CN114544350A - Airplane component strength test connecting strip plate with aluminum alloy frame and test method - Google Patents
Airplane component strength test connecting strip plate with aluminum alloy frame and test method Download PDFInfo
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- CN114544350A CN114544350A CN202210179520.8A CN202210179520A CN114544350A CN 114544350 A CN114544350 A CN 114544350A CN 202210179520 A CN202210179520 A CN 202210179520A CN 114544350 A CN114544350 A CN 114544350A
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- aluminum alloy
- alloy frame
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- strength test
- band plate
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/08—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/02—Details
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0058—Kind of property studied
- G01N2203/0069—Fatigue, creep, strain-stress relations or elastic constants
- G01N2203/0073—Fatigue
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/02—Details not specific for a particular testing method
- G01N2203/0202—Control of the test
- G01N2203/0212—Theories, calculations
- G01N2203/0216—Finite elements
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/02—Details not specific for a particular testing method
- G01N2203/06—Indicating or recording means; Sensing means
- G01N2203/067—Parameter measured for estimating the property
- G01N2203/0682—Spatial dimension, e.g. length, area, angle
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- General Physics & Mathematics (AREA)
- Health & Medical Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Chemical & Material Sciences (AREA)
- Analytical Chemistry (AREA)
- Biochemistry (AREA)
- General Health & Medical Sciences (AREA)
- Immunology (AREA)
- Pathology (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The utility model provides an on the one hand, the connection band plate is connected in aircraft subassembly strength test with aluminum alloy frame, the link that its design connection band plate is the step form, and the bolt hole has on every step, with can cooperate bolt fastening spare to be connected to the aluminum alloy frame, when concrete application, the accessible changes the quantity of step and the interval between the bolt hole on each step, guarantee to connect the fatigue life of band plate and satisfy the demands, and the height of each step is adjusted to the accessible, the size of bolt hole on each step, adjust the rigidity of connecting the band plate link, make the link and the bulk rigidity phase-match of aluminum alloy frame, have the ability of deformation with aircraft subassembly coordination. The application also provides a strength test method for the airplane component with the aluminum alloy frame, which is implemented based on the strength test connecting strip plate for the airplane component with the aluminum alloy frame, and can ensure that the fatigue life of the connecting strip plate and the rigidity matching of the aluminum alloy frame can meet the requirements, so that the smooth proceeding of the test and the accuracy of the test result can be ensured.
Description
Technical Field
The application belongs to the technical field of strength tests of airplane components with aluminum alloy frames, and particularly relates to a strength test connecting strip plate and a strength test method of an airplane component with an aluminum alloy frame.
Background
The aircraft assembly is mainly characterized in that the aircraft assembly is internally provided with an aluminum alloy frame, for example, an airtight top plate frame joint structure of an aircraft body, when the aircraft assembly is subjected to a strength test, the aluminum alloy frame is connected through a connecting strip plate, a loading mechanism transfers load to the aluminum alloy frame through the connecting strip plate, and then the load is applied to the assembly, so that the strength test of the aircraft assembly is completed.
At present, in order to guarantee the fatigue life who connects the band plate, the band plate is connected in many designs has great intensity, and thickness is thicker, and the quality is heavier, however, under some circumstances, not only require to exert test load on the aircraft subassembly, need connect the stable even transmission of load between band plate and aluminum alloy frame simultaneously, connect band plate and aluminum alloy frame rigidity phase-match, have the ability of deformation with aircraft subassembly coordination.
The present application has been made in view of the above-mentioned technical drawbacks.
It should be noted that the above background disclosure is only for the purpose of assisting understanding of the inventive concept and technical solutions of the present invention, and does not necessarily belong to the prior art of the present patent application, and the above background disclosure should not be used for evaluating the novelty and inventive step of the present application without explicit evidence to suggest that the above content is already disclosed at the filing date of the present application.
Disclosure of Invention
The application aims to provide a strength test connecting strip plate of an airplane component with an aluminum alloy frame and a test method, so as to overcome or alleviate at least one technical defect of the known existing technology.
The technical scheme of the application is as follows:
on one hand, the strength test connecting strip plate for the airplane component with the aluminum alloy frame is provided, one end of the connecting strip plate is a connecting end and is step-shaped, and a bolt hole is formed in each step so as to be capable of being connected to the aluminum alloy frame in a matched manner with a bolt fastener;
the other end of the connecting band plate is a loading end, a pin hole is formed in the other end of the connecting band plate, the connecting band plate can be connected to a loading mechanism through a pin in a matched mode, test loads applied by the loading mechanism can be transmitted to the aluminum alloy frame, then the test loads are transmitted to the aircraft assembly, and the aircraft assembly is subjected to strength test.
According to at least one embodiment of the application, in the strength test connecting strip plate of the airplane component with the aluminum alloy frame, the thickness of adjacent steps on the connecting end of the connecting strip plate is increased by no more than 2.
According to at least one embodiment of the application, in the strength test connecting strip plate of the airplane component with the aluminum alloy frame, the distance between the bolt holes on each step of the connecting end of the connecting strip plate is 3-6 times of the diameter of the bolt holes.
According to at least one embodiment of the application, in the strength test connecting strip plate of the airplane component with the aluminum alloy frame, the thickness increment between adjacent steps does not exceed 2.
In another aspect, a method for testing the strength of an aircraft component with an aluminum alloy frame comprises the following steps:
designing the appearance of the connecting band plate according to the shape and the size of the aluminum alloy frame;
the structure of the connecting band plate is designed in detail, and the structure comprises the number and the height of steps on the connecting end of the connecting band plate, and the number and the diameter of bolt holes on each step;
constructing a three-dimensional model of the matching of the connecting strip plate and the airplane component, verifying whether the fatigue life of the connecting strip plate and the rigidity matching of the connecting strip plate and the aluminum alloy frame meet the requirements or not by a finite element analysis method, and redesigning the structure of the connecting strip plate when the requirements are not met;
manufacturing a connecting band plate;
and carrying out strength test on the aircraft assembly by matching the connecting band plate with the loading mechanism.
According to at least one embodiment of the application, in the strength test method for the airplane component with the aluminum alloy frame, the loading mechanism is a ram or a tester.
The application has at least the following beneficial technical effects:
on the one hand, the utility model provides an aircraft subassembly strength test connects band plate with aluminum alloy frame, the link of its design connection band plate is the step form, and bolt hole has on every step, with can cooperate bolt fastening spare to be connected to the aluminum alloy frame, when concrete application, the accessible changes the quantity of step and the interval between the bolt hole on each step, guarantee to connect the fatigue life of band plate and satisfy the demands, and the accessible adjusts the height of each step, the size of bolt hole on each step, adjust the rigidity of connecting the band plate link, make the link and the bulk rigidity phase-match of aluminum alloy frame, have the ability of deformation with aircraft subassembly coordination.
On the other hand, the method for testing the strength of the airplane component with the aluminum alloy frame is implemented based on the connecting strip plate for testing the strength of the airplane component with the aluminum alloy frame, the fatigue life of the connecting strip plate can be guaranteed, the requirement can be met by matching the rigidity of the connecting strip plate with the rigidity of the aluminum alloy frame, and therefore smooth test and accuracy of a test result can be guaranteed.
Drawings
FIG. 1 is a schematic diagram of a strength test connecting strip plate of an aircraft component with an aluminum alloy frame provided by an embodiment of the application;
FIG. 2 is a schematic diagram of a strength test connecting strip plate and an airplane component matched with the airplane component, wherein the strength test connecting strip plate is provided with an aluminum alloy frame according to an embodiment of the application;
FIG. 3 is a flow chart of a method for testing the strength of an aircraft component with an aluminum alloy frame according to an embodiment of the present disclosure;
wherein:
1-connecting the band plate; 2-an aluminum alloy frame; 3-aircraft components.
For the purpose of better illustrating the embodiments, certain features of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; in addition, the drawings are used for illustrative purposes, and the positional relationship is only for illustrative purposes and is not to be construed as limiting the patent.
Detailed Description
In order to make the technical solutions and advantages of the present application clearer, the technical solutions of the present application will be further clearly and completely described in the following detailed description with reference to the accompanying drawings, and it should be understood that the specific embodiments described herein are only some of the embodiments of the present application, and are only used for explaining the present application, but not limiting the present application. It should be noted that, for convenience of description, only the parts related to the present application are shown in the drawings, other related parts may refer to general designs, and the embodiments and technical features in the embodiments in the present application may be combined with each other to obtain a new embodiment without conflict.
In addition, unless otherwise defined, technical or scientific terms used in the description of the present application shall have the ordinary meaning as understood by one of ordinary skill in the art to which the present application belongs. The terms "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", and the like used in the description of the present application, which indicate orientations, are used only to indicate relative directions or positional relationships, and do not imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and when the absolute position of the object to be described is changed, the relative positional relationships may be changed accordingly, and thus, should not be construed as limiting the present application. The use of "first," "second," "third," and the like in the description of the present application is for descriptive purposes only to distinguish between different components and is not to be construed as indicating or implying relative importance. The use of the terms "a," "an," or "the" and similar referents in the context of describing the application is not to be construed as an absolute limitation on the number, but rather as the presence of at least one. The word "comprising" or "comprises", and the like, when used in this description, is intended to specify the presence of stated elements or items, but not the exclusion of other elements or items.
Further, it is noted that, unless expressly stated or limited otherwise, the terms "mounted," "connected," and the like are used in the description of the invention in a generic sense, e.g., connected as either a fixed connection or a removable connection or integrally connected; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, or they may be connected through the inside of two elements, and those skilled in the art can understand their specific meaning in this application according to the specific situation.
The present application is described in further detail below with reference to fig. 1 to 3.
On one hand, the strength test connecting strip plate for the airplane component with the aluminum alloy frame is provided, one end of the connecting strip plate 1 is a connecting end and is step-shaped, and a bolt hole is formed in each step so as to be connected to the aluminum alloy frame 2 in a matched manner 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, test load applied by the loading mechanism can be transmitted to the aluminum alloy frame 2, the test load can be further transmitted to the airplane assembly 3, and strength test is conducted on the airplane assembly 3.
To the aircraft component strength test connection band plate with the aluminum alloy frame disclosed in the above embodiment, those skilled in the art can understand that the connection end of the connection band plate 1 is designed to be step-shaped, and a bolt hole is formed in each step to be capable of being connected to the aluminum alloy frame 2 in cooperation with a bolt fastener, when the aircraft component strength test connection band plate is applied specifically, the fatigue life of the connection band plate 1 can be guaranteed to meet requirements by changing the number of the steps and the distance between the bolt holes in each step, and the rigidity of the connection end of the connection band plate 1 can be adjusted by adjusting the height of each step and the size of the bolt holes in each step, so that the connection end is matched with the overall rigidity of the aluminum alloy frame 2, and the aircraft component strength test connection band plate has the capability of deformation in coordination with the aircraft component 3.
In some alternative embodiments, in the strength test connecting strip plate for the airplane component with the aluminum alloy frame, the thickness of the adjacent steps on the connecting end of the connecting strip plate 1 is increased by no more than 2.
In some alternative embodiments, in the strength test connecting band plate for the airplane component with the aluminum alloy frame, 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 hole.
In some alternative embodiments, in the strength test connecting strip plate of the airplane component with the aluminum alloy frame, the thickness between adjacent steps is increased by no more than 2.
In another aspect, a method for testing the strength of an aircraft component with an aluminum alloy frame comprises the following steps:
designing the appearance of the connecting band plate 1 according to the shape and the size of the aluminum alloy frame 2 and a loading scheme required by the airplane component 3;
the structure of the connecting band plate 1 is designed in detail, and 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 1 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 the connecting strip plate 1, wherein the specific process comprises drawing a processing drawing, designing a processing technology, producing and manufacturing and the like;
and carrying out a component-level strength test on the aircraft component 3 by matching the connecting strip plate 1 with a loading mechanism.
For the strength test method of the airplane component with the aluminum alloy frame disclosed in the above embodiment, it can be understood by those skilled in the art that, in the above description, it is verified whether the fatigue life of the belt connecting plate 1 meets the requirement, specifically, it is verified whether the fatigue life of the belt connecting plate 1 is much longer than that of the airplane component 3, and when the fatigue life of the belt connecting plate 1 is not superior to that of the airplane component 3, the stress distribution of the connecting end can be more uniform by increasing the number of steps on the connecting end of the belt connecting plate 1 and reducing the intervals between bolt holes on each step, so as to increase the fatigue life of the belt connecting plate 1, and make the fatigue life of the belt connecting plate 1 far exceed that of the airplane component 3, thereby meeting the requirement.
For the strength test method for the airplane component with the aluminum alloy frame disclosed in the above embodiment, it can be further understood by those skilled in the art that when the rigidity matching between the belt connecting plate 1 and the aluminum alloy frame 2 is not satisfied, the rigidity of the connecting end of the belt connecting plate 1 can be reduced by reducing the height of each step and the diameter of the bolt hole on each step, so that the connecting end is matched with the overall rigidity of the aluminum alloy frame 2, and the airplane component has the capability of deformation in coordination with the airplane component 3.
In some alternative embodiments, in the method for testing the strength of the aircraft component with the aluminum alloy frame, the loading mechanism is a hydraulic actuator cylinder or a standard testing machine.
The embodiments are described in a progressive manner in the specification, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
Having thus described the present application in connection with the preferred embodiments illustrated in the accompanying drawings, it will be understood by those skilled in the art that the scope of the present application is not limited to those specific embodiments, and that equivalent modifications or substitutions of related technical features may be made by those skilled in the art without departing from the principle of the present application, and those modifications or substitutions will fall within the 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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210179520.8A CN114544350A (en) | 2022-02-25 | 2022-02-25 | Airplane component strength test connecting strip plate with aluminum alloy frame and test method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210179520.8A CN114544350A (en) | 2022-02-25 | 2022-02-25 | Airplane component strength test connecting strip plate with aluminum alloy frame and test method |
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| CN114544350A true CN114544350A (en) | 2022-05-27 |
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| CN202210179520.8A Pending CN114544350A (en) | 2022-02-25 | 2022-02-25 | Airplane component strength test connecting strip plate with aluminum alloy frame and test method |
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