System and method for simulating air vehicle performance in urban environment traffic

Abstract

The present invention provides a system and a method for simulating air vehicle performance in urban environment traffic, the system comprising: a dynamics modeling module which simulates flight motion of an air vehicle on the basis of virtual flight conditions preconfigured through a user interface; an air vehicle motion model verification module which provides a control environment for reflecting pilot input data for the air vehicle, and performs real-time monitoring on motion data of the air vehicle flying on the basis of an operation scenario configured according to the control environment or the virtual flight conditions; an aviation control and performance monitoring module which collects and analyzes flight data by controlling, in real time, a flight path of the air vehicle flying on the basis of the operation scenario, and monitors performance of the air vehicle on the basis of the analyzed data; and a main control module which interlinks and controls the respective modules, integrally evaluates the performance of the air vehicle, and provides an evaluated result value to a user.

Description

Aircraft performance simulation system and method for urban environment transportation

[0001] The present embodiment relates to a system and method for simulating the performance of an urban environment vehicle, which can accurately evaluate the performance of UAM / PAV components in real time.

[0002] The content described in this section merely provides background information for the present embodiment and does not constitute prior art.

[0003] There is growing interest in the diversification of aviation technology and the adoption of new modes of transportation through the utilization and application of artificial intelligence and convergence technologies. From this perspective, key modes include Urban Air Mobility (UAM), Personal Air Vehicles (PAVs), Flying Cars (FCs), and Vertical Take-Off and Landing (VTOLs) rotary-wing aircraft. Interest is focused on future technological development for new modes of transportation that reflect creative ideas. Among these, UAM and PAVs are expected to be the most feasible, with PAVs, FCs, VTOLs, and eVTOLs (Electric-powered Vertical Take-Off and Landing) being suitable as UAM modes of transportation. UAM / PAVs, also known as urban air traffic or urban air mobility, are beginning to attract attention as a new transportation method that can reduce the time and cost of traveling from downtown Seoul to the airport.

[0004] Here, UAM is an air transport system that includes a traffic management system, takeoff and landing infrastructure, etc. to safely and conveniently transport people and cargo in urban areas using eco-friendly electric vertical takeoff and landing aircraft (eVTOL) and vertiports that can be used in urban areas.

[0005] Currently, UAM in Korea is called urban air mobility because it focuses on mobility in the city center (Intracity). However, in a broader sense, UAM can be seen as a new mobility option for megacities that encompass both the city center and the surrounding metropolitan area (Intercity).

[0006] UAM requires extensive flight simulations from the R&D stage to actual operation. By reproducing various flight environments that could occur in urban areas during UAM operation, the safety of the aircraft can be verified. These flight simulations can prevent hazardous situations in advance and enable location analysis of vertiports, key infrastructure for UAM operations. In Korea, they can be utilized in future UAM commercialization demonstration projects.

[0007] The UAM system is a complex system (System of Systems, SoS) in which components function as independent systems, and is largely composed of three independent systems: special aircraft, pilots / passengers, airports, and skyspace (including operations / control / regulations).

[0008] The requirements of the UAM system can be divided into requirements from a technical perspective (function, performance, etc.) for each independent system and requirements from a perspective of overall UAM operation through the interaction between them (safety, operating route, applicable laws, etc.).

[0009] Existing flight simulation systems integrate high-fidelity aerodynamic and structural dynamic data to simulate aircraft flight. However, these systems often suffer from high computational costs and complexity, making real-time simulation difficult. In particular, UAM requires unique characteristics that take into account flight characteristics in urban environments and various weather conditions. However, existing flight simulation systems are specialized for fossil-fuel-powered aircraft or drone systems, making it difficult to use them as simulation models that apply the requirements of UAM systems for flight scenario testing and safety verification in urban operating environments.

[0010] In the future, there is an urgent need to develop UAM-specific simulation technology to accelerate the realization of UAM services, including safe aircraft operation, route setting, and traffic management.

[0011] One embodiment of the present invention aims to provide a system and method for simulating the performance of an urban environment vehicle by combining actual hardware and simulation based on a HILS (Hardware In the Loop Simulation) model to evaluate and analyze the performance of UAM / PAV components in real time.

[0012] As a technical means for achieving the above-described technical task, the present invention provides an aircraft performance simulation system for urban environment traffic according to one embodiment. The system is characterized by including: a dynamic modeling module that simulates the flight motion of an aircraft based on virtual flight conditions preset through a user interface; an aircraft motion model verification module that provides a control environment for reflecting a pilot's input data for the aircraft and monitors in real time the motion data of the aircraft flying based on a driving scenario set by the control environment or virtual flight conditions; an aviation control and performance monitoring module that controls the flight path of the aircraft flying based on the control scenario in real time, collects and analyzes flight data, and monitors the performance of the aircraft based on the analyzed data; and a main control module that controls each module in conjunction to perform an integrated evaluation of the performance of the aircraft and provides the evaluated result value to the user.

[0013] Alternatively, the aircraft motion model verification module is characterized by collecting motion data of the aircraft in conjunction with a Hardware-In-the-Loop-Simulation (HILS) model and monitoring the dynamic response of the aircraft in real time by comparing it with simulation data.

[0014] Alternatively, the main control module is characterized in that it provides a result value including at least one of a performance evaluation result for evaluating the stability, responsiveness or efficiency of an aircraft being flown based on the operation scenario, a comparative analysis result for verifying the accuracy of the simulation by comparing it with actual flight data or expected performance, and an anomaly detection result for detecting an anomaly in the simulation result.

[0015] Alternatively, the dynamic modeling module is characterized by including: an input parameter acquisition unit for acquiring input parameters including specifications, aerodynamic characteristics, structural characteristics, and kinematic characteristics of the aircraft required for object modeling of the aircraft; a modeling engine unit for simulating flight dynamics of the aircraft using a motion modeling platform that models motion of three or more degrees of freedom of the aircraft based on the input parameters; and an interface unit for setting virtual flight conditions for the flight motion of the aircraft through a user interface and visualizing the simulation results by the modeling engine unit.

[0016] Alternatively, the specifications of the aircraft include mass, size, center of gravity, and moment of inertia of the aircraft, the aerodynamic characteristics include aerodynamic coefficients including lift, drag, and coefficient of moment, the structural characteristics include material properties and arrangement data of structural components, and the kinematic characteristics include maximum speed, acceleration, angular velocity, and flight path of the aircraft.

[0017] Alternatively, the aircraft motion model verification module is characterized by including a control environment providing unit that provides a control environment for controlling the aircraft; a data processing unit that collects motion data of the aircraft flown according to the operation scenario and compares the collected motion data of the aircraft with simulation data to verify the performance of aircraft components; and a feedback reflection unit that reflects the pilot's input data acquired through the control environment providing unit in real time to the simulation and provides feedback on the pilot's input data.

[0018] Alternatively, the data processing unit is characterized in that it monitors in real time the aircraft status information including the position, speed or angular velocity of the aircraft in conjunction with a Hardware-In-the-Loop-Simulation (HILS) model.

[0019] Alternatively, the air traffic control and performance monitoring module is characterized by including: an air traffic control unit that performs flight path setting, flight trajectory tracking, flight history management, or flight performance evaluation functions for the aircraft; a performance monitoring unit that collects and analyzes real-time flight data for the aircraft in flight based on the operation scenario to evaluate the performance of the aircraft; and a communication interface unit that processes data exchange with the air traffic control unit or the performance monitoring unit in real time and performs data communication to share aircraft status information with other modules.

[0020] Alternatively, the performance monitoring unit is characterized in that it evaluates the performance of the aircraft and generates a test report.

[0021] A method for simulating the performance of an aircraft in an urban environment traffic, performed by a computing device including at least one processor according to one embodiment of the present invention, is characterized by including: a dynamic modeling process for simulating the flight motion of an aircraft based on virtual flight conditions preset through a user interface; an aircraft motion model verification process for providing a control environment for reflecting a pilot's input data for the aircraft and for monitoring in real time the motion data of the aircraft flying based on an operation scenario set by the control environment or virtual flight conditions; an air traffic control and performance monitoring process for controlling the flight path of the aircraft in real time to collect and analyze flight data and monitor the flight performance of the aircraft based on the analyzed data; and a main control process for performing an integrated evaluation of the performance of the aircraft by interlockingly controlling each module and providing the evaluated result value to a user.

[0022] As described above, according to one aspect of the present embodiment, the performance of UAM / PAV components can be accurately evaluated in real time based on the HILS (Hardware In the Loop Simulation) model, various virtual flight conditions and control situations can be simulated, and real-time performance verification is possible through linkage with actual hardware, thereby helping to optimize the performance of an aircraft and improve safety, and providing the user with the result of an integrated evaluation of the performance of the aircraft, thereby enabling immediate feedback.

[0023] In addition, according to one aspect of the present embodiment, it is very useful in the aviation and space industries that require high stability and reliability, and it is possible to reduce research and development costs by enabling simulations in various environments, and it is possible to verify the suitability of an aircraft through simulation and apply the derived results to the production or operation of UMA / PAV.

[0024] FIG. 1 is a block diagram illustrating a computing device for simulating aircraft performance in urban environment traffic according to one embodiment of the present invention.

[0025] FIG. 2 is a diagram illustrating the configuration of an aircraft performance simulation system for urban environment traffic according to one embodiment of the present invention.

[0026] Figure 3 is a block diagram illustrating the configuration of a dynamic modeling module according to one embodiment of the present invention.

[0027] FIG. 4 is a block diagram illustrating the configuration of an aircraft motion model verification module according to one embodiment of the present invention.

[0028] FIG. 5 is a block diagram illustrating the configuration of an air traffic control and performance monitoring module according to one embodiment of the present invention.

[0029] FIG. 6 is a flowchart illustrating a method for simulating aircraft performance in urban environment traffic according to one embodiment of the present invention.

[0030] The present invention is susceptible to various modifications and embodiments. Specific embodiments are illustrated and described in detail in the drawings. However, this is not intended to limit the present invention to specific embodiments, but rather to encompass all modifications, equivalents, and alternatives falling within the spirit and technical scope of the present invention. Throughout the description of each drawing, similar reference numerals have been used to designate similar components.

[0031] Terms such as first, second, A, and B may be used to describe various components, but these components should not be limited by these terms. These terms are used solely to distinguish one component from another. For example, without departing from the scope of the present invention, a first component may be referred to as a second component, and similarly, a second component may also be referred to as a first component. The term "and / or" includes a combination of multiple related items described herein or any of multiple related items described herein.

[0032] When a component is referred to as being "connected" or "connected" to another component, it should be understood that it may be directly connected or connected to that other component, but that there may be other components intervening. Conversely, when a component is referred to as being "directly connected" or "connected" to another component, it should be understood that there are no other components intervening.

[0033] The terminology used in this application is solely for the purpose of describing specific embodiments and is not intended to limit the present invention. Singular expressions include plural expressions unless the context clearly dictates otherwise. It should be understood that terms such as "comprise" or "have" in this application do not preclude the presence or possibility of addition of features, numbers, steps, operations, components, parts, or combinations thereof described in the specification.

[0034] Unless otherwise defined, all terms used herein, including technical or scientific terms, have the same meaning as commonly understood by one of ordinary skill in the art to which the present invention belongs.

[0035] Terms defined in commonly used dictionaries should be interpreted to have a meaning consistent with their meaning in the context of the relevant technology, and will not be interpreted in an idealized or overly formal sense unless expressly defined in this application.

[0036] In addition, each configuration, process, procedure or method included in each embodiment of the present invention may be shared within a scope that is not technically inconsistent with each other.

[0037]

[0038] The present invention simulates the performance of urban air traffic (UAM) and personal air vehicles (PAV) in conjunction with a Hardware In the Loop Simulation (HILS) model, and can evaluate and analyze the performance of aircraft components in real time by combining actual hardware and simulation.

[0039] FIG. 1 is a block diagram illustrating a computing device for simulating aircraft performance in urban environment traffic according to one embodiment of the present invention.

[0040] A system (1) for simulating aircraft performance in urban environment traffic can be implemented as a portable terminal (hereinafter referred to as a user terminal) or a computing device (3) that can access a communication network such as the Internet. Here, the computing device includes, for example, a notebook, desktop, laptop, tablet PC, slate PC, etc. equipped with a web browser, and the user terminal can be implemented as, for example, any type of handheld-based wireless communication device such as a smart phone, etc., as a wireless communication device that guarantees portability and mobility.

[0041] Referring to FIG. 1, the computing device (3) may include a communication interface (11) for receiving various data such as a model for simulating aircraft performance or parameters for determining physical or aerodynamic characteristics from an external server (2), a memory (12) for storing the received data and model, an input unit (13) for receiving various input data such as flight conditions or simulation conditions, a processor (10) for controlling the overall system, and an output unit (14) for outputting simulation results performed by the processor (10). However, since FIG. 1 is only an example, the computing device (3) may include other components for implementing a computing environment. In addition, only some of the components disclosed above may be included in the computing device (3).

[0042] Specifically, the communication interface (11) may include one or more components that enable communication with an external communication network, and may include, for example, at least one of a short-range communication module, a wired communication module, and a wireless communication module.

[0043] The short-range communication module may include various short-range communication modules that transmit and receive signals using a wireless communication network at a short distance, such as a Bluetooth module, an infrared communication module, an RFID (Radio Frequency Identification) communication module, a WLAN (Wireless Local Access Network) communication module, an NFC communication module, and a Zigbee communication module.

[0044] The wired communication module may include various wired communication modules such as a Local Area Network (LAN) module, a Wide Area Network (WAN) module, or a Value Added Network (VAN) module, as well as various cable communication modules such as a Universal Serial Bus (USB), a High Definition Multimedia Interface (HDMI), a Digital Visual Interface (DVI), RS-232 (recommended standard 232), power line communication, or plain old telephone service (POTS).

[0045] The wireless communication module may include a wireless communication module that supports various wireless communication methods such as a WiFi module, a Wireless Broadband module, GSM (global System for Mobile Communication), CDMA (Code Division Multiple Access), WCDMA (Wideband Code Division Multiple Access), UMTS (universal mobile telecommunications system), TDMA (Time Division Multiple Access), and LTE (Long Term Evolution), in addition to the Wi-Fi module and the WiBro module.

[0046] The memory (12) can store a model required to implement the disclosed urban environment traffic aircraft performance simulation method, an algorithm required for the operation of the processor (10), or a program for implementing the algorithm. To this end, the memory (12) can be implemented as at least one of a non-volatile memory element such as a cache, a ROM (Read Only Memory), a PROM (Programmable ROM), an EPROM (Erasable Programmable ROM), an EEPROM (Electrically Erasable Programmable ROM), and a flash memory, a volatile memory element such as a RAM (Random Access Memory), or a storage medium such as a hard disk drive (HDD) or a CD-ROM, but is not limited thereto.

[0047] The input unit (13) can receive various input commands. Specifically, the input unit (13) may include a microphone that receives voices spoken in an image including text as subtitles in addition to receiving input text. In addition, the input unit (13) may include hardware devices such as various buttons, switches, pedals, keyboards, mice, trackballs, various levers, handles, or sticks for receiving execution commands required for the operation of the processor (10). In addition, the input unit (13) may include a GUI (Graphical User Interface), i.e., a software device, such as a touch pad, for user input commands. The touch pad may be implemented as a touch screen panel (TSP) and may form a mutual layer structure with the display of the output unit (14).

[0048] The output unit (14) may include, in addition to a speaker that outputs auditory sounds generated during the simulation, a display that outputs simulation results of a model for simulating aircraft performance or evaluation results of aircraft performance. The display may be provided as a cathode ray tube (CRT), a digital light processing (DLP) panel, a plasma display panel, a liquid crystal display (LCD) panel, an electroluminescence (EL) panel, an electrophoretic display (EPD) panel, an electrochromic display (ECD) panel, a light emitting diode (LED) panel, or an organic light emitting diode (OLED) panel, but is not limited thereto.

[0049] The processor (10) can provide a series of manufacturing functions necessary to evaluate the flight of an aircraft or the performance of each component by using at least one model for simulating the performance of an aircraft stored in the memory (12), and, in conjunction with the HILS model, can provide an automated process for evaluating and analyzing the performance of components in real time by combining actual hardware and simulation.

[0050] Meanwhile, the processor (10) may refer to a data processing device built into hardware that has a physically structured circuit to perform a function expressed by a code or command included in a program. As an example of a data processing device built into hardware, it may include processing devices such as a microprocessor, a central processing unit (CPU), a processor core, a multiprocessor, an application-specific integrated circuit (ASIC), a field programmable gate array (FPGA), a graphics processing unit (GPU), and a neural processing unit (NPU), but is not limited thereto. The processor (10) may be provided in multiple units. Since the type of the processor (10) described above is only one example, the type of the processor (10) may be configured in various ways within a range understandable to those skilled in the art based on the contents of the present invention.

[0051] The hardware configurations provided in the computing device (3) can send and receive data and signals through Network Termination (NT) of a digital network such as ISDN (Integrated Services Digital Network).

[0052] FIG. 2 is a diagram illustrating the configuration of an aircraft performance simulation system for urban environment traffic according to one embodiment of the present invention.

[0053] Referring to FIG. 2, the system (1) includes, but is not limited to, a dynamic modeling module (110), an aircraft motion model verification module (120), an air traffic control and performance monitoring module (130), and a main control module (140).

[0054] The dynamic modeling module (110) simulates the flight motion of an aircraft based on virtual flight conditions preset via a user interface. The virtual flight conditions may include climate conditions (temperature, wind speed, air density), environmental variables including terrain information, flight paths including route settings between departure and destination, takeoff and landing scenarios, and emergency situations including event scenarios for simulating the aircraft's response to specific failures or emergency situations.

[0055] The aircraft motion model verification module (120) provides a control environment for reflecting the pilot's input data for the aircraft, and monitors the motion data of the aircraft flying based on the operation scenario in real time. This aircraft motion model verification module (120) can collect the motion data of the aircraft in conjunction with the Hardware-In-the-Loop-Simulation (HILS) model, and monitor the dynamic response of the aircraft in real time by comparing it with the simulation data. Here, the operation scenario can be set by reflecting various virtual flight conditions set by the user or the pilot's input data.

[0056] The flight control and performance monitoring module (130) controls the flight path of an aircraft in real time, collects and analyzes flight data, and monitors the flight performance of the aircraft based on the analyzed data.

[0057] The main control module (140) controls each module in conjunction to comprehensively evaluate the performance of the aircraft and provides the evaluated results to the user. Accordingly, the user can check the results of simulating the attitude changes of the aircraft in urban traffic, such as UAM / PAV, and the performance changes according to climate environments such as high or low temperatures, and can analyze the complex interactions within the system and problems that may arise during the operation of the aircraft in real time compared to data that can be obtained through offline simulation of the UAM / PAV.

[0058] The results provided by the main control module (140) may include performance evaluation results that can evaluate the stability, responsiveness, or efficiency of the aircraft in a specific operating scenario, comparative analysis results that can verify the accuracy of the simulation by comparing it with actual flight data or expected performance, and anomaly detection results that can detect unexpected abnormal phenomena (e.g., EFDJ, vibration, excessive acceleration, etc.) in the simulation results.

[0059] To this end, the main control module (140) can use a time-varying variable comparison method that compares simulation results and experimental data over time, and an error analysis method that evaluates the accuracy of the model by analyzing the error between the simulation results and actual data.

[0060] The user can use the result values ​​provided from the main control module (140) to determine the performance evaluation criteria for evaluating the simulation results according to the set performance criteria, determine the need for improvement to determine whether the design or control algorithm of the aircraft needs improvement based on the result values, and ultimately use the simulation results to make decisions for determining the design and operation strategy of the aircraft.

[0061] The modules described above are merely examples for illustrating the present invention, and are not limited thereto and may be implemented in various variations. Furthermore, the modules described above are stored in memory as computer-readable recording media that can be controlled by a processor (10). Furthermore, at least some of the modules described above may be implemented as software, firmware, hardware, or a combination of at least two or more thereof, and may include modules, programs, routines, instruction sets, or processes for performing one or more functions.

[0062] Figure 3 is a block diagram illustrating the configuration of a dynamic modeling module according to one embodiment of the present invention.

[0063] Referring to FIG. 3, the dynamic modeling module (110) includes, but is not limited to, an input parameter acquisition unit (111), a modeling engine unit (112), and an interface unit (113).

[0064] The input parameter acquisition unit (111) can acquire input parameters including specifications of the aircraft including mass, size, moment of inertia of the aircraft, aerodynamic characteristics such as lift or drag, structural characteristics, and kinematic characteristics.

[0065] Here, the specifications of the aircraft include the mass, size (length, width, height), center of gravity (CG), and moment of inertia of the aircraft; the aerodynamic characteristics include aerodynamic coefficients such as lift, drag, and coefficient of moment; the structural characteristics include the material properties (strength, elasticity, etc.) and the arrangement data of structural components (wings, tail, fuselage, etc.); and the kinematic characteristics may include the maximum speed, acceleration, angular velocity, and flight path of the aircraft. These input parameters are essential elements for accurate flight simulation during the modeling process, and in particular, the mass and moment of inertia are very essential elements for accurately simulating the motion response of the aircraft.

[0066] The modeling engine unit (112) can simulate the flight dynamics of an aircraft using a motion modeling platform for modeling three or more degrees of freedom (DOF) aircraft motion based on MATLAB. The modeling engine unit (112) can accurately model the motion performance of an aircraft using MATLAB's six degrees-of-freedom (6DoF) motion modeling platform based on the physical and aerodynamic characteristics of the aircraft.

[0067] Specifically, the modeling engine unit (112) can calculate the 6DOF motion equation in MATLAB based on the acquired input parameters and simulate the position, velocity, acceleration, etc. of the aircraft.

[0068] The 6DoF motion equations can be expressed as mathematical equations 1 and 2 below by separating them into linear motion and rotational motion.

[0069]

[0070] The above mathematical expression 1 is a linear motion equation, where F represents the external force vector (N), m represents the mass of the gas (Kg), and a represents the acceleration vector (m / s²).

[0071]

[0072] The above mathematical expression 2 is a rotational motion equation, where T represents an external moment vector (Nm), I represents an inertia moment matrix (kg·m²), ω represents an angular velocity vector (rad / s), and ω˙ represents an angular acceleration vector (rad / s²).

[0073] To transform the position and orientation of an aircraft from the Earth-Fixed Equation (ECEF) to the body axis coordinate system, a translation matrix such as the following mathematical equation 3 is used.

[0074]

[0075] In mathematical expression 3, φ represents the roll angle (rad), θ represents the pitch angle (rad), and ψ represents the yaw angle (rad).

[0076] The interface unit (113) can set various virtual flight conditions for the flight motion of an aircraft through a user interface (UI) and visualize the simulation results by the modeling engine unit (112) in real time. At this time, the interface unit (113) can visualize the simulation results as a 3D model and generate and provide a dynamic data log.

[0077] The dynamic modeling module (110) performs three-dimensional object modeling of an aircraft using input parameters. At this time, as a modeling method, a 3D airframe model of the aircraft can be designed using CAD (Computer-Aided Design) software. CAD software such as SolidWorks, CATIA, or Autodesk can be used. The dynamic modeling module (110) converts the three-dimensional airframe model into a mesh form, which is the basic unit of calculation used in simulation, and assigns physical properties by applying input parameters such as mass distribution, material properties, and aerodynamic coefficients to the 3D airframe model.

[0078] The 3D airframe model completed in this way is integrated into MATLAB / Simulink or other dynamic simulation tools and used for dynamic modeling and flight simulation in the dynamic modeling module (110).

[0079] The dynamic modeling module (110) can obtain dynamic results including kinematic data, force and moment data, and state variables as a result of simulating the flight motion of an aircraft. At this time, the kinematic data includes information on the position, velocity, acceleration, angular velocity, and flight path of the aircraft, the force and moment data may include lift, drag, lateral force, and pitch / roll / yaw moments acting on the aircraft, and the state variables may include the roll, pitch, and yaw angles of the aircraft and their change rates over time.

[0080] This dynamic modeling module (110) can evaluate the flight stability, responsiveness and efficiency of an aircraft.

[0081] FIG. 4 is a block diagram illustrating the configuration of an aircraft motion model verification module according to one embodiment of the present invention.

[0082] Referring to FIG. 4, the aircraft motion model verification module (120) is intended to simulate various situations that may occur during the flight of an actual aircraft and to accurately evaluate the performance of aircraft parts, and includes, but is not limited to, a control environment provision unit (121), a data processing unit (122), and a feedback reflection unit (123).

[0083] The control environment provision unit (121) reproduces the control environment of an actual UAM / PAV and can provide a manned control environment or an unmanned control environment, such as a one-person or two-person cockpit structure, control stick, and display.

[0084] The pilot environment provision unit (121) can provide the pilot's input data as in the following mathematical expression 4.

[0085]

[0086] In mathematical expression 4, u roll , u pitch , u yaw are input signals for roll, pitch, and yaw, each controlled by the joystick.

[0087] The data processing unit (122) collects the motion data of the aircraft in real time in conjunction with the HILS model, and compares it with the simulation data of the dynamic modeling module (110), thereby verifying the performance of aircraft parts in real time according to the operating scenario. The data processing unit (122) monitors the status of the aircraft (position, speed, angular velocity, etc.) in real time, and can provide immediate feedback to the pilot through the feedback reflection unit (123).

[0088] The HILS model interacts in real time with the operator's input data and follows the communication model as shown in Equations 5 and 6, where H represents the system response function.

[0089]

[0090]

[0091] In mathematical expression 5, e(t) represents the error vector, r(t) represents the target value, and y(t) represents the actual system output, respectively. In mathematical expression 6, H represents the system response function.

[0092] The feedback reflection unit (123) reflects the pilot's input data in real time in the simulation by linking it with the HILS model, provides real-time feedback, and monitors the dynamic response of the aircraft in real time.

[0093] FIG. 5 is a block diagram illustrating the configuration of an air traffic control and performance monitoring module according to one embodiment of the present invention.

[0094] Referring to FIG. 5, the air traffic control and performance monitoring module (130) includes, but is not limited to, an air traffic control unit (131), a performance monitoring unit (132), and a communication interface unit (133).

[0095] The air traffic control unit (131) can perform functions such as setting a flight path, tracking a flight trajectory, managing a flight history, and evaluating flight performance. The air traffic control unit (131) can optimize a flight path using the following mathematical expression 7.

[0096]

[0097] In mathematical expression 7, J represents the cost function and L represents the optimization problem analysis equation.

[0098] The air traffic control unit (131) can track the flight trajectory using the following mathematical equation 8, where f represents the state change equation of the system.

[0099]

[0100] The performance monitoring unit (132) collects and analyzes real-time flight data for an aircraft in flight based on an operation scenario, evaluates the performance of the aircraft as shown in the following mathematical expression 9, and can automatically generate a test report.

[0101]

[0102] In mathematical expression 9, P is a performance indicator that evaluates performance by comparing actual results with expected results.

[0103] The communication interface unit (133) processes data exchange with the air traffic control unit (131) or the performance monitoring unit (132) in real time. In addition, the communication interface unit (133) enables the air traffic control and performance monitoring module (130) to communicate data with the dynamic modeling module (110) or the aircraft motion model verification module (120).

[0104] The air traffic control and performance monitoring module (130) can perform real-time communication using the communication interface unit (133) to share status information of the aircraft with other modules and support integrated performance evaluation of the entire system.

[0105] FIG. 6 is a flowchart illustrating a method for simulating aircraft performance in urban environment traffic according to one embodiment of the present invention.

[0106] Referring to FIG. 6, the computing device (3) simulates the flight motion of an aircraft using a dynamic modeling module (110) to obtain dynamic results (S10). The dynamic modeling module (110) can accurately model the motion state of the aircraft using MATLAB's 6DoF motion modeling platform based on the physical and aerodynamic characteristics of the aircraft. At this time, the dynamic modeling module (110) can set various virtual flight conditions through a user interface and provide the simulation results in real-time visualization to the user.

[0107] The aircraft motion model verification module (120) provides an actual control environment and verifies the performance of the aircraft in flight in real time based on an operating scenario that reflects the pilot's input data (S20). At this time, the aircraft motion model verification module (120) can immediately reflect the pilot's input data into the aircraft flight simulation by linking with the HILS model and monitor the aircraft's dynamic response in real time.

[0108] The air traffic control and performance monitoring module (130) can control the flight path of an aircraft in real time, monitor flight performance, manage flight history, and automatically generate a flight performance report by evaluating flight performance (S30). In addition, the air traffic control and performance monitoring module (130) can share aircraft status information with other modules through real-time communication, thereby supporting the main control module (140) to conduct an integrated performance evaluation of the entire system.

[0109] The main control module (140) controls each module in conjunction to comprehensively evaluate the performance of the aircraft and provide the evaluated result to the user (S40).

[0110] In this way, the present invention enables simulation of aircraft for urban environmental transportation in various environments, thereby saving time and cost, and not only enables accurate evaluation of the performance of UAM / PAV components through provision of accurate data, but also enables verification of operability and performance during manned control, thereby enabling reliable performance evaluation of UAM / PAV.

[0111] Although FIG. 6 describes each process as being executed sequentially, this is merely an illustrative description of the technical idea of ​​one embodiment of the present invention. In other words, a person of ordinary skill in the art to which one embodiment of the present invention pertains can modify and apply various modifications and variations, such as changing the order described in each drawing and executing the process, or executing one or more of the processes in parallel, without departing from the essential characteristics of one embodiment of the present invention. Therefore, FIG. 6 is not limited to a chronological order.

[0112] Meanwhile, the processes illustrated in FIG. 6 can be implemented as computer-readable code on a computer-readable recording medium. A computer-readable recording medium includes all types of recording devices that store data that can be read by a computer system. That is, a computer-readable recording medium includes storage media such as magnetic storage media (e.g., ROM, floppy disks, hard disks, etc.) and optical readable media (e.g., CD-ROMs, DVDs, etc.). In addition, a computer-readable recording medium can be distributed across network-connected computer systems, so that the computer-readable code can be stored and executed in a distributed manner.

[0113] The above description is merely an example of the technical idea of ​​the present embodiment, and those skilled in the art will appreciate that various modifications and variations can be made without departing from the essential characteristics of the present embodiment. Therefore, the present embodiments are not intended to limit the technical idea of ​​the present embodiment, but rather to explain it, and the scope of the technical idea of ​​the present embodiment is not limited by these embodiments. The scope of protection of the present embodiment should be interpreted by the claims below, and all technical ideas within a scope equivalent thereto should be interpreted as being included in the scope of rights of the present embodiment.

[0114]

[0115] CROSS-REFERENCE TO RELATED APPLICATION

[0116] This patent application claims priority under 35 USC § 119(a) of U.S. Patent Application No. 10-2024-0115992, filed in Korea on August 28, 2024, the entire contents of which are incorporated by reference herein. Furthermore, this patent application claims priority in countries other than the United States for the same reasons, the entire contents of which are incorporated by reference herein.

Claims

1. A dynamic modeling module that simulates the flight motion of an aircraft based on virtual flight conditions set through a user interface; An aircraft motion model verification module that provides a control environment for reflecting a pilot's input data for the aircraft, and monitors in real time the motion data of the aircraft flying based on an operation scenario set by the control environment or virtual flight conditions; An aviation control and performance monitoring module that collects and analyzes flight data by controlling the flight path of an aircraft flying based on the above operation scenario in real time, and monitors the performance of the aircraft based on the analyzed data; and A main control module that controls each module in conjunction to comprehensively evaluate the performance of the aircraft and provide the evaluated results to the user; An aircraft performance simulation system for urban environment transportation, characterized by including:

2. In paragraph 1, The above aircraft motion model verification module is, An urban environment traffic aircraft performance simulation system characterized by collecting the motion data of the aircraft in conjunction with a HILS (Hardware-In-the-Loop-Simulation) model and monitoring the dynamic response of the aircraft in real time by comparing it with the simulation data.

3. In paragraph 1, The above main control module, An urban environment traffic aircraft performance simulation system characterized in that it provides a result value including at least one of a performance evaluation result for evaluating the stability, responsiveness or efficiency of an aircraft flown based on the above operation scenario, a comparative analysis result for verifying the accuracy of the simulation by comparing it with actual flight data or expected performance, and an anomaly detection result for detecting anomalies in the simulation results.

4. In paragraph 1, The above dynamic modeling module, An input parameter acquisition unit that acquires input parameters including specifications, aerodynamic characteristics, structural characteristics, and kinematic characteristics of the aircraft required for object modeling of the aircraft; A modeling engine unit that simulates the flight dynamics of the aircraft using a motion modeling platform that models motions of three or more degrees of freedom for the aircraft based on the input parameters; and An interface section that sets virtual flight conditions for the flight motion of an aircraft through a user interface and visualizes the simulation results by the modeling engine section; An aircraft performance simulation system for urban environment transportation, characterized by including:

5. In paragraph 4, The specifications of the aircraft include the mass, size, center of gravity, and moment of inertia of the aircraft, The above aerodynamic characteristics include aerodynamic coefficients including lift, drag, and coefficient of moment. The above structural characteristics include the material properties and the arrangement data of the structural components, An urban environment traffic aircraft performance simulation system, wherein the above kinematic characteristics include the maximum speed, acceleration, angular velocity, and flight path of the aircraft.

6. In paragraph 1, The above aircraft motion model verification module is, A control environment providing unit that provides a control environment for controlling the above aircraft; A data processing unit that collects motion data of an aircraft flying according to the above operation scenario and compares the collected motion data of the aircraft with simulation data to verify the performance of aircraft parts; A feedback reflection unit that reflects the pilot's input data obtained through the above pilot environment provision unit in real time into the simulation and provides feedback on the pilot's input data; An aircraft performance simulation system for urban environment transportation, characterized by including:

7. In paragraph 6, The above data processing unit, An urban environment traffic aircraft performance simulation system characterized by real-time monitoring of aircraft status information, including aircraft position, speed, or angular velocity, in conjunction with a HILS (Hardware-In-the-Loop-Simulation) model.

8. In paragraph 1, The above air traffic control and performance monitoring module, An air traffic control unit that performs functions such as setting a flight path, tracking a flight trajectory, managing a flight history, or evaluating flight performance for the above aircraft; A performance monitoring unit that collects and analyzes real-time flight data for an aircraft in flight based on the above operation scenario and evaluates the performance of the aircraft; and A communication interface unit that processes data exchange with the above-mentioned air traffic control unit or performance monitoring unit in real time and performs data communication to share aircraft status information with other modules; An aircraft performance simulation system for urban environment transportation characterized by .

9. In paragraph 8, The above performance monitoring unit, An urban environment traffic aircraft performance simulation system characterized by evaluating the performance of the aircraft and generating a test report.

10. A method for simulating the performance of an aircraft in an urban environment, performed by a computing device including at least one processor, A dynamic modeling process that simulates the flight motion of an aircraft based on virtual flight conditions set through a user interface; An aircraft motion model verification process that provides a control environment for reflecting the pilot's input data for the aircraft, and monitors in real time the motion data of the aircraft flying based on an operation scenario set by the control environment or virtual flight conditions; An air traffic control and performance monitoring process that collects and analyzes flight data by controlling the flight path of the aircraft in real time and monitors the flight performance of the aircraft based on the analyzed data; and A main control process that integrates and evaluates the performance of the aircraft by controlling each module and provides the evaluated results to the user; A method characterized by comprising:

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