CN116312136A

CN116312136A - Aircraft cabin simulation system and fault simulation training method thereof

Info

Publication number: CN116312136A
Application number: CN202310383433.9A
Authority: CN
Inventors: 焦准; 严浩; 丁奇; 王发威; 张旭
Original assignee: Air Force Engineering University of PLA Aircraft Maintenace Management Sergeant School
Current assignee: Air Force Engineering University of PLA Aircraft Maintenace Management Sergeant School
Priority date: 2023-04-11
Filing date: 2023-04-11
Publication date: 2023-06-23

Abstract

The invention relates to an aircraft cabin simulation system and a fault simulation training method thereof, wherein the system comprises a simulation cabin, a simulation system and a fault simulation training system, wherein the simulation cabin is used for simulating the cabin and enabling a student to perform simulation operation on the simulation cabin; a teaching terminal on which a instructor operates to issue setting training contents; the simulation server side is used for providing models of various parts of the aircraft; the serial bus is connected with the teaching terminal and the simulation server end and is connected with the simulation cabin through an interface manager; the serial bus is used for carrying out data interaction among the teaching terminal, the simulation server and the simulation cabin; the simulation server side transmits the simulation video signals formed by simulation to the simulation cabin through the interface manager, and the simulation server side transmits the simulation audio signals formed by simulation to the audio equipment which is matched with the simulation cabin. The scheme solves the problems of high pressure and unstable simulation training display effect in the signal transmission process in the conventional simulation system.

Description

Aircraft cabin simulation system and fault simulation training method thereof

Technical Field

The present invention relates generally to the field of computer simulation technology. More particularly, the invention relates to an aircraft cabin simulation system and a fault simulation training method thereof.

Background

The flight simulation training device is a device for training pilots, and generally consists of a cockpit, interface devices, various instruments, a vision system and a training computer. The computer is a control center of the flight simulation training device. During training, a student sits in the cockpit and can perform various operations: the electric door is opened, the throttle is pushed and pulled, the flight bar and the rudder are operated, and various data such as the flight speed, the travel, the position, the height, the wind direction, the wind speed and the like can be obtained. The vision system can provide scene simulation for students, and the students feel the diving, upward and spiral actions like sitting in an airplane when operating, can see various scenes (clouds, fog, rivers and buildings) on and off the airplane, and can set various flying environments so as to comprehensively exercise technology and learn various operations with great difficulty and danger.

The flight simulation training device has the outstanding advantages of energy conservation, economy, safety, no limitation of site and meteorological conditions, shortening of training period, reduction of training cost, improvement of training efficiency and the like, and plays a very important role in pilot training. At present, various flight simulation training devices exist in China and are divided into two main categories of foreign import and domestic self-development. The civil aircraft flight simulation training device introduced from abroad mainly comprises two series of boeing, aeronautics and aeronautics. The number of the airplane flight simulation training devices which are automatically developed in China is relatively small, and the representative airplane flight simulation training device is mainly used for flight simulation training of a pilot basic piloting technology.

Aiming at the current domestic aircraft flight simulation training device, not only the content which can be seen by each visual angle of a student in the aircraft flight process is simulated by utilizing video, but also the audio signal is also assisted, so that the perception of the student to the actual operation environment in an instant state is met, and the video signal and the audio signal occupy larger bus resources at the moment. The utility model discloses a composition mode of a simulated aircraft, wherein communication and reflection memory card interconnection are established between a visual simulation computer, a simulation management computer, a cabin simulator, a real-time aircraft model and an onboard equipment simulation computer, a flight control flight tube computer simulator and a comprehensive computer through an optical fiber network switch, and real-time communication is performed. However, in the system, for simulation and data transmission of the view condition, the simulation and transmission of the video signal and the audio signal are required to occupy larger bus resources by uniformly completing the view simulation through a view simulation computer.

In view of this, in this aircraft flight simulation training device, in order to guarantee real-time and the synchronism of signal, data transmission bus faces great data transmission pressure, and the serious time probably leads to the stability of signal to become poor, seriously influences the effect of flight simulation training.

In view of this, the problems of the existing aircraft flight simulation training device are mainly that the pressure is high in the signal transmission process and the simulation training display effect is unstable.

Disclosure of Invention

In order to solve one or more of the technical problems, the invention proposes to transmit the signal with high synchronism requirement through the bus by separately wiring the audio signal and the video signal, and the audio signal can be directly transmitted to the audio device through the simulation server, so that the pressure of bus data transmission is reduced, and the sense of the pilot in simulating flying is more real and more similar. To this end, the present invention provides solutions in various aspects as follows.

In a first aspect, the present invention provides an aircraft simulation system comprising: a simulation cabin for simulating the cabin and enabling a trainee to perform a simulation operation thereon; a teaching terminal on which a instructor operates to issue setting training contents; the simulation server side is used for providing models of various parts of the aircraft; the serial bus is connected with the teaching terminal and the simulation server and is connected with the simulation cabin through an interface manager; the serial bus is used for carrying out data interaction among the teaching terminal, the simulation server and the simulation cabin; the simulation server side transmits simulation video signals formed by simulation to the simulation cabin through the interface manager, and transmits simulation audio signals formed by simulation to the audio equipment, wherein the audio equipment and the simulation cabin are matched for use.

In one embodiment, the analog cabin is communicatively coupled to the interface manager via a video signal, an ethernet signal, and a hard-wired signal.

In one embodiment, the serial bus is a 1394 bus.

In one embodiment, the simulation cabin is provided with a simulation cabin subsystem, the interface manager is provided with an interface management subsystem, the simulation server is provided with a software integration and environment operation subsystem, a sound simulation subsystem and an aircraft simulation subsystem, and the teaching terminal is provided with a teaching management subsystem; the system comprises a software integration and environment operation subsystem, a control interface management subsystem and an aircraft simulation subsystem, wherein the software integration and environment operation subsystem is used for scheduling each subsystem, controlling data interaction among each subsystem and controlling communication between the interface management subsystem and the aircraft simulation subsystem; the simulation cabin subsystem is used for supporting hardware of a simulation cabin, converting operation of a student into a hard wire signal or an Ethernet signal, transmitting the hard wire signal or the Ethernet signal to the interface management subsystem, and receiving a video signal transmitted by the interface management subsystem for image display; the aircraft simulation subsystem is used for running at least one component simulation model of an aircraft; the sound simulation subsystem is used for simulating at least one sound in flight; the teaching management and control subsystem is used for setting training contents; the interface management subsystem is used for carrying out data conversion transmission.

In one embodiment, the teaching management and control subsystem is configured to set training content, including: the teaching management and control subsystem is used for setting initial parameters of at least one component simulation model of the aircraft.

In one embodiment, the aircraft simulation subsystem is configured to run at least one component simulation model of an aircraft, comprising: and receiving control signals of the simulation cabin subsystem and model initial parameters of the teaching management and control subsystem, running corresponding set simulation models, and outputting data to other subsystems, wherein the control signals are generated by a student through controlling the simulation cabin.

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

In one embodiment, the component simulation model is connected with the DDS soft bus through an AMESim interface and a Simulink interface, the algorithm model is connected with the DDS soft bus through a C/C++ interface, and the flight dynamics model is connected with the DDS soft bus through a FlightSim interface.

In one embodiment, the integrated processing software includes flight management software, central alert software, and central maintenance software.

In one embodiment, the aircraft simulation subsystem is further configured to run an atmospheric data model for providing flight parameters based on the atmospheric data solution.

In one embodiment, the atmospheric data model is configured to receive corresponding parameters set by the teaching management and control subsystem and sensor information obtained by resolving by the aircraft simulation subsystem, further calculate flight control parameters, and further operate by the aircraft simulation subsystem.

In one embodiment, the analog cabin subsystem includes a roof control panel, a front control panel, a center console panel, a left console, a right console, and a steering mechanism within the cockpit, the steering mechanism including a steering column, a steering wheel, pedals, and a throttle lever.

In one embodiment, the interface management subsystem is used for completing signal acquisition, excitation and data conversion transmission of a top control board, a front control board, a central console panel, a left console and a right console of the cockpit in the analog cockpit subsystem; the interface management subsystem is also used for conditioning, adapting and transmitting the electric signals of the operating mechanism in the analog cabin subsystem.

In one embodiment, the component simulation model includes one or more of a hydraulic system model, a climate 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; the control models include a landing gear control system model and a door control system model.

In one embodiment, the top control panel comprises one or more of the following control panels: the emergency positioning control panel, the cabin lighting control panel, the avionics starting control panel, the flight control system control panel, the hydraulic system control panel, the backup parking control panel, the power supply system control panel, the engine starting control panel, the fuel system control panel, the external lighting control panel, the windshield wiper control switch, the landing lighting control panel, the fireproof system control panel, the cabin sound monitoring control panel, the electromechanical management system control panel, the lifesaving system control panel, the oxygen system control panel, the ice control system control panel, the air source system control panel, the air conditioning system control panel and the pressure regulating system control panel.

In one embodiment, the front control panel includes one or more of the following: left alarm lamp, right alarm lamp, left display control panel, right display control panel, automatic flight control panel, approach alarm lamp, undercarriage control handle, undercarriage lamp and automatic brake select plate.

In one embodiment, the central console includes one or more of the following: the system comprises a shutdown emergency brake, a horizontal stabilizer position indicator, a multifunctional display, a horizontal stabilizer balancing control handle, a speed reducing plate handle, a horizontal stabilizer balancing cut-off switch, a flap handle, a left track ball, a right track ball, a left multifunctional keyboard, a right multifunctional keyboard, a normal parking switch, a flap slat override control board, a radio tuning unit, a fire extinguishing control board, an accelerator control board, an audio control board, a balancing control board, a selection conversion board, a cabin door control board, a cabin air drop control board and an electronic warfare control board.

In one embodiment, the left console includes a front steering oxygen mask control board, a left dimming control board, a front steering handle, a left head up display control board, a key control box, a time key control box, and an earphone phone jack assembly.

In one embodiment, the right console includes a front passenger seat oxygen mask control, a right dimmer control board, a front passenger seat wheel steering handle, a right head up control board, an oxygen shut-off valve switch, a mission load/unload card.

In one embodiment, each control panel, panel and console in the cabin simulation subsystem is implemented by means of a physical simulation element and/or a virtual simulation interface.

In one embodiment, the aircraft simulation subsystem further comprises: the electric system model is used for carrying out data interaction 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; the electrical system model is also used for carrying out 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 carrying out state interconnection with the electrical control panel.

In one embodiment, the aircraft simulation subsystem further comprises: the fuel system model is used for carrying out data interaction with the engine model, the auxiliary power device model, the electromechanical management system model, the power supply system model, the teaching management and control subsystem and the fuel control panel.

In one embodiment, the aircraft simulation subsystem further comprises: and the landing gear retraction system model is used for carrying out data interaction with the landing gear control handle, the hydraulic system model, the power supply system model and the electromechanical management system.

In one embodiment, the interface manager includes: an image generating computer connected with the front control board and the central console through DVI signals; and the interface computer is used for being connected with the front control panel, the central console, the top control panel, the left console and the right console through the network switch.

In one embodiment, the interface manager further comprises: and the power supply control box is respectively connected with the front control board, the central control board, the top control board, the left control board and the right control board and is used for carrying out direct current power supply.

In one embodiment, the sound simulation subsystem is used for simulating at least one sound in flight, and comprises: superposition of one or more sounds of ambient noise, on-board equipment operating noise, alert tones, alarm voices, and audio signals.

In one embodiment, the warning sounds include voice warning sounds, and the on-board device operating noise includes landing gear retraction sounds, flap retraction sounds, aircraft engine sounds, sounds during tire dive tracks, and the ambient noise includes external weather ambient sounds and air conditioning noise.

In one embodiment, the sound simulation subsystem is coupled to the aircraft simulation subsystem for: acquiring simulation data of the aircraft simulation subsystem; analyzing an aircraft state signal and a first excitation signal from the simulation data; and selecting corresponding sounds according to the aircraft state signals and the first excitation signals to be overlapped so as to simulate the sounds perceived by the cockpit in the aircraft flight process.

In one embodiment, the sound simulation subsystem is further connected to the teaching management subsystem for: acquiring a control signal sent by the teaching management and control subsystem; and controlling the running state of the sound simulation subsystem according to the control signal of the teaching control subsystem.

In one embodiment, the sound simulation subsystem is further configured to: acquiring a second excitation signal sent by the teaching management and control subsystem; and selecting corresponding sound according to the second excitation signal to be overlapped with the sound perceived by the cockpit in the flight process of the aircraft so as to realize burst training in the teaching process.

In one embodiment, the first excitation signal includes an alert excitation signal and a navigational excitation signal, and the aircraft state signals include an aircraft flight state signal, an aircraft engine state signal, and a flap, landing gear state signal.

In one embodiment, the control signal includes adjusting a magnitude of the volume, configuring the sound channel, selecting the sound effect, starting, freezing, and resetting, and the second excitation signal includes a lightning excitation signal, a rain excitation signal, a snow excitation signal, and a high wind excitation signal.

In a second aspect, the invention also provides a fault simulation training method for an aircraft cabin simulation system as described in one or more of the embodiments above, comprising: receiving training content set by an instructor, wherein the training content comprises training subjects and training environments; loading aircraft parameters under corresponding configurations according to the training subjects and the training environment so as to simulate the aircraft running state corresponding to the training subjects; acquiring selection of possible faults of each subsystem of the aircraft; setting faults of all subsystems of the aircraft according to the selection completion so as to simulate the fault running state of the aircraft; receiving training operations of a learner aiming at the training content and the fault running state of the airplane; and driving the model to complete logic execution according to the training operation, and outputting an execution result to complete fault simulation training.

In one embodiment, the fault includes a jelly effect in the video image display, the selection of the fault that may occur to each subsystem of the aircraft includes a strength degree of the jelly effect, and the setting the fault of each subsystem of the aircraft according to the selection to simulate the fault running state of the aircraft includes: obtaining the strength degree of jelly effect selected by an instructor; simulating the jelly effect in the video image according to the strength degree of the jelly effect selected by the instructor to obtain a simulation result, wherein the simulation result comprises vibration conditions generated by the influence of external environment when the aircraft is in flight; and outputting the simulation result to a simulation cabin for display.

In one embodiment, the simulating the jelly effect in the video image according to the strength of the jelly effect selected by the instructor to obtain the simulation result includes: acquiring a standard image frame; calculating all vector differences between motion vectors of various areas 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 the pixel points of each class area, and carrying out weighted summation on the vector difference and the corresponding weight to obtain the vector difference of the whole image; and adjusting the size of the vector difference corresponding to the image according to the strength degree of the jelly effect selected by the instructor so as to adjust the display effect of the jelly effect in the image.

In one embodiment, the acquiring the standard image frame includes: and extracting a corresponding standard image frame from the current image with the jelly effect by using an optical flow method or jelly effect restoration software.

According to the scheme of the invention, the simulation video signals and the hard wire signals generated by the simulation server side are transmitted through the bus, so that the video signals and other signals on the bus are transmitted together, the synchronization is stronger, the operation is more real and reliable, the audio signals generated by the simulation server side are directly transmitted to the audio equipment through the independent wiring, the generated proper delay and the feeling of a pilot during simulated flight are more similar to the real condition, and the flight training simulation effect is effectively improved. Furthermore, corresponding subsystems and the like can be deployed in each part, and the subsystems are composed of software and/or hardware, so that the arrangement of the components of the aircraft cabin simulation system is thinned, and the training effect of a pilot in simulation training can be effectively improved.

Drawings

The above, as well as additional purposes, features, and advantages of exemplary embodiments of the present disclosure will become readily apparent from the following detailed description when read in conjunction with the accompanying drawings. Several embodiments of the present disclosure are illustrated by way of example, and not by way of limitation, in the figures of the accompanying drawings and in which like reference numerals refer to similar or corresponding parts and in which:

FIG. 1 is a schematic diagram schematically illustrating an aircraft cabin simulation system according to an embodiment of the invention;

FIG. 2 is a schematic diagram schematically illustrating the subsystem components of an aircraft cabin simulation system according to an embodiment of the invention;

FIG. 3 is a schematic diagram schematically illustrating an aircraft simulation subsystem according to an embodiment of the invention;

FIG. 4 is a schematic diagram schematically illustrating the cross-linking relationship of a flight management system according to an embodiment of the invention;

FIG. 5 is a schematic diagram schematically illustrating the cross-linking relationship of a central maintenance system according to an embodiment of the present invention;

FIG. 6 is a schematic diagram schematically illustrating a cross-linking relationship of an inertial navigation system according to an embodiment of the invention;

FIG. 7 is a schematic diagram schematically illustrating a top control panel according to an embodiment of the present invention;

FIG. 8 is a schematic diagram schematically illustrating a center console panel according to an embodiment of the present invention;

FIG. 9 is a schematic diagram schematically illustrating a left console according to an embodiment of the present invention;

FIG. 10 is a schematic diagram schematically illustrating a right console according to an embodiment of the present invention;

FIG. 11 is a schematic diagram schematically illustrating a steering mechanism according to an embodiment of the present invention;

FIG. 12 is a schematic diagram schematically illustrating the cross-linking relationship of a landing gear system with other systems according to an embodiment of the present invention; and

Fig. 13 is a flow chart schematically illustrating a fault simulation training method in accordance with an embodiment of the present invention.

Detailed Description

The following description of the embodiments of the present invention will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are some, but not all embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.

Specific embodiments of the present invention are described in detail below with reference to the accompanying drawings.

The aircraft cabin simulation system provided by the scheme is a set of semi-physical simulation system, can be designed based on the arrangement of a certain aircraft cabin, and can be used for completing various teaching training such as the area inspection of the aircraft cabin of the electromechanical system of the aircraft, the identification of cockpit parts, the inspection of the display function of the system cockpit, the system power-on inspection, the fault diagnosis and the fault isolation. Based on the above, the aircraft cabin simulation training system can be used for completing the operation training of the off-site maintenance subjects of the electromechanical profession and the avionics profession. In some application scenarios, practical subjects that the aircraft cabin simulation training system may accomplish include, but are not limited to, the following:

Engine starting, APU starting test run, engine cold running, landing gear retraction check, engine anti-icing system operation check, ram Air Turbine (RAT) hydraulic system performance check, cabin pressurization control system manual control function check, fuel system oil supply and delivery power check, pressure refueling control simulation, normal brake function check, front wheel steering system function check, cockpit inner lighting system power check, fuel system power check, hydraulic system power check, cabin door control system power check, environmental control system power check, anti-icing system power check, landing gear signal system power check, fire protection system power check, flight control system power check, exterior lighting lamp power check, emergency evacuation lighting system power check, electromechanical management system central maintenance MBIT and fault information check, atmospheric data subsystem operation test and the like.

Fig. 1 is a schematic diagram schematically illustrating an aircraft cabin simulation system according to an embodiment of the invention.

As shown in fig. 1, the aircraft simulation system comprises a simulation cabin, a teaching terminal, a simulation server side, an interface manager and audio equipment.

Wherein the simulation pod may be used to simulate the pod and have a trainee perform simulation operations thereon. In some embodiments, the simulation cabin can provide a hardware support structure for the simulation cabin and the base, which simulates the space layout of cabin sections and equipment in the cabin where the front and the back drivers are located on the floor of the cabin. The top control board, the front control board, the central control board, the left control board, the right control board and the like can be arranged in the simulation cabin to refer to the layout in the cabin for design, the size and the position can be approximately consistent with those of an airplane, and the internal space is equal to 1:1, except that some specific devices (such as a steering column, a steering wheel, a pedal, an accelerator lever and the like) are realized in a physical simulation mode, other devices can be realized in a mode of a touch screen and an equipment simulation software interface.

And the teaching terminal is used for a teacher to operate on the teaching terminal to release the set training content. The teaching terminal can realize the functions of development of control pages of training subjects, training environments and the like, interface drive development, development of process monitoring software and the like, such as training subject setting, training environment setting, process state monitoring function and initial parameter setting of an aircraft system model.

The simulation server side may be used to provide models of various components of the aircraft. The simulation server of the aircraft can be developed on the basis of a certain aircraft simulation model, and the working principle and the working flow simulation of each system of the aircraft are realized by means of digital simulation, data processing and the like through analyzing the system, the accessory working principle, the accessory working characteristic and the mathematical model on the basis of each system architecture of the aircraft. In the system design stage, simulation software in different fields can be used for establishing models of different subsystems (such as an engine, hydraulic pressure, fuel oil, landing gear, deicing prevention, flight dynamics and the like) in an aircraft system, the models established by the simulation software are effectively integrated, cooperatively simulated and optimally designed through a collaborative simulation technology, and dynamic simulation analysis is performed, so that the cross-linking influence among the subsystems is fully considered, design parameters of each aircraft subsystem are optimized, the goal of global optimization of the aircraft system is realized, and basis is provided for the design of an aircraft comprehensive management system.

Furthermore, the initial state parameters of the airplane system and the special condition simulation model can be set for special condition training.

The serial bus is connected with the teaching terminal and the simulation server, and is connected with the simulation cabin through an interface manager. The serial bus is used for carrying out data interaction among the teaching terminal, the simulation server side and the simulation cabin. In some embodiments, the interface manager can complete collection, excitation and transmission of control signals of a top control board and the like in the cockpit, and conditioning, adaptation and transmission of electrical signals of equipment such as a steering column, a steering wheel and the like are realized, so that instantaneity and effectiveness of the aircraft cabin simulation system in the training process are ensured. In one application scenario, the above-described analog pod is communicatively coupled to an interface manager via a video signal, an ethernet signal, and a hard-wired signal. The control box, track ball, etc. in the cockpit may output the ethernet signal and transmit it to the serial bus through the interface manager.

The serial bus can be a 1394 bus, and clock synchronization and simulation scheduling can be realized. Because the system adopts a real-time distributed simulation architecture, the synchronous clock adopts a mode that a 1394 network clock propagates through a data transmission network at a fundamental frequency, and each simulation model can judge whether to carry out simulation solution according to the solution period of the model and the received clock signal. Based on this, the real-time performance in the system can be determined by the accuracy of the master clock, the transmission characteristics of the data network, the operating system, and the like.

Specifically, the simulation server side transmits the simulation video signal formed by simulation to the simulation cabin through the interface manager, and transmits the simulation audio signal formed by simulation to the audio equipment, wherein the audio equipment and the simulation cabin are matched for use. In one application scenario, the emulated video signal is transmitted over the bus, while the emulated audio signal is transmitted and played over alone. By the method, signals with different synchronicity requirements are distinguished, and the simulation video signals on the bus, the Ethernet signals and the hard wire signals have better synchronicity, so that user experience is closer to the real situation. While the audio signal allows some delay, which is closer to the actual feel of the pilot when simulating a flight, the audio signal is slower than the video signal. Based on this, can independently transmit audio signal, on the one hand effectively save bus resource, reduced transmission pressure, on the other hand can make the simulation effect press close to reality more, promote the training experience of student.

In actual operation, a teacher can control operations such as powering on and powering off equipment of the whole system, starting, stopping and resetting of the simulation system through the teaching terminal, and complete training environment setting and initial setting of aircraft system model parameters, and can monitor states in the training process. The trainee completes the training by operating the simulation equipment in the simulation cabin. The operation signals are sent to the simulation server through the interface manager, and the simulation server drives models of electromechanics, avionics, flight control and the like according to the operation of a learner to complete corresponding logic execution and generate corresponding result states. And transmitting the result state of the model after execution to a corresponding state indication signal in the simulation cabin through an interface manager and audio equipment, and completing the training process.

The basic architecture and the working principle of the aircraft cabin simulation system according to the invention are described above in connection with fig. 1, and the different sets of shaping forms of each part will be described in detail below.

Fig. 2 is a schematic diagram schematically illustrating the subsystem components of an aircraft cabin simulation system according to an embodiment of the invention.

As shown in fig. 2, the simulation cabin is deployed with a simulation cabin subsystem, the interface manager is deployed with an interface management subsystem, the simulation server is deployed with a software integration and environment operation subsystem, a sound simulation subsystem and an aircraft simulation subsystem, and the teaching terminal is deployed with a teaching management and control subsystem.

The system comprises a software integration and environment operation subsystem, a control interface management subsystem and an aircraft simulation subsystem, wherein the software integration and environment operation subsystem is used for scheduling each subsystem, controlling data interaction among each subsystem and controlling communication between the interface management subsystem and the aircraft simulation subsystem. In some embodiments, the main functions of the software integration and environment execution subsystem may include, for example, the following aspects:

a) Network computing nodes can be added/deleted, and the states of the computing nodes of each simulation subsystem are monitored;

b) Remotely deploying the latest simulation software or model of each subsystem in each computing node;

c) Remotely running the models or software of each simulation node, and monitoring the running states of all simulation models;

d) The 1394 network is adopted to realize clock synchronization and data transmission, and the clock jitter is less than 5ms;

e) And monitoring the simulation network data transmission in real time.

The system comprises an analog cabin subsystem, a video signal receiving subsystem and an interface management subsystem, wherein the analog cabin subsystem is used for supporting hardware of an analog cabin, converting operation of a student into a hard wire signal or an Ethernet signal, transmitting the hard wire signal or the Ethernet signal to the interface management subsystem, and receiving a video signal transmitted by the interface management subsystem for image display. In particular, the simulation cockpit subsystem may provide a realistic aircraft pilot simulation cockpit. Cabin size, inside overall arrangement are unanimous with the aircraft being simulated, can simulate instrument, display, indicator, lamp, switch, button and controlling means, can be with its outward appearance, size, mounted position, instruction sign, function and working limit condition, instrument mode of operation, operation mode, operating characteristic etc. unanimous with the aircraft. In one application scenario, the analog cockpit subsystem may include a top control panel, a front control panel, a center console panel, a left console, a right console, and a steering mechanism within the cockpit, the steering mechanism including a steering column, a steering wheel, pedals, and a throttle lever.

In one application scenario, a certain type of aircraft cabin is taken as a simulation object, and the simulation cabin simulation subsystem can comprise a simulation cabin body, control mechanism functions (including a steering column, a steering wheel and pedals), equipment control boxes/boards (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 and the like). The arrangement of all the components in the aircraft cabin can be simulated by adopting a physical simulation piece, and also can be simulated by adopting a touch screen mode as a hardware equipment control interface so as to realize equipment simulation. Devices such as steering levers, steering wheels, pedals and the like are simulated by using physical simulation pieces. Other panel devices adopt a touch screen mode as a hardware device control interface, and software function interfaces of a device control box/board are developed on the touch screen interface, so that simulation of the hardware device is realized. The respective partial structure arrangements will be described in detail in the following exemplary schemes of fig. 4 to 8. Furthermore, in order to facilitate maintenance and later modification, the cabin body, the control box and other parts can be in modularized design, and reliability and simulation degree can be ensured as much as possible. Meanwhile, the hard wire signals generated by the operating mechanism and the like can be transmitted in an Ethernet communication mode, so that the data transmission efficiency, the reliability and the maintainability are improved.

An aircraft simulation subsystem for operating at least one component simulation model of an aircraft. The aircraft simulation subsystem is the core of the aircraft cabin simulation system, and can embody 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, simulation models of an aircraft power device, an auxiliary power device, a fuel system, a hydraulic system, a ring control system and the like can be developed. The aircraft simulation subsystem can provide a graphical environment, can define the parameter information of the aircraft such as the take-off weight, the oil quantity, the center and the like, and provides a typical aircraft flight dynamics model to be embedded into a simulation system to simulate in a cooperative manner with the models in the previous and later modes so as to provide environmental data excitation for the models.

And the sound simulation subsystem is used for simulating at least one sound in flight. In some embodiments, the sound simulation subsystem can simulate various stages of ground running, taking off, flying in the air, descending, landing in the approach and the like of the aircraft, and the flight personnel can feel sounds in the cockpit, including environmental noise, working noise of airborne equipment, prompt tones, alarm voices and the like. In the practical application process, various sounds in the aircraft flight process are stored in the sound database. The sound simulation subsystem can receive data in a simulation network (such as simulation data in an airplane simulation system, control commands input in a teaching management and control subsystem and the like), obtain a current sound list to be played through analysis and logic processing of the data, call corresponding sound files from a sound database according to the list to play, and finally play through audio equipment. The played sound can be one sound or a superposition of multiple sounds, so as to simulate the sound in the real environment.

In some embodiments, the above-described sound simulation subsystem may be used to simulate at least one sound in flight. These sounds may include: superposition of one or more sounds of ambient noise, on-board equipment operating noise, alert tones, alarm voices, and audio signals. The warning voice comprises voice warning sound, the working noise of the airborne equipment comprises landing gear retraction sound, flap retraction sound, aircraft engine sound and sound when a tire dives a runway, and the environmental noise comprises external weather environmental sound and air conditioning noise.

In some embodiments, a sound simulation subsystem is coupled to the aircraft simulation subsystem and may be used to obtain simulation data for the aircraft simulation subsystem. The aircraft state signal and the first excitation signal are then resolved from the simulation data. Corresponding sounds are selected to be overlapped according to the aircraft state signals and the first excitation signals so as to simulate sounds perceived by the cockpit in the aircraft flight process.

Further, the sound simulation subsystem is further connected with the teaching management and control subsystem and is further used for: and acquiring a control signal sent by the teaching management and control subsystem. And controlling the running state of the sound simulation subsystem according to the control signal of the teaching control subsystem.

In some embodiments, the sound simulation subsystem is further configured to: and obtaining a second excitation signal sent by the teaching management and control subsystem. And selecting corresponding sound according to the second excitation signal to be overlapped with the sound perceived by the cockpit in the flight process of the aircraft so as to realize burst training in the teaching process.

Specifically, the first excitation signal includes an alert excitation signal and a navigational excitation signal, and the aircraft state signal includes an aircraft flight state signal, an aircraft engine state signal, and a flap, landing gear state signal. The control signals may include adjusting the magnitude of the volume, configuring the sound channel, selecting the sound effect, starting, freezing, and resetting, and the second excitation signals include a lightning excitation signal, a rain excitation signal, a snow excitation signal, and a high wind excitation signal.

And the teaching management and control subsystem is used for setting training contents. In some embodiments, the teaching management subsystem is configured to set training content, including the teaching management subsystem being configured to set initial parameters of at least one component simulation model of the aircraft. For example, functions such as training environment settings (including airport condition settings, airline environment settings, weather condition settings, activity target settings, etc.), training subject settings (e.g., training aircraft settings, flight mission settings, fault clearance, etc.), interface settings (e.g., audio call settings, frequency settings, and tower settings), process status monitoring (aircraft data monitoring, maneuvering data monitoring, movement data monitoring, interface data monitoring, etc.), aircraft system model initial parameter settings (aircraft weight settings, start/stop, freeze/thaw, reset, etc.), record storage, and trainee assessment (e.g., trainee information management, assessment manual assessment, and system maintenance management) may be performed. In one application scenario, the teaching management and control subsystem software may provide the operator with airport conditions, airlines, natural environments, etc. before the simulated environment is run, where the specific settings include: airport condition settings such as airport selection, airport elevation, magnetic difference, take-off direction, initial setting of shutdown, radio frequency, field pressure, field temperature, audio signals and the like are provided.

Furthermore, the teaching management and control subsystem can set faults possibly occurring in each subsystem of the aircraft, fault pages are divided according to ATA chapters (Chinese-English contrast), functions of setting faults and presetting faults are provided for each system, and when faults are selected, pop-up text boxes are displayed in the teaching management and control subsystem to indicate system choices (such as left or right) possibly causing faults. The preselected criteria and fault impact and description are also displayed in the pop-up box. The instructor may review the effect of the fault and illustrate the system selected to cause the fault. The aircraft can also be recovered to a normal training state through a fault clearing function.

And the interface management subsystem is used for carrying out data conversion transmission. The interface management subsystem comprises a signal processing and interface adapting unit and a system simulation scheduling software module. The interface management subsystem is a center for data conversion and transmission of the training system and is responsible for conditioning, transmission and adaptation between the internal data of the aircraft simulation training system and a cabin hardware interface. The signal processing and interface adapting unit is used for completing the electric signal collection and lamp signal driving functions of the cab top control board, the front control board, the central operation desk, the left operation desk and the right operation desk. The electrical signals on the cockpit operating panel basically include discrete quantities, analog quantities, and a portion of the bus signal. In some embodiments, the interface management subsystem is configured to perform signal acquisition, excitation and data transfer for the top control panel, front control panel, center console panel, left console and right console of the cockpit in the analog cockpit subsystem by the above connection. The interface management subsystem is also used for conditioning, adapting and transmitting the electric signals of the operating mechanism in the analog cabin subsystem.

Because of the large number of equipment modules within the cockpit, each control panel contains a variety of electrical signals as well as drive signals. Therefore, the system uses each control board as a basic unit for signal processing and interface adaptation, and interacts with the aircraft system simulation subsystem, the teaching management and control subsystem and the like in a network signal mode. Meanwhile, the avionics simulation part of the virtual cabin needs a simulation image fusion function, so that the signal processing and interface adapting unit needs to acquire video signals, and the video signals are displayed on equipment after being transmitted. The network signal is used for collecting control data interaction, the equipment uploads the state of the equipment to the interface computer at regular time through the network, and the interface computer sends the control signal to each equipment through the network.

Fig. 3 is a schematic diagram schematically illustrating an aircraft simulation subsystem according to an embodiment of the invention.

As shown in fig. 3, the aircraft simulation subsystem includes integrated processing software and a DDS soft bus. And the comprehensive processing software performs data interaction with the component simulation model, the algorithm model and the flight dynamics model through the DDS soft bus. The distributed real-time simulation soft bus based on the DDS can effectively connect various simulation software on different computers, and can perform unified simulation management, including reliable data communication and time propulsion mechanisms, and interface data are shared among different simulation software so as to realize system simulation analysis. In some embodiments, the component simulation model may include one or more of a hydraulic system model, a climate 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. The control models include a landing gear control system model and a door control system model.

In some embodiments, the aircraft simulation subsystem described above may be used to run at least one component simulation model of an aircraft, comprising: and receiving control signals of the simulation cabin subsystem and model initial parameters of the teaching management and control subsystem, running corresponding set simulation models, and outputting data to other subsystems, wherein the control signals are generated by a student through controlling the simulation cabin.

In some embodiments, the emulation interfaces described above may include an AMESim interface, a Simulink interface, and a FlightSim interface. The component simulation model is connected with the DDS soft bus through an AMESim interface and a Simulink interface, the algorithm model is connected with the DDS soft bus through a C/C++ interface, and the flight dynamics model is connected with the DDS soft bus through a FlightSim interface.

The integrated processing software comprises flight management software, central alarm software and central maintenance software.

The flight management software mainly realizes the functions of airplane navigation, flight plan management, performance calculation, track connection optimization, guiding function, air drop task calculation, database management, comprehensive monitoring, alarming and the like. The main tasks are to optimize the flight path, improve the navigation precision and reduce the pilot driving burden, thereby ensuring the task to be completed with high efficiency. The flight management software can utilize relevant navigation and aircraft state data input by the sensors, and on the basis of reference data provided by the navigation database and the performance database, the flight guidance calculation is performed in real time, so that the pilot is assisted to control the flight track of the aircraft, and the aircraft flies according to a pre-established flight plan and the currently selected performance mode.

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 a general processing module (CPM) in the Integrated Processor (IPC) and other subsystems for providing functional support for it. The FMS takes an analog control display unit (SCDU), a Navigation Display (ND), a main flight display (PFD), a keyboard and the like provided by a display control subsystem (hereinafter referred to as CDS) as main human-computer interfaces; inertial/satellite integrated navigation equipment (INS), an atmospheric data device (ADC), a radio navigation device, an electromechanical management computer (EMP) and the like are used as navigation sensors and aircraft state sensors; an Automatic Flight Control System (AFCS) is used as the main executive component of the flight. In addition, the FMSA updates the navigation database and performance database contents through the loading and unloading device, and can unload the pilot database contents.

The flight management system model provides support for pilots to complete the entire flight mission, including guidance, information calculations related to the flight process, and the like. In particular, the flight management system model may simulate the following functions: integrated navigational management, flight planning management, performance calculation, guidance, military mission management, database management, and integrated monitoring and alerting. Correspondingly, according to the functional division, the flight management system model can be divided into the following interfaces: a comprehensive navigation control interface, a flight plan editing interface, a performance setting interface, a control interface (suppression, conversion, interception and the like) and a database interface.

Based on the above interface setting, the cross-linking relationship of the flight management system function interface and the dependency relationship between the flight management system function division and the functions are as shown in fig. 4:

a) The flight plan editing and managing function is completed through the flight plan editing interface, the editing of the flight plan is completed by relying on the navigation database managing function, and the database can complete the support of other functions through the database interface; b) Setting a control interface to complete a horizontal driving function, and horizontally guiding the horizontal driving according to aircraft parameters provided by a flight plan and a comprehensive navigation function; c) Carrying out parameter calculation of airplane position, airplane speed, airplane height and the like by comprehensive navigation; d) The track planning is used for generating a three-dimensional track of the aircraft according to the current process; e) The aircraft basic performance calculation is used for determining performance parameters of the aircraft platform under various conditions; f) Vertical piloting is used to control aircraft altitude to meet vertical constraint requirements of a flight plan; g) Based on the calculated three-dimensional flight path of the airplane, HSD information and fuel oil arrival time information can be calculated; h) An interface symbol, which represents that the CDS can control the execution of a certain function.

The central alarm software receives fault alarm information from various systems/devices in the aircraft, configuration alarm information of the aircraft and threat alarm information (danger level, warning level, attention level, consultation level and prompt level) outside the aircraft, carries out alarm information logic processing and priority sequencing, drives the lamplight alarm, drives the display processing unit to display the alarm information, drives the audio device to generate voice/tone alarm, receives and processes the threat alarm output by alarm types including electronic support reconnaissance equipment, ground proximity alarm equipment and the like, and carries out fault alarm output by in-aircraft systems/devices such as flight control, engine, hydraulic pressure, environmental control and the like, aircraft configuration alarm and the like.

The central maintenance software realizes basic functions of processing, storing, retrieving and displaying calling logic of fault information of an aircraft system, ground test operation flow, state monitoring operation flow, software and hardware configuration management identification, data loading operation flow and the like.

The central maintenance system may be constituted by the above-described central maintenance software, and the cross-linking relationship between the central maintenance system and each system is as shown in fig. 5, and the central maintenance system software may display maintenance information using a left and right multifunction flight monitor and transmit data to the outside by using a printer or a data link. LRU (line replaceable unit) faults may also be connected to avionics and non-avionics systems, such as air conditioning systems, automatic flight systems, fire protection systems, fuel systems, landing gear systems, lighting systems, navigation systems, oxygen systems, auxiliary power systems, engine systems, etc., may be received and the fault LRU name displayed.

The aircraft simulation subsystem in the invention also comprises an inertial navigation system model (hereinafter referred to as inertial navigation system model). The inertial navigation system is a parameter resolving system of a trainer, realizes an all-weather, all-gesture 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 airplane equation, receives satellite information and atmospheric data information from a GPS subsystem, outputs the information such as the position, the course, the gesture, the speed, the acceleration, the angular velocity, the altitude, the global magnetic difference, the time and the like of the airplane through an HB6096 simulation interface, and is used for airplane navigation calculation, data display, flight control, parameter recording and air drop.

As shown in fig. 6, the inertial navigation system may be coupled to a main flight control system, an automatic flight control system, a remote data concentrator (Remote Data Concentrator, RDC for short), and a decentralized processing unit (Distributed Processing Unit, DPU for short). The inertial navigation system can comprise inertial satellite integrated navigation 1, inertial satellite integrated navigation 2 and inertial satellite integrated navigation 3. The 2 inertial satellite integrated navigation systems are respectively crosslinked with a main flight control system, an automatic flight control system, RDC and DPU.

The external system crosslinked with the engine system (model) can be formed by a model of a flight control system, an avionics system, a power supply system, a hydraulic system, a environmental control system, a fuel system, a fire protection system and the like.

Furthermore, the aircraft simulation subsystem is further used for running an atmosphere data model, and the atmosphere data model is used for providing flight parameters obtained based on atmosphere data calculation. In some embodiments, the atmosphere data model is further configured to receive corresponding parameters set by the teaching control subsystem and sensor information obtained by the aircraft simulation subsystem through calculation, further calculate flight control parameters, and further operate by the aircraft simulation subsystem. The atmosphere data model may 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 management and control subsystem and the information of total pressure, static pressure, attack angle and sideslip angle calculated by an airplane model in a flight system, the data are input into an atmospheric data computer simulation module after passing through a sensor model, vacuum speed, indicated airspeed, mach number, air pressure height, corrected air pressure height, vertical speed and the like are obtained through stages, and finally the data are sent to each flight dynamics model for calculation so as to display flight data.

The software simulation part in each simulation subsystem is described in detail above, and the content of realizing the simulation of the aircraft structure by the cooperation of various functional models in the aircraft simulation subsystem is described. The following will describe the panels made up of the software and hardware of the various parts of the simulated cabin subsystem.

In some embodiments, each control panel, panel and console in the simulated cabin subsystem is implemented by way of a physical simulation and/or virtual simulation interface.

As shown in fig. 7, the top control panel may include one or more of the following control panels: the emergency positioning control panel, the cabin lighting control panel, the avionics starting control panel, the flight control system control panel, the hydraulic system control panel, the backup parking control panel, the power supply system control panel, the engine starting control panel, the fuel system control panel, the external lighting control panel, the windshield wiper control switch, the landing lighting control panel, the fireproof system control panel, the cabin sound monitoring control panel, the electromechanical management system control panel, the lifesaving system control panel, the oxygen system control panel, the ice control system control panel, the air source system control panel, the air conditioning system control panel and the pressure regulating system control panel.

The front control panel includes one or more of the following: left alarm lamp, right alarm lamp, left display control panel, right display control panel, automatic flight control panel, approach alarm lamp, undercarriage control handle, undercarriage lamp and automatic brake select plate.

As shown in fig. 8, the central console includes one or more of the following: the system comprises a shutdown emergency brake, a horizontal stabilizer position indicator, a multifunctional display, a horizontal stabilizer balancing control handle, a speed reducing plate handle, a horizontal stabilizer balancing cut-off switch, a flap handle, a left track ball, a right track ball, a left multifunctional keyboard, a right multifunctional keyboard, a normal parking switch, a flap slat override control board, a radio tuning unit, a fire extinguishing control board, an accelerator control board, an audio control board, a balancing control board, a selection conversion board, a cabin door control board, a cabin air drop control board and an electronic warfare control board. The shutdown emergency brake, the horizontal stabilizer position indication, the multifunctional display, the horizontal stabilizer balancing control handle, the speed reducing plate handle, the flap handle, the left and right track balls and the left and right multifunctional keyboards can be realized by adopting physical simulation pieces and are arranged around the multifunctional display. And the other parts are realized in the touch screen through software interface simulation.

As shown in fig. 9, the left console includes a front-driving-position oxygen mask control board, a left dimming control board, a front-driving-position front wheel steering handle, a left head-up display control board, a key control box, a time key control box, and an earphone phone jack assembly. The earphone microphone jack component is realized by adopting a physical simulation piece, and the other components can be realized by simulating a software interface in the touch screen.

As shown in FIG. 10, the right console includes a front passenger side oxygen mask control, a right dimmer control board, a front passenger side wheel steering handle, a right head up display control board, an oxygen shut-off valve switch, and a mission load/unload card. In addition, a headset microphone jack assembly is included for providing a voice call function device for the co-pilot.

As shown in fig. 11, a steering column mechanism, a steering wheel mechanism, and a foot pedal mechanism, which can be simulated by a physical simulation member, are also provided in the cockpit.

In some embodiments, the scheme of the invention also simulates a power supply system model for supplying power to the aircraft cabin simulation system, including an electrical system model, a fuel system model and the like.

Based on the above, the aircraft simulation subsystem further comprises: and the electric system model is used for crosslinking 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 carrying out 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 carrying out state interconnection with the electrical control panel.

Further, the aircraft simulation subsystem further comprises: the fuel system model is used for carrying out data interaction with the engine model, the auxiliary power device model, the electromechanical management system model, the power supply system model, the teaching management and control subsystem and the fuel control panel. Further, the fuel system model is also cross-linked with a fuel control panel to achieve fuel control.

Under normal conditions of the fuel system, each AC main power channel works independently, and the AC generator only supplies power to the generator bus bar and the AC main bus bar of the channel. When a certain channel fails, the system can automatically perform isolation and protection, and the other generator on the same side supplies power to the two generator bus bars and the alternating current main bus bar on the same side. When two channels on the same side are in failure, if the auxiliary generator does not work, the two generators on the other side supply power to the two alternating current main bus bars on the side through the power supply conversion control function of the power supply control management subsystem: if the auxiliary generator is put into operation, power is supplied to the two generator bus bars and the ac main bus bar on the present side by the auxiliary generator.

The aircraft simulation subsystem further comprises: and the landing gear retraction system model is used for carrying out data interaction with the landing gear control handle, the hydraulic system model, the power supply system model and the electromechanical management system.

As shown in fig. 12, the cross-linking relationship between the landing gear retraction system model and other systems in the aircraft cabin simulation system includes: the landing gear retraction system model is connected with the landing gear signal lamp box and is used for displaying landing gear position information. The landing gear retraction system model can be further connected with a ground proximity warning system, a system control device (System Control Unit, SCU for short), a brake control unit (Brake Control Unit, BCU for short), an electromagnetic pulse weapon (electromagnetic pulse, EMP, a neutral electronic waybill platform (Digital Air Waybill Platform, DAP for short), an accelerator table back-pushing unlocking device, a generator control device and the like so as to realize corresponding functions according to wheel load information.

In some embodiments, the interface manager includes an image generation computer and an interface computer. And the image generating computer is connected with the front control panel and the central console through DVI signals. The interface computer is used for connecting with the front control board, the central console, the top control board, the left console and the right console through the network switch. The interface manager also comprises a power control box which is respectively connected with the front control board, the central control board, the top control board, the left control board and the right control board for direct current power supply.

As shown in fig. 13, at step S1301, training content set by an instructor is received, the training content including a training subject and a training environment. In practical application, a teacher logs in the system general control and training setting software through the teaching terminal, and sets training subjects, training environments and the like while completing demonstration and explanation according to the outline requirement of the teaching.

At step S1302, aircraft parameters in a corresponding configuration are loaded according to a training subject and a training environment to simulate an aircraft running state corresponding to the training subject. After receiving information such as training subjects and training environments set by the teaching terminal, the simulation server can finish adjustment and simulation of the running state of the aircraft corresponding to the training subjects through loading each data model in the information, and transmits corresponding control signals to a simulation cabin and the like so as to simulate the running state of the aircraft.

At step S1303, a selection is obtained of possible faults for each subsystem of the aircraft. In some embodiments, the selection of the fault may be set at the time of setting the training subjects and training environment, or may be set during the training process.

At step S1304, the configuration of the faults of the aircraft subsystems is performed according to the selection completion to simulate a faulty operating state of the aircraft. Each subsystem in the simulation server side can inject corresponding fault information into the aircraft simulation system according to the set faults, so that the aircraft in the fault state is simulated.

At step S1305, training operations of the trainee are received with respect to training content and a faulty running state of the aircraft. The student looks over working process demonstration in the course of the instructor explanation, according to the training subjects that the instructor set up, through looking over the display content of comprehensive instrument software and vision display software, operate these 3 cabin simulation panels of autopilot control panel, state selection board and weapon operator control panel, accomplish the purpose operation process of training branch of academic or vocational study (the instructor before the student operates according to training subjects and in-process, select to inject various different grade system faults through the fault analysis module, the student can learn how to carry out fault analysis and troubleshooting according to the fault phenomenon).

At step S1306, the driving model completes logic execution according to the training operation, and outputs the execution result to complete the fault simulation training. In some embodiments, system control and training set-up software in the teaching terminal records the learner's operational process data. And the instructor checks the data recorded by the software to evaluate the operation process of the instructor.

Furthermore, the students can also check the data recorded by the system and the evaluation of the instructor through logging in the system general control and training setting software to carry out error correction and summarization.

In some embodiments, the failure includes a jelly effect in the video image display. The choice of possible faults for each subsystem of the aircraft includes the degree of jelly effect. For example, in a teaching management and control subsystem in a teaching terminal, a selection switch and an adjustment switch of the jelly effect can be correspondingly arranged, and the adjustment switch can be a knob type switch, so that stepless adjustment of the degree of the jelly effect is realized. When the fault of each subsystem of the airplane is set according to the selection of the instructor so as to simulate the fault running state of the airplane, firstly, the strength degree of the jelly effect selected by the instructor is obtained. Then, the jelly effect in the video image is simulated according to the strength of the jelly effect selected by the instructor, so as to obtain a simulation result, wherein the simulation result comprises vibration conditions generated by the influence of external environment on the aircraft in flight. And finally, outputting the simulation result to a simulation cabin subsystem for display.

The above-described simulation process may be implemented in the following manner, specifically, standard image frames are acquired. All vector differences between the motion vectors of the respective areas in the current image with the jelly effect and the standard image frame are calculated. And then calculating the weight of the corresponding vector difference according to the number of the pixel points of each category region, and carrying out weighted summation on the vector difference and the corresponding weight to obtain the vector difference of the whole image. And adjusting the size of the vector difference corresponding to the image according to the strength degree of the jelly effect selected by the instructor so as to adjust the display effect of the jelly effect in the image.

It will be appreciated that when the instructor selects the extent of the jelly effect, the adjustment switch corresponds to the magnitudes of the vector differences described above, each vector difference representing the extent of deviation between the jelly effect in the image and the standard image, respectively, whereby the extent of the jelly effect is selected by adjusting the magnitudes of the vector differences.

In one application scenario, the jelly effect in the video image is simulated and adjustably controlled, and can be graded or gradually increased, so that the jelly effect can be adjusted to the extent that the learner can adapt to.

In the practical application process, the adopted image has jelly effect, so that the corresponding standard image frame needs to be extracted from the image, namely the standard image without jelly effect. In some embodiments, the standard image frame corresponding to the current picture with the jelly effect can be obtained by using an optical flow method or jelly effect repairing software. The degree of the jelly effect is regulated by calculating the integral vector difference between the motion vector of each class area in the current picture and the standard image frame and utilizing the size of the integral vector difference. Specifically, the number (i.e. the area) of the pixel points of each area in the picture is taken as a reference to calculate the weight of the corresponding vector difference, the vector difference and the corresponding weight are weighted and summed to obtain the vector difference of the final whole image, and the corresponding degree of jelly effect can be generated in the image by utilizing the vector difference, so that the dynamic regulation and control of the jelly effect are realized by regulating the size of the vector difference.

In some embodiments, the process of regulating the jelly effect may be achieved by:

and binarizing the acquired video frame images with the jelly effect, and then calculating the frame difference of each front and rear continuous image, wherein the larger the frame difference is, the more obvious the jelly effect is. Since a new scene enters a picture in the process of moving the scene, the jelly effect is not accurately judged only by the frame difference, and therefore, the nearest neighbor density is introduced in the scheme, and is different from the nearest neighbor density calculated by distance in the traditional method, and the gray value among pixels after the frame difference is calculated as an index of the nearest neighbor density in the scheme.

The nearest neighbor density of the gray value of the pixel point in each image is calculated, wherein the anomaly score LOF (Local Outlier Factor, local anomaly factor algorithm) of each point is close to 1, and the local density of the sample point p is close to the neighbor. If the anomaly score LOF is less than 1, p is indicated to be in a relatively dense region, unlike an outlier. If the anomaly score LOF is much greater than 1, p is more distant than the other points, and is likely to be an anomaly point. Therefore, the pixel points can be clustered according to the gray values, namely, the pixel points with consistent gray values or very close gray values are in similar local densities.

In the process of calculating the nearest neighbor density, the region with the same or close gray connected domain in each image, which is used as one target class, namely the region with similar gray values but non-connected pixels, is divided into different target classes.

The union is taken for the target class in the previous and subsequent frames, and the motion vector can be calculated by the EPZS (Enhance Predictive Zonal Search) enhanced prediction area search algorithm through the overall motion vector between pixels in the union area of the target class. Then, the same or similar motion vectors are integrated again through k neighbor density to obtain different categories with different motion vectors. On the other hand, a standard image frame corresponding to the current picture with the jelly effect is obtained through an optical flow method or jelly effect restoration software, and the overall vector difference between the motion vector of each type of region and the standard image frame is calculated.

And finally, calculating the weight of the corresponding vector difference by taking the number (i.e. the area) of the pixel points of each class area as a reference, and carrying out weighted summation on the vector difference and the corresponding weight to obtain the vector difference of the final whole image, thereby finally realizing the dynamic regulation and control of the jelly effect by regulating the size of the vector difference.

While various embodiments of the present invention have been shown and described herein, it will be obvious to those skilled in the art that such embodiments are provided by way of example only. Many modifications, changes, and substitutions will now occur to those skilled in the art without departing from the spirit and scope of the invention. It should be understood that various alternatives to the embodiments of the invention described herein may be employed in practicing the invention. The appended claims are intended to define the scope of the invention and are therefore to cover all module forms, equivalents, or alternatives falling within the scope of the claims.

Claims

1. An aircraft simulation system, comprising:

a simulation cabin for simulating the cabin and enabling a trainee to perform a simulation operation thereon;

a teaching terminal on which a instructor operates to issue setting training contents;

the simulation server side is used for providing models of various parts of the aircraft;

the serial bus is connected with the teaching terminal and the simulation server and is connected with the simulation cabin through an interface manager; the serial bus is used for carrying out data interaction among the teaching terminal, the simulation server and the simulation cabin;

The simulation server side transmits simulation video signals formed by simulation to the simulation cabin through the interface manager, and transmits simulation audio signals formed by simulation to the audio equipment, wherein the audio equipment and the simulation cabin are matched for use.

2. An aircraft simulation system according to claim 1, wherein the simulation pod is communicatively connected to the interface manager via video signals, ethernet signals and hard-wired signals.

3. An aircraft simulation system according to claim 2, wherein the serial bus is a 1394 bus.

4. An aircraft simulation system according to claim 1, wherein the simulation cabin is deployed with a simulation cabin subsystem, the interface manager is deployed with an interface management subsystem, the simulation server is deployed with a software integration and environment operation subsystem, a sound simulation subsystem and an aircraft simulation subsystem, and the teaching terminal is deployed with a teaching management subsystem;

the system comprises a software integration and environment operation subsystem, a control interface management subsystem and an aircraft simulation subsystem, wherein the software integration and environment operation subsystem is used for scheduling each subsystem, controlling data interaction among each subsystem and controlling communication between the interface management subsystem and the aircraft simulation subsystem;

The simulation cabin subsystem is used for supporting hardware of a simulation cabin, converting operation of a student into a hard wire signal or an Ethernet signal, transmitting the hard wire signal or the Ethernet signal to the interface management subsystem, and receiving a video signal transmitted by the interface management subsystem for image display;

the aircraft simulation subsystem is used for running at least one component simulation model of an aircraft;

the sound simulation subsystem is used for simulating at least one sound in flight;

the teaching management and control subsystem is used for setting training contents;

the interface management subsystem is used for carrying out data conversion transmission.

5. The aircraft simulation system of claim 4, wherein the teaching management subsystem is configured to set training content, and comprises:

the teaching management and control subsystem is used for setting initial parameters of at least one component simulation model of the aircraft.

6. An aircraft simulation system according to claim 4, wherein the aircraft simulation subsystem is adapted to run at least one component simulation model of an aircraft, comprising:

and receiving control signals of the simulation cabin subsystem and model initial parameters of the teaching management and control subsystem, running corresponding set simulation models, and outputting data to other subsystems, wherein the control signals are generated by a student through controlling the simulation cabin.

7. An aircraft simulation system according to claim 6, wherein the aircraft simulation subsystem comprises integrated processing software and a DDS soft bus; and the comprehensive processing software performs data interaction with the component simulation model, the algorithm model and the flight dynamics model through the DDS soft bus.

8. The aircraft simulation system of claim 7, wherein the component simulation model is coupled to the DDS soft bus via an AMESim interface and a Simulink interface, the algorithm model is coupled to the DDS soft bus via a C/c++ interface, and the flight dynamics model is coupled to the DDS soft bus via a FlightSim interface.

9. An aircraft simulation system according to claim 7, wherein the integrated processing software includes flight management software, central alert software and central maintenance software.

10. An aircraft simulation system according to claim 4, wherein the aircraft simulation subsystem is further configured to run an atmospheric data model for providing flight parameters based on the atmospheric data solution.

11. The aircraft simulation system according to claim 10, wherein the atmospheric data model is configured to receive corresponding parameters set by the teaching control subsystem and sensor information obtained by the aircraft simulation subsystem through calculation, and further calculate flight control parameters, and the flight control parameters are further calculated by the aircraft simulation subsystem.

12. The aircraft simulation system of claim 4, wherein the simulation cockpit subsystem includes a top control panel, a front control panel, a center console panel, a left console, a right console, and a steering mechanism within the cockpit, the steering mechanism including a steering column, a steering wheel, a foot pedal, and a throttle lever.

13. An aircraft simulation system according to claim 12, wherein the interface management subsystem is adapted to perform signal acquisition, excitation and data transfer for the top control panel, front control panel, center console panel, left console and right console of the cockpit in the simulation system; the interface management subsystem is also used for conditioning, adapting and transmitting the electric signals of the operating mechanism in the analog cabin subsystem.

14. The aircraft simulation system of claim 12, wherein the component simulation model comprises one or more of a hydraulic system model, a climate 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; the control models include a landing gear control system model and a door control system model.

15. The aircraft simulation system of claim 12, wherein the top control panel comprises one or more of the following control panels:

the emergency positioning control panel, the cabin lighting control panel, the avionics starting control panel, the flight control system control panel, the hydraulic system control panel, the backup parking control panel, the power supply system control panel, the engine starting control panel, the fuel system control panel, the external lighting control panel, the windshield wiper control switch, the landing lighting control panel, the fireproof system control panel, the cabin sound monitoring control panel, the electromechanical management system control panel, the lifesaving system control panel, the oxygen system control panel, the ice control system control panel, the air source system control panel, the air conditioning system control panel and the pressure regulating system control panel.

16. The aircraft simulation system of claim 12, wherein the front control panel comprises one or more of:

left alarm lamp, right alarm lamp, left display control panel, right display control panel, automatic flight control panel, approach alarm lamp, undercarriage control handle, undercarriage lamp and automatic brake select plate.

17. An aircraft simulation system according to claim 12, wherein the central console comprises one or more of the following:

The system comprises a shutdown emergency brake, a horizontal stabilizer position indicator, a multifunctional display, a horizontal stabilizer balancing control handle, a speed reducing plate handle, a horizontal stabilizer balancing cut-off switch, a flap handle, a left track ball, a right track ball, a left multifunctional keyboard, a right multifunctional keyboard, a normal parking switch, a flap slat override control board, a radio tuning unit, a fire extinguishing control board, an accelerator control board, an audio control board, a balancing control board, a selection conversion board, a cabin door control board, a cabin air drop control board and an electronic warfare control board.

18. The aircraft simulation system of claim 12, wherein the left console comprises a front steering oxygen mask control panel, a left dimming control panel, a front steering handle, a left head up control panel, a key control box, a time key control box, and a headset phone jack assembly.

19. The aircraft simulation system of claim 12, wherein the right console includes a co-pilot oxygen mask control, a right dimmer control board, a co-pilot front wheel steering handle, a right head up control board, an oxygen shut-off valve switch, a mission add/drop card.

20. An aircraft simulation system according to any of claims 12-19, wherein the control panels, panels and consoles in the simulation cockpit subsystem are implemented by means of physical simulation elements and/or virtual simulation interfaces.

21. An aircraft simulation system according to claim 14, wherein the aircraft simulation subsystem further comprises:

the electric system model is used for carrying out data interaction 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; the electrical system model is also used for carrying out 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 carrying out state interconnection with the electrical control panel.

22. An aircraft simulation system according to claim 21, wherein the aircraft simulation subsystem further comprises:

the fuel system model is used for carrying out data interaction with the engine model, the auxiliary power device model, the electromechanical management system model, the power supply system model, the teaching management and control subsystem and the fuel control panel.

23. An aircraft simulation system according to claim 22, wherein the aircraft simulation subsystem further comprises:

and the landing gear retraction system model is used for carrying out data interaction with the landing gear control handle, the hydraulic system model, the power supply system model and the electromechanical management system.

24. An aircraft simulation system according to claim 12, wherein the interface manager comprises:

an image generating computer connected with the front control board and the central console through DVI signals;

and the interface computer is used for being connected with the front control panel, the central console, the top control panel, the left console and the right console through the network switch.

25. The aircraft simulation system according to claim 24, wherein the interface manager further comprises:

and the power supply control box is respectively connected with the front control board, the central control board, the top control board, the left control board and the right control board and is used for carrying out direct current power supply.

26. An aircraft simulation system according to claim 4, wherein the sound simulation subsystem is for simulating at least one sound in flight, comprising: superposition of one or more sounds of ambient noise, on-board equipment operating noise, alert tones, alarm voices, and audio signals.

27. The aircraft simulation system of claim 26, wherein the warning sounds comprise voice warning sounds, the on-board device operating noise comprises landing gear retraction sounds, flap retraction sounds, aircraft engine sounds, sounds during tire dive tracks, and the environmental noise comprises external weather environmental sounds and air conditioning noise.

28. An aircraft simulation system according to claim 26, wherein the sound simulation subsystem is connected to the aircraft simulation subsystem for:

acquiring simulation data of the aircraft simulation subsystem;

analyzing an aircraft state signal and a first excitation signal from the simulation data;

and selecting corresponding sounds according to the aircraft state signals and the first excitation signals to be overlapped so as to simulate the sounds perceived by the cockpit in the aircraft flight process.

29. The aircraft simulation system of claim 28, wherein the sound simulation subsystem is further coupled to the teaching management subsystem for:

acquiring a control signal sent by the teaching management and control subsystem;

and controlling the running state of the sound simulation subsystem according to the control signal of the teaching control subsystem.

30. An aircraft simulation system according to claim 29, wherein the sound simulation subsystem is further configured to:

acquiring a second excitation signal sent by the teaching management and control subsystem;

and selecting corresponding sound according to the second excitation signal to be overlapped with the sound perceived by the cockpit in the flight process of the aircraft so as to realize burst training in the teaching process.

31. An aircraft simulation system according to claim 29, wherein the first excitation signals comprise alert excitation signals and navigational excitation signals, and the aircraft status signals comprise aircraft flight status signals, aircraft engine status signals and flap and landing gear status signals.

32. An aircraft simulation system according to claim 30, wherein the control signals include volume adjustment, sound channel configuration, sound effect selection, start-up, freeze-up and reset, and the second excitation signals include a lightning excitation signal, a rain excitation signal, a snow excitation signal and a wind excitation signal.

33. A fault simulation training method for an aircraft cabin simulation system according to any one of claims 1-32, comprising:

receiving training content set by an instructor, wherein the training content comprises training subjects and training environments;

loading aircraft parameters under corresponding configurations according to the training subjects and the training environment so as to simulate the aircraft running state corresponding to the training subjects;

acquiring selection of possible faults of each subsystem of the aircraft;

setting faults of all subsystems of the aircraft according to the selection completion so as to simulate the fault running state of the aircraft;

Receiving training operations of a learner aiming at the training content and the fault running state of the airplane;

and driving the model to complete logic execution according to the training operation, and outputting an execution result to complete fault simulation training.

34. The method of claim 33, wherein the fault includes a jelly effect in a video image display, the selection of the possible faults of each subsystem of the aircraft includes a degree of jelly effect, and the setting of the faults of each subsystem of the aircraft according to the selection to simulate the fault operation state of the aircraft includes:

obtaining the strength degree of jelly effect selected by an instructor;

simulating the jelly effect in the video image according to the strength degree of the jelly effect selected by the instructor to obtain a simulation result, wherein the simulation result comprises vibration conditions generated by the influence of external environment when the aircraft is in flight;

and outputting the simulation result to a simulation cabin for display.

35. The method of claim 34, wherein simulating the jelly effect in the video image according to the extent of jelly effect selected by the instructor to obtain the simulation result comprises:

Acquiring a standard image frame;

calculating all vector differences between motion vectors of various areas 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 the pixel points of each class area, and carrying out weighted summation on the vector difference and the corresponding weight to obtain the vector difference of the whole image;

and adjusting the size of the vector difference corresponding to the image according to the strength degree of the jelly effect selected by the instructor so as to adjust the display effect of the jelly effect in the image.

36. The method of fault simulation training of an aircraft cabin simulation system according to claim 35, wherein the acquiring standard image frames comprises:

and extracting a corresponding standard image frame from the current image with the jelly effect by using an optical flow method or jelly effect restoration software.