Flight control system having a three control loop design

• US 8,473,124 B2
• Filed: 11/08/2005
• Issued: 06/25/2013
• Est. Priority Date: 11/08/2004
• Status: Active Grant

• Current Assignee: Textron Innovations Incorporated (Textron Inc)
• Original Assignee: Textron Innovations Incorporated (Textron Inc)
• Inventors: Shue, Shyhpyng Jack, Shillings, John J.
• Primary Examiner(s): MANCHO, RONNIE M
• Application Number:
  US11/665,138
• Publication Number:
  US 20080097658A1
• Time in Patent Office: 2,786 Days
• Field of Search: 701/24, 701/11, 701/13, 701/4, 701/23, 701/3, 701/12, 395/22, 395/21, 244/158.R, 244/164, 244/176, 607/91, 60/39, 318/560, 318/434, 700/29, 700/44, 700/90
• US Class Current: 701/4
• CPC Class Codes: G05D 1/101 specially adapted for aircraft

Abstract

A flight control system is configured for controlling the flight of an aircraft utilizing a three control loop design to robustly increase system performance. An inner loop comprises an improved linear quadratic regulator (LQR) search method, and an outer loop comprises a classic feedback summary gain design. A third loop comprises a steady state trim search method.

Claims

1. A flight control system for controlling the flight of an aircraft, the system comprising:

an inner loop configured to stabilize the flight control system, the inner loop having;

a control law;

wherein the control law is separated into flow paths for a longitudinal component and a lateral component;

wherein the longitudinal component includes a longitudinal motion input that passes to a longitudinal linear quadratic regulator and a first gain scheduling block, the lateral component includes a lateral motion input that passes to a lateral linear quadratic regulator and a second gain scheduling block; and

wherein an output from the first gain scheduling block and an output from the second gain scheduling block are regrouped;

an outer control loop utilizing a summary gain design to shorten a gain selection; and

a steady state trim loop configured to automatically catch the trim flight of the aircraft.

2. The flight control system of claim 1, wherein the inner loop achieves stabilization through use of an optimal phase margin and gain margin.

3. The flight control system of claim 1, wherein the inner loop achieves stabilization through use of an optimal phase margin and gain margin and wherein the inner loop utilizes an algorithm based on eigenvalue, eigenvector, and dampening ratio from time to determine the optimal phase margin and gain margin.

4. The flight control system of claim 1, wherein the outer control loop automatically holds lateral path guidance in a heading select mode.

5. The flight control system of claim 4, wherein the inner control loop, the outer control loop, and the steady state trim loop are pre-programmed.

6. The flight control system of claim 1, wherein the steady state trim loop automatically searches for an optimal trim condition at any flight conditions.

7. The flight control system of claim 6, wherein the steady state trim loop searches for the optimal trim condition based on altitude rate.

8. The flight control system of claim 6, wherein the steady state trim loop searches for the optimal trim condition based on roll rate.

9. The flight control system of claim 6, wherein the steady state trim loop searches for the optimal trim condition based on yaw rate.

10. The flight control system of claim 6, wherein the steady state trim loop utilizes a linear quadratic regulator method with a command generator to determine the optimal trim condition.

11. The flight control system of claim 6, wherein the steady state trim loop utilizes a linear quadratic regulator method with a command generator to determine the optimal trim condition, the command generator comprising a steady state trim value with an initial trim condition.

12. The flight control system of claim 6, wherein the steady state trim loop utilizes a linear quadratic regulator method with a command generator to determine the optimal trim condition, the command generator comprising a steady state trim value with an initial trim condition;

and

wherein a difference between a current flight state, the steady state trim value, and the initial trim condition is set as a tracking error.

13. The flight control system of claim 1, wherein a lateral heading is automatically engaged when a landing approach is missed.

14. A method for controlling the flight of an aircraft, the method comprising:

separating a flight control law into flow paths for a longitudinal component and a lateral component;

passing a longitudinal motion input of the longitudinal component through a longitudinal linear quadratic regulator and a first gain scheduling block;

passing a lateral motion input of the lateral component through a lateral linear quadratic regulator and a second gain scheduling block;

regrouping an output from the first gain scheduling block with that of an output of the second gain scheduling block;

shortening a gain selection with an outer loop utilizing a summary gain design; and

obtaining a trim flight of the aircraft with a steady state trim loop.