Flight simulation model for variable-stability flight simulator and modeling method

Abstract

The invention discloses a flight simulation model for a variable stability flight simulator and a modeling method. The flight simulation model comprises an interface control module, a variable pneumatic simulation module, a variable flight control simulation module, a physical characteristic simulation module and a six-degree-of-freedom motion simulation module. The interface control module defines external data needing to be received; the variable pneumatic simulation module establishes a pneumatic derivative interpolation table and a pneumatic coefficient expression according to the non-linear pneumatic data packet, and by reconstructing the pneumatic coefficient expression, influences generated by externally configured pneumatic parameters are used as increments to be superposed into pneumatic coefficients; the physical characteristic simulation module outputs the weight and inertia of the airplane; the six-degree-of-freedom motion simulation module calculates the motion state of the aircraft; the variable flight control simulation module constructs flight control laws under different instruction types, and switches corresponding control laws and control gains in real time according to external configuration. Dual adjustment of aerodynamic parameters and flight control laws in the same flight simulation model is realized.

Description

Technical Field

[0001] The present invention relates to the technical field of flight simulation, and in particular to a flight simulation model and a modeling method for a variable stability flight simulator, which supports adjusting aerodynamic parameters and flight control laws in the model, thereby changing the flight quality characteristics of the simulated aircraft and realizing variable stability flight simulation. Background Art

[0002] A flight simulator is a simulation system that simulates aircraft flight. It is widely used in the design and development of aircraft aerodynamics and flight control systems, as well as training scenarios such as aircraft operating procedures, fault handling and flight quality evaluation.

[0003] However, most flight simulators are designed and developed for specific aircraft types and can only simulate the flight qualities of the corresponding aircraft types. Since different aircraft types have completely different flight stability and handling characteristics, pilots need to use different simulators to train to operate multiple aircraft types. In order to enable pilots to perform different flight stability and handling characteristics training on the same flight simulator, variable stability flight simulators are needed to provide simulations of different flight quality characteristics.

[0004] The flight simulation model is the simulation core of the flight simulator, which can receive the control instructions of the simulator control equipment and solve the flight parameters that drive the simulator to respond. The variable stability function of the variable stability flight simulator is realized by changing the parameters of the flight simulation model. The existing variable stability flight simulation models can be divided into two types. One is to change the aerodynamic parameters and adjust the linear aerodynamic coefficient expression. However, the linear aerodynamic model cannot use the existing nonlinear aerodynamic data package, and only has a good control effect at the aircraft balance point. When the aircraft deviates from the balance point, it is difficult to produce the control response under the expected flight quality; the other is to use the feedback principle to change the flight stability by adjusting the flight control law gain. However, when conducting variable stability flight training, the pilot needs to feel the changes in flight quality caused by different aerodynamic characteristics, and also needs to experience the impact of different flight control laws and control gains on flight performance. Therefore, a flight simulation model that can cover the functions of aerodynamic parameter adjustment and flight control law adjustment is needed. Summary of the invention

[0005] The purpose of the present invention is to provide a flight simulation model and modeling method for a variable stability flight simulator, in which a variable aerodynamic simulation module and a variable flight control simulation module are added to the traditional flight simulation model. The variable aerodynamic simulation module adjusts the aerodynamic parameters on the basis of a nonlinear aerodynamic data package by reconstructing the aerodynamic coefficient expression. The variable flight control simulation module adjusts the flight control law by switching the instruction type and the control gain. The present invention makes full use of the nonlinear aerodynamic data package of the existing aircraft and realizes the function of adjusting different aerodynamic characteristics and different flight control laws in the same flight simulation model. The technical solution of the present invention is as follows.

[0006] A flight simulation model for a variable stability flight simulator, comprising: an interface control module, a variable aerodynamic simulation module, a variable flight control simulation module, a physical property simulation module, and a six-degree-of-freedom motion simulation module; The interface control module interacts with the variable pneumatic simulation module, the variable flight control simulation module, and the six-degree-of-freedom motion simulation module, and is used to receive external initialization data, control instructions, and configuration parameters, and output variable pneumatic identification and configured pneumatic parameters to the variable pneumatic simulation module; output trim rudder deflection, stick rudder control amount, instruction type identification, and configured flight control gain to the variable flight control simulation module; and output trim thrust and initial flight parameters such as initial speed, attitude, and position to the six-degree-of-freedom motion simulation module; The variable aerodynamic simulation module interacts with the six-degree-of-freedom motion simulation module to calculate and output the aerodynamic forces and aerodynamic moments of the aircraft under different motion states and aerodynamic parameter configurations; The variable flight control simulation module interacts with the variable aerodynamic simulation module to calculate and output the rudder surface deflection under different stick and rudder control amounts, flight control instruction types and control gains; The physical property simulation module interacts with the six-degree-of-freedom motion simulation module to calculate and output physical properties of the aircraft such as weight and inertia; The six-degree-of-freedom motion module interacts with the variable aerodynamic simulation module and the variable flight control simulation module to calculate and output flight motion parameters such as aircraft speed, attitude, and position.

[0007] Preferably, the variable aerodynamic simulation module includes an aerodynamic derivative interpolation submodule, an aerodynamic coefficient reconstruction calculation submodule, and an aerodynamic force and aerodynamic moment calculation submodule. Among them, the aerodynamic derivative interpolation submodule can interpolate the aerodynamic derivative using the nonlinear aerodynamic data package of the existing aircraft model, the aerodynamic coefficient reconstruction calculation submodule reconstructs the aerodynamic coefficient expression, calculates the aerodynamic coefficient after the variable aerodynamic setting, and the aerodynamic force and aerodynamic moment calculation submodule calculates the aerodynamic force and aerodynamic moment of the aircraft.

[0008] Preferably, the variable flight control simulation module includes a flight control law switching submodule and a control surface response submodule. The flight control law switching submodule can switch the flight control law and control gain under different instruction types in real time and calculate the expected control surface deflection angle, and the control surface response submodule calculates the actual control surface deflection angle.

[0009] A flight simulation model for a variable stability flight simulator, wherein the modeling method comprises the following steps: Step 1: Establish an interface control module and define the external data that needs to be received, including initial flight parameters, stick and rudder trim, stick and rudder control, variable aerodynamic identification, flight control instruction type identification, configuration of aerodynamic parameters, and configuration of flight control gain; Step 2: Establish a variable aerodynamic simulation module, establish an aerodynamic derivative interpolation table and aerodynamic coefficient expression based on the nonlinear aerodynamic data package, and determine whether to perform variable aerodynamic settings through the variable aerodynamic flag. If variable aerodynamic settings are performed, reconstruct the aerodynamic coefficient expression and add the impact of the externally configured aerodynamic parameters as an increment to the aerodynamic coefficient; otherwise, only use the basic nonlinear aerodynamic data package. Calculate the aerodynamic force and aerodynamic moment of the aircraft according to the aerodynamic force and aerodynamic moment formula; Step 3: Establish a physical characteristics simulation module to output aircraft weight, moment of inertia and product of inertia; Step 4: Establish a six-degree-of-freedom motion simulation module, and calculate the resultant force and torque of the aircraft in the air based on the gravity, thrust, aerodynamic force and torque it is subjected to. Use the six-degree-of-freedom motion equation to calculate the linear acceleration and angular acceleration of the aircraft in the aircraft system, and calculate the speed, attitude and position of the aircraft in the aircraft system and the earth axis system through integration and coordinate transformation; Step 5: Establish a variable flight control simulation module, construct flight control laws under different instruction types for the longitudinal channel, lateral channel, and heading channel, and switch the corresponding control laws and control gains in real time according to the instruction type identifier and the externally configured control gain. Under the action of the external stick and rudder control amount, calculate the expected deflection angle of the rudder surface, and calculate the actual deflection angle of the rudder surface through the dynamic response of the rudder surface.

[0010] Preferably, the aerodynamic parameters configured in step 2 include longitudinal and lateral aerodynamic parameters. The longitudinal aerodynamic parameters include , , the lateral and directional aerodynamic parameters include , , , , .

[0011] Preferably, the instruction types in step 5 include longitudinal, lateral and heading instruction types. The longitudinal instruction type includes angle of attack instruction, pitch rate instruction, pitch angle instruction, normal overload instruction, and direct link instruction; the lateral instruction type includes roll rate instruction, roll angle instruction, and direct link instruction; and the heading instruction type includes sideslip angle instruction, lateral overload instruction, and direct link instruction.

[0012] Preferably, the control gains configured in step five include command gain, feedforward gain, proportional gain, integral gain, differential gain, inner loop feedback gain, and outer loop feedback gain.

[0013] The beneficial effects of the present invention are: 1) A variable aerodynamic simulation module and a variable flight control simulation module are added to the traditional flight simulation model, which realizes the dual adjustment of aerodynamic parameters and flight control laws in the same flight simulation model, and provides a feasible technical solution for flight simulation modeling of variable stability flight simulators; 2) The variable aerodynamic simulation module can make full use of the existing nonlinear aerodynamic data package, reconstruct the aerodynamic coefficient expression based on it, and adjust the aerodynamic characteristics, solving the problem that the linear aerodynamic model is difficult to produce the desired flight quality control response after the aircraft deviates from the balance point; 3) The variable flight control simulation module can switch the control instruction type in real time according to the instruction type identifier and configure the control gain. The online adjustment of the flight control law reflects the impact of different control laws and control gains on flight performance. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 This is a structural diagram of the flight simulation model.

[0015] Figure 2 Schematic diagram of the process of modeling the flight simulation model.

[0016] Figure 3 It is a structural diagram of the flight control law of the variable flight control simulation module.

[0017] Figure 4 Figure 2 is the simulation result diagram for different longitudinal aerodynamic parameter configurations.

[0018] Figure 5 This is the simulation result diagram of the angle of attack instruction type.

[0019] Figure 6 This is the simulation result diagram of the pitch angle rate instruction type.

[0020] Figure 7 This is the simulation result diagram of the pitch angle command type.

[0021] Figure 8 This is the simulation result diagram of the normal overload instruction type. DETAILED DESCRIPTION

[0022] The present invention is further described in detail below in conjunction with the accompanying drawings and embodiments.

[0023] like Figure 1 As shown, an embodiment of the present invention discloses a flight simulation model for a variable stability flight simulator, comprising: an interface control module, a variable aerodynamic simulation module, a variable flight control simulation module, a physical property simulation module, and a six-degree-of-freedom motion simulation module; The interface control module interacts with the variable pneumatic simulation module, the variable flight control simulation module, and the six-degree-of-freedom motion simulation module, and is used to receive external initialization data, control instructions, and configuration parameters, and output variable pneumatic identification and configured pneumatic parameters to the variable pneumatic simulation module; output trim rudder deflection, stick rudder control amount, instruction type identification, and configured flight control gain to the variable flight control simulation module; and output trim thrust and initial flight parameters such as initial speed, attitude, and position to the six-degree-of-freedom motion simulation module; The variable aerodynamic simulation module interacts with the six-degree-of-freedom motion simulation module to calculate and output the aerodynamic forces and aerodynamic moments of the aircraft under different motion states and aerodynamic parameter configurations; The variable flight control simulation module interacts with the variable aerodynamic simulation module to calculate and output the rudder surface deflection under different stick and rudder control amounts, flight control instruction types and control gains; The physical property simulation module interacts with the six-degree-of-freedom motion simulation module to calculate and output physical properties of the aircraft such as weight and inertia; The six-degree-of-freedom motion module interacts with the variable aerodynamic simulation module and the variable flight control simulation module to calculate and output flight motion parameters such as aircraft speed, attitude, and position.

[0024] In order to further realize the above technical solution, the variable aerodynamic simulation module includes an aerodynamic derivative interpolation submodule, an aerodynamic coefficient reconstruction calculation submodule, and an aerodynamic force and aerodynamic moment calculation submodule. Among them, the aerodynamic derivative interpolation submodule can interpolate the aerodynamic derivative using the nonlinear aerodynamic data package of the existing aircraft model, the aerodynamic coefficient reconstruction calculation submodule reconstructs the aerodynamic coefficient expression, calculates the aerodynamic coefficient after the variable aerodynamic setting, and the aerodynamic force and aerodynamic moment calculation submodule calculates the aerodynamic force and aerodynamic moment of the aircraft.

[0025] In order to further implement the above technical solution, the variable flight control simulation module includes a flight control law switching submodule and a rudder response submodule. The flight control law switching submodule can switch the flight control law and control gain under different instruction types in real time and calculate the expected rudder deflection angle, and the rudder response submodule calculates the actual rudder deflection angle.

[0026] like Figure 2As shown, an embodiment of the present invention discloses a flight simulation model for a variable stability flight simulator, and its modeling method includes the following steps.

[0027] Step 1: Establish an interface control module and define the external data that needs to be received, including initial flight parameters, stick and rudder trim, stick and rudder control, variable aerodynamic identification, flight control instruction type identification, configuration of aerodynamic parameters, and configuration of flight control gains; among them, the initial flight parameters provide the initial value of the integral for the six-degree-of-freedom motion solution; the stick and rudder trim is the initial value of the rudder surface deflection, so that the aircraft is initially in a balanced state; the stick and rudder control is the external control input, and the aircraft produces motion changes under the action of the external control input; the variable aerodynamic identification is used to determine whether to perform variable aerodynamic settings. If variable aerodynamic settings are performed, the variable aerodynamic simulation module will receive the externally configured aerodynamic parameters and reconstruct the aerodynamic coefficient expression; the flight control instruction type identification and the configuration of flight control gains are used to switch different flight control instruction types and change the flight control gain in the variable flight control simulation module respectively.

[0028] Step 2: Establish a variable aerodynamic simulation module, and establish an aerodynamic derivative interpolation table and aerodynamic coefficient basic expression based on the nonlinear aerodynamic data package. The aerodynamic parameters of the external configuration include the longitudinal aerodynamic parameters , and lateral aerodynamic parameters , , , , , these aerodynamic parameters affect the pitch moment coefficient, rolling moment coefficient and yaw moment coefficient respectively. Therefore, the pitch moment coefficient is established according to the nonlinear aerodynamic data package , rolling moment coefficient and the yaw moment coefficient Here, the basic expression varies according to the aerodynamic data package of the aircraft model, but it does not affect the adjustment of aerodynamic parameters and the reconstruction of aerodynamic coefficient expressions.

[0029] Furthermore, the variable aerodynamic flag is used to determine whether to perform variable aerodynamic settings. If variable aerodynamic settings are performed, the aerodynamic coefficient expression is reconstructed. The state parameters of the aircraft at the equilibrium point are defined as , the basic pitching moment coefficient at the equilibrium point is , the basic rolling moment coefficient is , the basic yaw moment coefficient is The influence of the aerodynamic parameters of the external configuration is added to the aerodynamic coefficient as an increment, and the reconstructed aerodynamic coefficient expression is as follows: Reconstruct the pitch moment coefficient: (1) Reconstruct the rolling moment coefficient: (2) Reconstruct the yaw moment coefficient: (3) in, , , , , , , Pneumatic parameters for external configuration, is the change in aircraft angle of attack, is the change in the aircraft sideslip angle, is the aircraft system angular velocity, is the true airspeed of the aircraft, is the wing span, is the average aerodynamic chord length. The aerodynamic force and aerodynamic moment acting on the aircraft are then calculated according to the aerodynamic force and aerodynamic moment formula.

[0030] Step 3: Create a physical properties simulation module to output the aircraft weight , Moment of inertia and product of inertia This part of the data does not take into account the changes in the aircraft's weight and center of gravity caused by fuel consumption and other reasons.

[0031] Step 4: Establish a six-degree-of-freedom motion simulation module. According to the gravity, thrust, aerodynamic force and aerodynamic moment of the aircraft, calculate the resultant force and torque of the aircraft in the air, and use the following six-degree-of-freedom motion equation to calculate the linear acceleration and angular acceleration of the aircraft in the aircraft system: Linear acceleration of the machine system: (4) Angular acceleration of the machine system: (5) in, is the aircraft system speed, are the resultant force and moment acting on the aircraft, to is the correlation coefficient. Then, the speed, attitude and position of the aircraft in the aircraft system and the earth axis system are calculated through integration and coordinate transformation.

[0032] Step 5: Establish a variable flight control simulation module and construct flight control laws for different instruction types of longitudinal channel, lateral channel and heading channel. The control law structure diagram is as follows: Figure 3 shown.

[0033] Longitudinal command types include angle of attack command, pitch rate command, pitch angle command, normal overload command, and direct link command. Among them, the angle of attack command refers to the command input form in which the aircraft's longitudinal joystick amount corresponds to the angle of attack; the pitch rate command refers to the command input form in which the aircraft's longitudinal joystick amount corresponds to the pitch rate; the pitch angle command refers to the command input form in which the aircraft's longitudinal joystick amount corresponds to the pitch angle; the normal overload command refers to the command input form in which the aircraft's longitudinal joystick amount corresponds to the normal overload; and the direct link command refers to the command input form in which the aircraft's longitudinal joystick amount corresponds to the elevator deflection.

[0034] The lateral command types include roll rate command, roll angle command, and direct link command. Among them, the roll rate command refers to the command input form in which the aircraft's lateral joystick amount corresponds to the roll rate; the roll angle command refers to the command input form in which the aircraft's lateral joystick amount corresponds to the roll angle; the direct link command refers to the command input form in which the aircraft's lateral joystick amount corresponds to the aileron deflection.

[0035] The heading instruction types include sideslip angle instruction, lateral overload instruction, and direct link instruction. Among them, the sideslip angle instruction refers to the instruction input form in which the aircraft heading steering amount corresponds to the sideslip angle; the lateral overload instruction refers to the instruction input form in which the aircraft heading steering amount corresponds to the lateral overload; and the direct link instruction refers to the instruction input form in which the aircraft heading steering amount corresponds to the rudder deflection.

[0036] The configurable control gains for each command type include command gains , feedforward gain , proportional gain , integral gain , differential gain , inner loop feedback gain , outer loop feedback gain .

[0037] According to the command type identification and externally configured control gain, the corresponding control law and control gain are switched in real time. Under the action of the external stick and rudder control amount, the desired rudder surface deflection angle is solved. Taking the longitudinal pitch angle command type as an example, the control command is the longitudinal control stick amount , the outer loop feedback is the aircraft pitch angle , the inner loop feedback is the aircraft pitch rate , the desired elevator deflection angle is calculated as: (6) in, is the pitch angle control error. Then the actual deflection angle of the rudder surface is calculated through the dynamic response of the rudder surface.

[0038] After establishing a flight simulation model for a variable stability flight simulator according to the above modeling method, the following simulation verification can be performed. Here, the longitudinal variable aerodynamic setting and the longitudinal control instruction type switching are taken as examples.

[0039] First, verify the change in flight quality caused by external configuration of aerodynamic parameters. The initial flight state is selected as an altitude of 12,000 meters and a speed of 400 meters per second. The longitudinal aerodynamic parameters of the external configuration are: , ; Working condition 2: , ; Working condition three: , .because and It mainly affects the short-period mode of the aircraft, so the angle of attack under three working conditions is compared. and pitch rate changes, such as Figure 4 As shown. Increase, damping ratio increases, angle of attack and pitch rate The oscillations are weakened, changing the aircraft's short-period quality characteristics.

[0040] Furthermore, the influence of different instruction types of flight control laws on flight performance is verified. Figures 5 to 8 As shown in the figure, under the action of the pitch pulse of the joystick, the longitudinal command types are switched to angle of attack command, pitch angle rate command, pitch angle command, and normal overload command. For angle of attack command and pitch angle command, the aircraft will stabilize at the angle of attack and pitch angle corresponding to the joystick value, respectively. When the joystick returns to the center, the angle of attack and pitch angle will return to 0; for pitch angle rate command, the aircraft will stabilize at the pitch angle rate corresponding to the joystick value. When the joystick returns to the center, the pitch angle rate will return to 0 and the pitch angle will remain; for normal overload command, the aircraft will stabilize at the normal overload corresponding to the joystick value. When the joystick returns to the center, the normal overload will remain at 1G to achieve neutral speed stability.

[0041] In summary, the present invention provides a flight simulation model and modeling method for a variable stability flight simulator, which covers the functions of aerodynamic parameter adjustment and flight control law adjustment. It realizes the dual functions of reflecting the flight quality changes caused by different aerodynamic characteristics and the influence of different flight control laws and control gains on flight performance in the same flight simulation model.

[0042] It is understandable that those skilled in the art can make equivalent substitutions or changes based on the technical solution and inventive concept of the present invention, and all these substitutions or changes should fall within the protection scope of the claims attached to the present invention.

Claims

1. A flight simulation model for a variable stability flight simulator, characterized in that: include: Interface control module, variable aerodynamic simulation module, variable flight control simulation module, physical characteristics simulation module, six-degree-of-freedom motion simulation module; The interface control module interacts with the variable pneumatic simulation module, the variable flight control simulation module, and the six-degree-of-freedom motion simulation module, and is used to receive external initialization data, manipulation instructions, and configuration parameters, and output variable pneumatic identification and configured pneumatic parameters to the variable pneumatic simulation module; Output trim rudder deflection, stick and rudder control amount, instruction type identification and configured flight control gain to the variable flight control simulation module; output trim thrust and initial flight parameters such as initial speed, attitude, position, etc. to the six-degree-of-freedom motion simulation module; The variable aerodynamic simulation module interacts with the six-degree-of-freedom motion simulation module to calculate and output the aerodynamic forces and aerodynamic moments of the aircraft under different motion states and aerodynamic parameter configurations; The variable flight control simulation module interacts with the variable aerodynamic simulation module to calculate and output the rudder surface deflection under different stick and rudder control amounts, flight control instruction types and control gains; The physical property simulation module interacts with the six-degree-of-freedom motion simulation module to calculate and output physical properties of the aircraft, such as weight and inertia; The six-degree-of-freedom motion module interacts with the variable aerodynamic simulation module and the variable flight control simulation module to calculate and output flight motion parameters such as aircraft speed, attitude, and position.

2. A flight simulation model for a variable stability flight simulator according to claim 1, characterized in that: The variable aerodynamic simulation module includes an aerodynamic derivative interpolation submodule, an aerodynamic coefficient reconstruction calculation submodule, and an aerodynamic force and aerodynamic moment calculation submodule. Among them, the aerodynamic derivative interpolation submodule can interpolate the aerodynamic derivative using the nonlinear aerodynamic data package of the existing aircraft model, the aerodynamic coefficient reconstruction calculation submodule reconstructs the aerodynamic coefficient expression, calculates the aerodynamic coefficient after the variable aerodynamic setting, and the aerodynamic force and aerodynamic moment calculation submodule calculates the aerodynamic force and aerodynamic moment of the aircraft.

3. A flight simulation model for a variable stability flight simulator according to claim 1, characterized in that: The variable flight control simulation module includes a flight control law switching submodule and a control surface response submodule. The flight control law switching submodule can switch the flight control law and control gain under different instruction types in real time and calculate the expected control surface deflection angle, and the control surface response submodule calculates the actual control surface deflection angle.

4. A modeling method for a flight simulation model of a variable stability flight simulator, characterized in that: The following steps are involved: Step 1: Establish an interface control module and define the external data that needs to be received, including initial flight parameters, stick and rudder trim, stick and rudder control, variable aerodynamic identification, flight control instruction type identification, configuration of aerodynamic parameters, and configuration of flight control gain; Step 2: Establish a variable aerodynamic simulation module, establish an aerodynamic derivative interpolation table and aerodynamic coefficient expression according to the nonlinear aerodynamic data package, and determine whether to perform variable aerodynamic settings through the variable aerodynamic flag. If variable aerodynamic settings are performed, reconstruct the aerodynamic coefficient expression and add the influence of the externally configured aerodynamic parameters as an increment to the aerodynamic coefficient; otherwise, only use the basic nonlinear aerodynamic data package. Calculate the aerodynamic force and aerodynamic moment of the aircraft according to the aerodynamic force and aerodynamic moment formula; Step 3: Establish a physical characteristics simulation module to output aircraft weight, moment of inertia and product of inertia; Step 4: Establish a six-degree-of-freedom motion simulation module, calculate the resultant force and torque of the aircraft in the air according to the gravity, thrust, aerodynamic force and torque it is subjected to, calculate the linear acceleration and angular acceleration of the aircraft in the aircraft system using the six-degree-of-freedom motion equation, and calculate the speed, attitude and position of the aircraft in the aircraft system and the earth axis system through integration and coordinate transformation; Step 5: Establish a variable flight control simulation module, construct flight control laws under different instruction types for the longitudinal channel, lateral channel, and heading channel, and switch the corresponding control laws and control gains in real time according to the instruction type identifier and the externally configured control gain. Under the action of the external stick and rudder control amount, calculate the expected deflection angle of the rudder surface, and calculate the actual deflection angle of the rudder surface through the dynamic response of the rudder surface.

5. A modeling method for a flight simulation model for a variable stability flight simulator according to claim 4, characterized in that The aerodynamic parameters configured in step 2 include longitudinal and lateral aerodynamic parameters. The longitudinal aerodynamic parameters include , , the lateral and directional aerodynamic parameters include , , , , .

6. A modeling method for a flight simulation model for a variable stability flight simulator according to claim 4, characterized in that The instruction types in step 5 include longitudinal, lateral and heading instruction types. The longitudinal instruction type includes angle of attack instruction, pitch rate instruction, pitch angle instruction, normal overload instruction, and direct link instruction; the lateral instruction type includes roll rate instruction, roll angle instruction, and direct link instruction; and the heading instruction type includes sideslip angle instruction, lateral overload instruction, and direct link instruction.

7. A modeling method for a flight simulation model for a variable stability flight simulator according to claim 4, characterized in that The control gains configured in step five include command gain, feedforward gain, proportional gain, integral gain, differential gain, inner loop feedback gain, and outer loop feedback gain.

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