Abstract:
A method and device for displaying the performance of an aircraft when climbing and/or descending. The device includes devices for data capture, calculation and generating images for a display screen. The calculation device is configured to calculate a maximum slope that the aircraft can adopt depending on current data received from a data capture device. A display device presents images of the maximum slope superimposed with altitudes of a projected flight plan.

Description:
This application claims priority to French Patent Application No. 1354334 filed 15 May 2013, the entire contents of each of which are hereby incorporated by reference. 
     BACKGROUND OF INVENTION 
     The present invention relates to a method and a device for displaying the performance of an aircraft when climbing and/or descending, and also to an aircraft comprising this type of display device. 
     It is known that on present aircraft, when a change of flight level (climb or descent) is necessary during a flight, pilots can initiate the change of altitude manually. To do this, they select the required altitude and set a specific mode in a flight control unit (FCU). There is therefore an open descent mode to cause the aircraft to descend and an open climb mode to cause the aircraft to climb. 
     When one of these modes is set, the vertical slope taken by the aircraft corresponds to the maximum slope that the aircraft is capable of adopting. This maximum slope depends on the capability of the aircraft at the time the mode is applied. Parameters such as the mass and speed of the aircraft, and the engine thrust are factors that determine its ability to follow a slope. 
     However, pilots do not know exactly what slope the aircraft will take or the positions through which it will pass to reach the selected altitude. This is because no device exists that has been designed to calculate and provide this information to the crew. 
     SUMMARY OF INVENTION 
     The object of the present invention is to overcome this drawback, and it relates to a method and a device for displaying the performance of an aircraft when climbing and/or descending. 
     According to the invention, said method is noteworthy it comprises the following successive steps, implemented automatically and repetitively, and consisting of:
         receiving current flight data;   calculating at least one maximum slope that the aircraft can adopt depending on said current data and its performance; and   providing a constant display of a flight path with said maximum slope on at least a portion of a display screen, which is configured to display a vertical flight plan.       

     Therefore, with the help of the invention, pilots have constant access to the flight path with the maximum slope at which the aircraft is capable of flying, depending on the current conditions, in other words an image of the flight path that the aircraft will follow if one of the above-mentioned modes (open climb or open descent) is applied. As indicated above, these modes cause the aircraft to fly at its maximum slope. The maximum slope is calculated from the current flight data, which gives an accurate and reliable result. The maximum slope is displayed on a vertical display (VD) screen (or a screen portion) of the flight plan, which shows the characteristics of the vertical flight plan of the aircraft. 
     According to different embodiments of the invention, which can be taken together or separately:
         the maximum slope calculated is a climb slope for said aircraft;   the maximum slope calculated is a descent slope for said aircraft;   to calculate said maximum slope, the method consists of solving the following differential equations of thrust:       

     
       
         
           
             
               
                 m 
                 ⁢ 
                 
                   
                     ⅆ 
                     V 
                   
                   
                     ⅆ 
                     t 
                   
                 
                 ⁢ 
                 cos 
                 ⁢ 
                 
                     
                 
                 ⁢ 
                 γ 
               
               = 
               
                 
                   T 
                   ⁢ 
                   
                       
                   
                   ⁢ 
                   
                     cos 
                     ⁡ 
                     
                       ( 
                       
                         α 
                         + 
                         γ 
                       
                       ) 
                     
                   
                 
                 - 
                 
                   
                     1 
                     2 
                   
                   ⁢ 
                   ρ 
                   ⁢ 
                   
                       
                   
                   ⁢ 
                   
                     V 
                     2 
                   
                   ⁢ 
                   
                     S 
                     ⁡ 
                     
                       ( 
                       
                         
                           
                             C 
                             x 
                           
                           ⁢ 
                           cos 
                           ⁢ 
                           
                               
                           
                           ⁢ 
                           γ 
                         
                         + 
                         
                           
                             C 
                             z 
                           
                           ⁢ 
                           sin 
                           ⁢ 
                           
                               
                           
                           ⁢ 
                           γ 
                         
                       
                       ) 
                     
                   
                 
               
             
             ; 
           
         
       
       
         
           
             
               
                 m 
                 ⁢ 
                 
                   
                     ⅆ 
                     V 
                   
                   
                     ⅆ 
                     t 
                   
                 
                 ⁢ 
                 sin 
                 ⁢ 
                 
                     
                 
                 ⁢ 
                 γ 
               
               = 
               
                 
                   T 
                   ⁢ 
                   
                       
                   
                   ⁢ 
                   
                     sin 
                     ⁡ 
                     
                       ( 
                       
                         α 
                         + 
                         γ 
                       
                       ) 
                     
                   
                 
                 - 
                 mg 
                 - 
                 
                   
                     1 
                     2 
                   
                   ⁢ 
                   ρ 
                   ⁢ 
                   
                       
                   
                   ⁢ 
                   
                     V 
                     2 
                   
                   ⁢ 
                   
                     S 
                     ⁡ 
                     
                       ( 
                       
                         
                           
                             C 
                             x 
                           
                           ⁢ 
                           sin 
                           ⁢ 
                           
                               
                           
                           ⁢ 
                           γ 
                         
                         + 
                         
                           
                             C 
                             z 
                           
                           ⁢ 
                           cos 
                           ⁢ 
                           
                               
                           
                           ⁢ 
                           γ 
                         
                       
                       ) 
                     
                   
                 
               
             
             ; 
           
         
       
     
     where:
         T is the maximum thrust in open climb mode or the minimum thrust in open descent mode respectively, with the assumption that one engine is switched off,   V is the aircraft speed,   ρ is the air density, which depends on the altitude,   S is a reference area of the aircraft wings,   m is the aircraft mass,   Cx is the drag coefficient,   Cz is the lift coefficient,   α is the angle of attack of the aircraft, and   γ is the slope of the aircraft.       

     Furthermore, advantageously:
         said slope is displayed on request (in particular by the pilot) on said screen portion; and   said slope is displayed automatically on said screen portion.       

     It will be noted that the constant display of the flight path applies from the moment the display is actuated (either manually (in particular by a pilot), or automatically (for a particular flight phase, for example)). 
     The invention also relates to a device for displaying the performance of an aircraft when climbing and/or descending, comprising data capture means, calculation means and a display screen. 
     According to the invention, this device is noteworthy in that said calculation means are configured to calculate at least one maximum slope that the aircraft can adopt depending on the data received from the data capture means, and in that said device is also configured to display said calculated maximum slope on at least a portion of the display screen, which is configured to display a vertical flight plan. 
     Moreover, advantageously, said calculation means are capable of calculate a climb slope and/or a descent slope for said aircraft. 
     The invention also relates to an aircraft comprising a device of this type for displaying the performance of an aircraft when climbing and/or descending. 
    
    
     
       SUMMARY OF THE FIGURES 
       The figures of the appended drawings will make clear how the invention can be achieved. In these figures, identical references numerals designate similar elements. 
         FIG. 1  is a block diagram of a performance display device for an aircraft when climbing and/or descending, which illustrates the invention. 
         FIG. 2  is a diagrammatic representation which is displayed on a screen portion. 
         FIG. 3  shows diagrammatically an example of the use of the device according to an embodiment of the invention for a low altitude flight. 
         FIG. 4  shows diagrammatically another example of the use of the device for a high altitude flight. 
     
    
    
     DETAILED DESCRIPTION 
     In  FIG. 1 , the performance display device  1  of an aircraft when climbing and/or descending, comprises data capture means  2 , calculation means  3  and a display screen  4 . Said display device  1  also comprises means  14  enabling a pilot to adjust the display produced on the display screen  4 . The data capture means  2  receive, measure and/or determine current flight data and structural data for the aircraft. The current flight data are in particular the aircraft speed V, the air density ρ, the aircraft mass m, the flight plan, the angle of attack α, and the wind speed and direction. The aircraft structural data are the maximum thrust T when climbing or when descending with an engine switched off, the reference area S of the wing, the drag coefficient Cx, the lift coefficient Cz, and the mathematical relationship α(γ) between −+ 
     the angle of attack and slope of the aircraft. All these parameters are transmitted automatically to the calculation means  3 . 
     Said calculation means  3  are configured to calculate at least one maximum slope  7 ,  8  that the aircraft can adopt. The maximum slope  7 ,  8  calculated may be a climb slope  7  or a descent slope  8 . 
     Said device  1  is also configured to allow the maximum slope  7 ,  8  to be displayed on at least a portion  5  of a display screen  4 . This screen  4  (or at least this screen portion  5 ) is usually configured to display the vertical flight plan of the aircraft, as shown in  FIGS. 3 and 4 . This conventional illustration of a VD display usually shows a symbol  6  indicating the aircraft, the relief  9 , the flight path  11  of the aircraft at low altitude, and safe altitudes  10 . A vertical scale  12  shows the altitude in feet, and a horizontal scale  13  shows the distance to be covered in nautical miles. 
     Thus, with the help of the invention, after actuating the display, the pilots have constant access to the flight path with the maximum slope  7 ,  8  at which the aircraft is capable of flying depending on the current conditions, in other words an image of the flight path that the aircraft will follow if one of the normal modes (open climb or open descent) is applied, these modes causing the aircraft to fly at its maximum slope  7 ,  8 . The maximum slope  7 ,  8  is calculated from current flight data to obtain an accurate and reliable result. 
     This device  1  can also help pilots in particular situations so that they know when the aircraft should change altitude. For example, for a low altitude flight the aircraft may have to change altitude, depending on the ground relief. The flight path display has the advantage of ensuring that the pilot does not have to anticipate or delay the procedure to achieve a particular safe distance in relation to the relief. 
     Said slope or slopes  7 ,  8  are therefore displayed on said portion  5  of the screen  4 , as illustrated in  FIG. 2 . The image shows an aircraft  6 , with two dashed lines symbolising the maximum slopes  7  and  8 . A first maximum slope  7  indicates the performance of the aircraft  6  as it climbs, and a second maximum slope  8  indicates the performance of the aircraft  6  as it descends, for climb and descent procedures respectively. 
     The image is displayed automatically or on request. In the first case, the image of the slope or slopes  7 ,  8  appears constantly on the screen  4  throughout the journey of the aircraft, or when the aircraft attains particular conditions. The slopes  7 ,  8  are calculated continuously so that they are adjusted to successive flight conditions. Pilots are therefore always able to see updated slopes  7 ,  8 . In the second case the image appears when the pilots need it, by means of display control means, such as a button, which may form part of the means  14 . 
     Pilots are therefore informed of the capacity of the aircraft  6  to climb or descend because the maximum slopes  7 ,  8  are calculated and displayed. They can therefore choose in particular the appropriate moment to select a climb or descent mode. 
     The slope  7 ,  8  is calculated from the data supplied by the data capture means  2 . 
     To calculate said maximum slope  7 ,  8  the calculation means  3  solve the following differential equations of thrust: 
     
       
         
           
             
               
                 m 
                 ⁢ 
                 
                   
                     ⅆ 
                     V 
                   
                   
                     ⅆ 
                     t 
                   
                 
                 ⁢ 
                 cos 
                 ⁢ 
                 
                     
                 
                 ⁢ 
                 γ 
               
               = 
               
                 
                   T 
                   ⁢ 
                   
                       
                   
                   ⁢ 
                   
                     cos 
                     ⁡ 
                     
                       ( 
                       
                         α 
                         + 
                         γ 
                       
                       ) 
                     
                   
                 
                 - 
                 
                   
                     1 
                     2 
                   
                   ⁢ 
                   ρ 
                   ⁢ 
                   
                       
                   
                   ⁢ 
                   
                     V 
                     2 
                   
                   ⁢ 
                   
                     S 
                     ⁡ 
                     
                       ( 
                       
                         
                           
                             C 
                             x 
                           
                           ⁢ 
                           cos 
                           ⁢ 
                           
                               
                           
                           ⁢ 
                           γ 
                         
                         + 
                         
                           
                             C 
                             z 
                           
                           ⁢ 
                           sin 
                           ⁢ 
                           
                               
                           
                           ⁢ 
                           γ 
                         
                       
                       ) 
                     
                   
                 
               
             
             ; 
           
         
       
       
         
           
             
               
                 m 
                 ⁢ 
                 
                   
                     ⅆ 
                     V 
                   
                   
                     ⅆ 
                     t 
                   
                 
                 ⁢ 
                 sin 
                 ⁢ 
                 
                     
                 
                 ⁢ 
                 γ 
               
               = 
               
                 
                   T 
                   ⁢ 
                   
                       
                   
                   ⁢ 
                   
                     sin 
                     ⁡ 
                     
                       ( 
                       
                         α 
                         + 
                         γ 
                       
                       ) 
                     
                   
                 
                 - 
                 mg 
                 - 
                 
                   
                     1 
                     2 
                   
                   ⁢ 
                   ρ 
                   ⁢ 
                   
                       
                   
                   ⁢ 
                   
                     V 
                     2 
                   
                   ⁢ 
                   
                     S 
                     ⁡ 
                     
                       ( 
                       
                         
                           
                             C 
                             x 
                           
                           ⁢ 
                           sin 
                           ⁢ 
                           
                               
                           
                           ⁢ 
                           γ 
                         
                         + 
                         
                           
                             C 
                             z 
                           
                           ⁢ 
                           cos 
                           ⁢ 
                           
                               
                           
                           ⁢ 
                           γ 
                         
                       
                       ) 
                     
                   
                 
               
             
             ; 
           
         
       
     
     where:
         T is the maximum thrust in open climb mode or the minimum thrust in open descent mode respectively with the assumption that one engine is switched off,   V is the aircraft speed,   ρ is the air density, which depends on the altitude,   S is a reference area of the aircraft wings,   m is the aircraft mass,   Cx is the drag coefficient,   Cz is the lift coefficient,   α is the angle of attack of the aircraft, and   γ is the slope of the aircraft, in other words the angle between the velocity vector and the horizon.       

     The angle of attack α is defined between the direction plane of the airflow which circulates round the aircraft wings and the orientation of the plane formed by the wings (more precisely the reference cord of the wing). The mathematical relationship α( γ ) is an item of structural data associated with the aircraft type. 
     Thus, for α≠0, the data capture means supply the calculation means  3  with the mathematical relationship α( γ ) connecting the angle of attack α and the slope  γ . 
     In a simplified calculation mode, the slope  7 ,  8  is calculated in two parts. The curve part is calculated on the assumption that the acceleration of the aircraft is not zero, and that the variation in angle of the slope  γ  compensates for the variation in speed due to thrust that increases when climbing or decreases when descending. The asymptotic part of the curve, on the other hand, is calculated on the assumption that, firstly, acceleration is zero and, secondly, that α is zero. In this case, the following thrust  T  and slope  γ  equations are obtained from the earlier equations: 
     
       
         
           
             
               T 
               = 
               
                 
                   
                     1 
                     2 
                   
                   ⁢ 
                   ρ 
                   ⁢ 
                   
                       
                   
                   ⁢ 
                   
                     SV 
                     2 
                   
                   ⁢ 
                   
                     C 
                     x 
                   
                 
                 + 
                 
                   mg 
                   ⁢ 
                   
                       
                   
                   ⁢ 
                   sin 
                   ⁢ 
                   
                       
                   
                   ⁢ 
                   γ 
                 
               
             
             ; 
           
         
       
       
         
           
             γ 
             = 
             
               
                 
                   sin 
                   
                     - 
                     1 
                   
                 
                 [ 
                 
                   1 
                   
                     mg 
                     ⁡ 
                     
                       ( 
                       
                         T 
                         - 
                         
                           
                             1 
                             2 
                           
                           ⁢ 
                           ρ 
                           ⁢ 
                           
                               
                           
                           ⁢ 
                           
                             SV 
                             2 
                           
                           ⁢ 
                           
                             C 
                             x 
                           
                         
                       
                       ) 
                     
                   
                 
                 ] 
               
               . 
             
           
         
       
     
     This device  1  is particularly useful for a mission carried out during a low altitude flight. As shown in  FIG. 3 , a flight plan for a low altitude flight comprises, in addition to the flight path  11  to be followed, a succession of flight levels  10  arranged above the flight path  11 , which are known as safe altitudes. These safe altitudes are safe levels at which the aircraft can be positioned at a distance from the ground relief to avoid any risk of collision. However, these safe altitudes enable a reasonable distance from the ground relief to be maintained so that if need be low altitude flight can be resumed easily. 
     The maximum climb slope  7  shows pilots what flight path the aircraft will follow to reach the corresponding safe altitude if the open climb mode is engaged. Thus, they can react in the most appropriate way in relation to unforeseen obstacles or problems on the ground, using the calculation and display of the potential climb flight path of the aircraft. 
     Once the safe altitude  10  is reached, the crew can analyse the causes that produced the climb and choose either to return to low altitude or climb higher to a minimum flight altitude or alternatively remain at the safe altitude. 
     In another embodiment shown in  FIG. 4 , the aircraft maintains a flight path that corresponds to the safe levels  10 . Whenever the safe level  10  changes, the aircraft must make the corresponding changes in altitude to move from one safe level to the next. 
     Using the maximum slope  7 ,  8  display, the device  1  gives pilots the advantage of knowing when they should begin the climb in order to reach the next safe level without the risk of passing below the next safe level when that level is higher than the previous one or to avoid reaching it too soon. 
     In the embodiments in  FIGS. 3 and 4 , display of the maximum descent slope  8  is not necessary. In the first example, the aircraft can only climb higher as it is flying at low altitude. In the second example, it is sufficient to wait for the aircraft to cover the distance corresponding to the length of the previous level in its entirety, before descending to the next level. 
     The advantage of displaying a maximum descent slope  8  becomes apparent, for example, when the aircraft  6  must adhere to a maximum altitude which changes during the journey. When changing flight level, pilots must begin the descent at the appropriate time, firstly in order to avoid passing above the next level if that level is lower than the previous level and second to avoid descending too soon.