Multi-component load condition synchronous implementation test design method and device

Abstract

The invention belongs to the technical field of aviation aircraft ground tests, and relates to a multi-component load condition synchronous implementation test design method and device, and the method comprises the steps: S1, determining whether the component load condition can be trimmed or not; s2, when the component load working condition cannot be balanced, whether other component load working conditions capable of being subjected to stress decoupling with the component load working condition exist or not is determined; s3, when two component load working conditions capable of performing stress decoupling exist, determining the main force element direction and magnitude of each component load working condition; s4, when the main force elements are opposite in direction, the load difference of simultaneous implementation of the load working conditions of the two parts is determined according to the magnitude; and S5, when the load difference is smaller than a preset load threshold value, it is determined that the load working conditions of the two parts can be synchronously implemented, a combined working condition is formed, and load balancing of other parts of the aircraft is conducted according to the load difference of the combined working condition. According to the invention, the magnitude of the balancing load can be obviously reduced, and the design difficulty of the test load is reduced.

Description

Technical Field

[0001] The present application belongs to the technical field of ground testing of aviation vehicles, and in particular, relates to a method and device for designing a test for synchronously implementing multiple component load conditions. Background Art

[0002] Before the first flight of an aircraft, a full-aircraft static test is generally required to verify the structural strength of the aircraft. The full-aircraft static test is divided into full-aircraft load conditions and component load conditions. When the component load condition is implemented on the full-aircraft static test machine, load balancing is required on other components of the test machine. If the load magnitude of the component load condition is large, then the balancing load applied to other components will generally have a large load magnitude accordingly. It is possible that other aircraft components cannot withstand its balancing load, resulting in the component load condition being difficult to implement on the full-aircraft static test machine. It is necessary to plan a separate component load test, which greatly increases the test workload and time and economic costs; or although other aircraft components can barely withstand the balancing load, the test risk is too high. This makes the design of component load condition tests with large load magnitudes a difficult point.

[0003] Faced with this test design difficulty, the existing test design method is not to implement the component load condition on the full-machine static testing machine, but to redesign the component load test, which requires the production of large component test pieces and supporting fixtures, which dramatically increases the test time and economic costs. Summary of the invention

[0004] In order to solve the above problems, the present application provides a method and device for synchronously implementing test design of multiple component load conditions.

[0005] The first aspect of the present application provides a method for synchronously implementing a test design for multiple component load conditions, mainly comprising:

[0006] Step S1, determining whether a component load condition can be balanced based on a preset load threshold;

[0007] Step S2: when the component load condition cannot be balanced, determining whether there are other component load conditions that can be stress decoupled therefrom;

[0008] Step S3: when there are two component load conditions capable of stress decoupling, determine the main element direction and magnitude of each component load condition;

[0009] Step S4, when the main elements of the load conditions of the two components are in opposite directions, determine the load difference of the two component load conditions implemented simultaneously according to the magnitude;

[0010] Step S5: When the load difference is less than the preset load threshold, it is determined that the load conditions of the two components can be implemented synchronously to form a combined condition, and load balancing of other components of the aircraft is performed according to the load difference of the combined condition.

[0011] Preferably, in step S1, when the component load condition exceeds a preset load threshold, it is determined that the component load condition cannot be balanced, otherwise it is determined that the component load condition can be balanced.

[0012] Preferably, in step S1, the load conditions of the static test components are determined by a finite element model of the entire machine.

[0013] Preferably, in step S2, determining whether there are other component load conditions that can be stress-decoupled means: when there is no overlapping area of ​​the aircraft structure affected by two or more component load conditions.

[0014] Preferably, step S5 further includes:

[0015] Perform finite element stress analysis on the entire aircraft for the combined working condition for load balancing. When the stress analysis results meet the static strength requirements and test assessment requirements of each component, freeze the load design of the combined working condition. Otherwise, adjust the local balancing load and perform finite element stress calculation again until the static strength requirements and test assessment requirements of each component are met.

[0016] The second aspect of the present application provides a multi-component load condition synchronous implementation test design device, which mainly includes:

[0017] A component load condition balancing judgment module, used to determine whether the component load condition can be balanced based on a preset load threshold;

[0018] A component load condition selection module, used for determining whether there are other component load conditions that can be stress-decoupled with the component load condition when the component load condition cannot be trimmed;

[0019] A component load condition parameter determination module, for determining the main element direction and magnitude of each component load condition when there are two component load conditions capable of stress decoupling;

[0020] A load difference calculation module, used to determine the load difference of two component load conditions simultaneously implemented according to magnitude when the main elements of the two component load conditions are in opposite directions;

[0021] The load balancing module is used to determine that the load conditions of the two components can be implemented simultaneously to form a combined condition when the load difference is less than a preset load threshold, and to balance the loads of other components of the aircraft according to the load difference of the combined condition.

[0022] Preferably, in the component load condition balancing judgment module, when the component load condition exceeds a preset load threshold, it is determined that the component load condition cannot be balanced, otherwise it is determined that the component load condition can be balanced.

[0023] Preferably, in the component load condition balancing judgment module, the static test component load condition is determined by a full-machine finite element model.

[0024] Preferably, in the component load condition selection module, determining whether there are other component load conditions that can be stress decoupled means: when there is no overlapping area of ​​the aircraft structure affected by two or more component load conditions.

[0025] Preferably, the device comprises:

[0026] The load balancing optimization module is used to perform finite element stress analysis on the whole machine for the combined working condition for load balancing. When the stress analysis results meet the static strength requirements and test assessment requirements of each component, the load design of the combined working condition is frozen. Otherwise, the local balancing load is adjusted and the finite element stress calculation is performed again until the static strength requirements and test assessment requirements of each component are met.

[0027] A third aspect of the present application provides a computer device, including 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 test design method for synchronously implementing multiple component load conditions as described above.

[0028] A fourth aspect of the present application provides a readable storage medium, which stores a computer program, characterized in that when the computer program is executed by a processor, it is used to implement the test design method for synchronously implementing multiple component load conditions as described above.

[0029] This application is guided by the results of finite element stress analysis of the entire aircraft, selects component load conditions that can be stress-decoupled, and performs load balancing on the entire aircraft at the same time, which can significantly reduce the magnitude of the balancing load, reduce the difficulty of test load design and the risk of test implementation; this method is still carried out on the entire aircraft test machine, and there is no need to additionally produce large component test pieces and support fixtures, saving test funds. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 It is a flow chart of a preferred embodiment of the test design method for synchronously implementing multiple component load conditions of the present application.

[0031] Figure 2 This application Figure 1 Schematic diagram of load conditions and impact ranges of two components in the illustrated embodiment.

[0032] Figure 3 It is a schematic diagram of the structure of a computer device of a terminal or server suitable for implementing the implementation mode of the present application. DETAILED DESCRIPTION

[0033] 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.

[0034] The first aspect of the present application provides a method for synchronously implementing a test design for multiple component load conditions, mainly comprising:

[0035] Step S1, determining whether a component load condition can be balanced based on a preset load threshold;

[0036] Step S2: when the component load condition cannot be balanced, determining whether there are other component load conditions that can be stress decoupled therefrom;

[0037] Step S3: when there are two component load conditions capable of stress decoupling, determine the main element direction and magnitude of each component load condition;

[0038] Step S4, when the main elements of the load conditions of the two components are in opposite directions, determine the load difference of the two component load conditions implemented simultaneously according to the magnitude;

[0039] Step S5: When the load difference is less than the preset load threshold, it is determined that the load conditions of the two components can be implemented synchronously to form a combined condition, and load balancing of other components of the aircraft is performed according to the load difference of the combined condition.

[0040] In some optional implementations, in step S1, when the component load condition exceeds a preset load threshold, it is determined that the component load condition cannot be balanced, otherwise it is determined that the component load condition can be balanced.

[0041] In some optional implementations, in step S1, the load conditions of the static test components are determined by a finite element model of the entire machine.

[0042] refer to Figure 1In step S1, firstly, a finite element model of the whole aircraft needs to be established, and then a finite element stress analysis of the whole aircraft is performed. The load conditions of the static test components are determined by combining the finite element stress analysis results and the load envelope. Finally, it is determined whether "the load magnitude of the component is large, and it is difficult to balance the load on other components when implementing it on the static test machine of the whole aircraft"; if so, proceed to the next step, otherwise it indicates that it can be implemented on the static test machine of the whole aircraft, and load balancing can be performed on other components according to conventional techniques.

[0043] Step S1 of the present application is mainly used to determine whether it is necessary to implement multiple component load conditions simultaneously according to the magnitude of the component load condition, such as Figure 2 As shown, when the front fuselage of the aircraft is under load condition A, the load level of the front fuselage reaches hundreds of tons, and the direction is backward along the aircraft heading. When the rear fuselage is under load condition B, the load level of the rear fuselage also reaches hundreds of tons, and the direction is forward along the aircraft heading. It is difficult to balance the component load conditions A and B on the fuselage alone.

[0044] Step S1 is used to select component load condition A or component load condition B, and step S2 is used to check whether there are other component load conditions that are stress decoupled from the component load condition determined in step S1, such as component load condition B that is decoupled from component load condition A.

[0045] In some optional embodiments, in step S2, determining whether there are other component load conditions that can be stress-decoupled means: there is no overlapping area of ​​the aircraft structure affected by two or more component load conditions.

[0046] refer to Figure 1 In step S2, first determine the load stress distribution and stress influence range of each component, and then determine whether "stress decoupling exists in at least two component load conditions"; if so, proceed to the next step, if not, use other experimental design methods.

[0047] refer to Figure 2 By establishing a finite element model of the entire aircraft and conducting a stress analysis of the entire aircraft, it was found that the area affected by component load condition A is located before the fuselage frame 20, and the area affected by component load condition B is located after the fuselage frame 30, and there is a state of stress decoupling between the two conditions.

[0048] In step S3, refer to Figure 1 , analyze the size and direction of the six force elements (Fx, Fy, Fz, Mx, My, Mz) of the selected component load conditions, and determine the main force elements of the component load conditions respectively. In step S4, when the directions of the main force elements are opposite, calculate the load difference. In step S5, determine whether the two component load conditions can be combined for design based on the load difference. In other words, Figure 1In the design, “opposite force elements and equivalent magnitudes” is used to comprehensively judge whether the load conditions of the two components can be designed in combination.

[0049] It should be noted that the direction of the main force element can usually be judged by the size of the force elements in each direction. When the size of the force element in one direction far exceeds the size of the force elements in other directions, it is considered that there is a main force element. For example, if the force element along the heading is 100 tons, while the force elements in other directions are only a few tons or a dozen tons, then the heading is considered to be the main force element direction.

[0050] Back to Figure 2 After analyzing the loads of the two working conditions, it was found that the six force elements of working condition A are mainly Fx, with the heading backward, and the six force elements of working condition B are also mainly Fx, with the heading forward; the main loads of the two are of the same magnitude and opposite directions. Therefore, it is determined that component load conditions A and component load conditions B can be implemented simultaneously on the full-aircraft static test machine. After the two are combined into a new load condition, load balancing is performed on the whole aircraft, and the balancing load is greatly reduced.

[0051] In some optional implementations, step S5 further includes:

[0052] Perform finite element stress analysis on the entire aircraft for the combined working condition for load balancing. When the stress analysis results meet the static strength requirements and test assessment requirements of each component, freeze the load design of the combined working condition. Otherwise, adjust the local balancing load and perform finite element stress calculation again until the static strength requirements and test assessment requirements of each component are met.

[0053] In step S5, after further finite element analysis, it can be seen that the structural stress level caused by the trim load is low, the stress analysis results of the whole machine meet the static strength requirements and test assessment requirements of each component, and the structure is safe. The load design of this working condition can be frozen, and the load working condition tests of the two components can be designed and completed at the same time.

[0054] The smooth implementation of the test simultaneously assessed the most severe load conditions of the front and rear fuselages of the aircraft, and no front and rear fuselage large component test pieces were manufactured, which saved the test cycle by 3 months and a large amount of test funds.

[0055] This application adopts a test design method for simultaneously implementing multiple component load conditions. Guided by the results of finite element stress analysis of the entire aircraft, component load conditions that can be stress-decoupled are selected, and load balancing is performed on the entire aircraft at the same time. This can significantly reduce the magnitude of the balancing load, reduce the difficulty of test load design and the risk of test implementation; this method is still carried out on a full-aircraft test machine, and there is no need to additionally produce large component test pieces and support fixtures, saving test funds.

[0056] To sum up, the present application is a design method that can solve the test problem in the static test of the whole aircraft where the load magnitude of a single component load condition is large and it is difficult to balance the loads of other components of the whole aircraft. While solving the technical problems, the present application can save the time and economic costs of test design, and is an economical and efficient test design method.

[0057] The second aspect of the present application provides a multi-component load condition synchronous implementation test design device corresponding to the above method, mainly comprising:

[0058] A component load condition balancing judgment module, used to determine whether the component load condition can be balanced based on a preset load threshold;

[0059] A component load condition selection module, used for determining whether there are other component load conditions that can be stress-decoupled with the component load condition when the component load condition cannot be trimmed;

[0060] A component load condition parameter determination module, for determining the main element direction and magnitude of each component load condition when there are two component load conditions capable of stress decoupling;

[0061] A load difference calculation module, used to determine the load difference of two component load conditions simultaneously implemented according to magnitude when the main elements of the two component load conditions are in opposite directions;

[0062] The load balancing module is used to determine that the load conditions of the two components can be implemented simultaneously to form a combined condition when the load difference is less than a preset load threshold, and to balance the loads of other components of the aircraft according to the load difference of the combined condition.

[0063] In some optional embodiments, in the component load condition balancing judgment module, when the component load condition exceeds a preset load threshold, it is determined that the component load condition cannot be balanced, otherwise it is determined that the component load condition can be balanced.

[0064] In some optional implementations, in the component load condition balancing judgment module, the static test component load condition is determined by a full-machine finite element model.

[0065] In some optional embodiments, in the component load condition selection module, determining whether there are other component load conditions that can be stress decoupled means: when there is no overlapping area of ​​the aircraft structure affected by two or more component load conditions.

[0066] In some optional embodiments, the device comprises:

[0067] The load balancing optimization module is used to perform finite element stress analysis on the whole machine for the combined working condition for load balancing. When the stress analysis results meet the static strength requirements and test assessment requirements of each component, the load design of the combined working condition is frozen. Otherwise, the local balancing load is adjusted and the finite element stress calculation is performed again until the static strength requirements and test assessment requirements of each component are met.

[0068] 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 test design method for synchronously implementing multiple component load conditions.

[0069] 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 test design method for synchronously implementing multiple component load conditions 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.

[0070] Reference below Figure 3 , which shows a schematic structural diagram of a computer device 400 suitable for implementing the embodiments of the present application. Figure 3 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.

[0071] like Figure 3 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.

[0072] 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.

[0073] 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.

[0074] 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.

[0075] 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.

[0076] 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 synchronously implementing test design for multiple component load conditions, characterized in that: include: Step S1, determining whether a component load condition can be balanced based on a preset load threshold; Step S2: when the component load condition cannot be balanced, determining whether there are other component load conditions that can be stress decoupled therefrom; Step S3: when there are two component load conditions capable of stress decoupling, determine the main element direction and magnitude of each component load condition; Step S4, when the main elements of the load conditions of the two components are in opposite directions, determine the load difference of the two component load conditions implemented simultaneously according to the magnitude; Step S5: When the load difference is less than the preset load threshold, it is determined that the load conditions of the two components can be implemented synchronously to form a combined condition, and load balancing of other components of the aircraft is performed according to the load difference of the combined condition.

2. The method for synchronously implementing the test design of multiple component load conditions according to claim 1, characterized in that: In step S1 , when the component load condition exceeds a preset load threshold, it is determined that the component load condition cannot be balanced; otherwise, it is determined that the component load condition can be balanced.

3. The method for synchronously implementing the test design of multiple component load conditions according to claim 1, characterized in that: In step S1, the load conditions of the static test components are determined through the finite element model of the entire machine.

4. The method for synchronously implementing the test design of multiple component load conditions according to claim 1, characterized in that: In step S2, determining whether there are other component load conditions that can be stress-decoupled means that: there is no overlapping area of ​​the aircraft structure affected by two or more component load conditions.

5. The method for synchronously implementing the test design of multiple component load conditions according to claim 1, characterized in that: Step S5 further includes: Perform finite element stress analysis on the entire aircraft for the combined working condition for load balancing. When the stress analysis results meet the static strength requirements and test assessment requirements of each component, freeze the load design of the combined working condition. Otherwise, adjust the local balancing load and perform finite element stress calculation again until the static strength requirements and test assessment requirements of each component are met.

6. A device for synchronously implementing test design of multiple component load conditions, characterized in that: include: A component load condition balancing judgment module, used to determine whether the component load condition can be balanced based on a preset load threshold; A component load condition selection module, used for determining whether there are other component load conditions that can be stress-decoupled with the component load condition when the component load condition cannot be trimmed; A component load condition parameter determination module, for determining the main element direction and magnitude of each component load condition when there are two component load conditions capable of stress decoupling; A load difference calculation module, used to determine the load difference of two component load conditions simultaneously implemented according to magnitude when the main elements of the two component load conditions are in opposite directions; The load balancing module is used to determine that the load conditions of the two components can be implemented simultaneously to form a combined condition when the load difference is less than a preset load threshold, and to balance the loads of other components of the aircraft according to the load difference of the combined condition.

7. The device for synchronously implementing a test design for multiple component load conditions according to claim 6, characterized in that: In the component load condition balancing judgment module, when the component load condition exceeds a preset load threshold, it is determined that the component load condition cannot be balanced, otherwise it is determined that the component load condition can be balanced.

8. The device for synchronously implementing a test design for multiple component load conditions according to claim 6, characterized in that: In the component load condition balancing judgment module, the static test component load condition is determined through the whole aircraft finite element model.

9. The device for synchronously implementing a test design for multiple component load conditions according to claim 6, characterized in that: In the component load condition selection module, determining whether there are other component load conditions that can be stress decoupled means: when there is no overlapping area of ​​the aircraft structure affected by two or more component load conditions.

10. The device for synchronously implementing a test design for multiple component load conditions according to claim 6, characterized in that: The device includes: The load balancing optimization module is used to perform finite element stress analysis on the whole machine for the combined working condition for load balancing. When the stress analysis results meet the static strength requirements and test assessment requirements of each component, the load design of the combined working condition is frozen. Otherwise, the local balancing load is adjusted and the finite element stress calculation is performed again until the static strength requirements and test assessment requirements of each component are met.

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 synchronously implementing a test design for multiple component load conditions as described 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 test design method for synchronously implementing multiple component load conditions as described in any one of claims 1 to 5.

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