Ground simulation flight test technology for aircraft maneuverable and variable trajectory

Abstract

The application provides a kind of aircraft maneuvering variable trajectory ground simulation flight test technology, belongs to the technical field of aircraft ground simulation field.The application includes ground simulation system and digital twin system;Ground simulation system mainly includes six degrees of freedom platform and electric control subsystem;Digital twin system mainly includes modeling and simulation subsystem and data management subsystem.The application is based on ground simulation flight test, gives full play to the advantages of modeling and simulation and digital twin, and strengthens the mutual integration of the above two technologies, including aircraft geometric modeling, flow field numerical simulation and flight simulation in modeling and simulation means provides a basis for ground simulation test, ground simulation test provides a more close to real working condition Semi-physical simulation environment for aircraft.

Description

Technical Field

[0001] The present invention relates to a ground simulation flight test technology for an aircraft with maneuverable and variable trajectory, and belongs to the technical field of aircraft ground simulation. Background Art

[0002] Ground testing is a crucial step in the entire aircraft lifecycle, from design and manufacturing to flight testing and application. This is particularly true for highly maneuverable aircraft operating in complex and ever-changing environments, particularly when undertaking variable trajectory missions. To ensure flight safety and stable control, testing technologies, including flight testing, ground testing, and modeling and simulation, are crucial to aircraft development and evaluation.

[0003] The patent "A simulation test platform and control method for hypersonic aircraft assessment" (patent, Harbin Institute of Technology, CN104182272B, 20170412) proposes a simulation test platform and control method for hypersonic aircraft assessment, which can compare the advantages and disadvantages of hypersonic aircraft control methods.

[0004] The paper "A Flight Simulation Vision for Aeropropulsion Altitude Ground Test Facilities" (A Flight Simulation Vision for Aeropropulsion Altitude Ground Test Facilities[J].Journal of Engineering for Gas Turbines and Power,2005,127(1):21-31.) proposes a ground test method for aircraft and their engines. The test simulates flight conditions such as air pressure and incoming airflow, providing a ground characterization platform for quantifying engine performance.

[0005] The paper "Ground-Based Simulation of Complex Maneuvers of a Delta-Wing Aircraft" (Rein M, Hoehler G, Bergmann A, et al. Ground-Based Simulation of Complex Maneuvers of a Delta-Wing Aircraft [J]. Journal of Aircraft, 2008, 45 (1): 286-291.) proposed a ground simulation scheme for the complex maneuvers of the X-31 aircraft model in a low-speed wind tunnel, which can realize the six-freedom motion simulation of the aircraft.

[0006] The patent "A Simulation Test Platform and Control Method for Hypersonic Aircraft Assessment" (Harbin Institute of Technology, CN104182272B, 20170412) proposes a simulation test platform and control method for hypersonic aircraft assessment, capable of comparing the advantages and disadvantages of hypersonic aircraft control methods. However, as a software assessment and verification platform for control algorithms, it only covers simulation verification of known aircraft dynamic models, kinematic models, and related aerodynamic parameters, making it less useful for aircraft application testing.

[0007] The paper "A Flight Simulation Vision for Aeropropulsion Altitude Ground Test Facilities" (A Flight Simulation Vision for Aeropropulsion Altitude Ground Test Facilities [J]. Journal of Engineering for Gas Turbines and Power, 2005, 127(1): 21-31.) proposes a ground test method for aircraft and their engines. This test simulates flight conditions such as air pressure and incoming airflow, providing a ground characterization platform for quantifying engine performance. However, it focuses on engine-centric simulation verification and does not provide a detailed solution for ground simulation technology for aircraft with maneuverable and variable trajectory characteristics.

[0008] The paper "Ground-Based Simulation of Complex Maneuvers of a Delta-Wing Aircraft" (Rein M, Hoehler G, Bergmann A, et al. Ground-Based Simulation of Complex Maneuvers of a Delta-Wing Aircraft [J]. Journal of Aircraft, 2008, 45(1): 286-291.) proposed a ground simulation scheme for the complex maneuvers of an X-31 aircraft model in a low-speed wind tunnel, which can simulate the six-freedom motion of the aircraft. However, due to its specific research object, it is not general and does not provide a supplementary verification system based on modeling and simulation, which will lead to a large number of tests and test costs.

[0009] Compared with the aircraft maneuverable variable trajectory ground simulation flight test technology of the present application, the existing technology can only perform single modeling simulation, or perform numerous and time-consuming simulation tests.

[0010] Based on this, this patent proposes a ground-based simulated flight test technology for maneuverable and variable trajectory aircraft. This ground-based simulated flight test technology takes both ground simulation and digital twins as its foundation, employing a technical solution that combines the advantages of modeling and simulation with those of digital twins. This technology can achieve both simulation verification based on control theory and aircraft model levels, and semi-physical simulation tests that are closer to real-world operating conditions, providing a research and verification platform for simulated flight tests of maneuverable and variable trajectory aircraft. Summary of the Invention

[0011] The purpose of the present invention is to solve the problems existing in the above-mentioned prior art and to provide a ground simulation flight test technology for aircraft maneuverable variable trajectory.

[0012] The purpose of the present invention is achieved through the following technical solutions:

[0013] A ground simulation flight test device for aircraft maneuverable variable trajectory, comprising: a ground simulation system and a digital twin system;

[0014] The ground simulation system mainly includes a six-degree-of-freedom platform and an electronic control subsystem;

[0015] The six-degree-of-freedom platform includes: a parallel navigation system, an aircraft, a linkage platform, and a bracket containing a driver; the bracket containing the driver is installed on the parallel navigation system, the linkage platform is connected to the bracket containing the driver, the aircraft is installed on the linkage platform, and the connection between the linkage platform and the aircraft is the location of the center of gravity of the aircraft.

[0016] The electronic control subsystem includes a six-degree-of-freedom platform industrial computer, a dynamics industrial computer, a GNC computer, and a data image output unit. The GNC computer and the dynamics industrial computer are used to simulate common onboard equipment of aircraft. The six-degree-of-freedom platform industrial computer controls the six-degree-of-freedom platform in the ground simulation system. The data image output unit transmits information from the electronic control subsystem to the digital twin system.

[0017] The digital twin system mainly includes a modeling and simulation subsystem and a data management subsystem;

[0018] The modeling simulation subsystem mainly comprises a guidance and control algorithm module, a control-oriented modeling module and a six-degree-of-freedom high-fidelity model module; the guidance and control algorithm module designs guidance and control instructions as input according to a reference trajectory instruction, enters the six-degree-of-freedom high-fidelity model module, the control-oriented modeling module is a nominal model of the vehicle system, the six-degree-of-freedom high-fidelity model is iteratively updated by using the control-oriented modeling module, and then state feedback is fed back to the guidance and control algorithm module; necessary information obtained by the modeling simulation subsystem is transmitted to the data management subsystem under the influence of external disturbance torque;

[0019] The data management subsystem mainly comprises a function model, a model update, a reliability analysis, a state prediction, a historical record sub-module and a twin database unit; wherein, the function model, the model update, the reliability analysis, the state prediction, the historical record sub-module and the twin database unit are in a data update storage and driving relationship.

[0020] Preferably, the GNC computer calculates the guidance instruction by using the current six-degree-of-freedom position / attitude information and the expected position / attitude information, and then transmits the guidance instruction to the dynamics industrial computer to realize the control of the vehicle; further, the guidance / control instruction is transmitted to the six-degree-of-freedom platform industrial computer, and the six-degree-of-freedom platform is used to realize the control simulation of the vehicle.

[0021] The beneficial effects of the present application are:

[0022] The purpose of the present application is to provide a specific scheme of the current vehicle maneuvering variable trajectory ground simulation flight test. With the development of modeling simulation and ground test technology, the proportion of the traditional vehicle test mode "test-improvement-test" gradually decreases, so as to achieve the effect of reducing the number of flight tests, reducing the cost and shortening the time. The essence of the present application is to take the ground simulation flight test as the basis, fully exert the advantages of modeling simulation and digital twinning, and strengthen the mutual integration of the two technologies. Among them, the modeling simulation means including vehicle geometric modeling, flow field numerical simulation and flight simulation provide the basis for ground simulation test, and the ground simulation test provides a semi-physical simulation environment closer to the real working condition for the vehicle.

[0023] Digital twin technology, as the link between the physical and virtual worlds, offers the ability to represent aircraft in digital twin libraries with high precision, real-time performance, and high integration, thereby facilitating in-depth aircraft research. With the continuous advancement of technology, aircraft structures and systems are becoming increasingly complex, as are the coupling between these systems. This complicates comprehensive experiments and makes it difficult to establish a satisfactory test environment. Furthermore, conducting experiments requires extreme conditions, which, combined with multiple extreme conditions, can be highly risky and costly at a test site. Therefore, a digital twin library is designed to accommodate these requirements and avoid these issues. It also enables rapid adjustment of test conditions, prompt generation of test results, and correction of aircraft status. Aircraft design verification requires a variety of tests, including feasibility testing of individual systems, system integration testing, and airworthiness testing. These tests typically require the use of models or actual aircraft. However, existing testing models based on physical requirements present several challenges. First, because testing relies on physical objects, problems encountered during testing cannot be quickly fed back and corrected, requiring significant time and resources to correct errors during the design phase. Second, simulation testing is limited by conditions and struggles to capture the full range of conditions that may occur during flight. Finally, as the complexity of system coupling increases, comprehensive testing becomes increasingly difficult, and some tests may even be highly risky. Applying digital twin technology, based on technical requirements, the overall design framework, and detailed design elements, a high-precision, multi-system, and highly complex aircraft database is constructed using data twins for testing. Compared to the traditional design sample testing process, testing within a data twin database allows for early implementation in the aircraft design phase, enabling a "design, test, and correct" approach. This avoids the time-consuming and costly rework that occurs when testing lags behind design. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 It is a structural schematic diagram of the aircraft maneuverable variable trajectory ground simulation flight test technology of the present invention.

[0025] Figure 2 This is a schematic diagram of the six-degree-of-freedom platform structure for the aircraft maneuverable variable trajectory ground simulation flight test technology of the present invention.

[0026] In the figure, 1 is parallel navigation, 2 is aircraft, 3 is linkage platform, and 4 is bracket with drive. DETAILED DESCRIPTION

[0027] The present invention will be further described in detail below with reference to the accompanying drawings: This embodiment is implemented on the premise of the technical solution of the present invention, and a detailed implementation method is given, but the protection scope of the present invention is not limited to the following embodiment.

[0028] like Figure 1 and Figure 2 As shown, the aircraft maneuverable variable trajectory ground simulation flight test technology involved in this embodiment includes:

[0029] The ground simulation flight test device for aircraft maneuverable variable trajectory consists of a ground simulation system and a digital twin system, such as Figure 1 shown.

[0030] The ground simulation system in the present invention mainly includes a six-degree-of-freedom platform and an electronic control subsystem; wherein the six-degree-of-freedom platform is a mechanism that includes a wind tunnel environment, such as Figure 2 As shown, the six-degree-of-freedom platform includes a parallel navigation system 1, an aircraft 2, a linkage platform 3, and a bracket 4 containing a driver. Bracket 4 containing a driver is mounted on the parallel navigation system 1, and the linkage platform 3 is connected to the bracket 4 containing the driver. The aircraft 2 is mounted on the linkage platform 3, and the connection between the linkage platform 3 and the aircraft 2 is the location of the aircraft's center of gravity. This system enables the parallel aircraft 2 to perform six-degree-of-freedom motion, while meeting the requirements of large-amplitude, high-speed arbitrary motion. It also provides a wind tunnel environment under appropriate operating conditions, enabling ground-based simulation of aircraft maneuvers and variable trajectory missions.

[0031] The electronic control subsystem includes a 6DOF platform industrial computer, a dynamics industrial computer, a GNC computer, and a data and image output unit. These subsystems generate and execute commands to control the 6DOF platform's motion, based on the aircraft's various maneuvering tasks. This control is then transmitted to the digital twin system via the data and image output unit.

[0032] The GNC computer and the dynamics industrial computer are used to simulate common onboard aircraft equipment, while the 6DOF platform industrial computer controls the 6DOF platform in the ground simulation system. The GNC computer and the dynamics industrial computer simulate common onboard aircraft equipment, providing navigation, guidance, and control commands to the aircraft. The 6DOF platform industrial computer controls the 6DOF platform in the ground simulation system, acting as the actual control system for the aircraft's ground motion simulation. More specifically, the GNC computer calculates guidance commands using current and desired 6DOF position / attitude information. These commands are then transmitted to the dynamics industrial computer to control the aircraft. Furthermore, these guidance / control commands are transmitted to the 6DOF platform industrial computer, enabling the 6DOF platform to simulate aircraft control. The data image output unit transmits information from the electronic control subsystem to the digital twin system, enabling real-time feedback and iterative model updates.

[0033] The digital twin technology can collect the data obtained by the aircraft during flight, and construct the situation of the real environment according to the data, so that the constructed environment can be used for designing and verifying new aircraft for testing. Compared with the relatively single environment provided by the test site, the digital twin library has more diversity, can more accurately simulate various flight conditions in the flight envelope, especially those flight conditions that cannot be realized in the relatively stable climate conditions of the test site. The more complex the test is, the more reliable the test results will be, so that the aircraft can exhibit higher mission execution capability and safe flight capability during operation. When designing a new aircraft, the flight data of the previous aircraft can be used to simulate the test of the new digital twin, so as to reduce the test cost. In addition, tests can be carried out on the digital twins of new and old aircrafts at the same time, so that comparative conclusions can be easily drawn, and the development of new aircrafts can be promoted.

[0034] The digital twin system in the application mainly comprises a modeling simulation subsystem and a data management subsystem.

[0035] The modeling simulation system mainly comprises a guidance and control algorithm module, a control-oriented modeling module, and a six-degree-of-freedom nonlinear motion model module. The designed guidance and control algorithm module designs guidance and control instructions as inputs according to reference trajectory instructions, enters a six-degree-of-freedom high-fidelity model module (including an aircraft dynamics and kinematics model), then feeds back the state to the guidance and control algorithm module, and transmits simulation information to the data management subsystem. In the application, the guidance and control algorithm output instructions of the modeling simulation system consider the influence of external disturbance torque; the control-oriented modeling module is a nominal model of the aircraft system, which is established on the basis of the basic dynamics equation relationship. Considering that accurate modeling cannot be achieved by using the nominal model, the six-degree-of-freedom high-fidelity model of the adopted maneuverable aircraft can be iteratively updated, so that it is more close to the real aircraft system, and then the state is fed back to the guidance and control algorithm module to realize the compensation and correction of the defects of the simulation model.

[0036] The data management subsystem is another core component of the digital twin system, mainly comprising function modules, model updating, reliability analysis, state prediction, historical record and other submodules (hereinafter referred to as function submodules) and a twin database unit. The function submodules and the twin database unit are in a data updating and storage and driving relationship, and complement each other. Specifically, the twin database provides data support for the function submodules, the function submodules provide driving for the twin database, and the information interaction iteration of the two plays the role of the function submodules.

[0037] Functional model: used to model and analyze the aircraft's control system, environment, sensors, and faults, which helps improve the design and implementation of the test system and enhance the test effect and reliability. 1) Control system model: This component describes the aircraft's control system, including the movement of flight control surfaces (such as elevators, flaps, rudders, etc.), control input and feedback, etc. It simulates the aircraft's control response and control capabilities. 2) Environmental model: This component simulates the environmental conditions in which the aircraft is located, including atmospheric airflow, wind direction and speed, temperature, air pressure, etc. It affects the flight performance and stability of the aircraft. 3) Sensor model: Simulates sensor equipment such as inertial measurement units (IMUs), barometers, gyroscopes, etc., which are used to measure the state variables of the aircraft and input them into the system for data acquisition and feedback. 4) Fault model: Simulates the impact of fault events and faults on the test system. It can help analyze and evaluate the system's response capabilities and fault recovery strategies when a fault occurs.

[0038] Model Update: This is used to update and improve the digital twin model to more accurately reflect the performance and behavior of the actual aircraft. Methods for updating the digital twin model include: 1) Data-Driven Update: This utilizes sensor data and test data from the actual aircraft to continuously update the parameters and state of the digital twin model to maintain consistency with the actual aircraft. Machine learning and data analysis methods can be used to extract valuable information from massive amounts of data to update the model. 2) Ground Simulation Test Update: This involves conducting various tests on a ground simulation platform, such as aerodynamics and structural strength tests, to obtain aircraft performance data and apply it to the digital twin model. This allows for precise adjustment of the model's parameters and behavior to more accurately reflect the aircraft's actual operating conditions. 3) Mathematical Model Improvement: This involves improving and optimizing the mathematical models and algorithms within the digital twin model to more accurately describe the aircraft's physical characteristics and dynamic behavior. For example, improvements to the aerodynamics, control, and sensor models can be made to enhance the model's accuracy and predictive capabilities. 4) Integrating Multidisciplinary Models: The aircraft is a complex system, involving knowledge and models from multiple disciplines. When updating the digital twin model, more multidisciplinary models can be integrated, such as structural models, combustion models, and thermodynamic models, to comprehensively analyze and predict aircraft performance. In summary, the aircraft digital twin model can be updated through data-driven methods, ground simulation tests, mathematical model improvements, and the integration of multidisciplinary models to improve model accuracy and predictive capabilities.

[0039] Reliability Analysis: This is used to evaluate and ensure the reliability and effectiveness of ground simulation tests to simulate the behavior and performance of aircraft in maneuverable, variable-trajectory flight. High-quality data generated during ground simulation tests must be recorded and accurately and comprehensively analyzed. Possible failure modes, consequences, and impacts of ground simulation tests must be analyzed and evaluated to develop appropriate corrective and control measures. Furthermore, ground simulation tests must be verified for repeatability and consistency to ensure consistent results under identical input conditions.

[0040] State Prediction: This system is used to predict and forecast the aircraft's state during maneuverable variable trajectory ground simulation flight tests. A state prediction model is established by combining a high-fidelity six-degree-of-freedom model with historical test data. By analyzing the aircraft's historical operational data, the system learns and discovers the correlation between state, input parameters, and environmental conditions to predict future aircraft states.

[0041] Historical records: They provide data comparison and verification, fault diagnosis, trend prediction, and decision support, improving the reliability, effectiveness, and efficiency of ground-based simulated flight tests of aircraft maneuverable variable trajectory. 1) Historical records can be used for comparison and verification with current test data. By comparing them with previous test records, the accuracy and consistency of current test results can be determined, and the reliability of test equipment and methods can be evaluated. 2) Historical records provide a record of faults and problems encountered in past tests. When similar faults or problems recur, solutions in historical records can be referenced for rapid diagnosis and resolution. 3) The vast amount of data accumulated in historical records can be used for data analysis and trend prediction. By analyzing historical data, potential trends and patterns can be identified, predicting the likely outcomes of future tests and enabling appropriate adjustments and optimizations. 4) Historical records can provide valuable reference for decision-making. By analyzing test results, fault conditions, and parameter changes in historical records, decision-makers can be supported in making decisions regarding test planning, equipment configuration, and resource allocation.

[0042] Considering the complex structure and diverse functions of aircraft systems, especially for aircraft with strong maneuverability and variable trajectory, the test data is of various types and huge in quantity. The data management subsystem in the present invention can achieve the following tasks: first, safe and effective storage of test data, providing necessary information support for digital twins; second, it can display the current aircraft status and environmental status data in real time, strengthen the interoperability and connectivity of test resources, enable different types of test resources to interoperate, and provide support for effective interaction of simulated flight; third, it can dynamically compare with historical data as a powerful basis for modeling and controller correction.

[0043] The ground simulated flight test method for an aircraft maneuverable variable trajectory includes the following steps:

[0044] Step 1: In the modeling and simulation subsystem, a six-degree-of-freedom aircraft nominal model for control is established using kinematic and dynamic equations combined with known aircraft nominal parameters. This model is then transferred as empirical knowledge to the electronic control subsystem and the data management subsystem.

[0045] Step 2: The GNC computer uses the current 6DOF position / attitude information and the desired position / attitude information to calculate guidance instructions, and then transmits the guidance instructions to the dynamics industrial computer to achieve control of the aircraft. The above position / attitude information and guidance instructions are synchronized with the data image output unit and fed back to the digital twin system in real time.

[0046] Step 3: Based on Step 2, the modeling subsystem obtains the current reference trajectory instructions for modeling and simulation verification. Specifically, using the pre-designed guidance and control algorithm, considering the influence of external interference torque, based on the control-oriented 6-DOF aircraft nominal model in Step 1, a high-fidelity 6-DOF model is obtained through iterative optimization. At the same time, the high-fidelity model exchanges information with the data management subsystem and then transmits it to the ground simulation system for online control of the aircraft by the electronic control subsystem.

[0047] Step 4: Based on step 2, the guidance / control instructions are transmitted to the 6DOF platform industrial computer, which controls the 6DOF platform in the ground simulation system to realize the control simulation of the aircraft. The 6DOF platform can move on three rotation axes (roll, pitch, yaw) and three translation axes (front and back, left and right, up and down), simulating all possible movements of the aircraft in the air, thereby simulating the behavior of the aircraft in various flight environments and states. The real-time status information of the 6DOF platform and the guidance / control instruction information of the electronic control subsystem can be interactively utilized in real time. The two will work together to achieve precise control and simulation verification of the aircraft. The above-mentioned aircraft status information and guidance / control instruction information will be synchronized with the data image output unit and fed back to the digital twin system in real time.

[0048] Step 5: Based on the above steps, the digital twin system will collect and store the following information: real-time monitoring data of the aircraft, guidance / control instructions of the electronic control subsystem, simulation data and high-fidelity model parameters of the modeling and simulation subsystem; the data management subsystem will comprehensively process the above information and drive the twin database unit to update data based on the functional sub-module; establish a virtual model of the aircraft with digital twin properties, which is consistent with the control mode and parameters of the real aircraft, and display the working status of the system, forming several major functional modules such as functional model, model update, reliability analysis, status forecast, and historical record; with the support of real-time data, through the combination of virtual and real verification technology, the subsequent tests will be fully verified throughout the whole process and optimized and adjusted; combined with historical records, reliability analysis and model knowledge base, in-depth applications such as test evaluation, health assessment and fault prediction can also be carried out.

[0049] The foregoing are merely preferred embodiments of the present invention. These embodiments are all different implementations based on the overall concept of the present invention. The scope of protection of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be based on the scope of protection of the claims.

Claims

1. A ground-based simulated flight test device for aircraft maneuverable and variable trajectory, characterized in that: include: Ground simulation systems and digital twin systems; The ground simulation system mainly includes a six-degree-of-freedom platform and an electronic control subsystem; The six-degree-of-freedom platform comprises: a parallel navigation (1), an aircraft (2), a linkage platform (3) and a bracket (4) containing a driver; the bracket (4) containing the driver is installed on the parallel navigation (1), the linkage platform (3) is connected to the bracket (4) containing the driver, the aircraft (2) is installed on the linkage platform (3), and the connection point between the linkage platform (3) and the aircraft (2) is the location of the center of gravity of the aircraft; The electronic control subsystem includes a six-degree-of-freedom platform industrial computer, a dynamics industrial computer, a GNC computer, and a data image output unit. The GNC computer and the dynamics industrial computer are used to simulate common onboard equipment of aircraft. The six-degree-of-freedom platform industrial computer controls the six-degree-of-freedom platform in the ground simulation system. The data image output unit transmits information from the electronic control subsystem to the digital twin system. The digital twin system mainly includes a modeling and simulation subsystem and a data management subsystem; The modeling and simulation subsystem mainly includes a guidance and control algorithm module, a control-oriented modeling module, and a six-degree-of-freedom high-fidelity model module. The guidance and control algorithm module designs guidance and control instructions as input based on the reference ballistic instructions, and enters the six-degree-of-freedom high-fidelity model module. The control-oriented modeling module is the nominal model of the aircraft system, which is used to iteratively update the six-degree-of-freedom high-fidelity model. The state is then fed back to the guidance and control algorithm module. Taking into account the influence of external interference torque, the necessary information obtained by the modeling and simulation subsystem is transmitted to the data management subsystem. The data management subsystem mainly includes: functional model, model update, reliability analysis, state forecast, historical record submodules and twin database unit; among them, the functional model, model update, reliability analysis, state forecast, historical record submodules and the twin database unit have a data update storage and drive relationship; The GNC computer calculates guidance instructions using the current six-degree-of-freedom position / attitude information and the desired position / attitude information, and then transmits the guidance instructions to the dynamics industrial computer to achieve control of the aircraft; further, the guidance / control instructions are transmitted to the six-degree-of-freedom platform industrial computer, and the six-degree-of-freedom platform is used to achieve control simulation of the aircraft.

2. A method for ground simulation flight test of aircraft maneuverable variable trajectory implemented by the device of claim 1, characterized in that: The following steps are involved: Step 1: In the modeling and simulation subsystem, a six-degree-of-freedom aircraft nominal model for control is established using kinematic and dynamic equations combined with known aircraft nominal parameters. This model is then transferred as empirical knowledge to the electronic control subsystem and the data management subsystem. Step 2: The GNC computer uses the current 6DOF position / attitude information and the desired position / attitude information to calculate guidance instructions, and then transmits the guidance instructions to the dynamics industrial computer to achieve control of the aircraft. The above position / attitude information and guidance instructions are synchronized with the data image output unit and fed back to the digital twin system in real time. Step 3: Based on Step 2, the modeling subsystem obtains the current reference trajectory instructions for modeling and simulation verification. Specifically, using the pre-designed guidance and control algorithm, considering the influence of external interference torque, based on the control-oriented 6-DOF aircraft nominal model in Step 1, a high-fidelity 6-DOF model is obtained through iterative optimization. At the same time, the high-fidelity model exchanges information with the data management subsystem and then transmits it to the ground simulation system for online control of the aircraft by the electronic control subsystem. Step 4: Based on step 2, the guidance / control instructions are transmitted to the 6DOF platform industrial computer. The 6DOF platform industrial computer controls the 6DOF platform in the ground simulation system to simulate the control of the aircraft. The 6DOF platform can move in three rotational axes, namely roll, pitch, and yaw, and three translational axes, namely front-to-back, left-to-right, and up-to-down, simulating all possible movements of the aircraft in the air, thereby simulating the aircraft's behavior in various flight environments and states. The real-time status information of the 6DOF platform and the guidance / control instruction information of the electronic control subsystem can be interactively utilized in real time, and the two will work together to achieve precise control and simulation verification of the aircraft. The above-mentioned aircraft status information and guidance / control command information will be synchronized with the data image output unit and fed back to the digital twin system in real time; Step 5: Based on the above steps, the digital twin system will collect and store the following information: real-time monitoring data of the aircraft, guidance / control instructions of the electronic control subsystem, simulation data and high-fidelity model parameters of the modeling and simulation subsystem; the data management subsystem will comprehensively process the above information and drive the twin database unit to update data based on the functional sub-module; establish a virtual model of the aircraft with digital twin properties, which is consistent with the control mode and parameters of the real aircraft, and display the working status of the system, forming several major functional modules such as functional model, model update, reliability analysis, status forecast, and historical record; with the support of real-time data, through the combination of virtual and real verification technology, the subsequent tests will be fully verified throughout the whole process and optimized and adjusted; combined with historical records, reliability analysis and model knowledge base, in-depth applications such as test evaluation, health assessment and fault prediction can also be carried out.

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