Synthetic vision automatic landing system

• US 5,593,114 A
• Filed: 04/19/1994
• Issued: 01/14/1997
• Est. Priority Date: 04/19/1994
• Status: Expired due to Term

• Current Assignee: Mcdonnell Douglas Corporation (The Boeing Co.)
• Original Assignee: Mcdonnell Douglas Corporation (The Boeing Co.)
• Inventors: Ruhl, Louis F.
• Primary Examiner(s): BAREFOOT, GALEN L
• Application Number:
  US08/229,655
• Time in Patent Office: 1,001 Days
• Field of Search: 244/76 R, 244/1 R, 244/183, 244/185, 244/186, 244/187, 244/188, 244/194, 244/195, 304/407.1, 342/176
• US Class Current: 244/183
• CPC Class Codes: G05D 1/0676 specially adapted for landing

Abstract

A system is provided which permits a display of ground conditions to the pilot through the use of a forward looking sensor set and uses signals generated from the aircraft to simulate ground aid signals which are used for automatic landing of the aircraft. General flight path angle and course aim point corrections are made from the cockpit of the aircraft and are adjustable as the flight progresses. Most of the systems today that have fixed path capability to ground intercepts are based on ground installed equipment. This system can establish the inertial flight path track internally to the aircraft and provides an automatic landing system which allows the pilot to concentrate on the visibility of the forward scene to confirm the safe progress of the landing.

Claims

1. An aircraft automatic landing system capable of utilizing ground based ILS input signals input to said landing system adapted for use without ground based ILS signals, comprising:

a. a computer,

b. a display device coupled to said computer,

c. a vector cursor generated by said computer for displaying aircraft vector information on said display device,

d. an on-board forward looking sensor set coupled to said computer for detecting environmental information forward of said aircraft having an output for transmitting the information received from the sensor set to the computer for display on the display device,

f. at least one reference cursor, selectively movable with respect to said display, displayed on said display,

g. a cursor control for selecting the position of said reference cursor on the display,

h. a computing unit for computing the difference in position between the vector cursor and the reference cursor and generating difference information,

i. a converter for converting the difference information into a signal suitable for input to the automatic landing system, and

j. an interface for applying said signal to the input of the automatic landing system.

2. An aircraft automatic landing system as set forth in claim 1, wherein the computing unit;

the converter and the interface, are included on a controller which includes;

a. a computing apparatus adapted for computing the difference in position between said reference cursor and vector cursor,

b. a converter for converting the difference in position to a signal, and

c. a port to the automatic landing system coupled to said converter for receiving and applying said ILS signal the ILS input of the automatic landing system.

3. An automatic landing system as set forth in claim 2 wherein said computing unit and said converter include instructions applied to said controller for performing the following steps:

a. computing the difference in lateral and vertical position between the vector cursor and the reference cursor,

b. generating at least one lateral position signal based on the lateral difference,

c. inputing said lateral position signal to the input of the automatic landing system,

d. generating at least one vertical position signal based on the vertical difference, and

e. inputing said vertical position signal to at least one input of the automatic landing system.

4. An automatic landing system as set forth in claim 2 wherein said computing unit and said converting unit include instructions applied to said computing unit for performing the following steps:

a. computing the relative difference in lateral and vertical position between the vector cursor and the reference cursor on the display device,

b. generating at least one lateral position error from the lateral difference,

c. inputing said lateral position error to at least one input of the on-board automatic landing system,

d. generating at least one vertical position error from the vertical difference, and

e. input of said vertical position error to at least one input of the on-board automatic landing system.

5. An automatic landing system as set forth in claim 1 wherein the cursor control comprises:

a. at least one control mechanism for adjustment of the lateral position of the reference cursor,

b. at least one control mechanism for adjustment of the vertical position of the reference cursor, and

c. at least one control mechanism for adjustment of the shape of the reference cursor for the alignment thereof along a centerline.

6. An automatic landing system as set forth in claim 1 further comprising a reference cursor which comprises:

a. an elongated central axis which may be selectively adjusted to any angular position relative to the vertical,

b. a horizontal portion which is parallel with the horizon, and

c. a central portion having cross-hair which may be selectively centered on any point on the display.

7. An aircraft automatic landing system capable of utilizing ground based ILS input signals adapted for use without ground based ILS signals comprising:

a. a computer,

b. a display device coupled to said computer,

c. a vector cursor generated by said computer for displaying aircraft vector information on said display device,

d. an on-board forward looking sensor set coupled to said computer for detecting environmental information forward of said aircraft having an output for transmitting the information received from the sensor set to the computer for display on the display device,

f. at least one reference cursor, selectively movable with respect to said display, displayed on said display,

g. a cursor control for selecting the position of a reference cursor on the display,

h. means for computing the difference in position between the vector cursor and the reference cursor and generating difference information, and

i. means for converting the difference information into a signal suitable for input to the automatic landing system, said means having an output adapted for applying the error signals to the input of the automatic landing system.

8. An aircraft automatic landing system as set forth in claim 7, wherein the means for computing the difference in position between the vector cursor and the reference cursor, is a controller which includes

a. a computing apparatus adapted for computing the difference between said reference cursor and vector cursor, and

b. an interface to the automatic landing system computer coupled to said controller.

9. An automatic landing system as set forth in claim 8 wherein said means for computing and said means for converting further comprise computer instructions applied to said computing apparatus for performing the following:

a. computing the difference in lateral and vertical position between the vector cursor and the reference cursor,

b. generating at least one lateral position error from the lateral difference,

c. inputing said lateral position error to at least one input of the automatic landing system,

d. generating at least one vertical position error from the vertical difference,

e. converting said position errors into ILS error information, and

f. input of said vertical position error to at least one input of the automatic landing system.

10. An automatic landing system as set forth in claim 8 wherein said means for computing and said means for converting further comprises instructions applied to said computing unit for:

a. computing the difference in lateral and vertical position between the vector cursor and the reference cursor,

b. generating at least one lateral position error from the lateral difference,

c. inputing said lateral position error to at least one input of the on-board automatic landing system,

d. generating at least one vertical position error from the vertical difference,

e. converting the position errors into ILS information, and

f. inputing of said ILS information to at least one input of the on-board automatic landing system.

11. An automatic landing system as set forth in claim 7 wherein the reference cursor control comprises:

a. a control mechanism for adjustment of the lateral position of the reference cursor,

b. a control mechanism for adjustment of the vertical position of the reference cursor, and

c. a control mechanism for adjustment of the shape of the reference cursor.

12. An automatic landing system as set forth in claim 7 wherein the reference cursor control further comprises:

a. a first thumb wheel which operates the lateral position control mechanism,

b. a second thumb wheel which operates the vertical position control mechanism, and

c. a rotatable knob for operation of the reference cursor centerline adjustment control mechanism.

13. An automatic landing system as set forth in claim 7 wherein said reference cursor further comprises:

a. an elongated central axis which may be selectively aligned along a runway centerline,

b. a horizontal portion which remains parallel with the horizon, and

c. a central portion having cross-hair for centering of said reference cursor on a desired point on said display.

14. An aircraft automatic landing system capable of utilizing ground based ILS input signals adapted for use without ground based ILS signals, comprising

a. a computer

b. a display device coupled to said computer

c. a vector cursor generated by said computer for displaying aircraft vector information on said display device,

d. an on-board forward looking sensor set coupled to said computer for detecting environmental information forward of said aircraft, having an output for transmitting the information received from the sensor set to the computer for display on the display device,

f. at least one reference cursor, selectively movable with respect to said display, displayed on said display,

g. a cursor control for setting the position of a reference cursor on the display which comprises:

at least one control mechanism for adjustment of the lateral position of the reference cursor, at least one control mechanism for adjustment of the vertical position of the reference cursor, and at least one control mechanism for adjustment of the shape of the reference cursor for alignment along a line, and

h. a computer coupled to said display and said automatic landing system programmed to;

i. compute the difference in lateral and vertical position between the vector cursor and the reference cursor,

ii. generate at least one lateral position error from the lateral difference,

iii. input said lateral position error to at least one input of the on-board automatic landing system,

iv. generate at least one vertical position error from the vertical difference, and

v. input of said vertical position error to at least one input of the on-board automatic landing system.

15. An aircraft automatic landing system as set forth in claim 14, wherein the computer, is a controller which includes

a. a computing apparatus adapted for computing the difference between said reference cursor and vector cursor information, and

b. an interface coupling said computing apparatus to the automatic landing system computer.

16. An automatic landing system as set forth in claim 14 wherein the reference cursor control comprises:

a. a joystick coupled to the computer.

17. An automatic landing system as set forth in claim 14 wherein said reference cursor further comprises:

a. an elongated central axis which may be aligned along a runway centerline,

b. a horizontal portion which is parallel with the horizon, and

c. a central portion having cross-hair which may be centered on an aim point.

18. An aircraft automatic landing system capable of utilizing ground based ILS input signals adapted for use without ground based ILS signals comprising

a. an on-board computer

b. a display device coupled to said computer,

c. a vector cursor generated by said computer for displaying aircraft vector information on said display device,

d. an on-board forward looking sensor set coupled to said computer for detecting environmental information forward of said aircraft, having an output for transmitting the information received by the sensor set to the computer for display on the display device,

f. at least one reference cursor, selectively movable with respect to said display, displayed on said display,

g. a cursor control for selecting the position of a reference cursor on the display,

h. means for computing the difference in position between the vector cursor and the reference cursor and generating difference information,

i. means for converting the difference information into an ILS error signal suitable for input to the automatic landing system computer, and

j. an output coupled to said converting means for applying the error signals to the ILS input of the automatic landing system.

19. An aircraft automatic landing system as set forth in claim 18, wherein the means for computing the difference in position between the vector cursor and the reference cursor, is a controller which further comprises:

a. a computing unit adapted for computing the difference between said reference cursor position and the vector cursor position, and

b. an interface to the automatic landing system computer for coupling said differences to said automatic landing system.

20. An automatic landing system as set forth in claim 19 wherein said means for computing and said means for converting comprise computer instructions applied to said computing unit for performing the following:

a. computing the difference in lateral and vertical position between the vector cursor and the reference cursor,

b. generating at least one lateral position error from the lateral difference,

c. inputing said lateral position error to at least one input of the on-board automatic landing system,

d. generating at least one vertical position error from the vertical difference, and

e. input of said vertical position error to the input of the on-board automatic landing system.

21. An automatic landing system as set forth in claim 19 wherein said means for computing and said means for converting comprise computer instructions applied to said computing unit for performing the following:

a. computing the difference in lateral and vertical position between the vector cursor and the reference cursor,

b. generating at least one lateral position error from the lateral difference,

c. inputing said lateral position error to at least one input of the on-board automatic landing system,

d. generating at least one vertical position error from the vertical difference, and

e. inputing of said vertical position error to at least one input of the on-board automatic landing system.

22. An automatic landing system as set forth in claim 18 wherein the reference cursor control comprises:

a. at least one control mechanism for adjustment of the lateral position of the reference cursor,

b. at least one control mechanism for adjustment of the vertical position of the reference cursor, and

c. at least one control mechanism for adjustment of the shape of the reference cursor for alignment along a selected reference cursor centerline.

23. An automatic landing system as set forth in claim 18 wherein the reference cursor control further comprises:

a. a single joy stick which operates the lateral and vertical position control mechanism, and

b. a knob for rotational operation of the centerline adjustment control mechanism.

24. An automatic landing system as set forth in claim 18 wherein the controller further comprises:

a selection switch adapted for setting the glidepath angle during approach for coupling an angular glidepath error signal to said automatic landing computer.