Airplane high lift device multi-body dynamics analysis load calculation method and device

Abstract

The invention provides an aircraft high lift device multi-body dynamics analysis load calculation method and device, and belongs to the field of aircraft high lift device structure design. Equivalently decomposing each instantaneous aerodynamic load, acting on the aerodynamic surface of the high lift device, of the typical flight profile of the aircraft to corresponding surface nodes of the airfoil structure finite element model of the high lift device; step 2, fitting each instantaneous aerodynamic load on surface nodes of the decomposed finite element model of the airfoil structure of the high lift device into a load-time history function; and step 3, loading the load-time history function obtained by fitting to the multi-body dynamics analysis model of the high-lift device in a follow-up manner to realize multi-body dynamics analysis load calculation of the high-lift device of the airplane. According to the method, the key technical problem in the multi-body dynamic analysis process of the high-lift device is solved, the calculation efficiency is high, the calculation precision is relatively high, and the multi-body dynamic load calculation of the high-lift device can be quickly and accurately completed.

Description

Technical Field

[0001] The present application belongs to the field of aircraft high-lift device structural design, and in particular relates to a method and device for calculating loads in multi-body dynamics analysis of an aircraft high-lift device. Background Art

[0002] Aircraft high-lift devices generally belong to space motion systems, which have many kinematic pairs and complex motion forms. In addition, due to the harsh operating environment and heavy loads, they are prone to a series of problems such as reduced reliability and difficult maintenance and inspection during aircraft use. Studies have shown that dynamic analysis of high-lift devices from the design stage and optimization design based on this are of great significance for improving the reliability of high-lift device mechanisms and reducing flight accidents caused by failures in the control system of high-lift devices.

[0003] During the use of an aircraft, the size and direction of the aerodynamic load acting on the high-lift device will change accordingly due to changes in flight status and changes in the angular position of the high-lift device. Therefore, how to formulate a dynamic analysis load spectrum to simulate the aerodynamic load acting on the high-lift device during the actual use of the aircraft is the key technical problem that must be solved first in the dynamic analysis of the high-lift device. At present, neither the relevant standards nor the airworthiness clauses have clear provisions on the requirements and methods for the compilation of the multi-body dynamic analysis load spectrum of the aircraft high-lift device. The existing method for compiling the aircraft fatigue load spectrum is not applicable because it cannot accurately describe the actual load conditions of the high-lift device during the use of the aircraft. Summary of the invention

[0004] The purpose of the present application is to provide a method and device for calculating loads in multi-body dynamics analysis of an aircraft high-lift device, so as to solve or alleviate at least one problem in the background technology.

[0005] On the one hand, the technical solution of the present application is: a method for calculating loads of multi-body dynamics analysis of an aircraft high-lift device, comprising:

[0006] Step 1: Equivalently decompose each instantaneous aerodynamic load acting on the aerodynamic surface of the high-lift device in a typical flight profile of the aircraft to the surface nodes of the corresponding finite element model of the wing structure of the high-lift device;

[0007] Step 2: Fitting each instantaneous aerodynamic load on the surface node of the decomposed finite element model of the high-lift device wing surface structure into a load-time history function;

[0008] Step three, dynamically load the fitted load-time history function onto the multi-body dynamics analysis model of the high-lift device to realize the load calculation of the multi-body dynamics analysis of the aircraft high-lift device.

[0009] In the preferred embodiment of the present application, step 1, the process of equivalently decomposing each instantaneous aerodynamic load acting on the aerodynamic surface of the high-lift device in the typical flight profile of the aircraft to the surface nodes of the corresponding finite element model of the wing structure of the high-lift device is as follows:

[0010] First, a circular load decomposition region with the aerodynamic load action point as the center and an action diameter of D is defined. The aerodynamic load is decomposed into the load F on the finite element node i within the circular load decomposition region. i Expressed as: F i =F p *w i

[0011] In the formula, F p is the undetermined load in the circular load decomposition area, w i is the node load distribution factor (0≤w i ≤1), expressed as:

[0012]

[0013] F p Determined by the following formula: F total =∑F i =F p *∑w i

[0014] Where D is the diameter of the circular load decomposition area, d i is the distance from node i to the aerodynamic load action point, 0≤d i ≤D / 2, F total is the aerodynamic load on the aerodynamic grid point.

[0015] Then, a load decomposition optimization model for the lift-enhancing device is established. The optimization goal of the load decomposition optimization model for the lift-enhancing device is to minimize the deformation energy of the load-sharing area structure of the lift-enhancing device. The design variable is the diameter D of all circular load decomposition areas on the surface of the lift-enhancing device. The design constraint is the node load of the decomposed lift-enhancing device structure, which satisfies: ∑q i =∑F i *d i ≤ξ

[0016] Where, ξ is the given moment error;

[0017] Finally, by performing load decomposition optimization calculations, the load decomposition results that meet the design requirements are obtained, and the decomposition of the aerodynamic load of the high-lift device is finally completed.

[0018] In the preferred embodiment of the present application, the Lagrange interpolation method is used to perform polynomial fitting on each decomposed instantaneous aerodynamic load to obtain the load-time history function of the surface nodes of the finite element model of the wing structure of the lift-enhancing device:

[0019] Among them, Y i (t) is the load-time history function of node i, F ij is the decomposition result of the aerodynamic load on the jth transient node i, L j (t) is the Lagrange interpolation basis function, which is defined as:

[0020]

[0021] Where t is time and n is the number of discrete points of the instantaneous aerodynamic load of the high-lift device.

[0022] In the preferred embodiment of the present application, step three, the fitted load-time history function is dynamically loaded onto the multi-body dynamics analysis model of the lift-enhancing device using a dynamic loading method based on three-point forces. First, three points are defined, one point F1 determines the position of the force application point, and the other two points F2 and F3 are used to define the direction of the force or the direction of the moment. The magnitude of the force is defined as the fitted load-time history, and the points F2 and F3 that define the direction of the force or moment are fixed together with the wing structure of the lift-enhancing device, so that the loading direction remains unchanged relative to the lift-enhancing device.

[0023] In a second aspect, the present application provides a load calculation device for multi-body dynamics analysis of an aircraft high-lift device, comprising:

[0024] The aerodynamic load decomposition module is used to decompose the instantaneous aerodynamic loads acting on the aerodynamic surface of the high-lift device in the typical flight profile of the aircraft into the corresponding surface nodes of the finite element model of the high-lift device wing surface structure;

[0025] The aerodynamic load fitting module fits each instantaneous aerodynamic load on the surface nodes of the decomposed finite element model of the wing structure of the lift-enhancing device into a load-time history function;

[0026] The random loading module is used to dynamically load the fitted load-time history function onto the multi-body dynamics analysis model of the high-lift device to realize the load calculation of the multi-body dynamics analysis of the aircraft high-lift device.

[0027] In a preferred embodiment of the present application, the process by which the aerodynamic load decomposition module decomposes each instantaneous aerodynamic load acting on the aerodynamic surface of the high-lift device in the typical flight profile of the aircraft into the corresponding surface nodes of the finite element model of the high-lift device wing structure is as follows:

[0028] First, a circular load decomposition region with the aerodynamic load action point as the center and an action diameter of D is defined. The aerodynamic load is decomposed into the load F on the finite element node i within the circular load decomposition region. i Expressed as: F i =F p *wi

[0029] In the formula, F p is the undetermined load in the circular load decomposition area, w i is the node load distribution factor (0≤w i ≤1), expressed as:

[0030]

[0031] F p Determined by the following formula: F total =∑F i =F p *∑w i

[0032] Where D is the diameter of the circular load decomposition area, d i is the distance from node i to the aerodynamic load action point, 0≤d i ≤D / 2, F total is the aerodynamic load on the aerodynamic grid point.

[0033] Then, a load decomposition optimization model for the lift-enhancing device is established. The optimization goal of the load decomposition optimization model for the lift-enhancing device is to minimize the deformation energy of the load-sharing area structure of the lift-enhancing device. The design variable is the diameter D of all circular load decomposition areas on the surface of the lift-enhancing device. The design constraint is the node load of the decomposed lift-enhancing device structure, which satisfies: ∑q i =∑F i *d i ≤ξ

[0034] Where, ξ is the given moment error;

[0035] Finally, by performing load decomposition optimization calculations, the load decomposition results that meet the design requirements are obtained, and the decomposition of the aerodynamic load of the high-lift device is finally completed.

[0036] In a preferred embodiment of the present application, the aerodynamic load fitting module uses the Lagrange interpolation method to perform polynomial fitting on each decomposed instantaneous aerodynamic load to obtain the load-time history function of the surface nodes of the finite element model of the wing structure of the lift-enhancing device:

[0037] Among them, Y i (t) is the load-time history function of node i, F ij is the decomposition result of the aerodynamic load on the jth transient node i, L j (t) is the Lagrange interpolation basis function, which is defined as:

[0038]

[0039] Where t is time and n is the number of discrete points of the instantaneous aerodynamic load of the high-lift device.

[0040] In the preferred embodiment of the present application, the random loading module dynamically loads the fitted load-time history function onto the multi-body dynamics analysis model of the lift-enhancing device using a dynamic loading method based on three-point forces. First, three points are defined, one point F1 determines the position of the force application point, and the other two points F2 and F3 are used to define the direction of the force or the direction of the moment. The magnitude of the force is defined as the fitted load-time history, and the points F2 and F3 that define the direction of the force or moment are fixed together with the wing structure of the lift-enhancing device, so that the loading direction remains unchanged relative to the lift-enhancing device.

[0041] In a third aspect, the present application provides an electronic device, including:

[0042] one or more processors;

[0043] Memory;

[0044] One or more application programs are stored in the memory and configured to be executed by the one or more processors, and the one or more application programs are configured to implement the aircraft high-lift device multi-body dynamics analysis load calculation method as described in any one of the above items.

[0045] In the last aspect, the present application provides a computer storage medium, which stores at least one instruction, at least one program, a code set or an instruction set, and the at least one instruction, the at least one program, the code set or the instruction set is loaded and executed by the processor to implement the aircraft high-lift device multi-body dynamics analysis load calculation method as described in any of the above items.

[0046] The solution of the present application includes aerodynamic load decomposition, load fitting and follow-up loading of the lift-enhancing device, which solves the key technical problems in the multi-body dynamics analysis process of the lift-enhancing device. The proposed distributed node aerodynamic load method is used for aerodynamic load decomposition. It has been verified in practice that it has high calculation efficiency and high calculation accuracy, and can quickly and accurately complete the multi-body dynamics load calculation of the lift-enhancing device. BRIEF DESCRIPTION OF THE DRAWINGS

[0047] In order to more clearly illustrate the technical solution provided by the present application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of the present application.

[0048] Figure 1 This is a flow chart of a method for calculating loads in multi-body dynamics analysis of an aircraft high-lift device of the present application.

[0049] Figure 2 Schematic diagram of a circular load decomposition area in an embodiment of the present application.

[0050] Figure 3 It is a schematic diagram of three-point forces in one embodiment of the present application.

[0051] Figure 4 Schematic diagram of the composition of a load calculation device for multi-body dynamics analysis of an aircraft high-lift device in one embodiment of the present application.

[0052] Figure 5 A schematic diagram of an electronic device according to an embodiment of the present application. DETAILED DESCRIPTION

[0053] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below in conjunction with the drawings in the embodiments of this application.

[0054] The present application provides a method for calculating loads in multi-body dynamics analysis of an aircraft high-lift device. The method is based on transient aerodynamic loads acting on the aerodynamic surface of the high-lift device in a typical flight profile of the tailored aircraft. The typical flight profile of the aircraft related to the high-lift device includes take-off, climb, cruise, descent, approach and landing.

[0055] like Figure 1 As shown, the present application provides a method for calculating loads in multi-body dynamics analysis of an aircraft high-lift device, including the following process:

[0056] Step 1: Equivalently decompose each instantaneous aerodynamic load acting on the aerodynamic surface of the high-lift device in a typical flight profile of the aircraft to the surface nodes of the corresponding finite element model of the high-lift device wing surface structure.

[0057] 1.1) First, if Figure 2 As shown in the figure, a circular load decomposition area with a diameter D as the center and aerodynamic load action point is defined. The aerodynamic load is decomposed into the load F on the finite element node i within the circular load decomposition area. i It can be expressed as: F i =F p *w i ;

[0058] In the formula, F p is the undetermined load in the circular load decomposition area, w i is the node load distribution factor (0≤w i ≤1), which can be expressed as:

[0059]

[0060] F p Determined by the following formula: F total =∑F i =F p *∑wi

[0061] Where D is the diameter of the circular load decomposition area, d i is the distance from node i to the aerodynamic load action point, 0≤d i ≤D / 2, F total is the aerodynamic load on the aerodynamic grid point.

[0062] 1.2) Then, the load decomposition optimization model of the high-lift device is established:

[0063] The optimization goal is to minimize the deformation energy of the structure in the load-sharing area of ​​the high-lift device;

[0064] The design variable is the diameter D of all circular load decomposition areas on the surface of the high-lift device;

[0065] The design constraint is that the node load of the decomposed high-lift device structure satisfies the following formula:

[0066] ∑q i =∑F i *d i ≤ξ

[0067] Where ξ is the given torque error.

[0068] 1.3) Finally, by performing load decomposition optimization calculations, the load decomposition results that meet the design requirements are obtained, and the decomposition of the aerodynamic load of the high-lift device is finally completed.

[0069] Step 2: Fit each instantaneous aerodynamic load on the surface nodes of the decomposed finite element model of the high-lift device wing surface structure into a load-time history function.

[0070] In this application, the Lagrange interpolation method is used to perform polynomial fitting on the decomposed instantaneous aerodynamic loads to obtain the load-time history function of the surface nodes of the finite element model of the wing structure of the lift-enhancing device:

[0071] Among them, Y i (t) is the load-time history function of node i, F ij is the decomposition result of the aerodynamic load on the jth transient node i, L j (t) is the Lagrange interpolation basis function, which is defined as:

[0072]

[0073] Where t is time and n is the number of discrete points of the instantaneous aerodynamic load of the high-lift device.

[0074] Step three, dynamically load the fitted load-time history function onto the multi-body dynamics analysis model of the high-lift device to realize the load calculation of the multi-body dynamics analysis of the aircraft high-lift device.

[0075] like Figure 3 As shown, the dynamic loading is based on the three-point force method, which defines three points, one point F1 determines the position of the force application point, and the other two points F2 and F3 are used to define the direction of the force or the direction of the moment. The magnitude of the force is defined as the fitted load-time history, and the points F2 and F3 that define the direction of the force or moment are fixed together with the wing structure of the high-lift device, so that the loading direction remains unchanged relative to the high-lift device.

[0076] On this basis, if Figure 3 The present application provides a load calculation device 100 for multi-body dynamics analysis of an aircraft high-lift device, and the device 100 includes:

[0077] The aerodynamic load decomposition module 101 is used to decompose each instantaneous aerodynamic load acting on the aerodynamic surface of the high-lift device in the typical flight profile of the aircraft into the corresponding surface nodes of the finite element model of the high-lift device wing surface structure;

[0078] The aerodynamic load fitting module 102 fits each instantaneous aerodynamic load on the surface node of the decomposed finite element model of the airfoil structure of the lift-enhancing device into a load-time history function;

[0079] The random loading module 103 is used to dynamically load the fitted load-time history function onto the multi-body dynamics analysis model of the high-lift device to realize the multi-body dynamics analysis load calculation of the aircraft high-lift device.

[0080] For the calculation process of each module of the aircraft control surface anti-stuck hinge fixed force torque calculation device of the present application, specific reference can be made to the process steps of the aircraft lift-enhancing device multi-body dynamics analysis load calculation method of the present application, which will not be repeated here.

[0081] like Figure 4 As shown, an embodiment of the present application also provides an electronic device 200, which includes a processor 201, which can perform various appropriate actions and processes according to a program stored in a read-only memory (ROM) 202 or a program loaded from a storage device 108 to a random access memory (RAM) 203. Processor 101 may include, for example, a general-purpose microprocessor (such as a CPU), an instruction set processor and / or a related chipset and / or a special-purpose microprocessor (for example, an application-specific integrated circuit (ASIC)), etc. Processor 201 may also include an onboard memory for caching purposes. Processor 201 may include a single processing unit or multiple processing units for performing different actions of the method flow according to an embodiment of the present disclosure.

[0082] In RAM 203, various programs and data required for the operation of electronic device 200 are stored. Processor 201, ROM 202 and RAM 203 are connected to each other via bus 204. Processor 201 performs various operations of the method flow according to the embodiment of the present disclosure by executing the program in ROM 202 and / or RAM 203. It should be noted that the program can also be stored in one or more memories other than ROM 202 and RAM 203. Processor 201 can also perform various operations of the method or flow according to the embodiment of the application by executing the program stored in the one or more memories.

[0083] According to an embodiment of the present application, the electronic device 200 may further include an input / output (I / O) interface 205, which is also connected to the bus 204. The electronic device 200 may further include one or more of the following components connected to the I / O interface 205: an input device 206 including a keyboard, a mouse, etc.; an output device 207 including a cathode ray tube (CRT), a liquid crystal display (LCD), etc., and a speaker, etc.; a storage device 208 including a hard disk, etc.; and a communication device 209 including a network interface card such as a LAN card, a modem, etc. The communication device 209 performs communication processing via a network such as the Internet. A drive is also connected to the I / O interface 205 as needed. Removable media, such as magnetic disks, optical disks, magneto-optical disks, semiconductor memories, etc., are installed on the drive as needed so that the computer program read therefrom is installed into the storage device 208 as needed.

[0084] The present application also provides a computer-readable storage medium, which may be included in the device / apparatus / system described in the above embodiments; or may exist independently without being assembled into the device / apparatus / system. The above computer-readable storage medium carries one or more programs, and when the above one or more programs are executed, various operations of the above methods or processes according to the embodiments of the present application are implemented.

[0085] According to an embodiment of the present application, the computer-readable storage medium may be a non-volatile computer-readable storage medium, for example, may include but is not limited to: a portable computer disk, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), a portable compact disk read-only memory (CD ROM), an optical storage device, a magnetic storage device, or any suitable combination thereof. In the present application, a computer-readable storage medium may be any tangible medium containing or storing a program, which may be used by or in combination with an instruction execution system, an apparatus or a device. For example, according to an embodiment of the present application, a computer-readable storage medium may include the ROM 202 and / or RAM 203 described above and / or one or more memories other than ROM 102 and RAM 203.

[0086] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A method for calculating loads in multi-body dynamics analysis of aircraft high-lift devices, characterized in that: include: Step 1: Equivalently decompose each instantaneous aerodynamic load acting on the aerodynamic surface of the high-lift device in a typical flight profile of the aircraft to the surface nodes of the corresponding finite element model of the wing structure of the high-lift device; Step 2: Fitting each instantaneous aerodynamic load on the surface node of the decomposed finite element model of the high-lift device wing surface structure into a load-time history function; Step three, dynamically load the fitted load-time history function onto the multi-body dynamics analysis model of the high-lift device to realize the load calculation of the multi-body dynamics analysis of the aircraft high-lift device.

2. The method for calculating loads of multi-body dynamics analysis of aircraft high-lift devices according to claim 1, characterized in that: Step 1: The process of equivalently decomposing each instantaneous aerodynamic load acting on the aerodynamic surface of the high-lift device in the typical flight profile of the aircraft to the surface nodes of the corresponding finite element model of the wing structure of the high-lift device is as follows: First, a circular load decomposition region with the aerodynamic load action point as the center and an action diameter of D is defined. The aerodynamic load is decomposed into the load F on the finite element node i within the circular load decomposition region. i Expressed as: F i =F p *w i In the formula, F p is the undetermined load in the circular load decomposition area, w i is the node load distribution factor (0≤w i ≤1), expressed as: F p Determined by the following formula: F total =∑F i =F p *∑w i Where D is the diameter of the circular load decomposition area, d i is the distance from node i to the aerodynamic load action point, 0≤d i ≤D / 2, F total is the aerodynamic load on the aerodynamic grid point. Then, a load decomposition optimization model for the lift-enhancing device is established. The optimization goal of the load decomposition optimization model for the lift-enhancing device is to minimize the deformation energy of the load-sharing area structure of the lift-enhancing device. The design variable is the diameter D of all circular load decomposition areas on the surface of the lift-enhancing device. The design constraint is the node load of the decomposed lift-enhancing device structure, which satisfies: ∑q i =∑F i *d i ≤ξ Where, ξ is the given moment error; Finally, by performing load decomposition optimization calculations, the load decomposition results that meet the design requirements are obtained, and the decomposition of the aerodynamic load of the high-lift device is finally completed.

3. The method for calculating loads of multi-body dynamics analysis of aircraft high-lift devices according to claim 2, characterized in that: The Lagrange interpolation method is used to perform polynomial fitting on the decomposed instantaneous aerodynamic loads, and the load-time history function of the surface nodes of the finite element model of the lift-enhancing device wing structure is obtained: Among them, Y i (t) is the load-time history function of node i, F ij is the decomposition result of the aerodynamic load on the transient node i at the jth moment, L j (t) is the Lagrange interpolation basis function, which is defined as: Where t is time and n is the number of discrete points of the instantaneous aerodynamic load of the high-lift device.

4. The method for calculating loads of multi-body dynamics analysis of aircraft high-lift devices according to claim 3, characterized in that: Step 3: Load the fitted load-time history function onto the multi-body dynamics analysis model of the lift-enhancing device using a three-point force-based dynamic loading method. First, define three points, one of which, point F1, determines the position of the force point, and the other two points, F2 and F3, are used to define the direction of the force or the direction of the moment. The magnitude of the force is defined as the fitted load-time history, and the points F2 and F3 that define the direction of the force or moment are fixed together with the wing structure of the lift-enhancing device, so that the loading direction remains unchanged relative to the lift-enhancing device.

5. A load calculation device for multi-body dynamics analysis of aircraft lift-enhancing devices, characterized in that: include: The aerodynamic load decomposition module is used to decompose the instantaneous aerodynamic loads acting on the aerodynamic surface of the high-lift device in the typical flight profile of the aircraft into the corresponding surface nodes of the finite element model of the high-lift device wing surface structure; The aerodynamic load fitting module fits each instantaneous aerodynamic load on the surface nodes of the decomposed finite element model of the lift-enhancing device wing surface structure into a load-time history function; The random loading module is used to dynamically load the fitted load-time history function onto the multi-body dynamics analysis model of the high-lift device to realize the load calculation of the multi-body dynamics analysis of the aircraft high-lift device.

6. The aircraft high-lift device multi-body dynamics analysis load calculation device according to claim 5, characterized in that: The process of the aerodynamic load decomposition module equivalently decomposing each instantaneous aerodynamic load acting on the aerodynamic surface of the high-lift device in the typical flight profile of the aircraft to the surface nodes of the corresponding finite element model of the wing structure of the high-lift device is as follows: First, a circular load decomposition region with the aerodynamic load action point as the center and an action diameter of D is defined. The aerodynamic load is decomposed into the load F on the finite element node i within the circular load decomposition region. i Expressed as: F i =F p *w i In the formula, F p is the undetermined load in the circular load decomposition area, w i is the node load distribution factor (0≤w i ≤1), expressed as: F p Determined by the following formula: F total =∑F i =F p *∑w i Where D is the diameter of the circular load decomposition area, d i is the distance from node i to the aerodynamic load action point, 0≤d i ≤D / 2, F total is the aerodynamic load on the aerodynamic grid point. Then, a load decomposition optimization model for the lift-enhancing device is established. The optimization goal of the load decomposition optimization model for the lift-enhancing device is to minimize the deformation energy of the load-sharing area structure of the lift-enhancing device. The design variable is the diameter D of all circular load decomposition areas on the surface of the lift-enhancing device. The design constraint is the node load of the decomposed lift-enhancing device structure, which satisfies: ∑q i =∑F i *d i ≤ξ Where, ξ is the given moment error; Finally, by performing load decomposition optimization calculations, the load decomposition results that meet the design requirements are obtained, and the decomposition of the aerodynamic load of the high-lift device is finally completed.

7. The aircraft high-lift device multi-body dynamics analysis load calculation device according to claim 6, characterized in that: The aerodynamic load fitting module uses the Lagrange interpolation method to perform polynomial fitting on each decomposed instantaneous aerodynamic load to obtain the load-time history function of the surface nodes of the finite element model of the wing structure of the lift-enhancing device: Among them, Y i (t) is the load-time history function of node i, F ij is the decomposition result of the aerodynamic load on the jth transient node i, L j (t) is the Lagrange interpolation basis function, which is defined as: Where t is time and n is the number of discrete points of the instantaneous aerodynamic load of the high-lift device.

8. The aircraft high-lift device multi-body dynamics analysis load calculation device according to claim 7, characterized in that: The random loading module dynamically loads the fitted load-time history function onto the multi-body dynamics analysis model of the lift-enhancing device using a dynamic loading method based on three-point forces. First, three points are defined, one point F1 determines the position of the force application point, and the other two points F2 and F3 are used to define the direction of the force or the direction of the moment. The magnitude of the force is defined as the fitted load-time history, and the points F2 and F3 that define the direction of the force or moment are fixed together with the wing structure of the lift-enhancing device, so that the loading direction remains unchanged relative to the lift-enhancing device.

9. An electronic device, characterized in that: include: one or more processors; Memory; One or more application programs, the one or more application programs are stored in the memory and are configured to be executed by the one or more processors, the one or more application programs are configured to implement the aircraft high-lift device multi-body dynamics analysis load calculation method according to any one of claims 1 to 4.

10. A computer storage medium, characterized in that: The computer storage medium stores at least one instruction, at least one program, a code set or an instruction set, and the at least one instruction, the at least one program, the code set or the instruction set are loaded and executed by the processor to implement the aircraft high-lift device multi-body dynamics analysis load calculation method according to any one of claims 1 to 4.

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