Process for displaying flying aid symbols on a screen on board an aircraft

• US 5,289,185 A
• Filed: 08/30/1991
• Issued: 02/22/1994
• Est. Priority Date: 09/05/1990
• Status: Expired due to Term

• Current Assignee: Aerospatiale Societe Nationale Industrielle
• Original Assignee: Aerospatiale Societe Nationale Industrielle
• Inventors: Duturc, Daniel, Saint-Upery, Yves, Ramier, Alain
• Primary Examiner(s): Swarthout, Brent
• Application Number:
  US07/753,109
• Time in Patent Office: 907 Days
• Field of Search: 340/961, 340/967, 340/968, 340/970, 340/971, 340/972, 340/973, 340/974, 340/975, 340/976, 340/977, 340/978, 340/979, 340/980, 364/424.06, 364/461, 364/428, 364/439, 73/178 T, 342/29, 342/33
• US Class Current: 340/971
• CPC Class Codes: G01C 23/005 Flight directors indicating arrangements specially adapted for rotary gyroscopes G01C19/32

Abstract

The invention relates to a process for the display on a screen on board an aircraft of flying aid symbols. On the basis of information supplied by an inertial system and ground beacons processed by an on board computer, the process consists of displaying on an on board screen (EV) symbols more particularly representing the wings of the aircraft (A1, A2), the model of the aircraft (CP), its speed (V), the tendency to acceleration and deceleration (AD1, AD2), a flight path prediction (PT), the artificial horizon (H), the roll angle (φ), the sideslip (AL) and the total energy (ET1, ET2). It also consists of displaying the flight path to be followed in perspective (P1, P2, S3, S4, S5) and in projection (S'"'"'1 to S'"'"'5) on the plane of the runway. Any flight path segment during passage, as well as the segment following the latter are displayed in parallelepipedic form (P1, P2) in perspective. A final segment preceding the touchdown point of the wheels on the runway is displayed in the form of a pyramid (P3) in perspective. A display also takes place of the runway (P) and a grid (M1, M2, PE1, PE2) superimposed on said runway, in perspective.

Claims

1. Process for the display of flying aid symbols on a screen (EV) on board an aircraft, for traversing a flight path formed by successive approach segments (S1 to S4), a final segment (S5) and a rounding off segment traversed up to the touchdown point (F) of the aircraft wheels on a runway (P) comprising:

defining a fixed reference mark frame (O, Xt, Yt, Zt) linked with the runway and having orthogonal axes, having for its origin a theoretical wheel touchdown point on the runway, said point being located on a longitudinal axis of the runway, the fixed reference frame having a first axis (Xt) coinciding with the longitudinal axis of the runway, a second axis (Yt) perpendicular to the first axis in a plane of the runway and a third axis (Zt) perpendicular to the first and second axes of the fixed reference mark frame;

defining a mobile reference mark frame (G, X_A, Y_A Z_A) linked with the aircraft and having for its origin the center of gravity (G) of the aircraft and a first axis (X_A) coinciding with a longitudinal axis of the aircraft, a second axis (Y_A) perpendicular to a plane of symmetry of the aircraft and passing through the longitudinal axis and a third axis (Z_A) perpendicular to the first and second axes of the mobile reference mark frame;

recording in a memory of on board computer, reference coordinates of the essential points of the segments of the flight path (S1 to S5, PR) measured in the fixed reference mark frame (Co, Xt, Yt, Zt);

determining on the basis of information received from an inertial system, the coordinates of the effective positions of the aircraft relative to the fixed reference mark frame, during the traversing of the flight path, as well as values respectively corresponding to the roll (φ

), attitude (θ

) and bearing (ψ

) angles or Eulerian angles of the aircraft, and the orientations of a speed vector (V) of the aircraft, measured in the mobile reference mark frame;

displaying on said screen (EV) during the traversing of the flight path, an image obtained in a plane perpendicular to the first axis (X_A) of the aircraft, in the vicinity of its center of gravity (G) following a processing of the values of the Eulerian angles, of the effective coordinates, of the reference coordinates and the orientations of the speed vector, said image comprising at least;

two identical fixed symbols (A1, A2) representing the aircraft wings, aligned on a first axis (Y_E) of the screen, parallel to the second axis (Y_A) of the mobile reference frame and passing through a central point (O'"'"') of the screen,

a symbol (CP) representing a model of the aircraft indicating the orientation of the longitudinal axis of the aircraft and moving along the first axis of the screen, between the two fixed symbols representing the wings of the aircraft,

a line (H) moving in translation and in inclination, called the artificial horizon, subdividing the screen (EV) into an upper part (H1) representing the sky and a lower part (H2) representing the ground, and making it possible to reference with respect to the fixed symbols representing the aircraft wings, the roll (φ

) and attitude (θ

) pitch angles of the aircraft during passage, said line being graduated so as to form a heading scale and for indicating the bearing (ψ

) of the aircraft, a symbol (V) indicating the orientation of the speed vector of the aircraft and mobile along said orientation, along a second axis (Z_E) of the screen (EV) and passing through the central point (O'"'"') and perpendicular to the first axis (YE) of the screen,

characterized in that it also comprises displaying in accordance with a three-dimensional representation, approach segments (S1 to S5) located on the flight path to be covered by the aircraft, the segment being traversed, as well as at least the segment following that being traversed, being respectively displayed in accordance with two elongated parallelepipeds, in perspective, having respectively segments for axes, each parallelepiped in perspective, having in the traversing direction of the corresponding segment, an entrance base (B1) into the segment and an exit base (B2) from the segment, said bases being rectangular, so that during the traversing of a segment, the entry base (B1) of a parallelepiped corresponding to said segment has a fixed dimension in the reference mark frame and the exit base (B2) an increasing dimension between a minimum dimension, when the aircraft starts to traverse this segment, and a maximum dimension equal to the dimension of the entry base (B1) with which it coincides at the end (B) of the traversing of said segment and at the start of the traversing of the following segment (S2) of the flight path, the process also consisting of displaying the final segment (S5) in the form of a pyramid (P3) in perspective and having a rectangular base (F3), with on the screen an apex corresponding to the touchdown point (PR) of the wheels on the runway, so that during the traversing of the final segment, the base (F3) of the pyramid of the final segment (S5) has a decreasing dimension during the traversing of said final segment up to the touchdown point (PR) of the wheels, each base of the parallelepiped and the base of the pyramid having sides located on the screen (EV) as a function of the values of the Eulerian angles and coordinates of the origin (G) of the mobile reference mark frame with respect to the fixed reference mark frame, the symbol indicating the orientation of the speed vector (V) having to be located in the center of the entry base (B1) of the parallelepiped (P1) in perspective, representing the segment being traversed, or in the center of the base (F3) of the pyramid (P3) representing the final segment, when the aircraft is correctly located on a segment.

2. Process according to claim 1, characterized in that the entry base of each parallelepiped, as well as the base of the pyramid are positioned in advance by a constant delay in front of the aircraft.

3. Process according to claim 2, characterized in that at the start of traversing a rounded off flight path segment during which the aircraft leaves the final segment (S5) for joining by a rounded off portion a horizontal flight path (S6) immediately preceding wheel touchdown, the sides of the base of the pyramid maintain a constant dimension close to that of the symbol of the speed vector, which is circular.

4. Process according to claim 1, characterized in that it also consists of displaying on the screen the runway and the projection on the plane of the runway the flight path still to be covered.

5. Process according to claim 1, characterized in that it also comprises displaying a roll scale (E1) shaped like a circular arc and rotatable about a central point (O'"'"') of the screen, said scale having a first slide or cursor (C1) fixed to the screen and linked with said scale (E1) on the second axis (Z_E) of the screen, in order to indicate the direction of the third axis (Z_A) of the mobile reference frame, and a second slide or cursor (C2) moving with the scale (E1) and linked with the latter, located on a third mobile axis (Z'"'"') of the screen, passing through the central point (O'"'"') of the screen and remaining parallel to the third axis (Z_A) of the reference mark frame during a roll movement, the roll angle (φ

) being indicated by the displacement between the fixed cursor (C1) and the mobile cursor (C2), and displaying the lateral acceleration or sideslip of the aircraft by a symbol mobile parallel to the first axis of the screen and linked with the first fixed cursor of the roll scale.

6. Process according to claim 5, characterized in that it also comprises displaying an attitude scale (E2) extending along the third axis (Z'"'"') of the screen from the artificial horizon (H) to the mobile roll scale (E1).

7. Process according to claim 1, characterized in that it also comprises displaying the tendency to acceleration or deceleration of the aircraft on the flight path, by two identical tendency indicating symbols (AD1, AD2) arranged parallel to the first axis (Y_E) of the screen and mobile parallel to the second axis (Z_E), said two symbols being located above the speed vector symbol (V) if the tendency is to acceleration and below the speed vector symbol (V) if the tendency is to deceleration, the distance between the speed vector symbol and the two acceleration or deceleration tendency symbols (AD1, AD2) being proportional to the acceleration of the aircraft on the flight path.

8. Process according to claim 7, characterized in that it also comprises displaying the total energy variation direction to be adopted in order to reach a selected speed, by two identical energy variation direction indicating symbols (ET1, ET2) arranged parallel to the second axis of symmetry (Z_E) of the screen, said two symbols being mobile parallel to the second axis (Z_E) of the screen, the distance between these two variation direction symbols and the speed vector symbol representing the difference between the selected speed and the effective speed of the aircraft.

9. Process according to claim 8, characterized in that the symbol (CP) representing an aircraft model is mobile along the first screen axis (Y_E), the symbols (A1, A2) representing the aircraft wings, the acceleration and deceleration tendency indicating symbols (AD1, AD2) and the energy variation direction indicating symbols (ET1, ET2) are arranged symmetrically with respect to the second screen axis (Z_E).

10. Process according to claim 8, characterized in that the symbol (CP) representing a model of the aircraft is fixed and located at the central point O'"'"' of the screen, the symbols (A1, A2) representing the wings of the aircraft being positioned symmetrically relative to the second axis of the screen, the symbol (V) indicating the orientation of the speed vector being mobile, in accordance with said orientation, on a first secondary axis (Y_E '"'"') of the screen parallel to the first axis (Y_E) of the reference mark frame and on a second secondary axis (Z_E '"'"') of the screen parallel to the second axis (Z_E) of the reference frame, the acceleration or deceleration tendency indicating symbols (AD1, AD2) and the energy variation direction indicating symbols (ET1, ET2) being positioned symmetrically relative to the second secondary axis.

11. Process according to claim 1, characterized in that it also comprises displaying a flight path prediction by a symbol (PT) mobile on a line passing through the speed vector symbol (V) and parallel to the artificial horizon line (H), said prediction symbol indicating the aircraft position direction at a predetermined future time projected onto the first two axes of the mobile reference frame.

12. Process according to claim 1, characterized in that it also comprises displaying the orientation of the runway (P) on the artificial horizon (H) by a mobile symbol (AP) linked with the artificial horizon (H) and positioned thereon as a function of the value of the roll angle (φ

) and the heading of the aircraft.

13. Process according to claim 1, characterized in that it also comprises displaying the runway, the runway axis (Xt), a line perpendicular to the runway axis at the wheel touchdown point and a grid of lines parallel (M1, M2, M3) and perpendicular (PE1, PE2) to the runway axis.

14. Process according to claim 13, characterized in that it comprises using specific colors for representing the ground, the sky, symbols, the artificial horizon, scale cursors, the runway and said grid of lines.

15. Process according to claim 14, characterized in that it also comprises displaying on the screen complimentary information useful in flying the aircraft.

16. Process according to claim 13, characterized in that it comprises using specific colors for representing the ground, the sky, symbols, the artificial horizon, scale cursors, the runway and said grid of lines.

17. Process according to claim 16, characterized in that it also comprises displaying on the screen complimentary information useful in flying the aircraft.