CN109592075B - Dynamic monitoring method for measuring data of airplane structure fatigue test - Google Patents
Dynamic monitoring method for measuring data of airplane structure fatigue test Download PDFInfo
- Publication number
- CN109592075B CN109592075B CN201811312002.9A CN201811312002A CN109592075B CN 109592075 B CN109592075 B CN 109592075B CN 201811312002 A CN201811312002 A CN 201811312002A CN 109592075 B CN109592075 B CN 109592075B
- Authority
- CN
- China
- Prior art keywords
- strain
- fatigue
- value
- displacement
- test
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
-
- 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
- G01N3/32—Investigating strength properties of solid materials by application of mechanical stress by applying repeated or pulsating forces
Landscapes
- Engineering & Computer Science (AREA)
- General Health & Medical Sciences (AREA)
- Immunology (AREA)
- Chemical & Material Sciences (AREA)
- Analytical Chemistry (AREA)
- Biochemistry (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Life Sciences & Earth Sciences (AREA)
- Pathology (AREA)
- Health & Medical Sciences (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention relates to a dynamic monitoring method for measuring data of an airplane structure fatigue test, which is characterized by comprising the following steps of: firstly, measuring static strain displacement; step two, establishing a basic data template for static strain displacement measurement; measuring fatigue strain displacement; establishing a basic data template for fatigue strain displacement measurement; fifthly, performing formal fatigue test and performing static error calculation and judgment; and sixthly, performing formal fatigue test and performing fatigue error calculation and judgment. The method has the advantages of correct theoretical basis, clear and simple implementation steps, easy control and implementation of a computer and clear engineering concept. The invention solves the problem that whether the test is normally operated in the airplane structure fatigue test is not easy to determine.
Description
Technical Field
The invention belongs to the field of aviation fatigue damage tolerance tests, and particularly relates to a dynamic data monitoring method for an airplane structure fatigue test.
Background
The airplane structure fatigue test has the advantages of long test period, large measurement data volume, difficult monitoring of test states, high difficulty in real-time monitoring and analysis of measurement data and difficult conclusion on whether the fatigue test is effectively, continuously and stably carried out.
In the fatigue test, for the analysis of the measurement data, the test is stopped after the test is completed for a period of time, and the effectiveness and stability of the measured strain and displacement in the past period of time are analyzed and judged by specially leaving time, but the data volume is very large, the analysis and observation are performed only by naked eyes, the participation of human factors is large, the operability is not strong, and the time consumption is too long.
Aiming at the characteristics of large measurement data volume, large analysis difficulty of measurement data, difficult monitoring and the like in the fatigue test of the aircraft structure, the conclusion of whether the fatigue test of the aircraft structure is effectively and continuously carried out can be given by firstly establishing a basic template for static strain displacement measurement, then establishing a basic template for fatigue strain displacement measurement, then comparing the basic template for fatigue strain displacement measurement with the basic template for fatigue strain displacement measurement in a formal fatigue test, comparing the basic template for static strain displacement measurement with the basic template for static strain displacement measurement, and finally carrying out true and false identification and error analysis of the data.
Disclosure of Invention
The purpose of the invention is: a dynamic data monitoring method for an airplane structure fatigue test is provided.
The technical scheme of the invention is as follows: a dynamic data monitoring method for an aircraft structure fatigue test comprises the following steps:
step one, measuring static strain displacement. Measuring static strain displacement under the load of each peak and each valley value, and sequentially and respectively measuring the strain value epsilon of each strain gauge of the monitoring part (including the main examination part and the load monitoring part) of each peak and each valley value under the 100% load according to the sequence in the arrangement of the fatigue load spectrum and the measurement requirement of the static strain displacementij(i 1,2,3.. times.n; j 1,2,3.. times.m) and a displacement value μijAnd N, j is 1,2,3, N, L, wherein N is the total number of peaks and troughs in the load spectrum, M is the number of strain gauges of monitoring parts (including main checking parts and load monitoring parts) in the test piece, and L is the number of displacement measuring points of the monitoring parts in the test piece.
And step two, establishing a basic data template for static strain displacement measurement. Repeating the step one for 3 times, and respectively calculating the average value of each strain measurement value
Average of individual displacement measurements
Wherein the content of the first and second substances,
and step three, measuring fatigue strain displacement. According to the sequence of the fatigue load spectrum and the determined loading frequency, the strain values epsilon 'of the strain gauges of the monitoring parts (including the main checking part and the load monitoring part) at the moment of each wave crest value and each wave trough value are sequentially and respectively measured'ij,(i＝1,2,3......,N；j＝1,2,3,......,M) And displacement value of μ'ij,(i＝1,2,3......,N；j＝1,2,3,......,L)。
And step four, establishing a basic data template for fatigue strain displacement measurement. Repeating the step three for 10 times, and respectively calculating the average value of each strain measurement value
Average of individual displacement measurements
Wherein the content of the first and second substances,
and fifthly, performing formal fatigue test and performing static error calculation and judgment. When static measurement is needed in a fatigue test, strain values epsilon of strain gauges of monitoring parts (including main checking parts and load monitoring parts) with wave crest and wave trough values under 100% load of the strain gauges are measured according to the sequence in the arrangement of fatigue load spectrums and the measurement requirements of static strain displacement sequentially and respectivelyijAnd the shift value muijAnd calculating a relative error η 'between the static strain displacement measurement and the static strain displacement measurement base data template'ijAnd η "ijJudging eta'ijAnd η "ijWhether or not to satisfy
Or
If the data meets the requirements, the test is stopped immediately, and checking, troubleshooting and data authenticity identification are carried out.
And sixthly, performing formal fatigue test and performing fatigue error calculation and judgment. Strain gauge strain values epsilon 'of all wave crest and wave trough value instant monitoring parts are measured in real time according to fatigue load spectrum sequence'ijAnd displacement value μ μ μ'ijAnd calculating the relative error between the fatigue strain displacement measurement value and the basic data template of the fatigue strain displacement measurement in real time
And
judgment of
And
whether or not to satisfy
Or
If the data meets the requirements, the test is stopped immediately, and the authenticity of the data can be identified by checking, troubleshooting and the like.
The invention has the advantages that:
the invention provides a dynamic data monitoring method for an airplane structure fatigue test, which aims at solving the problem of whether the test in the airplane structure fatigue test is effective and continuous and stable, and provides a dynamic data monitoring method for the airplane structure fatigue test from the data dynamic monitoring angle of the airplane structure fatigue test. Based on the characteristics of long test period, large test measurement data amount, difficult comparison and analysis of test data, difficult identification of true and false of test data and the like in the aircraft structure fatigue test, the invention provides a method for comparing fatigue strain displacement measurement data with a fatigue strain displacement measurement basic data template in a formal fatigue test, comparing the static strain displacement measurement data with the static strain displacement measurement basic data template, and finally giving a conclusion whether the aircraft structure fatigue test is effective, continuous and stable through true and false identification and error analysis of the data. The method has the advantages of correct theoretical basis, clear and simple implementation steps, easy control and implementation of a computer and clear engineering concept. The invention solves the problem that whether the test is normally operated in the airplane structure fatigue test is not easy to determine.
Drawings
FIG. 1 is a schematic view of a fatigue load peak valley;
FIG. 2 is a schematic view of a wave block of fatigue loading;
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings, referring to fig. 1 to 2.
As shown in FIG. 1, a schematic diagram of the fatigue load peaks and troughs is shown, wherein a schematic diagram of 4 wave blocks in a fatigue test is given according to the sequence of the peaks and the troughs. The device consists of 4 wave crests, 4 wave troughs, a time shaft and a load value.
As shown in fig. 2, a diagram of a wave block for fatigue loading.
A dynamic data monitoring method for an aircraft structure fatigue test comprises the following steps:
step one, measuring static strain displacement. Measuring static strain displacement under the load of each peak and each valley value, and sequentially and respectively measuring the strain value epsilon of each strain gauge of the monitoring part (including the main examination part and the load monitoring part) of each peak and each valley value under the 100% load according to the sequence in the arrangement of the fatigue load spectrum and the measurement requirement of the static strain displacementij(i 1,2,3.. times.n; j 1,2,3.. times.m) and a displacement value μijAnd N, j is 1,2,3, N, L, wherein N is the total number of peaks and troughs in the load spectrum, M is the number of strain gauges of monitoring parts (including main checking parts and load monitoring parts) in the test piece, and L is the number of displacement measuring points of the monitoring parts in the test piece.
And step two, establishing a basic data template for static strain displacement measurement. Repeating the step two for 3 times, and respectively calculating the average value of each strain measurement value
Average of individual displacement measurements
Wherein the content of the first and second substances,
and step three, measuring fatigue strain displacement. According to the sequence of the fatigue load spectrum and the determined loading frequency, the strain values epsilon 'of the strain gauges of the monitoring parts (including the main checking part and the load monitoring part) at the moment of each wave crest value and each wave trough value are sequentially and respectively measured'ij(i ═ 1,2,3.. times, N: 1,2,3.. times, M) and a displacement value μ'ij,(i＝1,2,3......,N；j＝1,2,3,......,L)。
And step four, establishing a basic data template for fatigue strain displacement measurement. Repeating the step three for 10 times, and respectively calculating the average value of each strain measurement value
Average of individual displacement measurements
Wherein the content of the first and second substances,
and fifthly, performing formal fatigue test and performing static error calculation and judgment. When static measurement is needed in a fatigue test, strain values epsilon of strain gauges of monitoring parts (including main checking parts and load monitoring parts) with wave crest and wave trough values under 100% load of the strain gauges are measured according to the sequence in the arrangement of fatigue load spectrums and the measurement requirements of static strain displacement sequentially and respectivelyijAnd the shift value muijAnd calculating a relative error η 'between the static strain displacement measurement and the static strain displacement measurement base data template'ijAnd η "ijJudging eta'ijAnd η "ijWhether or not to satisfy
Or
If the data meets the requirements, the test is stopped immediately, and checking, troubleshooting and data authenticity identification are carried out.
And sixthly, performing formal fatigue test and performing fatigue error calculation and judgment. Strain gauge strain values epsilon 'of all wave crest and wave trough value instant monitoring parts are measured in real time according to fatigue load spectrum sequence'ijAnd displacement value μ μ μ'ijAnd calculating the relative error between the fatigue strain displacement measurement value and the basic data template of the fatigue strain displacement measurement in real time
And
judgment of
And
whether or not to satisfy
Or
If the data meets the requirements, the test is stopped immediately, and the authenticity of the data can be identified by checking, troubleshooting and the like.
Examples
The present invention will be described in further detail with reference to a specific example.
A dynamic data monitoring method for an aircraft structure fatigue test comprises the following steps:
it is known that:
the total number N of peaks and troughs in the load spectrum is 4 (each load value is 0N, 1200N, -800N, 1500N, -500N, 0N in sequence), the number M of strain gauges of monitoring parts (including main checking parts and load monitoring parts) in a test piece is 1, the number L of displacement measuring points is 1, and the number Z of wave blocks passing through each minute during fatigue spectrum walking is 5.
Step one, measuring static strain displacement. Measuring static strain displacement under the load of each peak and each valley value, and sequentially and respectively measuring the strain value epsilon of each strain gauge of the monitoring part (including the main examination part and the load monitoring part) of each peak and each valley value under the 100% load according to the sequence in the arrangement of the fatigue load spectrum and the measurement requirement of the static strain displacementij(i 1,2,3.. times.n; j 1,2,3.. times.m) and a displacement value μijAnd N, j is 1,2,3, N, L, wherein N is the total number of peaks and troughs in the load spectrum, M is the number of strain gauges of monitoring parts (including main checking parts and load monitoring parts) in the test piece, and L is the number of displacement measuring points of the monitoring parts in the test piece.
And step two, establishing a basic data template for static strain displacement measurement. Repeating the step two for 3 times, and respectively calculating the average value of each strain measurement value
Average of individual displacement measurements
Wherein the content of the first and second substances,
| static force | / | Static force | Load(s) | Load(s) | Load(s) | Load(s) |
| / | / | Serial number | 1200 | -800 | 1500 | -500 |
| First static force | Strain of | 1 | 2560 | -1264 | 3060 | -1001 |
| First static force | Displacement of | 2 | 12.55 | -8.63 | 15.78 | -7.24 |
| 2 nd static force | Strain of | 1 | 2500 | -1294 | 3160 | -1101 |
| 2 nd static force | Displacement of | 2 | 12.05 | -8.13 | 14.98 | -6.84 |
| 3 rd static force | Strain of | 1 | 2660 | -1162 | 2968 | -964 |
| 3 rd static force | Displacement of | 2 | 13.21 | -8.96 | 16.48 | -7.87 |
| 3 times average value | Strain of | 1 | 2573 | -1240 | 3063 | -1022 |
| 3 times average value | Displacement of | 2 | 12.60 | -8.57 | 15.75 | -7.32 |
And step three, measuring fatigue strain displacement. According to the sequence of the fatigue load spectrum and the determined loading frequency, the strain values epsilon 'of the strain gauges of the monitoring parts (including the main checking part and the load monitoring part) at the moment of each wave crest value and each wave trough value are sequentially and respectively measured'ij(i ═ 1,2,3.. times, N: 1,2,3.. times, M) and a displacement value μ'ij,(i＝1,2,3......,N；j＝1,2,3,......,L)。
And step four, establishing a basic data template for fatigue strain displacement measurement. Repeating the step three for 10 times, and respectively calculating the average value of each strain measurement value
Average of individual displacement measurements
Wherein the content of the first and second substances,
| fatigue | / | Fatigue | Load(s) | Load(s) | Load(s) | Load(s) |
| / | / | Serial number | 1200 | -800 | 1500 | -500 |
| Fatigue of 1 st time | Strain of | 1 | 2560 | -1264 | 3060 | -1001 |
| Fatigue of 1 st time | Displacement of | 2 | 12.55 | -8.63 | 15.78 | -7.04 |
| Fatigue of 2 nd time | Strain of | 1 | 2500 | -1294 | 3160 | -1051 |
| Fatigue of 2 nd time | Displacement of | 2 | 12.05 | -8.13 | 14.98 | -6.8 |
| 3 rd time fatigue | Strain of | 1 | 2660 | -1172 | 2968 | -964 |
| 3 rd time fatigue | Displacement of | 2 | 13.21 | -8.96 | 16.48 | -7.87 |
| Fatigue of 4 th time | Strain of | 1 | 2523 | -1204 | 3045 | -1021 |
| Fatigue of 4 th time | Displacement of | 2 | 12.65 | -8.63 | 15.68 | -7.24 |
| Fatigue of 5 th time | Strain of | 1 | 2506 | -1251 | 3198 | -1108 |
| Fatigue of 5 th time | Displacement of | 2 | 12.45 | -8.13 | 14.88 | -6.75 |
| Fatigue of 6 th time | Strain of | 1 | 2620 | -1162 | 2978 | -964 |
| Fatigue of 6 th time | Displacement of | 2 | 13.71 | -8.96 | 16.2 | -7.87 |
| Fatigue of 7 th time | Strain of | 1 | 2660 | -1244 | 3062 | -1102 |
| Fatigue of 7 th time | Displacement of | 2 | 12.05 | -8.63 | 15.74 | -7.22 |
| Fatigue of 8 th time | Strain of | 1 | 2520 | -1304 | 3140 | -1051 |
| Fatigue of 8 th time | Displacement of | 2 | 12.25 | -8.13 | 14.64 | -6.84 |
| 9 th fatigue | Strain of | 1 | 2610 | -1145 | 2968 | -964 |
| 9 th fatigue | Displacement of | 2 | 13.11 | -8.96 | 16.41 | -7.97 |
| Fatigue of 10 th time | Strain of | 1 | 2614 | -1162 | 2985 | -986 |
| Fatigue of 10 th time | Displacement of | 2 | 13.21 | -8.96 | 16.48 | -7.57 |
| Average value of 10 times | Strain of | 1 | 2581 | -1204 | 3031 | -1000 |
| Average value of 10 times | Displacement of | 2 | 12.86 | -8.68 | 15.84 | -7.46 |
And fifthly, performing formal fatigue test and performing static error calculation and judgment. When static measurement is needed in a fatigue test, strain values epsilon of strain gauges of monitoring parts (including main checking parts and load monitoring parts) with wave crest and wave trough values under 100% load of the strain gauges are measured according to the sequence in the arrangement of fatigue load spectrums and the measurement requirements of static strain displacement sequentially and respectivelyijAnd the shift value muijAnd calculating a relative error η 'between the static strain displacement measurement and the static strain displacement measurement base data template'ijAnd η "ijCalculated of η'ij＝5.5％，η”ijWhen the test is judged to be 6.1%, the test should be stopped immediately and the test, failure and authenticity identification of the data should be carried out.
Based on the analysis of relative errors, the test should be stopped immediately and the inspection, troubleshooting and authenticity identification of the data should be carried out.
And sixthly, performing formal fatigue test and performing fatigue error calculation and judgment. Strain gauge strain values epsilon 'of all wave crest and wave trough value instant monitoring parts are measured in real time according to fatigue load spectrum sequence'ijAnd displacement value μ μ μ'ijAnd calculating the relative error between the fatigue strain displacement measurement value and the basic data template of the fatigue strain displacement measurement in real time
And
is calculated by
At this time, the test should be stopped immediately and the authenticity of the data should be identified by checking, troubleshooting, and the like.
| Fatigue | / | Load(s) | Load(s) | Load(s) | Load(s) |
| / | / | 1200 | -800 | 1500 | -500 |
| Mean value of fatigue | Strain of | 2581 | -1204 | 3031 | -1000 |
| Mean value of fatigue | Displacement of | 12.86 | -8.68 | 15.84 | -7.46 |
| Current measured value | Strain of | 2866 | -1012 | 3264 | -1196 |
| Current measured value | Displacement of | 14.26 | -7.85 | 17.55 | -6.59 |
| Relative error | Strain of | 11.0％ | 15.9％ | 7.7％ | 19.6％ |
| Relative error | Displacement of | 10.9％ | 9.6％ | 10.8％ | 11.7％ |
Based on the analysis of relative errors, the test should be stopped immediately and the inspection, troubleshooting and authenticity identification of the data should be carried out.
The invention provides a dynamic data monitoring method for an airplane structure fatigue test, which aims at solving the problem of whether the test in the airplane structure fatigue test is effective and continuous and stable, and provides a dynamic data monitoring method for the airplane structure fatigue test from the data dynamic monitoring angle of the airplane structure fatigue test. Based on the characteristics of long test period, large test measurement data amount, difficult comparison and analysis of test data, difficult identification of true and false of test data and the like in the aircraft structure fatigue test, the invention provides a method for comparing fatigue strain displacement measurement data with a fatigue strain displacement measurement basic data template in a formal fatigue test, comparing the static strain displacement measurement data with the static strain displacement measurement basic data template, and finally giving a conclusion whether the aircraft structure fatigue test is effective, continuous and stable through true and false identification and error analysis of the data. The method has the advantages of correct theoretical basis, clear and simple implementation steps, easy control and implementation of a computer and clear engineering concept. The invention solves the problem that whether the test is normally operated in the airplane structure fatigue test is not easy to determine.
Claims (1)
1. A dynamic monitoring method for measuring data of an airplane structure fatigue test is characterized by comprising the following steps:
step one, carrying out static strain displacement measurement: measuring static strain displacement under the load of each peak and each valley value, and measuring the strain value epsilon of the strain gauge at the monitoring part of each peak and each valley value under the 100% load of the peak and each valley value according to the sequence in the arrangement of the fatigue load spectrum and the measurement requirement of the static strain displacement in turnij1,2,3.. cndot.n; j 1,2,3.. said., M; displacement value muij,i＝1,2,3......,N；j1,2,3, L, N is the total number of peaks and troughs in the load spectrum, M is the number of strain gauges of a monitored part in the test piece, and L is the number of displacement measurement points of the monitored part in the test piece;
step two, establishing a basic data template for static strain displacement measurement: establishing a basic data template for measuring the static strain displacement, repeating the step one for 3 times, and respectively calculating the average value of each strain measurement value
Average of individual displacement measurements
Wherein the content of the first and second substances,
step three, fatigue strain displacement measurement is carried out: according to the sequence of the fatigue load spectrum and the determined loading frequency, the strain value epsilon 'of the strain gauge at the monitoring part at each peak value and each trough value moment is measured respectively in sequence'ij1,2,3.. cndot.n; j 1,2,3.. said., M; displacement value of mu'ij,i＝1,2,3......,N；j＝1,2,3,......,L；
Step four, establishing a basic data template for fatigue strain displacement measurement: repeating the step three for 10 times, and respectively calculating the average value of each strain measurement value
Average of individual displacement measurements
Wherein the content of the first and second substances,
and fifthly, performing formal fatigue test and performing static error calculation and judgment, and when static measurement is needed in the fatigue test, sequentially and respectively measuring strain values epsilon of each monitored part with wave crest and wave trough values under 100% load according to the sequence in the arrangement of the fatigue load spectrum and the static strain displacement measurement requirementijAnd the shift value muijAnd calculating a relative error η 'between the static strain displacement measurement and the static strain displacement measurement base data template'ijAnd η "ijJudging eta'ijAnd η "ijWhether or not to satisfy
Or
If the data meets the requirements, the test is stopped immediately, and checking, troubleshooting and data authenticity identification are carried out;
and sixthly, performing formal fatigue test, calculating and judging fatigue errors, and measuring strain values epsilon 'of the strain gauge at each peak value and trough value instant monitoring position in real time according to the sequence of the fatigue load spectrum'ijAnd displacement value μ μ μ'ijAnd calculating the relative error between the fatigue strain displacement measurement value and the basic data template of the fatigue strain displacement measurement in real time
And
judgment of
And
whether or not to satisfy
Or
If the data meets the requirements, the test is stopped immediately, and checking, troubleshooting and data authenticity identification are carried out.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811312002.9A CN109592075B (en) | 2018-11-05 | 2018-11-05 | Dynamic monitoring method for measuring data of airplane structure fatigue test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811312002.9A CN109592075B (en) | 2018-11-05 | 2018-11-05 | Dynamic monitoring method for measuring data of airplane structure fatigue test |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109592075A CN109592075A (en) | 2019-04-09 |
| CN109592075B true CN109592075B (en) | 2022-04-19 |
Family
ID=65957599
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811312002.9A Active CN109592075B (en) | 2018-11-05 | 2018-11-05 | Dynamic monitoring method for measuring data of airplane structure fatigue test |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109592075B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110362896B (en) * | 2019-06-28 | 2023-05-05 | 中国飞机强度研究所 | Non-linearity-based aircraft structure static strength test data screening method and device |
| CN111274648B (en) * | 2019-12-24 | 2023-04-07 | 中国航空工业集团公司沈阳飞机设计研究所 | Distributed flight load design method for civil aircraft leading edge flap |
| CN110987422B (en) * | 2019-12-25 | 2021-09-14 | 中国航空工业集团公司西安飞机设计研究所 | Component looseness checking method for aircraft control system dynamic fatigue test |
| CN112224444B (en) * | 2020-10-16 | 2024-04-09 | 中国飞机强度研究所 | Whole machine test monitoring device and method based on multi-source data fusion |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105474796B (en) * | 2012-06-18 | 2014-07-16 | 上海宇航系统工程研究所 | Solar cell wing ground fatigue test load spectrum formulating method |
| CN107092728A (en) * | 2017-03-30 | 2017-08-25 | 成都航空职业技术学院 | A kind of fanjet tenses axle fatigue test method |
| CN108163225A (en) * | 2017-11-29 | 2018-06-15 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft nose landing gear outer barrel suspension joint launch fatigue test method |
| CN108168855A (en) * | 2017-11-29 | 2018-06-15 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft nose landing gear outer barrel suspension joint launch slow test method |
| RO129022B1 (en) * | 2013-05-24 | 2020-06-30 | Universitatea "Transilvania" Din Braşov | Stand for accelerated fatigue testing of blades and testing method |
-
2018
- 2018-11-05 CN CN201811312002.9A patent/CN109592075B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105474796B (en) * | 2012-06-18 | 2014-07-16 | 上海宇航系统工程研究所 | Solar cell wing ground fatigue test load spectrum formulating method |
| RO129022B1 (en) * | 2013-05-24 | 2020-06-30 | Universitatea "Transilvania" Din Braşov | Stand for accelerated fatigue testing of blades and testing method |
| CN107092728A (en) * | 2017-03-30 | 2017-08-25 | 成都航空职业技术学院 | A kind of fanjet tenses axle fatigue test method |
| CN108163225A (en) * | 2017-11-29 | 2018-06-15 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft nose landing gear outer barrel suspension joint launch fatigue test method |
| CN108168855A (en) * | 2017-11-29 | 2018-06-15 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft nose landing gear outer barrel suspension joint launch slow test method |
Non-Patent Citations (3)
| Title |
|---|
| 操纵面非线性气动弹性响应引起的结构疲劳损伤分析方法研究;李毅等;《振动与冲击》;20150615;第34卷(第11期);全文 * |
| 波浪腹板工形构件疲劳性能试验研究及设计建议;郭彦林等;《土木工程学报》;20151015;第48卷(第10期);全文 * |
| 螺栓疲劳寿命计算方法探讨及研究;翟新康;《制造业自动化》;20160125;第38卷(第1期);全文 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109592075A (en) | 2019-04-09 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109592075B (en) | Dynamic monitoring method for measuring data of airplane structure fatigue test | |
| Mohammed et al. | Vibration signal analysis for gear fault diagnosis with various crack progression scenarios | |
| Lu et al. | Fault severity recognition of aviation piston pump based on feature extraction of EEMD paving and optimized support vector regression model | |
| EP2384971B1 (en) | Method of determining a maneuver performed by an aircraft | |
| Park et al. | A positive energy residual (PER) based planetary gear fault detection method under variable speed conditions | |
| CN110095274B (en) | Steel trestle static load test evaluation method considering inelastic deformation | |
| CN101819096B (en) | Cable force monitoring based health monitoring method for identifying damaged cables and support displacement | |
| CN102184291A (en) | System level fault diagnosis method for full-test non-feedback system | |
| CN103018063A (en) | Bridge random fatigue life prediction method based on Mittag-Leffler distribution | |
| CN102156873A (en) | Chaos-based method for detecting and classifying early single-point faults of mechanical component | |
| Tang et al. | Feature extraction for latent fault detection and failure modes classification of board-level package under vibration loadings | |
| Brandão et al. | Calculation of gear tooth flank surface wear during an FZG micropitting test | |
| CN103678938B (en) | A kind of degradation model consistency check method of space-oriented shape and range of error | |
| Xie et al. | Comprehensive fatigue estimation and fault diagnosis based on Refined Generalized Multi-Scale Entropy method of centrifugal fan blades | |
| CN109592074B (en) | Method for determining loading frequency of airplane structure fatigue test | |
| Junior et al. | Unbalance evaluation of a scaled wind turbine under different rotational regimes via detrended fluctuation analysis of vibration signals combined with pattern recognition techniques | |
| Niknam et al. | Techniques of trend analysis in degradation-based prognostics | |
| Liu et al. | A new impact model for vibration features of a defective ball bearing | |
| CN107577902B (en) | UKF-based airplane fatigue structure residual life prediction method | |
| CN107798149A (en) | A kind of aircraft maintainability appraisal procedure | |
| Rudd et al. | Probabilistic fracture mechanics analysis methods for structural durability | |
| CN111351655A (en) | Method for diagnosing gear fault in locomotive gear box | |
| Ghodake et al. | A review on fault diagnosis of gear-box by using vibration analysis method | |
| RU2517772C1 (en) | Vibration-based diagnostics of mechanisms by vibration characteristic function | |
| Merzoug et al. | Early detection of gear failure by vibration analysis |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |