Method and System For Highlighting a Flight Path Deviation of an Aircraft

Abstract

A method and system for highlighting a flight path deviation of an aircraft to a user in a multi-parameter aircraft instrument display, such as a flat panel display. A visibility attribute is configured to toggle between a standard state when the actual aircraft position is within a predetermined range of the target aircraft position, and an enhanced state when the actual aircraft position is outside the predetermined range. The electronic display is configured to highlight a flight path deviation when in the enhanced state, such as by displaying deviation scales having an actual aircraft position indicator relative to the target position, and increasing the size or changing the color of certain displayed elements, or displaying/concealing new elements. Such display features aid in focusing the pilot's attention to deviations from optimal flight paths and ensuring navigation accuracy and, therefore, safety.

What is claimed is: 
     
         1 . An apparatus for indicating flight path deviation for an aircraft, the apparatus comprising:
 a graphics rendering controller configured to generate an instrumentation image; and   an electronic display coupled to the graphics rendering controller to present the instrumentation image;
 the instrumentation image comprises:
 a deviation scale comprising an actual aircraft position indicator representative of an actual aircraft position; 
 a pointer movable along the deviation scale to represent the target aircraft position; and 
 a visibility attribute configured to toggle between:
 a standard state when the actual aircraft position is within a predetermined range of the target aircraft position; and 
 an enhanced state when the actual aircraft position is outside the predetermined range of the target aircraft position; 
 
 
   wherein the electronic display is configured to highlight a flight path deviation when in the enhanced state.   
     
     
         2 . The apparatus of  claim 1 , wherein:
 the instrumentation image further comprises an attitude indicator image; and   the deviation scale is presented adjacent to the attitude indicator image.   
     
     
         3 . The apparatus of  claim 1 , wherein:
 the pointer comprises a perimeter and an inner area;   the perimeter of the pointer comprises a perimeter color;   the visibility attribute comprises an inner color of the inner area of the pointer;   the inner color matches the perimeter color when the standard state of the visibility attribute is enabled; and   the inner color differs from the perimeter color when the enhanced state of the visibility attribute is enabled.   
     
     
         4 . The apparatus of  claim 1 , wherein:
 the pointer comprises a perimeter and an inner area;   the perimeter of the pointer comprises a perimeter color;   the visibility attribute comprises an inner color of the inner area of the pointer;   the inner color matches the perimeter color when the enhanced state of the visibility attribute is enabled; and   the inner color differs from the perimeter color when the standard state of the visibility attribute is enabled.   
     
     
         5 . The apparatus of  claim 1 , wherein:
 the visibility attribute comprises a size of the pointer;   the size of the pointer comprises a default size when the standard state of the visibility attribute is enabled; and   the size of the pointer is increased relative to the default size when the enhanced state of the visibility attribute is enabled.   
     
     
         6 . The apparatus of  claim 1 , wherein:
 the visibility attribute comprises a color of the deviation scale;   the color of the deviation scale comprises a first color when the standard state of the visibility attribute is enabled; and   the color of the deviation scale comprises a second color when the enhanced state of the visibility attribute is enabled.   
     
     
         7 . The apparatus of  claim 1 , wherein:
 the target aircraft position comprises an active route position for the aircraft;   the predetermined range comprises a required navigation performance value for the aircraft; and   the flight path deviation comprises a lateral deviation of the aircraft from the active route.   
     
     
         8 . The apparatus of  claim 1 , wherein an enhanced state is triggered when a distance between the actual aircraft position and the active route position is greater than the required navigation performance value. 
     
     
         9 . The apparatus of  claim 1 , wherein the deviation scales further comprise:
 a first deviation limit representative of a first deviation limit magnitude from a target aircraft position, the first deviation limit located at a first end of the deviation scale; and   a second deviation limit representative of a second deviation limit magnitude from the target aircraft position, the second deviation limit located at a second end of the deviation scale and opposite the first deviation limit.   
     
     
         10 . The apparatus of  claim 9 , wherein:
 when the enhanced state of the visibility attribute is enabled:   a digital readout showing an actual value of the aircraft deviation is displayed when the actual aircraft position exceeds the predetermined range past the first or second deviation limit.   
     
     
         11 . The apparatus of  claim 10 , wherein:
 the target aircraft position comprises a target aircraft altitude; and   the aircraft deviation comprises a vertical deviation of the aircraft from the target aircraft altitude.   
     
     
         12 . The apparatus of  claim 11 , wherein an enhanced state is triggered when a distance between the actual aircraft position and the target aircraft altitude is greater than the predetermined range. 
     
     
         13 . The apparatus of  claim 10 , wherein:
 when the enhanced state of the visibility attribute is enabled, the digital readout is zoomed when the actual aircraft position exceeds the first or second deviation limit.   
     
     
         14 . The apparatus of  claim 9 , wherein:
 during a standard condition, the first and second deviation limits are scaled to a default deviation tolerance;   during a heightened condition, the first and second deviation limits are scaled to a heightened deviation tolerance; and   the heightened deviation tolerance is smaller in range than the default deviation tolerance.   
     
     
         15 . The apparatus of  claim 14 , wherein the heightened condition is triggered as a result of a condition selected from the group consisting of a radio height of less than approximately 2500 feet, a landing gear down condition, an enabled landing gear override switch, a landing flaps set condition, and an enabled flap override switch. 
     
     
         16 . The apparatus of  claim 14 , wherein:
 when the first and second deviation limits are scaled to the heightened deviation tolerance:
 the first deviation limit represents the first deviation limit magnitude to be of approximately 25 feet to approximately 75 feet below the target aircraft position; and 
 the second deviation limit represents the second deviation limit magnitude to be of approximately 50 feet to approximately 100 above the target aircraft position. 
   
     
     
         17 . The apparatus of  claim 14 , wherein:
 when the first and second deviation limits are scaled to the heightened deviation tolerance:
 the first deviation limit represents the first deviation limit magnitude to be of approximately 50 feet below the target aircraft position; and 
 the second deviation limit represents the second deviation limit magnitude to be of approximately 75 feet above the target aircraft position. 
   
     
     
         18 . The apparatus of  claim 14 , wherein:
 when the first and second deviation limits are scaled to the default deviation tolerance:
 the first deviation limit represents the first deviation limit magnitude to be of approximately 200 feet to approximately 500 feet below the target aircraft position; and 
 the second deviation limit represents the second deviation limit magnitude to be of approximately 200 feet to approximately 500 feet above the target aircraft position. 
   
     
     
         19 . The apparatus of  claim 14 , wherein:
 when the first and second deviation limits are scaled to the default deviation tolerance:
 the first deviation limit represents the first deviation limit magnitude to be of approximately 400 feet below the target aircraft position; and 
 the second deviation limit represents the second deviation limit magnitude to be of approximately 400 feet above the target aircraft position. 
   
     
     
         20 . The apparatus of  claim 1 , wherein:
 the graphics rendering controller is coupled to an aircraft computer;   the first and second deviation limits are based on required navigation path data from the aircraft computer.   
     
     
         21 . The apparatus of  claim 1 , wherein when in the standard state, at least one of the deviation scale or the pointer are concealed. 
     
     
         22 . The apparatus of  claim 1 , wherein:
 the deviation scale comprises at least one of:
 a lateral deviation scale to indicate a cross track error; or 
 a vertical deviation scale to indicate a vertical path deviation.