Concave quadratic aircraft attitude reference display system

• US 4,305,057 A
• Filed: 07/19/1979
• Issued: 12/08/1981
• Est. Priority Date: 07/19/1979
• Status: Expired due to Term

• Current Assignee: Mcdonnell Douglas Corporation (The Boeing Co.)
• Original Assignee: Mcdonnell Douglas Corporation (The Boeing Co.)
• Inventors: Rolston, David R.
• Primary Examiner(s): Groody, James J.
• Application Number:
  US06/059,273
• Time in Patent Office: 873 Days
• Field of Search: 340/27 R, 340/27 AT, 340/27 NA, 340/721, 340/724, 340/734, 340/747, 340/750, 340/705, 340/723, 244/179-182, 244/194, 244/186, 364/424, 364/427, 364/428, 364/430, 364/433-435, 434/38, 434/40, 434/43, 434/44, 73/178 R, 73/178 T, 35/12 F, 35/12 N
• US Class Current: 340/974
• CPC Class Codes: G01C 23/005 Flight directors indicating arrangements specially adapted for rotary gyroscopes G01C19/32

Abstract

A Heads-Up Display system which displays an attitude reference to pilots in order to provide a reference display system as a primary flight instrument. The Heads-up Display system uses a pitch ladder system based on Euler angle data which eliminates the erratic motion or "flip-flop" of the typical pitch ladder which is inherent and unavoidable when pitching near plus or minus 90°, by utilizing a flexible graphics display which presents the pilot with a heads-up view as if he were located inside and at the center of an imaginary sphere which has heading and pitch angle information marked on its inner surface. The display of appropriately curved bars as opposed to a straight bar pitch ladder for attitude reference more realistically depicts to the pilot the aircraft situation relative to the outside world. This presentation is more easily and more reliably interpreted by the pilot and simplifies the recognition and recovery from unusual attitudes. In addition, ground track, yaw rate, turn rate information is available over the entire HUD field-of-view, thus there is no need for the pilot to redirect his attention away from his primary point of interest, the velocity vector, to obtain heading and track information. Appropriate equations are evaluated to obtain line-of-sight angles from the aircraft longitudinal axis to the desired pitch and heading points on the pitch ladder display. Such equations are solved by computer techniques for a sufficient number of intersecting points to complete the display and the graphics hardware connects the points to form the segments of the pitch ladder which represent the imaginary lines on the sphere and displays the same in the pilot'"'"'s field-of-view.

Claims

1. A graphics display system for displaying aircraft flight information comprising:

a. a screen for displaying graphic data,

b. an optical system for transmitting an image of said screen display to a position within a field of view of a pilot of the aircraft,

c. means for sensing a pitch angle of said aircraft and generating a signal indicative of said pitch angle,

d. means for selecting a pitch ladder bar display sequence based on said pitch angle signal,

e. means for generating said pitch ladder bar display sequence such that each pitch ladder bar possesses a generally different radius of curvature, and

f. means for displaying said generated pitch ladder bar display sequence on said screen.

2. A display system as described in claim 1 further comprising:

a. means for sensing aircraft heading and generating a signal indicative of aircraft heading, and

b. means for displaying aircraft heading data on said screen superimposed on some of said displayed pitch ladder bars, said data based on said heading signal.

3. A display system as described in claim 2 wherein the radius of curvature of said pitch ladder bars decreases as the absolute value of pitch angle increases.

4. A display system as described in claim 3 wherein the radius of curvature of the 0°

pitch ladder bar is infinite and the pitch ladder bar displayed for plus or minus 90°

pitch is a closed figure.

5. A display system as described in claim 4 further comprising:

a. means for sensing aircraft roll and generating a signal indicative of the magnitude of roll,

b. means for generating a curved scale having roll angle indicia disposed thereon,

c. means for generating a bank symbol on the scale indicating the angle of bank, said position of said symbol based on said roll signal, and

d. means for displaying said scale and said symbol on said screen.

6. A display system as described in claim 5 further comprising:

a. means for inhibiting display of said symbol for roll angles greater than 30°

.

7. A display system as described in claim 6 further comprising:

a. means for rotating the pitch ladder bar display through an angle equivalent to roll angle responsive to said roll signal.

8. A display system as described in claim 7 further comprising:

a. means for sensing aircraft speed and direction, and generating signals indicative thereof,

b. means for displaying the magnitude of said speed, and

c. means for displaying the direction of said aircraft relative to heading and pitch displays.

9. A display system as described in claim 8 further comprising:

a. means for displaying numerical data as indicia of altitude based on aircraft altitude sensor.

10. A display system as described in claim 9 further comprising:

a. means for labeling heading indicia on said pitch ladder bars at pre-determined intervals, and

b. means for selecting said intervals based on said pitch angle signal.

11. A display system as described in claim 10 wherein said selecting means selects heading intervals proportional to pitch angle.

12. A display system as described in claim 11 wherein said intervals are selected as follows:

a. for pitch angles greater than ⊥

75°

⊥

said selection means selects an interval of 30°

,

b. for pitch angles greater than ⊥

70°

⊥

but less than or equal to ⊥

75°

⊥

said selection means selects an interval of 15°

,

c. for pitch angles greater than ⊥

30°

⊥

but less than or equal to ⊥

70°

⊥

said selection means selects an interval of 10°

, and

d. for pitch angles of ⊥

30°

⊥

or less said selection means selects an interval of 5°

.

13. A display system as described in claim 11 wherein said means for selecting a pitch ladder bar display sequence is a portion of a computer program comprising:

a. means for comparing the screen field of view angle with the pitch angle,

b. means for incrementally reducing the pitch angle until the angle of pitch is within the screen field of view, and

c. means for storing the original value of the pitch angle.

14. A display system as described in claim 13 wherein said means for generating said pitch ladder bar sequence is a portion of a computer program comprising:

a. means for generating a plurality of intersection points of heading and pitch on the inner surface of a reference sphere as though the aircraft was positioned at the center of said sphere, and

b. means for converting such intersection points to display points for display on said screen.

15. A display system as described in claim 14 further comprising:

a. means for interconnecting said points.

16. A graphics display system for displaying aircraft attitude information comprising:

a. screen for displaying graphic data,

b. an optical system for coupling an image of said displayed graphic data to a position within a field of view of a pilot of the aircraft,

c. means for detecting a pitch angle of said aircraft and generating a signal proportional thereto,

d. means for selecting a plurality of pitch ladder bars for display based on said pitch angle signal,

e. means for generating said pitch ladder bar display, each of said pitch ladders comprising a plurality of coordinate points interconnected by straight line segments, said segments having different slopes for different pitch angles, and

f. a means for displaying said generated pitch ladder bar display on said screen.

17. A display system as described in claim 16 further comprising:

a. means for detecting aircraft heading information and generating a signal proportional thereto, and

b. means for displaying aircraft heading information as graphic data on said screen superimposed on some of said displayed pitch ladder bars, said graphic heading data based on said heading signal.

18. A display system as described in claim 17 wherein the radius of curvature of said pitch ladder bars decreases as the absolute value of pitch angle increases.

19. A display system as described in claim 17 wherein the zero degree pitch bar line segments have zero slope, and the pitch bar displayed for plus or minus 90°

is a closed figure.

20. A display system as described in claim 19 further comprising:

a. means for sensing aircraft roll and generating a signal indicative of the magnitude of roll,

b. means for generating a curved scale having roll angle indicia disposed thereon,

c. means for generating a bank symbol on the scale indicating the angle of bank, said position of said symbol based on said roll signal, and

d. means for displaying said scale and said symbol on said screen.

21. A display system as described in claim 20 further comprising:

a. means for selectively inhibiting the display of said symbol based on said roll signal.

22. A display system as described in claim 21 further comprising:

a. means for rotating the pitch bar display through an angle equivalent to roll angle responsive to said roll signal.

23. A display system for viewing aircraft flight information comprising:

a. means for sensing pitch and roll angles of an aircraft;

b. means for generating a reference spherical surface with an origin at the position of the aircraft, said surface having a vertical polar axis and latitudinal reference markings corresponding to different pitch angles from -90°

to 90°

;

c. means for calculating, from said pitch and roll angles, an intersection of a projected flight path of the aircraft with the surface based on said angles; and

d. means for displaying to an operator of said aircraft an effective segment of such surface surrounding the intersection from the perspective of the aircraft at the origin.

24. The display system of claim 23 further comprising:

a. means for sensing the heading angle of an aircraft;

b. means whereby the spherical surface is referenced to north;

c. means for calculating the intersection of the projected flight path of the aircraft with the surface based on the heading angle of the aircraft; and

d. means for displaying the effective segment of such surface surrounding the intersection wherein the displayed segment indicates the heading angle of the aircraft.

25. The system of claim 23 wherein the displayed segment indicates the pitch angle of the aircraft in relation to a pitch ladder bar, wherein the pitch ladder bars comprise those portions of the latitudinal reference markings within the displayed segment of the spherical surface.

26. The system of claim 25 wherein a plurality of absolute heading angles are indicated along the pitch ladder bars.

27. The system of claim 23 wherein the horizontal axis of the display means is essentially parallel to the lateral axis of the aircraft as projected onto the displayed segment.

28. The system of claim 23 wherein the display means comprise:

a. a screen for displaying the segment of the spherical surface,

b. optical system for transmitting an image of the screen display to a position within a field of view of a pilot of the aircraft.