In-situ printing apparatus and method for vibration performance testing of an aeronautical component

Abstract

The application relates to an in-situ printing device and method for testing the damping performance of an aviation component, belonging to the technical field of aerospace, which is prepared by 3D printing technology in-situ in the form of an alternative sandwich composite of a novel semi-crystalline aromatic plastic engineering plastic material and damping rubber. The device comprises the following steps: detecting the amplitude and vibration acceleration generated by multiple points of the aviation component during work, recording the coordinate position information of each point, and analyzing the vibration of each point; and selecting multiple vibration points with the most representative vibration data from the analysis results as vibration sources. The in-situ printing mechanical arm of the device prints an aviation component damping pad with a sinusoidal composite sandwich damping structure according to the collected vibration source data and distribution information; the device can freely detect the vibration data of the aviation component during work, and in-situ print a sinusoidal sandwich structure at the vibration source, so that the effect of in-situ damping is achieved; and the device can adapt to the shape and structure of various aviation components.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of aerospace, and particularly relates to an in-situ printing device and method for testing the vibration reduction performance of an aviation component. BACKGROUND

[0002] With the development of social economy and the progress of modern industrial technology, the research on vibration and noise control technology has attracted more and more attention from experts and scholars. Vibration is one of the phenomena that occur frequently in nature, and in the fields of aerospace, ship engineering, automobile industry, medical instruments and military equipment, the influence of vibration is conducive to the production and manufacture of people, the medical application. For example, the mechanical industry uses vibration for cutting processing, and the vibration drying machine and other vibration machines bring great changes to the development of engineering projects. The influence of vibration also has certain negative effects. For example, vibration and noise will directly affect people's physical and mental health and daily life; in the mechanical field, vibration will cause serious fatigue damage to mechanical equipment and reduce the service life of parts.

[0003] Taking an aero-engine as an example, vibration is an important monitoring parameter of the aero-engine, and various vibration problems need to be solved when the engine is tested. The engine vibration is particularly important because the vibration directly affects the normal work and service life of the engine, and if the engine vibration is abnormal and not checked and eliminated in time, it may cause serious consequences. The vibration failure of the aero-engine has complexity and randomness, and the causes of the engine vibration failure are various, and the vibration failure phenomena are different. The traditional vibration reduction parts of the aero-engine are difficult to adapt to the complex curved surface of the aero-component shape, and can only re-design the assembly relationship of the vibration reduction parts on the aero-component shape structure and reserve the vibration reduction part assembly position, and it is helpless for the parts with dead space in the structure design. However, the aero-component that can provide a reserved position may not be the vibration source point or far away from the vibration source point, so that the vibration reduction effect cannot achieve the expected vibration reduction effect. On the other hand, the selection of vibration reduction materials and the structure design of vibration reduction parts are also very important. The traditional vibration reduction material directly selects an alloy material to make a vibration reduction block to fix the vibration part to reduce the vibration, and such vibration reduction block is thick and has poor shape adaptation ability, and in the design of the vibration reduction structure, a solid structure produced by a traditional processing technology or a spring vibration reduction is mostly selected. For some topologically optimized structures, the selection of processing technology is too high or even cannot be realized. SUMMARY

[0004] The application aims to provide an in-situ printing device and method for testing the vibration reduction performance of an aviation component, which provides a new solution for testing the vibration reduction performance of the aviation component and the structure of the vibration reduction part, is better suitable for various complex surface shapes of the aviation component, provides a new vibration reduction structure to ensure that the vibration reduction performance meets the requirements and reduces the vibration reduction part.

[0005] To achieve this object, the following technical solutions are adopted:

[0006] A kind of in-situ printing device for the vibration performance test of aeronautical component, adopts six-axis in-situ printing mechanical arm, uses the vibration measuring probe of piezoelectric sensor on mechanical arm, uses the multi-nozzle structure of rotation on mechanical arm, selects new semi-crystalline aromatic plastic engineering plastic material and damping rubber as damping structure material;Sinusoidal sandwich damping structure is printed in-situ at vibration source.

[0007] Further, the thickness of piezoelectric sensor is 0.5-1.5mm;Vibration displacement measurement range is 0.001-1.999mm;The measurement range of vibration velocity is 0.1-199.9m / s effective value;The measurement range of vibration acceleration is 0.1-199.9m / s 2 , measurement error is guaranteed at ±5%Hz.

[0008] Further, the new semi-crystalline aromatic plastic engineering plastic material and damping rubber are used as structural materials.

[0009] A kind of in-situ printing method for the vibration performance test of aeronautical component, suitable for the in-situ printing device for the vibration performance test of aeronautical component described above, comprising:

[0010] Step S1, after installing and positioning aeronautical component, it is in working condition, let the vibration probe of mechanical arm start vibration test and collect data on aeronautical component;

[0011] Step S2, obtain the vibration velocity, vibration displacement, vibration acceleration and other parameters of each vibration point of aeronautical component respectively, analyze the vibration transmission characteristics of vibration point according to each parameter;

[0012] Step S3, after determining the vibration source point position of aeronautical component, the in-situ printing device of mechanical arm determines the printing space coordinate system according to the surface contour shape of aeronautical component;

[0013] Step S4, further on the basis of step S3, the sinusoidal alternating sandwich structure printed using PEEK material and damping rubber is a subunit of the damping part designed;

[0014] Step S5, after the damping part established in step S4, the steps of step S1 and step S2 are carried out again, vibration test data is obtained again, and the damping effect is analyzed by comparing the two test data.

[0015] Further, after vibration data is collected by vibration probe, the most significant vibration data is selected as measurement point.

[0016] Further, the method further comprises detecting the amplitude and vibration acceleration generated by the plurality of points of the aviation component in operation, recording the coordinate position information of each point, and analyzing the vibration of each point, and screening a plurality of vibration points with the most representative vibration data from the analysis results as the vibration source.

[0017] Compared with the prior art, the present application has the following beneficial effects:

[0018] 1. The in-situ printing device and method for testing the vibration reduction performance of aviation components provided by the present application have a short response time and high degree of freedom, and can replace manual work in high-risk and harmful environments.

[0019] 2. The in-situ printing device and method for testing the vibration reduction performance of aviation components provided by the present application can print in more complex environments and adapt to the curved surface shapes of various aviation components.

[0020] 3. The in-situ printing device and method for testing the vibration reduction performance of aviation components provided by the present application use a piezoelectric ceramic spherical probe to measure vibration in a wider range on the surface of complex aviation components, improve the accuracy of measurement data, and the measurement data includes vibration speed, vibration displacement, and vibration acceleration to ensure the reliability of the data.

[0021] 4. The in-situ printing device and method for testing the vibration reduction performance of aviation components provided by the present application use a rotary multi-nozzle structure to mix and print multiple materials on the same part to improve the use performance of the printed part, the overall coordinate position is guaranteed by the mechanical arm printing device itself during single printing, the coordinate error caused by human factors is reduced, and the accuracy of part printing is ensured in real time.

[0022] 5. The in-situ printing device and method for testing the vibration reduction performance of aviation components provided by the present application use a new type of semi-crystalline aromatic plastic engineering plastic material and a vibration reduction rubber as a structural material. PEEK material has strong mechanical properties, is resistant to chemical corrosion, is fatigue-resistant and has high resilience, and still has good performance under high temperature conditions. The weight of PEEK material is lighter, which meets the needs of aviation engineering. The vibration reduction rubber has good vibration isolation and impact buffering strength, high resilience and high friction coefficient, and can maintain the stability of the vibration reduction structure skeleton, and has good protection effect.

[0023] 6. The in-situ printing device and method for testing the vibration reduction performance of aviation components provided by the present application can increase the gap between vibration and vibration source to increase the damping of vibration transmission. The distribution of the sinusoidal structure has good load-bearing performance, and the gap between the structure units plays an important role in weight reduction. BRIEF DESCRIPTION OF DRAWINGS

[0024] Figure 1 Schematic diagram of a six-axis robot for in-situ 3D printing;

[0025] Figure 2 Schematic diagram of an in-situ printing device;

[0026] Figure 3 Material distribution diagram of a subunit of a vibration reduction structure;

[0027] Figure 4 Diagram of a sinusoidal alternating sandwich structure;

[0028] Figure 5 Diagram of vibration data analysis of an aviation component DETAILED DESCRIPTION

[0029] The present application is described in the following based on examples, but the present application is not limited to these examples only. In the following detailed description of the present application, some specific details are described in detail. The present application can also be completely understood without the description of these details by those skilled in the art. In order to avoid obscuring the essence of the present application, well-known methods, processes, procedures, elements and circuits are not described in detail.

[0030] In addition, it should be understood by those of ordinary skill in the art that the drawings provided herein are for illustrative purposes only and the drawings are not necessarily drawn to scale.

[0031] At the same time, it should be understood that in the following description, "circuit" refers to a conductive loop composed of at least one element or sub-circuit through electrical or electromagnetic connection. When an element or circuit is said to be "connected to" another element or said to be "connected between" two nodes, it can be directly coupled or connected to another element or there can be intermediate elements, and the connection between elements can be physical, logical, or a combination thereof. On the contrary, when an element is said to be "directly coupled to" or "directly connected to" another element, it means that there is no intermediate element between the two.

[0032] Unless the context clearly requires otherwise, throughout the description and the claims, "comprise", "comprise", and similar words such as "comprise" should be interpreted as inclusive rather than exclusive or exhaustive; that is, in the sense of "including, but not limited to".

[0033] In the description of the present application, it should be understood that the terms "first", "second", etc. are only for descriptive purposes and should not be understood as indicating or implying relative importance. In addition, in the description of the present application, unless otherwise stated, the meaning of "multiple" is two or more.

[0034] The specific content of the present application is further described below in conjunction with the drawings.

[0035] In Figure 1The in-situ 3D printing six-axis mechanical arm in the in-situ 3D printing system contacts the aviation component as a vibration measurement point as a first step in actual work Figure 2 The vibration measurement probe in the in-situ 3D printing system contacts the aviation component as a vibration measurement point as a first step in actual work Figure 2 The in-situ printing device of the mechanical arm constructs a printing coordinate system of the vibration source measurement point according to the surface shape of the aviation component, and transmits the position information of the vibration source measurement point to the data receiving end of the mechanical arm and enters the next printing work. Figure 4 The printing device starts heating the PEEK raw material and the damping rubber raw material, and the operating system uses the sinusoidal alternating sandwich structure as a subunit, and uses the PEEK material and the damping rubber alternately according to the material forming and layout Figure 3 The vibration data of the damping parts at each vibration source point is measured again after the aviation component is in the working state, and the vibration data after the damping parts are installed is compared with the vibration data before the damping parts are installed. Figure 5 The vibration amplitude curve shows that the damping effect is obvious.

[0036] The rotating multi-nozzle design can mix and print multiple materials on the same part, improving the performance of the printed part. In addition, the rotating nozzle can ensure the overall coordinate position during single printing, reducing the coordinate error caused by human factors and ensuring the accuracy of part printing in real time. The PEEK material used has excellent physical and mechanical properties, and can replace traditional materials such as metal and ceramic, making a significant contribution to weight reduction. The sinusoidal alternating sandwich structure can greatly improve the resilience of the damping pad, thereby increasing the damping of vibration transmission, and has a significant effect on weight reduction. The damping rubber itself has good vibration isolation effect on the vibration generated by the aviation component, and the high friction coefficient of the damping rubber can increase the stability of the sinusoidal alternating sandwich structure, protect the PEEK material from wear and tear, and improve the service life of the damping pad.

[0037] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present application, and are not limited thereto; although the present application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the foregoing embodiments, or make equivalent substitutions for part or all of the technical features; and these modifications or substitutions do not make the essence of the corresponding technical solutions deviate from the scope of the technical solutions of the embodiments of the present application.

Claims

1. An in-situ printing device for vibration performance testing of an aeronautical component, characterized in that, The six-axis in-situ printing mechanical arm is provided with a piezoelectric sensor vibration measuring probe, a rotary multi-nozzle structure on the mechanical arm is used, and a new type of semi-crystalline aromatic plastic engineering plastic material and a damping rubber are selected as damping structure materials. A sine sandwich damping structure is printed in situ at the vibration source. The piezoelectric sensor has a thickness of 0.5-1.5 mm, a vibration displacement measurement range of 0.001-1.999 mm, a vibration velocity measurement range of 0.1-199.9 m / s, and a vibration acceleration measurement range of 0.1-199.9 m / s2, and the measurement error is guaranteed to be within ±5% Hz. The new type of semi-crystalline aromatic plastic engineering plastic material and the damping rubber are used as the structure materials.

2. A method for in-situ printing for aero component vibration performance test, applicable to the in-situ printing device for aero component vibration performance test of claim 1, characterized in that, The method comprises the following steps: Step S1, after the aviation component is installed and positioned, the aviation component is in a working state, the vibration measuring probe of the mechanical arm starts vibration test on the aviation component and collects data; Step S2, the vibration velocity, vibration displacement, vibration acceleration and other parameters of each vibration measuring point of the aviation component are obtained respectively, and the vibration transmission characteristics of the vibration measuring point are analyzed according to the parameters; Step S3, after the vibration source point position of the aviation component is determined, the in-situ printing device of the mechanical arm determines the printing space coordinate system according to the surface shape of the aviation component; Step S4, further based on step S3, the sine alternating sandwich structure printed by the PEEK material and the damping rubber is used to construct and design a damping part as a subunit; Step S5, after the damping part established in step S4, the steps of step S1 and step S2 are performed again, vibration test data is obtained again, and the damping effect is analyzed by comparing the two test data.

3. The method for in-situ printing of aero component for vibration performance test according to claim 2, wherein, After the vibration data of the measuring points are collected by the vibration measuring probe, the most significant vibration data are selected as the measuring points.

4. The in-situ printing method for vibration performance test of an aeronautical component according to claim 3, characterized in that, Further comprising: The amplitudes and vibration accelerations generated by multiple points of the aviation component during work are detected, the coordinate position information of each point is recorded, and the vibration of each point is analyzed, and multiple vibration points with the most representative vibration data are selected as the vibration sources from the analysis results.

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