CN112763304B - Fatigue test loading spectrum forming method and device and fatigue performance testing method - Google Patents
Fatigue test loading spectrum forming method and device and fatigue performance testing method Download PDFInfo
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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
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
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- G01N2203/0069—Fatigue, creep, strain-stress relations or elastic constants
- G01N2203/0073—Fatigue
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- 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
- G01N2203/0208—Specific programs of loading, e.g. incremental loading or pre-loading
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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
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Abstract
The application relates to a fatigue test loading spectrum forming method and device and a fatigue performance testing method, belongs to the technical field of aircraft environmental engineering, and solves the problems that an existing load loading control system cannot directly identify a structural fatigue load spectrum and cannot apply load. The fatigue test loading spectrum forming method comprises the following steps: determining the load direction applied to each loading section of the structural member to be tested and a load value corresponding to the load direction to form a load condition table; generating a plurality of step instructions according to a load condition table and load change time and a load change sequence; and according to the structure of the flight-continuation-flight fatigue load spectrum, forming a load sequence block spectrum corresponding to the load working condition by a plurality of step instructions according to different load working conditions. The structural fatigue load spectrum can be converted into a fatigue test load spectrum identified by a load control system, and the test efficiency is improved on the basis of ensuring the test accuracy and effectiveness.
Description
Technical Field
The application relates to the technical field of aircraft environmental engineering, in particular to a fatigue test loading spectrum forming method and device and a fatigue performance testing method.
Background
The structural fatigue load spectrum is an important condition and basis for structural member fatigue performance assessment. The application of the fatigue load in the structural fatigue performance assessment test is realized through a load loading control system, but the load loading control system cannot directly identify the structural fatigue load spectrum and cannot apply the load. The fatigue test load spectrum is converted from a fatigue load spectrum (the fatigue load spectrum is a load or stress with the size and direction periodically or irregularly changed along with time) to a fatigue test load spectrum, and the fatigue test load spectrum can be identified by a load control system, so that the fatigue performance assessment of the structural part is successfully completed. A reasonable and efficient load equivalent conversion method is needed, and the test feasibility and the test efficiency are improved. The realization of the fatigue load spectrum is completed by a load loading control system. However, the original fatigue load spectrum cannot be directly realized on the load control system, and proper equivalent conversion is required, and the converted spectrum is called a fatigue test load spectrum.
Disclosure of Invention
In view of the above analysis, the embodiment of the application aims to provide a fatigue test loading spectrum forming method and device and a fatigue performance testing method, which are used for solving the problems that the existing load loading control system cannot directly identify a structural fatigue loading spectrum and cannot apply load.
In one aspect, an embodiment of the present application provides a method for forming a fatigue test loading spectrum, including: determining the load direction applied to each loading section of the structural member to be tested and a load value corresponding to the load direction to form a load condition table; generating a plurality of step instructions according to the load condition table and the load change time and the load change sequence; and according to the structure of the flight-continuation-flight fatigue load spectrum, according to different load working conditions, forming the load sequence block spectrum corresponding to the load working conditions by the step instructions.
The beneficial effects of the technical scheme are as follows: the embodiment of the application provides a method for forming a fatigue test loading spectrum, which converts a structural fatigue loading spectrum into a test loading spectrum identified by a loading control system, and improves test efficiency on the basis of ensuring test accuracy and effectiveness.
Based on a further improvement of the above method, before forming the load situation table, the method further comprises: analyzing different flight phases of the aircraft to determine a plurality of load conditions, wherein the structural member to be tested is the aircraft or a component in the aircraft; determining the heading load, the side load and/or the longitudinal load of each load working condition; and dividing the heading load, the side load, and/or the longitudinal load into an X-direction load, a Y-direction load, and a Z-direction load, respectively, to determine a load application direction.
Based on further improvements of the method, the plurality of load conditions include ground taxiing, off-site maneuvers, climbing gusts, flat fly gusts and flat fly maneuvers.
Based on a further improvement of the method, the X-direction load is an axial load; the Y-direction load is a vertical direction load; and the Z-direction load is a horizontal direction load, wherein the Z-direction load is perpendicular to the X-direction load and the Y-direction load.
Based on a further improvement of the above method, forming the load scenario table further comprises: dividing the X-direction load into +X-direction load and-X-direction load; dividing the Z-direction load into +Z-direction load and-Z-direction load; and the Y-direction load is a vertically downward load.
Based on a further development of the above method, the load situation table is formed according to the following principle: firstly, applying a load in the Y direction; and then applying the X-direction load and the Z-direction load, wherein a symmetrical direction load is applied by the following sequence: sequentially applying +X direction load or-X direction load, zero load in X direction and-X direction load or +X direction load; and sequentially applying a +Z direction load or a-Z direction load, a zero Z direction load, and a-Z direction load or a +Z direction load.
Based on a further improvement of the method, the components in the aircraft include a suspension joint, a tank compartment and a warhead compartment.
In another aspect, an embodiment of the present application provides a fatigue performance testing method, including: transmitting the load sequence block spectrum described in each embodiment to a load loading control system; the load loading control system automatically identifies the load sequence block spectrum, then displays a fatigue test loading spectral line graph on a display according to the load sequence block spectrum and applies a load to the structural member to be tested to determine the fatigue performance of the structural member to be tested.
In still another aspect, an embodiment of the present application provides a fatigue test loading spectrum forming apparatus, including: the load condition table forming module is used for determining the load directions applied to each loading section of the structural member to be tested and the load values corresponding to the load directions so as to form a load condition table; the step instruction generation module is used for generating a plurality of step instructions according to the load condition table and the load change time and the load change sequence; and the load sequence block spectrum generation module is used for forming a load sequence block spectrum corresponding to the load working condition by the plurality of step instructions according to the structure of the fly-continuous-fly fatigue load spectrum and different load working conditions.
Based on a further improvement of the above device, the fatigue test loading spectrum forming device further includes: the load working condition determining module is used for analyzing different flight phases of the aircraft to determine a plurality of load working conditions; and a heading, lateral, and longitudinal load determination module to determine a heading load, a lateral load, and/or a longitudinal load for each of the plurality of load conditions; and a load application direction determination module for dividing the heading load, the side load, and/or the longitudinal load into an X-direction load, a Y-direction load, and a Z-direction load, respectively, to determine a load application direction.
Compared with the prior art, the application has at least one of the following beneficial effects:
1. the structural fatigue load spectrum is converted into a test load spectrum identified by a load control system, and the test efficiency is improved on the basis of ensuring the test accuracy and effectiveness.
2. Dividing the X-direction load into +X-direction load and-X-direction load; dividing the Z-direction load into +Z-direction load and-Z-direction load; and the Y-direction load is a vertically downward load to facilitate the load control system applying the load.
3. The symmetrical directional load is applied by the following sequence: sequentially applying +X direction load or-X direction load, zero load in X direction and-X direction load or +X direction load; and sequentially applying a +Z direction load or a-Z direction load, a Z direction zero load and a-Z direction load or a +Z direction load, so as to facilitate the load adjustment of the load control system.
In the application, the technical schemes can be mutually combined to realize more preferable combination schemes. Additional features and advantages of the application will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the application. The objectives and other advantages of the application may be realized and attained by the structure particularly pointed out in the written description and drawings.
Drawings
The drawings are only for purposes of illustrating particular embodiments and are not to be construed as limiting the application, like reference numerals being used to refer to like parts throughout the several views.
FIG. 1 is a flow chart of a method of forming a fatigue test loading spectrum according to an embodiment of the application.
FIG. 2 is a chart of a fatigue test loading spectrum according to an embodiment of the present application.
Fig. 3 is a block diagram of a fatigue test loading spectrum forming device according to an embodiment of the present application.
Detailed Description
The following detailed description of preferred embodiments of the application is made in connection with the accompanying drawings, which form a part hereof, and together with the description of the embodiments of the application, are used to explain the principles of the application and are not intended to limit the scope of the application.
In one embodiment of the application, a method of forming a fatigue test loading spectrum is disclosed. As shown in fig. 1, the fatigue test loading spectrum forming method includes: step S102, determining the load direction applied to each loading section of the structural member to be tested and the load value corresponding to the load direction to form a load condition table; step S104, generating a plurality of step instructions according to a load condition table and the change time of the load and the load change sequence; and step S106, according to the structure of the Fei-Xue-Fei fatigue load spectrum, forming a load sequence block spectrum corresponding to the load working condition by a plurality of step instructions according to different load working conditions.
Compared with the prior art, the fatigue test loading spectrum forming method provided by the embodiment converts the structural fatigue loading spectrum into the test loading spectrum (namely the loading sequence block spectrum) identified by the loading control system, and improves the test efficiency on the basis of ensuring the test accuracy and effectiveness.
Hereinafter, with reference to fig. 1 and 2, step S102, step S104, and step S106 of the fatigue test loading spectrum forming method are described in detail.
Referring to fig. 1, step S102, a load direction and a load value corresponding to the load direction applied to each loading section of the structural member to be tested are determined to form a load case table. In an embodiment, a load direction applied on each loading section of the structure to be tested and a load value corresponding to the load direction are determined from the fatigue load spectrum.
First, generating a fatigue load spectrum includes the following three steps: first, different flight phases of the aircraft are analyzed to determine a plurality of load conditions. In embodiments, the structure to be tested is an aircraft or a component in an aircraft, and the components in an aircraft include a suspension joint, an oil tank compartment, a warhead compartment, and possibly other aircraft structures. The plurality of load conditions include ground sliding, off-site maneuver, climbing gust, flat flying gust and flat flying maneuver. Next, a heading load, a side load, and/or a longitudinal load for each load condition is determined. Finally, the heading load, the side load and/or the longitudinal load are divided into an X-direction load, a Y-direction load and a Z-direction load, respectively. The load in the X direction is an axial load; the Y-direction load is a vertical direction load; the Z-direction load is a horizontal direction load, wherein the Z-direction load is perpendicular to the X-direction load and the Y-direction load.
After generating the fatigue load spectrum, forming the load case table further includes: first, the load directions (X, Y and Z-direction loads) applied to the respective loading sections of the structural member to be tested and the load values corresponding to the load directions are determined from the fly-by-fly fatigue load spectrum. Next, the X-direction load is divided into +x-direction load and-X-direction load; dividing the Z-direction load into +Z-direction load and-Z-direction load; the Y-direction load is divided into vertically downward loads. The load case table is formed according to the following principle: firstly, applying a load in the Y direction; then, an X-direction load and a Z-direction load are applied, wherein a symmetrical direction load is applied by the following sequence: sequentially applying +X direction load or-X direction load, zero load in X direction and-X direction load or +X direction load; and sequentially applying a +Z direction load or a-Z direction load, a zero Z direction load, and a-Z direction load or a +Z direction load.
After the load condition table is formed, the flow proceeds to step S104, where a plurality of step instructions are generated in the load change order according to the load condition table and the change time of the load. The load-based step command load control system is capable of applying loads in a time sequence. For example, a plurality of step instructions are generated based on the ground taxi heading and the Y-direction load, the X-direction load and the Z-direction load in the load situation table, and variations thereof, respectively. For example, the following 5-step instruction: the first step of the command is to apply a Y-direction load, the second step of the command is to apply a Y-direction load and an-X-direction load, the third step of the command is to apply a Y-direction load, the fourth step of the command is to apply a Y-direction load and an X-direction load, and the fifth step of the command is to apply a Y-direction load. In addition, a plurality of step instructions, for example, 32 step instructions, are generated according to the ground sliding heading, the ground sliding longitudinal direction, the ground sliding lateral direction, the off-site maneuver longitudinal direction, the climbing gust lateral direction, the flat flying gust longitudinal direction, the flat flying gust lateral direction, and the Y-direction load, the X-direction load, and the Z-direction load, and variations thereof, respectively, in the load case table.
And S106, according to the structure of the flight-continuation-flight fatigue load spectrum, forming a load sequence block spectrum corresponding to the load working condition by a plurality of step instructions according to different load working conditions. And combining the step instructions generated in the step S104 into a load sequence block spectrum corresponding to the load working condition. The load control system can automatically identify the load sequence block spectrum.
In another embodiment of the application, a method for testing fatigue performance is disclosed. The fatigue performance testing method comprises the following steps: the load sequence block spectrum described in the above embodiment is transmitted to the load loading control system, for example, directly transmitted to the load loading control system through an upper computer or the like storing the load sequence block spectrum, without manually inputting the load sequence block spectrum to the load loading control system; and the load loading control system automatically identifies a load sequence block spectrum, then displays a fatigue test loading spectral line graph on a display according to the load sequence block spectrum and applies load to the structural member to be tested to determine the fatigue performance of the structural member to be tested.
Compared with the prior art, the fatigue test loading spectrum forming method provided by the embodiment displays the fatigue test loading spectrum diagram on the display according to the load sequence block spectrum, and can check each load loaded in the fatigue test on the display. In addition, the upper computer and the like storing the load sequence block spectrum are directly transmitted to the load loading control system, and the load sequence block spectrum is not required to be manually input to the load loading control system, so that the preparation time of a fatigue test is greatly shortened.
In still another embodiment of the present application, a fatigue test loading spectrum forming device is disclosed, comprising: a load case table forming module 302, configured to determine a load direction applied to each loading section of the structural member to be tested and a load value corresponding to the load direction to form a load case table; the step instruction generating module 304 is configured to generate a plurality of step instructions according to the load condition table and the change time of the load and the load change sequence; and a load sequence block spectrum generating module 306, configured to form a load sequence block spectrum corresponding to the load condition by a plurality of step instructions according to the structure of the femto-continuous-femto fatigue load spectrum and different load conditions.
The fatigue test loading spectrum forming device further comprises a load working condition determining module, which is used for analyzing different flight phases of the aircraft to determine a plurality of load working conditions; a heading, lateral, and longitudinal load determination module to determine a heading load, a lateral load, and/or a longitudinal load for each of a plurality of load conditions; and a load application direction determination module for determining a load application direction by dividing the heading load, the side load, and/or the longitudinal load into an X-direction load, a Y-direction load, and a Z-direction load, respectively.
Hereinafter, by way of specific example, a fatigue test loading spectrum forming method will be described in detail.
The practice of the present application is illustrated in terms of a typical fatigue load spectrum of a typical structure.
Typical fatigue load spectrum of a typical structural test piece is generally divided into different task profiles (load working conditions) including ground sliding, off-site maneuver, climbing gust, flat flying maneuver and the like. As shown in table 1. The exemplary structural members herein may be the entire aircraft or may be one or more portions of the aircraft structure. Such as hanging joints, oil tank cabins, warhead cabins, etc.
TABLE 1 typical fatigue load spectrum
According to the load spectrum in table 1, the load in the X direction is divided into +x direction and-X direction, the load in the Z direction is divided into +z direction and-Z direction, and the load in the Y direction is vertically downward. The fatigue load spectrum in table 1 was decomposed into 5 loading sections, 37 loading cases, and a load case table was formed according to the principle of applying the Y-direction load first, and then applying the X-direction and Z-direction loads after the Y-direction load was applied, as shown in table 2.
The ground sliding stage is divided into a ground sliding heading section, a longitudinal section and a lateral section.
Table 2 load case table
Step two, defining a step instruction according to the load condition table and the change time of each load condition and the load change sequence.
And thirdly, forming a load sequence block spectrum by all the step instructions according to different task sections.
Each task profile is defined as a load sequence block spectrum. The load sequence block spectrum consists of different step instructions. The execution sequence of the step instructions is based on the principle that the Y-direction load is firstly applied and then the X-direction load and the Z-direction load are applied. Taking the ground taxi heading profile as an example, a load sequence block spectrum is formed as shown in table 3 below.
Table 3 load sequence block spectrum (ground taxi course)
| Step instruction sequence number | Load case numbering | Step instruction sequence number | Load case numbering | |
| 1 | condition_1 | 2 | condition_2 | |
| 3 | condition_3 | 4 | condition_4 | |
| 5 | condition_5 |
And fourthly, carrying out different cycles on the load sequence block spectrum, and drawing a load loading spectrum diagram. The load loading spectrum diagram in fig. 1 is a real application example. In the actual test, the fatigue load is applied to the test piece according to the loading spectral line.
Each sequence block spectrum corresponds to a different load profile, each load profile is cycled a certain number of times, and load loading spectral lines are formed according to a fixed sequence of load profiles (refer to fig. 2).
The structural fatigue load spectrum can not be directly realized on a loading control system, and the application provides a reasonable and efficient load equivalent conversion method. According to the spectrum editing principle of the flight-continuous-flight fatigue load spectrum, the structural fatigue load spectrum is converted into a test load spectrum which can be used for the identification of a load control system, and the test feasibility is improved.
Compared with the prior art, the fatigue test loading spectrum forming method provided by the embodiment converts the structural fatigue loading spectrum into the test loading spectrum identified by the loading control system by adopting a reasonable load equivalent conversion method, and improves the test efficiency on the basis of ensuring the test accuracy and effectiveness. The method can be applied to fatigue performance assessment tests of various aircrafts.
Compared with the prior art, the application has at least one of the following beneficial effects:
1. the structural fatigue load spectrum is converted into a test load spectrum identified by a load control system, and the test efficiency is improved on the basis of ensuring the test accuracy and effectiveness.
2. Dividing the X-direction load into +X-direction load and-X-direction load; dividing the Z-direction load into +Z-direction load and-Z-direction load; and the Y-direction load is a vertically downward load to facilitate the load control system applying the load.
3. The symmetrical directional load is applied by the following sequence: sequentially applying +X direction load or-X direction load, zero load in X direction and-X direction load or +X direction load; and sequentially applying a +Z direction load or a-Z direction load, a Z direction zero load and a-Z direction load or a +Z direction load, so as to facilitate the load adjustment of the load control system.
Those skilled in the art will appreciate that all or part of the flow of the methods of the embodiments described above may be accomplished by way of a computer program to instruct associated hardware, where the program may be stored on a computer readable storage medium. Wherein the computer readable storage medium is a magnetic disk, an optical disk, a read-only memory or a random access memory, etc.
The present application is not limited to the above-mentioned embodiments, and any changes or substitutions that can be easily understood by those skilled in the art within the technical scope of the present application are intended to be included in the scope of the present application.
Claims (4)
1. A fatigue test loading spectrum forming method, characterized by comprising:
analyzing different flight phases of the aircraft to determine a plurality of load conditions, wherein the plurality of load conditions comprise ground sliding, departure maneuver, climbing gust, flat flying gust and flat flying maneuver;
determining the heading load, the side load and the longitudinal load of each load working condition;
dividing the heading load, the side load, and the longitudinal load into an X-direction load, a Y-direction load, and a Z-direction load, respectively, to determine a load application direction;
determining the load direction applied to each loading section of a structural member to be tested and a load value corresponding to the load direction to form a load situation table, wherein the structural member to be tested is an aircraft or a component in the aircraft; forming the load scenario table further comprises: dividing the X-direction load into +X-direction load and-X-direction load; dividing the Z-direction load into +Z-direction load and-Z-direction load; and the Y-direction load is divided into a vertically downward load; the load case table is formed according to the following principle: firstly, applying a load in the Y direction; and then applying the X-direction load and the Z-direction load, wherein a symmetrical direction load is applied by the following sequence: sequentially applying +X direction load or-X direction load, zero load in X direction and-X direction load or +X direction load; sequentially applying +Z direction load or-Z direction load, Z direction zero load and-Z direction load or +Z direction load;
generating a plurality of step instructions according to the load condition table and the load change time and the load change sequence; and
according to the structure of the flight-continuation-flight fatigue load spectrum which cannot be directly identified by the load loading control system, according to different load working conditions, the plurality of step instructions are formed into load sequence block spectrums which are directly identified by the load loading control system and correspond to the load working conditions, wherein each load sequence block spectrum corresponds to different load sections, and the components in the aircraft comprise a hanging connector, an oil tank cabin and a fighter cabin.
2. The method for forming a fatigue test loading spectrum according to claim 1, wherein,
the X-direction load is an axial load;
the Y-direction load is a vertical direction load; and
the Z-direction load is a horizontal direction load, wherein the Z-direction load is perpendicular to the X-direction load and the Y-direction load.
3. A fatigue performance testing method, comprising:
transmitting the load sequence block spectrum as set forth in claim 1 or 2 above to a load loading control system; and
the load loading control system automatically identifies the load sequence block spectrum, then displays a fatigue test loading spectral line graph on a display according to the load sequence block spectrum and applies a load to the structural member to be tested to determine the fatigue performance of the structural member to be tested.
4. A fatigue test loading spectrum forming device, characterized by comprising:
the load working condition determining module is used for analyzing different flight phases of the aircraft to determine a plurality of load working conditions, wherein the plurality of load working conditions comprise ground sliding, departure maneuver, climbing gust, flat flying gust and flat flying maneuver;
a heading, lateral, and longitudinal load determination module for determining a heading load, a lateral load longitudinal load for each of the plurality of load conditions;
a load application direction determining module for dividing the heading load, the side load, and the longitudinal load into an X-direction load, a Y-direction load, and a Z-direction load, respectively, to determine a load application direction;
the load condition table forming module is used for determining the load direction applied to each loading section of the structural member to be tested and the load value corresponding to the load direction, and dividing the load in the X direction into a +X direction load and a-X direction load; dividing the Z-direction load into +Z-direction load and-Z-direction load; dividing the Y-direction load into loads vertically downwards to form a load condition table, wherein the structural member to be tested is an aircraft or a component in the aircraft; wherein the load situation table is formed according to the following principle: firstly, applying a load in the Y direction; and then applying the X-direction load and the Z-direction load, wherein a symmetrical direction load is applied by the following sequence: sequentially applying +X direction load or-X direction load, zero load in X direction and-X direction load or +X direction load; sequentially applying +Z direction load or-Z direction load, Z direction zero load and-Z direction load or +Z direction load;
the step instruction generation module is used for generating a plurality of step instructions according to the load condition table and the load change time and the load change sequence; and
the load sequence block spectrum generation module is used for forming load sequence block spectrums which are directly recognized by the load loading control system and correspond to the load working conditions according to different load working conditions by the plurality of step instructions according to the structure of the flight-continuation-flight fatigue load spectrums which cannot be directly recognized by the load loading control system, wherein each load sequence block spectrum corresponds to different load sections, and components in the aircraft comprise a hanging connector, an oil tank cabin and a fighter part cabin.
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