Aircraft panoramic display

• US 4,740,779 A
• Filed: 04/16/1986
• Issued: 04/26/1988
• Est. Priority Date: 04/16/1986
• Status: Expired due to Term

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Cleary, Patrick J., Gesell, Arnold G., Stewart, Warren P., Hopperstad, Craig A.
• Primary Examiner(s): NOT, DEFINED
• Application Number:
  US06/852,653
• Time in Patent Office: 741 Days
• Field of Search: 340/705, 340/974, 340/975, 340/976, 340/977, 340/979, 340/980, 340/717, 340/729, 340/734, 340/720, 364/433, 364/434, 364/435, 364/428, 358/87, 358/104
• US Class Current: 345/7
• CPC Class Codes: B64D 43/00 Arrangements or adaptations of instruments arrangements of cameras B64D47/08; aeronautical measuring instruments per se G01C

Abstract

A panoramic display system for an aircraft comprising a display screen and line generation means for generating a line image on the display screen. The position of the line image on the display screen corresponds to the position of a projection of an artifact external to the aircraft onto an imaginary window to an eye point within the aircraft. The eye point is positioned on the opposite side of the window from the artifact. The line image may be generated by determining the position of a great circle on a sphere having its center at the eye point, such that the position of the great circle corresponds to the artifact projected onto the sphere to the eye point. The position of the line image on the display screen corresponds to the position of the great circle on the sphere. The display system may comprise a plurality of display screens positioned adjacent to one another such that each can be viewed from a single viewing point. Partial line images are generated on each display screen such that the position of each partial line image corresponds to the position of the projection of the artifact onto a window portion to the eye point. The eye point is common to all window portions, and the spatial relationship of the window portions with respect to one another is congruent with the spatial relationship of the display screens with respect to one another.

Claims

1. A display system for use in an aircraft, the display system being adapted to receive signals representing the orientation of the aircraft and to produce a corresponding display, the display system comprising:

a nonspherical display screen; and

line generation means for generating a line image on the nonspherical display screen such that the position of the line image on the display screen corresponds to the position of a projection of a three-dimensional artifact external to the aircraft onto an imaginary window to an eye point within the aircraft, the eye point being positioned on the opposite side of the window from the artifact, wherein the line generation means includes means for determining the position of a great circle on a sphere having its center at the eye point such that the position of the great circle on the sphere corresponds to the artifact projected onto the sphere to the eye point, and means for generating the line image on the display screen such that the position of the line image on the nonspherical display screen corresponds to the position of the great circle on the sphere.

2. The display system of claim 1, wherein the means for determining the position of the great circle comprises means for determining the position of an intersection point between the great circle and an equator on the sphere, the equator being defined as the line of intersection between the sphere and a plane that passes through the eye point and that is horizontal with respect to the aircraft.

3. The display system of claim 2, wherein the means for determining the position of the great circle further comprises means for determining the spherical angle between the great circle and the equator at the intersection point.

4. The display system of claim 1, wherein the window is a segment of the surface of a cylinder having an axis oriented vertically with respect to the aircraft.

5. The display system of claim 4, wherein the axis of the cylinder passes through the eye point, and wherein the radius of the cylinder is equal to the distance between the eye point and the window.

6. The display system of claim 5, wherein the window includes a longitude direction normal to said axis of the cylinder, and a latitude direction parallel to said axis of the cylinder, the window having a greater angular extent in the longitude direction than in the latitude direction.

7. The display system of claim 6, wherein the line generation means includes means for determining the position of a great circle on a sphere having its center at the eye point such that the position of the great circle on the sphere corresponds to the artifact projected onto the sphere to the eye point, and means for generating the line image such that the position of the line image on the display screen corresponds to the position of the great circle on the sphere.

8. The display system of claim 7, wherein the line generation means further includes means for projecting the great circle from the sphere onto the cylinder in a direction away from the eye point to determine the position of the line image on the display screen.

9. The display system of claim 8, wherein the means for determining the position of the great circle comprises means for determining the position of an intersection point between the great circle and an equator on the sphere, the equator being defined as the line of intersection between the sphere and a plane that passes through the eye point and is horizontal with respect to the aircraft.

10. The display system of claim 9, wherein the means for determining the position of the great circle further comprises means for determining the spherical angle between the great circle and the equator at the intersection point.

11. The display system of claim 1, comprising a plurality of display screens positioned approximately adjacent to one another, such that each display screen can be viewed from a single viewing point, and wherein the line generation means includes means for generating a partial line image on each display screen such that the position of each partial line image on its associated display screen corresponds to the position of the projection of the artifact onto a window portion to the eye point, such that the eye point is common to all window portions and such that the spatial relationship of the window portions with respect to one another is congruent with the spatial relationship of the display screens with respect to one another.

12. The display system of claim 11, wherein each display screen is positioned such that a line normal to a portion of the display screen passes approximately through the eye point.

13. The display system of claim 12, wherein the window portions comprise laterally adjacent segments of the surface of a cylinder having an axis oriented vertically with respect to the aircraft.

14. The display system of claim 13, wherein the axis of the cylinder passes through the eye point, and wherein the radius of the cylinder is equal to the distance between the eye point and each window portion.

15. The display system of claim 14, wherein each window portion includes a longitude direction normal to said axis of the cylinder, and a latitude direction parallel to said axis of the cylinder, the window portions being aligned side-by-side with respect to one another along a common longitude direction.

16. The display system of claim 15, wherein the line generation means includes means for determining the position of a great circle on a sphere having its center at the eye point such that the position of the great circle on the sphere corresponds to the artifact projected onto the sphere to the eye point, and means for generating the partial line images such that the position of each partial line image on its associated display screen corresponds to the position of the great circle on the sphere.

17. The display system of claim 16, wherein the line generation means further includes means for projecting the great circle from the sphere onto the cylinder in a direction away from the eye point to determine the position of the partial line images on each display screen.

18. The display system of claim 17, wherein the means for determining the position of the great circle comprises means for determining the position of an intersection point between the great circle and an equator on the sphere, the equator being defined as the line of intersection between the sphere and a plane that passes through the eye point and is horizontal with respect to the aircraft.

19. The display system of claim 18, wherein the means for determining the position of the great circle further comprises means for determining the spherical angle between the great circle and the equator at the intersection point.

20. The display system of claim 19, wherein the line generation means comprises a master processor, a plurality of display processors, one display processor being associated with each display screen, and communication means for transmitting data from the master processor to the display processors, the master processor being operative to periodically determine the position of the intersection point and the spherical angle, and to periodically transmit data specifying the intersection point and spherical angle to each display processor, each display processor being operative to receive said data and to periodically generate the partial line image corresponding to the range of longitude positions associated with that display screen.

21. The display system of claim 1, 11, or 21, wherein the artifact comprises a straight line forward of the aircraft in a position approximately corresponding to the position of the actual horizon as viewed from the aircraft.

22. The display system of claims 1, 11, or 20, wherein the artifact comprises a pair of straight lines defining the lateral boundaries of a planar strip, the planar strip having a constant altitude and extending forwardly from the position of the aircraft.

23. The display system of claim 22, wherein the altitude of the planar strip can be any one of a discrete number of altitude values, and wherein the altitude values selected at a given time is the smallest altitude value having a latitude greater than the current altitude of the aircraft.

24. The display system of claim 23, where the artifact comprises a first pair of straight lines corresponding to the lateral edges of a first planar strip and a second pair of straight lines corresponding to the lateral edges of a second planar strip, the first and second planar strips being parallel to one another, each planar strip having a constant altitude and extending forwardly from the aircraft position away from the aircraft, wherein each planar strip can take on any one of a discrete number of altitude values, the altitude value of the first planar strip being the smallest of said discrete values greater than the current aircraft altitude, and the altitude value of the second planar strip being the largest of said discrete values less than the current aircraft altitude.