Multi-objective control system with control allocation

Patent metadata

Field	Value
Publication number	US-10526077-B2
Application number	US-201715441506-A
Country	US
Kind code	B2
Filing date	Feb 24, 2017
Priority date	May 11, 2016
Publication date	Jan 7, 2020
Grant date	Jan 7, 2020

Abstract

A flight system for an aircraft and method for controlling a clearance between a first rotor disk and a second rotor disk of an aircraft is disclosed. The flight system includes a sensor for measuring an angle of deviation of at least one of a first rotor disk and a second rotor disk of the aircraft to indicate a clearance between the first rotor disk and the second rotor disk as well as sensors for measuring a flight condition of the aircraft. A control allocation module uses the measured angle of deviation and the flight condition of the aircraft to determine an allocation of control settings to axis-controlling devices of the aircraft to attain a selected pitch of the aircraft, wherein the allocation is based at least on the measured angle of deviation and the flight state of the aircraft.

First claim

The invention claimed is:

1. A method of controlling a clearance between a first rotor disk and a second rotor disk of a main rotor of an aircraft, the method comprising:
measuring an angle of deviation of at least one of the first rotor disk and the second rotor disk of the aircraft, wherein the angle of deviation is indicative of the clearance between the first rotor disk and the second rotor disk;
determining a flight state of the aircraft;
determining an allocation of control settings between the main rotor and an elevator of the aircraft to attain a selected pitch of the aircraft, wherein the allocation is based at least on the measured angles of deviation and the flight state of the aircraft; and
implementing the control settings between the main rotor and the elevator to control the clearance.

2. The method of claim 1 , wherein the first rotor disk and the second rotor disk are coaxially rotating rotor disks and the clearance is a distance between a blade tip of the first rotor disk and a blade tip of the second rotor disk.

3. The method of claim 1 , wherein the control settings are related to an angle of attack (AoA) feedback signal that indicates the current angle of attack of the aircraft.

4. The method of claim 3 , wherein the AoA feedback signal further includes a combination of the AoA feedback signal, a commanded pitch rate and a feedback signal from a feedback module of the aircraft.

5. The method of claim 1 , wherein the control settings include at least one of: (i) a longitudinal setting for the main rotor of the aircraft; (ii) a lateral setting for the main motor of the aircraft; (iii) a setting for an angle of attack of the elevator; and (iv) a collective setting for the main rotor.

6. The method of claim 5 , further comprising allocating the control settings based on at least one of: (i) a velocity of the aircraft; (ii) an altitude of the aircraft; and (iii) a weight of the aircraft.

7. The method of claim 1 , wherein the angle of deviation is at least one of a longitudinal tip angle of the one of the first and second rotor disks and a lateral tilt angle of the first rotor disk.

8. The method of claim 1 , wherein implementing the control settings further comprises at least one of: (i) implementing the aircraft pitch rate to track the commanded pitch rate when the aircraft is hovering; and (ii) implementing the aircraft pitch rate to align with the aircraft flight path.

9. A flight control system for an aircraft, comprising:
a sensor for measuring an angle of deviation of at least one of a first rotor disk and a second rotor disk of a main rotor of the aircraft, wherein the angle of deviation is indicative of a clearance between the first rotor disk and the second rotor disk;
a sensor for measuring a flight state of the aircraft; and
a processor that uses the measured angle of deviation and the flight state of the aircraft to determine an allocation of control settings between the main rotor and an elevator of the aircraft to attain a selected pitch of the aircraft that controls the clearance, wherein the allocation is based at least on the measured angle of deviation and the flight state of the aircraft.

10. The flight system of claim 9 , wherein the first rotor disk and the second rotor disk are coaxially rotating rotor disks and the clearance is a distance between a blade tip of the first rotor disk and a blade tip of the second rotor disk.

11. The flight system of claim 10 , wherein the processor allocates the control settings based on an angle of attack (AoA) feedback signal that indicates the current angle of attack of the aircraft.

12. The flight system of claim 11 , wherein the AoA feedback signal further includes a combination of the AoA feedback signal, a commanded pitch rate, and a feedback signal from a feedback module of the aircraft.

13. The flight system of claim 11 , wherein the control settings include at least one of: (i) a longitudinal setting for the main rotor; (ii) a lateral setting for the main rotor of the aircraft; (iii) a setting for an angle of attack of the elevator; and (iv) a collective setting for the main rotor.

14. The flight system of claim 12 , wherein the processor allocates the control settings based on at least one of: (i) a velocity of the aircraft; (ii) an altitude of the aircraft; and (iii) a weight of the aircraft.

15. The flight system of claim 12 , wherein the angle of deviation is at least one of a longitudinal tip angle of the one of the first and second rotor disks and a latitudinal tilt angle of the first rotor disk.

Assignees

• Sikorsky Aircraft Corp

Inventors

• Wulff Ole
• Geiger Derek

Classifications

• B64C27/80

  for differential adjustment of blade pitch between two or more lifting rotors · CPC title

• B64C27/463

  Blade tips · CPC title

• B64C27/008 Primary

  Rotors tracking or balancing devices · CPC title

• B64C27/10 Primary

  arranged coaxially · CPC title