CN114544350A - A connecting strip for strength test of aircraft component with aluminum alloy frame and test method - Google Patents

Abstract

One aspect of the present application provides a connecting strip for strength test of an aircraft component with an aluminum alloy frame. The connecting end of the connecting strip is designed to be stepped, and each step is provided with a bolt hole, so as to be able to be connected with a bolt fastener. On the aluminum alloy frame, in specific applications, the number of steps and the spacing between the bolt holes on each step can be changed to ensure that the fatigue life of the connecting belt plate meets the requirements, and the height of each step and the bolt holes on each step can be adjusted by adjusting the height of each step. Adjust the rigidity of the connecting end of the connecting belt plate, so that the connecting end matches the overall rigidity of the aluminum alloy frame, and has the ability to coordinate deformation with the aircraft components. Another aspect of the present application provides a method for testing the strength of an aircraft component with an aluminum alloy frame. The stiffness matching can meet the requirements, which can ensure the smooth progress of the test and the accuracy of the test results.

Description

A connecting strip for strength test of aircraft component with aluminum alloy frame and test method

technical field

The application belongs to the technical field of strength testing of aircraft components with aluminum alloy frames, and in particular relates to a connecting strip for strength testing of aircraft components with aluminum alloy frames and a test method.

Background technique

Aircraft components mostly contain aluminum alloy frames, such as the airtight roof-frame joint structure of the aircraft fuselage. In the strength test of such aircraft components, the aluminum alloy frames are mostly connected by connecting strips, and the loading mechanism is connected to the aluminum alloy through the connecting strips. The alloy frame transmits the load and then applies it to the component to complete the strength assessment of the aircraft component.

Currently, in order to ensure the fatigue life of the connecting strips, the connecting strips are designed with greater strength, thicker thickness and heavier mass. However, in some cases, it is not only required to apply test loads to aircraft components, but also It is necessary to transfer the load smoothly and evenly between the connecting strip and the aluminum alloy frame, and to match the overall rigidity of the connecting strip and the aluminum alloy frame, and to have the ability to coordinate deformation with the aircraft components.

The present application is made in view of the existence of the above-mentioned technical defects.

It should be noted that the disclosure of the above background technology content is only used to assist the understanding of the inventive concept and technical solution of the present invention, and it does not necessarily belong to the prior art of the present patent application. If the filing date has been disclosed, the above background art should not be used to evaluate the novelty and inventive step of the present application.

SUMMARY OF THE INVENTION

The purpose of the present application is to provide a connecting strip for strength test of an aircraft component with an aluminum alloy frame and a test method, so as to overcome or alleviate the known technical defects in at least one aspect.

The technical solution of this application is:

On the one hand, there is provided a connecting strip for strength test of aircraft components with an aluminum alloy frame. One end of the connecting strip is a connecting end, which is in the shape of steps, and each step has a bolt hole, so as to be able to be connected to the aluminum alloy frame with a bolt fastener. superior;

The other end of the connecting belt plate is the loading end, and there are pin holes on it, so that the pins can be connected to the loading mechanism, so that the test load applied by the loading mechanism can be transferred to the aluminum alloy frame, and then transferred to the aircraft components. Components are tested for strength.

According to at least one embodiment of the present application, in the above-mentioned connecting strip for the strength test of the aircraft component with an aluminum alloy frame, the thickness increment between adjacent steps on the connecting end of the connecting strip does not exceed 2.

According to at least one embodiment of the present application, in the above-mentioned connecting strip for strength test of aircraft components with aluminum alloy frame, the spacing between bolt holes on each step of the connecting end of the connecting strip is 3-6 times the diameter of the bolt holes.

According to at least one embodiment of the present application, in the above-mentioned connecting strip for the strength test of an aircraft component with an aluminum alloy frame, the thickness increment between adjacent steps does not exceed 2.

On the other hand, a method for testing the strength of an aircraft component with an aluminum alloy frame, comprising:

Design the shape of the connecting strip according to the shape and size of the aluminum alloy frame;

Carry out detailed design of the structure of the connecting strip, including the number and height of the steps on the connecting end of the connecting strip, and the number and diameter of the bolt holes on each step;

Build a three-dimensional model of the connection between the strip and the aircraft components, and use the finite element analysis method to verify whether the fatigue life of the strip and the rigidity of the aluminum alloy frame meet the requirements. If the requirements are not met, the structure of the connection strip is redesigned carry out detailed design;

Making connecting strips;

The strength test of the aircraft components is carried out by connecting the belt plate with the loading mechanism.

According to at least one embodiment of the present application, in the above-mentioned method for testing the strength of an aircraft component with an aluminum alloy frame, the loading mechanism is an actuator or a testing machine.

The present application has at least the following beneficial technical effects:

On the one hand, there is provided a connecting strip for strength test of an aircraft component with an aluminum alloy frame, the connecting end of the connecting strip is designed to be stepped, and each step has a bolt hole, so as to be able to be connected to the aluminum alloy with a bolt fastener. On the frame, in specific applications, the number of steps and the spacing between the bolt holes on each step can be changed to ensure that the fatigue life of the connecting belt plate meets the requirements, and the height of each step and the size of the bolt holes on each step can be adjusted. , Adjust the rigidity of the connecting end of the connecting belt plate, so that the connecting end matches the overall rigidity of the aluminum alloy frame, and has the ability to coordinate deformation with the aircraft components.

On the other hand, a strength test method for aircraft components with aluminum alloy frame is provided, which is implemented based on the above-mentioned strength test of aircraft components with aluminum alloy frame connecting strips, which can ensure the fatigue life of the connecting strips to match the rigidity of the aluminum alloy frame. To meet the needs, it can ensure the smooth progress of the test and the accuracy of the test results.

Description of drawings

Fig. 1 is the schematic diagram of the strength test connection belt plate with aluminum alloy frame aircraft components provided by the embodiment of the present application;

Fig. 2 is the schematic diagram of the strength test of the aircraft assembly with the aluminum alloy frame provided by the embodiment of the present application, the connection strip and the aircraft assembly are matched;

3 is a flow chart of a method for testing the strength of an aircraft component with an aluminum alloy frame provided by an embodiment of the present application;

in:

1-connecting belt plate; 2-aluminum alloy frame; 3-aircraft components.

In order to better illustrate this embodiment, some parts in the drawings are omitted, enlarged or reduced, which do not represent the size of the actual product; in addition, the drawings are used for exemplary description, and their positional relationship is only for exemplary description and cannot be understood to limit this patent.

Detailed ways

In order to make the technical solution of the present application and its advantages more clear, the technical solution of the present application will be further described in detail and completely with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only part of the present application. The examples are only used to explain the present application, but 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 drawings, and other related parts may refer to the general design. If there is no conflict, the embodiments in the present application and the techniques in the embodiments Features can be combined with each other to obtain new embodiments.

Also, unless otherwise defined, technical or scientific terms used in the description of this application shall have the ordinary meaning as understood by those of ordinary skill in the art to which this application belongs. The words "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", etc. used in the description of this application to indicate orientation are only used To indicate relative direction or positional relationship, rather than implying that the device or element must have a specific orientation, be constructed and operated in a specific orientation, and when the absolute position of the described object changes, its relative positional relationship may also change accordingly. , so it cannot be construed as a limitation on this application. The terms "first", "second", "third" and similar terms used in the description of this application are only used for descriptive purposes, to distinguish different components, and cannot be construed as indicating or implying relative importance. Words like "a," "an," or "the" used in the description of this application should not be construed as an absolute limitation on quantity, but rather as the presence of at least one. As used in the description of this application, "comprises" or "comprising" and similar words mean that the elements or things appearing before the word encompass the elements or things listed after the word and their equivalents, but do not exclude other elements or things.

In addition, it should be noted that, unless otherwise expressly specified and limited, the words "installed", "connected", "connected" and the like used in the description of this application should be understood in a broad sense, for example, the connection may be a fixed The connection can also be a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, or it can be an internal connection between two components. A skilled person can understand its specific meaning in this application according to specific circumstances.

The present application will be further described in detail below with reference to FIGS. 1 to 3 .

On the one hand, a connecting strip plate with an aluminum alloy frame for strength test of aircraft components is provided. One end of the connecting strip plate 1 is a connecting end, which is in the shape of steps, and each step has a bolt hole, so as to be able to cooperate with bolt fasteners to connect to the aluminum alloy. on box 2;

The other end of the connecting strip 1 is the loading end, which has pin holes on it, so that the pins can be connected to the loading mechanism, so that the test load applied by the loading mechanism can be transferred to the aluminum alloy frame 2, and then transferred to the aircraft component 3. , the strength test of aircraft component 3 is carried out.

For the strength test connecting strip plate with an aluminum alloy frame disclosed in the above embodiment, those skilled in the art can understand that the connecting end of the connecting strip plate 1 is designed to be stepped, and each step has a bolt hole, It can be connected to the aluminum alloy frame 2 with bolt fasteners. In specific applications, the number of steps and the spacing between the bolt holes on each step can be changed to ensure that the fatigue life of the connecting strip 1 meets the requirements, and can be passed through. Adjust the height of each step, the size of the bolt hole on each step, and adjust the stiffness of the connecting end of the connecting belt plate 1 so that the connecting end matches the overall stiffness of the aluminum alloy frame 2 and has the ability to coordinate deformation with the aircraft component 3 .

In some optional embodiments, in the above-mentioned connecting strip for strength test of aircraft components with aluminum alloy frame, the thickness increment between adjacent steps on the connecting end of connecting strip 1 does not exceed 2.

In some optional embodiments, in the above-mentioned connecting strip for strength test of aircraft components with aluminum alloy frame, the spacing between bolt holes on each step of the connecting end of connecting strip 1 is 3-6 times the diameter of the bolt holes.

In some optional embodiments, in the above-mentioned connecting strips for the strength test of aircraft components with aluminum alloy frames, the thickness increment between adjacent steps does not exceed 2.

On the other hand, a method for testing the strength of an aircraft component with an aluminum alloy frame, comprising:

According to the shape and size of the aluminum alloy frame 2 and the loading scheme required by the aircraft component 3, the shape of the connecting strip 1 is designed;

Carry out a detailed design of the structure of the connecting belt plate 1, including the number and height of the steps on the connecting end of the connecting belt plate 1, and the number and diameter of the bolt holes on each step;

Build a three-dimensional model of the connection between the connecting plate 1 and the aircraft component 3, and use the finite element analysis method to verify whether the fatigue life of the connecting plate 1 and the stiffness matching of the aluminum alloy frame 2 meet the requirements. If the requirements are not met, reconnect the connection The structure of the belt plate 1 is designed in detail;

Making the connecting strip 1, the specific process is drawing processing drawings, designing processing technology and manufacturing, etc.;

The component-level strength test of the aircraft component 3 is carried out with the connecting strip 1 and the loading mechanism.

For the strength test method for an aircraft component with an aluminum alloy frame disclosed in the above embodiments, those skilled in the art can understand that the verification of whether the fatigue life of the splicing plate 1 meets the requirements specifically refers to verifying that the splicing plate 1 Whether the fatigue life is much greater than that of aircraft component 3, when its fatigue life has no advantage over aircraft component 3, the connection can be made by increasing the number of steps on the connecting end of the connecting strip 1 and reducing the spacing between the bolt holes on each step. The stress distribution at the ends is more uniform, thereby increasing the fatigue life of the splicing plate 1, so that the fatigue life of the splicing plate 1 far exceeds that of the aircraft component 3 to meet the requirements.

For the strength test method for an aircraft assembly with an aluminum alloy frame disclosed in the above-mentioned embodiments, those skilled in the art can also understand that when it is verified that the stiffness matching between the splicing plate 1 and the aluminum alloy frame 2 does not meet the requirements, the The height of the steps and the diameter of the bolt holes on each step are reduced, and the rigidity of the connecting end of the connecting strip 1 is reduced, so that the connecting end matches the overall rigidity of the aluminum alloy frame 2, and has the ability to coordinate deformation with the aircraft component 3.

In some optional embodiments, in the above-mentioned method for testing the strength of an aircraft component with an aluminum alloy frame, the loading mechanism is a hydraulic cylinder or a standard testing machine.

The various embodiments in the specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments, and the same and similar parts between the various embodiments may be referred to each other.

So far, the technical solutions of the present application have been described with reference to the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments, without departing from the principles of the present application. Under the premise that those skilled in the art can make equivalent changes or replacements to the relevant technical features, the technical solutions after these changes or replacements will fall within the protection scope of the present application.

Claims (6)

1. An airplane component strength test connecting strip plate with an aluminum alloy frame is characterized in that,

one end of the connecting band plate (1) is a connecting end and is step-shaped, and each step is provided with a bolt hole so as to be connected to the aluminum alloy frame (2) by matching with a bolt fastener;

the other end of the connecting belt plate (1) is a loading end, a pin hole is formed in the connecting belt plate, the connecting belt plate can be connected to a loading mechanism through a pin in a matched mode, test load applied by the loading mechanism can be transmitted to the aluminum alloy frame (2) and then to the aircraft assembly (3), and strength test is conducted on the aircraft assembly (3).

2. The aircraft component strength test connecting strip with the aluminum alloy frame as claimed in claim 1,

the thickness of the adjacent steps on the connecting end of the connecting band plate (1) is gradually increased by no more than 2.

3. The aircraft component strength test connecting strip with the aluminum alloy frame as claimed in claim 1,

the distance between the bolt holes on each step of the connecting end of the connecting band plate (1) is 3-6 times of the diameter of the bolt holes.

4. The aircraft component strength test connecting strip with the aluminum alloy frame as claimed in claim 1,

the thickness between adjacent steps increases by no more than 2.

5. The method for testing the strength of the airplane component with the aluminum alloy frame is characterized by comprising the following steps of:

designing the appearance of the connecting band plate (1) according to the shape and the size of the aluminum alloy frame (2);

the structure of the connecting band plate (1) is designed in detail, and the structure comprises the number and the height of steps on the connecting end of the connecting band plate (1) and the number and the diameter of bolt holes on each step;

constructing a three-dimensional model of the connection belt plate (1) matched with the airplane component (3), verifying whether the fatigue life of the connection belt plate (1) and the rigidity matching of the connection belt plate and the aluminum alloy frame (2) meet requirements or not by a finite element analysis method, and re-designing the structure of the connection belt plate (1) in detail when the requirements are not met;

manufacturing a connecting belt plate (1);

and the connecting belt plate (1) is matched with the loading mechanism to carry out strength test on the airplane assembly (3).

6. The strength test method of an airplane component with an aluminum alloy frame according to claim 5,

the loading mechanism is an actuating cylinder or a testing machine.

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