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

• US 7,630,798 B2
• Filed: 08/05/2005
• Issued: 12/08/2009
• Est. Priority Date: 08/05/2005
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Butkiewicz, John D., Mossman, David C.
• Primary Examiner(s): Tran; Dalena
• Application Number:
  US11/197,977
• Publication Number:
  US 20070032923A1
• Time in Patent Office: 1,586 Days
• Field of Search: 701/15, 701/16, 701/120, 701/300, 701/301, 701/4, 340/945, 340/961, 340/971, 342/29, 342/30, 342/32, 342 36- 38
• 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 continuously predicts a final aircraft state of a maneuvering aircraft provided a control input of the aircraft is at least one of released and relaxed, the system comprising:

a computer processor;

and an algorithm programmed into said computer processor and adapted to calculate, during a maneuver, the predicted final aircraft state based on a mathematical command model, which comprises a basic heading and yaw rate response, comprising at least one of a desired final heading and a desired final pitch attitude, at least a first three derivatives of at least one of the desired final heading and the desired final pitch attitude, limiting values for each of the at least first three derivatives, closed loop algorithms, a plant canceller element, and a control input for at least one of the desired final heading and the desired final pitch attitude.

2. The computerized system of claim 1, wherein the basic heading and the yaw rate response comprise both the desired final heading and the desired final pitch attitude.

3. The computerized system of claim 1, wherein the mathematical command model is tailored to maintain aircraft angular acceleration within specified limits.

4. The computerized system of claim 3, wherein the specified limits include limits of angular acceleration about an aircraft yaw axis.

5. The computerized system of claim 1, wherein the mathematical command model is tailored to maintain aircraft angular jerk within specified limits.

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

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

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

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

10. A method of continually predicting a final aircraft state of a maneuvering aircraft provided a control input is at least one of released and relaxed, the method comprising:

providing a computer processor;

programming an algorithm which includes a mathematical command model, comprising a basic heading and yaw rate response, which comprises at least one of a desired final heading and a desired final pitch attitude, at least a first three derivatives of each of at least one of the desired final heading and the desired final pitch attitude limiting values for each of the at least first three derivatives, closed loop algorithms, a plant canceller element, and at least one control input for at least one of the desired final heading and the desired final pitch attitude; and

calculating, during a maneuver, said predicted final aircraft state using said algorithm.

11. The method of claim 10, wherein the basic heading and the yaw rate response comprise both the desired final heading and the desired final pitch attitude.

12. The method of claim 10, wherein the mathematical command model is tailored to maintain aircraft angular acceleration within specified limits.

13. The method of claim 10, wherein calculating the predicted final aircraft state includes using an exact solution algorithm.

14. The method of claim 10, wherein calculating the predicted final aircraft state includes using an iterative solution algorithm.

15. The method of claim 10, wherein calculating the predicted final aircraft state includes using an approximate solution algorithm.