Flight training simulation method and system capable of quickly simulating airport environment

Abstract

The present disclosure provides a flight training simulation method and system that can quickly simulate an airport environment, which relates to the field of civil aviation flight training technology. By acquiring the real-time position information of the target aircraft and the parameter information of the target simulated airport, a deviation control signal is generated, and a simulated navigation signal is generated based on the signal using a programmable signal generator. Finally, the intensity is attenuated and the frequency is synthesized through the transmitting circuit, and then transmitted through the transmitting antenna. The target aircraft receives and parses the simulated navigation signal to generate navigation information. The method avoids signal interference with other aircraft by dynamically adjusting the transmission power of the signal, and collaboratively generates accurate navigation signals through multiple programmable signal generators to provide high-precision training support. The invention can effectively simulate the airport environment, reduce training costs, and improve the safety, flexibility, and realism of flight training.

Description

Technical Field

[0001] The present disclosure relates to the field of civil aviation flight training technology, and in particular to a flight training simulation method and system that can quickly simulate an airport environment. Background Art

[0002] Airports are the primary locations for aircraft takeoff, landing, and ground operations, typically comprising runways, taxiways, aprons, control towers, navigational aids, and communication and navigation facilities. Flight training units require access to airports of varying airfield classifications and distances to complete various training exercises. However, due to the limited number of existing airports and airspace resources, flight training units struggle to obtain ideal training environments. Furthermore, due to factors such as geographical conditions and financial investment, flight training units face difficulties in site selection, high investment costs, long construction periods, and significant risks when building their own airports.

[0003] To this end, for example, Chinese patent application publication number CN118942310A discloses an avionics simulation system for aircraft flight simulation training, which relates to the field of simulation training technology. The system includes: a data acquisition module for acquiring radio station environment data at an airport, which includes communication station data and navigation station data; a communication simulation module for acquiring pilot setting data, which establishes a wireless communication connection when the setting data matches the communication station data; and a navigation simulation module for acquiring radio data and simulating the radio data into navigation signals. The navigation simulation module also determines the aircraft's radio bearing relative to the navigation station based on the navigation signal and converts the radio bearing into a corresponding distance. By simulating wireless communication and navigation, this application allows pilots to experience realistic training simulation effects, greatly improving the quality of training.

[0004] However, although the system can provide simulation of communication and navigation signals, its functions and flexibility are still subject to certain limitations, especially in terms of the accuracy and real-time performance of simulating airport environments and interference between multiple devices. Summary of the Invention

[0005] In view of the shortcomings of the existing technology, the present disclosure provides a flight training simulation method and system that can quickly simulate an airport environment.

[0006] In a first aspect, the present disclosure provides a flight training simulation method capable of rapidly simulating an airport environment, comprising:

[0007] acquiring real-time position information of a target aircraft and parameter information of a target simulated airport, and generating a deviation control signal based on the real-time position information of the target aircraft and the parameter information of the target simulated airport; wherein the parameter information includes runway length, width, elevation, navigation station location, and approach path information; and the deviation control signal is used to represent the difference between the current track of the target aircraft and the ideal track of the target simulated airport;

[0008] Based on the deviation control signal, a program-controlled signal generator is used to generate a simulated navigation signal;

[0009] Performing intensity attenuation and frequency synthesis on the analog navigation signal through a transmitting circuit, and transmitting the signal through a transmitting antenna; wherein the transmission intensity of the analog navigation signal is limited to a receiving range of the target aircraft;

[0010] The simulated navigation signal is received by the receiving antenna assembly of the target aircraft, and analyzed to generate navigation information.

[0011] As an optional implementation manner, the acquiring of the real-time position information of the target aircraft and the parameter information of the target simulated airport includes:

[0012] Receive satellite signals and analyze the real-time position information of the target aircraft through a GPS receiver or Beidou receiver installed on the target aircraft;

[0013] The parameter information of the target simulated airport is stored in an airport location database deployed in the target aircraft;

[0014] The airport location database includes: runway parameters, location information of navigation stations, geometric data of approach paths, and three-dimensional coordinate information of surrounding obstacles.

[0015] As an optional implementation manner, generating the deviation control signal includes:

[0016] Extracting ideal track data from the airport location database; wherein the ideal track data includes: navigation station location, approach path geometry data, and runway location;

[0017] comparing the real-time position information of the target aircraft with the ideal track data to generate course deviation information, azimuth deviation information, distance deviation information, and position point deviation information;

[0018] The course deviation information, the azimuth deviation information, the distance deviation information, and the positioning point deviation information are integrated to generate the deviation control signal.

[0019] As an optional implementation manner, the simulated navigation signal includes:

[0020] Dynamically adjust the modulation parameters of the output signal of the program-controlled signal generator based on the course deviation signal, the azimuth deviation signal, the distance deviation signal, and the positioning point deviation signal in the deviation control signal; wherein the modulation parameters include amplitude modulation parameters and frequency modulation parameters;

[0021] The program-controlled signal generators include: VOR program-controlled signal generator, LOC program-controlled signal generator, GS program-controlled signal generator, MK program-controlled signal generator, DME program-controlled signal generator, and ADF program-controlled signal generator;

[0022] generating a radio frequency signal having characteristics consistent with the navigation station signal of the target simulated airport, wherein the navigation station signal is used to provide track guidance and distance positioning;

[0023] The radio frequency signal is output as an analog navigation signal.

[0024] As an optional implementation, the course deviation signal is used to indicate a lateral error of the target aircraft from the ideal track centerline;

[0025] The bearing deviation signal is used to indicate the relative bearing error of the target aircraft relative to the navigation station;

[0026] The distance deviation signal is used to indicate the straight-line distance error between the target aircraft and the navigation station;

[0027] The positioning point deviation signal is used to indicate the three-dimensional position information of the target aircraft relative to the reference positioning point of the navigation system.

[0028] As an optional implementation, the transmitting circuit further includes: an adaptive signal attenuator;

[0029] The adaptive signal attenuator is used to dynamically adjust the transmission power based on the airspace environment around the target aircraft and the positions of other aircraft.

[0030] As an optional implementation, the dynamic adjustment of the transmission power includes: the adaptive signal attenuator perceives the airspace environment around the target aircraft and the positions of other aircraft in real time through an onboard sensing device deployed in the target aircraft.

[0031] As an optional implementation manner, the dynamically adjusting the transmit power further includes:

[0032] Determining, based on the airspace environment and the positions of the other aircraft, the relative distance between the target aircraft and the other aircraft, and information on the impact of the airspace environment on signal propagation;

[0033] The transmission power of the simulated navigation signal is dynamically adjusted based on the relative distance and the impact information by using a preset power control algorithm, so that the coverage range of the simulated navigation signal is limited to the receiving range of the target aircraft.

[0034] As an optional implementation manner, the preset power control algorithm includes:

[0035] Setting a multi-level safety distance threshold value and dividing the relative distance into multiple threshold intervals;

[0036] Dynamically selecting a corresponding transmit power level based on a threshold interval within which the relative distance lies;

[0037] Based on the impact information of the airspace environment, a signal propagation loss model is established to evaluate and determine attenuation, reflection, and scattering information in signal propagation;

[0038] In response to the relative distance being less than a first safety distance threshold, a target transmit power is determined based on the signal propagation loss model, and an attenuation parameter of the adaptive signal attenuator is adjusted.

[0039] In a second aspect, the present disclosure further provides a flight training simulation system capable of rapidly simulating an airport environment, comprising:

[0040] a processing module configured to obtain real-time position information of a target aircraft and parameter information of a target simulated airport, and based on the real-time position information of the target aircraft and the parameter information of the target simulated airport, calculate a relative position difference between the target aircraft and the target simulated airport, and generate a deviation control signal; wherein the parameter information includes runway length, width, elevation, navigation station location, and approach path information; and the deviation control signal is used to represent a difference between the current track of the target aircraft and the ideal track of the target simulated airport;

[0041] a signal generating module, configured to generate a simulated navigation signal using a program-controlled signal generator based on the deviation control signal;

[0042] a signal transmission module, configured to perform intensity attenuation and frequency synthesis on the analog navigation signal through a transmission circuit, and transmit the signal through a transmission antenna; wherein the transmission intensity of the analog navigation signal is limited to a receiving range of the target aircraft;

[0043] The signal analysis module is used to receive the simulated navigation signal using the receiving antenna component of the target aircraft, and analyze it to generate navigation information.

[0044] Compared with the existing technology, the beneficial effects of the present invention are: it can accurately simulate the airport environment and provide high-precision navigation signals, including channel deviation, azimuth deviation, distance deviation and positioning point deviation information, to effectively guide pilots in training. Secondly, the present invention generates different types of navigation signals through the collaborative work of multiple programmable signal generators, making the training scenarios more diverse and targeted. At the same time, adaptive signal attenuators and airspace sensing equipment are used to dynamically adjust the signal transmission power to ensure accurate signal coverage, avoid interference, and improve the safety of training. The invention does not need to rely on actual airport construction and airspace resources, reduces training costs, and optimizes signal transmission through signal propagation loss models, further enhancing the realism and effectiveness of training. Overall, the present invention provides an efficient, flexible and safe solution for flight training, with high innovation and practical value. BRIEF DESCRIPTION OF THE DRAWINGS

[0045] Figure 1 A flowchart of a flight training simulation method capable of quickly simulating an airport environment provided by an embodiment of the present disclosure;

[0046] Figure 2 A schematic diagram of a flight training simulation scenario provided by an embodiment of the present disclosure;

[0047] Figure 3 A schematic structural diagram of a mainframe box provided in an embodiment of the present disclosure;

[0048] Figure 4 A schematic diagram of a flight training simulation system that can quickly simulate an airport environment provided by an embodiment of the present disclosure.

[0049] Reference numerals: 10, processing module; 20, signal generating module; 30, signal transmitting module; 40, signal analyzing module. DETAILED DESCRIPTION

[0050] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0051] See Figure 1 , Figure 1 This is a flow chart of a flight training simulation method for rapidly simulating an airport environment provided by an embodiment of the present disclosure. The method comprises steps S101 to S104, wherein:

[0052] S101: Acquire real-time position information of a target aircraft and parameter information of a target simulated airport, and based on the real-time position information of the target aircraft and the parameter information of the target simulated airport, calculate the relative position difference between the target aircraft and the target simulated airport, and generate a deviation control signal; wherein the parameter information includes: runway length, width, elevation, navigation station location, and approach path information; the deviation control signal is used to represent the difference between the current track of the target aircraft and the ideal track of the target simulated airport;

[0053] S102: Based on the deviation control signal, generate a simulated navigation signal using a program-controlled signal generator;

[0054] S103: performing intensity attenuation and frequency synthesis on the analog navigation signal through a transmitting circuit, and transmitting the signal through a transmitting antenna; wherein the transmission intensity of the analog navigation signal is limited to a receiving range of the target aircraft;

[0055] S104: Utilize the receiving antenna assembly of the target aircraft to receive the simulated navigation signal, analyze it, and generate navigation information.

[0056] Among them, the present invention provides a flight training simulation method that can quickly simulate the airport environment. The method aims to provide an efficient, low-cost and flexible virtual airport environment for flight training, which can simulate the navigation signals and operating environment of the target simulated airport, and assist pilots in completing flight training at various stages.

[0057] Regarding S101 above:

[0058] In a specific implementation, real-time location information can be obtained through navigation and positioning equipment on the target aircraft and parsed to generate the target aircraft's real-time location information, such as three-dimensional coordinates such as longitude, latitude, and altitude. Furthermore, parameter information for the target simulated airport is pre-stored in an airport location database within the aircraft.

[0059] Exemplarily, the database uses a standardized format to store data, including: the target simulated airport's runway length, width, and elevation; the location coordinates of navigation stations (such as VOR, DME, and ILS); geometric point information on the approach path; the three-dimensional coordinates and altitude data of obstacles surrounding the airport; and information on navigation stations, approach charts, and departure charts. At the start of a flight training mission, the aircraft navigation system loads the target simulated airport data from the airport location database and inputs it, along with real-time aircraft position data, into the calculation module, providing a foundation for subsequent calculations.

[0060] As an optional implementation manner, the acquiring of the real-time position information of the target aircraft and the parameter information of the target simulated airport includes:

[0061] Receive satellite signals and analyze the real-time position information of the target aircraft through a GPS receiver or Beidou receiver installed on the target aircraft;

[0062] The parameter information of the target simulated airport is stored in an airport location database deployed in the target aircraft;

[0063] The airport location database includes: runway parameters, location information of navigation stations, geometric data of approach paths, and three-dimensional coordinate information of surrounding obstacles.

[0064] For example, a GPS receiver and a BeiDou receiver each receive navigation signals from their corresponding satellites. These signals include the satellite's position, time stamp, and navigation message. A parsing module within the receiver calculates the longitude, latitude, and altitude of the target aircraft. The parsed three-dimensional coordinate data is output as the target aircraft's real-time position information for subsequent calculations.

[0065] In practice, to simulate the operating environment of the target simulated airport, an airport location database is pre-deployed inside the target aircraft. The database stores relevant parameter information of the target simulated airport in a standardized storage structure, including, for example:

[0066] Runway parameters: The runway length, width and elevation data of the target simulated airport, which are used to determine the reference track when generating the simulated navigation signal;

[0067] Navigation station location information: including the ground coordinates and frequency information of the navigation stations (such as VOR stations, DME stations and ILS stations) at the target simulated airport;

[0068] Approach path geometry data: includes the three-dimensional coordinates of the approach track points, describing the geometry of the target aircraft's ideal approach route;

[0069] Surrounding obstacle information: stores the three-dimensional coordinates and height information of obstacles around the airport, which is used to simulate complex terrain and obstacle avoidance scenarios.

[0070] In practice, when a flight mission is initiated, the target aircraft's navigation system loads the database data for the target simulated airport. Using the database query function, parameter information related to the target simulated airport is extracted and loaded into the navigation system's working memory. Simultaneously, the aircraft's real-time position information is dynamically updated and integrated into the calculation module. At this point, the target aircraft's real-time position information and the target simulated airport's parameter information are matched within the system, ready for use in subsequent relative position calculations and navigation signal generation steps.

[0071] In this way, the target aircraft can obtain its own three-dimensional position and complete parameter information of the target simulated airport in real time, providing accurate input data for subsequent simulated navigation signal generation.

[0072] Furthermore, the relative position difference between the target aircraft and the target simulated airport is calculated based on the real-time position information and the parameter information of the target simulated airport. By calling the ideal track data in the database, including the ground coordinates of the navigation station and the three-dimensional position of the ideal track point, and comparing it with the real-time collected target aircraft position, the lateral deviation, longitudinal deviation and altitude deviation are calculated respectively. Among them, the lateral deviation represents the lateral distance of the target aircraft from the centerline of the ideal track, the longitudinal deviation represents the time or space offset of the target aircraft in the track direction, and the altitude deviation represents the vertical deviation of the current altitude of the target aircraft from the ideal altitude. These deviation information are summarized as deviation control signals and transmitted to the program-controlled signal generator in real time to guide the generation of navigation signals.

[0073] As an optional implementation manner, generating the deviation control signal includes:

[0074] Extracting ideal track data from the airport location database; wherein the ideal track data includes: navigation station location, approach path geometry data, and runway location;

[0075] comparing the real-time position information of the target aircraft with the ideal track data to generate course deviation information, azimuth deviation information, distance deviation information, and position point deviation information;

[0076] The course deviation information, the azimuth deviation information, the distance deviation information, and the positioning point deviation information are integrated to generate the deviation control signal.

[0077] In specific implementation, in order to generate a deviation control signal, it is necessary to combine the real-time position information of the target aircraft with the ideal track data of the target simulated airport, and generate the course deviation information, azimuth deviation information, distance deviation information and positioning point deviation information through a series of calculations, and integrate this information into a deviation control signal.

[0078] In practice, the target aircraft's navigation system extracts ideal track data from its internal airport location database. This database uses a standardized structure to store key parameters of the target simulated airport, including navigation station coordinates (such as the 3D coordinates and frequency information of VOR, DME, and ILS stations), approach path geometry, and the 3D coordinates and elevation of the runway centerline. Extracting ideal track data provides the foundation for subsequent deviation calculations.

[0079] Furthermore, the three-dimensional spatial position information of the target aircraft, including longitude, latitude, and altitude, is obtained through real-time navigation and positioning equipment. Then, the real-time position information of the target aircraft is compared with the extracted ideal track data to generate the following deviation information:

[0080] Course Deviation Information: Course deviation information is calculated by projecting the target aircraft's current position onto the ideal track centerline. It represents the lateral deviation of the target aircraft from the track centerline. Specifically, the system calculates the lateral distance between the target aircraft and the closest point on the track centerline using a geometric projection algorithm and outputs this distance as course deviation information.

[0081] Azimuth Deviation Information: Azimuth deviation information is calculated from the relative azimuth between the target aircraft's current position and the navigation station's position. It represents the relative bearing error between the target aircraft and the navigation station. The system uses trigonometric relationships to calculate the azimuth between the target aircraft and the navigation station and compares it with the ideal azimuth to generate the deviation information.

[0082] Range Deviation Information: Range deviation information is calculated using the three-dimensional straight-line distance between the target aircraft's current position and the navigation station's location. It represents the distance error between the target aircraft and the navigation station. In practice, the system calculates the actual distance between the target aircraft and the navigation station using a three-dimensional coordinate formula and compares it with the ideal distance to generate the range deviation information.

[0083] Fix Deviation Information: Fix Deviation information is calculated by comparing the three-dimensional position of the target aircraft with a target fix (such as the runway touchdown point or a key point defined by the navigation system). It represents the target aircraft's specific deviation from the fix. The system compares the target aircraft's current position with the target fix coordinates item by item, generating the difference in longitude, latitude, and altitude to form the fix deviation information.

[0084] Finally, the generated course deviation, bearing deviation, range deviation, and position deviation information are integrated into a deviation control signal. This integration process represents this information as a multidimensional vector, with each dimension corresponding to a different type of deviation information, and its direction and amplitude respectively reflecting the target aircraft's deviation direction and degree. The generated deviation control signal is transmitted in real time to a programmable signal generator, providing accurate input data for the subsequent generation of simulated navigation signals.

[0085] In this way, the present invention can calculate various deviation information between the target aircraft and the ideal track of the target simulated airport in real time, and integrate them into deviation control signals, providing high-precision navigation information support for flight training.

[0086] Regarding S102 above:

[0087] As an optional implementation manner, the simulated navigation signal includes:

[0088] Dynamically adjust the modulation parameters of the output signal of the program-controlled signal generator based on the course deviation signal, the azimuth deviation signal, the distance deviation signal, and the positioning point deviation signal in the deviation control signal; wherein the modulation parameters include amplitude modulation parameters and frequency modulation parameters;

[0089] generating a radio frequency signal having characteristics consistent with the navigation station signal of the target simulated airport, wherein the navigation station signal is used to provide track guidance and distance positioning;

[0090] The radio frequency signal is output as an analog navigation signal.

[0091] As an optional implementation:

[0092] The course deviation signal is used to indicate the lateral error of the target aircraft from the ideal track centerline;

[0093] The bearing deviation signal is used to indicate the relative bearing error of the target aircraft relative to the navigation station;

[0094] The distance deviation signal is used to indicate the straight-line distance error between the target aircraft and the navigation station;

[0095] The positioning point deviation signal is used to indicate the three-dimensional position information of the target aircraft relative to the reference positioning point of the navigation system.

[0096] The generation of the simulated navigation signal is accomplished by various types of programmable signal generators. These programmable signal generators include but are not limited to:

[0097] VOR programmable signal generator: used to generate VOR signals to provide angular deviation information of the target aircraft on the track;

[0098] LOC programmable signal generator: used to generate the localizer signal (LOC), providing guidance information of the channel centerline during the approach process;

[0099] GS programmable signal generator: used to generate glide slope (GS) signals to provide accurate landing glide angle guidance for aircraft;

[0100] MK programmable signal generator: used to generate marker beacon (MK) signals to indicate the aircraft's position relative to the runway reference point;

[0101] DME programmable signal generator: used to generate distance measuring equipment (DME) signals, providing distance information between the aircraft and the navigation station;

[0102] ADF programmable signal generator: used to generate automatic direction finder (ADF) signals for wide-area navigation or backup navigation signals.

[0103] In a specific implementation, each programmable signal generator receives deviation control signals transmitted by the computing processor, including a course deviation signal, a bearing deviation signal, a range deviation signal, and a position deviation signal. These deviation signals are used as a basis for adjusting the output signal of the programmable signal generator.

[0104] For example, the VOR programmable signal generator adjusts the frequency modulation parameters according to the azimuth deviation signal to generate a radio frequency signal representing the aircraft's track angle deviation; the LOC programmable signal generator adjusts the amplitude modulation parameters based on the course deviation signal to generate a course centerline guidance signal consistent with the characteristics of the navigation station; the GS programmable signal generator combines the range deviation signal and altitude data to adjust the amplitude and frequency modulation parameters to generate a glide slope signal; the DME programmable signal generator uses the range deviation signal to generate ranging information to indicate the precise distance between the aircraft and the navigation station.

[0105] After the modulation parameters of each programmable signal generator are adjusted, the corresponding radio frequency signals are generated. These signals respectively represent the functional characteristics of the navigation station, such as VOR signals for omnidirectional navigation and LOC signals for precise channel guidance.

[0106] All generated RF signals are synthesized and attenuated by the transmitting circuit, integrated into the final analog navigation signal and transmitted for reception by the aircraft.

[0107] In this way, through the coordinated work of multiple programmable signal generators, the present invention can generate accurate simulated navigation signals, fully simulate the characteristics of the airport's navigation stations, and meet the navigation needs of different stages in flight training.

[0108] Regarding S103 above:

[0109] The resulting analog navigation signal is then processed by the transmitter circuit. This circuit attenuates the signal and synthesizes its frequency to ensure that the signal strength is within the target aircraft's reception range. After signal processing, the analog navigation signal is transmitted via the target aircraft's transmitting antenna. The transmission intensity and coverage are strictly controlled to ensure that the signal is limited to the target aircraft's reception area and does not interfere with the normal navigation signal reception of other nearby aircraft.

[0110] As an optional implementation:

[0111] The transmitting circuit further includes: an adaptive signal attenuator;

[0112] The adaptive signal attenuator is used to dynamically adjust the transmission power based on the airspace environment around the target aircraft and the positions of other aircraft.

[0113] As an optional implementation, the dynamic adjustment of the transmission power includes: the adaptive signal attenuator perceives the airspace environment around the target aircraft and the positions of other aircraft in real time through an onboard sensing device deployed in the target aircraft.

[0114] As an optional implementation manner, the dynamically adjusting the transmit power further includes:

[0115] Determining, based on the airspace environment and the positions of the other aircraft, the relative distance between the target aircraft and the other aircraft, and information on the impact of the airspace environment on signal propagation;

[0116] The transmission power of the simulated navigation signal is dynamically adjusted based on the relative distance and the impact information by using a preset power control algorithm, so that the coverage range of the simulated navigation signal is limited to the receiving range of the target aircraft.

[0117] In this invention, an adaptive signal attenuator is incorporated into the transmission circuit to dynamically adjust the transmission power based on the airspace surrounding the target aircraft and the location of other aircraft. This adaptive signal attenuator effectively controls the coverage of the analog navigation signal, preventing interference with other aircraft while ensuring navigation signal accuracy.

[0118] In a specific implementation, the adaptive signal attenuator receives real-time data from airspace environment perception, including airspace information around the target aircraft (such as terrain obstacles, weather conditions, etc.) and position data of other aircraft (such as relative distance and heading information).

[0119] Based on the received environmental parameters, the internal algorithm of the adaptive signal attenuator evaluates the current signal propagation requirements and dynamically calculates the appropriate power attenuation parameters.

[0120] For example, when other aircraft are close, the signal attenuation is increased to limit the signal coverage range; when the signal propagation loss in the airspace environment is large, the signal attenuation is reduced to ensure that the target aircraft can receive clear navigation signals.

[0121] Furthermore, the adaptive signal attenuator applies the calculated attenuation parameter to the transmitting circuit, adjusting the transmit power of the analog navigation signal in real time. The adjusted signal strength is strictly controlled within the receiving range of the target aircraft, ensuring the reliability of the navigation signal.

[0122] In this way, through the dynamic adjustment of the adaptive signal attenuator, the present invention can adapt to different airspace environments and flight training scenarios, achieve accurate coverage of navigation signals, and avoid interference with other aircraft.

[0123] In the present invention, the adaptive signal attenuator senses the airspace environment around the target aircraft and the positions of other aircraft in real time through the airborne sensing equipment deployed in the target aircraft, providing basic data support for dynamically adjusting the transmission power.

[0124] In specific implementations, the target aircraft carries onboard sensing equipment including ADS-B (Automatic Dependent Surveillance-Broadcast) receivers, radar sensors, and environmental monitors.

[0125] Among them, the ADS-B receiver is used to receive real-time data on the position, speed, heading, etc. of surrounding aircraft; the radar sensor is used to perceive the three-dimensional position and motion status of close-range aircraft; and the environmental monitor is used to obtain weather conditions (such as wind speed, humidity, visibility) and terrain obstacle information around the target aircraft.

[0126] In practice, the data collected by the sensing device is transmitted to the aircraft's internal environmental processing module for data fusion and analysis. The fused data includes the relative position of the target aircraft and other aircraft, heading deviation, and the potential impact of the airspace environment on signal propagation.

[0127] The analyzed environmental data is fed into the adaptive signal attenuator, which updates the transmit power adjustment parameters in real time. By sensing the airspace surrounding the target aircraft and the positions of other aircraft, the adaptive signal attenuation can be dynamically adjusted to effectively cope with complex flight environments.

[0128] In the present invention, the process of dynamically adjusting the transmission power is further combined with the relative distance between the target aircraft and other aircraft, as well as the impact of the airspace environment on signal propagation, to achieve precise control through a preset power control algorithm.

[0129] In a specific implementation, the relative distance between the target aircraft and other aircraft is calculated in real time through ADS-B receivers and radar sensors.

[0130] In addition, weather monitoring and terrain data are combined to evaluate the impact of the airspace environment on signal propagation, such as signal attenuation, reflection and scattering.

[0131] In specific implementations, the power control algorithm built into the adaptive signal attenuator dynamically adjusts the transmission power based on relative distance and environmental impact information. For example, when the relative distance between the target aircraft and other aircraft is far, the signal attenuation is reduced to ensure that the target aircraft can receive clear navigation signals; when the relative distance is close or the airspace environment is complex (such as strong signal reflection or scattering), the signal attenuation is increased to limit the signal coverage range.

[0132] Furthermore, the adaptive signal attenuator, using adjustment parameters calculated by the power control algorithm, updates the transmit power output level in real time, ensuring that the simulated navigation signal's coverage is strictly limited to the target aircraft's reception area. This adjusted signal strength satisfies the target aircraft's navigation needs while avoiding interference with other aircraft's normal signal reception.

[0133] As an optional implementation manner, the preset power control algorithm includes:

[0134] Setting a multi-level safety distance threshold value and dividing the relative distance into multiple threshold intervals;

[0135] Dynamically selecting a corresponding transmit power level based on a threshold interval within which the relative distance lies;

[0136] Based on the impact information of the airspace environment, a signal propagation loss model is established to evaluate and determine attenuation, reflection, and scattering information in signal propagation;

[0137] In response to the relative distance being less than a first safety distance threshold, a target transmit power is determined based on the signal propagation loss model, and an attenuation parameter of the adaptive signal attenuator is adjusted.

[0138] To precisely control the transmit power of simulated navigation signals, the present invention employs a pre-defined power control algorithm, designed as a dynamic adjustment mechanism based on the relative distance between the target aircraft and other aircraft and the airspace environment. This power control algorithm uses multiple safety distance thresholds, combined with the results of a signal propagation loss model, to determine the target transmit power and adjust the parameters of the adaptive signal attenuator in real time, thereby strictly controlling the navigation signal coverage.

[0139] In practice, multiple safety distance thresholds are preset, dividing the relative distance between the target aircraft and other aircraft into several threshold intervals. For example, the first safety distance threshold is the minimum safety distance, indicating that the signal needs to be highly attenuated to avoid interference; the second and third safety distance thresholds correspond to medium and long distances, respectively, indicating that the signal needs to be gradually attenuated to ensure navigation effectiveness. The specific ranges of each threshold interval are adjusted based on the actual requirements of the flight training scenario and airspace environment.

[0140] For example, during a flight mission, the relative distance between the target aircraft and surrounding aircraft is monitored in real time using an ADS-B receiver and airborne radar. When the relative distance data is updated, the threshold range within which the current distance falls is automatically determined, and the corresponding transmit power level is dynamically selected. For example, when the relative distance is within the first safe distance threshold, the lowest power level is selected, significantly increasing the degree of signal attenuation. When the relative distance exceeds the third safe distance threshold, a higher power level is selected to reduce signal attenuation and ensure navigation signal clarity.

[0141] At the same time, the power control algorithm also dynamically optimizes signal propagation based on the impact information of the airspace environment.

[0142] In the specific implementation, a signal propagation loss model is established through weather sensors, terrain data and historical flight data to evaluate the attenuation, reflection and scattering in signal propagation.

[0143] For example, in complex terrain or low visibility conditions, the signal propagation loss model calculates the multipath effect caused by environmental reflections on the signal and predicts its possible attenuation.

[0144] Based on the model calculation results, the transmit power level is further modified to offset the impact of adverse environmental factors.

[0145] When the relative distance is less than the first safety distance threshold, minimizing signal interference is prioritized. The power control algorithm, combined with the calculation results of the signal propagation loss model, determines the appropriate target transmit power and outputs the updated attenuation parameter to the adaptive signal attenuator. Based on this parameter, the adaptive signal attenuator adjusts the output power of the navigation signal in real time to ensure that the signal coverage is strictly limited to the reception area of ​​the target aircraft.

[0146] For example, a signal propagation loss model can be based on the classic free-space path loss model, combined with environmental corrections from the ITU-R signal propagation model, to evaluate the propagation characteristics of simulated navigation signals in an airspace environment. The model dynamically adjusts transmit power by inputting the positions of the target aircraft and other aircraft, airspace environment parameters, and terrain information to ensure signal coverage and navigation accuracy.

[0147] In this way, the preset power control algorithm can achieve precise control of the transmission power of the simulated navigation signal in a dynamic flight environment, which not only meets the navigation needs but also effectively avoids interference with other aircraft, significantly improving the safety of flight training and the intelligence level of signal management.

[0148] Regarding S104 above:

[0149] The target aircraft's receiving antenna assembly then receives and interprets the simulated navigation signals. The interpreted signals are processed by the aircraft's navigation system, generating track guidance information and displaying detailed deviation information on the flight instruments, including lateral, longitudinal, and altitude deviations. The pilot adjusts flight operations based on these displayed deviations, ensuring the target aircraft completes the training mission on the desired trajectory at the target simulated airport.

[0150] In this way, through the above method, the present invention realizes the function of quickly constructing a simulated airport environment around the target aircraft. The generated simulated navigation signal accurately reflects the deviation information of the target aircraft, has the characteristics of high efficiency, low cost and flexibility, and can provide reliable technical support for flight training.

[0151] See Figure 2 and Figure 3 , Figure 2 A schematic diagram of a flight training simulation scenario provided by an embodiment of the present disclosure; Figure 3 A schematic structural diagram of a host chassis provided in an embodiment of the present disclosure.

[0152] For example, the system first acquires the real-time location of the target aircraft. This information is obtained by using the aircraft's GPS or Beidou receiver to receive satellite signals in real time and parse the information into three-dimensional coordinates (longitude, latitude, and altitude), thereby determining the target aircraft's location. Simultaneously, relevant parameter information for the target simulated airport is pre-stored in the aircraft's internal airport location database. This database stores information in a standardized format, including runway length, width, and elevation; the location coordinates of navigation stations (such as VOR, DME, and ILS); approach path geometry; and the three-dimensional coordinates of obstacles surrounding the airport.

[0153] Next, the system calculates the relative position difference between the target aircraft and the target simulated airport based on the target aircraft's real-time position information and the parameters of the target simulated airport, generating a deviation control signal. This deviation control signal primarily represents the difference between the target aircraft's current track and the ideal track, including information on course deviation, bearing deviation, distance deviation, and position deviation. At this point, the deviation control signal is transmitted to a programmable signal generator, providing input data for the subsequent generation of simulated navigation signals.

[0154] When generating simulated navigation signals, the system dynamically adjusts the signal's modulation parameters through a programmable signal generator. Specifically, the system adjusts the amplitude and frequency modulation parameters based on the different deviation information (such as course deviation and azimuth deviation) contained in the deviation control signal. To simulate the navigation signal characteristics of the target simulated airport, multiple programmable signal generators work together, including a VOR programmable signal generator, a LOC programmable signal generator, a GS programmable signal generator, and a DME programmable signal generator. Each programmable signal generator adjusts its modulation parameters based on the deviation control signal to generate a corresponding radio frequency signal. The VOR signal provides the aircraft's angular deviation information, the LOC signal guides the aircraft's course during approach, the GS signal provides precise glide path guidance, and the DME signal provides distance information between the aircraft and the navigation station.

[0155] The generated RF signal undergoes intensity attenuation and frequency synthesis processing in the transmitting circuit to ensure that the simulated navigation signal's transmission intensity is limited to the target aircraft's reception range, avoiding interference with other aircraft. After signal processing, the simulated navigation signal is transmitted into the airspace via the target aircraft's transmitting antenna, where it is received by the target aircraft's receiving antenna.

[0156] After receiving the signal, the target aircraft's receiving antenna assembly interprets the simulated navigation signal and processes it through the navigation system to generate navigation information. This navigation information includes track guidance and flight deviation information. The pilot uses this information to adjust flight operations, ensuring the target aircraft follows the desired flight path at the target simulated airport. Ultimately, through this simulated training environment, pilots can complete different stages of flight missions, thereby improving the quality and efficiency of training.

[0157] Furthermore, the remote control box, a key control unit, provides comprehensive system control and data feedback through its connection to the computer processor. The connection lines between the remote control box and the computer processor are labeled with function control, status display, and data interface signals. These signals are used for signal transmission and interaction between the remote control box and the system, ensuring efficient and flexible flight training.

[0158] In this way, the present invention provides pilots with an accurate, flexible, low-cost and safe virtual flight training environment by dynamically adjusting the transmission power of the simulated navigation signal, the modulation parameters of the programmable signal generator, and signal attenuation processing, thereby meeting the different training needs of pilots.

[0159] Based on the same inventive concept, the embodiment of the present disclosure also provides a flight training simulation system that can quickly simulate an airport environment, corresponding to a flight training simulation method that can quickly simulate an airport environment. Since the principle of solving the problem by the system in the embodiment of the present disclosure is similar to the above-mentioned flight training simulation method that can quickly simulate an airport environment, the implementation of the system can refer to the implementation of the method, and the repeated parts will not be repeated.

[0160] Reference Figure 4 As shown, Figure 4 This is a schematic diagram of a flight training simulation system capable of rapidly simulating an airport environment according to an embodiment of the present disclosure. The system includes:

[0161] The processing module 10 is configured to obtain real-time position information of a target aircraft and parameter information of a target simulated airport, and based on the real-time position information of the target aircraft and the parameter information of the target simulated airport, calculate the relative position difference between the target aircraft and the target simulated airport, and generate a deviation control signal; wherein the parameter information includes runway length, width, elevation, navigation station location, and approach path information; the deviation control signal is used to represent the difference between the current track of the target aircraft and the ideal track of the target simulated airport;

[0162] A signal generating module 20 is configured to generate a simulated navigation signal using a program-controlled signal generator based on the deviation control signal;

[0163] a signal transmitting module 30 configured to perform intensity attenuation and frequency synthesis on the analog navigation signal through a transmitting circuit and transmit the signal through a transmitting antenna; wherein the transmission intensity of the analog navigation signal is limited to within the receiving range of the target aircraft;

[0164] The signal analysis module 40 is used to receive the simulated navigation signal using the receiving antenna assembly of the target aircraft, analyze the signal, and generate navigation information.

[0165] It should be understood that in the various embodiments of the present application, the size of the serial numbers of the above-mentioned processes does not mean the order of execution. The execution order of each process should be determined by its function and internal logic, and should not constitute any limitation on the implementation process of the embodiments of the present application.

[0166] It should be understood that determining B based on A does not mean determining B based solely on A. B can also be determined based on A and / or other information.

[0167] Those skilled in the art will appreciate that the units and algorithm steps of each example described in conjunction with the embodiments disclosed in the present invention can be implemented in electronic hardware, or a combination of computer software and electronic hardware. Whether these functions are performed in hardware or software depends on the specific application and design constraints of the technical solution. Professionals and technicians can use different methods to implement the described functions for each specific application, but such implementation should not be considered beyond the scope of the present invention.

[0168] Throughout this specification, references to terms such as "one embodiment," "example," or "specific example" indicate that the specific features, structures, materials, or characteristics described in conjunction with that embodiment or example are included in at least one embodiment or example of the present invention. In this specification, schematic representations of these terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

[0169] The preferred embodiments of the present invention disclosed above are intended only to help illustrate the present application. The preferred embodiments do not describe all details in detail, nor do they limit the present application to specific embodiments. Obviously, many modifications and variations can be made based on the contents of this specification. This specification selects and describes these embodiments in detail to better explain the principles and practical applications of the present application, so that those skilled in the art can better understand and utilize the present application. The present application is limited only by the claims and their full scope and equivalents.

Claims

1. A flight training simulation method capable of rapidly simulating an airport environment, characterized in that: include: Acquiring real-time position information of a target aircraft and parameter information of a target simulated airport stored in an internal airport position database of the aircraft, and generating a deviation control signal based on the real-time position information of the target aircraft and the parameter information of the target simulated airport; wherein the parameter information includes: runway length, width, elevation, navigation station location and approach path information, and three-dimensional coordinate information of surrounding obstacles; the deviation control signal is used to represent the difference between the current track of the target aircraft and the ideal track of the target simulated airport; the deviation control signal includes course deviation information, azimuth deviation information, distance deviation information, and position point deviation information; The deviation control signal is formed by integrating multiple deviation information generated by the following direct calculation method: Course deviation information, calculated by projecting the current position of the target aircraft onto the ideal track centerline, indicating the lateral deviation of the target aircraft from the ideal track centerline; Azimuth deviation information is obtained by calculating the relative azimuth angle between the target aircraft and the navigation station through trigonometric functions, and is used to indicate the relative azimuth error of the target aircraft relative to the navigation station; Distance deviation information, obtained by calculating the straight-line distance between the target aircraft and the navigation station using a three-dimensional coordinate formula, indicating the straight-line distance error between the target aircraft and the navigation station; and Position deviation information, formed by comparing the current position of the target aircraft with the coordinates of the target position point, generating the difference in longitude, latitude and altitude, which is used to indicate the three-dimensional position information of the target aircraft relative to the reference position of the navigation system; In a multi-channel programmable signal generator integrated into the target aircraft, the amplitude modulation parameters and frequency modulation parameters of each signal are dynamically adjusted based on the deviation control signal to generate a simulated navigation signal consistent with the signal characteristics of the target simulated airport navigation station; wherein the multi-channel programmable signal generator includes VOR, LOC, GS, DME, MK, and ADF programmable signal generators; The analog navigation signal is subjected to intensity attenuation and frequency synthesis by a transmitting circuit including an adaptive signal attenuator, and is transmitted through an aircraft transmitting antenna; and the transmission power is dynamically adjusted based on the following rules: Real-time awareness of the airspace environment around the target aircraft and the positions of other aircraft through ADS-B receivers, airborne radars, and environmental monitors; and The relative distance between the target aircraft and other aircraft is divided into multiple safety distance thresholds. The corresponding transmission power level is selected based on the signal propagation loss model of the airspace environment to limit the coverage of the radio frequency signal to the receiving range of the target aircraft. The simulated navigation signal is received by the receiving antenna assembly of the target aircraft, and analyzed to generate navigation information.

2. The method according to claim 1, characterized in that The step of obtaining the real-time position information of the target aircraft and the parameter information of the target simulated airport includes: The GPS receiver or BeiDou receiver installed on the target aircraft receives satellite signals and parses the real-time position information of the target aircraft.

3. The method according to claim 2, characterized in that Generating the deviation control signal includes: Extracting ideal track data from the airport location database; wherein the ideal track data includes: navigation station locations, approach path geometry data, and runway locations; Comparing the real-time position information of the target aircraft with the ideal track data to generate course deviation information, azimuth deviation information, distance deviation information, and position point deviation information respectively; The course deviation information, the azimuth deviation information, the distance deviation information, and the positioning point deviation information are integrated to generate the deviation control signal.

4. The method according to claim 3, characterized in that The simulated navigation signal includes: Dynamically adjust the modulation parameters of the output signal of the programmable signal generator based on the course deviation information, azimuth deviation information, distance deviation information and positioning point deviation information in the deviation control signal; wherein the modulation parameters include amplitude modulation parameters and frequency modulation parameters; generating a radio frequency signal having characteristics consistent with the navigation station signal of the target simulated airport, wherein the navigation station signal is used to provide track guidance and distance positioning; The radio frequency signal is output as an analog navigation signal.

5. The method according to claim 4, characterized in that The dynamic adjustment of the transmission power includes: the adaptive signal attenuator perceives the airspace environment around the target aircraft and the positions of other aircraft in real time through the airborne sensing equipment deployed in the target aircraft.

6. The method according to claim 5, characterized in that The dynamically adjusting the transmit power further includes: Determining, based on the airspace environment and the positions of the other aircraft, the relative distance between the target aircraft and the other aircraft, and information on the impact of the airspace environment on signal propagation; The transmission power of the simulated navigation signal is dynamically adjusted based on the relative distance and the impact information by using a preset power control algorithm, so that the coverage range of the simulated navigation signal is limited to the receiving range of the target aircraft.

7. The method according to claim 6, characterized in that The preset power control algorithm includes: Setting a multi-level safety distance threshold value and dividing the relative distance into multiple threshold intervals; Dynamically selecting a corresponding transmit power level based on a threshold interval within which the relative distance lies; Based on the impact information of the airspace environment, a signal propagation loss model is established to evaluate and determine attenuation, reflection, and scattering information in signal propagation; In response to the relative distance being less than a first safety distance threshold, a target transmit power is determined based on the signal propagation loss model, and an attenuation parameter of the adaptive signal attenuator is adjusted.

8. A flight training simulation system capable of rapidly simulating an airport environment, characterized in that: Used to perform the method according to any one of claims 1 to 7, comprising: a processing module configured to obtain real-time position information of a target aircraft and parameter information of a target simulated airport, and based on the real-time position information of the target aircraft and the parameter information of the target simulated airport, calculate a relative position difference between the target aircraft and the target simulated airport, and generate a deviation control signal; wherein the parameter information includes runway length, width, elevation, navigation station location, and approach path information; and the deviation control signal is used to represent a difference between the current track of the target aircraft and the ideal track of the target simulated airport; a signal generating module, configured to generate a simulated navigation signal using a program-controlled signal generator based on the deviation control signal; a signal transmission module, configured to perform intensity attenuation and frequency synthesis on the analog navigation signal through a transmission circuit, and transmit the signal through a transmission antenna; wherein the transmission intensity of the analog navigation signal is limited to a receiving range of the target aircraft; The signal analysis module is used to receive the simulated navigation signal using the receiving antenna component of the target aircraft, and analyze it to generate navigation information.

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