Apparatuses and methods for displaying and receiving tactical and strategic flight guidance information

• US 8,005,582 B2
• Filed: 12/01/2009
• Issued: 08/23/2011
• Est. Priority Date: 12/24/2003
• Status: Expired due to Fees

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Gunn, Peter D., Mumaw, Randall J., Griffin, John C. III, Boorman, Daniel J.
• Primary Examiner(s): ARTHUR JEANGLAUDE, GERTRUDE
• Application Number:
  US12/629,007
• Publication Number:
  US 20100076627A1
• Time in Patent Office: 630 Days
• Field of Search: 701/3, 701/4, 701/11, 701 14- 16, 244/75.1, 340/945, 340/971, 340/980
• US Class Current: 701/3
• CPC Class Codes: G01C 23/00 Combined instruments indicating more than one navigational value, e.g. for aircraft; Combined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration
• CPC Class Codes: G08G 5/0021 located in the aircraft
• CPC Class Codes: G08G 5/0052 for cruising combined instruments indicating more than one navigational value G01C23/00

Abstract

Methods and apparatuses for displaying and receiving tactical and strategic flight guidance information are disclosed. A method in accordance with one aspect of the invention includes displaying at least one first indicator to an operator of the aircraft, with a first indicator corresponding to a first instruction input by the operator for directing a first aircraft behavior and implemented upon receiving an activation instruction from the operator. At least one second indicator corresponding to a second instruction for directing a second aircraft behavior at least proximately the same as the first aircraft behavior is displayed, with the at least one second instruction to be automatically implemented at a future time. The at least one second indicator is at least approximately the same as the at least one first indicator. Indicators can be hierarchically organized to simplify presentation and reduce pilot training time.

Claims

1. An aircraft system including a computer-readable medium having contents that perform a method, comprising:

receiving an input corresponding to an instruction for directing an aircraft to a target position above or below its current position; and

automatically directing the aircraft to the target position by;

automatically controlling a first force on the aircraft by directing one of either a) a pitch axis control device or b) a thrust axis control device; and

automatically controlling a second force on the aircraft by directing the other of either a) the pitch axis control device or b) the thrust axis control device.

2. The system of claim 1 wherein the contents of the computer-readable medium are configured to automatically direct one of an aircraft elevator, an aircraft engine and an aircraft speed brake.

3. The system of claim 1, further comprising a computer having an least one input device to receive the input.

4. The system of claim 1 wherein a receiver portion receives the input.

5. The system of claim 1, further comprising:

the aircraft; and

a computer having an least one input device to receive the input.

6. The system of claim 1, wherein the contents of the computer-readable medium are configured to perform the following processes:

when a requested rate of altitude change is above a threshold value, automatically controlling a speed of the aircraft by directing an elevator of the aircraft and automatically controlling a rate of altitude change of the aircraft by controlling engine thrust; and

when a requested rate of altitude change is below the threshold value, automatically controlling a speed of the aircraft by controlling engine thrust and automatically controlling a rate of altitude change of the aircraft by directing an elevator of the aircraft.

7. The system of claim 1 wherein the computer-readable medium includes a special-purpose computer specifically programmed with instructions to perform the receiving and directing functions.

8. The system of claim 1 wherein receiving an input is performed by a special-purpose computer specifically programmed with instructions to perform the receiving function.

9. The system of claim 1 wherein directing the aircraft is performed by a special-purpose computer specifically programmed with instructions to perform the directing function.

10. The system of claim 1 wherein automatically controlling the first force is automatically performed by one of a pitch control system and an engine control system, and wherein automatically controlling the second force is automatically performed by the other of the pitch control system and the engine control system.

11. The system of claim 1 wherein the computer-readable medium:

displays a first indicator corresponding to the first force;

displays a second indicator corresponding to the second force;

displays a longitudinal target and a vertical target;

displays a first control link indicating whether the first force is being used to control to the longitudinal target or the vertical target; and

displays a second control link indicating whether the second force is being used to control to the longitudinal target or the vertical target.

12. The system of claim 11 wherein the first indicator is an indicator of thrust and the second indicator is an indicator of pitch.

13. The system of claim 11 wherein:

the first indicator is a textual indicator corresponding to thrust;

the second indicator is a textual indicator corresponding to pitch;

the longitudinal target is a textual indicator corresponding to longitudinal speed;

the vertical target is a textual indicator corresponding to vertical rate;

the first control link includes a first line and arrowhead; and

the second control link includes a second line and arrowhead.

14. A computer-implemented method for controlling an aircraft, comprising:

receiving an input corresponding to an instruction for directing the aircraft to a target position above or below its current position; and

automatically directing the aircraft to the target position by;

automatically controlling a first force on the aircraft by directing one of either a) a pitch axis control device or b) a thrust axis control device; and

automatically controlling a second force on the aircraft by directing the other of either a) the pitch axis control device or b) the thrust axis control device.

15. The method of claim 14 wherein automatically directing the aircraft further comprises automatically directing one of an aircraft elevator, an aircraft engine and an aircraft speed brake.

16. The method of claim 14, further comprising:

when a requested rate of altitude change is above a threshold value, automatically controlling a speed of the aircraft by directing an elevator of the aircraft and automatically controlling a rate of altitude change of the aircraft by controlling engine thrust; and

when a requested rate of altitude change is below the threshold value, automatically controlling a speed of the aircraft by controlling engine thrust and automatically controlling a rate of altitude change of the aircraft by directing an elevator of the aircraft.

17. The method of claim 14 wherein automatically controlling the first force is automatically performed by one of a pitch control system and an engine control system, and wherein automatically controlling the second force is automatically performed by the other of the pitch control system and the engine control system.

18. The method of claim 14, further comprising:

displaying a first indicator corresponding to the first force;

displaying a second indicator corresponding to the second force;

displaying a longitudinal target and a vertical target;

displaying a first control link indicating whether the first force is being used to control to the longitudinal target or the vertical target; and

displaying a second control link indicating whether the second force is being used to control to the longitudinal target or the vertical target.

19. The method of claim 18 wherein the first indicator is an indicator of thrust and the second indicator is an indicator of pitch.

20. The method of claim 18 wherein:

the first indicator is a textual indicator corresponding to thrust;

the second indicator is a textual indicator corresponding to pitch;

the longitudinal target is a textual indicator corresponding to longitudinal speed;

the vertical target is a textual indicator corresponding to vertical rate;

the first control link includes a first line and arrowhead; and

the second control link includes a second line and arrowhead.