A self-checking method and device based on a flight simulation cockpit

Abstract

The application relates to a self-checking method and device based on a flight simulation cockpit, the self-checking method comprising the following steps: in response to a starting control signal from a teaching terminal, controlling equipment in the flight simulation cockpit to be powered on; obtaining a self-checking signal after the equipment in the flight simulation cockpit is powered on, and judging whether the self-checking signal is in a set range to obtain a self-checking result; and recording the self-checking result, a corresponding time node and equipment information to complete self-checking, wherein the flight simulation cockpit comprises a simulation cockpit, a simulation server end, an interface manager and a serial bus. According to the scheme, the problem that the equipment in the flight simulation cockpit has a large checking workload and low efficiency is solved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of computer simulation in general. More particularly, the present application relates to a self-checking method and device based on a flight simulation cockpit. BACKGROUND

[0002] The flight simulation cockpit is a device for training pilots, which is generally composed of a cockpit, an interface device, various instruments, a visual system, and a training computer, and is a semi-closed cockpit structure. When training, the student can sit in the cockpit and perform various operations: opening the switch, pushing and pulling the throttle, operating the flight stick and rudder, and obtaining various data such as flight speed, distance, position, height, wind direction, and wind speed. The visual system can provide a simulation of the scenery in which the student is located, and the student can feel the diving, climbing, and circling actions as if sitting in an airplane, and can also see various scenes on the airplane (clouds, fog, rivers, buildings), and can set various flight environments to comprehensively train the technology and learn to master various operations that are difficult and dangerous.

[0003] The flight simulation cockpit has the advantages of energy saving, economy, safety, no restriction on site and weather conditions, shortening of training period, reduction of training cost, and improvement of training efficiency, and plays a very important role in pilot training. At present, there are various flight simulation cockpits in China, which are divided into two categories: imported and self-developed. The imported civil aircraft flight simulation training devices mainly include Boeing and Airbus series. The self-developed aircraft flight simulation training devices are relatively few, and the representative aircraft flight simulation training devices are mainly used for flight simulation training of basic pilot driving technology.

[0004] In the Chinese patent application for invention with the application publication number CN115547143A and the invention name of an aircraft fire control system simulation training device, the content for carrying out the aircraft fire control system power-on process demonstration, component disassembly and fault simulation training is disclosed. The pilot human-computer interaction system, the photoelectric turret simulation training system, the photoelectric pod simulation training system, the training console, and the data acquisition and control system are interconnected through a network switch, and the control information, the collected data, and the display content are transmitted between the systems through the network switch. However, there is no way to check the system in this scheme, which may cause errors in the device power-on demonstration process.

[0005] At present, the inspection of each device in the flight simulation cockpit is usually realized based on an offline manual inspection method, that is, the working personnel checks the specific situation of the device according to the inspection list in sequence, and then manually records the real-time running state data of the device on the corresponding record table to artificially judge whether the running of each device meets the established standard based on the record table.

[0006] Therefore, in the case that a large number of devices are arranged in the flight simulation cockpit, a large amount of time and manpower is consumed for the inspection of the devices, and the final determination of whether the devices are normal is not accurate, resulting in a very low inspection efficiency of the devices.

[0007] Therefore, the current problems of the flight simulation cockpit mainly include a large amount of device inspection and low efficiency. SUMMARY

[0008] To solve one or more of the above technical problems, the present application proposes to obtain a self-check signal of each device after power-on when each device in the flight simulation cockpit is powered on, so as to realize an intelligent self-check process of the flight simulation cockpit, effectively improve the inspection efficiency of the flight simulation cockpit, and ensure the safe and reliable operation of the whole system. For this purpose, the present application provides solutions in the following aspects.

[0009] In a first aspect, the present application provides a self-check method based on a flight simulation cockpit, the self-check method comprising: in response to receiving a start control signal, controlling a device in the flight simulation cockpit to be powered on; obtaining a self-check signal of the device in the flight simulation cockpit after power-on, and determining whether the self-check signal is within a set range to obtain a self-check result; recording the self-check result and corresponding time node and device information to complete self-check; wherein the flight simulation cockpit comprises: a simulation cockpit for simulating a cockpit and enabling a trainee to perform simulation operation thereon; a simulation server end for providing models of various components of an airplane; a serial bus connected to the simulation server end and connected to the simulation cockpit through an interface manager to complete data interaction between the simulation server end and the simulation cockpit; the serial bus is also used to connect to an external teaching terminal to perform information interaction between the teaching terminal and the simulation cockpit and the simulation server end; wherein the simulation server end transmits a simulation video signal formed by simulation to the simulation cockpit through the interface manager, and the simulation server end transmits a simulation audio signal formed by simulation to an audio device, wherein the audio device is used in combination with the simulation cockpit.

[0010] In one embodiment, the simulation cockpit is in communication connection with the interface manager through a video signal, an Ethernet signal and a hard-wired signal.

[0011] In one embodiment, the serial bus is a 1394 bus.

[0012] In one embodiment, the simulation cockpit is deployed with a simulation cockpit subsystem, the interface manager is deployed with an interface management subsystem, the simulation server is deployed with a software integration and environment running subsystem, a sound simulation subsystem and an aircraft simulation subsystem; wherein the software integration and environment running subsystem is configured to schedule each subsystem, control data interaction between each subsystem, and control communication between the interface management subsystem and the aircraft simulation subsystem; the simulation cockpit subsystem is configured to support hardware of the simulation cockpit, convert operation of a student into a hard-wired signal or an Ethernet signal, transmit the hard-wired signal or the Ethernet signal to the interface management subsystem, and accept a video signal transmitted by the interface management subsystem for image display; the aircraft simulation subsystem is configured to run at least one component simulation model of an aircraft; the sound simulation subsystem is configured to simulate at least one sound in a flight; and the interface management subsystem is configured to perform data conversion and transmission.

[0013] In one embodiment, the aircraft simulation subsystem is configured to run at least one component simulation model of an aircraft, including: receiving a control signal of the simulation cockpit subsystem and a model initial parameter set by a teaching terminal, running a corresponding set simulation model, and outputting data to other subsystems, wherein the control signal is generated by a student through manipulation of the simulation cockpit.

[0014] In one embodiment, the aircraft simulation subsystem includes integrated processing software and a DDS soft bus; the integrated processing software performs data interaction with a component simulation model, an algorithm model and an aircraft dynamics model through the DDS soft bus.

[0015] In one embodiment, the component simulation model is connected to the DDS soft bus through an AMESim interface and a Simulink interface, the algorithm model is connected to the DDS soft bus through a C / C++ interface, and the aircraft dynamics model is connected to the DDS soft bus through a FlightSim interface.

[0016] In one embodiment, the integrated processing software includes flight management software, central warning software and central maintenance software.

[0017] In one embodiment, the aircraft simulation subsystem is further configured to run an atmospheric data model, the atmospheric data model being configured to provide a flight parameter calculated based on atmospheric data.

[0018] In one embodiment, the atmospheric data model is configured to receive a corresponding parameter set by a teaching terminal and sensor information calculated by the aircraft simulation subsystem, and then calculate a flight control parameter, which is further calculated by the aircraft simulation subsystem.

[0019] In one embodiment, the simulated cockpit subsystem includes a top control panel, a front control panel, a center console panel, a left console, a right console, and a control mechanism within the cockpit, the control mechanism including a yoke, a stick, a rudder, and a throttle lever.

[0020] In one embodiment, the interface management subsystem is configured to accomplish signal acquisition, excitation, and data conversion transmission for the top control panel, the front control panel, the center console panel, the left console, and the right console of the cockpit in the simulated cockpit subsystem; the interface management subsystem is further configured to implement conditioning, adaptation, and transmission of electrical signals for the control mechanism in the simulated cockpit subsystem.

[0021] In one embodiment, the component simulation model includes one or more of a hydraulic system model, an environmental control system model, a fuel system model, a power plant model, an auxiliary power plant model, an oxygen system model, an environmental protection system model, a control model, and an illumination system model; the control model includes a landing gear control system model and a door control system model.

[0022] In one embodiment, the top control panel includes one or more of the following control panels: an emergency positioning control panel, an in-cabin lighting control panel, an avionics start control panel, a flight control system control panel, a hydraulic system control panel, a backup parking control panel, a power supply system control panel, an engine start control panel, a fuel system control panel, an external lighting control panel, a windshield wiper control switch, a landing lighting control panel, a fire protection system control panel, a cabin sound monitoring control panel, an electromechanical management system control panel, a life-saving system control panel, an oxygen system control panel, an anti-icing system control panel, a gas source system control panel, an air conditioning system control panel, and a pressure regulation system control panel.

[0023] In one embodiment, the front control panel includes one or more of the following: a left warning light, a right warning light, a left display control panel, a right display control panel, an automatic flight control panel, an approach warning light, a landing gear control handle, a landing gear light, and an automatic brake selection panel.

[0024] In one embodiment, the center console includes one or more of the following: a parking emergency brake, a horizontal stabilizer position indicator, a multifunction display, a horizontal stabilizer trim control handle, a speed brake handle, a horizontal stabilizer trim cutoff switch, a flap handle, left and right trackballs, left and right multifunction keyboards, a normal parking switch, a flap override control panel, a radio tuning unit, a fire control panel, a throttle console, an audio control panel, a trim control panel, a select switch panel, a door control panel, a cockpit air drop control panel, and an electronic warfare control panel.

[0025] In one embodiment, the left console includes a front seat oxygen mask control panel, a left dimming control panel, a front seat front wheel turning handle, a left HUD control panel, a key control box, a time key control box, and a headphone jack assembly.

[0026] In one embodiment, the right console includes a co-pilot seat oxygen mask control, a right dimming control panel, a co-pilot seat front wheel turning handle, a right HUD control panel, an oxygen cutoff valve switch, and a mission load / unload card.

[0027] In one embodiment, each control panel, panel and console in the analog cockpit subsystem are implemented by means of physical simulation and / or virtual simulation interface.

[0028] In one embodiment, the interface manager includes an image generation computer connected to the front control panel and the central console through a DVI signal, and an interface computer connected to the front control panel, the central console, the top control panel, the left console and the right console through a network switch.

[0029] In one embodiment, the interface manager further includes a power control box connected to the front control panel, the central console, the top control panel, the left console and the right console respectively for direct current power supply.

[0030] In one embodiment, the sound simulation subsystem is used to simulate at least one sound in flight, including one or more of the following: environmental noise, airborne device working noise, prompt tone, alarm voice and superposition of audio signals.

[0031] In one embodiment, the alarm voice includes a voice alarm sound, the airborne device working noise includes a landing gear retraction sound, a flap retraction sound, an aircraft engine sound, and a tire skid runway sound, and the environmental noise includes an external weather environment sound and an air conditioning noise.

[0032] In one embodiment, the self-checking method further includes a step of self-checking the display device: obtaining a standard image frame; calculating all vector differences between motion vectors of each category region in the current image with jelly effect and the standard image frame; calculating the weight of the corresponding vector difference according to the number of pixel points of each category region, and performing weighted summation on the vector difference and the corresponding weight to obtain the vector difference of the whole image; matching the strength of the jelly effect selected at the teaching terminal with the size of the vector difference corresponding to the image to determine whether the display device is abnormal.

[0033] In a second aspect, the present application also provides a self-checking device using the self-checking method in one or more of the preceding embodiments, comprising: a detection device connected with devices in the flight simulation cockpit, for detecting state information of the devices in the flight simulation cockpit after the devices are powered on, to obtain self-checking information; a processor connected with the detection device, for judging whether the self-checking signal is in a set range, to obtain a self-checking result; and a memory connected with the processor, for recording the self-checking result and corresponding time node and device information, to complete self-checking.

[0034] According to the scheme of the present application, the intelligent self-checking process of the flight simulation cockpit can be realized by detecting the devices according to the self-checking signals of the devices in the flight simulation cockpit after receiving the start control signal from the teaching terminal, thereby improving the self-checking efficiency of the system and effectively reducing the workload of the staff when checking the devices. Further, the composition of the aircraft cockpit simulation system can be refined by respectively deploying corresponding sub-systems, and the sub-systems are composed of software and / or hardware, thereby on the one hand, the training effect of the pilot during simulation training can be effectively improved, and on the other hand, the devices in the self-checking process are refined, the self-checking process is refined, and the operation reliability of the flight simulation cockpit is improved. Further, in the present application, the display of the jelly effect in the display device is monitored BRIEF DESCRIPTION OF DRAWINGS

[0035] The above and other objects, features and advantages of the disclosed example embodiments will be more apparent from the following detailed description taken in conjunction with the accompanying drawings, in which several example embodiments of the present disclosure are illustrated by way of example and not limitation in which like reference numerals refer to similar components throughout the various figures and wherein:

[0036] Figure 1 is a schematic view schematically showing an aircraft cockpit simulation system according to an embodiment of the present application;

[0037] Figure 2 is a flowchart schematically showing a self-checking method based on a flight simulation cockpit according to an embodiment of the present application;

[0038] Figure 3 is a schematic view schematically showing a sub-system composition of a flight simulation cockpit according to an embodiment of the present application;

[0039] Figure 4 is a schematic view schematically showing an aircraft simulation sub-system according to an embodiment of the present application;

[0040] Figure 5 is a schematic view schematically showing a cross-linking relationship of a central maintenance system according to an embodiment of the present application;

[0041] Figure 6 Fig. 9 is a schematic diagram illustratively showing the interconnection of an inertial navigation system according to an embodiment of the present application;

[0042] Figure 7 Fig. 10 is a schematic diagram illustratively showing a top control panel according to an embodiment of the present application;

[0043] Figure 8 Fig. 11 is a schematic diagram illustratively showing a center console panel according to an embodiment of the present application;

[0044] Figure 9 Fig. 12 is a schematic diagram illustratively showing a left operator console according to an embodiment of the present application; and

[0045] Figure 10 Fig. 13 is a schematic diagram illustratively showing the interconnection of a landing gear system with other systems according to an embodiment of the present application. DETAILED DESCRIPTION

[0046] The technical solutions in the embodiments of the present application will be apparently and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are part of, rather than all of, the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by a person of ordinary skill in the art without any creative effort fall within the protection scope of the present application.

[0047] The specific embodiments of the present application will be described in detail below with reference to the drawings.

[0048] The flight simulation cockpit proposed in the present solution is a semi-physical simulation system, which can be designed based on the layout of a certain type of aircraft cockpit and can be used to complete various types of teaching and training such as inspection of the cockpit area of the electromechanical system of the aircraft, identification of cockpit components, inspection of the display function of the system cockpit, power-on inspection of the system, fault diagnosis and fault isolation. Based on this, the aircraft cockpit simulation training system in the present application can complete the off-site maintenance subject operation training of the electromechanical and avionics professionals. In some application scenarios, the practical subjects that can be completed by the aircraft cockpit simulation training system include but are not limited to the following:

[0049] Engine start, APU start and run, engine run, engine cold run, landing gear extension and retraction check, engine anti-icing system check, ram air turbine (RAT) hydraulic system performance check, cabin pressurization control system manual control function check, fuel system oil supply check, pressure refueling control simulation, normal brake function check, nose wheel steering system function check, cockpit interior lighting system check, fuel system check, hydraulic system check, door control system check, environmental control system check, anti-icing system check, landing gear signal system check, fire protection system check, flight control system check, external lighting check, emergency evacuation lighting system check, central maintenance MBIT and fault information viewing of electromechanical management system, atmospheric data subsystem operation test, and the like.

[0050] Figure 1 is a schematic diagram schematically showing an aircraft cockpit simulation system according to an embodiment of the present application.

[0051] As shown in Figure 1 , the aircraft simulation system includes a simulation cockpit, a teaching terminal, a simulation server, an interface manager, and an audio device.

[0052] The simulation cockpit can be used to simulate a cockpit and enable a trainee to perform simulation operations thereon. In some embodiments, the simulation cockpit can provide a hardware support structure simulating a cockpit and a base, simulating the layout of a space in which a pilot and a co-pilot are located on a cockpit floor and equipment in the cockpit. A top control panel, a front control panel, a central console panel, a left console, a right console, and the like can be provided in the simulation cockpit, designed with reference to the layout in the cockpit, the size and position of which can be substantially consistent with that of an aircraft, and the interior is arranged with simulated equipment in the cockpit at a scale of 1:1, except that some specific equipment (such as a steering column, a steering wheel, a footrest, a throttle lever, and the like) is implemented in a form of physical simulation, and other equipment can be implemented in a form of a touch screen plus a simulated software interface of the equipment.

[0053] The teaching terminal is used by an instructor to perform operations to publish and set training content. The teaching terminal can implement functions such as development of a control page of a training subject and a training environment, development of an interface driver, and development of process monitoring software, for example, training subject setting, training environment setting, process state monitoring function, and initial parameter setting of a model of an aircraft system.

[0054] The simulation server end can be used to provide models of various components of the aircraft. The simulation server end of the aircraft can be developed on the basis of a simulation model of a certain type of aircraft, based on the architecture of each system of the aircraft, by analyzing the system, the working principle of the accessories, the working characteristics of the accessories and the mathematical model, using digital simulation, data processing and other means to realize the working principle and working process simulation of each system of the aircraft. In the system design stage, simulation software in different fields can be applied to establish models of different subsystems (such as engines, hydraulic systems, fuel systems, landing gears, deicing systems, flight dynamics, etc.) in the aircraft system, and the models established by the simulation software can be effectively integrated through collaborative simulation technology, collaborative simulation and optimization design, and dynamic simulation analysis, fully considering the cross-linking influence between the subsystems, optimizing the design parameters of each aircraft subsystem, to realize the global optimization goal of the aircraft system, and provide a basis for the design of the aircraft integrated management system.

[0055] Further, the initial state parameters of the simulation model of the aircraft system and special cases can also be set to conduct special situation training.

[0056] The serial bus connects the above teaching terminal, simulation server end, and a simulated cockpit through an interface manager. The serial bus is used for data interaction between the teaching terminal, the simulation server end and the simulated cockpit. In some embodiments, the interface manager can complete the collection, excitation and transmission of control signals of the top control panel in the cockpit and the like, and realize the conditioning, adaptation and transmission of electrical signals of devices such as the control column and the control panel, so as to ensure the real-time and effectiveness of the aircraft cockpit simulation system during the training process. In one application scenario, the above simulated cockpit is in communication connection with the interface manager through video signals, Ethernet signals and hard-wired signals. The control box and trackball in the cockpit can output Ethernet signals and transmit them to the serial bus through the interface manager.

[0057] The serial bus can be a 1394 bus, which can realize clock synchronization and simulation scheduling. Since the system adopts a real-time distributed simulation architecture, the synchronization clock adopts the mode of propagating through the data transmission network at the base frequency, and each simulation model can determine whether to perform simulation solving according to its own model solving period and the received clock signal. Based on this, the real-time performance of the system can be determined by the accuracy of the master clock, the data network transmission characteristics and the operating system.

[0058] Specifically, the simulation server end delivers the simulation video signal formed by simulation to the interface manager and delivers the simulation audio signal formed by simulation to the audio device, wherein the audio device is used in conjunction with the simulated cockpit. In one application scenario, the simulation video signal is transmitted through a bus, and the simulation audio signal is transmitted and played separately. In this way, signals with different synchronization requirements are distinguished, and the simulation video signal on the bus has better synchronization together with the Ethernet signal and the hard-wired signal, which can make the user experience closer to the real situation. The audio signal is allowed to have a certain delay, which is closer to the real feeling of the pilot during simulation, and the audio signal is relatively slower than the video signal. Based on this, the audio signal can be transmitted independently, on the one hand, effectively saving the bus resources and reducing the transmission pressure, and on the other hand, making the simulation effect closer to the actual situation and improving the training experience of the trainee.

[0059] In actual operation, the instructor can control the power-on and power-off of the devices of the entire system, the start, stop, and reset of the simulation system, and the like through the teaching terminal, and complete the training environment setting, initial setting of the aircraft system model parameters, and state monitoring during the training process. The trainee completes the training by operating the simulation devices in the simulated cockpit. The operation signal is sent to the simulation server end through the interface manager, and the simulation server end drives the electromechanical, avionics, and flight control models according to the trainee's operation to complete the corresponding logic execution and generate the corresponding result state. The result state after the execution of the aforementioned model is transmitted to the corresponding state indication signal in the simulated cockpit through the interface manager and the audio device, and the training process is completed.

[0060] The above Figure 1 The basic framework and working principle of the aircraft cockpit simulation system in the present application are described, and each part will be described in detail in combination with different component forms.

[0061] Figure 2 is a flowchart schematically showing a self-checking method 200 based on a flight simulation cockpit according to an embodiment of the present application. It should be noted that the method 200 can be implemented in particular according to the flight simulation cockpit described above. Therefore, the foregoing description in combination with the flight simulation cockpit is also applicable hereinafter. Figure 1 The foregoing description in combination with the flight simulation cockpit is also applicable hereinafter. Figure 1 The foregoing description in combination with the flight simulation cockpit is also applicable hereinafter.

[0062] As Figure 2 shown in FIG. 2, at step S201, in response to receiving a start control signal, the devices in the flight simulation cockpit are powered on. In some embodiments, the instructor or maintenance personnel sends a start control signal to the flight simulation cockpit through the teaching terminal, or directly controls the flight simulation cockpit to start through the power supply device of the aircraft simulation cockpit, so as to control the devices in the flight simulation cockpit to be powered on.

[0063] At step S202, a self-check signal after power-on of the equipment in the flight simulation cockpit is acquired, and it is determined whether the self-check signal is in a set range to obtain a self-check result. In some embodiments, the self-check signal after power-on of the equipment in the flight simulation cockpit can be acquired in various ways. For example, for various display equipment, the self-check process of the display equipment can be implemented by setting a screen display single-chip microcomputer to detect whether the screen of the corresponding display equipment is turned on, or by a light sensor to detect the brightness of the screen. The current or voltage of some equipment after power-on can also be detected to detect whether the equipment can work normally after power-on. Then, according to the set range corresponding to the normal working state of each equipment, the self-check signal is determined to determine whether the equipment in the flight simulation cockpit can work normally.

[0064] At step S203, the self-check result and the corresponding time node and equipment information are recorded to complete the self-check. In some embodiments, by recording the self-check result obtained after each power-on, a corresponding self-check log can be generated. In the subsequent work process, the staff can check the historical self-check information by reviewing the self-check log.

[0065] The above describes the self-check process of the flight simulation cockpit. Next, the composition information of the flight simulation cockpit in the present application will be further refined by combining other specific components of the flight simulation cockpit, so as to improve the reliability of the operation of the equipment in the flight simulation cockpit. Figure 2

[0066] Figure 3 FIG. 1 is a schematic diagram illustrating the composition of a flight simulation cockpit according to an embodiment of the present application.

[0067] As shown in FIG. 1, the simulation cockpit is deployed with a cockpit subsystem, the interface manager is deployed with an interface management subsystem, the simulation server end is deployed with a software integration and environment running subsystem, a sound simulation subsystem and an aircraft simulation subsystem, and the teaching terminal is deployed with a teaching control subsystem. Figure 3

[0068] The software integration and environment running subsystem is configured to schedule each subsystem, control the data interaction between each subsystem, and control the communication between the interface management subsystem and the aircraft simulation subsystem. In some embodiments, the main functions of the software integration and environment running subsystem may, for example, include the following aspects:

[0069] a) capable of adding / deleting network computing nodes and monitoring the state of the computing nodes of each simulation subsystem;

[0070] ​​b) remotely deploying the latest simulation software or model of each subsystem in each computing node;

[0071] c) remotely running the model or software of each simulation node and monitoring the running state of all simulation models;

[0072] d) using 1394 network to realize clock synchronization and data transmission, clock jitter less than 5ms;

[0073] e) monitoring the simulation network data transmission in real time.

[0074] The simulation cockpit subsystem is used to support the hardware of the simulation cockpit, to convert the operation of the student into hard-wired signals or Ethernet signals, and to transmit the signals to the interface management subsystem, and to accept the video signals transmitted by the interface management subsystem for image display. Specifically, the simulation cockpit subsystem can provide a realistic simulation cockpit for the pilot of an aircraft. The cockpit size, internal layout, appearance, size, mounting position, indication label, function, and working limit condition, instrument working mode, operation mode, and operation characteristics of the simulation cockpit are consistent with those of the aircraft being simulated. In one application scenario, the simulation cockpit subsystem can include a top control panel, a front control panel, a central console panel, a left console, a right console, and a control mechanism in the cockpit, and the control mechanism includes a joystick, a steering wheel, a footrest, and a throttle lever. Based on this, when performing self-checking on the hardware devices in the simulation cockpit subsystem, the state information of the above-mentioned display, indicator, lamp, and control device after power-on can be obtained through the corresponding detection device, so as to obtain the self-checking information of the device. The voltage, current, or state information of each device can also be directly collected, thereby realizing the self-checking process.

[0075] In one application scenario, a certain type of aircraft cockpit is taken as the simulation object, and the simulation cockpit subsystem can include a simulation cockpit body, a control mechanism function (including a joystick, a steering wheel, and a footrest), a device control box / panel (including an instrument panel console, a top console, a central console, a left console, and a right console), and other auxiliary equipment (including a seat, a headset, etc.). The arrangement of the components in the cockpit can be simulated by using physical simulation parts, or a touch screen can be used as the hardware device control interface to realize the simulation of the device. For example, the joystick, the steering wheel, and the footrest are simulated by using physical simulation parts. Other panel devices use a touch screen as their hardware device control interface, and the software function interface of the device control box / panel is developed on the touch screen interface, thereby realizing the simulation of the hardware device. The arrangement of each part will be described below. Figure 4 to Figure 8The above-mentioned cabin body and control box and other parts can be designed in a modular manner for the convenience of maintenance and later modification, and the reliability and simulation degree are ensured as much as possible. Meanwhile, the hard-wire signals generated by the above-mentioned operating mechanism and the like can be transmitted in the form of Ethernet communication to improve the data transmission efficiency, reliability and maintainability.

[0076] The aircraft simulation subsystem is configured to run at least one component simulation model of an aircraft. The aircraft simulation subsystem is the core of the aircraft cockpit simulation system, and can reflect the fidelity and training effect of the system training process. The aircraft simulation subsystem can be developed according to the working principle of the system, for example, the simulation models of the aircraft power plant, auxiliary power plant, fuel system, hydraulic system, environmental control system, etc. can be developed. Through the aircraft simulation subsystem, a graphical environment can be provided, which can define aircraft takeoff weight, fuel quantity, center, and other parameter information, and provide a typical aircraft flight dynamics model to be embedded into the simulation system, and cooperatively simulate with the models in the foregoing and the following, to provide environmental data excitation for the models.

[0077] The sound simulation subsystem is configured to simulate at least one sound during flight. In some embodiments, the sound simulation subsystem can simulate the sounds that the flight crew can experience in the cockpit during the various stages of the aircraft flight, including environmental noise, airborne equipment working noise, prompt sound, alarm voice, etc. In actual application, various sounds during the flight of the aircraft are stored in a sound database. The sound simulation subsystem can receive data in the simulation network (such as simulation data in the aircraft simulation system, control commands input in the teaching control subsystem, etc.), obtain a current sound list to be played by analyzing and logically processing the data, then call corresponding sound files from the sound database according to the list for playing, and finally play through an audio device. The played sound can be one sound or a superposition of multiple sounds, thereby simulating the sound in the real environment.

[0078] In some embodiments, the above-mentioned sound simulation subsystem can be used to simulate at least one sound during flight. These sounds can include a superposition of one or more of environmental noise, airborne equipment working noise, prompt sound, alarm voice, and audio signal. Among them, the alarm voice includes a voice alarm sound, the airborne equipment working noise includes a landing gear retraction sound, a flap retraction sound, an aircraft engine sound, a tire sound when diving on a runway, and the environmental noise includes an external weather environment sound and an air conditioning noise.

[0079] In some embodiments, the sound simulation subsystem is connected with the aircraft simulation subsystem, and is configured to acquire simulation data of the aircraft simulation subsystem. Then, the aircraft state signal and the first excitation signal are parsed from the simulation data. The corresponding sound is selected according to the aircraft state signal and the first excitation signal, and is superimposed to simulate the sound that can be perceived in the cockpit during the flight of the aircraft.

[0080] Further, the sound simulation subsystem is also connected with the teaching control subsystem, and is further configured to acquire the control signal sent by the teaching control subsystem. The operation state of the sound simulation subsystem is controlled according to the control signal of the teaching control subsystem.

[0081] In some embodiments, the sound simulation subsystem is further configured to acquire the second excitation signal sent by the teaching control subsystem. The sound that can be perceived in the cockpit during the flight of the aircraft is superimposed according to the second excitation signal to realize the sudden training in the teaching process.

[0082] Specifically, the first excitation signal includes an alarm excitation signal and a navigation excitation signal, the aircraft state signal includes an aircraft flight state signal, an aircraft engine state signal, and a flap and landing gear state signal. The control signal can include the size of the adjusted volume, the configuration of the sound channel, the selection of the sound effect, the start, the freeze, and the reset. The second excitation signal includes a thunder excitation signal, a rain excitation signal, a snow excitation signal, and a strong wind excitation signal.

[0083] The teaching control subsystem is configured to set the training content. In some embodiments, the teaching control subsystem is configured to set the training content, including that the teaching control subsystem is configured to set the initial parameters of at least one component simulation model of the aircraft. For example, the functions of training environment setting (for example, including airport condition setting, air route environment setting, meteorological condition setting, activity target setting, etc.), training subject setting (for example, training aircraft setting, flight task setting, fault setting, fault clearing, etc.), interface setting (for example, sound communication setting, frequency setting, and tower setting), process state monitoring (aircraft data monitoring, control data monitoring, motion data monitoring, interface data monitoring, etc.), initial parameter setting of aircraft system model (aircraft weight setting, start / stop, freeze / thaw, reset, etc.), record storage, and student assessment and evaluation (for example, student information management, assessment manual judgment, and system maintenance management) can be performed. In one application scenario, the teaching control subsystem software can provide the setting of the airport condition, the air route, and the natural environment to the operator before the simulation environment runs. The specific setting content includes: providing the airport selection, the airport elevation, the magnetic difference, the take-off direction, the initial setting of the parking, the radio frequency, the field pressure, the field temperature, the audio signal, and the like.

[0084] Further, the teaching control subsystem can also set possible faults of each subsystem of the aircraft, and the fault page is divided according to the ATA chapter (Chinese-English contrast), which provides the functions of setting faults and presetting faults for each system. When a fault is selected, a pop-up text box is displayed in the teaching control subsystem, which indicates the selection of the system that may cause the fault (for example, left or right). The preselected standard and the fault influence and description are also displayed in the pop-up box. The instructor can view the fault influence and description to select the system that causes the fault. The aircraft can also be restored to a normal training state through a fault clearing function.

[0085] The interface management subsystem is used for data conversion and transmission. The interface management subsystem includes a signal processing and interface adaptation unit and a system simulation scheduling software module. The interface management subsystem is the center of data conversion and transmission of the training system, and is responsible for the conditioning, transmission and adaptation between the internal data of the aircraft simulation training system and the cockpit hardware interface. The signal processing and interface adaptation unit is used to complete the electrical signal acquisition and lamp signal driving functions of the cockpit overhead control panel, front control panel, central operating table, left operating table and right operating table. The electrical signals on the cockpit operating table basically include discrete quantities, analog quantities and part of bus signals. In some embodiments, through the above connection mode, the interface management subsystem is used to complete the signal acquisition, excitation and data conversion and transmission of the cockpit overhead control panel, front control panel, central operating table panel, left operating table and right operating table in the simulation cockpit subsystem. The interface management subsystem is also used to realize the conditioning, adaptation and transmission of the electrical signals of the operating mechanism in the simulation cockpit subsystem.

[0086] Since there are many device modules in the cockpit, each control panel contains various electrical signals and driving signals. Therefore, the system processes the signals and adapts the interface for each control panel as a basic unit, and interacts with the aircraft system simulation subsystem, the teaching control subsystem and the like through network signals. At the same time, the avionics simulation part of the virtual cockpit needs to simulate image fusion function, so the signal processing and interface adaptation unit needs to obtain video signals, which are displayed on the device after transmission. Network signals are used to collect control data interaction, and the device uploads its state to the interface computer through the network at a fixed time, and the interface computer sends control signals to each device through the network.

[0087] Figure 4 is a schematic diagram schematically showing an aircraft simulation subsystem according to an embodiment of the present application.

[0088] As Figure 4As shown, the aircraft simulation subsystem includes integrated processing software and a DDS soft bus. The integrated processing software interacts with component simulation models, algorithm models, and aircraft dynamics models via the DDS soft bus. The distributed real-time simulation soft bus based on DDS can effectively connect various simulation software on different computers, while being able to perform unified simulation management, including data reliable communication and time advancing mechanism, sharing interface data between different simulation software, to realize system simulation analysis. In some embodiments, the component simulation models can include one or more of a hydraulic system model, an environmental control system model, a fuel system model, a power plant model, an auxiliary power unit model, an oxygen system model, an environmental protection system model, a control model, and a lighting system model. The control model includes a landing gear control system model and a hatch control system model.

[0089] In some embodiments, the above aircraft simulation subsystem can be used to run at least one component simulation model of an aircraft, including: receiving a control signal of a simulated cockpit subsystem and a model initial parameter of a teaching control subsystem, running a corresponding set simulation model, and outputting data to other subsystems, wherein the control signal is generated by a student through the simulated cockpit.

[0090] In some embodiments, the above simulation interface can include an AMESim interface, a Simulink interface, and a FlightSim interface. The component simulation models are connected to the DDS soft bus via the AMESim interface and the Simulink interface, the algorithm models are connected to the DDS soft bus via a C / C++ interface, and the aircraft dynamics models are connected to the DDS soft bus via the FlightSim interface.

[0091] The integrated processing software includes flight management software, central warning software, and central maintenance software.

[0092] The flight management software mainly realizes functions such as aircraft navigation, flight plan management, performance calculation, trajectory optimization, guidance function, air drop task calculation, database management, integrated monitoring and warning, etc. Its main task is to optimize the flight trajectory, improve the navigation accuracy, and reduce the pilot's driving burden, so as to ensure efficient completion of the task. The flight management software can use the sensor input data related to navigation and aircraft state, on the basis of the reference data provided by the navigation database and the performance database, to perform real-time flight guidance calculation, to assist the pilot in controlling the flight trajectory of the aircraft, so that it flies according to the pre-prepared flight plan and the currently selected performance mode.

[0093] The flight management system model (hereinafter referred to as FM) in the integrated processing software is composed of a set of application software (FMSA) running on the general processing module (CPM) in the integrated processor (IPC) and other subsystems providing functional support for the same. The FMS takes the analog control display unit (SCDU), navigation display (ND), primary flight display (PFD), keyboard and the like provided by the display control subsystem (hereinafter referred to as CDS) as the main man-machine interface; takes the inertial / satellite integrated navigation device (INS), atmospheric data device (ADC), radio navigation device and electromechanical management computer (EMP) and the like as the navigation sensor and aircraft state sensor; takes the automatic flight control system (AFCS) as the main execution component of flight. In addition, the FMSA also updates the contents of the navigation database and performance database through loading and unloading devices, and can unload the contents of the pilot database.

[0094] The flight management system model provides support for the pilot to complete the entire flight task, including guidance, information calculation related to the flight process and the like. Specifically, the flight management system model can simulate the following functions: integrated navigation management, flight plan management, performance calculation, guidance, military task management, database management and integrated monitoring and warning. Correspondingly, according to the functional division, the flight management system model can be divided into the following types of interfaces: integrated navigation control interface, flight plan editing interface, performance setting interface, control interface (suppression, conversion and interception and the like) and database interface.

[0095] Based on the above interface settings, the cross-linking relationship of the flight management system functional interface, the functional division of the flight management system and the dependency relationship between functions include the following contents:

[0096] a) The flight plan editing management function is completed through the flight plan editing interface, which depends on the navigation database management function to complete the editing of the flight plan, and the database can support other functions through the database interface; b) The horizontal driving function is completed through the control interface setting, which provides horizontal guidance according to the aircraft parameters provided by the flight plan and integrated navigation function; c) The integrated navigation performs aircraft position and aircraft speed, height and the like parameter calculation; d) The flight path planning is used to generate the three-dimensional flight path of the aircraft according to the current progress; e) The aircraft basic performance calculation is used to determine the performance parameters of the aircraft platform itself under various conditions; f) The vertical driving is used to control the aircraft height to meet the vertical constraint requirements of the flight plan; g) On the basis of the calculated three-dimensional flight path of the aircraft, HSD information and fuel-to-point time information can be calculated; h) The interface symbol represents that the CDS can control the execution process of a certain function.

[0097] The central warning software receives the failure warning information from the systems / devices inside the aircraft, the configuration warning information of the aircraft itself and the threat warning information (danger level, warning level, attention level, consultation level, prompt level) outside the aircraft, carries out logical processing and priority sorting of the warning information, drives the light warning, drives the display processing unit to display the warning information, drives the audio equipment to produce voice / tone warning, receives and processes the threat warning output by the electronic support reconnaissance equipment, the near-ground warning equipment and the failure warning output by the flight control, engine, hydraulic, environmental control and other systems / devices inside the aircraft, and the configuration warning of the aircraft.

[0098] The central maintenance software realizes the basic functions of the aircraft system failure information processing, storage, retrieval, display calling logic, ground test operation process, state monitoring operation process, software and hardware configuration management identification, data loading operation process, etc.

[0099] The central maintenance system can be formed by the above-mentioned central maintenance software, and the cross-linking relationship of the central maintenance system with each system is as shown in Figure 5 The central maintenance system software can display the maintenance information by using the left and right multifunctional flight displays, and transmit data to the outside by using the printer or data link. It can also be connected with the avionics system and non-avionics system, for example, it can receive the failure of the LRU (line replaceable unit) of the air conditioning system, automatic flight system, fire protection system, fuel system, landing gear system, lighting system, navigation system, oxygen system, auxiliary power system, engine system, etc., and display the failure LRU name.

[0100] The aircraft simulation subsystem in the application also includes an inertial navigation system model (hereinafter referred to as an inertial navigation system model). The inertial navigation system is a parameter solving system of the trainer, which realizes an all-weather, all-attitude and autonomous navigation system, and has the functions of alignment, navigation and navigation data output. The system model can receive the original acceleration and angular velocity output by the aircraft equation, receive satellite information and atmospheric data information from the GPS subsystem, output the information of position, heading, attitude, speed, acceleration, angular velocity, height, global magnetic difference and time of the aircraft through the HB6096 simulation interface, and supply the information for aircraft navigation calculation, data display, flight control, parameter recording and air drop.

[0101] As shown in Figure 6 ​As shown, the inertial navigation system can be connected with the main flight control system, the automatic flight control system, the remote data concentrator (RDC), and the distributed processing unit (DPU). The inertial navigation system can include an inertial satellite integrated navigation 1, an inertial satellite integrated navigation 2, and an inertial satellite integrated navigation 3. The two inertial satellite integrated navigations are respectively connected with the main flight control system, the automatic flight control system, the RDC, and the DPU.

[0102] The external system connected with the above engine system (model) can include a flight control system, an avionics system, a power supply system, a hydraulic system, a climate control system, a fuel system, a fire prevention system, and the like.

[0103] Further, the above aircraft simulation subsystem is also used to run an atmospheric data model, which is used to provide flight parameters calculated based on atmospheric data. In some embodiments, the atmospheric data model is also used to receive corresponding parameters set by the teaching control subsystem and sensor information calculated by the aircraft simulation subsystem, and then calculate flight control parameters for further calculation by the aircraft simulation subsystem. The atmospheric data model can include the following software modules: a data controller, a model controller, a data processor, and a sensor controller. The atmospheric data model receives the ambient temperature set by the teaching control subsystem and the total pressure, static pressure, angle of attack, and sideslip angle information calculated by the aircraft model in the flight system, and sends these data as inputs to the atmospheric data computer simulation module after the sensor model. After a stage, true airspeed, indicated airspeed, Mach number, barometric altitude, corrected barometric altitude, vertical speed, and the like are obtained, and finally these data are sent to various aircraft dynamics models for calculation to display flight data.

[0104] The above describes the software simulation part in each simulation subsystem in detail, and describes the content of the aircraft structure simulation in the aircraft simulation subsystem through the cooperation of various functional models. Next, the panels composed of software and hardware in the simulated cockpit subsystem will be described.

[0105] In some embodiments, each control panel, panel, and console in the simulated cockpit subsystem is realized through physical simulation pieces and / or virtual simulation interfaces.

[0106] As Figure 7As shown, the top control panel may include one or more of the following control panels: emergency positioning control panel, cabin lighting control panel, avionics start control panel, flight control system control panel, hydraulic system control panel, backup shutdown control panel, power system control panel, engine start control panel, fuel system control panel, external lighting control panel, windshield wiper control switch, landing lighting control panel, fire protection system control panel, cabin voice monitoring control panel, electromechanical management system control panel, lifesaving system control panel, oxygen system control panel, anti-icing system control panel, gas supply system control panel, air conditioning system control panel, and pressure regulation system control panel.

[0107] The forward control panel includes one or more of the following: left warning light, right warning light, left display control panel, right display control panel, automatic flight control panel, approach warning light, landing gear control handle, landing gear light, and automatic brake selector panel.

[0108] like Figure 8 As shown, the central control console includes one or more of the following: emergency stop brake, horizontal stabilizer position indicator, multifunction display, horizontal stabilizer trim control handle, speed brake handle, horizontal stabilizer trim cut-off switch, flap handle, left and right trackballs, left and right multifunction keyboards, normal stop switch, flap and slat overrun control panel, radio tuning unit, fire suppression control panel, throttle control console, audio control panel, trim control panel, selection switch panel, cabin door control panel, cockpit airdrop control panel, and electronic warfare control panel. The emergency stop brake, horizontal stabilizer position indicator, multifunction display, horizontal stabilizer trim control handle, speed brake handle, flap handle, left and right trackballs, and left and right multifunction keyboards can all be implemented using physical simulation components and are arranged around the multifunction display. The other components are simulated through a software interface on a touchscreen.

[0109] like Figure 9 As shown, the left control panel includes the driver's side oxygen mask control panel, left dimming control panel, driver's side front wheel steering handle, left head-up display control panel, key control box, time key control box, and headphone / microphone jack assembly. The headphone / microphone jack assembly is implemented using a physical simulation component, while the others can be simulated through a software interface on the touchscreen.

[0110] Corresponding to the left control panel described above, the right control panel includes the passenger-side oxygen mask control, right dimming control panel, passenger-side front wheel steering handle, right head-up display control panel, oxygen shut-off valve switch, and task loading / unloading card. Additionally, it includes a headset / microphone jack assembly for providing voice communication functionality for the passenger side.

[0111] Furthermore, the cockpit is equipped with a control stick mechanism, a control wheel mechanism, and a foot pedal mechanism, all of which can be simulated using physical simulation components.

[0112] In some embodiments, the power supply system model for powering the aircraft cockpit simulation system is also simulated in the scheme of the present application, including the electrical system model, the fuel system model, etc.

[0113] Based on this, the aircraft simulation subsystem further includes an electrical system model for cross-linking with the hydraulic system model, the fuel system model, the power plant model, the oxygen system model, the landing gear system model, the cabin door system model, and the lighting system model to realize data interaction. The electrical system model is also used for data interaction with the avionics system model, the flight control system model, the engine model, and the electromechanical management system model, and the electrical system model is also used for state interconnection of the electrical control panel.

[0114] Further, the aircraft simulation subsystem further includes a fuel system model for data interaction with the engine model, the auxiliary power plant model, the electromechanical management system model, the power supply system model, the teaching control subsystem, and the fuel control panel. Further, the fuel system model is cross-linked with the fuel control panel to realize fuel control.

[0115] Under normal circumstances, each AC main power channel works independently, and the alternator only supplies power to the generator bus bar and the AC main bus bar of the channel. When a channel fails, the system can automatically isolate and protect, and the same side alternator supplies power to the two generator bus bars and the AC main bus bar on this side. When both channels on the same side fail, if the auxiliary generator is not working, the power supply switching control function of the power supply control management subsystem is used to realize power supply from the two alternators on the other side to the two AC main bus bars on this side: if the auxiliary generator is put into work, the auxiliary generator supplies power to the two generator bus bars and the AC main bus bar on this side.

[0116] The aircraft simulation subsystem further includes a landing gear retraction system model for data interaction with the landing gear control handle, the hydraulic system model, the power supply system model, and the electromechanical management system.

[0117] As shown in Figure 10 The cross-linking relationship of the landing gear retraction system model with other systems in the aircraft cockpit simulation system includes that the landing gear retraction system model is connected with the landing gear signal light box for displaying the landing gear position information. The landing gear retraction system model can also be connected with the terrain warning system, the SCU, the BCU, the EMP, the DAP, the throttle table reverse thrust unlocking device, the generator control device, etc. to realize corresponding functions according to the wheel load information. The landing gear retraction system model is also connected with the landing gear control handle, the hydraulic system, the power supply system, and the EMS, so as to receive the power supply signals of the corresponding control signals and realize the corresponding functions.

[0118] In some embodiments, the interface manager includes an image generation computer and an interface computer. The image generation computer is connected to the front control panel and the central console through a DVI signal. The interface computer is connected to the front control panel, the central console, the top control panel, the left console and the right console through a network switch. The interface manager further includes a power control box connected to the front control panel, the central console, the top control panel, the left console and the right console respectively for direct current power supply.

[0119] In some embodiments, the self-checking process can further detect the degree of the jelly effect in the video image in the display device. For example, after receiving the intensity of the jelly effect selected by the teaching terminal, it is determined whether the intensity of the jelly effect in the video image meets the requirements, and whether an abnormal situation occurs. In the teaching management and control subsystem in the teaching terminal, a selection switch and an adjustment switch corresponding to the jelly effect can be provided, and the adjustment switch can be a knob switch, so as to realize stepless adjustment of the degree of the jelly effect. When setting the faults of each subsystem of the aircraft according to the selection of the instructor to simulate the fault running state of the aircraft, first, the intensity of the jelly effect selected by the instructor is obtained. Then, the jelly effect in the video image is simulated according to the intensity of the jelly effect selected by the instructor to obtain a simulation result, which includes the vibration situation of the aircraft in flight affected by the external environment. Finally, the simulation result is output to the simulation cockpit subsystem for display.

[0120] Based on this, when the display device in the flight simulation cockpit is self-checked, whether an abnormality occurs can also be determined through the calculation process of the vector difference.

[0121] The above determination process can be implemented in the following manner. Specifically, a standard image frame is obtained. All vector differences between the motion vectors of each category region in the image with the jelly effect and the standard image frame are calculated. Then, the weights of the corresponding vector differences are calculated according to the number of pixel points of each category region, and the vector differences and the corresponding weights are weighted and summed to obtain the vector difference of the entire image. The intensity of the selected jelly effect is matched with the size of the vector difference corresponding to the image to determine whether the display device has an abnormality.

[0122] It can be understood that when the degree of the jelly effect is selected, the adjustment switch corresponds to the size of the above-mentioned vector difference, and each vector difference respectively represents the deviation degree between the jelly effect in the image and the standard image, so that the selection of the degree of the jelly effect is realized by adjusting the size of the vector difference. Based on this, whether the selected degree of the jelly effect matches the size of the calculated vector difference can be determined, thereby realizing the self-checking of the display device.

[0123] In one application scenario, the jelly effect in a video image is simulated and controllable, which can be increased in stages so as to adjust the jelly effect to a level that can be adapted by a student.

[0124] In some embodiments, the calculation process of the jelly effect can be implemented in the following way:

[0125] The collected video frame image with the jelly effect is binarized, and then the frame difference of each consecutive image is calculated. The larger the frame difference is, the more obvious the jelly effect is. Since new scenes will enter the picture during the movement of the scene, it will lead to inaccurate judgment of the jelly effect by frame difference only. Therefore, in this scheme, the nearest neighbor density is introduced, and unlike the traditional method of calculating the nearest neighbor density by distance, the gray value between each pixel after frame difference calculation is used as an indicator of the nearest neighbor density.

[0126] The nearest neighbor density of the gray value of each pixel in the image is calculated. If the anomaly score LOF (Local Outlier Factor) of each point is close to 1, it indicates that the local density of the sample point p is close to the neighbor. If the anomaly score LOF is less than 1, it indicates that p is in a relatively dense area and is not like an outlier. If the anomaly score LOF is much greater than 1, it indicates that p is relatively distant from other points and is likely to be an outlier. Thus, clustering of each pixel according to the gray value can be achieved, that is, the pixel points with consistent or close gray values will be in similar local densities.

[0127] In the process of calculating the nearest neighbor density, each image with the same or similar gray connected domain is taken as a target class, that is, the areas with similar gray values but not connected pixel points are distinguished as different target classes.

[0128] The union of the target classes in the front and rear frames is taken, and the overall motion vector between the pixels in the union area of the target classes can be calculated by the EPZS (Enhanced Predictive Zonal Search) enhanced predictive region search algorithm. Then, the same or similar motion vectors are merged again by k-neighbor density to obtain different classes with different motion vectors. On the other hand, the standard image frame corresponding to the current picture with the jelly effect is obtained by the optical flow method or the jelly effect repair software, and the overall vector difference between the motion vectors of each class area and the standard image frame is calculated.

[0129] Finally, the weight of the corresponding vector difference is calculated based on the number of pixels (i.e. area) of each class area, and the weighted sum of the vector difference and the corresponding weight is obtained to obtain the final vector difference of the whole image.

[0130] In another aspect of the present application, a self-checking device based on a flight simulation cockpit is also provided, comprising a detection device, a processor and a memory; the detection device is connected with devices in the flight simulation cockpit, and is used for detecting state information of the devices in the flight simulation cockpit after the devices are powered on, so as to obtain self-checking information; the processor is connected with the detection device, and is used for judging whether the self-checking signal is in a set range, so as to obtain a self-checking result; and the memory is connected with the processor, and is used for recording the self-checking result and corresponding time nodes and device information, so as to complete self-checking.

[0131] While the present application has been illustrated and described in detail in the drawings and foregoing description, such illustration and description is to be considered illustrative or exemplary and not restrictive; the present application is not limited to the disclosed embodiments. Various modifications, changes, and alternatives can be suggested to one skilled in the art without departing from the spirit and scope of the present application. It is understood that in the course of practicing the present application, various alternatives to the embodiments of the present application described herein can be employed. The claims appended hereto are intended to define the scope of the present application and thus cover any and all such alternatives, equivalents, or substitutes of elements of the modules claimed by the claims.

Claims

1. A self-checking method based on a flight simulation cockpit, characterized in that, The self-checking method comprises: in response to receiving the start control signal, controlling the equipment in the flight simulation cockpit to power on; acquiring a self-checking signal of the equipment in the flight simulation cockpit after the equipment is powered on, and judging whether the self-checking signal is in a set range to obtain a self-checking result; the self-checking method further comprises a step of self-checking the display equipment: acquiring a standard image frame; calculating all vector differences between motion vectors of each category region in a current image with the jelly effect and the standard image frame, wherein the step of calculating the motion vectors of each category region comprises: calculating the motion vectors by an enhanced prediction region search algorithm; calculating the weight of the corresponding vector difference according to the number of pixel points of each category region, and performing weighted summation on the vector difference and the corresponding weight to obtain the vector difference of the whole image; matching the strength of the jelly effect selected at the teaching terminal with the size of the vector difference corresponding to the image to judge whether the display equipment is abnormal; recording the self-checking result and corresponding time node and equipment information to complete self-checking; The flight simulation cockpit comprises: a simulation cockpit for simulating a cockpit and enabling a trainee to perform simulation operation thereon; a simulation server end for providing models of various components of an airplane; wherein the simulation server end is deployed with an airplane simulation subsystem, the airplane simulation subsystem comprising integrated processing software and a DDS soft bus, and the integrated processing software performing data interaction with component simulation models, algorithm models and airplane dynamics models through the DDS soft bus; a serial bus connected to the simulation server end and connected to the simulation cockpit through an interface manager to complete data interaction between the simulation server end and the simulation cockpit; the serial bus is also used to connect to an external teaching terminal to perform information interaction between the teaching terminal and the simulation cockpit and the simulation server end; The simulation server end transmits simulation video signals formed by simulation to the simulation cockpit through the interface manager, and transmits simulation audio signals formed by simulation to an audio device, wherein the audio device is used in combination with the simulation cockpit.

2. The self-checking method based on a flight simulation cockpit according to claim 1, characterized in that, The simulation cockpit is in communication connection with the interface manager through video signals, Ethernet signals and hard-wired signals.

3. The self-checking method based on a flight simulation cockpit according to claim 2, characterized in that, The serial bus is a 1394 bus.

4. The self-checking method based on a flight simulation cockpit according to claim 1, characterized in that, The simulation cockpit is deployed with a simulation cockpit subsystem, the interface manager is deployed with an interface management subsystem, and the simulation server end is deployed with a software integration and environment running subsystem, a sound simulation subsystem and an airplane simulation subsystem; The software integration and environment running subsystem is used to schedule each subsystem, control data interaction between each subsystem, and control communication between the interface management subsystem and the airplane simulation subsystem. The simulation cockpit subsystem is used to support hardware of the simulation cockpit, convert operations of a trainee into hard-wired signals or Ethernet signals, transmit the signals to the interface management subsystem, and accept video signals transmitted by the interface management subsystem for image display. The airplane simulation subsystem is used to run at least one component simulation model of an airplane. The sound simulation sub-system is configured to simulate at least one sound in flight. The interface management sub-system is configured to perform data conversion and transmission.

5. The self-checking method based on a flight simulation cockpit according to claim 4, characterized in that, The aircraft simulation sub-system is configured to run at least one component simulation model of an aircraft, including: The interface management sub-system is configured to perform data conversion and transmission.

6. The self-checking method based on a flight simulation cockpit according to claim 5, characterized in that, The component simulation model is connected to the DDS soft bus through an AMESim interface and a Simulink interface, the algorithm model is connected to the DDS soft bus through a C / C++ interface, and the flight dynamics model is connected to the DDS soft bus through a FlightSim interface.

7. The self-checking method based on a flight simulation cockpit according to claim 5, characterized in that, The integrated processing software includes flight management software, central warning software, and central maintenance software.

8. The self-checking method based on a flight simulation cockpit according to claim 4, characterized in that, The aircraft simulation sub-system is further configured to run an atmospheric data model configured to provide flight parameters calculated based on atmospheric data.

9. The self-checking method based on a flight simulation cockpit according to claim 8, characterized in that, The atmospheric data model is configured to receive corresponding parameters set by the teaching terminal and sensor information calculated by the aircraft simulation sub-system, and further calculate flight control parameters for further calculation by the aircraft simulation sub-system.

10. The self-checking method based on a flight simulation cockpit according to claim 4, characterized in that, The simulated cockpit sub-system includes a top control panel, a front control panel, a central console panel, a left console, a right console, and a control mechanism in the cockpit, and the control mechanism includes a steering column, a steering wheel, a footrest, and a throttle lever.

11. The self-checking method based on a flight simulation cockpit according to claim 10, characterized in that, The interface management sub-system is configured to complete signal acquisition, excitation, and data conversion and transmission of the top control panel, the front control panel, the central console panel, the left console, and the right console in the cockpit of the simulated cockpit sub-system; and the interface management sub-system is further configured to realize conditioning, adaptation, and transmission of electrical signals of the control mechanism in the simulated cockpit sub-system.

12. The self-checking method based on a flight simulation cockpit according to claim 10, characterized in that, The component simulation model includes one or more of a hydraulic system model, an environmental control system model, a fuel system model, a power plant model, an auxiliary power plant model, an oxygen system model, an environmental protection system model, a control model, and a lighting system model; and the control model includes a landing gear control system model and a hatch control system model.

13. The self-checking method based on a flight simulation cockpit according to claim 10, characterized in that, The top control panel includes one or more of the following control panels: An emergency positioning control panel, an in-cabin lighting control panel, an avionics start control panel, a flight control system control panel, a hydraulic system control panel, a backup parking control panel, a power supply system control panel, an engine start control panel, a fuel system control panel, an external lighting control panel, a windshield wiper control switch, a landing lighting control panel, a fire protection system control panel, a cabin audio monitoring control panel, an electromechanical management system control panel, a life-saving system control panel, an oxygen system control panel, an anti-icing system control panel, an air source system control panel, an air conditioning system control panel, and a pressure regulation system control panel.

14. The self-checking method based on a flight simulation cockpit according to claim 10, characterized in that, The front control panel includes one or more of the following: A left warning light, a right warning light, a left display control panel, a right display control panel, an automatic flight control panel, an approach warning light, a landing gear control handle, a landing gear light, and an automatic brake selection panel.

15. The flight simulation cockpit-based self-test method of claim 10, wherein, The central console includes one or more of the following: Emergency stop brake, horizontal stabilizer position indicator, multi-function display, horizontal stabilizer trim control handle, speed brake handle, horizontal stabilizer trim cutoff switch, flap handle, left and right trackball, left and right multi-function keyboard, normal stop switch, slat over-ride control panel, radio tuning unit, fire control panel, throttle control panel, audio control panel, trim control panel, select switch panel, door control panel, cockpit release control panel and electronic warfare control panel.

16. The self-checking method based on a flight simulation cockpit according to claim 10, characterized in that, The left console comprises a front seat oxygen mask control panel, a left dimmer control panel, a front seat front wheel turn handle, a left HUD control panel, a key control box, a time key control box and a headphone jack assembly.

17. The flight simulation cockpit-based self-test method of claim 10, wherein, The right console comprises a co-pilot seat oxygen mask control, a right dimmer control panel, a co-pilot seat front wheel turn handle, a right HUD control panel, an oxygen cutoff valve switch and a task loading / unloading card.

18. The self-checking method based on a flight simulation cockpit according to any one of claims 10 to 17, characterized in that, The control panels, the panels and the consoles in the analog cockpit subsystem are realized through physical simulation components and / or virtual simulation interfaces.

19. The self-checking method based on a flight simulation cockpit according to claim 10, characterized in that, The interface manager comprises: An image generation computer connected to the front control panel and the central control console through a DVI signal; An interface computer connected to the front control panel, the central control console, the top control panel, the left console and the right console through a network switch.

20. The flight simulation cockpit-based self-test method of claim 19, wherein, The interface manager further comprises: A power control box connected to the front control panel, the central control console, the top control panel, the left console and the right console respectively for direct current power supply.

21. The self-checking method based on a flight simulation cockpit according to claim 4, characterized in that, The sound simulation subsystem is used to simulate at least one sound in flight, including one or more sounds of environmental noise, airborne equipment working noise, prompt tone, alarm voice and audio signal superposition.

22. The flight simulation cockpit-based self-test method of claim 21, wherein, The alarm voice comprises a voice alarm sound, the airborne equipment working noise comprises a landing gear retraction sound, a flap retraction sound, an aircraft engine sound and a tire skid runway sound, and the environmental noise comprises external weather environment sound and air conditioning noise.

23. A self-checking device employing the self-checking method according to any one of claims 1 to 22, characterized in that, The sound simulation subsystem comprises: A detection device connected to the equipment in the flight simulation cockpit for detecting state information of the equipment after being powered on to obtain self-check information; A processor connected to the detection device for judging whether the self-check signal is in a set range to obtain a self-check result; and A memory connected to the processor for recording the self-check result and corresponding time node and equipment information to complete self-checking.

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