• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    - The device (10) comprises a display unit (11) configured to display, on at least one display screen (12) of the cockpit, indications relating to the operation and at least the current engine speed (15). said engine (1A, 1B) of the aircraft (AC), as well as a set (20) of graphic elements comprising at least one graphic element (21), the at least one graphic element (21) being configured to be able to be actuated and activated by an operator to control at least one engine speed, said graphics unit (20) comprising at least one selection graphics element (22) configured to control the transition from the current engine speed (15) to at a preconfigured engine speed (31).
    公开号:FR3028498A1
    申请号:FR1461038
    申请日:2014-11-14
    公开日:2016-05-20
    发明作者:Brice Fernandez
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    [0001] The present invention relates to a device for controlling a thrust regime of at least one engine of an aircraft, in particular a transport aircraft. It is known that, in many aircraft, especially those intended for civil transport, engine speeds are likely to be controlled individually, during a flight (consisting in particular of the take-off, climb, cruise, descent phases and approach), by throttle control levers respectively associated with said engines. The information concerning the speed of these engines is retransmitted to the pilot of the aircraft through at least one information screen located in the cockpit of the aircraft. These levers are located on the central pylon next to the pilot in order to be easily operated by the pilot, while the screen is located in front of the driver so as to be seen by the latter. This disparity in location between the joysticks and the information screen requires the pilot to visually check two distinct places on the cockpit, in particular at each change of engine speed: the place where the joysticks are located. and the place where the information screen is located. Thus, the comfort of the pilot, when controlling the engine thrust regime of the aircraft, may not be optimal. The present invention relates to a device for controlling a thrust regime, said engine speed, of at least one engine of an aircraft, including a transport aircraft, to overcome this drawback. For this purpose, said device comprising a display unit configured to display on at least one display screen of the cockpit indications relating to the operation and at least the current engine speed of said engine of the aircraft, is remarkable, according to the invention, in that said display unit is further configured to display, on said screen, a set of graphic elements comprising at least one graphic element, said graphic element (s) being configured to be able to be activated and activated by an operator for controlling at least one engine speed, said set of graphical elements including at least one graphic selection element 3028498 2 configured to control the transition from the current engine speed to a preconfigured engine speed. Thus, thanks to the invention, the control for adjusting the thrust ratio of the engines of the aircraft and the information concerning these speeds are managed and presented via the same screen. The pilot can then change the speed and control that the change has been made through the same interface located at a single location on the cockpit, which overcomes the disadvantage mentioned above. According to various embodiments of the invention, which can be taken together or separately: said screen is a touch screen on which said set of graphic elements is displayed, each of said graphic elements being able to be actuated by direct contact on said touch screen at the location of said graphic element; The one or more selection graphic elements are configured to select, respectively, at least one of the following preconfigured motor speeds: an idle speed; - a continuous maximum thrust regime; A reduced take-off speed; - an idle go-around mode; - a maximum take-off and go-around regime; a climb phase regime of the aircraft; an intermediate speed of automatic regulation of the engine speed; the device is configured to control the speed of at least two engines, wherein said selection graphic element is configured to control the transition from the current engine speed to a preconfigured engine speed for all said engines; The device is configured so that, in the event of a situation limiting the speed of a first of the engines at a limit speed, the activation of a selection graphic element corresponding to an engine speed greater than the limit speed, 3028498 3 the change from the current engine speed to the limit speed for this first engine and to the higher engine speed corresponding to said graphic selection element activated for the other engine; - The device is configured to, in case of failure of one of the five engines, automatically control the increase of the engine speed of at least one of the engines; the set of graphic elements comprises at least one movable graphic element displaceable on the screen by an operator and configured to control the transition from the current engine speed to any engine speed defined between a minimum engine speed and an engine speed. maximum engine speed and depending on the position on the screen of said mobile graphic element; the device is configured to control the speed of at least two motors, the set of graphic elements comprising a graphic activation element by motor, each of the graphic activation elements being configured to be actuated so as to select independently for each engine, a guided speed control mode or an automatic speed control mode; said display unit is configured to display at least one of the following indications relating to the operation of the motor: a current engine speed; - a mode of change of engine speed; - the level of at least one preconfigured engine speed; - the difference between a selected engine speed and the current engine speed; A percentage value of the current engine speed with respect to a maximum theoretical engine speed; - an automatic or guided mode of operation. The invention also relates to a method for controlling a thrust regime of at least one engine of an aircraft, using a device as previously specified. The method is remarkable, according to the invention, in that it consists in operating at least one graphic element displayed on the screen of the display unit 3028498 4 of said device, the actuation of a graphic element controlling a corresponding engine speed. Furthermore, the invention also relates to an aircraft, in particular a transport aircraft, which comprises a device for controlling a thrust regime of at least one engine of the aircraft, as described above. The appended figures will make it clear how the invention can be realized. In these figures, identical references designate similar elements. FIG. 1 diagrammatically shows a twin-engine aircraft in view from above, as well as a device for controlling a thrust regime of at least one engine of the aircraft, represented on the outside of said aircraft for the purposes of FIG. 2a, 2b and 2c schematically represent the device of FIG. 1, illustrating an engine speed control at take off from the aircraft.
    [0002] FIGS. 3a, 3b and 3c schematically represent the device of FIG. 1, illustrating an engine speed control between a current engine speed and a maximum engine speed. Figures 4a, 4b and 4c show schematically the device of Figure 1, illustrating a control engine speed in the navigation phase (4a), 20 descent (4b) and slight go-around (4c). FIGS. 5a, 5b and 5c show schematically the device of FIG. 1, illustrating an engine speed control during the climb phase of the aircraft. Figures 6a and 6b schematically show the device of Figure 1 illustrating engine speed control when engine speed is limited. Figure 7 schematically shows the device of Figure 1, illustrating a control engine speed when the aircraft is on the ground. FIG. 1 shows, in a view from above, an AC aircraft, in particular a transport aircraft, comprising two engines 1A and 1B suspended at each of its two wings 2, symmetrically with respect to the fuselage 3 of the aircraft AC of longitudinal axis XX.
    [0003] The engine speed 1A and 1B of the aircraft AC can be controlled via a device 10. As shown in FIG. 1, this device 10 comprises a display unit 11 configured to display, on a less a display screen 12 5 installed in the cockpit, indications relating to operation and at least the current engine speed 15 of the engine (s) of the aircraft AC. The device 10 makes it possible to control the engine speed of the two motors 1A and 1B shown diagrammatically on the screen 12. According to the invention, said display unit 11 is further configured to simultaneously display on the screen 12 a set Graphical elements comprising at least one graphic element 21, said graphic element (s) being configured to be operable and activated by an operator so as to control at least one engine speed of one engine and the two engines 1A and 1B in the example under consideration.
    [0004] In a preferred embodiment, the screen 12 is a touch screen on which the set of graphics is displayed. Each of the graphic elements 21 of the assembly 20 is capable of being actuated by direct contact on the screen 12 (touch) at the location of said graphic element 21. Preferably, the graphic elements 21 are controlled by a digital contact of The operator, a hand 27 is shown schematically in Figure 1 for illustration (in connection with several graphical elements 21). In another embodiment, the device 10 further comprises control units (not shown), which are connected to the screen 12 (by a usual wired or electromagnetic wave link) and which may be actuated by an operator to control the movement of a conventional cursor for acting on the graphics 21 and / or the displacement of some of these graphics 21. The display unit 11 is configured to display on the display screen 12 at least one of the following indications, specified below and relating to the operation of at least one of the motors 1A and 1B: the current engine speed; a mode of selective engine speed change 31; 302 84 98 6 - a mode of change of mobile engine speed 32; a level of preconfigured engine speeds 34; a difference 60 between a selected engine speed and the current engine speed; 5 - a value 37, as a percentage, of the current engine speed with respect to a maximum theoretical engine speed; and - an automatic or guided mode of operation. The device 10 makes it possible to control the engine speeds in guided mode or in automatic mode, each engine 1A, 1B being independently managed. The device 10 comprises for this purpose a graphic activation element 38, 39 by motor 1A, 1B. Each of the activation graphics 38 and 39 is configured to be operated to independently select, for each motor, a guided speed control mode or an automatic speed control mode. In the example illustrated in FIG. 1, the motor 1A located on the left in FIG. 1 is in guided mode, while the motor 1B located on the right in FIG. 1 is in automatic mode. The guided mode allows the operator to choose the engine speed that he wants to apply to the engine, while the automatic mode uses an onboard computer to automatically change the engine speed in particular based on current flight data. Each of the activation graphic elements 38 and 39 makes it possible to activate the automatic mode or the guided mode independently for each engine. The set of graphic elements comprises at least one movable graphic element 23a, 23b displaying the current regime. The graphic element 23a, 23b is movable on the screen 12 by the operator and configured to control the passage of the current engine speed to any engine speed. Any such engine speed is defined between a minimum engine speed IDLE 41 and a maximum engine speed TOGA 45 and depends on the position of said movable graphic element 23a, 23b on the screen 12. This mode of operation is illustrated in FIG. the control of the engine speed of the engine 1A. The operator can move the mobile graphic element 23a, 23b where he wishes between the minimum speed IDLE 41 and the maximum speed TOGA 45 by contact on the screen 12 at the level of the engine speed value that he wishes. give to the engine. In other words, the engine speed is represented on a scale of values, the selection of a point of the scale of values between the minimum and the maximum (for example 50%) causes a change of the value of the engine speed to arrive at the level which corresponds to the point of the selected scale. To do this, the operator can move the mobile graphic element 23a, 23b by moving his hand on the screen 12, as shown in FIG. 1, or by using a slider or a wheel that is part of a control unit (not shown) as previously indicated.
    [0005] The graphic element set 20 comprises at least one selection graphic element 22 configured to control the transition from the current engine speed to one of the preconfigured engine speeds 31. Thus, when the operator selects and activates the engine In selection graphical element 22, the engine speed changes from the current engine speed 15 to the preconfigured engine speed 31 which corresponds to the selection graphic element 22 thus activated. The selection graphic element (s) 22 are configured to select, respectively, at least some of the following preconfigured engine speeds: - Idle speed ("IDLE" in English) 41; A maximum continuous thrust regime MCT 42 ("Maximum Continuous Thrust"); - a reduced thrust take-off speed FLEX TO ("Flexible Take Off" in English); an idle go-around GA SOFT ("Go Around Soft" in English); - the maximum take-off and go-around regime TOGA 45 ("Take Off Go Around"); a climb phase regime of the aircraft CLB ("Climb" in English); an intermediate speed A / THR (Automatic Thrust) for automatic regulation of the engine speed. The activation of a selection graphical element 22 causes the engine speeds of the two motors 1A and 1B of the aircraft AC to change to the selected preconfigured engine speed. Thus, using a single graphic element, the operator changes the engine speed of two engines 1A and 1B of the aircraft AC. The set of graphic elements also comprises a graphic limiting element 28 indicating the maximum engine speed that each of the motors 1A and 1B can reach, which correspond in FIG. 1 to the maximum speed TOGA 45. FIGS. 2a, 2b and 2c schematically represent the device 10, illustrating the control of the engine speed of the engines 1A and 1B at takeoff of the aircraft AC. In these figures, the automatic mode is selected by virtue of the activation of the activation graphic elements 38 and 39. In FIG. 2a, the value 37 of the current engine speed of the two motors 1A and 1B is 25% and passes automatically at the preconfigured speed FLEX TO 43, as shown in Figure 2b, corresponding to a value 37 of the engine speed of 75%. The device 10 also displays the difference between the target engine speed (FLEX 15 TO) and the current engine speed (25%) by arrows referenced 60. In the event of a motor failure 1A while the engine speeds are at the preconfigured speeds FLEX TO 43, as illustrated in Figure 2b, it is possible to increase the engine speed of the engine 1B which continues to operate, guided or automatic (Figure 2c). The device 10 then indicates that one of the motors 1A has failed through a graphical failure element 35. FIGS. 3a, 3b and 3c schematically represent the device 10, illustrating the control of the engine speed between the engine and the engine. motor 15 and a maximum engine speed TOGA 45. In these figures, the automatic mode is selected by activating the activation graphic elements 38 and 39. In FIG. 3a, the value 37 of the engine speed of the two engines is at 25% and automatically switches to the preconfigured TOGA 45 engine speed corresponding to a value of 98.5% as illustrated in FIG. 3b. The device 10 also displays the difference between the target engine speed (TOGA) and the current engine speed (25%) by arrows referenced 60. In the event of a failure of a 1A of the engines, the engine speed of the engine 1B which continues The operation can remain on the maximum speed TOGA 45, as illustrated in FIG. 3c. Figures 4a, 4b and 4c show schematically the device of Figure 1, illustrating the control of the engine speed in the navigation phase (Figure 4a), descent (Figure 4b) and slight go-around (Figure 4c). In these figures, the automatic mode is selected by activating the activation graphic elements 38 and 39. In FIG. 4a, representing a steady-state engine speed, the value 37 of the engine speed of the two engines 1A and 1B is located at 82%. In the automatic mode of operation, this value may vary depending on the flight data, in particular current values of AC aircraft parameters, engines 1A and 1B and / or the environment. FIG. 4b illustrates an example of a descent phase of the aircraft AC. The engine speed of the two motors 1A and 1B then goes down to the minimum speed IDLE 41 automatically. FIG. 4c illustrates the activation of a preconfigured GA SOFT 44 regime, making it possible to increase the engine speed in a gentle manner if necessary. FIGS. 5a, 5b and 5c schematically represent the device 10, illustrating the control of the engine speed during the climb phase of the aircraft AC. In FIG. 5a, the preconfigured engine speed CLB 46 is activated. The value 37 of the engine speed is then, for example, 75%. In case of failure of a 1A of the engines as shown in Figure 5b, the engine speed of the other engine 1B can increase automatically to go from the engine speed CLB 46 MCT 42 as shown in Figure 5c. The device 10 also displays the difference between the target engine speed MCT 42 and the current engine speed CLB 46 by arrows referenced 60. FIGS. 6a and 6b schematically represent the device 10, illustrating the control of the engine speed, when the engine speed one of the engines is limited. As can be seen in FIG. 6a, the engine speed of the engine 1A is limited and the screen 12 indicates this information via the limiting graphic element 28, notably thanks to its positioning on the screen 12. activation of a selection graphical element 22 corresponding to a higher engine speed than the limit speed, then causes: - the transition from the current engine speed 15 to the limit speed for the first engine 1A; the passage from the current engine speed 15 to the preconfigured engine speed 31 corresponding to said selected graphic selection element 22, 5 for the other engine 1B. On the other hand, if the preconfigured engine speed 31 corresponding to said activated selection graphic element 22 is below the limit, as illustrated in FIG. 6b, the engine speed of the two motors 1A and 1B will be identical.
    [0006] FIG. 7 schematically represents the device 10, illustrating the control of the engine speed of the engines 1A and 1B when the aircraft AC is on the ground. The operator has the choice of the type of engine speed he wants for take-off, for example the FLEX TO 43 engine speed or the TOGA 45 engine speed.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Device for controlling a thrust regime of at least one engine (1A, 1B) of an aircraft (AC), said engine speed, said device (10) comprising a display unit (11) configured to display on at least one display screen (12) of the cockpit, indications relating to the operation and at least the current engine speed (15) of said engine (1A, 1B) of the aircraft (AC), characterized in that said display unit (11) is further configured to display simultaneously on said screen (12) a set (20) of graphic elements comprising at least one graphic element (21), said one or more graphic elements (21). ) being configured to be operable and actuated by an operator to control at least one engine speed, said graphics unit (20) including at least one selection graphics element (22) configured to control the engine speed changeover current (15) to a motor speed unconfigured (31).
    [0002]
    2. Device (10) according to claim 1, wherein said screen (12) is a touch screen (12) on which is displayed said set (20) of graphic elements, each of said graphic elements (21) being capable of be operated by direct contact on said touch screen (12) at the location of said graphic element (21).
    [0003]
    3. Device (10) according to one of claims 1 or 2, wherein said one or more graphical selection elements (22) are configured to select, respectively, at least one of the following engine speeds preconfigured: - idle speed (41); a continuous maximum thrust regime (42); a reduced thrust take-off regime (43); - idle restart mode (44); - a maximum take-off and overshoot regime (45); a climb phase regime of the aircraft (46); - an intermediate speed of automatic regulation of the engine speed. 3028498 12
    [0004]
    A device (10) according to any one of the preceding claims, said device (10) being configured to control the speed of at least two motors (1A, 1B), said graphic selection element (22) is configured to control switching from the current engine speed (15) to a pre-configured engine speed (31) for all said engines (1A, 1B).
    [0005]
    5. Device (10) according to claim 4, said device (10) being configured so that in case of situation limiting the speed of a first (1A) of the motors (1A, 1B) to a limit regime, the activation a selection graphical element (22) corresponding to an engine speed greater than the limit speed, causes the passage 10 of the current engine speed (15) up to the limit speed for this first engine (1A) and up to the upper engine speed corresponding to said selection graphic element (22) activated for the other engine (1B).
    [0006]
    6. Device (10) according to claim 4, said device (10) being configured to, in case of failure of a first (1A) of the motors (1A, 1B), automatically control the increase of the engine speed of at least one other (1B) engine.
    [0007]
    7. Device (10) according to any one of the preceding claims, wherein the set (20) of graphic elements comprises at least one movable graphic element (23a, 23b) movable on the screen (12) by an operator 20 and configured to control the transition from the current engine speed (15) to any engine speed, defined between a minimum engine speed (41) and a maximum engine speed (45) and dependent on the position on the screen (12). ) of said movable graphic element (23a, 23b).
    [0008]
    Apparatus (10) according to any one of the preceding claims, said device (10) being configured to control the speed of at least two motors (1A, 1B), wherein said set (20) of graphic elements comprises a graphics activation element (38, 39) by motor (1A, 1B), each of the graphic activation elements (38, 39) being configured to be actuated to select independently for each motor (1A) , 1B), a guided speed control mode or an automatic speed control mode. 3028498 13
    [0009]
    The device (10) according to any one of the preceding claims, wherein said display unit (11) is configured to display at least one of the following indications relating to the operation of the motor (1A, 1B): a current engine speed (15); A mode of change of engine speed (31, 32); a level of at least one preconfigured engine speed (34); a difference (60) between a selected engine speed and the current engine speed; a value (37), in percentage, of the current engine speed (15) with respect to a maximum theoretical engine speed; - an automatic or guided mode of operation.
    [0010]
    A method of controlling a thrust regime of at least one engine (1A, 1B) of an aircraft (AC), using a device (10) as specified in any one of Claims 1 to 9, characterized in that it consists in actuating at least one graphic element (21) displayed on the screen (12) of the display unit (11) of said device (10), the actuation a graphic element (21) controlling a corresponding engine speed.
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    同族专利:
    公开号 | 公开日
    US20160137307A1|2016-05-19|
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    引用文献:
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    法律状态:
    2015-11-19| PLFP| Fee payment|Year of fee payment: 2 |
    2016-05-20| PLSC| Publication of the preliminary search report|Effective date: 20160520 |
    2016-11-18| PLFP| Fee payment|Year of fee payment: 3 |
    2017-11-21| PLFP| Fee payment|Year of fee payment: 4 |
    2018-11-23| PLFP| Fee payment|Year of fee payment: 5 |
    2019-11-20| PLFP| Fee payment|Year of fee payment: 6 |
    2020-11-20| PLFP| Fee payment|Year of fee payment: 7 |
    2021-11-22| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1461038A|FR3028498B1|2014-11-14|2014-11-14|DEVICE FOR CONTROLLING A PUSHING REGIME OF AT LEAST ONE AIRCRAFT ENGINE.|
    FR1461038|2014-11-14|FR1461038A| FR3028498B1|2014-11-14|2014-11-14|DEVICE FOR CONTROLLING A PUSHING REGIME OF AT LEAST ONE AIRCRAFT ENGINE.|
    US14/940,433| US20160137307A1|2014-11-14|2015-11-13|Device for controlling a thrust of at least one aircraft engine|
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