A load calculation method and device for multi-body dynamics analysis of an aircraft high-lift device

Abstract

The application provides a load calculation method and device for a multi-body dynamics analysis of an aircraft high-lift device, and belongs to the field of structural design of an aircraft high-lift device. The method comprises the following steps: step one, equivalent decomposition of each instantaneous aerodynamic load of a typical flight profile of an aircraft acting on the aerodynamic surface of the high-lift device to the surface nodes of a high-lift device airfoil structure finite element model; step two, fitting of each instantaneous aerodynamic load on the surface nodes of the high-lift device airfoil structure finite element model after decomposition into a load-time history function; and step three, dynamic loading of the fitted load-time history function on a multi-body dynamics analysis model of the high-lift device to realize load calculation for the multi-body dynamics analysis of the aircraft high-lift device. The application solves the key technical problems in the multi-body dynamics analysis of the high-lift device, has high calculation efficiency and high calculation accuracy, and can quickly and accurately complete the multi-body dynamics load calculation of the high-lift device.

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 aircraft high-lift devices. Background Art

[0002] Aircraft high-lift devices are generally space motion systems with numerous kinematic pairs and complex motion patterns. Furthermore, due to their harsh operating environments and heavy loads, these systems can easily lead to a range of issues, including reduced reliability and difficult maintenance and inspections. Research has shown that dynamic analysis of high-lift devices from the outset of the design phase, coupled with optimized design, is crucial for improving their reliability and reducing flight accidents caused by malfunctions in their control systems.

[0003] During aircraft operation, the magnitude and direction of the aerodynamic loads acting on the high-lift device change accordingly due to changes in flight state and the angular position of the high-lift device. Therefore, developing a dynamic analysis load spectrum to simulate the aerodynamic loads acting on the high-lift device during actual aircraft operation is a key technical issue to be addressed in dynamic analysis of high-lift devices. Currently, neither relevant standards nor airworthiness regulations clearly define the requirements and methods for compiling load spectra for multi-body dynamic analysis of aircraft high-lift devices. Existing methods for compiling aircraft fatigue load spectra are not applicable because they cannot accurately describe the actual loading conditions of the high-lift device during aircraft operation. 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 art.

[0005] On the one hand, the technical solution of the present application is: a method for calculating loads in 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 during a typical flight profile of the aircraft into corresponding surface nodes of a finite element model of the high-lift device wing structure;

[0007] Step 2: Fitting the instantaneous aerodynamic loads on the surface nodes of the decomposed finite element model of the high-lift device wing 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 a 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 during a typical flight profile of the aircraft into corresponding surface nodes of the finite element model of the high-lift device wing structure is as follows:

[0010] First, a circular load decomposition area 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 area. i Expressed as: F i =F p *w i

[0011] Where, 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 high-lift device is established. The optimization objective of the load decomposition optimization model is to minimize the deformation energy of the load distribution area structure of the high-lift device. The design variable is the diameter D of all circular load decomposition areas on the surface of the high-lift device. The design constraint is the node load of the decomposed high-lift 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 a preferred embodiment of the present 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 high-lift device wing structure:

[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 a preferred embodiment of this application, step three involves dynamically loading the fitted load-time history function onto the multi-body dynamics analysis model of the high-lift device. This method employs a three-point force-based dynamic loading method. First, three points are defined: one point, F1, determines the location of the force application point, while the other two, F2 and F3, define the force or torque direction. The force magnitude is defined by the fitted load-time history. Points F2 and F3, which define the force or torque direction, are fixed to the high-lift device's wing structure, ensuring that the loading direction remains constant relative to the high-lift 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 the instantaneous aerodynamic loads on the surface nodes of the decomposed finite element model of the high-lift device wing structure 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 aerodynamic load decomposition module decomposes each instantaneous aerodynamic load acting on the aerodynamic surface of the high-lift device in a typical flight profile of the aircraft into the corresponding surface nodes of the finite element model of the high-lift device wing surface structure in the following process:

[0028] First, a circular load decomposition area 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 area. i Expressed as: F i =Fp *w i

[0029] Where, 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 high-lift device is established. The optimization objective of the load decomposition optimization model is to minimize the deformation energy of the load distribution area structure of the high-lift device. The design variable is the diameter D of all circular load decomposition areas on the surface of the high-lift device. The design constraint is the node load of the decomposed high-lift 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 the decomposed instantaneous aerodynamic loads to obtain the load-time history function of the surface nodes of the finite element model of the high-lift device airfoil structure:

[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 a preferred embodiment of this application, the random loading module dynamically applies the fitted load-time history function to the multi-body dynamics analysis model of the high-lift device using a three-point force-based dynamic loading method. Three points are first defined: one point, F1, determines the location of the force application point, while the other two, F2 and F3, define the force or torque direction. The force magnitude is defined by the fitted load-time history. Points F2 and F3, which define the force or torque direction, are fixed to the high-lift device's wing structure, ensuring that the loading direction remains constant relative to the high-lift device.

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

[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, wherein the one or more application programs are configured to implement the method for calculating loads in multi-body dynamics analysis of an aircraft high-lift device as described in any one of the above items.

[0045] In a final aspect, the present application provides a computer storage medium storing at least one instruction, at least one program, a code set, or an instruction set, wherein 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 method for calculating loads in multi-body dynamics analysis of an aircraft high-lift device as described in any one of the above items.

[0046] The solution of this application includes aerodynamic load decomposition, load fitting and follow-up loading of the lift-enhancing device, which solves the key technical difficulties 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 dynamic load calculation of the lift-enhancing device. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0048] Figure 1 This is a flow chart of the load calculation method for the multi-body dynamics analysis of the aircraft high-lift device of this application.

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

[0050] Figure 3 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 This is 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] This application provides a load calculation method for multi-body dynamics analysis of an aircraft high-lift device. This method is based on the transient aerodynamic loads acting on the aerodynamic surfaces of the high-lift device during a tailored typical aircraft flight profile. Typical aircraft flight profiles related to the high-lift device include takeoff, 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 of D and a center of the 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] Where, 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 =∑Fi =F p *∑w i

[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, establish the load decomposition optimization model of the high-lift device:

[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, a load decomposition result that meets the design requirements is obtained, and the aerodynamic load decomposition 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 high-lift device wing structure:

[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, dynamic loading is based on a three-point force method, which defines three points: one point, F1, determines the location of the force application point, and the other two points, F2 and F3, define the direction of the force or moment. The magnitude of the force is defined by the fitted load-time history. Points F2 and F3, which define the direction of the force or moment, are fixed to the high-lift device wing structure, ensuring that the loading direction remains constant 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, the device 100 comprising:

[0077] The aerodynamic load decomposition module 101 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 airfoil structure;

[0078] The aerodynamic load fitting module 102 fits each instantaneous aerodynamic load on the surface nodes of the decomposed finite element model of the high-lift device airfoil structure 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 implement load calculation for the multi-body dynamics analysis of the aircraft high-lift device.

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

[0081] like Figure 4 As shown, an embodiment of the present application further provides an electronic device 200, which includes a processing device 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 208 into a random access memory (RAM) 203. The processing device 201 may, for example, include a general-purpose microprocessor (such as a CPU), an instruction set processor and / or a related chipset and / or a special-purpose microprocessor (such as an application-specific integrated circuit (ASIC)), etc. The processing device 201 may also include an onboard memory for caching purposes. The processing device 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. Processing device 201 performs various operations of the method flow according to the embodiment of the present disclosure by executing the programs 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. Processing device 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), 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 in the drive as needed so that computer programs read therefrom can be installed into the storage device 208 as needed.

[0084] This 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 and not be incorporated into the device / apparatus / system. The computer-readable storage medium carries one or more programs, and when the one or more programs are executed, the various operations of the above methods or processes according to the embodiments of this 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, it 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 that can be used by or in conjunction with an instruction execution system, apparatus, or device. For example, according to an embodiment of the present application, the computer-readable storage medium may include the ROM 202 and / or RAM 203 described above and / or one or more memories other than ROM 202 and RAM 203.

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

Claims

1. A load calculation method for 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 during a typical flight profile of the aircraft into corresponding surface nodes of a finite element model of the high-lift device wing structure; Step 2: The instantaneous aerodynamic loads on the surface nodes of the decomposed finite element model of the high-lift device wing structure are fitted into a load-time history function using the Lagrange interpolation method; Step 3: 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; Among them, the process of equivalently decomposing each instantaneous aerodynamic load acting on the aerodynamic surface of the high-lift device during the typical flight profile of the aircraft to the corresponding surface nodes of the finite element model of the high-lift device wing surface structure is as follows: First, a circular load decomposition area 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 area. i Expressed as: F i =F p *w i Where, 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 high-lift device is established. The optimization objective of the load decomposition optimization model is to minimize the deformation energy of the load distribution area structure of the high-lift device. The design variable is the diameter D of all circular load decomposition areas on the surface of the high-lift device. The design constraint is the node load of the decomposed high-lift device structure, which satisfies: ∑q i =∑F i *d i ≤ξ Where, ξ is the given moment error; Finally, the load decomposition optimization calculation is performed to obtain the load decomposition results that meet the design requirements, and the decomposition of the aerodynamic load of the high-lift device is finally completed; Step three: The fitted load-time history function is dynamically loaded onto the multi-body dynamics analysis model of the high-lift device using a three-point force-based dynamic loading method. First, three points are defined, where 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 torque. The magnitude of the force is defined as the fitted load-time history, and points F2 and F3, which define the direction of the force or torque, 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.

2. The method for calculating loads in multi-body dynamics analysis of an aircraft high-lift device according to claim 1, wherein: The decomposed instantaneous aerodynamic loads are fitted with polynomials to obtain the load-time history function of the surface nodes of the finite element model of the lift-enhancing device wing structure: 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.

3. A load calculation device for multi-body dynamics analysis of aircraft high-lift 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 is used to fit the instantaneous aerodynamic loads on the surface nodes of the decomposed finite element model of the high-lift device wing surface structure into a load-time history function using the Lagrange interpolation method; 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; The process of the aerodynamic load decomposition module equivalently decomposing each instantaneous aerodynamic load acting on the aerodynamic surface of the high-lift device during 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: First, a circular load decomposition area 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 area. i Expressed as: F i =F p *w i Where, 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 high-lift device is established. The optimization objective of the load decomposition optimization model is to minimize the deformation energy of the load distribution area structure of the high-lift device. The design variable is the diameter D of all circular load decomposition areas on the surface of the high-lift device. The design constraint is the node load of the decomposed high-lift device structure, which satisfies: ∑q i =∑F i *d i ≤ξ Where, ξ is the given moment error; Finally, the load decomposition optimization calculation is performed to obtain the load decomposition results that meet the design requirements, and the decomposition of the aerodynamic load of the high-lift device is finally completed; The random loading module dynamically loads the fitted load-time history function onto the multi-body dynamics analysis model of the high-lift device using a three-point force-based dynamic loading method. First, three points are defined: one point, F1, determines the location of the force application point, and the other two points, F2 and F3, define the direction of the force or torque. The magnitude of the force is defined by the fitted load-time history. Points F2 and F3, which define the direction of the force or torque, are fixed to the high-lift device's wing structure, thereby ensuring that the loading direction remains unchanged relative to the high-lift device.

4. The aircraft high-lift device multi-body dynamics analysis load calculation device according to claim 3, characterized in that: The aerodynamic load fitting module performs 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 high-lift device wing structure: 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.

5. An electronic device, characterized in that: include: one or more processors; Memory; One or more application programs are stored in the memory and configured to be executed by the one or more processors, wherein 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 2.

6. 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 is loaded and executed by a processor to implement the aircraft high-lift device multi-body dynamics analysis load calculation method according to any one of claims 1 to 2.

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