Method and device for determining load transfer ratio of longitudinal beam of fuselage under action of symmetric bending moment

Abstract

The invention belongs to the technical field of aircraft design, and particularly relates to a fuselage longitudinal beam load transfer proportion determination method and device under the action of symmetrical bending moment, and the method comprises the steps: S1, determining the radius, the section rigidity, the elastic modulus and the borne symmetrical bending moment of a circular section of a fuselage frame; s2, constructing a polar coordinate system, and determining a polar angle of a connecting point of the fuselage longitudinal beam and the fuselage frame in the polar coordinate system; s3, the constraint load of the fuselage longitudinal beam on the fuselage frame is equivalent to spring elasticity, and the spring elasticity at the connecting point of the fuselage longitudinal beam and the fuselage frame is calculated by combining the displacement equation at the connecting point of the fuselage longitudinal beam and the fuselage frame and the displacement equation at the symmetrical bending moment applying point; s4, calculating the torque transmitted by the fuselage longitudinal beam according to the elastic force of the spring at the connecting point of the fuselage longitudinal beam and the fuselage frame; and S5, determining the load transfer ratio of the fuselage longitudinal beam according to the torque. According to the method, the time of traditional finite element modeling calculation is shortened, and the design optimization efficiency of the fuselage longitudinal beam is improved.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft design, and in particular relates to a method and device for determining the load transfer ratio of a fuselage longitudinal beam under the action of a symmetrical bending moment. Background Art

[0002] The fuselage frame usually needs to be supported by the fuselage longitudinal beams, which are also called side beams. They are arranged up and down on both sides of the fuselage frame. The structural design of the fuselage longitudinal beams and the selection of the connection position with the fuselage frame have a great influence on the structural strength of the fuselage frame. The load transfer ratio is usually used to indicate the design quality of the fuselage longitudinal beams. The load transfer ratio refers to the ratio of the torque transmitted by the fuselage longitudinal beams to the torque applied to the fuselage frame.

[0003] In the prior art, aircraft designers mainly use the finite element method to calculate the load transfer ratio, but there are certain requirements for the selection of the mesh density of the fuselage frame and the fuselage longitudinal beam, the boundary conditions and the application of the load. At the same time, the finite element analysis is relatively cumbersome and is not conducive to the automated integration of strength analysis. Summary of the invention

[0004] In order to solve the above problems, the present application provides a method and device for determining the load transfer ratio of the fuselage longitudinal beam under the action of symmetrical bending moment. The load transfer ratio of the fuselage longitudinal beam is obtained by theoretical calculation, which provides a reference for the design of the circular section fuselage reinforcement frame and the fuselage longitudinal beam.

[0005] In a first aspect, the present application provides a method for determining a load transfer ratio of a fuselage longitudinal beam under a symmetrical bending moment, wherein the fuselage longitudinal beam is used to support a fuselage frame. The method mainly comprises:

[0006] Step S1, determining the radius R, section stiffness I, elastic modulus E and symmetrical bending moment M of the circular section of the fuselage frame, wherein the direction of the line connecting the points of application of the symmetrical bending moment is perpendicular to the fuselage longitudinal beam;

[0007] Step S2, constructing a polar coordinate system with the point of the circular cross section of the fuselage frame as the pole and the direction of the line connecting the symmetrical bending moment application points as the polar axis, and determining the polar angle β of the connection point between the fuselage longitudinal beam and the fuselage frame in the polar coordinate system;

[0008] Step S3, equating the constraint load of the fuselage longitudinal beam on the fuselage frame to the spring elastic force, combining the displacement equation at the connection point between the fuselage longitudinal beam and the fuselage frame and the displacement equation at the symmetrical bending moment application point, and calculating the spring elastic force at the connection point between the fuselage longitudinal beam and the fuselage frame;

[0009] Step S4, calculating the torque transmitted by the fuselage stringer according to the spring elastic force at the connection point between the fuselage stringer and the fuselage frame;

[0010] Step S5: determining the load transfer ratio of the fuselage longitudinal beam according to the torque.

[0011] Preferably, step S5 further includes:

[0012] Step S6: Optimize the structure of the fuselage longitudinal beams according to the load transfer ratio of the fuselage longitudinal beams so that the load transfer ratio of the fuselage longitudinal beams exceeds a set value.

[0013] Preferably, in step S6, optimizing the structure of the fuselage longitudinal beams includes: replacing the material of the fuselage longitudinal beams.

[0014] Preferably, in step S6, optimizing the structure of the fuselage longitudinal beams includes: modifying the connection mode of the fuselage longitudinal beams.

[0015] Preferably, in step S6, structural optimization of the fuselage longitudinal beams includes: modifying the number, position and tension of prestressed tendons in the fuselage longitudinal beams.

[0016] Preferably, in step S6, structural optimization of the fuselage longitudinal beams includes: modifying structural dimensions and performing topological optimization on the fuselage longitudinal beams.

[0017] Preferably, step S5 further includes:

[0018] Step S7, determining the load transfer ratio of the fuselage longitudinal beams at different polar angles β, determining the polar angle range in which the load transfer ratio of the fuselage longitudinal beams exceeds 100%, and arranging the fuselage longitudinal beams within the polar angle range.

[0019] In a second aspect of the present application, there is provided a device for determining a load transfer ratio of a fuselage longitudinal beam under a symmetrical bending moment, wherein the fuselage longitudinal beam is used to support a fuselage frame, and the device comprises:

[0020] A fuselage frame parameter determination module, used to determine the radius R, section stiffness I, elastic modulus E and symmetrical bending moment M of the circular section of the fuselage frame, wherein the direction of the line connecting the points of application of the symmetrical bending moment is perpendicular to the fuselage longitudinal beam;

[0021] A polar coordinate system construction module is used to construct a polar coordinate system with the point of the circular section of the fuselage frame as the pole and the direction of the line connecting the symmetrical bending moment application points as the polar axis, and determine the polar angle β of the connection point between the fuselage longitudinal beam and the fuselage frame in the polar coordinate system;

[0022] The displacement calculation module is used to equate the constraint load of the fuselage longitudinal beam on the fuselage frame to the spring elastic force, combine the displacement equation at the connection point of the fuselage longitudinal beam and the fuselage frame and the displacement equation at the symmetrical bending moment application point, and calculate the spring elastic force at the connection point of the fuselage longitudinal beam and the fuselage frame;

[0023] A torque calculation module, used to calculate the torque transmitted by the fuselage stringer according to the spring elastic force at the connection point between the fuselage stringer and the fuselage frame;

[0024] The load transfer ratio calculation module is used to determine the load transfer ratio of the fuselage longitudinal beam according to the torque.

[0025] Preferably, the device further comprises:

[0026] The fuselage longitudinal beam structure optimization module is used to optimize the structure of the fuselage longitudinal beam according to the load transfer ratio of the fuselage longitudinal beam so that the load transfer ratio of the fuselage longitudinal beam exceeds a set value.

[0027] Preferably, in the fuselage longitudinal beam structure optimization module, optimizing the structure of the fuselage longitudinal beam comprises: replacing the material of the fuselage longitudinal beam.

[0028] Preferably, in the fuselage longitudinal beam structure optimization module, optimizing the structure of the fuselage longitudinal beam comprises: modifying the connection mode of the fuselage longitudinal beam.

[0029] Preferably, in the fuselage longitudinal beam structure optimization module, structural optimization of the fuselage longitudinal beam includes: modifying the number, position and tension of prestressed tendons in the fuselage longitudinal beam.

[0030] Preferably, in the fuselage longitudinal beam structure optimization module, structural optimization of the fuselage longitudinal beam includes: modifying the structural dimensions and performing topological optimization on the fuselage longitudinal beam.

[0031] Preferably, the device further comprises:

[0032] The fuselage longitudinal beam connection point position selection module is used to determine the load transfer ratio of the fuselage longitudinal beam under different polar angles β, determine the polar angle range in which the load transfer ratio of the fuselage longitudinal beam exceeds 100%, and arrange the fuselage longitudinal beam within the polar angle range.

[0033] A third aspect of the present application provides a computer device, comprising a processor, a memory, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the method for determining the load transfer ratio of a fuselage longitudinal beam under the action of a symmetrical bending moment as described above.

[0034] A fourth aspect of the present application provides a readable storage medium, which stores a computer program. When the computer program is executed by a processor, it is used to implement the method for determining the load transfer ratio of the fuselage longitudinal beam under the action of the symmetrical bending moment as described above.

[0035] This application does not require finite element analysis, has simple calculations, and can automatically integrate strength analysis, and has wide applicability. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] Figure 1 It is a flow chart of a preferred embodiment of the method for determining the load transfer ratio of the fuselage longitudinal beam under the action of symmetrical bending moment of the present application.

[0037] Figure 2 It is a schematic diagram of the force on the fuselage frame section and the fuselage longitudinal beam of the present application in a polar coordinate system.

[0038] Figure 3 It is a schematic diagram of the 1 / 4 arc beam model of the present application subjected to external torque.

[0039] Figure 4 It is a schematic diagram of cantilever beam torsion.

[0040] Figure 5 It is a schematic diagram of cantilever beam bending.

[0041] Figure 6 It is a schematic diagram of the influence of the fuselage longitudinal beam position on the unknown reaction force.

[0042] Figure 7 It is a schematic diagram of the change of the fuselage longitudinal beam load transfer ratio with the installation position of the fuselage longitudinal beam.

[0043] Figure 8 It is a schematic diagram of the bending moment distribution of the fuselage frame section.

[0044] Fig. 9 It is a schematic diagram of the structure of a computer device suitable for implementing the embodiments of the present application. DETAILED DESCRIPTION

[0045] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the implementation of this application will be described in more detail in combination with the drawings in the implementation of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described implementation is a part of the implementation of this application, not all of the implementations. The implementation described below with reference to the drawings is exemplary and is intended to be used to explain this application, and cannot be understood as a limitation on this application. Based on the implementation in this application, all other implementations obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The implementation of this application is described in detail below in combination with the drawings.

[0046] The first aspect of the present application provides a method for determining the load transfer ratio of a fuselage longitudinal beam under the action of a symmetrical bending moment, such as Figure 1 As shown, it mainly includes:

[0047] Step S1, determining the radius R, section stiffness I, elastic modulus E and symmetrical bending moment M of the circular section of the fuselage frame, wherein the direction of the line connecting the points of application of the symmetrical bending moment is perpendicular to the fuselage longitudinal beam;

[0048] Step S2, constructing a polar coordinate system with the point of the circular cross section of the fuselage frame as the pole and the direction of the line connecting the symmetrical bending moment application points as the polar axis, and determining the polar angle β of the connection point between the fuselage longitudinal beam and the fuselage frame in the polar coordinate system;

[0049] Step S3, equating the constraint load of the fuselage longitudinal beam on the fuselage frame to the spring elastic force, combining the displacement equation at the connection point between the fuselage longitudinal beam and the fuselage frame and the displacement equation at the symmetrical bending moment application point, and calculating the spring elastic force at the connection point between the fuselage longitudinal beam and the fuselage frame;

[0050] Step S4, calculating the torque transmitted by the fuselage stringer according to the spring elastic force at the connection point between the fuselage stringer and the fuselage frame;

[0051] Step S5: determining the load transfer ratio of the fuselage longitudinal beam according to the torque.

[0052] The fuselage frame including the fuselage longitudinal beam under the bending moment load M of this application is as follows Figure 2 As shown in the figure, the fuselage longitudinal beam is arranged at EE'. The influence of the fuselage longitudinal beam on the fuselage frame is simplified to limit the deformation of the fuselage frame through equivalent springs in the X and Y directions. A polar coordinate system is established with the center of the circle as the origin. According to the load and constraint symmetry conditions, the 1 / 4 arc beam is subjected to an external load of M / 2 as follows: Figure 3 As shown, a spring force F is applied at section E. x With F y , shear force F1 is applied at section D. These quantities are the unknown quantities to be determined.

[0053] In step S3, the deformation coordination condition of the fuselage frame is the displacement u of point E in the X direction. x (E) Deformation of the spring in the X direction Equal, the displacement u of point E in the Y direction y (E) Deformation of the spring in the Y direction Equal, the X displacement u of point D x (D) is 0, where k x is the spring stiffness in the X direction, k y is the spring stiffness in the Y direction, and the above parameters are replaced by the unknown spring force F x 、F y and the unknown shear force F1, and thus a set of three-variable linear equations can be constructed to solve the spring force, using the spring force F in the X direction x The torque can then be calculated in step S4.

[0054] First, the spring stiffness k in the X direction x It is mainly generated by the torsional stiffness of the fuselage longitudinal beam. According to the aircraft structure layout, the torsion of the cantilever beam is used as an example. Figure 4 As shown, the spring stiffness in the X direction is calculated as follows:

[0055]

[0056] Spring stiffness k in the Y direction y It is mainly generated by the bending stiffness of the fuselage longitudinal beam. According to the aircraft structure layout, the bending of the cantilever beam is used as an example. Figure 5 As shown, the spring stiffness in the Y direction is calculated as follows:

[0057]

[0058] After that, the displacement calculation of points E and D is based on the bending moment. The bending moment generated by the true load M / 2 is:

[0059]

[0060] Based on this, the bending moment generated by the unit force at point D is: The bending moment generated by the unit force in the X direction at point E is: The bending moment generated by the unit force in the Y direction at point E is:

[0061] Therefore, the X-direction displacement of point D is u x (D) is:

[0062]

[0063] X-direction displacement u of point E x (E) is:

[0064]

[0065] The Y displacement of point E y (E) is:

[0066]

[0067] Finally, bring the above parameters into the three-variable linear equation system, and we get:

[0068] in:

[0069]

[0070] Solving the three-variable linear equation system yields:

[0071]

[0072] In step S4, the spring force F in the X direction is used. x The torque transmitted by the longitudinal beam is calculated as: T = F x ×h.

[0073] In step S5, the load transfer ratio of the fuselage longitudinal beam is defined as η=T / M.

[0074] In some optional implementations, step S5 further includes:

[0075] Step S6: Optimize the structure of the fuselage longitudinal beams according to the load transfer ratio of the fuselage longitudinal beams so that the load transfer ratio of the fuselage longitudinal beams exceeds a set value.

[0076] In some optional implementations, in step S6, structural optimization of the fuselage longitudinal beams includes: replacing the materials of the fuselage longitudinal beams. This embodiment provides that the rigidity of the fuselage longitudinal beams can be improved by optimizing the materials. The use of new materials such as high-strength fiberglass, carbon fiber, etc. can also significantly improve the strength and durability of the structure.

[0077] In some optional implementations, in step S6, structural optimization of the fuselage longitudinal beams includes: modifying the connection mode of the fuselage longitudinal beams. This embodiment provides a method of improving the rigidity of the fuselage longitudinal beams by optimizing parameters, such as the connection mode of hardware parts, the connection mode of beams and columns, etc., to optimize the performance of the entire structure.

[0078] In some optional embodiments, in step S6, structural optimization of the fuselage longitudinal beam includes: modifying the number, position and tension of prestressed tendons in the fuselage longitudinal beam.

[0079] In some optional implementations, in step S6, structural optimization of the fuselage longitudinal beams includes: modifying the structural dimensions and performing topological optimization of the fuselage longitudinal beams.

[0080] In this embodiment, the strength and stability of the structure can be improved by optimizing the cross-sectional parameters or overall geometric dimensions of beams and slabs. The size optimization technology is relatively mature, and can adopt the method based on scattered points, gradient method or heuristic algorithm. Topological optimization mainly refers to the change of data such as connection mode and internal opening position, which is suitable for improving the overall performance of complex structures and optimizing the overall performance by changing the topological form of the structure.

[0081] In some optional implementations, step S5 further includes:

[0082] Step S7, determining the load transfer ratio of the fuselage longitudinal beams at different polar angles β, determining the polar angle range in which the load transfer ratio of the fuselage longitudinal beams exceeds 100%, and arranging the fuselage longitudinal beams within the polar angle range.

[0083] For example, the fuselage reinforcement frame of an aircraft is a circle with a radius of R = 2500mm, and the edge beam structure EE' is arranged. The influence of the surrounding skin deformation on the rigid frame is ignored, and the section stiffness of the reinforcement frame is I = 106mm 4 , elastic modulus is E = 70GPa, and the symmetrical tensile bending moment is M = 10 8N.mm is in a self-balanced state. First calculate k x =5000N / mm, k y =1000N / mm, then calculate F1, F x 、F y The relationship between the installation position of the random longitudinal beam (side beam) (indicated by the polar angle β) is as follows Figure 6 The load transfer ratio of the fuselage longitudinal beam (side beam) varies with the installation position of the fuselage longitudinal beam as shown in Figure 7 As shown, it can be seen that as the arrangement angle of the fuselage longitudinal beam increases, the load transfer ratio of the fuselage longitudinal beam first increases and then decreases, and there is a range in which the load transfer ratio of the fuselage longitudinal beam is greater than 100%, and the fuselage longitudinal beam can be arranged within this range.

[0084] The spring force at the connection point between the fuselage longitudinal beam and the fuselage frame calculated by the above method in the present application can be further calculated to obtain the bending moment distribution of the fuselage frame section according to the equilibrium condition. For example, the fuselage longitudinal beam is β = 30°, and the bending moment distribution of the fuselage frame is obtained as follows: Figure 8 The fuselage frame can be optimized according to the above-mentioned optimization method for the fuselage longitudinal beam.

[0085] The present application obtains the load transfer ratio of the fuselage longitudinal beam and the bending moment distribution of the reinforcement frame under the action of symmetrical bending moment through a theoretical method, which reduces the time of traditional finite element modeling and calculation and improves the efficiency of fuselage longitudinal beam design optimization.

[0086] In a second aspect, the present application provides a device for determining the load transfer ratio of a fuselage longitudinal beam under the action of a symmetrical bending moment corresponding to the above method, wherein the fuselage longitudinal beam is used to support a fuselage frame, and the device comprises:

[0087] A fuselage frame parameter determination module, used to determine the radius R, section stiffness I, elastic modulus E and symmetrical bending moment M of the circular section of the fuselage frame, wherein the direction of the line connecting the points of application of the symmetrical bending moment is perpendicular to the fuselage longitudinal beam;

[0088] A polar coordinate system construction module is used to construct a polar coordinate system with the point of the circular section of the fuselage frame as the pole and the direction of the line connecting the symmetrical bending moment application points as the polar axis, and determine the polar angle β of the connection point between the fuselage longitudinal beam and the fuselage frame in the polar coordinate system;

[0089] The displacement calculation module is used to equate the constraint load of the fuselage longitudinal beam on the fuselage frame to the spring elastic force, combine the displacement equation at the connection point of the fuselage longitudinal beam and the fuselage frame and the displacement equation at the symmetrical bending moment application point, and calculate the spring elastic force at the connection point of the fuselage longitudinal beam and the fuselage frame;

[0090] A torque calculation module, used to calculate the torque transmitted by the fuselage stringer according to the spring elastic force at the connection point between the fuselage stringer and the fuselage frame;

[0091] The load transfer ratio calculation module is used to determine the load transfer ratio of the fuselage longitudinal beam according to the torque.

[0092] In some optional embodiments, the device further comprises:

[0093] The fuselage longitudinal beam structure optimization module is used to optimize the structure of the fuselage longitudinal beam according to the load transfer ratio of the fuselage longitudinal beam so that the load transfer ratio of the fuselage longitudinal beam exceeds a set value.

[0094] In some optional embodiments, in the fuselage longitudinal beam structure optimization module, optimizing the structure of the fuselage longitudinal beam includes: replacing the material of the fuselage longitudinal beam.

[0095] In some optional implementations, in the fuselage longitudinal beam structure optimization module, optimizing the structure of the fuselage longitudinal beams includes: modifying the connection method of the fuselage longitudinal beams.

[0096] In some optional embodiments, in the fuselage longitudinal beam structure optimization module, structural optimization of the fuselage longitudinal beam includes: modifying the number, position and tension of prestressed tendons in the fuselage longitudinal beam.

[0097] In some optional implementations, in the fuselage longitudinal beam structure optimization module, structural optimization of the fuselage longitudinal beam includes: modifying the structural dimensions and performing topological optimization of the fuselage longitudinal beam.

[0098] In some optional embodiments, the device further comprises:

[0099] The fuselage longitudinal beam connection point position selection module is used to determine the load transfer ratio of the fuselage longitudinal beam under different polar angles β, determine the polar angle range in which the load transfer ratio of the fuselage longitudinal beam exceeds 100%, and arrange the fuselage longitudinal beam within the polar angle range.

[0100] In a third aspect of the present application, a computer device includes a processor, a memory, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement a method for determining a load transfer ratio of a fuselage longitudinal beam under a symmetrical bending moment.

[0101] In a fourth aspect of the present application, a readable storage medium stores a computer program, and when the computer program is executed by a processor, it is used to implement the method for determining the load transfer ratio of a fuselage longitudinal beam under the action of a symmetrical bending moment as described above. The computer readable storage medium may be included in the device described in the above embodiment; or it may exist independently without being assembled into the device. The above computer readable storage medium carries one or more programs, and when the above one or more programs are executed by the device, the data is processed according to the above method.

[0102] Reference below Fig. 9, which shows a schematic structural diagram of a computer device 400 suitable for implementing the embodiments of the present application. Fig. 9 The computer device shown is only an example and should not bring any limitation to the functions and scope of use of the embodiments of the present application.

[0103] like Fig. 9 As shown, the computer device 400 includes a central processing unit (CPU) 401, which can perform various appropriate actions and processes according to a program stored in a read-only memory (ROM) 402 or a program loaded from a storage part 408 into a random access memory (RAM) 403. In the RAM 403, various programs and data required for the operation of the device 400 are also stored. The CPU 401, the ROM 402, and the RAM 403 are connected to each other via a bus 404. An input / output (I / O) interface 405 is also connected to the bus 404.

[0104] The following components are connected to the I / O interface 405: an input section 406 including a keyboard, a mouse, etc.; an output section 407 including a cathode ray tube (CRT), a liquid crystal display (LCD), etc., and a speaker, etc.; a storage section 408 including a hard disk, etc.; and a communication section 409 including a network interface card such as a LAN card, a modem, etc. The communication section 409 performs communication processing via a network such as the Internet. A drive 410 is also connected to the I / O interface 405 as needed. A removable medium 411, such as a magnetic disk, an optical disk, a magneto-optical disk, a semiconductor memory, etc., is installed on the drive 410 as needed, so that a computer program read therefrom is installed into the storage section 408 as needed.

[0105] In particular, according to the embodiment of the present application, the process described above with reference to the flowchart can be implemented as a computer software program. For example, the embodiment of the present application includes a computer program product, which includes a computer program carried on a computer-readable medium, and the computer program includes a program code for executing the method shown in the flowchart. In such an embodiment, the computer program can be downloaded and installed from the network through the communication part 409, and / or installed from the removable medium 411. When the computer program is executed by the central processing unit (CPU) 401, the above functions defined in the method of the present application are executed. It should be noted that the computer storage medium of the present application can be a computer-readable signal medium or a computer-readable storage medium or any combination of the above two. The computer-readable storage medium can be, for example, - but not limited to - a system, device or device of electricity, magnetism, light, electromagnetic, infrared, or semiconductor, or any combination of the above. More specific examples of computer-readable storage media may include, but are not limited to, electrical connections with one or more conductors, portable computer disks, hard disks, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), optical fibers, portable compact disk read-only memory (CD-ROM), optical storage devices, magnetic storage devices, or any suitable combination of the above. 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 combination with an instruction execution system, device, or device. In the present application, a computer-readable signal medium may include a data signal propagated in a baseband or as part of a carrier wave, which carries a computer-readable program code. Such propagated data signals may take a variety of forms, including but not limited to electromagnetic signals, optical signals, or any suitable combination of the above. A computer-readable signal medium may also be any computer-readable medium other than a computer-readable storage medium, which may send, propagate, or transmit a program for use by or in combination with an instruction execution system, device, or device. The program code contained on the computer-readable medium may be transmitted using any appropriate medium, including but not limited to: wireless, wire, optical cable, RF, etc., or any suitable combination of the above.

[0106] The flow chart and block diagram in the accompanying drawings illustrate the possible architecture, function and operation of the system, method and computer program product according to various embodiments of the present application. In this regard, each square box in the flow chart or block diagram can represent a module, a program segment or a part of a code, and the module, the program segment or a part of the code contains one or more executable instructions for realizing the specified logical function. It should also be noted that in some implementations as replacements, the functions marked in the square box can also occur in a sequence different from that marked in the accompanying drawings. For example, two square boxes represented in succession can actually be executed substantially in parallel, and they can sometimes be executed in the opposite order, depending on the functions involved. It should also be noted that each square box in the block diagram and / or flow chart, and the combination of the square boxes in the block diagram and / or flow chart can be implemented with a dedicated hardware-based system that performs a specified function or operation, or can be implemented with a combination of dedicated hardware and computer instructions.

[0107] The modules or units involved in the embodiments described in this application may be implemented by software or hardware. The modules or units described may also be set in a processor, and the names of these modules or units do not constitute limitations on the modules or units themselves in some cases.

[0108] 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 determining the load transfer ratio of a fuselage longitudinal beam under symmetrical bending moment, wherein: The fuselage longitudinal beam is used to support the fuselage frame, and is characterized in that the method comprises: Step S1, determining the radius R, section stiffness I, elastic modulus E and symmetrical bending moment M of the circular section of the fuselage frame, wherein the direction of the line connecting the points of application of the symmetrical bending moment is perpendicular to the fuselage longitudinal beam; Step S2, constructing a polar coordinate system with the point of the circular cross section of the fuselage frame as the pole and the direction of the line connecting the symmetrical bending moment application points as the polar axis, and determining the polar angle β of the connection point between the fuselage longitudinal beam and the fuselage frame in the polar coordinate system; Step S3, equating the constraint load of the fuselage longitudinal beam on the fuselage frame to the spring elastic force, combining the displacement equation at the connection point between the fuselage longitudinal beam and the fuselage frame and the displacement equation at the symmetrical bending moment application point, and calculating the spring elastic force at the connection point between the fuselage longitudinal beam and the fuselage frame; Step S4, calculating the torque transmitted by the fuselage stringer according to the spring elastic force at the connection point between the fuselage stringer and the fuselage frame; Step S5: determining the load transfer ratio of the fuselage longitudinal beam according to the torque.

2. The method for determining the load transfer ratio of a fuselage longitudinal beam under the action of a symmetrical bending moment as claimed in claim 1, characterized in that: Step S5 further includes: Step S6: Optimize the structure of the fuselage longitudinal beams according to the load transfer ratio of the fuselage longitudinal beams so that the load transfer ratio of the fuselage longitudinal beams exceeds a set value.

3. The method for determining the load transfer ratio of fuselage longitudinal beams under symmetrical bending moment as claimed in claim 2, characterized in that: In step S6, structural optimization of the fuselage longitudinal beams includes: replacing the material of the fuselage longitudinal beams.

4. The method for determining the load transfer ratio of a fuselage longitudinal beam under the action of a symmetrical bending moment as claimed in claim 2, characterized in that: In step S6, structural optimization of the fuselage longitudinal beams includes: modifying the connection method of the fuselage longitudinal beams.

5. The method for determining the load transfer ratio of fuselage longitudinal beams under symmetrical bending moment as claimed in claim 2, characterized in that: In step S6, structural optimization of the fuselage longitudinal beam includes: modifying the number, position and tension of the prestressed tendons in the fuselage longitudinal beam.

6. The method for determining the load transfer ratio of fuselage longitudinal beams under symmetrical bending moment as claimed in claim 2, characterized in that: In step S6, structural optimization of the fuselage longitudinal beams includes: modifying the structural dimensions and topological optimization of the fuselage longitudinal beams.

7. The method for determining the load transfer ratio of fuselage longitudinal beams under symmetrical bending moment according to claim 1, characterized in that: Step S5 further includes: Step S7, determining the load transfer ratio of the fuselage longitudinal beams at different polar angles β, determining the polar angle range in which the load transfer ratio of the fuselage longitudinal beams exceeds 100%, and arranging the fuselage longitudinal beams within the polar angle range.

8. A device for determining the load transfer ratio of a fuselage longitudinal beam under symmetrical bending moment, wherein: The fuselage longitudinal beam is used to support the fuselage frame, and is characterized in that the device comprises: A fuselage frame parameter determination module, used to determine the radius R, section stiffness I, elastic modulus E and symmetrical bending moment M of the circular section of the fuselage frame, wherein the direction of the line connecting the points of application of the symmetrical bending moment is perpendicular to the fuselage longitudinal beam; A polar coordinate system construction module is used to construct a polar coordinate system with the point of the circular section of the fuselage frame as the pole and the direction of the line connecting the symmetrical bending moment application points as the polar axis, and determine the polar angle β of the connection point between the fuselage longitudinal beam and the fuselage frame in the polar coordinate system; The displacement calculation module is used to equate the constraint load of the fuselage longitudinal beam on the fuselage frame to the spring elastic force, combine the displacement equation at the connection point of the fuselage longitudinal beam and the fuselage frame and the displacement equation at the symmetrical bending moment application point, and calculate the spring elastic force at the connection point of the fuselage longitudinal beam and the fuselage frame; A torque calculation module, used to calculate the torque transmitted by the fuselage stringer according to the spring elastic force at the connection point between the fuselage stringer and the fuselage frame; The load transfer ratio calculation module is used to determine the load transfer ratio of the fuselage longitudinal beam according to the torque.

9. The device for determining the load transfer ratio of fuselage longitudinal beams under symmetrical bending moment as claimed in claim 8, characterized in that: The device further comprises: The fuselage longitudinal beam structure optimization module is used to optimize the structure of the fuselage longitudinal beam according to the load transfer ratio of the fuselage longitudinal beam so that the load transfer ratio of the fuselage longitudinal beam exceeds a set value.

10. The device for determining the load transfer ratio of fuselage longitudinal beams under symmetrical bending moment according to claim 9, characterized in that: In the fuselage longitudinal beam structure optimization module, the structural optimization of the fuselage longitudinal beam includes: replacing the material of the fuselage longitudinal beam.

11. The device for determining the load transfer ratio of fuselage longitudinal beams under symmetrical bending moment according to claim 9, characterized in that: In the fuselage longitudinal beam structure optimization module, the structural optimization of the fuselage longitudinal beam includes: modifying the connection mode of the fuselage longitudinal beam.

12. The device for determining the load transfer ratio of fuselage longitudinal beams under symmetrical bending moment according to claim 9, characterized in that: In the fuselage longitudinal beam structure optimization module, the structural optimization of the fuselage longitudinal beam includes: modifying the number, position and tension of the prestressed tendons in the fuselage longitudinal beam.

13. The device for determining the load transfer ratio of fuselage longitudinal beams under symmetrical bending moment as claimed in claim 9, characterized in that: In the fuselage longitudinal beam structure optimization module, structural optimization of the fuselage longitudinal beam includes: modifying the structural dimensions of the fuselage longitudinal beam and performing topological optimization.

14. The device for determining the load transfer ratio of fuselage longitudinal beams under symmetrical bending moment according to claim 8, characterized in that: The device further comprises: The fuselage longitudinal beam connection point position selection module is used to determine the load transfer ratio of the fuselage longitudinal beam under different polar angles β, determine the polar angle range in which the load transfer ratio of the fuselage longitudinal beam exceeds 100%, and arrange the fuselage longitudinal beam within the polar angle range.

15. A computer device, characterized in that: The method comprises a processor, a memory and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the method for determining the load transfer ratio of a fuselage longitudinal beam under the action of a symmetrical bending moment as described in any one of claims 1 to 7.

16. A readable storage medium storing a computer program, characterized in that: When the computer program is executed by a processor, it is used to implement the method for determining the load transfer ratio of a fuselage longitudinal beam under the action of a symmetrical bending moment as described in any one of claims 1 to 7.

Images