CN-121982955-A - Digital twin platform of aircraft flight control system, data processing method and medium thereof

CN121982955ACN 121982955 ACN121982955 ACN 121982955ACN-121982955-A

Abstract

The invention discloses a digital twin platform of an aircraft flight control system, a data processing method and a medium thereof, relating to the technical field of aircraft simulation training, wherein the platform comprises a parameter setting unit, a control unit and a control unit, wherein the parameter setting unit 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 initial control surface aerodynamic force according to the control surface aerodynamic force calculation model, calculating a control surface deflection angle according to the control surface aerodynamic force transmission model and recalculating the control surface aerodynamic force according to the control surface aerodynamic force calculation model, and the sensing force feedback unit is used for calculating control lever 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 the generated corresponding control resistance to the control device. The platform not only saves the economic cost and the occupied area for building the solid iron bird test bed, but also can test the performance of the flight control system of the aircraft under different flight states.

Inventors

QIN WENFENG
LI HAOYU
LI CHUNSHENG

Assignees

中国民用航空飞行学院

Dates

Publication Date: 20260505
Application Date: 20260408

Claims (10)

1. The digital twin platform of the aircraft flight control system is characterized by comprising a state analysis module, wherein the state analysis module comprises a parameter setting unit, a control signal acquisition unit, a calculation unit and a force sensing feedback unit, The parameter setting unit is used for setting aircraft basic information and current flight state parameters; The manipulation signal acquisition unit is used for acquiring an electric signal generated when a user operates the manipulation device; The calculation unit is used for calculating initial control surface aerodynamic force according to the control surface aerodynamic force calculation model, calculating a control surface deflection angle according to the control surface aerodynamic force transmission model, and recalculating the control surface aerodynamic force according to the control surface aerodynamic force calculation model; The sensing force feedback unit is used for calculating the feedback force of the control rod in the current aircraft flight state and the current control state according to the control surface aerodynamic force-control device force transmission model, feeding back the feedback force to the control device to generate corresponding control resistance, and providing real control feedback for a user.
2. The aircraft flight control system digital twinning platform of claim 1, further comprising a status display module including a flight control system 3D model for generating a three-dimensional model from aircraft basic information and a display unit for displaying the status of the flight control system 3D model under different maneuvers.
3. The aircraft flight control system digital twin platform of claim 1or2, wherein the aircraft base information comprises a target model and the flight status parameters comprise altitude, speed and initial deflection angle of the control surface.
4. The digital twin platform of an aircraft flight control system according to claim 3, wherein the computing unit comprises a first computing subunit, the first computing subunit comprises a control plane aerodynamic force computing model, the control plane aerodynamic force computing model obtains a flight air density according to a flight altitude, obtains a lift coefficient according to a control plane deflection angle, and calculates a control plane aerodynamic force according to the flight air density, an aircraft flight speed, the lift coefficient and an aircraft control plane area; The control surface pneumatic-operating device force transmission model calculates an operating transmission ratio according to the distance between an operating point of an operating device and a fulcrum and the distance between the operating point of the operating device and a lever bottom, calculates the lever bottom displacement according to the operating transmission ratio and the distance of a user moving the operating device, obtains a rocker arm transmission ratio according to the ratio of the input arm length to the output arm length of the transmission device, multiplies the lever bottom displacement by the rocker arm transmission ratio of a plurality of sections of rocker arms to obtain an output lever push displacement, and divides the output lever push displacement by the control surface operating length to obtain a control surface deflection angle.
5. The aircraft flight control system digital twin platform of claim 4, wherein the force sensing feedback unit comprises a feedback force calculation subunit for calculating the lever feedback force based on the control surface aerodynamic force, the control surface average aerodynamic chord length, the control surface actuation length, the control transmission ratio, the rocker transmission ratio of the multi-segment rocker, and the system efficiency coefficient.
6. A method of processing data for a digital twin platform of an aircraft flight control system, comprising: Acquiring airplane basic information and current flight state parameters set by a user; Acquiring an electric signal generated when a user operates the operating device; calculating initial control surface aerodynamic force according to the control surface aerodynamic force calculation model, calculating a control surface deflection angle according to the control surface aerodynamic force transmission model, and recalculating the control surface aerodynamic force according to the control surface aerodynamic force calculation model; And calculating the current aircraft flight state and the feedback force of the control rod under the current control state according to the control surface aerodynamic force-control device force transmission model, feeding back the feedback force to the control device to generate corresponding control resistance, and providing real control feedback for a user.
7. The method of data processing for an aircraft flight control system digital twin platform of claim 6, further comprising: Generating a three-dimensional model according to the aircraft basic information; and displaying the 3D model states of the flight control system under different control.
8. The method for processing data of a digital twin platform of an aircraft flight control system according to claim 7, wherein the aircraft basic information comprises a target model, and the flight status parameters comprise a flight altitude, a flight speed and a control surface initial deflection angle; the specific method for calculating the initial control surface aerodynamic force according to the control surface aerodynamic force calculation model comprises the following steps: acquiring current air density according to the flying height, and acquiring an initial lift coefficient according to the initial deflection angle of the control surface; The calculation formula for calculating the aerodynamic force of the control surface according to the aerodynamic force calculation model of the control surface is as follows: F B = 0.5*C*ρ*v 2 *S; Wherein F B is the aerodynamic force of the control surface, 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 control surface area of the aircraft; the specific method for calculating the deflection angle of the control surface according to the force transmission model of the control surface pneumatic-control device comprises the following steps: Acquiring a distance l 1 between an operating point of the operating device and a fulcrum and a distance l 2 between a rod bottom and the fulcrum; the calculation formula for calculating the control transmission ratio i A according to the control point distance l 1 from the fulcrum and the lever bottom distance l 2 of the control device is as follows: i A = l 1 /l 2 ; the distance X of the user moving the operating device is obtained, and the calculation formula of the pole bottom displacement X 1 is obtained according to the operating transmission ratio and the distance of the user moving the operating device, wherein the calculation formula is as follows: X 1 = X*i A ; The input arm length l in and the output arm length l out of the transmission device are obtained, and the calculation formula for calculating the rocker arm transmission ratio i B of the n-section rocker arm is as follows: i B1 = l in-1 /l out-1; i B2 = l in-2 /l out-2; ..... i Bn = l in-n /l out-n; wherein n is an integer of 2 or more; The calculation formula for calculating the push-out displacement X 2 of the output rod according to the rocker arm transmission ratio of the bottom displacement X 1 and the n sections of rocker arms is as follows: X 2 = X 1 *i B1 *...*i Bn ; the calculation formula for calculating the deflection angle alpha of the control surface according to the push displacement X 2 of the output rod and the control surface actuation length R is as follows: α = X 2 /R; And updating the lift coefficient according to the deflection angle of the control surface to obtain a new lift coefficient C (t).
9. The method for processing data of a digital twin platform of an aircraft flight control system according to claim 8, wherein the specific method for calculating the feedback force of the control lever in the current aircraft flight state and the current control state according to the control surface aerodynamic force-control device force transmission model comprises the following steps: Calculating control surface aerodynamic force F B (t) according to the new lift coefficient; The calculation formula for calculating the feedback force F A (t) of the control rod by acquiring the average aerodynamic chord length D of the control surface, the actuation length R of the control surface, the control transmission ratio i A and the rocker transmission ratio of n sections of rocker arms and the system efficiency coefficient eta is as follows: 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 comprising program instructions which, when executed by a processor, cause the processor to perform the method of any of claims 6-9.

Description

Digital twin platform of aircraft flight control system, data processing method and medium thereof Technical Field The invention relates to the technical field of aircraft simulation training, in particular to a digital twin platform of an aircraft flight control system, a data processing method and a medium thereof. Background Flight control systems are among the most important systems of an aircraft. In the development and design process and maintenance capability training of an aircraft, an iron bird test bed of a target aircraft needs to be established. The iron bird test bed is used for installing a flight control system of an airplane on a fixed rack to display and test related functions. The iron bird test bed can generally re-etch the critical dimension of the flight control system of the target aircraft in a ratio of 1:1, so that the occupied area is large, the control relation of the flight control system is mainly tested, if the states of the flight control system in different flight states are required to be tested, a force applying device is additionally arranged on a control surface, the equipment investment cost is increased, and the complexity of the test operation is improved. Disclosure of Invention The invention aims to provide a digital twin platform of an aircraft flight control system, a data processing method and a medium thereof, which solve the problems of high cost and large occupied area of a solid iron bird test bed and the problem that the performance of the flight control system of a test aircraft in different flight states needs to be additionally provided with a force applying unit. The invention is realized by the following technical scheme: In a first aspect, the invention provides a digital twin platform of an aircraft flight control system, which comprises a state analysis module, a control signal acquisition unit, a calculation unit and a force sensing feedback unit, The parameter setting unit is used for setting aircraft basic information and current flight state parameters; The manipulation signal acquisition unit is used for acquiring an electric signal generated when a user operates the manipulation device; The calculation unit is used for calculating initial control surface aerodynamic force according to the control surface aerodynamic force calculation model, calculating a control surface deflection angle according to the control surface aerodynamic force transmission model, and recalculating the control surface aerodynamic force according to the control surface aerodynamic force calculation model; The sensing force feedback unit is used for calculating the feedback force of the control rod in the current aircraft flight state and the current control state according to the control surface aerodynamic force-control device force transmission model, feeding back the feedback force to the control device to generate corresponding control resistance, and providing real control feedback for a user. Further, the system further comprises a state display module, wherein the state display module comprises a flight control system 3D model and a display unit, the flight control system 3D model is used for generating a three-dimensional model according to aircraft basic information, and the display unit is used for displaying the states of the flight control system 3D model under different control. Further, the aircraft basic information comprises a target model, and the flight state parameters comprise flight altitude, flight speed and control surface initial deflection angle. Further, the calculating unit comprises a first calculating subunit, the first calculating subunit comprises a control surface aerodynamic force calculating model, the control surface aerodynamic force calculating model obtains flying air density according to flying height, obtains lift coefficient according to the deflection angle of the control surface, and calculates control surface aerodynamic force according to the flying air density, the flying speed of the airplane, the lift coefficient and the control surface area of the airplane; The calculation unit further comprises a second calculation subunit, the second calculation subunit comprises a control surface pneumatic-operating device force transmission model, the control surface pneumatic-operating device force transmission model calculates an operating transmission ratio according to the distance between an operating point of an operating device and a fulcrum and the distance between the operating point of the operating device and a lever bottom, lever bottom displacement is calculated according to the operating transmission ratio and the distance of a user moving the operating device, a rocker arm transmission ratio is further obtained according to the ratio of the input arm length to the output arm length of the transmission device, the lever bottom displacement is multiplied by the multi-section rocker arm transmission ratio to obtain output le