Digital twin platform of aircraft flight control system, data processing method of digital twin platform and medium

Abstract

The invention discloses a digital twin platform of an aircraft flight control system, a data processing method of the digital twin platform and a medium, and relates to the technical field of aircraft simulation training, and the platform comprises a parameter setting unit which is used for setting aircraft basic information and current flight state parameters; the control signal acquisition unit is used for acquiring an electric signal generated when a user operates the control device; the calculation unit is used for calculating the initial control surface aerodynamic force according to the control surface aerodynamic force calculation model, calculating the control surface deflection angle according to the control surface aerodynamic-control device force transmission model, and recalculating the control surface aerodynamic force according to the control surface aerodynamic force calculation model; and the force sensing feedback unit is used for calculating joystick feedback force in the current aircraft flight state and the current control state according to the control surface aerodynamic force-control device force transmission model, and feeding back generated corresponding control resistance to the control device. The platform not only saves the economic cost and occupied area for establishing an entity iron bird test bench, but also can test the performance of a flight control system of an airplane in different flight states.

Description

Technical Field

[0001] This invention relates to the field of aircraft simulation training technology, specifically to a digital twin platform for an aircraft flight control system, its data processing method, and its medium. Background Technology

[0002] The flight control system is one of the most important systems in an aircraft. During the aircraft's research and development, design, and maintenance training, it is necessary to establish a metal bird test bench for the target aircraft. The metal bird test bench is a fixed platform on which the aircraft's flight control system is mounted to demonstrate and test its functions. Metal bird test benches typically replicate the key dimensions of the target aircraft's flight control system at a 1:1 scale, thus requiring a large footprint. They primarily test the control relationships of the flight control system. If it is necessary to test the state of the flight control system under different flight conditions, force application devices need to be installed on the control surfaces, which not only increases equipment investment costs but also enhances the complexity of the testing operation. Summary of the Invention

[0003] The purpose of this invention is to provide a digital twin platform for an aircraft flight control system, its data processing method and medium, which solves the problems of high cost and large footprint of physical iron bird test benches, and the need to add additional force application units to test the performance of the flight control system under different flight conditions of the aircraft.

[0004] This invention is achieved through the following technical solution: In a first aspect, a digital twin platform for an aircraft flight control system is provided in a first embodiment of the present invention, comprising: a state analysis module, wherein the state analysis module includes a parameter setting unit, a control signal acquisition unit, a calculation unit, and a force feedback unit. The parameter setting unit is used to set basic aircraft information and current flight status parameters; The control signal acquisition unit is used to acquire electrical signals generated when the user operates the control device. The calculation unit is used to calculate the initial control surface aerodynamic force according to the control surface aerodynamic calculation model, and to calculate the control surface deflection angle according to the control surface aerodynamic-control device force transmission model, and to recalculate the control surface aerodynamic force according to the control surface aerodynamic calculation model. The force feedback unit is used to calculate the control stick feedback force under the current aircraft flight state and current control state based on the control surface aerodynamic-control device force transmission model, and feed it back to the control device to generate corresponding control resistance, providing the user with realistic control feedback.

[0005] Furthermore, it also includes a status display module, which includes a 3D model of the flight control system and a display unit. The 3D model of the flight control system is used to generate a three-dimensional model based on the basic information of the aircraft, and the display unit is used to display the status of the 3D model of the flight control system under different operations.

[0006] Furthermore, the basic aircraft information includes the target aircraft type, and the flight status parameters include flight altitude, flight speed, and initial deflection angle of the control surfaces.

[0007] Furthermore, the calculation unit includes a first calculation subunit, which includes a control surface aerodynamic calculation model. The control surface aerodynamic calculation model obtains the air density based on the flight altitude, obtains the lift coefficient based on the control surface deflection angle, and calculates the control surface aerodynamic force based on the air density, aircraft flight speed, lift coefficient, and aircraft control surface area.

[0008] The calculation unit also includes a second calculation subunit, which includes a control surface aerodynamic-control device force transmission model. The control surface aerodynamic-control device force transmission model calculates the control transmission ratio based on the distance between the control point and the pivot point of the control device and the distance between the bottom of the stick and the pivot point. It calculates the bottom displacement of the stick based on the control transmission ratio and the distance the user moves the control device. It also obtains the rocker arm transmission ratio based on the ratio of the input arm length to the output arm length of the transmission device. It multiplies the bottom displacement of the stick with the multi-segment rocker arm transmission ratio to obtain the output stick push-out displacement. It uses the output stick push-out position to remove the control surface actuation length to obtain the control surface deflection angle.

[0009] Furthermore, the force feedback unit includes a feedback force calculation subunit, which is used to calculate the control stick feedback force based on the aerodynamic force of the control surface, the average aerodynamic chord length of the control surface, the actuation length of the control surface, the control transmission ratio, the rocker arm transmission ratio of the multi-segment rocker arm, and the system efficiency coefficient.

[0010] Secondly, another embodiment of the present invention provides a data processing method for a digital twin platform of an aircraft flight control system, comprising: Retrieve basic aircraft information and current flight status parameters set by the user; Acquire electrical signals generated when the user operates the control device; The initial aerodynamic forces of the control surface are calculated based on the control surface aerodynamic calculation model, and the control surface deflection angle is calculated based on the control surface aerodynamic-control device force transmission model. The control surface aerodynamic forces are then recalculated based on the control surface aerodynamic calculation model. The control stick feedback force is calculated based on the aerodynamic-control force transmission model of the control surfaces and the control device, and then fed back to the control device to generate corresponding control resistance, providing the user with realistic control feedback.

[0011] Furthermore, the method also includes: Generate a 3D model based on the aircraft's basic information; Displays the 3D model status of the flight control system under different maneuvers.

[0012] Furthermore, the basic aircraft information includes the target aircraft type, the flight state parameters include flight altitude, flight speed, and initial control surface deflection angle, and the specific method for calculating the initial control surface aerodynamic forces based on the control surface aerodynamic calculation model includes: The current air density is obtained based on the flight altitude, and the initial lift coefficient is obtained based on the initial deflection angle of the control surfaces. The formula for calculating the aerodynamic forces of the control surface based on the control surface aerodynamic calculation model is as follows: F B = 0.5*C*ρ*v 2 *S; Among them, F B For the control surface aerodynamic force, C is the initial lift coefficient, ρ is the current air density, V is the current flight speed of the aircraft, and s is the area of ​​the aircraft control surface. The specific method for calculating the control surface deflection angle based on the control surface aerodynamic-control device force transmission model includes: Obtain the distance l1 from the control point of the control device to the fulcrum and the distance l2 from the bottom of the rod to the fulcrum; The control transmission ratio i is calculated based on the distance l1 from the control point to the fulcrum and the distance l2 from the bottom of the lever to the fulcrum. A The calculation formula is: i A = l1 / l2; The distance X of the user's moving control device is obtained. Based on the control transmission ratio and the distance of the user's moving control device, the formula for calculating the pole bottom displacement X1 is as follows: X1 = X*i A ; Obtain the input arm length l of the transmission device in and output arm length l out Calculate the rocker arm transmission ratio i of n rocker arm segments. B The calculation formula is: i B1 = l in-1 / l out-1； i B2 = l in-2 / l out-2； ..... i Bn = l in-n / l out-n； Where n is an integer greater than or equal to 2; The formula for calculating the output rod displacement X2 based on the rod bottom displacement X1 and the rocker arm transmission ratio of n segments is as follows: X2 = X1*i B1 *...*iBn ; The formula for calculating the rudder deflection angle α based on the output rod displacement X2 and the rudder actuation length R is as follows: α = X² / R; The new lift coefficient C(t) is obtained by updating the lift coefficient based on the deflection angle of the control surface.

[0013] Furthermore, the specific method for calculating the control stick feedback force under the current aircraft flight state and current control state based on the control surface aerodynamic-control device force transmission model includes: The aerodynamic force F of the control surface was calculated based on the new lift coefficient. B (t); Obtain the mean aerodynamic chord length D of the control surface, the control surface actuation length R, and the control gear ratio i. A The feedback force F of the control lever is calculated from the transmission ratio of the n-segment rocker arm and the system efficiency coefficient η. A The formula for calculating (t) is: F A (t)=F B (t)*D / (R*i A *i B1 *···*i Bn *η).

[0014] Thirdly, another embodiment of the present invention provides a computer-readable storage medium storing a computer program, the computer program including program instructions, which, when executed by a processor, cause the processor to perform the method described in the second embodiment above.

[0015] Compared with the prior art, the present invention has the following advantages and beneficial effects:

[0016] This invention provides a digital twin platform for an aircraft flight control system, its data processing method, and a medium. By constructing a 3D model of the flight control system in a virtual environment using digital twin technology, it eliminates the need for a 1:1 replica of an iron bird test bench, significantly reducing the floor space required and saving the construction, maintenance, and additional force application device costs associated with physical test benches. Without the need for additional equipment, it can simulate the performance of the flight control system under different flight conditions, overcoming the limitations of traditional test benches that primarily test control relationships, and providing a wider range of test scenarios. The 3D model of the flight control system is strictly constructed based on the actual parameters of the target aircraft. The force transmission model quantifies the correspondence between control and control surface actions, providing control drag that matches actual control, making the simulation and test results more closely resemble real flight scenarios and increasing reliability. Attached Figure Description

[0017] To more clearly illustrate the technical solutions of the exemplary embodiments of the present invention, the accompanying drawings used in the embodiments will be briefly described below. It should be understood that the following drawings only show some embodiments of the present invention and should not be considered as a limitation of the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort. In the drawings: Figure 1 A structural block diagram of a digital twin platform for an aircraft flight control system provided in the first embodiment of the present invention; Figure 2 A flowchart illustrating a data processing method for a digital twin platform of an aircraft flight control system, provided in the second embodiment of the present invention. Detailed Implementation

[0018] To make the objectives, technical solutions, and advantages of the present invention clearer, the present invention will be further described in detail below with reference to the embodiments and accompanying drawings. The illustrative embodiments and descriptions of the present invention are only used to explain the present invention and are not intended to limit the present invention.

[0019] like Figure 1 As shown, the first embodiment of the present invention provides a digital twin platform for an aircraft flight control system, comprising: a status display module and a status analysis module. The status analysis module includes a parameter setting unit, a control signal acquisition unit, a calculation unit, and a force feedback unit. The status display module includes a 3D model of the flight control system and a display unit. The parameter setting unit is used to set basic aircraft information and current flight status parameters; The flight control system 3D model is used to generate a three-dimensional model based on the basic information of the aircraft. The control signal acquisition unit is used to acquire electrical signals generated when the user operates the control device. The calculation unit is used to calculate the initial control surface aerodynamic force according to the control surface aerodynamic calculation model, and to calculate the control surface deflection angle according to the control surface aerodynamic-control device force transmission model, and to recalculate the control surface aerodynamic force according to the control surface aerodynamic calculation model. The force feedback unit is used to calculate the control stick feedback force under the current flight state and current control state of the aircraft based on the control surface aerodynamic-control device force transmission model, and feed it back to the control device to generate corresponding control resistance, providing the user with real control feedback. The display unit is used to display the 3D model status of the flight control system under different maneuvers.

[0020] In this embodiment, the user can select between a status display module and a status analysis module as needed. The status display module mainly displays the composition and operation of the simulated target aircraft's flight control system, while the status analysis module mainly simulates the operation of the flight control system under different flight conditions. The display unit in the status display module is a monitor or a head-mounted virtual display device, which allows the user to intuitively see the operation of the aircraft's flight control system under different flight conditions.

[0021] The state analysis module includes a parameter setting unit, a control signal acquisition unit, a calculation unit, and a force feedback unit. Users can set basic aircraft information and current flight status parameters through the parameter setting unit. Basic aircraft information includes the target aircraft type, and flight status parameters include flight altitude, flight speed, and initial control surface deflection angle. After selecting the target aircraft type, the relevant information for the control devices, transmission devices, and control surfaces is determined. The control devices, mainly composed of a joystick / control wheel and pedals, are physical devices. When the user performs related operations, the corresponding electrical signals are generated as input to the state display and state analysis modules. The 3D model of the flight control system mainly consists of the aircraft's main control surfaces (ailerons, rudder, elevators), transmission devices (drive sticks, cables, cams, etc.), and fixed units. The size and installation position of the 3D model are determined by the actual parameters of the target aircraft. The components in the 3D model are assembled according to the "control device—transmission device—control surface" order. Each control surface has only one degree of rotational freedom, and the control device signals are used as input to the 3D model.

[0022] The control signal acquisition unit acquires the electrical signals generated when the user operates the control device and transmits them to the calculation unit. The calculation unit includes a first subunit, which includes a control surface aerodynamic calculation model. The control surface aerodynamic calculation model obtains the air density based on the flight altitude, the lift coefficient based on the control surface deflection angle, and calculates the control surface aerodynamic forces based on the air density, aircraft speed, lift coefficient, and control surface area. The calculation unit also includes a second calculation subunit, which includes a control surface aerodynamic-control device force transmission model. The control surface aerodynamic-control device force transmission model calculates the control transmission ratio based on the distance from the control point to the pivot point and the distance from the stick bottom to the pivot point. It calculates the stick bottom displacement based on the control transmission ratio and the distance the user moves the control device, and obtains the rocker arm transmission ratio based on the ratio of the input arm length to the output arm length of the transmission device. The stick bottom displacement is multiplied by the rocker arm transmission ratio of n rocker arms to obtain the output stick extension displacement. The control surface deflection angle is obtained by removing the control surface actuation length using the output stick extension position.

[0023] The first calculation subunit calculates the initial aerodynamic forces of the control surfaces based on the control surface aerodynamic calculation model. The specific calculation process is as follows: The current air density is obtained based on the flight altitude, and the initial lift coefficient is obtained based on the initial deflection angle of the control surfaces. The formula for calculating the aerodynamic forces of the control surface based on the control surface aerodynamic calculation model is as follows: F B = 0.5*C*ρ*v 2 *S; Among them, F B For the control surface aerodynamic force, C is the initial lift coefficient, ρ is the current air density, V is the current flight speed of the aircraft, and s is the area of ​​the aircraft control surface. The specific methods used by the second calculation subunit to calculate the control surface deflection angle based on the control surface aerodynamic-control device force transmission model include: Obtain the distance l1 from the control point of the control device to the fulcrum and the distance l2 from the bottom of the rod to the fulcrum; The control transmission ratio i is calculated based on the distance l1 from the control point to the fulcrum and the distance l2 from the bottom of the lever to the fulcrum. A The calculation formula is: i A = l1 / l2; The distance X of the user's moving control device is obtained. Based on the control transmission ratio and the distance of the user's moving control device, the formula for calculating the pole bottom displacement X1 is as follows: X1 = X*i A ; Obtain the input arm length l of the transmission device in and output arm length l out Calculate the rocker arm transmission ratio i of n rocker arm segments. B The calculation formula is: i B1 = l in-1 / l out-1； i B2 = l in-2 / l out-2； ..... i Bn = l in-n / l out-n； Where n is an integer greater than or equal to 2; The formula for calculating the output rod displacement X2 based on the rod bottom displacement X1 and the rocker arm transmission ratio of n segments is as follows: X2 = X1*i B1 *...*i Bn ; The formula for calculating the rudder deflection angle α based on the output rod displacement X2 and the rudder actuation length R is as follows: α = X² / R; The new lift coefficient C(t) is obtained by updating the lift coefficient based on the deflection angle of the control surface.

[0024] The calculation unit also includes a third calculation subunit, which recalculates the aerodynamic forces of the control surfaces based on the control surface aerodynamic calculation model, and substitutes the new lift coefficient C(t) into the control surface aerodynamic calculation formula to obtain F. B (t) = 0.5*C(t)*ρ*v 2 *S.

[0025] The force feedback unit includes a feedback force calculation subunit, which calculates the joystick feedback force based on the aerodynamic forces of the control surfaces, the average aerodynamic chord length of the control surfaces, the actuation length of the control surfaces, the control transmission ratio, the rocker arm transmission ratio of the multi-segment rocker arm, and the system efficiency coefficient. The joystick feedback force F A The formula for calculating (t) is: F A (t)=F B (t)*D / (R*i A *i B1 *···*i Bn *η); Where D is the mean aerodynamic chord length of the control surface, R is the actuation length of the control surface, and i A To manipulate the transmission ratio, iB1*···*iB n Let η be the transmission ratio of the n-segment rocker arm, and η be the system efficiency coefficient. For a cable-pulley system: η ≈ 0.70-0.85; for a pure pushrod system: η ≈ 0.85-0.95; for an old or poorly maintained system: η may be as low as 0.50-0.70.

[0026] The force feedback unit calculates the force under the current flight and control conditions of the aircraft and feeds it back to the control device to generate corresponding control resistance, providing users with realistic control feedback. Users can see the current flight status through the status display module.

[0027] This invention provides a digital twin platform for an aircraft flight control system. By constructing a 3D model of the flight control system in a virtual environment using digital twin technology, it eliminates the need for a 1:1 replica of an iron bird test bench, significantly reducing the floor space required and saving the construction, maintenance, and additional force application device costs associated with physical test benches. Through a state analysis module, the performance of the flight control system under different flight conditions can be simulated without additional equipment, overcoming the limitations of traditional test benches that primarily test control relationships, and providing a wider range of test scenarios. The 3D model of the flight control system is strictly constructed based on the actual parameters of the target aircraft. The force transmission model quantifies the correspondence between control and control surface actions, and the force feedback unit provides control drag that matches actual control, making the simulation and test results more closely resemble real flight scenarios and increasing reliability.

[0028] like Figure 2 As shown, the second embodiment of the present invention provides a data processing method for a digital twin platform of an aircraft flight control system, comprising: Retrieve basic aircraft information and current flight status parameters set by the user; Generate a 3D model based on the aircraft's basic information; Acquire electrical signals generated when the user operates the control device; The initial aerodynamic forces of the control surface are calculated based on the control surface aerodynamic calculation model, and the control surface deflection angle is calculated based on the control surface aerodynamic-control device force transmission model. The control surface aerodynamic forces are then recalculated based on the control surface aerodynamic calculation model. Based on the aerodynamic-control force transmission model of the control surface, the control stick feedback force under the current flight state and current control state is calculated and fed back to the control device to generate corresponding control resistance, providing users with realistic control feedback. Displays the 3D model status of the flight control system under different maneuvers.

[0029] In this embodiment, the basic aircraft information includes the target aircraft type, and the flight status parameters include flight altitude, flight speed, and initial deflection angle of the control surfaces; The specific method for calculating the initial aerodynamic forces of the control surface based on the control surface aerodynamic calculation model includes: The current air density is obtained based on the flight altitude, and the initial lift coefficient is obtained based on the initial deflection angle of the control surfaces. The formula for calculating the aerodynamic forces of the control surface based on the control surface aerodynamic calculation model is as follows: F B = 0.5*C*ρ*v 2 *S; In this embodiment, F B For the control surface aerodynamic force, C is the initial lift coefficient, ρ is the current air density, V is the current flight speed of the aircraft, and s is the area of ​​the aircraft control surface. The specific method for calculating the control surface deflection angle based on the control surface aerodynamic-control device force transmission model includes: Obtain the distance l1 from the control point of the control device to the fulcrum and the distance l2 from the bottom of the rod to the fulcrum; The control transmission ratio i is calculated based on the distance l1 from the control point to the fulcrum and the distance l2 from the bottom of the lever to the fulcrum. A The calculation formula is: i A = l1 / l2; The distance X of the user's moving control device is obtained. Based on the control transmission ratio and the distance of the user's moving control device, the formula for calculating the pole bottom displacement X1 is as follows: X1 = X*iA ; Obtain the input arm length l of the transmission device in and output arm length l out Calculate the rocker arm transmission ratio i of n rocker arm segments. B The calculation formula is: i B1 = l in-1 / l out-1； i B2 = l in-2 / l out-2； ..... i Bn = l in-n / l out-n； Where n is an integer greater than or equal to 2; The formula for calculating the output rod displacement X2 based on the rod bottom displacement X1 and the rocker arm transmission ratio of n segments is as follows: X2 = X1*i B1 *...*i Bn ; The formula for calculating the rudder deflection angle α based on the output rod displacement X2 and the rudder actuation length R is as follows: α = X² / R; The new lift coefficient C(t) is obtained by updating the lift coefficient based on the deflection angle of the control surface.

[0030] In this embodiment, the specific method for calculating the control stick feedback force under the current aircraft flight state and current control state based on the control surface aerodynamic-control device force transmission model includes: The aerodynamic force F of the control surface was calculated based on the new lift coefficient. B (t); Obtain the mean aerodynamic chord length D of the control surface, the control surface actuation length R, and the control gear ratio i. A The feedback force F of the control lever is calculated from the transmission ratio of the n-segment rocker arm and the system efficiency coefficient η. A The formula for calculating (t) is: F A (t)=F B (t)*D / (R*i A *i B1 *···*i Bn *η).

[0031] The control stick feedback force is calculated based on the aerodynamic-control force transmission model of the control surfaces and the control device, and then fed back to the control device to generate corresponding control resistance, providing the user with realistic control feedback.

[0032] This invention provides a data processing method for a digital twin platform of an aircraft flight control system. By constructing a 3D model of the flight control system in a virtual environment using digital twin technology, it eliminates the need for a 1:1 replica of an iron bird test bench, significantly reducing the floor space required and saving the construction, maintenance, and additional force application device costs associated with physical test benches. Without the need for additional equipment, it can simulate the performance of the flight control system under different flight conditions, overcoming the limitations of traditional test benches that primarily test control relationships, and providing a wider range of test scenarios. The 3D model of the flight control system is strictly constructed based on the actual parameters of the target aircraft. The force transmission model quantifies the correspondence between control and control surface actions, providing control drag that matches actual control, making the simulation and test results more closely resemble real flight scenarios and increasing reliability.

[0033] Another embodiment of the present invention provides an embodiment of a computer-readable storage medium storing a computer program, the computer program including program instructions, which, when executed by a processor, cause the processor to perform the method described in the second embodiment above.

[0034] The computer-readable storage medium can be an internal storage unit of the terminal described in the foregoing embodiments, such as the terminal's hard drive or memory. The computer-readable storage medium can also be an external storage device of the terminal, such as a plug-in hard drive, Smart Media Card (SMC), Secure Digital (SD) card, or Flash Card equipped on the terminal. Furthermore, the computer-readable storage medium can include both internal storage units and external storage devices of the terminal. The computer-readable storage medium is used to store the computer program and other programs and data required by the terminal. The computer-readable storage medium can also be used to temporarily store data that has been output or will be output.

[0035] Those skilled in the art will recognize that the units and algorithm steps of the various examples described in conjunction with the embodiments disclosed herein can be implemented in electronic hardware, computer software, or a combination of both. To clearly illustrate the interchangeability of hardware and software, the components and steps of the various examples have been generally described in terms of functionality in the foregoing description. Whether these functions are implemented in hardware or software depends on the specific application and design constraints of the technical solution. Those skilled in the art can use different methods to implement the described functions for each specific application, but such implementations should not be considered beyond the scope of this invention.

[0036] Those skilled in the art will understand that, for the sake of convenience and brevity, the specific working processes of the terminals and units described above can be referred to the corresponding processes in the foregoing method embodiments, and will not be repeated here.

[0037] In the several embodiments provided in this application, it should be understood that the disclosed terminals and methods can be implemented in other ways. For example, the device embodiments described above are merely illustrative. For instance, the division of units is only a logical functional division, and in actual implementation, there may be other division methods. For example, multiple units or components may be combined or integrated into another system, or some features may be ignored or not executed. In addition, the mutual coupling or direct coupling or communication connection shown or discussed may be indirect coupling or communication connection through some interfaces, devices or units, or may be electrical, mechanical or other forms of connection.

[0038] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention, and they should all be covered within the scope of the claims and specification of the present invention.

Claims

1. A digital twin platform for an aircraft flight control system, characterized in that, include: The state analysis module includes a parameter setting unit, a control signal acquisition unit, a calculation unit, and a force feedback unit. The parameter setting unit is used to set basic aircraft information and current flight status parameters; The control signal acquisition unit is used to acquire electrical signals generated when the user operates the control device. The calculation unit is used to calculate the initial control surface aerodynamic force according to the control surface aerodynamic calculation model, and to calculate the control surface deflection angle according to the control surface aerodynamic-control device force transmission model, and to recalculate the control surface aerodynamic force according to the control surface aerodynamic calculation model. The force feedback unit is used to calculate the control stick feedback force under the current aircraft flight state and current control state based on the control surface aerodynamic-control device force transmission model, and feed it back to the control device to generate corresponding control resistance, providing the user with realistic control feedback.

2. The digital twin platform for aircraft flight control system according to claim 1, characterized in that, It also includes a status display module, which includes a 3D model of the flight control system and a display unit. The 3D model of the flight control system is used to generate a three-dimensional model based on the basic information of the aircraft, and the display unit is used to display the status of the 3D model of the flight control system under different operations.

3. The digital twin platform for aircraft flight control system according to claim 1 or 2, characterized in that, The basic aircraft information includes the target aircraft type, and the flight status parameters include flight altitude, flight speed, and initial deflection angle of the control surfaces.

4. The digital twin platform for aircraft flight control system according to claim 3, characterized in that, The calculation unit includes a first calculation subunit, which includes a control surface aerodynamic calculation model. The control surface aerodynamic calculation model obtains the air density based on the flight altitude, obtains the lift coefficient based on the control surface deflection angle, and calculates the control surface aerodynamic force based on the air density, aircraft flight speed, lift coefficient, and aircraft control surface area. The calculation unit further includes a second calculation subunit, which includes a control surface aerodynamic-control device force transmission model. The control surface aerodynamic-control device force transmission model calculates the control transmission ratio based on the distance between the control point and the pivot point of the control device and the distance between the bottom of the stick and the pivot point. It calculates the bottom displacement of the stick based on the control transmission ratio and the distance the user moves the control device. It also obtains the rocker arm transmission ratio based on the ratio of the input arm length to the output arm length of the transmission device. The bottom displacement of the stick is multiplied by the rocker arm transmission ratio of the multi-segment rocker arm to obtain the output stick push-out displacement. The control surface deflection angle is obtained by removing the output stick push-out position with the control surface actuation length.

5. The digital twin platform for aircraft flight control system according to claim 4, characterized in that, The force feedback unit includes a feedback force calculation subunit, which is used to calculate the control stick feedback force based on the aerodynamic force of the control surface, the average aerodynamic chord length of the control surface, the actuation length of the control surface, the control transmission ratio, the rocker transmission ratio of the multi-segment rocker arm, and the system efficiency coefficient.

6. A data processing method for a digital twin platform of an aircraft flight control system, characterized in that, include: Retrieve basic aircraft information and current flight status parameters set by the user; Acquire electrical signals generated when the user operates the control device; The initial aerodynamic forces of the control surface are calculated based on the control surface aerodynamic calculation model, and the control surface deflection angle is calculated based on the control surface aerodynamic-control device force transmission model. The control surface aerodynamic forces are then recalculated based on the control surface aerodynamic calculation model. The control stick feedback force is calculated based on the aerodynamic-control force transmission model of the control surfaces and the control device, and then fed back to the control device to generate corresponding control resistance, providing the user with realistic control feedback.

7. The data processing method for the digital twin platform of the aircraft flight control system according to claim 6, characterized in that, The method further includes: Generate a 3D model based on the aircraft's basic information; Displays the 3D model status of the flight control system under different maneuvers.

8. The data processing method for the digital twin platform of the aircraft flight control system according to claim 7, characterized in that, The basic aircraft information includes the target aircraft type, and the flight status parameters include flight altitude, flight speed, and initial deflection angle of the control surfaces. The specific method for calculating the initial aerodynamic forces of the control surface based on the control surface aerodynamic calculation model includes: The current air density is obtained based on the flight altitude, and the initial lift coefficient is obtained based on the initial deflection angle of the control surfaces. The formula for calculating the aerodynamic forces of the control surface based on the control surface aerodynamic calculation model is as follows: F B = 0.5*C*ρ*v 2 *S; Among them, F B For the control surface aerodynamic force, C is the initial lift coefficient, ρ is the current air density, V is the current flight speed of the aircraft, and s is the area of ​​the aircraft control surface. The specific method for calculating the control surface deflection angle based on the control surface aerodynamic-control device force transmission model includes: Obtain the distance l1 from the control point of the control device to the fulcrum and the distance l2 from the bottom of the rod to the fulcrum; The control transmission ratio i is calculated based on the distance l1 from the control point to the fulcrum and the distance l2 from the bottom of the lever to the fulcrum. A The calculation formula is: i A = l1 / l2； The distance X of the user's moving control device is obtained. Based on the control transmission ratio and the distance of the user's moving control device, the formula for calculating the pole bottom displacement X1 is as follows: X1 = X*i A ; Obtain the input arm length l of the transmission device in and output arm length l out Calculate the rocker arm transmission ratio i of n rocker arm segments. B The calculation formula is: i B1 = l in-1 / l out-1； i B2 = l in-2 / l out-2； ..... i Bn = l in-n / l out-n； Where n is an integer greater than or equal to 2; The formula for calculating the output rod displacement X2 based on the rod bottom displacement X1 and the rocker arm transmission ratio of n segments is as follows: X2 = X1*i B1 *...*i Bn ; The formula for calculating the rudder deflection angle α based on the output rod displacement X2 and the rudder actuation length R is as follows: α = X² / R; The new lift coefficient C(t) is obtained by updating the lift coefficient based on the deflection angle of the control surface.

9. The data processing method for the digital twin platform of the aircraft flight control system according to claim 8, characterized in that, The specific method for calculating the control stick feedback force under the current aircraft flight state and current control state based on the control surface aerodynamic-control device force transmission model includes: The aerodynamic force F of the control surface was calculated based on the new lift coefficient. B (t); Obtain the mean aerodynamic chord length D of the control surface, the control surface actuation length R, and the control gear ratio i. A The feedback force F of the control lever is calculated from the transmission ratio of the n-segment rocker arm and the system efficiency coefficient η. A The formula for calculating (t) is: F A (t)=F B (t)*D / (R*i A *i B1 *···*i Bn *η)。 10. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores a computer program, the computer program including program instructions that, when executed by a processor, cause the processor to perform the method as described in any one of claims 6-9.

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