Aircraft piloting aid system

• US 4,419,079 A
• Filed: 07/20/1981
• Issued: 12/06/1983
• Est. Priority Date: 07/23/1980
• Status: Expired due to Term

• Current Assignee: Avions Marcel Dassault-Breguet Aviation, Thomson-CSF
• Original Assignee: Avions Marcel Dassault-Breguet Aviation, Thomson-CSF
• Inventors: Parus, Roger, Georges, Jean-Francois M.
• Primary Examiner(s): Hum, Vance Y.
• Assistant Examiner(s): Picard, Leo P.
• Application Number:
  US06/284,666
• Time in Patent Office: 869 Days
• Field of Search: 434/35, 434/36, 434/43, 434/239-244, 434/44, 434/57, 340/27 NA, 358/104
• US Class Current: 434/43
• CPC Class Codes: G01C 23/005 Flight directors indicating arrangements specially adapted for rotary gyroscopes G01C19/32
• CPC Class Codes: G05D 1/0676 specially adapted for landing

Abstract

A piloting aid system for displaying symbols representative of determined characteristics of the flight of an aircraft and representative of its environment is disclosed. The symbols are displayed on the screen of a display unit which displays a symbol representing the aircraft near a predetermined point on the display screen and a rectangular window for guiding the flight path of the aircraft. The sides of the guidance window are parallel to mutually perpendicular axes provided on the screen. The abscissa and ordinate of the predetermined point are respectively proportional to the drift and to the slope relative to the ground of the aircraft flight path.

Claims

1. A piloting aid system for aiding in piloting or in simulating the piloting of an aircraft, comprising:

a display unit having a display screen and means for displaying on said display screen symbols representative of a plurality of determined flight and environmental characteristics of said aircraft;

means for determining drift angle δ and

a slope relative to ground γ

_S of a flight path of said aircraft;

means for displaying a symbol representing said aircraft near a point having an abscissa and an ordinate on said display screen, said abscissa and said ordinate of said point with respect to two mutually perpendicular axes on said display screen being respectively proportional to the determined values of δ and

γ

_S ; and

means for displaying a guidance symbol for the aircraft flight path comprising a rectangular guidance window having pairs of sides respectively parallel to said mutually perpendicular axes.

2. A piloting aid system as claimed in claim 1, further comprising an inertial guidance device mounted on said aircraft and wherein the drift angle δ

and the slope relative to ground γ

_S of said aircraft flight path are derived from said inertial guidance device mounted on said aircraft.

3. A piloting aid system as claimed in claim 1, further comprising:

means for determining an actual incidence α

of said aircraft and aircraft speed V_S relative to ground;

means to select an aircraft reference speed;

means to compute a difference Δ

α

between a determined value of the aircraft actual incidence and an incidence corresponding to said aircraft reference speed;

means for displaying near said symbol representing said aircraft at least one aircraft incidence characterizing symbol, the difference between the ordinate of said aircraft incidence symbol and that of said symbol representing said aircraft being equal to a product KΔ

α

, wherein K is a proportionality coefficient; and

at least one potential-slope characterizing symbol the ordinate of which is proportional to ##EQU7## where g is the intensity of the force of gravity and dVs/dt is the time differential of said aircraft speed V_s representing acceleration of said aircraft.

4. A piloting aid system as claimed in claim 3, wherein said proportionality coefficient K comprises a variable coefficient means increasing with said difference Δ

α

, at least above a certain value of said difference Δ

α

.

5. A piloting aid system as claimed in claim 3, further comprising:

means for determining an aircraft longitudinal inclination θ

, and horizontal and vertical components, J_x and J_z, respectively, of aircraft acceleration; and

a plurality of circuits for computing said potential slope from an equation γ

_p =[J_z (θ

-γ

_s)+J_x ]/g.

6. A piloting aid system as claimed in claim 3, further comprising:

means for determining a roll angle Ψ

of said aircraft;

means for displaying a plurality of stationary marks for representing a pitch axis and a yaw axis of said aircraft; and

means for displaying a drift angle δ

axis in the form of a mobile graduated horizon line forming an angle with said pitch axis which is equal to the determined value of said roll angle Ψ

, the distance between said horizon line and the point of convergence of said stationary marks being proportional to a longitudinal inclination θ

of said aircraft.

7. A piloting aid system as claimed in claim 3, further comprising means for displaying a realistic time-evolving image of a runway as said runway would normally be seen by a pilot of said aircraft.

8. A piloting aid system as claimed in claim 7 for aiding in landing or in simulating landing of said aircraft on a runway equipped with an instrument landing system or like system, further comprising:

means for determining coordinates of an ideal touchdown point on said runway;

means for further displaying an axis of said runway passing through said ideal touchdown point; and

means for displaying said rectangular guidance window during instrument landings, said guidance window comprising a center point having coordinates differing from those of said ideal touchdown point by amounts respectively proportional to a localizer-beam deviation and a glide-slope deviation, wherein both of said deviations are derived from an instrument landing system receiver on board said aircraft.

9. A piloting aid system as claimed in claim 7, wherein said display screen is installed in a cockpit of said aircraft and optical means are provided for projecting said display screen to infinity before a pilot'"'"'s eyes, in a position such that said mobile graduated horizon line and said time-evolving image of said runway coincide substantially with an actual horizon and runway seen by said pilot through a windshield of said aircraft.

10. A piloting aid system as claimed in claim 1, further comprising means for changing the shape or dimensions of said rectangular guidance window in accordance with successive phases in the flight of said aircraft such as cruise flight, runway approach, and successive phases in an instrument landing system landing.

11. A piloting aid system as claimed in claim 1, wherein said display unit comprises a cathode-ray tube.