Heading reference command and control algorithm systems and methods for aircraft turn-to-target maneuvers

• US 20070032923A1
• Filed: 08/05/2005
• Published: 02/08/2007
• Est. Priority Date: 08/05/2005
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Mossman, David, Butkiewicz, John
• Granted Patent: US 7,630,798 B2
• Time in Patent Office: Days
• US Class Current: 701/4
• CPC Class Codes: G05D 1/0858 specially adapted for vertical take-off of aircraft

Abstract

Systems and methods are provided for determining a final heading of a turning vehicle, such as a rotorcraft. The system may include an algorithm that calculates an advance prediction of a final heading that will be achieved after control input is terminated.

Claims

1. A computerized system that predicts a final attitude of a maneuvering aircraft, the system comprising:

a computer processor; and

an algorithm programmed into said computer processor and adapted to calculate, during a maneuver, a predicted final aircraft attitude based on aircraft parameters

wherein said algorithm includes calculations based upon model following control laws.

2. The computerized system of claim 1, wherein the algorithm further includes a plant canceller element.

3. The computerized system of claim 1, wherein the final attitude includes a final heading.

4. The computerized system of claim 1, wherein the final attitude includes a final pitch attitude.

5. The computerized system of claim 1, wherein the model following control laws are tailored to maintain aircraft angular acceleration within specified limits.

6. The computerized system of claim 5, wherein the specified limits include limits of angular acceleration about an aircraft yaw axis.

7. The computerized system of claim 1, wherein the model following control laws are tailored to maintain aircraft angular jerk within specified limits.

8. The computerized system of claim 7, wherein the specified limits include limits of angular jerk about an aircraft yaw axis.

9. The computerized system of claim 1, wherein the predicted final aircraft attitude is calculated using an exact solution algorithm.

10. The computerized system of claim 1, wherein the predicted final aircraft attitude is calculated using an iterative solution algorithm.

11. The computerized system of claim 1, wherein the predicted final aircraft attitude is calculated using an approximate solution algorithm.

12. A method of predicting a final attitude of a maneuvering aircraft, the method comprising:

providing a computer processor;

programming an algorithm into said computer processor to calculate a predicted final aircraft attitude based on aircraft parameters; and

calculating, during a maneuver, said predicted final aircraft attitude.

13. The method of claim 12, wherein the algorithm further includes a plant canceller element.

14. The method of claim 12, wherein the final attitude includes a final heading.

15. The method of claim 12, wherein the final attitude includes a final pitch attitude.

16. The method of claim 12, wherein the algorithm includes model following control laws that are tailored to maintain aircraft angular acceleration within specified limits.

17. The method of claim 12, wherein calculating the predicted final aircraft attitude includes using an exact solution algorithm.

18. The method of claim 12, wherein calculating the predicted final aircraft attitude includes using an iterative solution algorithm.

19. The method of claim 12, wherein calculating the predicted final aircraft attitude includes using an approximate solution algorithm.