CN115407796A - Thrust change guidance method and device for aircraft and storage medium - Google Patents
Thrust change guidance method and device for aircraft and storage medium Download PDFInfo
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- CN115407796A CN115407796A CN202211073529.7A CN202211073529A CN115407796A CN 115407796 A CN115407796 A CN 115407796A CN 202211073529 A CN202211073529 A CN 202211073529A CN 115407796 A CN115407796 A CN 115407796A
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- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course or altitude of land, water, air, or space vehicles, e.g. automatic pilot
- G05D1/10—Simultaneous control of position or course in three dimensions
- G05D1/101—Simultaneous control of position or course in three dimensions specially adapted for aircraft
Abstract
The invention discloses a thrust change guiding method, a device and a storage medium for an aircraft, wherein the method comprises the following steps: generating a thrust change guide comprising a thrust target value, a throttle lever moving direction and a current thrust actual value based on the thrust change instruction; when the thrust target value is different from the current thrust actual value, displaying a plurality of symbols on a display screen to guide a pilot to operate a throttle stick of the aircraft; and updating the current thrust actual value and the display positions of the symbols in real time along with the control of the pilot on the throttle stick until the thrust target value is equal to the current thrust actual value. The technical scheme provided by the invention can solve the technical problem that in the prior art, when the automatic accelerator is unavailable or a pilot is not connected with the automatic accelerator, the pilot can only operate the throttle stick by experience, and the invention can provide thrust guidance for the pilot, help the pilot to operate the throttle stick more accurately, improve the accuracy of airplane speed control and save fuel consumption.
Description
Technical Field
The invention relates to the technical field of airplane control, in particular to a thrust change guiding method and device for an aircraft and a storage medium.
Background
With the birth and development of airplanes, airplane flight control becomes an important technical field of control engineering. The early airplane has simple structure, low performance requirement and simple flight control, and along with the continuous improvement of the airplane performance, the flight task is increasingly complex, particularly the appearance of a fighter with high speed and high maneuverability and a large-scale high-altitude and long-range transporter, the airplane is more widely applied, and the requirement on the flight control is higher and higher.
The flight control of the airplane is divided into manual control and automatic control. Manual operation means that a pilot operates a control surface and a throttle lever through an on-machine mechanical operation system to control the flight of the airplane. The automatic control means that the flight of the airplane is automatically controlled by controlling a control surface and an accelerator lever through a flight automatic control system. The purpose of flight control is to complete the flight task by stabilizing and controlling the attitude motion and the mass center motion of the aircraft. When the airplane is controlled through manual operation, a pilot operates a control plane and a power device of the airplane through an onboard manual operation system to control the flight of the airplane.
In the prior art, most of the aircraft types of the civil aircraft on active service do not have the function of providing thrust guidance, when the automatic throttle is unavailable or a pilot is not connected with the automatic throttle, the aircraft control system cannot provide thrust guidance for the pilot, the pilot can only rely on the experience of the pilot to manually control the throttle stick, on one hand, the pilot is required to have rich experience, on the other hand, the accuracy and the timeliness of speed control can have certain difference, and the fuel consumption of the aircraft can be increased.
Disclosure of Invention
The invention provides a thrust change guiding method, a device and a storage medium for an aircraft, and aims to effectively solve the technical problem that in the prior art, when an automatic throttle is unavailable or a pilot is not connected with the automatic throttle, the pilot can only operate a throttle lever by experience.
According to an aspect of the present invention, there is provided a thrust alteration guidance method for an aircraft, the method comprising:
s1, generating thrust change guidance based on a thrust change instruction, wherein the thrust change guidance comprises a thrust target value, a throttle lever moving direction and a current thrust actual value;
s2, under the condition that the thrust target value is different from the current thrust actual value, displaying a first symbol indicating the thrust target value, a second symbol indicating the current thrust actual value and a third symbol indicating the motion direction of the throttle lever at different positions of a display screen so as to guide a pilot to control the throttle lever of the aircraft according to the displayed motion direction of the throttle lever;
and S3, updating the current thrust actual value in real time along with the control of the pilot on the throttle lever, and changing the relative display positions of the first symbol, the second symbol and the third symbol according to the difference value between the current thrust actual value and the thrust target value until the thrust target value is the same as the current thrust actual value, blanking the third symbol and enabling the first symbol and the second symbol to be displayed in the same position in an overlapping mode.
Further, the method further comprises:
and before generating a thrust change guide based on the thrust change instruction, acquiring an automatic accelerator on-state parameter, determining the state of an automatic accelerator function according to the automatic accelerator on-state parameter, and generating the thrust change instruction when the automatic accelerator function is in an inactivated state or an unavailable state.
Further, the generating the thrust force change instruction includes:
receiving a preselected thrust level and a manual thrust level sent by a flight management system, and receiving an N1 reference value and a throttle lever N1 instruction sent by a full-weight digital engine control device;
acquiring a first speed target value selected by a pilot or a second speed target value corresponding to the flight management system;
determining a current thrust guidance mode according to a flight guidance vertical mode of an automatic flight system, when the thrust guidance mode is a thrust mode, determining an N1 reference value based on the preselected thrust level and the manual thrust level, generating the thrust change instruction based on the N1 reference value and the throttle lever N1 instruction, and when the thrust guidance mode is a speed mode, generating the thrust change instruction based on a speed target value, the throttle lever N1 instruction and the N1 reference value, wherein the speed target value is the first speed target value or the second speed target value.
Further, the generating the thrust force alteration command based on the N1 reference value and the throttle lever N1 command comprises:
determining the thrust target value based on the N1 reference value;
determining the current thrust actual value based on the throttle lever N1 instruction;
and generating the thrust force change instruction based on the thrust force target value and the current thrust force actual value.
Further, the generating the thrust force alteration command based on the speed target value, the throttle lever N1 command, and the N1 reference value includes:
determining a first thrust target value based on the speed target value, determining a second thrust target value based on the N1 reference value, and determining a value with a smaller value of the first thrust target value and the second thrust target value as the thrust target value;
determining the current thrust actual value based on the throttle lever N1 instruction;
and generating the thrust change instruction based on the thrust target value and the current thrust actual value.
Further, the step S2 includes:
in a case where the thrust target value is not identical to the current thrust actual value, the first symbol, the second symbol, and the third symbol are displayed at different positions on the same column of the display screen, and the third symbol is always located between the first symbol and the second symbol.
Further, the third symbol includes a first direction sub-symbol and a second direction sub-symbol, and the step S2 includes:
displaying only the first direction sub-symbol in a case where the thrust target value is greater than the current thrust actual value, and displaying only the second direction sub-symbol in a case where the thrust target value is less than the current thrust actual value.
Further, a distance between the display position of the first symbol and the display position of the second symbol is proportional to a difference between the current thrust actual value and the thrust target value.
Further, the step S3 includes:
and gradually reducing the relative distance between the display positions of the first symbol and the second symbol in the process from the current thrust actual value to the thrust target value being different to the same, wherein the relative distance is reduced in proportion to the reduction of the difference value.
Further, the step S3 includes:
when the current thrust actual value changes from being different from the thrust target value to being the same as the thrust target value, the first symbol and the second symbol are displayed in an overlapping manner.
Further, the first direction sub-symbol includes a line between the first symbol and the second symbol and an arrow indicating a first direction on the line, and the second direction sub-symbol includes a line between the first symbol and the second symbol and an arrow indicating a second direction on the line.
Further, the first symbol is a circular line and the second symbol is a straight line segment.
According to another aspect of the present invention, there is also provided a thrust alteration guidance apparatus for an aircraft, the apparatus including:
the thrust change guide generation module is used for generating thrust change guide based on a thrust change instruction, and the thrust change guide comprises a thrust target value, a throttle lever movement direction and a current thrust actual value;
the symbol display module is used for displaying a first symbol indicating the thrust target value, a second symbol indicating the current thrust actual value and a third symbol indicating the movement direction of the throttle lever at different positions of a display screen under the condition that the thrust target value is different from the current thrust actual value so as to guide a pilot to control the throttle lever of the aircraft according to the displayed movement direction of the throttle lever;
and the real-time updating module is used for updating the current thrust actual value in real time along with the control of the pilot on the throttle stick and changing the relative display positions of the first symbol, the second symbol and the third symbol according to the difference value between the current thrust actual value and the thrust target value until the thrust target value is the same as the current thrust actual value, blanking the third symbol and enabling the first symbol and the second symbol to be displayed in the same position in an overlapping mode.
According to another aspect of the present invention, there is also provided a storage medium having stored therein a plurality of instructions adapted to be loaded by a processor to perform any of the thrust alteration guidance methods for an aircraft described above.
Through one or more of the above embodiments of the present invention, at least the following technical effects can be achieved:
according to the technical scheme disclosed by the invention, when the automatic throttle is unavailable or a pilot is not connected with the automatic throttle, a thrust target value required by the aircraft is determined, a current thrust actual value is monitored in real time, a thrust change guide is generated based on the thrust target value and the current thrust actual value, the thrust guide is provided for the pilot through the display and change of a plurality of symbols, the pilot is helped to more accurately control a throttle lever in key stages such as take-off, the target speed is further accurately controlled, the workload of the pilot is further reduced, the working efficiency is improved, and the fuel consumption of the aircraft is properly reduced.
Drawings
The technical solution and other advantages of the present invention will become apparent from the following detailed description of specific embodiments of the present invention, which is to be read in connection with the accompanying drawings.
FIG. 1 is a flowchart illustrating steps of a thrust alteration guidance method for an aircraft according to an embodiment of the present invention;
FIG. 2 is a logic diagram of generating a thrust force alteration guide according to an embodiment of the present invention;
FIG. 3 is a schematic diagram of a thrust force alteration guide according to an embodiment of the present invention;
fig. 4 is a schematic diagram illustrating a variation of a thrust force modification guide according to an embodiment of the present invention;
FIG. 5 is a schematic diagram illustrating another variation of the thrust force modification guidance according to the embodiment of the present invention;
fig. 6 is a schematic structural diagram of a thrust alteration directing device for an aircraft according to an embodiment of the present invention.
Detailed Description
The technical solution in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. It should be apparent that the described embodiments are only some embodiments of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it should be noted that, unless explicitly stated or limited otherwise, the term "and/or" herein is only one kind of association relationship describing the associated object, and means that there may be three kinds of relationships, for example, a and/or B, and may mean: a exists alone, A and B exist simultaneously, and B exists alone. In addition, the character "/" in this document generally indicates that the preceding and following related objects are in an "or" relationship unless otherwise specified.
The invention discloses a thrust change guiding method, a device and a storage medium for an aircraft, in particular to a guiding mode for helping a pilot to operate an accelerator lever. The technical solution of the present invention is described below based on fig. 1 to 6.
Fig. 1 is a flowchart illustrating steps of a thrust alteration guidance method for an aircraft according to an embodiment of the present invention, where as shown in fig. 1, the thrust alteration guidance method for an aircraft includes:
the method comprises the following steps that S1, thrust change guidance is generated based on a thrust change instruction, and the thrust change guidance comprises a thrust target value, a throttle lever moving direction and a current thrust actual value;
s2, under the condition that the thrust target value is different from the current thrust actual value, displaying a first symbol indicating the thrust target value, a second symbol indicating the current thrust actual value and a third symbol indicating the movement direction of the throttle lever at different positions of a display screen so as to guide a pilot to control the throttle lever of the aircraft according to the displayed movement direction of the throttle lever;
and S3, updating the current thrust actual value in real time along with the control of the pilot on the throttle stick, and changing the relative display positions of the first symbol, the second symbol and the third symbol according to the difference value between the current thrust actual value and the thrust target value until the thrust target value is the same as the current thrust actual value, blanking the third symbol and enabling the first symbol and the second symbol to be displayed in the same position in an overlapping mode.
The purpose of flight control is to complete the flight task by stabilizing and controlling the attitude motion and the mass center motion of the aircraft. The flight control of the airplane is divided into manual control and automatic control, wherein the manual control means that a pilot controls a control surface and a throttle lever through an on-machine mechanical control system to control the flight of the airplane. When the airplane is controlled through manual operation, a pilot operates the control surface and the power device of the airplane through an onboard manual operation system to control the flight of the airplane.
In the present invention, the flight system may provide a guidance to help the pilot operate the throttle stick for some critical flight phases, such as take-off, landing, etc., in order to achieve the desired speed target more accurately and in a less time consuming manner. In order to accurately guide the pilot to operate the throttle stick, a thrust change instruction needs to be generated based on various parameters of an aircraft system.
After the thrust force change command is generated, the thrust force change guide is further generated and displayed, and the steps S1 to S3 described above will be described in detail below.
In step S1, a thrust force change direction is generated based on the thrust force change command, the thrust force change direction including a thrust force target value, a throttle lever movement direction, and a current thrust force actual value.
The thrust alteration guidance is used for guiding a pilot how to operate the throttle lever to make the running speed of the aircraft reach the optimal speed, and therefore, a thrust target value calculated based on various parameters is included in the thrust alteration guidance, a current thrust actual value at the current moment is obtained in real time, and then a throttle lever moving direction is determined based on the thrust target value and the current thrust actual value, so that the simplest thrust alteration guidance at least includes the thrust target value, the throttle lever moving direction and the current thrust actual value.
In step S2, when the thrust target value is different from the current thrust actual value, displaying a first symbol indicating the thrust target value, a second symbol indicating the current thrust actual value, and a third symbol indicating the movement direction of the throttle stick at different positions on a display screen to guide a pilot to operate the throttle stick of the aircraft according to the displayed movement direction of the throttle stick;
exemplarily, fig. 3 is a schematic diagram showing a thrust change guidance according to an embodiment of the present invention, where the automatic flight system compares two values after calculating a thrust target value and obtaining a current thrust actual value, and guides the pilot to operate the throttle stick when the current thrust actual value of the thrust target value is different, so that the thrust change guidance is shown on a display screen of a main flight display of the display system. Specifically, as shown in fig. 3, a first symbol for representing a thrust target value, a second symbol for representing a current thrust actual value, and a third symbol for representing a throttle stick movement direction are displayed at different positions on the display screen, and the pilot is guided to operate the throttle stick of the aircraft along the throttle stick movement direction by the three symbols.
In step S3, the current thrust actual value is updated in real time along with the pilot' S operation of the throttle stick, and the relative display positions of the first symbol, the second symbol, and the third symbol are changed according to the magnitude of the difference between the current thrust actual value and the thrust target value, until the thrust target value is the same as the current thrust actual value, the third symbol is blanked, and the first symbol and the second symbol are displayed in an overlapped manner at the same position.
Illustratively, after the pilot operates the throttle stick, the automatic flight system acquires a current thrust actual value of the airplane at the current moment in real time, and adjusts the relative display positions among the first symbol, the second symbol and the third symbol in real time based on the current thrust actual value to guide the pilot to adjust the thrust to a thrust target value, and when the thrust target value is the same as the current thrust actual value, the third symbol is hidden and the first symbol and the second symbol are displayed in an overlapped mode on the same position.
Further, the method further comprises:
before generating a thrust change guide based on the thrust change instruction, acquiring an automatic throttle on-state parameter, determining the state of an automatic throttle function according to the automatic throttle on-state parameter, and generating the thrust change instruction when the automatic throttle function is in an inactivated state or an unavailable state.
The invention is exemplarily applied to a specific application scenario, that is, an automatic throttle function on an airplane is not activated or available, in which a pilot can be guided by the technical solution of the invention to realize a function of thrust guidance. And before generating the thrust change guide, receiving an automatic throttle on-state parameter sent by an automatic throttle function on the airplane, wherein 1 represents on, 0 represents off or unavailable, and when the automatic throttle is unavailable or the pilot does not on the automatic throttle, providing the thrust guide for the pilot.
Further, the generating the thrust force change instruction includes:
receiving a preselected thrust level and a manual thrust level sent by a flight management system, and receiving an N1 reference value and a throttle lever N1 instruction sent by a full-weight digital engine control device;
acquiring a first speed target value selected by a pilot or a second speed target value corresponding to the flight management system;
determining a current thrust guidance mode according to a flight guidance vertical mode of an automatic flight system, when the thrust guidance mode is a thrust mode, determining an N1 reference value based on the preselected thrust level and the manual thrust level, generating the thrust change instruction based on the N1 reference value and the throttle lever N1 instruction, and when the thrust guidance mode is a speed mode, generating the thrust change instruction based on a speed target value, the throttle lever N1 instruction and the N1 reference value, wherein the speed target value is the first speed target value or the second speed target value.
Exemplarily, fig. 2 is a schematic logic diagram of generating a thrust force change direction according to an embodiment of the present invention, and as shown in fig. 2, the aircraft control system mainly includes a Flight Management System (FMS) and a full authority digital engine control device (FADEC), and further includes a display system, an air data system, and a throttle platform. The Flight Management System (FMS) sends a preselected thrust level, a manual thrust level and a second speed target value to the automatic flight system, the full authority digital engine control device (FADEC) sends signals such as an N1 reference value and a throttle lever N1 instruction to the automatic flight system to calculate a thrust change instruction, the thrust change instruction is calculated in the automatic flight system computer, meanwhile, the thrust level N1 reference value provided by the full authority digital engine control device (FADEC) is received and serves as a thrust guide control upper limit constraint thrust change instruction, and finally when the automatic throttle function is not connected and a flight guide mode is not connected, the calculated thrust change instruction is sent to the display system, and the display system is displayed on the main flight display (PFD) to be referred by a pilot and help the pilot to operate the throttle lever.
In the flight management system, the pilot selects the thrust level and flexible temperature to be used (input only at flexible takeoff) on the Flight Management System (FMS) page, and the data is transmitted to the automatic flight system via the ARINC664 bus.
In a full authority digital engine control device (FADEC), the FADEC sends signals such as an N1 reference value and a throttle lever N1 command for each thrust level to an automatic flight system, and data is transmitted to the automatic flight system via an ARINC664 bus.
In the throttle station, the throttle station feeds back the throttle motion state to a full authority digital engine control device (FADEC), and transmits it through an analog line.
In the atmosphere data system, the atmosphere data system collects the environment information of the aircraft, provides airspeed and other information, and transmits the information to the automatic flight system through an ARINC429 bus.
In the automatic flight system, the automatic flight system receives the thrust level and the flexible temperature sent by the Flight Management System (FMS), determines the thrust level according to the pilot command and the current state, and sends the determined thrust level to the full authority digital engine control device (FADEC) and the Flight Management System (FMS). Meanwhile, a thrust change command is calculated based on signals such as an N1 reference value of a full authority digital engine control device (FADEC) and a throttle lever N1 command, and throttle motion feedback of a throttle stand.
In the display system, the display system receives a thrust change command from the automatic flight system via the ARINC664 bus and displays it on the Primary Flight Display (PFD).
The pilot operates the airplane according to the thrust change guide on a main flight display (PFD), and the throttle lever is manually controlled to adjust the flying speed of the airplane.
When the thrust change instruction is calculated in the automatic flight system computer, the calculation is performed based on signals such as a preselected thrust level, a manual thrust level, an N1 reference value, and a throttle lever N1 instruction. Specifically, the mode of thrust direction is determined according to the vertical mode of the flight direction in which the automatic flight system is switched on, and specifically comprises a thrust mode and a speed mode.
Further, the generating the thrust force alteration command based on the N1 reference value and the throttle lever N1 command comprises:
determining the thrust target value based on the N1 reference value;
determining the current thrust actual value based on the throttle lever N1 instruction;
and generating the thrust change instruction based on the thrust target value and the current thrust actual value.
In the thrust mode, a thrust change command is calculated by comparing a thrust target value corresponding to the mode actually turned on with a throttle lever N1 command fed back from a full authority digital engine control device (FADEC) by a difference value.
Further, the generating the thrust force alteration command based on the speed target value, the throttle lever N1 command, and the N1 reference value includes:
determining a first thrust target value based on the speed target value, determining a second thrust target value based on the N1 reference value, and determining a value with a smaller value of the first thrust target value and the second thrust target value as the thrust target value;
determining the current thrust actual value based on the throttle lever N1 instruction;
and generating the thrust change instruction based on the thrust target value and the current thrust actual value.
Illustratively, in the speed mode, a thrust force modification command is generated based on a speed target value, a throttle lever N1 command and an N1 reference value, wherein the speed target value is a first speed target value or a second speed target value. The first speed target value is the speed selected by the pilot on the flight mode control panel, which the automatic flight system can directly acquire. The second velocity target value is a value that the Flight Management System (FMS) generates to the automatic flight system, typically a flight tube velocity target. According to a first speed target value selected by a pilot or a second speed target value managed by a Flight Management System (FMS), a first thrust target value is calculated by interpolation, a thrust level N1 reference value provided by a full-weight digital engine control device (FADEC) is received, a second thrust target value corresponding to the N1 reference value is calculated to serve as a thrust guide control upper limit constraint thrust change instruction, namely, the smaller value of the two is taken as the thrust target value, and the thrust target value is compared with a throttle lever N1 instruction fed back by the full-weight digital engine control device (FADEC) to calculate a thrust change instruction.
Further, the step S2 includes:
in a case where the thrust target value is not identical to the current thrust actual value, the first symbol, the second symbol, and the third symbol are displayed at different positions on the same column of the display screen, and the third symbol is always located between the first symbol and the second symbol.
Illustratively, among the three symbols, the first symbol representing the thrust target value and the second symbol representing the current thrust actual value mainly serve as references, while the third symbol representing the motion direction of the throttle lever serves as a guide. Therefore, in the case where the thrust target value is not the same as the current thrust actual value, the third symbol is always located between the first symbol and the second symbol to direct the pilot to perform the operation.
Further, the third symbol includes a first direction sub-symbol and a second direction sub-symbol, and the step S2 includes:
displaying only the first direction sub-symbol in a case where the thrust target value is greater than the current thrust actual value, and displaying only the second direction sub-symbol in a case where the thrust target value is less than the current thrust actual value.
For example, when the flying speed of the aircraft needs to be adjusted, the thrust value may need to be increased or decreased, and therefore, in order to distinguish between the two, the pilot is prompted to increase the thrust by a first direction sub-symbol and decrease the thrust by a second direction sub-symbol, the directions indicated by the first direction sub-symbol and the second direction sub-symbol being opposite to each other.
Further, a distance between the display position of the first symbol and the display position of the second symbol is proportional to a difference between the current thrust actual value and the thrust target value.
Illustratively, the distance between the display positions of the first symbol and the second symbol is in a fixed proportion to the difference between the pushing forces. Before displaying the thrust force change guide, the distance between the first symbol and the second symbol in the initial state is obtained, and then the difference between the thrust force actual value and the thrust force target value in the initial state is obtained. The ratio in this guidance process is then determined based on the difference and the distance, and therefore, the ratio is not fixed, and differs from case to case.
Further, the method step S3 comprises:
and gradually reducing the relative distance between the display positions of the first symbol and the second symbol in the process of changing from the current thrust actual value to the thrust target value to the same value, wherein the relative distance is reduced in proportion to the reduction of the difference value.
Illustratively, in an initial state before the thrust change, the current thrust actual value and the thrust target value are different, in an end state, the current thrust actual value and the thrust target value are the same, and in the gradual change process, the relative distance between the first symbol and the second symbol is reduced in proportion to the reduction of the difference.
Fig. 4 is a schematic diagram illustrating a variation of a thrust change guidance according to an embodiment of the present invention, in fig. 4, in an initial state, a current actual value of thrust is smaller than a target value of thrust, and gradually varies to be the same as the target value of thrust as the pilot continuously increases the thrust. In a of fig. 4, the display position of the second symbol is unchanged, and the distances between the display positions of the first symbol and the third symbol and the display position of the second symbol decrease in proportion to the upward direction as the difference decreases. In fig. 4-b, the display position of the first symbol is unchanged, and the distances of the display positions of the second symbol and the third symbol from the display position of the first symbol decrease in proportion to the upward direction as the difference decreases. Fig. 5 is a schematic diagram of another variation of the thrust alteration guidance provided by the embodiment of the present invention, in fig. 5, in an initial state, a current thrust actual value is greater than a thrust target value, and gradually varies to be the same as the thrust target value as the pilot continuously decreases the thrust, where a of fig. 4 and a of fig. 5 are opposite operation processes, and b of fig. 4 and b of fig. 5 are opposite operation processes. In a specific application, the display mode and the change mode may be determined according to an application requirement, which is not limited in the present invention.
Further, the step S3 includes:
when the current thrust actual value changes from being different from the thrust target value to being the same as the thrust target value, the first symbol and the second symbol are displayed in an overlapping manner.
Illustratively, under the direction of a plurality of symbols, the current thrust actual value gradually reaches the thrust target value, and when the change termination state is reached, a first symbol and a second symbol are displayed on the screen in an overlapping manner, and the pilot stops operating the throttle stick.
Further, the first direction sub-symbol includes a line between the first symbol and the second symbol and an arrow on the line indicating a first direction, and the second direction sub-symbol includes a line between the first symbol and the second symbol and an arrow on the line indicating a second direction.
Further, the first symbol is a circular line and the second symbol is a straight line segment.
Illustratively, as shown in FIG. 3, an exemplary graph of a plurality of symbols, a first symbol being a circular line, a second symbol being a transverse straight line segment, and a third symbol being a combination of a vertical straight line segment and an arrow, wherein different arrows represent an increase or decrease in thrust. It should be noted that, in practical applications, the number and the shape of the plurality of symbols may be determined according to application requirements, and the present invention is not limited thereto, and designs capable of implementing the directing function are within the protection scope of the present invention.
Through one or more of the above embodiments in the present invention, at least the following technical effects can be achieved:
according to the technical scheme disclosed by the invention, when the automatic throttle is unavailable or a pilot is not connected with the automatic throttle, a thrust target value required by the airplane is determined, a current thrust actual value is monitored in real time, a thrust change guide is generated based on the thrust target value and the current thrust actual value, the thrust guide is provided for the pilot through the display and change of a plurality of symbols, the pilot is helped to more accurately control a throttle lever in key stages such as take-off and the like, the target speed is further accurately controlled, the workload of the pilot is further reduced, the working efficiency is improved, and the fuel consumption of the airplane is properly reduced.
Based on the same inventive concept as the thrust alteration guidance method for the aircraft according to the embodiment of the present invention, the embodiment of the present invention provides a thrust alteration guidance apparatus for an aircraft, referring to fig. 6, the apparatus including:
the thrust change guide generation module 201 is configured to generate a thrust change guide based on a thrust change instruction, where the thrust change guide includes a thrust target value, a throttle lever movement direction, and a current thrust actual value;
a symbol display module 202, configured to display, at different positions on a display screen, a first symbol indicating the thrust target value, a second symbol indicating the current thrust actual value, and a third symbol indicating the movement direction of the throttle stick when the thrust target value is different from the current thrust actual value, so as to guide a pilot to operate the throttle stick of the aircraft according to the displayed movement direction of the throttle stick;
and the real-time updating module 203 is used for updating the current thrust actual value in real time along with the control of the pilot on the throttle stick and changing the relative display positions of the first symbol, the second symbol and the third symbol according to the difference value between the current thrust actual value and the thrust target value until the thrust target value is the same as the current thrust actual value, blanking the third symbol and enabling the first symbol and the second symbol to be displayed in an overlapped mode at the same position.
Further, the symbol display module 202 is further configured to:
s2, under the condition that the thrust target value is different from the current thrust actual value, displaying the first symbol, the second symbol and the third symbol at different positions of the same column of the display screen, wherein the third symbol is always located between the first symbol and the second symbol.
Further, the third symbol comprises a first direction sub-symbol and a second direction sub-symbol, and the symbol display module 202 is further configured to:
displaying only the first direction sub-symbol in case the thrust target value is greater than the current thrust actual value, and displaying only the second direction sub-symbol in case the thrust target value is less than the current thrust actual value.
Further, a distance between the display position of the first symbol and the display position of the second symbol is proportional to a difference between the current thrust actual value and the thrust target value.
Further, the real-time update module 203 is further configured to:
and gradually reducing the relative distance between the display positions of the first symbol and the second symbol in the process from the current thrust actual value to the thrust target value being different to the same, wherein the relative distance is reduced in proportion to the reduction of the difference value.
Further, the real-time update module 203 is further configured to:
when the current thrust actual value changes from being different from the thrust target value to being the same as the thrust target value, the first symbol and the second symbol are displayed in an overlapping manner.
Further, the first direction sub-symbol includes a line between the first symbol and the second symbol and an arrow indicating a first direction on the line, and the second direction sub-symbol includes a line between the first symbol and the second symbol and an arrow indicating a second direction on the line.
Further, the first symbol is a circular line and the second symbol is a straight line segment.
Further, the apparatus is further configured to:
before generating a thrust change guide based on the thrust change instruction, acquiring an automatic throttle on-state parameter, determining the state of an automatic throttle function according to the automatic throttle on-state parameter, and generating the thrust change instruction when the automatic throttle function is in an inactivated state or an unavailable state.
Other aspects and implementation details of the thrust alteration guiding device for the aircraft are the same as or similar to those of the thrust alteration guiding method for the aircraft described above, and are not repeated herein.
According to another aspect of the present invention, there is also provided a storage medium having stored therein a plurality of instructions adapted to be loaded by a processor to perform any of the thrust alteration guidance methods for aircraft described above.
In view of the foregoing, it is intended that the present invention cover the preferred embodiment of the invention and not be limited thereto, but that various changes and modifications can be made therein by those skilled in the art without departing from the spirit and scope of the invention.
Claims (14)
1. A thrust alteration guidance method for an aircraft, the method comprising:
s1, generating thrust change guidance based on a thrust change instruction, wherein the thrust change guidance comprises a thrust target value, a throttle lever moving direction and a current thrust actual value;
s2, under the condition that the thrust target value is different from the current thrust actual value, displaying a first symbol indicating the thrust target value, a second symbol indicating the current thrust actual value and a third symbol indicating the movement direction of the throttle lever at different positions of a display screen so as to guide a pilot to control the throttle lever of the aircraft according to the displayed movement direction of the throttle lever;
and S3, updating the current thrust actual value in real time along with the control of the pilot on the throttle lever, and changing the relative display positions of the first symbol, the second symbol and the third symbol according to the difference value between the current thrust actual value and the thrust target value until the thrust target value is the same as the current thrust actual value, blanking the third symbol and enabling the first symbol and the second symbol to be displayed in the same position in an overlapping mode.
2. The method of claim 1, wherein the method further comprises:
before generating a thrust change guide based on the thrust change instruction, acquiring an automatic throttle on-state parameter, determining the state of an automatic throttle function according to the automatic throttle on-state parameter, and generating the thrust change instruction when the automatic throttle function is in an inactivated state or an unavailable state.
3. The method of claim 1, wherein the generating the thrust alteration command comprises:
receiving a preselected thrust level and a manual thrust level sent by a flight management system, and receiving an N1 reference value and a throttle lever N1 instruction sent by a full-weight digital engine control device;
acquiring a first speed target value selected by a pilot or a second speed target value corresponding to the flight management system;
determining a current thrust guidance mode according to a flight guidance vertical mode of an automatic flight system, when the thrust guidance mode is a thrust mode, determining an N1 reference value based on the preselected thrust level and the manual thrust level, generating the thrust change instruction based on the N1 reference value and the throttle lever N1 instruction, and when the thrust guidance mode is a speed mode, generating the thrust change instruction based on a speed target value, the throttle lever N1 instruction and the N1 reference value, wherein the speed target value is the first speed target value or the second speed target value.
4. The method of claim 3, wherein said generating the thrust alteration command based on the N1 reference value and the throttle lever N1 command comprises:
determining the thrust target value based on the N1 reference value;
determining the current thrust actual value based on the throttle lever N1 instruction;
and generating the thrust change instruction based on the thrust target value and the current thrust actual value.
5. The method of claim 3, wherein said generating the thrust alteration command based on the speed target value, the throttle lever N1 command, and the N1 reference value comprises:
determining a first thrust target value based on the speed target value, determining a second thrust target value based on the N1 reference value, and determining a value with a smaller value of the first thrust target value and the second thrust target value as the thrust target value;
determining the current thrust actual value based on the throttle lever N1 instruction;
and generating the thrust change instruction based on the thrust target value and the current thrust actual value.
6. The thrust force alteration guidance method according to claim 1, wherein the step S2 includes:
in a case where the thrust target value is not identical to the current thrust actual value, the first symbol, the second symbol, and the third symbol are displayed at different positions on the same column of the display screen, and the third symbol is always located between the first symbol and the second symbol.
7. The thrust force alteration guidance method according to claim 6, wherein the third symbol includes a first direction sub-symbol and a second direction sub-symbol, and the step S2 includes:
displaying only the first direction sub-symbol in a case where the thrust target value is greater than the current thrust actual value, and displaying only the second direction sub-symbol in a case where the thrust target value is less than the current thrust actual value.
8. The thrust force alteration guidance method according to claim 7, wherein a distance between the display position of the first symbol and the display position of the second symbol is proportional to a difference between the current thrust actual value and the thrust target value.
9. The thrust force change guidance method according to claim 8, wherein the step S3 includes:
and gradually reducing the relative distance between the display positions of the first symbol and the second symbol in the process from the current thrust actual value to the thrust target value being different to the same, wherein the relative distance is reduced in proportion to the reduction of the difference value.
10. The thrust force change guidance method according to claim 9, wherein the step S3 includes:
when the current thrust actual value changes from being different from the thrust target value to being the same as the thrust target value, the first symbol and the second symbol are displayed in an overlapping manner.
11. The thrust force alteration guidance method according to any one of claims 1 to 10, wherein the first direction sub-symbol includes a line between the first symbol and the second symbol and an arrow indicating a first direction on the line, and the second direction sub-symbol includes a line between the first symbol and the second symbol and an arrow indicating a second direction on the line.
12. The thrust force alteration guidance method according to claim 11, wherein the first symbol is a circular line, and the second symbol is a straight line segment.
13. A thrust alteration guidance device for an aircraft, characterized in that the device comprises:
the thrust change guide generation module is used for generating thrust change guide based on a thrust change instruction, and the thrust change guide comprises a thrust target value, a throttle lever movement direction and a current thrust actual value;
the symbol display module is used for displaying a first symbol indicating the thrust target value, a second symbol indicating the current thrust actual value and a third symbol indicating the movement direction of the throttle lever at different positions of a display screen under the condition that the thrust target value is different from the current thrust actual value so as to guide a pilot to control the throttle lever of the aircraft according to the displayed movement direction of the throttle lever;
and the real-time updating module is used for updating the current thrust actual value in real time along with the control of the pilot on the throttle stick and changing the relative display positions of the first symbol, the second symbol and the third symbol according to the difference value between the current thrust actual value and the thrust target value until the thrust target value is the same as the current thrust actual value, blanking the third symbol and enabling the first symbol and the second symbol to be displayed in the same position in an overlapping mode.
14. A storage medium having stored therein a plurality of instructions adapted to be loaded by a processor to perform the method of any one of claims 1 to 12.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202211073529.7A CN115407796A (en) | 2022-09-02 | 2022-09-02 | Thrust change guidance method and device for aircraft and storage medium |
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| CN202211073529.7A CN115407796A (en) | 2022-09-02 | 2022-09-02 | Thrust change guidance method and device for aircraft and storage medium |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117690332A (en) * | 2024-02-02 | 2024-03-12 | 北京东方瑞丰航空技术有限公司 | Manipulation guiding method, device, equipment and medium |
| CN117690332B (en) * | 2024-02-02 | 2024-04-26 | 北京东方瑞丰航空技术有限公司 | Manipulation guiding method, device, equipment and medium |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117690332A (en) * | 2024-02-02 | 2024-03-12 | 北京东方瑞丰航空技术有限公司 | Manipulation guiding method, device, equipment and medium |
| CN117690332B (en) * | 2024-02-02 | 2024-04-26 | 北京东方瑞丰航空技术有限公司 | Manipulation guiding method, device, equipment and medium |
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