CN114444324A - Method for evaluating stress magnitude of structural stress focus point on structural member after multi-region respective loading and superposition - Google Patents
Method for evaluating stress magnitude of structural stress focus point on structural member after multi-region respective loading and superposition Download PDFInfo
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- CN114444324A CN114444324A CN202210135130.0A CN202210135130A CN114444324A CN 114444324 A CN114444324 A CN 114444324A CN 202210135130 A CN202210135130 A CN 202210135130A CN 114444324 A CN114444324 A CN 114444324A
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- G06F30/20—Design optimisation, verification or simulation
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Abstract
The invention belongs to the technical field of structural design and strength test, and particularly relates to a method for evaluating the stress magnitude of a structural stress focus point on a structural member after multi-region respective loading superposition. The method is scientific and reasonable, is convenient to operate, can efficiently and quickly estimate the total stress value of each structural stress concern point, and realizes the structural load monitoring in the whole life cycle of the machine body.
Description
Technical Field
The invention belongs to the technical field of structural design and strength test, and particularly relates to a method for evaluating stress at a structural stress focus point on a structural member after multi-region respective loading and superposition.
Background
The method for evaluating the service life of the airplane structure requires knowing the loading condition of the airplane in the use process, generally tracking the loading condition of hundreds of key parts of the airplane structure by pasting strain gauges at corresponding points for measurement and recording, and measuring the stress through the strain gauges has the advantage that the structural stress at a certain point can be accurately measured, but the glue used for pasting the strain gauges loses efficacy after a certain period of time and is generally far shorter than the service life of the airplane structure, the strain gauges need to be pasted again after the failure, the workload is higher, meanwhile, the strain gauges at some parts are pasted in the airplane assembly process, the strain gauges at the parts can not be replaced after the airplane is delivered, and therefore, the method for pasting the strain gauges is not practical under the condition that the structural loading monitoring is required according to the whole service life of the airplane.
Disclosure of Invention
In view of the above problems, an object of the present invention is to provide a method for evaluating the stress at structural stress focus points on a structural member after multi-region respective loading and stacking, which can efficiently and quickly estimate the total stress value at each structural stress focus point, thereby realizing the monitoring of the structural loading during the whole life cycle of the machine body.
A method for evaluating stress magnitude of a structural stress focus point on a structural member after multi-region respective loading superposition is disclosed, when the loading condition of any structural stress focus point in the structural member needs to be tracked in a full life cycle, the structural member is divided into a limited number of measurement regions, then the contribution amount of the loading condition of each measurement region to the stress value of the structural stress focus point is measured, and the contribution amounts of all the measurement regions are superposed to evaluate the loading condition of the structural stress focus point in the structural member.
Further, when the number of the structural stress concerns to be evaluated is multiple, the steps recited in claim 1 are repeated continuously, and the evaluation of the loading condition of all other structural stress concerns can be completed.
Further, the structural member is an aircraft wing.
A method for evaluating the stress magnitude of a structural stress focus point on a structural member after multi-region respective loading and superposition comprises the following steps:
s1, when the stress magnitude of a stress focus point of a certain structure needs to be evaluated, dividing the wing into a limited number of measurement areas, wherein the more the divided measurement areas are, the more accurate the stress evaluation of the stress focus point of the structure is;
s2, when the airplane is in a test stage, adhering a strain gauge to the stress attention point of the structure on the wing;
s3, independently applying loads with different sizes to a certain measuring area, respectively recording stress values of strain gages at stress attention points of the structure under different loads, and then establishing a relation curve of the loads and the stress attention points of the structure;
s4, continuously replacing the measurement areas and repeating the step S3 until all the measurement areas respectively establish a relation curve of the load and the structural stress attention points;
s5, when the airplane is in a delivery and use stage, the load at the structural stress attention point is not accurately measured through a strain gauge in the step S1, and a sensor is arranged in each measuring area; the measuring area of the stage is consistent with the measuring area of the test stage;
s6, interpolating and fitting the load of each measuring area by reading the value of each sensor, wherein the load is an estimated value; combining the load with the relation curve corresponding to the measurement region obtained in the step S3, and estimating the contribution of the load of the measurement region to the stress value at the structure stress attention point;
and S7, superposing the contributions of the loads of all the measurement areas to the stress values of the structure stress attention points, and estimating the total stress value of the structure stress attention points.
Further, when the stress magnitudes at the plurality of structural stress attention points need to be evaluated, the steps S1-S7 are repeated continuously, so that the total stress values at all the structural stress attention points can be evaluated respectively.
Further, when the total stress value at the first structural stress concern point is estimated, a strain gauge is respectively adhered to each structural stress concern point on the wing in step S2, and when the total stress value at other structural stress concern points is subsequently estimated, step S2 is directly skipped.
Further, when estimating the total stress value at the first structural stress attention point, in step S3 and step S4, the stress values of the strain gauge at the first structural stress attention point under different loads are recorded for a certain measurement region, respectively, a relationship curve of the load and the first structural stress attention point is established, and simultaneously, the stress values of the strain gauge at other structural stress attention points under different loads can be recorded, respectively, a relationship curve of the load and other structural stress attention points is established, and when subsequently estimating the total stress value at other structural stress attention points, the obtained relationship curve is directly used, so that step S3 and step S4 are skipped.
Further, the sensor is a pneumatic load sensor.
Further, the sensor is installed at the area center of each measurement area, and the application position of the load in step S3 is also at the area center of each measurement area.
Furthermore, the number of the measurement areas is more than 6, and the measurement areas are increased according to actual requirements.
The method is scientific and reasonable, is convenient to operate, can efficiently and quickly estimate the total stress value of each structural stress concern point, and realizes the structural load monitoring in the whole life cycle of the machine body.
Drawings
The present invention will be described in further detail with reference to the accompanying drawings.
FIG. 1 is a schematic view of a wing section;
FIG. 2 is a schematic view of the pneumatic load cell placement position at the stage of delivery for use;
shown in the figure:
1. 2, 3, 4, 5, 6, 7, 8 and 9 are respectively measurement areas on the wing;
1-1 and 1-2 are structural stress concerns on the wing respectively;
2-1, 2-2, 2-3, 2-4, 2-5, 2-6, 2-7, 2-8 and 2-9 respectively show the positions of the pneumatic load sensors.
Detailed Description
The following description of the embodiments of the present invention is provided for illustrative purposes, and other advantages and effects of the present invention will become apparent to those skilled in the art from the present disclosure. The described embodiments are only some embodiments of the invention, not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be understood that the structures, proportions, and dimensions shown in the drawings and described herein are for illustrative purposes only and are not intended to limit the scope of the present invention, which is defined by the claims, but rather by the claims. In addition, the terms such as "upper", "lower", "left", "right" and "middle" used in the present specification are for convenience of description only, and are not intended to limit the scope of the present invention, and changes or modifications of the relative relationship thereof may be regarded as the scope of the present invention without substantial changes in the technical contents.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "connected" and "connected" are to be interpreted broadly, e.g., as being fixed or detachable or integrally connected; can be mechanically or electrically connected; may be directly connected or indirectly connected through an intermediate. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
The first embodiment is as follows:
as shown in fig. 1 and 2, the method for evaluating the stress magnitude of a structural stress focus point on a structural member after being respectively loaded and superimposed through multiple regions, wherein the structural member is an airplane wing, comprises the following steps:
s1, when the stress magnitude at a stress attention point 1-1 of a certain structure needs to be evaluated, the wing is divided into 9 measurement regions (regions shown by reference numerals 1 to 9 in figure 1), and the more the measurement regions are divided, the more accurate the stress evaluation of the stress attention point of the structure is.
S2, when the airplane is in a test stage, a strain gauge is pasted on the wing at the structural stress attention point 1-1.
S3, firstly, loads with different sizes are applied to the center (positions shown as reference numbers 2-1, 2-2, 2-3, 2-4, 2-5, 2-6, 2-7, 2-8 and 2-9 in the figure 2) of a certain measuring area (measuring area shown as reference number 1 in the figure 1) independently, then the stress values of the strain gauge at the structural stress attention point 1-1 under different loads are recorded respectively, and then a relation curve of the loads and the structural stress attention point 1-1 is established.
And S4, continuously replacing the measurement areas and repeating the step S3 until all the measurement areas respectively establish a relation curve of the load and structural stress attention points 1-1. Each measurement region (such as the regions marked by reference numerals 1 to 9 in fig. 1) is in one-to-one correspondence with a relationship curve of a load and structural stress attention point 1-1.
S5, when the airplane is in a delivery and use stage, the load at the structural stress attention point 1-1 is not accurately measured through a strain gauge in the step S1, a pneumatic load sensor is arranged in the center of each measuring area (such as the areas shown by the reference numerals 1 to 9 in the figure 1), and the arrangement positions of the pneumatic load sensors are shown by the reference numerals 2-1, 2-2, 2-3, 2-4, 2-5, 2-6, 2-7, 2-8 and 2-9 in the figure 2; the measurement area of the wing at this stage coincides with the measurement area of the wing at the test stage.
S6, fitting the load of each measurement area through mathematical interpolation by reading the value of each pneumatic load sensor, wherein the load is an estimated value; and combining the load with the relation curve corresponding to the measurement region obtained in the step S3 to estimate the contribution of the load of the measurement region to the stress value at the structure stress attention point 1-1.
And S7, superposing the load of all the measurement areas on the contribution of the stress value at the structure stress attention point 1-1, and estimating to obtain the total stress value at the structure stress attention point 1-1.
The principle of the invention is as follows:
in the elastic deformation range of the metal part, the stress and the strain can be in a linear relation, so that the stress change of a specific point on the structural part caused by loading of a plurality of points can be regarded as linear superposition of the stress caused by the specific point when the load is respectively applied to a single point. Aiming at a complex system such as an airplane wing, the wing can be divided into a plurality of areas in a test stage, a load is applied to one area alone, the stress magnitude of the point is accurately measured through a strain gauge adhered to the point concerned by one structure, the stress value is recorded, then the load applied to the area is cancelled, and the stress value of the point concerned by the structure is recorded again after the load is applied to the other area. This is repeated until all the regions are individually loaded and stress values are recorded for the structural concern. Finally, the stress values at the points of interest of the structure under each load are added, so that the stress values at the points of interest of the structure under the condition that the loads are applied to all the regions of the wing at the same time can be calculated. For the mass production airplane, a pneumatic load sensor is arranged at a specific point (such as the center of the area) in each area in the test stage to measure the pneumatic load at the specific point, then the pneumatic load of the area is estimated in a mathematical interpolation fitting mode, and then the load at the structure attention point can be estimated by comparing the corresponding relation curve of the area applied load and the stress value at the structure attention point acquired in the test stage.
Example two:
as shown in fig. 1 and 2, the method for evaluating the stress magnitude of a structural stress focus point on a structural member after being respectively loaded and superimposed through multiple regions, wherein the structural member is an airplane wing, comprises the following steps:
s1, when stress magnitudes at two structural stress attention points 1-1 and 1-2 need to be evaluated, the wing is divided into 9 measurement regions (regions shown by reference numerals 1 to 9 in FIG. 1), and the more the measurement regions are divided, the more accurate the stress evaluation of the structural stress attention points is.
S2, when the airplane is in a test stage, strain gauges are pasted on all structural stress attention points 1-1 and 1-2 on the wings.
S3, firstly, loads with different sizes are applied to the center (positions shown as reference numbers 2-1, 2-2, 2-3, 2-4, 2-5, 2-6, 2-7, 2-8 and 2-9 in the figure 2) of a certain measuring area (measuring area shown as reference number 1 in the figure 1) independently, then stress values of strain gages at structural stress attention points 1-1 and 1-2 under different loads are recorded respectively, and then relation curves of the load and structural stress attention points 1-1 and the load and structural stress attention points 1-2 are established respectively.
And S4, continuously replacing the measurement areas and repeating the step S3 until the relation curves of the load and structure stress attention points 1-1 and the load and structure stress attention points 1-2 are respectively established in all the measurement areas. Each measurement region (such as the regions marked by reference numerals 1 to 9 in fig. 1) is in one-to-one correspondence with a relationship curve of a load and structural stress attention point 1-1. Meanwhile, a relation curve of load and structural stress attention points 1-2 is established in a one-to-one correspondence mode in each measuring region (regions shown as reference numbers 1 to 9 in figure 1).
S5, when the airplane is in a delivery and use stage, the load at the structural stress attention point 1-1 is not accurately measured through a strain gauge in the step S1, a pneumatic load sensor is arranged in the center of each measuring area (such as the areas shown by the reference numerals 1 to 9 in the figure 1), and the arrangement positions of the pneumatic load sensors are shown by the reference numerals 2-1, 2-2, 2-3, 2-4, 2-5, 2-6, 2-7, 2-8 and 2-9 in the figure 2; the measurement area of the wing at this stage coincides with the measurement area of the wing at the test stage.
S6, fitting the load of each measurement area through mathematical interpolation by reading the value of each pneumatic load sensor, wherein the load is an estimated value; and combining the load with the relation curve corresponding to the measuring region obtained in the step S3 to estimate the contribution of the load of the measuring region to the stress value at the structural stress attention point 1-1.
And S7, superposing the load of all the measurement areas on the contribution of the stress value at the structural stress attention point 1-1, and then estimating the total stress value at the structural stress attention point 1-1.
S8, repeating the mode shown in the steps S5-S7 to estimate the total stress value of another structural stress focus point 1-2
Example three:
the difference between this embodiment and the first embodiment is:
when the stress magnitude at a plurality of structural stress attention points needs to be evaluated, the steps S1-S7 are repeated continuously, and the total stress values at all the structural stress attention points can be evaluated respectively.
When the total stress value at the first structural stress attention point 1-1 is estimated, a strain gauge is respectively stuck to each structural stress attention point on the wing in the step S2, and when the total stress values at other structural stress attention points are subsequently estimated, the step S2 is directly skipped.
When estimating the total stress value at the first structural stress attention point 1-1, respectively recording the stress value of the strain gauge at the first structural stress attention point 1-1 under different loads for a certain measuring area in step S3 and step S4, establishing a relationship curve between the load and the first structural stress attention point 1-1, and simultaneously, respectively recording the stress values of the strain gauges at other structural stress attention points under different loads, respectively establishing a relationship curve between the load and other structural stress attention points, and when subsequently estimating the total stress value at other structural stress attention points, directly using the obtained relationship curve to skip step S3 and step S4.
It is to be noted that the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
The scope of the present invention is not limited to the technical solutions disclosed in the embodiments, and any modifications, equivalent substitutions, improvements, etc. made to the above embodiments according to the technical spirit of the present invention fall within the scope of the present invention.
Claims (10)
1. The utility model provides a method for aassessment structure stress focus point stress size on structure through multizone is loaded respectively after the stack which characterized in that: when the loading condition of any structural stress focus point in the structural member needs to be tracked in the whole life cycle, the structural member is divided into a limited number of measurement areas, then the contribution amount of the loading condition of each measurement area to the stress value of the structural stress focus point is measured, and the contribution amounts of all the measurement areas are superposed to evaluate the loading condition of the structural stress focus point in the structural member.
2. The method for evaluating the stress magnitude of the structural stress focus point on the structural member after the multiple regions are respectively loaded and superposed according to claim 1, wherein the method comprises the following steps: when the number of the structural stress concerns to be evaluated is multiple, the steps of claim 1 are repeated continuously, and the evaluation of the loading condition of all other structural stress concerns can be completed.
3. The method for evaluating the stress magnitude of the structural stress focus point on the structural member after the multiple regions are respectively loaded and superposed according to claim 1, wherein the method comprises the following steps: the structural member is an aircraft wing.
4. The method for evaluating the stress magnitude of a structural stress focus on a structural member after superposition of multiple zones separately loaded according to claim 3, comprising the steps of:
s1, when the stress magnitude of a stress focus point of a certain structure needs to be evaluated, dividing a wing into a limited number of measurement areas;
s2, when the airplane is in a test stage, adhering a strain gauge to the stress attention point of the structure on the wing;
s3, independently applying loads with different sizes to a certain measuring area, respectively recording stress values of strain gages at stress attention points of the structure under different loads, and then establishing a relation curve of the loads and the stress attention points of the structure;
s4, continuously replacing the measurement areas and repeating the step S3 until all the measurement areas respectively establish a relation curve of the load and the structural stress attention points;
s5, when the airplane is in a delivery and use stage, arranging a sensor in each measuring area; the measuring area of the stage is consistent with the measuring area of the test stage;
s6, interpolating and fitting the load of each measuring area by reading the value of each sensor, wherein the load is an estimated value; combining the load with the relation curve corresponding to the measurement region obtained in the step S3, and estimating the contribution of the load of the measurement region to the stress value at the structure stress attention point;
and S7, superposing the load of all the measurement areas on the contribution of the stress value at the structure stress attention point, and estimating to obtain the total stress value at the structure stress attention point.
5. The method for evaluating the stress magnitude of the structural stress focus point on the structural member after the multiple regions are respectively loaded and superposed according to claim 4, wherein the method comprises the following steps: when the stress magnitude at a plurality of structural stress attention points needs to be evaluated, the steps S1-S7 are repeated continuously, and the total stress values at all the structural stress attention points can be evaluated respectively.
6. The method for evaluating the stress magnitude of the structural stress focus point on the structural member after the multiple regions are respectively loaded and superposed according to claim 5, wherein the method comprises the following steps: when the total stress value of the first structural stress concern point is estimated, a strain gauge is respectively adhered to each structural stress concern point on the wing in the step S2, and when the total stress value of other structural stress concern points is estimated subsequently, the step S2 is directly skipped.
7. The method for evaluating the stress magnitude of the structural stress focus point on the structural member after the multiple regions are respectively loaded and superposed according to claim 6, wherein the method comprises the following steps: when estimating the total stress value at the first structural stress attention point, in step S3 and step S4, the stress values of the strain gauge at the first structural stress attention point under different loads are recorded for a certain measurement region, a relationship curve of the load and the first structural stress attention point is established, meanwhile, the stress values of the strain gauge at other structural stress attention points under different loads can be recorded, a relationship curve of the load and other structural stress attention points is established, and when estimating the total stress value at other structural stress attention points subsequently, the obtained relationship curve is directly used, and step S3 and step S4 are skipped.
8. The method for evaluating the stress magnitude of the structural stress focus point on the structural member after the multiple regions are respectively loaded and superposed according to claim 4, wherein the method comprises the following steps: the sensor is a pneumatic load sensor.
9. The method for evaluating the stress magnitude of the structural stress focus point on the structural member after the multiple regions are respectively loaded and superposed according to claim 4, wherein the method comprises the following steps: the sensor is installed at the area center of each measurement area, and the position of application of the load in step S3 is also at the area center of each measurement area.
10. The method for evaluating the stress magnitude at the structural stress focus point on the structural member after the multi-region separate loading and stacking according to any one of claims 1 to 9, wherein: the number of the measuring areas is more than 6, and the measuring areas are increased according to actual requirements.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115165298A (en) * | 2022-09-09 | 2022-10-11 | 中国航空工业集团公司哈尔滨空气动力研究所 | Method for monitoring real-time dynamic load monitoring coefficient of rotary shaft balance |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115165298A (en) * | 2022-09-09 | 2022-10-11 | 中国航空工业集团公司哈尔滨空气动力研究所 | Method for monitoring real-time dynamic load monitoring coefficient of rotary shaft balance |
| CN115165298B (en) * | 2022-09-09 | 2022-12-23 | 中国航空工业集团公司哈尔滨空气动力研究所 | Method for monitoring real-time dynamic load monitoring coefficient of rotary shaft balance |
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Effective date of registration: 20230627 Address after: 561000 Songqi Town, Anshun economic and Technological Development Zone, Guizhou Province Applicant after: AVIC GUIZHOU AIRPLANE Co.,Ltd. Address before: 561000 Anshun economic and Technological Development Zone, Guizhou Applicant before: Guizhou Guifei aircraft design and Research Institute Co.,Ltd. |