A multi-component load case synchronous implementation test design method and device

Abstract

The application belongs to the technical field of ground test of aviation aircraft, and relates to a multi-component load working condition synchronous implementation test design method and device, which comprises the following steps: S1, determining whether the component load working condition can be trimmed; S2, when the component load working condition cannot be trimmed, determining whether there is another component load working condition capable of stress decoupling; S3, when there are two component load working conditions capable of stress decoupling, determining the principal direction and magnitude of each component load working condition; S4, when the principal directions are opposite, determining the load difference of the synchronous implementation of the two component load working conditions according to the magnitude; and S5, when the load difference is less than a preset load threshold, determining that the two component load working conditions can be synchronously implemented, forming a combined working condition, and trimming the load of other components of the aircraft according to the load difference of the combined working condition. The application can significantly reduce the magnitude of the trimmed load and reduce the difficulty of test load design.

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. Full-aircraft static tests are 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 must be performed on other components of the test machine. If the load magnitude of the component load condition is large, the balancing load applied to other components will generally be large in magnitude. It is possible that other aircraft components will not be able to withstand the balancing load, making it difficult to implement the component load condition on the full-aircraft static test machine. A separate component load test needs to be planned, which greatly increases the test workload, time cost, and economic cost. Alternatively, 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, resulting in a sharp increase in 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 designing a test for simultaneous implementation of multiple component load conditions, mainly comprising:

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

[0007] Step S2: When the component load condition cannot be balanced, determining whether there is another component load condition that can be stress decoupled from the component load condition;

[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 when they are simultaneously implemented according to the magnitude;

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

[0012] Preferably, in step S1, the load conditions of the static test components are determined by using 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 that 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 where load balancing is performed. 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] A second aspect of the present application provides a device for synchronously implementing a test design for multiple component load conditions, mainly comprising:

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

[0018] A component load condition selection module, configured to determine whether there are other component load conditions that can be stress-decoupled from the component load condition when the component load condition cannot be trimmed;

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

[0020] A load difference calculation module is used to determine the load difference of two component load conditions simultaneously implemented based on 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 balance judgment module, the static test component load condition is determined by a finite element model of the entire aircraft.

[0024] Preferably, in the component load condition selection module, 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.

[0025] Preferably, the device comprises:

[0026] The load balancing optimization module is used to 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, 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 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 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, and is characterized in that when the computer program is executed by a processor, it is used to implement the above-mentioned method for synchronously implementing the test design of multiple component load conditions.

[0029] This application is guided by the results of the 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 structural diagram of a computer device of a terminal or server suitable for implementing the embodiments of the present application. DETAILED DESCRIPTION

[0033] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the implementation of this application will be described in more detail below in conjunction with the drawings in the implementation of this application. In the drawings, the same or similar numbers 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 should not 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 conjunction with the drawings.

[0034] The first aspect of the present application provides a method for designing a test for simultaneous implementation of multiple component load conditions, mainly comprising:

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

[0036] Step S2: When the component load condition cannot be balanced, determining whether there is another component load condition that can be stress decoupled from the component load condition;

[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 when they are simultaneously implemented according to the magnitude;

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

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

[0042] refer to Figure 1In step S1, it is first necessary to establish a finite element model of the entire aircraft, and then perform a finite element stress analysis of the entire aircraft. 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 full-aircraft static test machine"; if so, proceed to the next step; otherwise, it indicates that it can be implemented on the full-aircraft static test machine, and load balancing can be performed on other components according to conventional technology.

[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, under load condition A, the load level of the front fuselage of the aircraft reaches hundreds of tons, and the direction is backward along the aircraft heading. 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 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 that 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. The two conditions are in a state of stress decoupling.

[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” are used to comprehensively judge whether the load conditions of the two components can be combined for design.

[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, and the force elements in other directions are around a few tons or more than ten 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 conditions, it was found that the six force elements of Condition A were dominated by Fx, with a backward heading, while the six force elements of Condition B were also dominated by Fx, with a forward heading. The main loads of the two conditions were of similar magnitude but in opposite directions. Therefore, it was determined that Component Load Conditions A and B could be simultaneously tested on the full-aircraft static test machine. After combining the two into a new load condition, load balancing was performed on the entire aircraft, significantly reducing the trim load.

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

[0052] Perform finite element stress analysis on the entire aircraft for the combined working condition where load balancing is performed. 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, further finite element analysis reveals that the structural stress caused by the trim load is low. The full-aircraft stress analysis results meet the static strength requirements and test assessment requirements for each component, and the structure is safe. The load design for this operating condition can be frozen, and the load test for both components can be designed and completed simultaneously.

[0054] The smooth implementation of the test simultaneously assessed the most severe load conditions of the aircraft's front and rear fuselages, 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 finite element stress analysis results 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 the entire 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 level 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 device for synchronously implementing a test design for multiple component load conditions corresponding to the above method, mainly comprising:

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

[0059] A component load condition selection module, configured to determine whether there are other component load conditions that can be stress-decoupled from the component load condition when the component load condition cannot be trimmed;

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

[0061] A load difference calculation module is used to determine the load difference of two component load conditions simultaneously implemented based on 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 balance 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: 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 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, 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 method for synchronously implementing a test design for multiple component load conditions.

[0069] In a fourth aspect of the present application, a computer-readable storage medium stores a computer program that, when executed by a processor, implements the aforementioned method for synchronously implementing a test design for multiple component load conditions. The computer-readable storage medium may be included in the apparatus described in the aforementioned embodiments, or it may exist independently and not be incorporated into the apparatus. The computer-readable storage medium carries one or more programs that, when executed by the apparatus, process data according to the aforementioned method.

[0070] Reference below Figure 3 , which shows a 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 limit the functions and scope of use of the embodiments of the present application.

[0071] like Figure 3 As shown, 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 portion 408 into a random access memory (RAM) 403. Various programs and data required for the operation of device 400 are also stored in RAM 403. CPU 401, ROM 402, and RAM 403 are connected to each other via a bus 404. An input / output (I / O) interface 405 is also connected to bus 404.

[0072] The following components are connected to the I / O interface 405: an input section 406 including a keyboard, a mouse, and the like; an output section 407 including devices such as a cathode ray tube (CRT), a liquid crystal display (LCD), and a speaker; a storage section 408 including a hard disk; and a communication section 409 including a network interface card such as a LAN card or a modem. 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. Removable media 411, such as a magnetic disk, an optical disk, a magneto-optical disk, or a semiconductor memory, is installed in the drive 410 as needed, so that computer programs read therefrom can be 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 component 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 having one or more conductors, a portable computer disk, a hard disk, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination thereof. In this application, a computer-readable storage medium may be any tangible medium that contains or stores a program that can be used by or in conjunction with an instruction execution system, apparatus, or device. In this application, a computer-readable signal medium may include a data signal propagated in baseband or as part of a carrier wave, which carries computer-readable program code. Such a propagated data signal may take a variety of forms, including, but not limited to, electromagnetic signals, optical signals, or any suitable combination thereof. A computer-readable signal medium may also be any computer-readable medium other than a computer-readable storage medium that can transmit, propagate, or transfer a program for use by or in conjunction with an instruction execution system, apparatus, or device. The program code embodied on a computer-readable medium may be transmitted using any suitable medium, including, but not limited to, wireless, wire, optical cable, RF, etc., or any suitable combination thereof.

[0074] The flow charts and block diagrams in the accompanying drawings illustrate the possible architecture, functions and operations of the systems, methods and computer program products according to various embodiments of the present application. In this regard, each box in the flow chart or block diagram can represent a module, program segment or a part of code, and the module, program segment or a part of code includes one or more executable instructions for realizing the specified logical function. It should also be noted that in some alternative implementations, the functions marked in the box can also occur in a sequence different from that marked in the accompanying drawings. For example, two 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 box in the block diagram and / or flow chart, and the combination of the boxes in the block diagram and / or flow chart can be implemented by a dedicated hardware-based system that performs the specified function or operation, or can be implemented by a combination of dedicated hardware and computer instructions.

[0075] The modules or units described in the embodiments of this application may be implemented in software or hardware. The modules or units described may also be provided in a processor, and the names of these modules or units do not, in certain circumstances, limit the modules or units themselves.

[0076] The above description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in this application should be included in the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection of the claims.

Claims

1. A method for simultaneous implementation of test design for multiple component load conditions, characterized in that: include: Step S1: determining whether a component load condition can be trimmed based on a preset load threshold; Step S2: When the component load condition cannot be balanced, determining whether there is another component load condition that can be stress decoupled from the component load condition; 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 when they are simultaneously implemented according to the magnitude; Step S5: When the load difference is less than the preset load threshold, it is determined that the two component load conditions can be implemented synchronously to form a combined condition, and load balancing of other aircraft components is performed according to the load difference of the combined condition.

2. The method for simultaneous implementation of test design for 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 trimmed; otherwise, it is determined that the component load condition can be trimmed.

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

4. The method for simultaneous implementation of test design for 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 simultaneous implementation of test design for multiple component load conditions according to claim 1, characterized in that: After step S5, the method further comprises: Perform finite element stress analysis on the entire aircraft for the combined working condition where load balancing is performed. 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 for multiple component load conditions, characterized in that: include: A component load condition balancing judgment module is used to determine whether the component load condition can be balanced based on a preset load threshold; A component load condition selection module, configured to determine whether there are other component load conditions that can be stress-decoupled from the component load condition when the component load condition cannot be trimmed; A component load condition parameter determination module, for determining the direction and magnitude of the main element of each component load condition when there are two component load conditions capable of stress decoupling; A load difference calculation module is used to determine the load difference of two component load conditions simultaneously implemented based on 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 components under load conditions according to claim 6, characterized in that: In the component load condition balance judgment module, the static test component load condition is determined through the finite element model of the entire aircraft.

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

10. The device for synchronously implementing a test design for multiple components under 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 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, 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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