Intelligent simulation system for flight command

Abstract

The invention discloses a flight command intelligent simulation system, which belongs to the field of flight command simulators and comprises a command set, a main control computer, a flight plan computer and a control tower visual computer which are all in signal connection with a network switch. The flight plan computer is mainly composed of a flight plan management system and a special situation command system. The command set is electrically connected with the flight plan management system and the special situation command system. According to the speech recognition system, the recognition instruction is split for command, the speech recognition precision is guaranteed, meanwhile, recognition vocabulary input is greatly reduced, the recognition range is single Chinese characters, phrases, phrases and numbers, the word library capacity is 2000, the recognition precision is that the phrases of the phrases are larger than 98%, the input speed is 30-80 characters / m in, and the input speed is 30-80 characters / m in. The anti-noise capability is that the background noise is less than 75dB, the system can work normally, the recognition adaptive capability is more than 200 persons, and the multi-phrase resolution interval is more than 1s.

Description

Technical Field

[0001] The present invention belongs to the technical field of flight command simulation systems, and particularly relates to an intelligent flight command simulation system. Background Art

[0002] A flight command training simulator is a highly realistic training system developed for training flight commanders. It involves multiple technical fields such as system integration, speech recognition, computer force generation, virtual reality, and network communication, and is implemented by using modern control theory and similarity principles, combined with aviation theory knowledge and actual flight data.

[0003] The existing flight command simulators have the following problems:

[0004] 1. Most of the existing flight command simulators adopt the method of manually outputting commands, and the flight command simulators using voice input have poor recognition accuracy, require a large number of word libraries to be entered, and have a slow response time.

[0005] 2. In the existing simulated flight systems, complex formulas are used to calculate data collection, and some parameters need to be obtained from flight data, which easily misses the opportunity for timely correction.

[0006] 3. In the existing simulated flight systems, the sound effects are poor, and the commander cannot hear the sound, so more information cannot be judged from the environment. Summary of the Invention

[0007] The purpose of the present invention is to address the deficiencies of the prior art and solve the above-mentioned technical problems through the designed flight command simulation system.

[0008] To achieve the above object, the present invention provides the following technical solutions:

[0009] An intelligent simulation system for flight command, including a command console, a main control computer, a flight plan computer, and a tower visual scene computer. The flight plan computer, the main control computer, and the tower visual scene computer are all connected to a network switch for signal transmission. The flight plan computer mainly consists of a flight plan management system and a special situation command system. The command console is electrically connected to the flight plan management system and the special situation command system respectively. The main control computer mainly consists of a voice recognition system, a voice synthesis system, a training evaluation system, an intelligent flight system, an interface system, and an airspace radar system. The command console is connected to the voice recognition system through voice transmission. The voice recognition system is connected to the intelligent flight system through signal transmission. The intelligent flight system is connected to the airspace radar system and the voice synthesis system through signal transmission respectively. The airspace radar system transmits the received information to the command console. The training evaluation system transmits the processed information to the command console. The main control computer is connected to the tower visual scene computer through the interface system. The flight plan management system and the special situation command system send instructions to the intelligent flight system. The tower visual scene computer mainly consists of an audio simulation system and a visual imaging system. The airspace radar system transmits the processed information to the audio simulation system and the visual imaging system respectively.

[0010] The command console includes a simulated tower, a command microphone, a control switch, and an indicator light. It is connected to the voice recognition system through the command microphone. The control switch is used to control the flight plan management system and the special situation command system. The indicator light is used to display the flight status.

[0011] The voice recognition system adopts the command recognition mode in Microsoft speech recognition. Developers write their own internal dictionaries and use XML files as a data storage method, defining the tags and matching vocabulary that the SDK needs to determine in a preset format.

[0012] The intelligent flight system is for the simulation of the centroid motion of the aircraft, the simulation of the change of attitude angles, a database system, and the construction of a random error function. The centroid motion of the aircraft includes the magnitude and direction of the velocity vector. The pitch angle and yaw angle of the aircraft are determined by the direction of the velocity vector of the aircraft, so as to simulate the change of attitude angles. The database system includes the dynamic characteristics of the aircraft, the flight route, and the spatial characteristic coordinate parameters of the airspace.

[0013] The direction of the flight speed is achieved by the following method. The aircraft flies from point A to point B. V1 is the initial velocity direction of the aircraft, V2 is the velocity vector direction of the aircraft after a calculation interval, and V3 is the final velocity vector direction of the aircraft. The calculation formula of V3 is as follows:

[0014] V x3 =|V1|·(x B -x A ) / |B A|;

[0015] V y3 = |V1|·(y B - y A ) / |B A |;

[0016] V z3 = |V1|·(z B - z A ) / |B A |;

[0017] Wherein V x3 , V y3 and V z3 are the three components of V3; the angle θ 13 between V3 and V1 is calculated by the following formula:

[0018] θ 13 = arccos(V1·V3 / (|V1|·|V3|))·57.3;

[0019] The pilot will adjust the speed at which the aircraft approaches the target vector according to the angle θ 13 between the current speed vector direction and the target speed vector direction of the aircraft. The larger the angle, the faster the deflection of the aircraft. During actual simulation, the deflection magnitude of the speed vector of the aircraft in a calculation interval is determined according to the dynamic characteristics of the aircraft type and the magnitude of the current angle. The specific calculation method is as follows: first, determine ΔV corresponding to a calculation time interval according to the magnitude of θ 13 , and then calculate the direction of V2, which is the direction of the vector V1 + ΔV. The magnitude of the modulus of V2 is equal to that of V1;

[0020] V x2 = (V x1 + ΔV x )·|V1| / |V1 + ΔV|;

[0021] V y2 = (V y1 + ΔV y )·|V1| / |V1 + ΔV|;

[0022] V z2 = (V z1 + ΔV z )·|V1| / |V1 + ΔV|;

[0023] Through cumulative calculation, the speed vectors V1 and V3 are continuously approximated, and the aircraft flies towards point B.

[0024] The sound simulation system has the characteristics of omnidirectional three-dimensional positioning, three-dimensional real-time tracking, and Doppler effect. The three-dimensional positioning characteristic refers to the ability to locate the actual sound signal to a specific virtual sound source in a three-dimensional virtual space. The three-dimensional real-time tracking characteristic refers to the ability to track the position change or image change of the virtual sound source in real time in the three-dimensional virtual space. When there is relative motion between the user and the sound source, the frequency of the sound emitted by the sound source will change, thus generating the Doppler effect.

[0025] The flight plan management system includes an organization description module for rules and data, an inference process, meta-rules, and an inference process design.

[0026] The training evaluation system includes a data center for pilot simulation training units, cockpit monitoring, three-dimensional situation, virtual cockpit, and flight parameter interpretation system. By reading the flight parameter data of each flight, and based on the evaluation criteria of each subject, it analyzes and gives the flight reports of each flight and each stage. The reports display the flight quality in different colors, reproduce the two-dimensional curves and three-dimensional situations of the flight parameter data of any flight and any time period, and provide a basis for flight instructors' evaluation.

[0027] The visual imaging system takes the data input in the trainee flight simulator as external input data, and then generates a corresponding output virtual simulation system. It mainly consists of an external input receiving module, a scene graph organization module, a camera control module, a meteorological environment simulation module, and a rendering engine. The external input receiving module sends the meteorological environment information parameters to the meteorological environment simulation module. The meteorological environment simulation module transmits the processed meteorological environment data for rendering to the rendering engine. The external input receiving module transmits the aircraft position to the scene graph organization module. The scene graph organization module transmits the landscape data of the current spatial position to the rendering engine. The external input receiving module sends the aircraft position and orientation to the camera control module. After processing, the camera control module transmits the spatial coordinates, camera orientation, and camera forward direction to the rendering engine. The rendering engine transmits the rendered data that has been cropped and optimized through organization to the screen display for output.

[0028] Compared with the prior art, the beneficial effects of the present invention are:

[0029] 1. The voice recognition system in the present invention commands by splitting the recognition instructions, which not only ensures the voice recognition accuracy but also greatly reduces the recognition vocabulary input. Its recognition range includes Chinese single characters, phrases, expressions, and numbers. The vocabulary capacity is 2,000 entries. The recognition accuracy for phrases and expressions is greater than 98%. The input speed is 30 - 80 words / min. The anti-noise ability is that it can work normally when the background noise is less than 75 dB. The recognition adaptability is greater than 200 people, and the multi-phrase discrimination interval is greater than 1 s.

[0030] 2. In the intelligent flight system of the present invention, real data is directly adopted to establish a pilot knowledge base system, a dynamic parameter library for multiple aircraft models, a flight mission and route feature database, and the kinematic equation of the aircraft is simplified.

[0031] 3. The audio simulation system in the command training system of the present invention can run in parallel with vision simultaneously, enabling the commander to obtain more information from an environment with both vision and hearing, thus enhancing the immersion and interactivity.

[0032] 4. The flight plan management system in the present invention can reasonably arrange the flight plan for the flight day, which is beneficial for accelerating the training progress, improving the training quality, shortening the on-site time, and also beneficial for ensuring flight safety. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following will briefly introduce the drawings required for the description of the embodiments. Obviously, the following described drawings are only some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0034] Figure 1 is the system structure block diagram of the present invention;

[0035] Figure 2 is the voice recognition principle diagram in the voice recognition system of the present invention;

[0036] Figure 3 is the speed vector change diagram in the intelligent flight system of the present invention;

[0037] Figure 4 is the working schematic diagram of the data center of the training evaluation system of the present invention.

[0038] In the figure: 1. Command console; 21. Flight plan management system; 22. Special situation command system; 31. Voice recognition system; 32. Voice synthesis system; 33. Training evaluation system; 34. Intelligent flight system; 35. Interface system; 36. Airspace radar system; 41. Audio simulation system; 42. Visual imaging system; 5. Network switch. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0039] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, rather than all embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts belong to the scope of protection of the present invention.

[0040] Please refer toFigures 1 to 4 , the present invention provides the following technical solutions: An intelligent flight command simulation system includes a command console 1, a main control computer, a flight plan computer, and a tower visual scene computer. The flight plan computer, the main control computer, and the tower visual scene computer are all signal-connected to a network switch 5. The flight plan computer mainly consists of a flight plan management system 21 and a special situation command system 22. The command console 1 is electrically connected to the flight plan management system 21 and the special situation command system 22 respectively. The main control computer mainly consists of a voice recognition system 31, a voice synthesis system 32, a training evaluation system 33, an intelligent flight system 34, an interface system 35, and an airspace radar system 36. The command console 1 is connected to the voice recognition system 31 through voice transmission. The voice recognition system 31 and the intelligent flight system 34 are signal-connected. The intelligent flight system 34 is signal-connected to the airspace radar system 36 and the voice synthesis system 32 respectively. The airspace radar system 36 transmits the received information to the command console 1. The information processed by the training evaluation system 33 is transmitted to the command console 1. The main control computer is connected to the tower visual scene computer through the interface system 35. The flight plan management system 21 and the special situation command system 22 send instructions to the intelligent flight system 34. The tower visual scene computer mainly consists of an audio simulation system 41 and a visual scene imaging system 42. The airspace radar system 36 transmits the processed information to the audio simulation system 41 and the visual scene imaging system 42 respectively.

[0041] Further, the command console 1 consists of an analog tower, a command microphone, a control switch, an indicator light, etc. It is connected to the voice recognition system 31 through the command microphone. The control switch is used to control the flight plan management system 21 and the special situation command system 22. The indicator light is used to display the flight status.

[0042] In this embodiment, the command console system includes an analog tower, a command microphone, a control switch, an indicator light, etc. The visual scene system consists of a visual scene generation system and a visual scene display system. The computer communication and interface system consists of network communication devices and various interface boards. The audio simulation system consists of a digital audio computer and a sound card.

[0043] Further, as Figure 2 shown, the voice recognition system 31 adopts the command recognition mode in Microsoft speech recognition. The developer writes an internal dictionary by himself, uses an XML file as a data storage method, and defines some tags that the SDK needs to determine and the matching vocabulary in a preset format.

[0044] In this embodiment, the speech recognition system 31 adopts split recognition instructions. The general format of the command is: pilot code + instruction (for example: "Two-hole takeoff"), pilot code + airspace number + instruction (for example: "Two-hole Five takeoff"), pilot code + instruction + airspace number (for example: "Two-hole can exit turning number"), etc. The instruction is split into three parts: pilot code, airspace number, and instruction. A complete commander's command consists of two or three of these parts. At the same time, the instruction combination method can be set in the XML file to restore it to the general instruction. Since different flight subjects use different instructions, the speech recognition system 31 generates the required word library in real time according to the training subject. Suppose there are a total of 2,000 instructions, and only 200 instructions are used in the takeoff and landing route subject. Then, only these 200 instructions need to be added to the word library to further reduce the number of vocabulary. The pilot code is usually from 1 to 999. Since different schedules may involve different pilot codes and the schedule can be modified according to needs, any one of the 999 codes may appear in the schedule. However, generally, there are less than 40 different codes in a schedule. If all 999 codes are added to the word library, it will obviously increase the recognition volume and reduce the recognition rate. The pilot codes involved in the corresponding schedule can be extracted and added to the word library in real time to improve the recognition rate. The speech recognition system 31 uses Gaussian component level to limit the observation probability of the noise-sensitive feature subvector to directly eliminate the impact of impulse noise on speech recognition. In addition, turning off the automatic adaptation function of Microsoft Speech and using a directional microphone will further improve the recognition rate. At the same time, the speech recognition system 31 may not be able to recognize some instructions of someone. Therefore, redundancy design is required. These instructions can be input through other means (keyboard input) to avoid stagnation and ensure the smooth progress of training.

[0045] Furthermore, as Figure 3 shown, the intelligent flight system 34 mainly simulates the centroid motion of the aircraft, the change of attitude angle, the database system, and constructs a random error function. The centroid motion of the aircraft includes the magnitude and direction of the velocity vector. The pitch angle and yaw angle of the aircraft are determined by the direction of the velocity vector of the aircraft, so as to simulate the change of attitude angle. The database system contains various parameters of the aircraft: the dynamic characteristics of the aircraft, the spatial characteristic coordinates of the route and airspace.

[0046] In this embodiment, the centroid motion of the aircraft includes the magnitude and direction of the velocity vector. By separating the magnitude and direction of the velocity vector for consideration, the magnitude of the velocity is calculated according to specific flight phases. For example, during the takeoff phase, the flight speed should gradually increase, and its acceleration at different stages is determined according to the dynamic characteristics of the aircraft. During cruise flight, the speed of the aircraft remains basically unchanged. The direction of the flight speed is achieved by the following method. The aircraft flies from point A to point B. V1 is the initial velocity direction of the aircraft, V2 is the velocity vector direction after a calculation interval of the aircraft, and V3 is the final direction of the aircraft velocity vector. The calculation formula for V3 is as follows:

[0047] V x3 = |V1| · (x B - x A ) / |BA|;

[0048] V y3 = |V1| · (y B - y A ) / |BA|;

[0049] V z3 = |V1| · (z B - z A ) / |BA|;

[0050] In the formula, V x3 , V y3 and V z3 are the three components of V3. The angle θ 13 between V3 and V1 is calculated by the following formula:

[0051] θ 13 = arccos(V1 · V3 / (|V1| · |V3|)) · 57.3;

[0052] Generally, the pilot will adjust the speed at which the aircraft approaches the target vector according to the angle θ 13 between the current velocity vector direction and the target velocity vector direction of the aircraft. The larger the angle, the faster the aircraft deflects. During actual simulation, the deflection magnitude of the velocity vector of the aircraft in a calculation interval can be determined according to the dynamic characteristics of the aircraft type and the magnitude of the current angle. The specific calculation method is as follows: First, determine ΔV corresponding to a calculation time interval according to the magnitude of θ 13 , and then calculate the direction of V2, which is the direction of the vector V1 + ΔV. The magnitude of the modulus of V2 is equal to that of V1.

[0053] V x2 = (V x1 + ΔV x ) · |V1| / |V1 + ΔV|;

[0054] V y2 = (Vy1 +ΔV y )·|V1| / |V1 + ΔV|;

[0055] V z2 =(V z1 +ΔV z )·|V1| / |V1 + ΔV|;

[0056] In this way, through the cumulative calculation of time, the velocity vectors V1 and V3 can be continuously approximated, enabling the aircraft to fly towards point B. To make the attitude change of the aircraft more reasonable, a more reasonable approach is to first determine the target attitude angles, namely the pitch angle θt, yaw angle ψt, and bank angle γt according to the requirements for the attitude angles. Given the deflection angular rates ωθ, ωψ, and ωγ of the aircraft according to its dynamic characteristics. In this way, using the current attitude angle of the aircraft, approach the target attitude angle at the given angular rate, and exit the loop when it is equal to the target attitude angle. The database system in the intelligent flight system 34 contains various parameters of the aircraft: the dynamic characteristics of the aircraft, the spatial characteristic coordinates of the flight route and airspace. When the system runs, the records in the database are guided into the memory to generate two types of libraries, permanent and temporary. The data in the temporary library is one of the data sources for reasoning and can be updated in real time according to the flight situation and command instructions to enable the target aircraft to change its flight state. To more realistically simulate the training scenario, a random error function is added to the trajectory formula. The commander assists the pilot to land safely based on the speed, altitude, descent speed, flight attitude, etc. of the aircraft. During the landing phase, the landing point of the aircraft conforms more to the normal distribution. The NormalDis function in the boost / random.hpp library is called in VC to obtain the normal random number. Since the inverse function of the normal distribution does not have an elementary primitive function and the boost library call is rather cumbersome, uniform random numbers can also be used instead.

[0057] Furthermore, the audio simulation system 41 includes omnidirectional three-dimensional positioning characteristics, three-dimensional real-time tracking characteristics, and Doppler effect characteristics. The three-dimensional positioning characteristic refers to the ability to locate the actual sound signal to a specific virtual sound source in the three-dimensional virtual space. The three-dimensional real-time tracking characteristic refers to the ability to real-time track the position change or image change of the virtual sound source in the three-dimensional virtual space. When there is relative motion between the user and the sound source, the frequency of the sound emitted by the sound source will change, thus generating the Doppler effect.

[0058] In this embodiment, the sound simulation system 41 is implemented using DirectSound. All buffers contain sound sample data in pulse code modulation (PCM) format. When playing the sound buffer object, DirectSound takes data from each buffer and then mixes it in the main buffer. When playing the new waveform data, you can hear the effect of the original two sounds playing together. When mixing, it will perform all necessary format conversions. After mixing in the main buffer, the sound is sent to the output device. When the hardware buffer and hardware mixing device are idle, DirectSound automatically sends as many sound objects as possible to the hardware memory. The sound objects remaining in the host system memory are mixed by software by DirectScund and are mixed with the sound objects in the hardware buffer in a streaming manner. The sound is sent to the hardware mixer, DirectSound automatically creates the main sound buffer, and the secondary sound buffer is created by the application. In DirectSound, whether it is the sound source position and sound speed, or the direction of the sound source and the direction of the listener in 3D space, they are all represented by the following scale system: the X-axis direction is from left to right, the Y-axis direction is from bottom to top, and the Z-axis direction is from far to near. At the same time, 3D sound effects are applied to independent DirectSound buffers. Because different sound sources can be directed to different audio tracks, and each audio track has an independent buffer, different 3D sound effects can be set for different sound sources. DirectSound provides an efficient 3D sound interface. 3D parameters are set through this interface, and DirectSound automatically completes the processing of the 3D effects of the sound.

[0059] Furthermore, the flight plan management system 21 includes the organization and description of rules and data, reasoning process and meta-rules, and reasoning process design.

[0060] In this embodiment, the database in the flight plan management system 21 includes pilot status information, airport data, aircraft data and real-time conditions on the flight day. Formulating a flight plan on the flight day involves a wide range of aspects and is inevitably affected by various factors and constrained by many conditions. It cannot be done arbitrarily or reluctantly.

[0061] Furthermore, if Figure 4 As shown, the training evaluation system 33 is mainly composed of a pilot simulation training unit data center, cockpit monitoring, three-dimensional situation, virtual cockpit and flight parameter interpretation systems. By reading the flight parameter data of each sortie and analyzing and giving flight reports for each sortie and each stage according to the assessment standards of each subject, the report displays the flight quality in different colors, and can reproduce the flight parameter data of any sortie and any time period in 2D curves and 3D situation, providing a basis for flight instructors' comments.

[0062] In this embodiment, the data center collects the real-time monitoring data, flight parameter data, and engine parameters of each simulator, then processes and distributes them, and is responsible for solving the problem of network parallel transmission in the case of a large amount of data. The cockpit monitoring system is used to monitor the actual situation of the cockpits of each simulator and can also play back video signals to provide a basis for evaluation and review. The three-dimensional situation system synchronously displays the flight state of the aircraft, records the flight situation at the same time, and provides a playback function at multiple speeds, which is convenient for students to observe and instructors to review training. The virtual cockpit system enables students to intuitively and real-time observe the operations of the pilots and can also reproduce the manipulation actions of the flight crew after training. The flight parameter interpretation system displays information such as the flight parameters, engine parameters, and various control quantities of the simulated flight through various forms of charts and curves, and can realize the training review of typical courses by flight instructors, providing a basis for instructors to evaluate the performance of simulated teaching.

[0063] Further, the visual imaging system 42 takes the data input in the student flight simulator as external input data, and then generates a corresponding output virtual simulation system therefrom. It mainly consists of an external input receiving module, a scene graph organizing module, a camera control module, a meteorological environment simulation module, and a rendering engine. The external input receiving module sends the relevant parameters of the meteorological environment information to the meteorological environment simulation module. The meteorological environment simulation module transmits the processed meteorological environment data for rendering to the rendering engine. The external input receiving module transmits the aircraft position to the scene graph organizing module. The scene graph organizing module transmits the landscape data of the current spatial position to the rendering engine. The external input receiving module sends the aircraft position and orientation to the camera control module. After processing, the camera control module transmits the spatial coordinates, camera orientation, and camera forward direction to the rendering engine. The rendering engine transmits the rendered data that has been cropped and optimized through organization to the screen display for output.

[0064] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by terms such as "front and back", "left and right", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or component referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention.

[0065] Certainly, in this technical solution, those skilled in the art should understand that the term "one" should be understood as "at least one" or "one or more". That is, in one embodiment, the number of one element can be one, while in other embodiments, the number of this element can be multiple. The term "one" should not be construed as a limitation on the quantity.

[0066] As described above, it is only the preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the art in the technical field of the present invention under the technical hint of the present invention should be covered within the protection scope of the present invention. Therefore, the protection scope of the present invention should be subject to the protection scope of the claims.

Claims

1. A flight command intelligent simulation system, comprising a control desk (1), a main control computer, a flight plan computer and a tower visual computer, characterized in that: The flight plan computer, the main control computer and the tower visual computer are all connected to the network switch (5) by signal. The flight plan computer is mainly composed of a flight plan management system (21) and a special situation command system (22). The control desk (1) is electrically connected to the flight plan management system (21) and the special situation command system (22). The main control computer is mainly composed of a speech recognition system (31), a speech synthesis system (32), a training evaluation system (33), an intelligent flight system (34), an interface system (35) and an airspace radar system (36). The control desk (1) and the speech recognition system (31) are connected by voice transmission, and the speech recognition system (31) and the intelligent flight system (34) are connected by signals. The intelligent flight system (34) is connected to the airspace radar system (36) and the speech synthesis system (32) respectively through signals. The airspace radar system (36) transmits the received information to the command console (1). The training evaluation system (33) transmits the processed information to the command console (1). The main control computer is connected to the tower visual computer through the interface system (35). The flight plan management system (21) and the special situation command system (22) send designated information to the intelligent flight system (34). The tower visual computer is mainly composed of an audio simulation system (41) and a visual imaging system (42). The airspace radar system (36) transmits the processed information to the audio simulation system (41) and the visual imaging system (42).

2. The flight command intelligent simulation system according to claim 1, characterized in that: The control desk (1) comprises a simulated control tower, a command microphone, a control switch and an indicator light, and is connected to a voice recognition system (31) via the command microphone. The control switch is used to control the command flight plan management system (21) and the special situation command system (22), and the indicator light is used to display the flight status.

3. The flight command intelligent simulation system according to claim 1, characterized in that: The speech recognition system (31) adopts the command recognition mode in Microsoft speech recognition. Developers compile their own internal dictionaries, use XML files as a data storage method, and define the tags and matching words that the SDK needs to determine according to a preset format.

4. The flight command intelligent simulation system according to claim 1, characterized in that: The intelligent flight system (34) is a simulation of the movement of the center of mass of the aircraft, a simulation of the change of the attitude angle, a database system and a construction of a random error function. The movement of the center of mass of the aircraft includes the magnitude and direction of the velocity vector. The pitch angle and yaw angle of the aircraft are determined by the direction of the velocity vector of the aircraft, thereby simulating the change of the attitude angle. The database system includes the dynamic characteristics of the aircraft, the route and the spatial characteristic coordinate parameters of the airspace; The direction of the flight speed is achieved by the following method. The aircraft flies from point A to point B. V1 is the initial speed direction of the aircraft, V2 is the speed vector direction of the aircraft after one calculation interval, and V3 is the final direction of the aircraft speed vector. The calculation formula of V3 is as follows: V x3 =|V1|·(x B -x A ) / |B A |; V y3 =|V1|·(y B -y A ) / |BA|; In z3 =|V1|·(with B -with A ) / |BA|; Where V x3 、V y3 and V z3 are the three components of V3; the angle θ between V3 and V1 13 Calculated by the following formula: θ 13 =arccos(V1·V3 / (|V1|·|V3|))·57.3; The pilot will adjust the angle θ between the current velocity vector direction of the aircraft and the target velocity vector direction. 13 To adjust the speed of the aircraft approaching the target vector, the larger the angle, the faster the aircraft deflects. In actual simulation, the deflection size of the aircraft's velocity vector in a calculation interval is determined according to the dynamic characteristics of the aircraft model and the size of the current angle. The specific calculation method is to first calculate the deflection size of the aircraft's velocity vector according to θ 13 The size of determines a ΔV corresponding to the calculation time interval, and then calculates the direction of V2, which is the direction of vector V1+ΔV. The magnitude of V2 is equal to that of V1. V x2 =(V x1 +ΔV x )·|V1| / |V1+ΔV|; V y2 =(V y1 +ΔV y )·|V1| / |V1+ΔV|; V z2 =(V z1 +ΔV z )·|V1| / |V1+ΔV|; After cumulative calculation, the velocity vectors V1 and V3 are continuously approached, making the aircraft fly to point B.

5. The flight command intelligent simulation system according to claim 1, characterized in that: The sound simulation system (41) has omnidirectional three-dimensional positioning characteristics, three-dimensional real-time tracking characteristics and Doppler effect characteristics. The three-dimensional positioning characteristic refers to the ability to locate the actual sound signal to a specific virtual sound source in the three-dimensional virtual space. The three-dimensional real-time tracking characteristic refers to the ability to track the position change or image change of the virtual sound source in real time in the three-dimensional virtual space. When a relative motion occurs between the user and the sound source, the frequency of the sound emitted by the sound source will change, thereby generating a Doppler effect.

6. The flight command intelligent simulation system according to claim 1, characterized in that: The flight plan management system (21) comprises a rule and data organization description module, a reasoning process and meta-rules, and a reasoning process design.

7. The flight command intelligent simulation system according to claim 1, characterized in that: The training evaluation system (33) includes a pilot simulation training unit data center, cockpit monitoring, three-dimensional situation, virtual cockpit and flight parameter interpretation system. By reading the flight parameter data of each sortie, according to the evaluation standards of each subject, a flight report of each sortie and each stage is analyzed and given. The report displays the flight quality in different colors, and reproduces the flight parameter data of any sortie and any time period in a two-dimensional curve and a three-dimensional situation, providing a basis for the flight instructor's comments.

8. The flight command intelligent simulation system according to claim 1, characterized in that: The visual imaging system (42) uses the data input in the student flight simulator as external input data, and then uses this data to generate a virtual simulation system with corresponding output. It mainly consists of an external input receiving module, a scene graph organization module, a camera control module, a meteorological environment simulation module and a rendering engine. The external input receiving module sends meteorological environment information parameters to the meteorological environment simulation module, and the meteorological environment simulation module transmits the processed rendering meteorological environment data to the rendering engine. The external input receiving module transmits the aircraft position to the scene graph organization module, and the scene graph organization module transmits the current spatial position scenery data to the rendering engine. The external input receiving module transmits the aircraft position and orientation to the camera control module, and the camera control module transmits the spatial coordinates, camera orientation and camera positive direction to the rendering engine after processing. The rendering engine transmits the cropped, organized and optimized rendering data to the screen for output.

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