Method and device for determining external load of angle section of airtight cabin

Abstract

The invention belongs to the technical field of structural strength design, and particularly relates to an airtight cabin angle section external load determination method and device.The method comprises the steps that S1, the length L1, the elasticity modulus E1 and the sectional inertia moment I1 of a cross beam connected with an angle section horizontal plate are determined, and the cross beam bears evenly-distributed aerodynamic loads q; s2, the length L2, the elastic modulus E2 and the section inertia moment I2 of the angle section vertical plate from the end, connected with the longitudinal beam, of the angle section vertical plate to the root section are determined; and S3, solving the external load borne by the angle section. The calculation time is shortened, the calculation is simple, and the scheme design efficiency of the structure is improved.

Description

Technical Field

[0001] The present application belongs to the technical field of structural strength design, and in particular relates to a method and device for determining the external load of an airtight cabin angle material. Background Art

[0002] Aircraft airtight cabin refers to the cabin that can maintain a certain pressure inside the cabin at high altitudes to ensure safe and comfortable living and working conditions for passengers when flying at high altitudes. The airtightness and structural strength of the airtight cabin need to be guaranteed. Under the action of internal pressure, the structural stability of the airtight cabin is inseparable from the connection strength of the connection points of the longitudinal and transverse beam structures. The longitudinal beams and transverse beams of the airtight cabin are generally connected by angle bars. The external loads on the angle bars and the degree of deformation caused by them need to be analyzed in detail. The existing method for determining the external loads of the angle bars of aircraft airtight cabins is mainly solved by establishing a structural finite element model; after the structural parameters are changed, the model needs to be re-established, which is not conducive to the process of variable parameter research and iterative optimization of solutions. Summary of the invention

[0003] In order to solve the above problems, the present application provides a method and device for determining the external load of an airtight cabin angle material, so as to get rid of the limitations of the finite element calculation method.

[0004] The first aspect of the present application provides a method for determining the external load of an airtight cabin angle material, mainly comprising:

[0005] Step S1, determining the length L1, elastic modulus E1 and section inertia moment I1 of the beam connected to the angle bar horizontal plate, wherein the beam bears a uniformly distributed aerodynamic load q;

[0006] Step S2, determining the length L2, elastic modulus E2 and section moment of inertia I2 of the vertical plate connected to the angle bar from one end of the longitudinal beam to the root section;

[0007] Step S3, calculate the external load M0 on the angle material:

[0008]

[0009] Preferably, in step S3, calculating the external load M0 on the angle bar includes:

[0010] Step S31, determining the first rotation angle θ1 of the angle bar root caused by the beam according to the unit load method:

[0011]

[0012] Step S32, simplifying the angle material into a cantilever beam to determine the second rotation angle θ2 at its root:

[0013]

[0014] Step S33, according to the deformation coordination condition θ1=θ2, the external load M0 on the angle material is calculated.

[0015] Preferably, after step S3, the method further comprises:

[0016] Step S4, optimizing the connection relationship between the angle bar and the cross beam and the longitudinal beam according to the external load on the angle bar.

[0017] Preferably, in step S4, optimizing the connection relationship between the angle bar and the cross beam and the longitudinal beam includes modifying the connection point positions between the angle bar and the cross beam and the longitudinal beam.

[0018] Preferably, in step S4, optimizing the connection relationship between the angle bar and the cross beam and the longitudinal beam includes modifying the number of connection points between the angle bar and the cross beam and the longitudinal beam.

[0019] The second aspect of the present application provides a device for determining the external load of an airtight cabin angle material, mainly comprising:

[0020] A beam parameter acquisition module is used to determine the length L1, elastic modulus E1 and section inertia moment I1 of the beam connected to the angle bar horizontal plate, wherein the beam bears a uniformly distributed aerodynamic load q;

[0021] An angle bar parameter acquisition module, used to determine the length L2, elastic modulus E2 and section inertia moment I2 of the vertical plate connected to the angle bar from one end of the longitudinal beam to the root section;

[0022] External load calculation module, used to solve the external load M0 on the angle material:

[0023]

[0024] Preferably, the external load calculation module includes:

[0025] The first rotation angle and external load relationship determination unit is used to determine the first rotation angle θ1 of the angle material root caused by the beam according to the unit load method:

[0026]

[0027] The second rotation angle and external load relationship determination unit is used to simplify the angle material into a cantilever beam to determine the second rotation angle θ2 at its root:

[0028]

[0029] The external load solving unit is used to solve the external load M0 on the angle material according to the deformation coordination condition θ1=θ2.

[0030] Preferably, the device further comprises:

[0031] The connection relationship optimization module is used to optimize the connection relationship between the angle bar and the crossbeam and longitudinal beam according to the external load on the angle bar.

[0032] Preferably, in the connection relationship optimization module, optimizing the connection relationship between the angle bar and the cross beam and the longitudinal beam comprises modifying the connection point positions between the angle bar and the cross beam and the longitudinal beam.

[0033] Preferably, in the connection relationship optimization module, optimizing the connection relationship between the angle bar and the cross beam and the longitudinal beam comprises modifying the number of connection points between the angle bar and the cross beam and the longitudinal beam.

[0034] 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 external load of an airtight compartment angle member as described above.

[0035] A fourth aspect of the present application provides a readable storage medium, wherein the 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 external load of an airtight compartment angle member as described above.

[0036] This application shortens the calculation time, simplifies the calculation, and improves the efficiency of structural design scheme. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] Figure 1 It is a flow chart of a preferred embodiment of the method for determining the external load of the airtight cabin angle material of the present application.

[0038] Figure 2 This is a schematic diagram of the connection of the longitudinal and transverse beams of the aircraft airtight compartment through angle materials.

[0039] Figure 3 yes Figure 2 Schematic diagram of the mechanical model at the corner of the embodiment shown.

[0040] Figure 4 It is a schematic diagram of the structure of a computer device suitable for implementing the embodiments of the present application. DETAILED DESCRIPTION

[0041] 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.

[0042] The first aspect of the present application provides a method for determining the external load of an airtight cabin angle material, such as Figure 1 As shown, it mainly includes:

[0043] Step S1, determining the length L1, elastic modulus E1 and section inertia moment I1 of the beam connected to the angle bar horizontal plate, wherein the beam bears a uniformly distributed aerodynamic load q;

[0044] Step S2, determining the length L2, elastic modulus E2 and section moment of inertia I2 of the vertical plate connected to the angle bar from one end of the longitudinal beam to the root section;

[0045] Step S3, calculate the external load M0 on the angle material:

[0046]

[0047] This application uses engineering algorithms to quickly calculate the external load of the airtight cabin angle material under uniform pressure, providing input for the structural design of the angle material. Figure 2 The aircraft airtight cabin includes a crossbeam and a longitudinal beam, which are connected by an angle bar. The angle bar is a T-shaped angle bar, which includes a horizontal plate and a vertical plate located in the middle of the horizontal plate and perpendicular to the horizontal plate. The horizontal plate of the angle bar is connected to the crossbeam by riveting, and the vertical plate of the angle bar is connected to the longitudinal beam by riveting. The crossbeam is subjected to a uniformly distributed aerodynamic load q. Figure 2 Simplified to Figure 3 In the mechanical model shown, the external load M0 on the angle bar is actually the bending moment of the angle bar. In order to calculate the bending moment, this application extracts the length L1 of the beam, the elastic modulus E1 and the section inertia moment I1 at section 1, and the parameters of the vertical plate of the angle bar, and Figure 2 The elastic modulus E2 and the section inertia moment I2 at the middle section 2, and the length L2 from the angle bar vertical plate connection bolt to the root of the vertical plate. Finally, the external load can be solved by the formula in step S3.

[0048] In some optional implementations, in step S3, calculating the external load M0 on the angle bar includes:

[0049] Step S31, determining the first rotation angle θ1 of the angle bar root caused by the beam according to the unit load method:

[0050]

[0051] Step S32, simplifying the angle material into a cantilever beam to determine the second rotation angle θ2 at its root:

[0052]

[0053] Step S33, according to the deformation coordination condition θ1=θ2, the external load M0 on the angle material is calculated.

[0054] This embodiment provides the steps and principles for solving the external load in step S3.

[0055] In step S31, for the crossbeam, the first rotation angle θ1 is calculated using the unit load method:

[0056]

[0057] In step S32, the angle material is simplified to a cantilever beam, and the following is obtained:

[0058]

[0059] In step S33, according to the deformation coordination condition θ1=θ2, it can be obtained that:

[0060]

[0061] Substituting into the calculation formula of the first and second angles, we can get:

[0062]

[0063] For example, it is known that the crossbeam of the airtight compartment of an aircraft fuselage is made of aluminum alloy, E1 = 70 GPa, length 2000 mm, and the crossbeam section bending stiffness is 7963000 mm 4 ; Angle material is T-section aluminum alloy profile, E2 = 70GPa, length L2 = 100mm, out-of-plane bending stiffness 15000mm 4 ; When a dense load of 48.4MPa is applied to the unit length of the beam, the external load bending moment M0 generated on the angle material is calculated to be 0.44tm, and θ1=θ2=2.4°.

[0064] When the angle bar is simplified to a simple support constraint, M0 is 0tm. When the angle bar is simplified to a clamped support constraint, M0 is 1.6tm. It can be seen that compared with the traditional method of simplifying the angle bar to a simple support or a clamped support constraint, the angle bar external load and deformation results obtained by considering the angle bar stiffness using the elastic constraint boundary proposed in this application are quite different, and the method of this application is more reasonable and accurate.

[0065] In some optional implementations, after step S3, the method further includes:

[0066] Step S4, optimizing the connection relationship between the angle bar and the cross beam and the longitudinal beam according to the external load on the angle bar.

[0067] In some optional implementations, in step S4, optimizing the connection relationship between the angle bar and the cross beam and the longitudinal beam includes modifying the connection point positions between the angle bar and the cross beam and the longitudinal beam.

[0068] In some optional implementations, in step S4, optimizing the connection relationship between the angle bar and the cross beam and the longitudinal beam includes modifying the number of connection points between the angle bar and the cross beam and the longitudinal beam.

[0069] The second aspect of the present application provides a device for determining the external load of an airtight cabin angle material corresponding to the above method, mainly comprising:

[0070] A beam parameter acquisition module is used to determine the length L1, elastic modulus E1 and section inertia moment I1 of the beam connected to the angle bar horizontal plate, wherein the beam bears a uniformly distributed aerodynamic load q;

[0071] An angle bar parameter acquisition module, used to determine the length L2, elastic modulus E2 and section inertia moment I2 of the vertical plate connected to the angle bar from one end of the longitudinal beam to the root section;

[0072] External load calculation module, used to solve the external load M0 on the angle material:

[0073]

[0074] In some optional implementations, the external load calculation module includes:

[0075] The first rotation angle and external load relationship determination unit is used to determine the first rotation angle θ1 of the angle material root caused by the beam according to the unit load method:

[0076]

[0077] The second rotation angle and external load relationship determination unit is used to simplify the angle material into a cantilever beam to determine the second rotation angle θ2 at its root:

[0078]

[0079] The external load solving unit is used to solve the external load M0 on the angle material according to the deformation coordination condition θ1=θ2.

[0080] In some optional embodiments, the device further comprises:

[0081] The connection relationship optimization module is used to optimize the connection relationship between the angle bar and the crossbeam and longitudinal beam according to the external load on the angle bar.

[0082] In some optional implementations, in the connection relationship optimization module, optimizing the connection relationship between the angle bar and the cross beam and the longitudinal beam includes modifying the connection point positions between the angle bar and the cross beam and the longitudinal beam.

[0083] In some optional implementations, in the connection relationship optimization module, optimizing the connection relationship between the angle bar and the cross beam and the longitudinal beam includes modifying the number of connection points between the angle bar and the cross beam and the longitudinal beam.

[0084] 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 the external load of an angle member of an airtight compartment.

[0085] 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, the computer program is used to implement the method for determining the external load of an angle member of an airtight compartment 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 computer readable storage medium carries one or more programs, and when the one or more programs are executed by the device, the data is processed according to the above method.

[0086] Reference below Figure 4 , which shows a schematic structural diagram of a computer device 400 suitable for implementing the embodiments of the present application. Figure 4 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.

[0087] like Figure 4 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.

[0088] 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.

[0089] 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, an electrical connection with one or more conductors, 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), an optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, 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, an apparatus or a 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, an apparatus or a 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.

[0090] 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.

[0091] 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.

[0092] 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 external load of an airtight cabin angle material, characterized in that: include: Step S1, determining the length L1, elastic modulus E1 and section inertia moment I1 of the beam connected to the angle bar horizontal plate, wherein the beam bears a uniformly distributed aerodynamic load q; Step S2, determining the length L2, elastic modulus E2 and section moment of inertia I2 of the vertical plate connected to the angle bar from one end of the longitudinal beam to the root section; Step S3, calculate the external load M0 on the angle material:

2. The method for determining the external load of an airtight compartment angle member according to claim 1, characterized in that: In step S3, calculating the external load M0 on the angle bar includes: Step S31, determining the first rotation angle θ1 of the angle bar root caused by the beam according to the unit load method: Step S32, simplifying the angle material into a cantilever beam to determine the second rotation angle θ2 at its root: Step S33, according to the deformation coordination condition θ1=θ2, the external load M0 on the angle material is calculated.

3. The method for determining the external load of an airtight cabin angle material according to claim 1, characterized in that: After step S3, the method further comprises: Step S4, optimizing the connection relationship between the angle bar and the cross beam and the longitudinal beam according to the external load on the angle bar.

4. The method for determining the external load of an airtight cabin angle member according to claim 3, characterized in that: In step S4, optimizing the connection relationship between the angle bar and the cross beam and the longitudinal beam includes modifying the connection point positions between the angle bar and the cross beam and the longitudinal beam.

5. The method for determining the external load of an airtight cabin angle member according to claim 3, characterized in that: In step S4, optimizing the connection relationship between the angle bar and the cross beam and the longitudinal beam includes modifying the number of connection points between the angle bar and the cross beam and the longitudinal beam.

6. A device for determining the external load of an airtight cabin angle material, characterized in that: include: A beam parameter acquisition module is used to determine the length L1, elastic modulus E1 and section inertia moment I1 of the beam connected to the angle bar horizontal plate, wherein the beam bears a uniformly distributed aerodynamic load q; An angle bar parameter acquisition module, used to determine the length L2, elastic modulus E2 and section inertia moment I2 of the vertical plate connected to the angle bar from one end of the longitudinal beam to the root section; External load calculation module, used to solve the external load M0 on the angle material:

7. The device for determining the external load of an angle bar of an airtight compartment according to claim 6, characterized in that: The external load calculation module includes: The first rotation angle and external load relationship determination unit is used to determine the first rotation angle θ1 of the angle material root caused by the beam according to the unit load method: The second rotation angle and external load relationship determination unit is used to simplify the angle material into a cantilever beam to determine the second rotation angle θ2 at its root: The external load solving unit is used to solve the external load M0 on the angle material according to the deformation coordination condition θ1=θ2.

8. The device for determining the external load of an angle bar of an airtight compartment according to claim 7, characterized in that: The device also includes: The connection relationship optimization module is used to optimize the connection relationship between the angle bar and the crossbeam and longitudinal beam according to the external load on the angle bar.

9. The device for determining the external load of an angle bar of an airtight compartment according to claim 8, characterized in that: In the connection relationship optimization module, optimizing the connection relationship between the angle bar and the cross beam and the longitudinal beam includes modifying the connection point positions between the angle bar and the cross beam and the longitudinal beam.

10. The device for determining the external load of an angle bar of an airtight compartment according to claim 8, characterized in that: In the connection relationship optimization module, optimizing the connection relationship between the angle bar and the cross beam and the longitudinal beam includes modifying the number of connection points between the angle bar and the cross beam and the longitudinal beam.

11. 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 external load of an angle material of an airtight compartment as claimed in any one of claims 1 to 5.

12. 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 external load of the airtight cabin angle material as described in any one of claims 1 to 5.

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