a control monitor configured to monitor one or more flight control inputs that are controllable by an operator of the aircraft;

a maximum pitch module configured to dynamically determine a maximum collective blade pitch based on the one or more flight control inputs monitored by the control monitor;

a rotor module configured to monitor information related to the rotational velocity of the one or more rotors; and

a pitch adjustment module configured to (i) receive information related to the rotational velocity of the one or more rotors from the rotor module and (ii) adjust the collective blade pitch of the one or more rotors to regulate the rotational velocity of the one or more rotors, wherein the pitch adjustment module is constrained by the determined maximum collective blade pitch determined by the maximum pitch module such that as the pitch adjustment module adjusts the collective blade pitch of the one or more rotors the collective blade pitch remains below the maximum collective blade pitch.

2. The governor of claim 1, wherein the one or more flight control inputs monitored by the control module comprise a flight control input that dictates a mast angle of the one or more rotors.

3. The governor of claim 2, wherein the maximum pitch module is configured to determine the maximum pitch amount such that the maximum pitch amount has an inversely proportional relationship with the mast angle dictated by the flight control input that dictates the mast angle of the one or more rotors.

4. The governor of claim 1, wherein the one or more flight control inputs monitored by the control module comprise a flight control input that dictates a thrust generated by the one or more rotors.

5. The governor of claim 4, wherein the maximum pitch module is configured to determine the maximum pitch amount such that the maximum pitch amount has a directly proportional relationship with the thrust dictated by the flight control input that dictates the thrust generated by the one or more rotors.

6. The governor of claim 1, wherein the one or more flight control inputs monitored by the control module comprise a flight control input that dictates a mast angle of the one or more rotors and a flight control input that dictates a thrust generated by the one or more rotors.

7. A flight control system that controls an aircraft, the flight control system comprising:

an operator interface configured to enable an operator of the aircraft to control one or more flight control inputs that dictate one or more aspects of the operation of the aircraft; and

a governor configured to regulate the rotational velocity of one or more rotors of the aircraft by adjusting a collective blade pitch of the one or more rotors, the governor comprising;

a control monitor configured to monitor the operator interface to determine information related to the control of the one or more flight control inputs by the operator of the aircraft;

a maximum pitch module configured to dynamically determine a maximum collective blade pitch based on the information related to the control of the one or more flight control inputs determined by the control monitor;

a rotor module configured to monitor information related to the rotational velocity of the one or more rotors;

a pitch adjustment module configured to (i) receive information related to the rotational velocity of the one or more rotors from the rotor module and (ii) adjust the collective blade pitch of the one or more rotors to regulate the rotational velocity of the one or more rotors, wherein the pitch adjustment module is constrained by the determined maximum collective blade pitch determined by the maximum pitch module such that as the pitch adjustment module adjusts the collective blade pitch of the one or more rotors the collective blade pitch remains below the maximum collective blade pitch.

8. The flight control system of claim 7, wherein the information related to the control of the one or more flight control inputs determined by the control monitor comprises information related to a mast angle of the one or more rotors dictated by the one or more flight control inputs controlled by the operator.

9. The flight control system of claim 8, wherein the maximum pitch module is configured to determine the maximum pitch amount such that the maximum pitch amount has an inversely proportional relationship with the mast angle of the one or more rotors dictated by the one or more flight control inputs controlled by the operator.

10. The flight control system of claim 7, wherein the information related to the control of the one or more flight control inputs determined by the control monitor comprises information related to a thrust generated by the one or more rotors that is dictated by the one or more flight control inputs controlled by the operator.

11. The flight control system of claim 10, wherein the maximum pitch module is configured to determine the maximum pitch amount such that the maximum pitch amount has a directly proportional relationship with the thrust generated by the one or more rotors that is dictated by the one or more flight control inputs controlled by the operator.

12. The flight control system of claim 7, wherein the information related to the control of the one or more flight control inputs determined by the control monitor comprises (i) information related to a mast angle of the one or more rotors dictated by the one or more flight control inputs controlled by the operator, and (ii) information related to a thrust generated by the one or more rotors that is dictated by the one or more flight control inputs controlled by the operator.

13. A method of regulating a rotational velocity of one or more rotors of an aircraft, the method comprising:

monitoring one or more flight control inputs that are controllable by an operator of the aircraft;

determining a maximum collective blade pitch based on the monitored one or more flight control inputs;

adjusting the collective blade pitch of the one or more rotors to regulate the rotational velocity of the one or more rotors, wherein the adjustment of the collective blade pitch of the one or more rotors is constrained by the determined maximum collective blade pitch determined by the maximum pitch module such that the collective blade pitch of the one or more rotors remains below the maximum collective blade pitch.

14. The method of claim 13, wherein the one or more flight control inputs that are monitored comprise a flight control input that dictates a mast angle of the one or more rotors.

15. The method of claim 14, wherein the maximum pitch amount is determined such that it has an inversely proportional relationship with the mast angle dictated by the flight control input that dictates the mast angle of the one or more rotors.

16. The method of claim 13, wherein the one or more flight control inputs that are monitored comprise a flight control input that dictates a thrust generated by the one or more rotors.

17. The method of claim 16, wherein the maximum pitch amount is determined such that it has a directly proportional relationship with the thrust dictated by the flight control input that dictates the thrust generated by the one or more rotors.

18. The method of claim 13, wherein the one or more flight control inputs that are monitored comprise a flight control input that dictates a mast angle of the one or more rotors and a flight control input that dictates a thrust generated by the one or more rotors.