Airplane ground vibration test design method based on model driving

Abstract

The invention belongs to the technical field of full-size aircraft ground vibration tests, and particularly relates to an aircraft ground vibration test design method based on model driving, which comprises the following steps: S1, establishing an aircraft dynamics model, and carrying out dynamics characteristic analysis; s2, designing a bracket system according to the size, the weight, the gravity center and the inertia moment data of the aircraft dynamics model and the frequency required by test support; designing a measurement point arrangement scheme and an excitation point arrangement scheme according to the modal shape of the dynamic characteristic analysis result and discrete mass data; and S3, according to the designed bracket system, the measurement point arrangement scheme and the excitation point arrangement scheme, combining a test system model with the aircraft dynamics model to perform assembly, thereby forming a full-aircraft ground vibration test simulation model. And S4, carrying out a physical test based on the full-aircraft ground vibration test simulation model. According to the invention, the scheme design reliability and efficiency of the whole aircraft ground vibration test are effectively improved, and the risk in the physical test process is reduced.

Description

Technical Field

[0001] The present application belongs to the technical field of full-scale aircraft ground vibration tests, and in particular relates to a model-driven aircraft ground vibration test design method. Background Art

[0002] The Ground Vibration Test (GVT) is a test method to determine the dynamic characteristics of the aircraft structure (also known as modal parameters). These parameters include the natural frequencies of each order, natural vibration mode, damping coefficient and generalized mass of the aircraft structure. It is a large-scale ground verification test that must be carried out during the development or modification of the aircraft. The test data is an important basis for the modification of the finite element model of the whole aircraft, aeroelastic analysis, vibration control, etc. It is an important means to verify the compliance of aeroelastic indicators.

[0003] There are generally many different aircraft configurations for the ground vibration test of the whole aircraft, and they are all carried out before the first flight, which puts a lot of pressure on the test cycle. Moreover, with the continuous emergence of new materials, new structures, and new aerodynamic layouts, the dynamic characteristics of aircraft structures are becoming more and more complex. The design verification of the aircraft support system, the application of exciting forces, and the identification of modes are currently existing technical difficulties, which make the aircraft development cost high and the cycle long. How to improve the efficiency and accuracy of the GVT test and reduce the physical test cycle and risk is the current research trend at home and abroad. In order to shorten the cycle of physical tests and improve the accuracy and efficiency of tests, it is necessary to fully consider the influence of various factors in the scheme design stage. Traditional test designs are based on the physical prototype of the aircraft. It is often found at the test site that the support system and the aircraft interfere with each other, and the arrangement of the exciter is not very reasonable. Problems such as rework and modification are required, which lengthens the test cycle. Therefore, the traditional scheme design method can no longer meet the test requirements of modern aircraft. The present invention proposes a model-driven aircraft ground vibration test scheme design method, which can effectively improve the design reliability and reduce the rework rate of the test design. It is of great significance to improve the efficiency of aircraft ground vibration tests and improve the accuracy of test results. After extensive research, no reports on this method were found in the publicly published literature at home or abroad. Summary of the invention

[0004] In order to solve the above problems, this application provides a model-driven aircraft ground vibration test design method, including:

[0005] Step S1: Establish an aircraft dynamics model and perform dynamics characteristics analysis.

[0006] Step S2: designing a support system according to the size, weight, center of gravity, moment of inertia data of the aircraft dynamics model and the frequency required for test support; designing a measurement point arrangement scheme and an excitation point arrangement scheme according to the modal vibration shape and discrete mass data of the dynamic characteristics analysis results;

[0007] Step S3: assembling the test system model and the aircraft dynamics model according to the designed support system, measurement point arrangement scheme, and excitation point arrangement scheme to form a full-aircraft ground vibration test simulation model.

[0008] Step S4: Performing a physical test based on the full-machine ground vibration test simulation model.

[0009] Preferably, the test system model includes but is not limited to a sensor simulation model, an exciter simulation model, and a test control device model.

[0010] Preferably, the test supports a required frequency of no more than one third of an elastic modal frequency of the aircraft, and the elastic modal frequency of the aircraft is obtained by dynamic characteristic analysis.

[0011] Preferably, after the support system is designed, a parameterized model of the support system is established and verified through simulation.

[0012] Preferably, after step S3, the following steps are further included:

[0013] Step S31: performing interference checks between devices and between devices and aircraft structures, and verifying the rationality of the arrangement schemes of excitation points and measurement points on the full-aircraft ground vibration test simulation model;

[0014] Step S32: When the interference check and rationality verification are passed, the final full-machine ground vibration test simulation model is formed, otherwise the support system, measurement point arrangement plan, and excitation point arrangement plan are adjusted and returned to step S3.

[0015] Preferably, a plurality of sensors are arranged at each measuring point, and faulty sensors are eliminated by a voting method.

[0016] The advantages of the present invention are as follows: strong applicability, and can be effectively applied to the scheme design stage of the ground vibration test of a full-scale aircraft; the support system is designed and the sensor and the exciter are optimally arranged through model driving, and the support process simulation, interference inspection, excitation and measurement scheme verification can be carried out on the model, thereby effectively improving the scheme design reliability and efficiency of the ground vibration test of the whole aircraft and reducing the risks in the physical test process. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 The invention is a model-driven aircraft ground vibration test design method according to a preferred embodiment of the present application. DETAILED DESCRIPTION

[0018] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be further described in detail in detail and in detail in conjunction with the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design. In the absence of conflict, the embodiments in the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0019] like Figure 1 As shown, the present application provides a model-driven aircraft ground vibration test design method, including:

[0020] Step S1: Establish an aircraft dynamics model and perform dynamics characteristics analysis.

[0021] Step S2: designing a support system according to the size, weight, center of gravity, moment of inertia data of the aircraft dynamics model and the frequency required for test support; designing a measurement point arrangement scheme and an excitation point arrangement scheme according to the modal vibration shape and discrete mass data of the dynamic characteristics analysis results;

[0022] Step S3: According to the designed support system, measurement point arrangement scheme, and excitation point arrangement scheme, the test system model is assembled with the aircraft dynamics model to form a full-aircraft ground vibration test simulation model. In the above steps, the designed support system is combined with the aircraft dynamics model, and the sensor simulation model and the exciter simulation model are arranged and connected according to the measurement point arrangement scheme and the excitation point arrangement scheme, and are connected with the test control device model. Here, the test system model also includes other equipment required in the test.

[0023] The method further includes: step S31: performing interference checks between devices and between devices and aircraft structures, and verifying the rationality of the arrangement schemes of excitation points and measurement points on the full-aircraft ground vibration test simulation model;

[0024] Step S32: When the interference check and rationality verification are passed, the final test plan is formed, otherwise the support system, measurement point arrangement plan, and excitation point arrangement plan are adjusted and the process returns to step S3.

[0025] Step S4: Performing a physical test based on the full-machine ground vibration test simulation model.

[0026] Preferably, the test supports a required frequency of no more than one third of an elastic modal frequency of the aircraft, and the elastic modal frequency of the aircraft is obtained by dynamic characteristic analysis.

[0027] Preferably, after the support system is designed, a parameterized model of the support system is established and verified through simulation.

[0028] Preferably, a plurality of sensors are arranged at each measuring point, and faulty sensors are eliminated by a voting method.

[0029] The advantages of the present invention are as follows: strong applicability, and can be effectively applied to the scheme design stage of the ground vibration test of a full-scale aircraft; the support system is designed and the sensor and the exciter are optimally arranged through model driving, and the support process simulation, interference inspection, excitation and measurement scheme verification can be carried out on the model, thereby effectively improving the scheme design reliability and efficiency of the ground vibration test of the whole aircraft and reducing the risks in the physical test process.

[0030] 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 model-driven aircraft ground vibration test design method, characterized in that: include: Step S1: Establish an aircraft dynamics model and perform dynamics characteristics analysis. Step S2: designing a support system according to the size, weight, center of gravity, moment of inertia data of the aircraft dynamics model and the frequency required for test support; designing a measurement point arrangement scheme and an excitation point arrangement scheme according to the modal vibration shape and discrete mass data of the dynamic characteristics analysis results; Step S3: assembling the test system model and the aircraft dynamics model according to the designed support system, measurement point arrangement scheme, and excitation point arrangement scheme to form a full-aircraft ground vibration test simulation model. Step S4: Performing a physical test based on the full-machine ground vibration test simulation model.

2. The model-driven aircraft ground vibration test design method according to claim 1, characterized in that: The test system model includes but is not limited to a sensor simulation model, an exciter simulation model, and a test control device model.

3. The model-driven aircraft ground vibration test design method according to claim 1, characterized in that: The test supports the required frequency to be no higher than one third of the elastic modal frequency of the aircraft, which is obtained through dynamic characteristic analysis.

4. The model-driven aircraft ground vibration test design method according to claim 1, characterized in that: After the support system is designed, a parameterized model of the support system is established and verified through simulation.

5. The model-driven aircraft ground vibration test design method according to claim 1, characterized in that: The step S3 further includes: Step S31: performing interference checks between devices and between devices and aircraft structures, and verifying the rationality of the arrangement schemes of excitation points and measurement points on the full-aircraft ground vibration test simulation model; Step S32: When the interference check and rationality verification are passed, the final full-machine ground vibration test simulation model is formed, otherwise the support system, measurement point arrangement plan, and excitation point arrangement plan are adjusted and returned to step S3.

6. The model-driven aircraft ground vibration test design method according to claim 1, characterized in that: Multiple sensors are arranged at each measuring point, and faulty sensors are eliminated through voting.

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