Iterative follow-up loading method for large-deformation structure of airplane

Abstract

The invention belongs to the field of airplane structure strength tests, and particularly relates to an iteration follow-up loading method for a large-deformation structure of an airplane. The method comprises the following steps: step 1, acquiring estimated deformation data of an aircraft structure under a fatigue test load, and giving a synchronous follow-up driving instruction in a test load spectrum according to the estimated deformation data; step 2, performing fatigue test static measurement and pilot run according to the follow-up driving instruction, and obtaining real deformation data of the aircraft structure under a fatigue test load; and 3, judging whether an error between the follow-up driving instruction and the real deformation data meets a requirement or not, if not, correcting the follow-up driving instruction according to the real deformation data, and returning to the step 2. The follow-up driving instruction is subjected to multi-round iteration and is highly matched with real deformation of the aircraft structure, and high-precision follow-up loading can be achieved; the follow-up driving instruction is preset in the test load spectrum, the risks of load divergence and unstable follow-up driving do not exist, and the systematic test risk is prevented from being increased.

Description

Technical Field

[0001] The present application belongs to the field of aircraft structure strength testing, and in particular relates to an iterative dynamic loading method for aircraft large deformation structures. Background Art

[0002] In the aircraft structure strength fatigue test, some aircraft structures will produce large deformation after being loaded, and dynamic loading is required to ensure the accuracy of the load direction. Active dynamic loading requires the driving device to synchronously drive the loading point position to match the aircraft structure deformation, and the driving instruction is the aircraft structure deformation data. Real-time collection of deformation data as driving instructions has high dynamic loading accuracy, but it may cause load divergence and unstable position drive problems, increasing the risk of systematic testing.

[0003] Therefore, it is desired to have a technical solution to overcome or at least alleviate at least one of the above-mentioned defects of the prior art. Summary of the invention

[0004] The purpose of the present application is to provide an iterative dynamic loading method for a large deformation structure of an aircraft to solve at least one problem existing in the prior art.

[0005] The technical solution of this application is:

[0006] A first aspect of the present application provides an iterative dynamic loading method for a large deformation structure of an aircraft, characterized by comprising:

[0007] Step 1: obtaining estimated deformation data of the aircraft structure under fatigue test load, and providing a synchronous follow-up drive instruction in the test load spectrum according to the estimated deformation data;

[0008] Step 2: Performing fatigue test static measurement and trial operation according to the follow-up drive instruction to obtain real deformation data of the aircraft structure under fatigue test load;

[0009] Step three: determine whether the error between the follow-up drive instruction and the real deformation data meets the requirement; if not, correct the follow-up drive instruction according to the real deformation data, and return to step two.

[0010] In at least one embodiment of the present application, in step 1, providing a synchronous follow-up drive instruction in the test load spectrum according to the estimated deformation data includes:

[0011] The estimated deformation data is used as a follow-up driving instruction in a test load spectrum.

[0012] In at least one embodiment of the present application, in step three, when the error range between the follow-up drive instruction and the actual deformation data does not exceed 5%, the error meets the requirement.

[0013] In at least one embodiment of the present application, in step three, the follow-up drive instruction is corrected according to the real deformation data, including:

[0014] The actual deformation data is used as a follow-up driving instruction in a test load spectrum.

[0015] In at least one embodiment of the present application, the method further includes step 4, performing follow-up loading of the large deformation structure of the aircraft according to the follow-up drive instructions that meet the requirements.

[0016] A second aspect of the present application provides an iterative follow-up loading system for a large deformation structure of an aircraft, comprising:

[0017] A follow-up drive instruction acquisition module is used to obtain the estimated deformation data of the aircraft structure under the fatigue test load, and give a synchronized follow-up drive instruction in the test load spectrum according to the estimated deformation data;

[0018] A real deformation data acquisition module, used to perform fatigue test static measurement and test run according to the follow-up drive instruction, and obtain the real deformation data of the aircraft structure under the fatigue test load;

[0019] The iteration module is used to determine whether the error between the follow-up drive instruction and the real deformation data meets the requirement. If not, the follow-up drive instruction is corrected according to the real deformation data and returned to the real deformation data acquisition module.

[0020] In at least one embodiment of the present application, in the follow-up drive instruction acquisition module, a synchronized follow-up drive instruction is given in the test load spectrum according to the estimated deformation data, including:

[0021] The estimated deformation data is used as a follow-up driving instruction in a test load spectrum.

[0022] In at least one embodiment of the present application, in the iteration module, when the error range between the follow-up drive instruction and the actual deformation data does not exceed 5%, the error meets the requirement.

[0023] In at least one embodiment of the present application, in the iteration module, the follow-up drive instruction is corrected according to the real deformation data, including:

[0024] The actual deformation data is used as a follow-up driving instruction in a test load spectrum.

[0025] In at least one embodiment of the present application, a follow-up loading module is further included, which is used to perform follow-up loading of the large deformation structure of the aircraft according to the follow-up drive instructions that meet the requirements.

[0026] The invention has at least the following beneficial technical effects:

[0027] The iterative follow-up loading method for large deformation structures of aircraft of the present application provides follow-up drive instructions at preset positions according to the estimated deformation data of the aircraft structure in the test load spectrum, collects the actual deformation data of the test and iteratively corrects the preset instructions until the error between the follow-up drive instructions and the actual deformation data actually measured for the aircraft structure reaches the expected target, thereby achieving high-precision loading and avoiding increasing the test risk. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 It is a flow chart of an iterative follow-up loading method for an aircraft large deformation structure according to one embodiment of the present application. DETAILED DESCRIPTION

[0029] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the embodiment of this application will be described in more detail below in conjunction with the drawings in the embodiment 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 embodiments are part of the embodiments of this application, not all of them. The embodiments described below with reference to the drawings are exemplary and are intended to be used to explain this application, and should not be construed as limitations on this application. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The embodiments of this application are described in detail below in conjunction with the drawings.

[0030] In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the scope of protection of the present application.

[0031] The following is combined with Figure 1 This application is described in further detail.

[0032] A first aspect of the present application provides an iterative dynamic loading method for a large deformation structure of an aircraft, comprising the following steps:

[0033] Step 1: Obtain the estimated deformation data of the aircraft structure under the fatigue test load, and give a synchronous follow-up drive instruction in the test load spectrum according to the estimated deformation data;

[0034] Step 2: Perform static measurement and test run of fatigue test according to follow-up drive instructions to obtain real deformation data of aircraft structure under fatigue test load;

[0035] Step 3: determine whether the error between the follow-up drive instruction and the actual deformation data meets the requirement. If not, correct the follow-up drive instruction according to the actual deformation data and return to step 2.

[0036] The invention relates to an iterative servo loading method for large deformation structure of an aircraft. First, according to the estimated deformation data of the aircraft structure under fatigue test load, the estimated deformation data is used as the servo drive instruction in the test load spectrum; then, the fatigue test static measurement and trial operation are performed according to the servo drive instruction to obtain the real deformation data of the aircraft structure under fatigue test load; further, the servo drive instruction in the test load spectrum is corrected according to the obtained real deformation data, and the correction method is to use the real deformation data as the servo drive instruction in the test load spectrum; the fatigue test static measurement and trial operation are continued according to the corrected servo drive instruction to obtain the real deformation data of the aircraft structure under fatigue test load after iteration; the servo drive instruction in the test load spectrum is further corrected according to the real deformation data obtained after iteration, and the iterative correction process is repeated until the error between the servo drive instruction and the measured deformation data of the aircraft structure reaches the expected target. In a preferred embodiment of the invention, when the error range between the servo drive instruction and the real deformation data does not exceed 5%, the error meets the requirement.

[0037] The iterative follow-up loading method for large deformation structures of aircraft of the present application is that the follow-up drive instructions are highly matched with the actual deformation of the aircraft structure after multiple rounds of iterations, and high-precision follow-up loading can be achieved; the follow-up drive instructions are pre-set in the test load spectrum, and there is no risk of load divergence and follow-up drive instability, thus avoiding increasing the risk of systematic testing; the method is simple in principle and has strong versatility.

[0038] Based on the above-mentioned iterative servo loading method for large deformation structure of aircraft, the second aspect of the present application provides an iterative servo loading system for large deformation structure of aircraft, comprising:

[0039] A follow-up drive instruction acquisition module is used to obtain the estimated deformation data of the aircraft structure under fatigue test loads, and to give a synchronized follow-up drive instruction in the test load spectrum according to the estimated deformation data;

[0040] The real deformation data acquisition module is used to perform static measurement and test operation of fatigue test according to the follow-up drive instruction, and obtain the real deformation data of the aircraft structure under the fatigue test load;

[0041] The iteration module is used to determine whether the error between the follow-up drive instruction and the real deformation data meets the requirements. If not, the follow-up drive instruction is corrected according to the real deformation data and returned to the real deformation data acquisition module.

[0042] In a preferred embodiment of the present application, in the follow-up drive instruction acquisition module, a synchronized follow-up drive instruction is given in the test load spectrum according to the estimated deformation data, including: using the estimated deformation data as the follow-up drive instruction in the test load spectrum. In the iteration module, when the error range between the follow-up drive instruction and the actual deformation data does not exceed 5%, the error meets the requirement. In the iteration module, the follow-up drive instruction is corrected according to the actual deformation data, including: using the actual deformation data as the follow-up drive instruction in the test load spectrum. The aircraft large deformation structure iterative follow-up loading system of the present application also includes a follow-up loading module, which is used to perform follow-up loading of the aircraft large deformation structure according to the follow-up drive instruction that meets the requirements.

[0043] 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. An iterative dynamic loading method for large deformation structure of aircraft, characterized in that: include: Step 1: obtaining estimated deformation data of the aircraft structure under fatigue test load, and providing a synchronous follow-up drive instruction in the test load spectrum according to the estimated deformation data; Step 2: Performing fatigue test static measurement and trial operation according to the follow-up drive instruction to obtain real deformation data of the aircraft structure under fatigue test load; Step three: determine whether the error between the follow-up drive instruction and the real deformation data meets the requirement; if not, correct the follow-up drive instruction according to the real deformation data, and return to step two.

2. The iterative dynamic loading method for large deformation structure of aircraft according to claim 1, characterized in that: In step 1, a synchronous follow-up drive instruction is given in the test load spectrum according to the estimated deformation data, including: The estimated deformation data is used as a follow-up driving instruction in a test load spectrum.

3. The iterative dynamic loading method for large deformation structure of aircraft according to claim 1, characterized in that: In step three, when the error range between the follow-up drive instruction and the actual deformation data does not exceed 5%, the error meets the requirement.

4. The iterative dynamic loading method for large deformation structure of aircraft according to claim 1, characterized in that: In step three, the follow-up drive instruction is corrected according to the real deformation data, including: The actual deformation data is used as a follow-up driving instruction in a test load spectrum.

5. The iterative dynamic loading method for large deformation structure of aircraft according to claim 1, characterized in that: The method also includes step 4, performing follow-up loading of the large deformation structure of the aircraft according to the follow-up drive instructions that meet the requirements.

6. An iterative follow-up loading system for large deformation structures of aircraft, characterized in that: include: A follow-up drive instruction acquisition module is used to obtain the estimated deformation data of the aircraft structure under the fatigue test load, and give a synchronized follow-up drive instruction in the test load spectrum according to the estimated deformation data; A real deformation data acquisition module, used to perform fatigue test static measurement and test run according to the follow-up drive instruction, and obtain the real deformation data of the aircraft structure under the fatigue test load; The iteration module is used to determine whether the error between the follow-up drive instruction and the real deformation data meets the requirement. If not, the follow-up drive instruction is corrected according to the real deformation data and returned to the real deformation data acquisition module.

7. The aircraft large deformation structure iterative follow-up loading system according to claim 6, characterized in that: In the follow-up drive instruction acquisition module, a synchronous follow-up drive instruction is given in the test load spectrum according to the estimated deformation data, including: The estimated deformation data is used as a follow-up driving instruction in a test load spectrum.

8. The aircraft large deformation structure iterative follow-up loading system according to claim 6, characterized in that: In the iteration module, when the error range between the follow-up drive instruction and the actual deformation data does not exceed 5%, the error meets the requirement.

9. The aircraft large deformation structure iterative follow-up loading system according to claim 6, characterized in that: In the iteration module, the follow-up drive instruction is corrected according to the real deformation data, including: The actual deformation data is used as a follow-up driving instruction in a test load spectrum.

10. The aircraft large deformation structure iterative follow-up loading system according to claim 6, characterized in that: It also includes a follow-up loading module, which is used to perform follow-up loading of the large deformation structure of the aircraft according to the follow-up driving instructions that meet the requirements.

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