초록 ▼

A human machine interface linked to the throttle lever of an aircraft used to control the energy of an aircraft is disclosed. The HMI has upper part, which corresponds to the forward stroke of the lever, and a lower part, which corresponds to the rearward stroke of the lever. An upper shutter is pos

A human machine interface linked to the throttle lever of an aircraft used to control the energy of an aircraft is disclosed. The HMI has upper part, which corresponds to the forward stroke of the lever, and a lower part, which corresponds to the rearward stroke of the lever. An upper shutter is positioned over the upper part, and a lower shutter is positioned over the lower part. A “cursor” acts as a visual representation in the HMI of the lever and its handle. The cursor moves forward or backward as the pilot acts on the lever/handle. The cursor indicates an ordered release of more or less aircraft energy, depending on its position on the display. The upper and lower shutters also indicate the ordered release of more or less aircraft energy, depending on the respective lengths of the two shutters. The HMI also includes a column in the display having a length symbolizing a current value in actual aircraft push or braking, depending on whether an aircraft push or braking has been ordered by releasing of more or less aircraft energy. The column changes in length as the actual aircraft push or braking changes. The cursor is further depicted in the HMI display as containing a memorizing button on the handle and a Go-Lever button on the lever below the handle.

대표청구항 ▼

1. An interface for displaying information relative to the energy of an aircraft, the interface being a display comprising: a cursor symbolizing and corresponding to a lever handled by a pilot to control the energy of the aircraft,a first part corresponding to a first direction in which the lever is

1. An interface for displaying information relative to the energy of an aircraft, the interface being a display comprising: a cursor symbolizing and corresponding to a lever handled by a pilot to control the energy of the aircraft,a first part corresponding to a first direction in which the lever is moved to increase the energy of the aircraft,a second part corresponding to a second direction in which the lever is moved to decrease the energy of the aircraft,a neutral position located between the first and second parts,the cursor being movable so as to follow actual strokes of the lever to increase or decrease the energy of the aircraft, and to return to the neutral position in the race when the lever is not being handled,a first shutter positioned over the first part of the display which changes in length as the cursor moves in the first part of the display, the length of the first shutter symbolizing an ordered value in the increase in the energy of the aircraft,a second shutter positioned over the second part of the display which changes in length as the cursor moves in the second part of the display, the length of the second shutter symbolizing an ordered value in the decrease in the energy of the aircraft,a first column having a length symbolizing a current value in actual aircraft push, the first column changing in length as the actual aircraft push changes and the length of the first shutter changes in response to the ordered value in the increase in the energy of the aircraft,a second column having a length symbolizing a current value in actual aircraft braking, the second column changing in length as the actual aircraft braking changes and the length of the second shutter changes in response to the ordered value in the decrease in the energy of the aircraft, anda plurality of switches, including one for memorizing a selected aircraft push or aircraft deceleration when the lever is operated in a manual mode, and for setting a range of authority when the lever is operated in an automatic mode, and one which enables automatic triggering of a flight phase change when the lever is operated in an automatic mode. 2. The interface according to claim 1, wherein the first part includes a first scale to provide measures of ordered and actual values in the increase in the energy of the aircraft, and wherein the second part includes a second scale to provide measures of ordered and actual values in the decrease in the energy of the aircraft. 3. The interface according to claim 2, wherein the first scale depicts ordered values in the increase in the energy of the aircraft and actual values of aircraft push as percentages of a maximum limit in aircraft energy, and wherein the second scale depicts ordered values in the decrease in the energy of the aircraft and actual values of aircraft braking as percentages of a minimum limit in aircraft energy. 4. The interface according to claim 3, wherein the display further comprises third and fourth shutters which indicate maximum and minimum limits in aircraft energy. 5. The interface according to claim 1, wherein the plurality of switches are a memorizing button on a handle at an end of the lever for initiating a memorizing function in which an ordered increase or decrease in the energy of the aircraft is memorized when the lever is operated in a manual mode, or the range of authority is set in which the energy of the aircraft can increase or decrease when the lever is operated in an automatic mode, and a Go-Lever button on the lever which enables the automatic triggering of the flight phase change when the lever is operated in the automatic mode, and wherein the memorizing button is depicted in an ON position when a memorizing function is activated. 6. The interface according to claim 5, wherein the interface display further comprises a mark that is added to the first or second part of the display which symbolizes the ordered increase or decrease, respectively, in the energy of the aircraft corresponding to the position of the lever when the lever is operated in the manual mode, the mark serving to block the first or second shutter, respectively, when the lever is released and the cursor return to the neutral position, and wherein the interface display further comprises a range indicator that is added to the first and/or second part of the display which symbolizes the range of authority in which the energy of the aircraft can increase or decrease, respectively, when the lever is operated in the automatic mode. 7. The interface according to claim 1, wherein the neutral position is identified on the display with an IDLE label. 8. The interface according to claim 6, wherein when a selected automatic mode (ATHR) of operation of the aircraft is selected, the memorizing button is depicted in an OFF position and the Go-Lever button is depicted as including an acronym associated with a mode of aircraft operation, wherein the range display is depicted with first and second bars added to the first or second part of the display with one bar at the neutral position and the other bar at the value ordered by the automatic mode in the increase or decrease, respectively, in the energy of the aircraft, and wherein the range display further includes a flag symbol indicating the value in the increase or decrease in the energy of the aircraft ordered by the automatic mode, and either a reduction in width of the second shutter to prevent the cursor from ordering a brake value where the automatic mode has ordered an increase in aircraft energy or of the first shutter to prevent the cursor from ordering a push value where the automatic mode has ordered a decrease in aircraft energy. 9. The interface according to claim 8, wherein when during a selected automatic mode of operation the cursor goes back to the neutral position, the memorizing button is depicted in an ON position, and the second bar of the range display widens until either a limit of the second shutter is reached where the cursor is positioned in the first part of the display so as to have ordered an increase in aircraft power, thereby making it possible for the pilot to extend the range of the automatic mode such that the second bar of the range is positioned in the second part of the display. 10. The interface according to claim 8, wherein when during takeoff the pilot presses a takeoff (T/O) button on the lever, the acronym depicted on the Go-Lever button is take off (T/O) and a symbol associated with an automatic push mode is displayed in the first part to indicate the value ordered by the automatic push mode to increase aircraft energy to a level corresponding to a mode “FLEX”, the first shutter is reduced in length so as to be automatically placed at the value ordered by the automatic push mode, the second and fourth shutters are changed in length so as to be placed respectively at positions to be reached to activate RTO “software” and RTO “MAX” modes of operation, and notches are placed on the second part of the display to present exact positions for activation of the RTO “software” and RTO “MAX” modes of operation. 11. The interface according to claim 8, wherein the display includes a second acronym indicating a mode of operation of the aircraft when the lever is operated in automatic mode. 12. The interface according to claim 4, wherein all of the shutters are delineated in the interface display through the use of different colors for each of the shutters or different shades of a color for each of the shutters versus portions of the first and second parts of the display not covered by the shutters. 13. An human machine interface (HMI) for displaying information relative to the energy of an aircraft, the interface being a vertical display comprising: a cursor symbolizing a lever handled by a pilot to control the energy of the aircraft,a race includingan upper part corresponding to a forward direction in which the lever is moved to increase the energy of the aircraft,a lower part corresponding to a reverse direction in which the lever is moved to decrease the energy of the aircraft, andan idle position located between the upper and lower parts,the cursor being movable so as to follow actual strokes of the lever to increase or decrease the energy of the aircraft, and to return to the idle position in the race when the lever is not being handled,an upper shutter positioned over the upper part of the race which changes in length as the cursor moves in the upper part of the race, the length of the upper shutter symbolizing an ordered value in the increase in the energy of the aircraft,a lower shutter positioned over the lower part of the race which changes in length as the cursor moves in the lower part of the race, the length of the lower shutter symbolizing an ordered value in the decrease in the energy of the aircraft,an upper column having a height symbolizing a current value in actual aircraft push, the upper column changing in height as the actual aircraft push changes and the length of the upper shutter changes in response to the ordered value in the increase in the energy of the aircraft,a lower column having a height symbolizing a current value in actual aircraft braking, the lower column changing in height as the actual aircraft braking changes and the height of the lower shutter changes in response to the ordered value in the decrease in the energy of the aircraft, anda memory button for a selected aircraft push or aircraft deceleration when the lever is operated in a manual mode, and for a range of authority when the lever is operated in an automatic mode, and a Go-Lever button which enables automatic triggering of a flight phase change. 14. The HMI according to claim 13, wherein the vertical display includes a scale to provide measures of ordered and actual values in the increase and decrease in the energy of the aircraft. 15. The HMI according to claim 14, wherein the scale depicts ordered values in the increase and decrease in the energy of the aircraft and actual values of aircraft push as percentages of a maximum limit in aircraft energy, and actual values of aircraft braking as percentages of a minimum limit in aircraft energy. 16. The HMI according to claim 13, wherein the display further comprises second upper and lower shutters which indicate respectively the maximum and minimum limits in aircraft energy. 17. A human machine interface (HMI) for displaying information relative to the energy of an aircraft, the interface being a display comprising: a depiction of a lever handled by a pilot to control the energy of the aircraft,a depiction of a race within which the lever moves as the lever handled by the pilot is moved,indications of a maximum limit of aircraft acceleration and of a minimum limit of aircraft deceleration of the race within which the lever moves,a depiction of a plurality of buttons, including (1) a memory button for (i) a selected aircraft push or aircraft deceleration when the lever is operated in a manual mode, and (ii) for a range of authority when the lever is operated in an automatic mode, and (2) and a Go Lever which enables automatic triggering of a flight phase change, including: (i) takeoff when the aircraft is aligned for doing so, and (ii) a go-around when the aircraft is in a landing approach phase,indications of a current, actual value of aircraft forward thrust and a current, actual value of aircraft backward air deceleration or ground braking,an indication of controlled values, when the lever is operated in a manual mode, of aircraft forward thrust and of aircraft backward air deceleration or ground braking, and when the lever is operated in automatic mode, of aircraft forward thrust and of aircraft backward air deceleration or ground braking,an indication of a range of authority allocated to forward maximum thrust and backward maximum deceleration, andan indication of activated automatic modes. 18. The HMI according to claim 17, wherein the activated automatic modes are selected from TOGA, Flex, Climb, Self-delay, Brake-To-Vacate (BTV), Max rejected takeoff (RTO) braking, and Soft RTO optimized braking. 19. The HMI according to claim 18, wherein (i) TOGA is an automatic mode of application of maximum thrust (TOGA thrust); (ii) Flex is an automatic mode using a reduced thrust during takeoff or during go-around compared to the maximum thrust (TOGA); (iii) Climb is an automatic mode using a reduced thrust for the climbing phase compared to the maximum thrust (TOGA); (iv) Self-delay is an automatic mode to reduce the thrust toward the IDLE level during the flare-out phase on landing; (v) Brake-To-Vacate (BTV) is an automatic braking mode to reach an exit ramp at an adequate speed while optimizing runway occupation time and brake wear; (vi) Max rejected takeoff (RTO) braking is a mode which uses all the aircraft's braking capacity following cancellation of take-off; and (vii) Soft RTO optimized braking is a mode following a take-off cancellation. 20. A system for displaying information relative to the energy of an aircraft, the system comprising: a control unit,a control interface linked to the control unit by a first link, the control interface being connected to a lever by which a pilot increases and decreases aircraft energy by a plurality of sensors,a display device linked to the control unit by a second link, the display device including a display comprising:a cursor symbolizing a lever handled by a pilot to control the energy of the aircraft,a race includingan upper part corresponding to a forward direction in which the lever is moved to increase the energy of the aircraft,a lower part corresponding to a reverse direction in which the lever is moved to decrease the energy of the aircraft, andan idle position located between the upper and lower parts,the cursor being movable so as to follow actual strokes of the lever to increase or decrease the energy of the aircraft, and to return to the idle position in the race when the lever is not being handled,an upper shutter positioned over the upper part of the race which changes in length as the cursor moves in the upper part of the race, the length of the upper shutter symbolizing an ordered value in the increase in the energy of the aircraft,a lower shutter positioned over the lower part of the race which changes in length as the cursor moves in the lower part of the race, the length of the lower shutter symbolizing an ordered value in the decrease in the energy of the aircraft,an upper column having a height symbolizing a current value in actual aircraft push, the upper column changing in height as the actual aircraft push changes and the length of the upper shutter changes in response to the ordered value in the increase in the energy of the aircraft,a lower column having a height symbolizing a current value in actual aircraft braking, the lower column changing in height as the actual aircraft braking changes and the height of the lower shutter changes in response to the ordered value in the decrease in the energy of the aircraft, anda memory button for a selected aircraft push or aircraft deceleration when the lever is operated in a manual mode, and for a range of authority when the lever is operated in an automatic mode, and a Go-Lever button which enables automatic triggering of a flight phase change. 21. The system according to claim 20, wherein the display further includes a scale to provide measures of ordered and actual values in the increase and decrease in the energy of the aircraft. 22. The system according to claim 21, wherein the scale depicts ordered values in the increase and decrease in the energy of the aircraft and actual values of aircraft push as percentages of a maximum limit in aircraft energy, and actual values of aircraft braking as percentages of a minimum limit in aircraft energy. 23. The system according to claim 22, wherein the display further comprises second upper and lower shutters which indicate respectively the maximum and minimum limits in aircraft energy.