MODEL BASED SENSOR SYSTEM FOR LOADS AWARE CONTROL LAWS

• US 20100017048A1
• Filed: 06/01/2007
• Published: 01/21/2010
• Est. Priority Date: 06/01/2007
• Status: Active Grant

• Current Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Original Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Inventors: Sahasrabudhe, Vineet, Faynberg, Alex
• Granted Patent: US 7,970,498 B2
• Time in Patent Office: Days
• US Class Current: 701/3
• CPC Class Codes: B64C 27/57 automatic or condition responsive, e.g. responsive to rotor speed, torque or thrust
• CPC Class Codes: G05D 1/0858 specially adapted for vertical take-off of aircraft

Abstract

A flight control system includes a model-based sensor system which estimates angular accelerations to control rotor system moment such that loads on the aircraft structure are reduced to thereby allow an aircraft structural envelope to more closely follow an aircraft service flight envelope.

Claims

1. A fly-by-wire flight control system comprising:

a system which estimates an angular acceleration of an aircraft flight control with at least one model and, data from at least one sensor to obtain an angular acceleration estimate; and

a flight control law in communication with said system to control a moment applied to the aircraft flight control using at least said angular acceleration estimate reduce a load applied to an aircraft.

2. The system as recited in claim 1, wherein said aircraft flight control includes a main rotor hub.

3. The system as recited in claim 2, wherein said system estimates angular pitch accelerations of said main rotor hub.

4. The system as recited in claim 2, wherein said system estimates angular roll accelerations of said main rotor hub.

5. The system as recited in claim 1, wherein said at least one model includes a rotor flapping model.

6. The system as recited in claim 5, wherein an output from said rotor flapping model is multiplied by a hub moment constant.

7. The system as recited in claim 1, wherein said aircraft flight control includes a cyclic control system.

8. The system as recited in claim 1, wherein said aircraft flight control includes a tail rotor.

9. The system as recited in claim 1, wherein said system includes an angular rate path and a stick input path which are calculated in parallel then combined through a complementary filter prior to input to said flight control law.

10. A method of flight control for a rotary-wing aircraft comprising:

estimating angular accelerations of an aircraft flight control using at least one model and data from at least one sensor to obtain an angular acceleration estimate; and

using at least said angular acceleration estimate, controlling a moment applied to said aircraft flight control to reduce a load applied to said aircraft.

11. A method as recited in claim 10, wherein said estimating further comprises:

performing a first estimation of acceleration from a stick input;

at least partially in parallel with performing a first estimation, performing a second estimation of angular acceleration from a rate; and

filtering through a high-pass filter the angular acceleration determined from the first estimation;

filtering through a low-pass filter the angular acceleration determined from the second estimation; and

combining results of said and filtering through a high pass filter and filtering through a low pass filter to obtain the angular accelerations of the aircraft flight control.

12. A method as recited in claim 11, wherein said performing a first, estimation further comprises:

communicating the stick input through a rotor flapping model to determine an estimate of rotor flapping; and

multiplying the estimate of rotor flapping by a rotor hub moment constant.

13. A method as recited in claim 10, wherein said estimating further comprises:

performing a first estimation a rotor system angular acceleration from a stick input;

at least partially in parallel with performing a first estimation, performing a second estimation of the rotor system angular acceleration from an angular rate; and

filtering through a high-pass filter the rotor system angular acceleration determined from the first estimation;

filtering through a low-pass filter the rotor system angular acceleration determined from the second estimation; and

combining results filtering through a high-pass filter and filtering through a low-pass filter to obtain the angular accelerations of the aircraft flight control.

14. A method as recited in claim 10, wherein said controlling further comprises:

controlling the moment applied to the aircraft flight control to limit a load applied to an aircraft structure of said aircraft.

15. A fly-by-wire flight control system implemented method of estimating angular acceleration of a rotary-wing aircraft rotor system comprising the steps of:

performing a first estimation of angular acceleration from a stick input;

performing a second estimation of angular acceleration from a rate; and

filtering the angular acceleration determined using the first estimation;

filtering the angular acceleration determined using the second estimation;

combining filtered results from said filtering the angular acceleration determined using the first estimation and said filtering the angular acceleration using the second estimate to obtain an estimate of the angular acceleration of the rotor system.

16. A method as recited in claim 15, wherein said performing a first estimation and said performing a second estimation are performed in parallel.

17. A method as recited in claim 15, wherein

filtering the angular acceleration determined using the first estimation further comprises filtering through a high-pass filter the angular acceleration determined, using the first estimation;

filtering the angular acceleration determined in using the second, estimation further comprises filtering through a low-pass filter the angular acceleration determined using the second estimation; and

combining;

further comprises combining results said filtering through a high-pass filter and said filtering through a low pass filter to obtain an estimate of the angular acceleration of the rotor system.

18. A method as recited in claim 15, wherein said performing a first estimation further comprises:

communicating the stick input through a rotor flapping model to determine an estimate of rotor flapping;

multiplying the estimate of rotor flapping by a rotor hub moment constant to obtain a hub moment estimate.

19. A method as recited in claim 18, wherein said performing a first estimation further comprises:

dividing the hub moment estimate by an inertia to obtain an angular acceleration.

20. A method as recited in claim 15, wherein said performing a second estimation further comprises:

communicating the rate through a differentiator to determine an acceleration estimate.