CN105334032B - A kind of calculation method in model structure service life - Google Patents
A kind of calculation method in model structure service life Download PDFInfo
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Abstract
A kind of calculation method in model structure service life, it is related to aircraft fatigue technical field, for providing the comparison model structure service life according to the comparative test of existing aircraft model structural life-time, a kind of method for passing through prototype and improvement type key position and simulating test specimen Fatigue Comparative provided by the invention, provide close model structure service life quantitative relationship, on the basis of original machine type full scale fatigue test longevity assessment result, provide the service life for improving type, to reach under the premise of guaranteeing aircraft utilization safety, shorten the model lead time, save the purpose of research fund.The calculation method in model structure service life provided by the invention by key position simulate test specimen Fatigue Comparative on the basis of organic type full scale fatigue test longevity assessment result, it provides and improves model structure service life quantitative relationship, the longevity is determined to improve model structure, and important evidence is provided, it is of great significance to shortening the new machine lead time, saving development cost, and provides safety guarantee to type is improved.
Description
Technical field
The present invention relates to aircraft fatigue technical field, in particular to a kind of calculation method in model structure service life,
For providing the structural life-time for improving type according to the comparative test of existing aircraft model structural life-time.
Background technique
The aircraft on production line need to be extracted to determine structure fatigue life according to the development and design process of aircraft, is carried out complete
Scale fatigue test.It, generally can be using a certain reference type machine as base to meet different use demands in modern aircraft design research
Plinth derives the type for the model that multiple structures are close, use condition is different.It is not referring to type machine relative to reference type machine
Based on the new architecture developed due to being completely new aircraft, it is necessary to press normal development process, carry out the whole of corresponding code requirement
Development task, but for the improvement type of the derivation model based on referring to type machine, generally take two kinds of development modes:
A) identical as referring to type machine, it carries out all developing task by code requirement；
B) it is limited by research fund and lead time, by comparing with referring to type machine, only carries out design analysis and design
Development test, and without full-scale verification test.
The shortcomings that the first in above two development mode a) plants mode is that research fund is more, the lead time is long, and
Although two kinds b) mode save research fund, shorten the lead time, larger sacrifice is made that in terms of the safety of aircraft.
The technical issues of present urgent need to resolve is how to reduce reasearch funds and lead time, that is, is not using the first
A) under the premise of the development mode of mode can with second b) mode carry out the development of new architecture, and can be improved improvement
The safety of the aircraft of type.
Summary of the invention
It is an object of the invention to solve above-mentioned deficiency in the prior art, a kind of calculating side in model structure service life is provided
Method reduces research fund, shortens the development time and improve the safety of new architecture.
The purpose of the present invention is achieved through the following technical solutions: a kind of calculation method in model structure service life passes through the service life
Comparative test obtains the structural life-time for improving type, includes the following steps:
S1 is determined according to the difference for improving type usage mode on the basis of prototype and is improved the typically used as task of type
Section；
S2 works out the fatigue load spectrum for improving type longevity assessment；
S3 determines the structural key position for improving type, according to the geometry of key position, material characteristics, designs and presses phase
The type testing part of comparative trial of life-span is used for technique processing and manufacturing；
The testpieces of same specification is equally divided into two groups by S4, is carried out prototype respectively and is improved under type loading spectrum
Fatigue test, log；
S5 analyzes test result, and longevity of the structural key position for improving type in the case where two kinds of different loads are composed is calculated
Order relativity；
S6, the comparative trial of life-span analysis of comprehensive multiple key positions are provided as a result, based on prototype longevity assessment conclusion
Improve the service life quantitative relationship of type.
In above scheme preferably, typically used as mission profile is the typically used as situation for improving type in S1, including
The taking off, climb, cruising of aircraft, maneuvering flight, attack, downslide and landing.
In any of the above-described scheme preferably, the quantity of the type testing part processing of same specification is 14-20 in S3.
In any of the above-described scheme preferably, include following calculating step in S5:
S5-1, parameter Estimation
According to fatigue statisic principle, fatigue life obeys logarithm normal distribution, remembers x=logN, then the probability density letter of x
Number isRelevant parameter estimated value is
In formula,Average value after taking logarithm for all test results,
It is the standard deviation of testpieces fatigue test results with s,
N50For logarithmic mean value；
S5-2, error analysis
Confidence level γ is taken, corresponding t distribution quantile is t1-γ, logarithm median life estimated valueWith logarithm median life
The relative error of true value is
In formula, n is testpieces number；
S5-3, homogeneity test of variance；
The Typical Aircraft testpieces of comparison prototype and improvement type the ratio between service life variance under different loads spectrumWith
Fα/2(ν2,ν1) judge whether two test results have homogeneity of variance,
In formula, ν2=n2- 1, ν1=n2- 1 is the freedom degree of two groups of testpieces of respective function, n2、n1For two groups of testpieces
Number；
S5-4, t distribution inspection
Construct t distribution function
Its freedom degree is
In formula,For the t distribution function of corresponding two groups of testpieces,
WithRespectively two groups of test results take the average value after logarithm,
s1And s2The logarithm standard deviation of respectively two groups test results,
n1And n2The testpieces quantity of respectively two groups tests,
νtFor the freedom degree of t distribution function,
Show that two test results are not significantly different, on the contrary, it is obvious poor to show that two test results have
It is different；
S5-5, two comparison of test results
The index of aging and prototype of type are improved by the homogeneity of variance and the judgement of t inspection result that compare two test results
It is whether identical, improve type and prototype type testing part service life ratio
In formula, N50,1And N50,2The respectively logarithmic mean value of prototype and improvement type test.
In any of the above-described scheme preferably, type is improved in S6 with prototype type testing part service life ratio is
In formula, N50,1And N50,2The respectively logarithmic mean value of prototype and improvement type test, calculates according to formula (5)
The service life of type is improved out.
The beneficial effect of the calculation method in model structure service life provided by the present invention is, is simulated and is tried by key position
Part Fatigue Comparative provides on the basis of organic type full scale fatigue test longevity assessment result and improves the model structure service life
Quantitative relationship determine the longevity to improve model structure and provides important evidence, to shorten the new machine lead time, save development cost have it is heavy
Meaning is wanted, and provides safety guarantee to type is improved.
Detailed description of the invention
Fig. 1 is the flow diagram of the preferred embodiment of the calculation method in model structure service life according to the invention；
Fig. 2 is preferred embodiment shown in Fig. 1 of the calculation method in model structure service life according to the invention for the service life
The schematic diagram of the type testing part of comparative test；
Fig. 3 is the improvement type of preferred embodiment shown in Fig. 1 of the calculation method in model structure service life according to the invention
Overload surmounts number curve and the curve graph compared with prototype；
Fig. 4 is the improvement type of preferred embodiment shown in Fig. 1 of the calculation method in model structure service life according to the invention
Middle outer wing to the schematic diagram of 14 auricle testpieces of band plate Φ；
Fig. 5 is the improvement type of preferred embodiment shown in Fig. 1 of the calculation method in model structure service life according to the invention
Central wing lower wall panels titanium alloy welding testpieces schematic diagram；
Fig. 6 is the improvement type of preferred embodiment shown in Fig. 1 of the calculation method in model structure service life according to the invention
Undercarriage beam test part schematic diagram.
Specific embodiment
In order to better understand according to the calculation method in the model structure service life of the present invention program, below in conjunction with the present invention
Attached drawing in embodiment, technical solution in the embodiment of the present invention are further described in more detail.In the accompanying drawings, from beginning to end
Same or similar label indicates same or similar element or element with the same or similar functions.Described embodiment
It is a part of the embodiment of the present invention, instead of all the embodiments.Embodiment below with reference to attached drawing description is exemplary
, it is intended to it is used to explain the present invention, and is not considered as limiting the invention.Based on the embodiments of the present invention, this field
Those of ordinary skill's every other embodiment obtained without creative efforts, belongs to protection of the present invention
Range.The embodiment of the present invention is described in detail with reference to the accompanying drawing.
Attached drawing is merely for convenience of description of the present invention and simplification of the description in the description of the present invention, it is to be understood that, and
It is not that the device of indication or suggestion meaning or element must have a particular orientation, be constructed and operated in a specific orientation, therefore
It should not be understood as limiting the scope of the invention.
As shown in figs 1 to 6, the calculation method in model structure service life provided by the invention, is obtained by comparative trial of life-span
The structural life-time for improving type, includes the following steps:
S1, on the basis of prototype, according to the difference of improvement type usage mode, (that such as develops on the basis of prototype is same
Type trainer aircraft and prototype compare aerial mission ratio shared by training Co-pilot and are significantly more than prototype) it determines and improves type
Typically used as mission profile；
S2 works out the fatigue load spectrum for improving type longevity assessment；
S3 determines the structural key position for improving type, according to the geometry of key position, material characteristics, designs and presses phase
The type testing part of comparative trial of life-span is used for technique processing and manufacturing；
The testpieces of same specification is equally divided into two groups by S4, is carried out prototype respectively and is improved under type loading spectrum
Fatigue test, log；
S5 analyzes test result, and longevity of the structural key position for improving type in the case where two kinds of different loads are composed is calculated
Order relativity；
S6, the comparative trial of life-span analysis of comprehensive multiple key positions are provided as a result, based on prototype longevity assessment conclusion
Improve the service life quantitative relationship of type.
The typically used as mission profile of S1 is the typically used as situation for improving type, including aircraft in above-mentioned steps S1-S6
Take off, climb, cruising, maneuvering flight, attack, downslide and landing.The quantity of the type testing part processing of same specification in S3
For 14-20.
Include following calculating step in S5:
S5-1, parameter Estimation
According to fatigue statisic principle, fatigue life obeys logarithm normal distribution, remembers x=logN, then the probability density letter of x
Number isRelevant parameter estimated value is
In formula,Average value after taking logarithm for all test results,
It is the standard deviation of testpieces fatigue test results with s,
N50For logarithmic mean value；
S5-2, error analysis
Confidence level γ is taken, corresponding t distribution quantile is t1-γ, logarithm median life estimated valueWith logarithm median life
The relative error of true value is
In formula, n is testpieces number；
S5-3, homogeneity test of variance；
The Typical Aircraft testpieces of comparison prototype and improvement type the ratio between service life variance under different loads spectrumWith
Fα/2(ν2,ν1) judge whether two test results have homogeneity of variance,
In formula, ν2=n2- 1, ν1=n2- 1 is the freedom degree of two groups of testpieces of respective function, n2、n1For two groups of testpieces
Number；
S5-4, t distribution inspection
Construct t distribution function
Its freedom degree is
In formula,For the t distribution function of corresponding two groups of testpieces,
WithRespectively two groups of test results take the average value after logarithm,
s1And s2The logarithm standard deviation of respectively two groups test results,
n1And n2The testpieces quantity of respectively two groups tests,
νtFor the freedom degree of t distribution function,
Show that two test results are not significantly different, on the contrary, it is obvious poor to show that two test results have
It is different；
S5-5, two comparison of test results
The index of aging and prototype of type are improved by the homogeneity of variance and the judgement of t inspection result that compare two test results
It is whether identical.
5, the calculation method in model structure service life as described in claim 1, which is characterized in that type and original are improved in S6
Type machine type testing part service life ratio is
In formula, N50,1And N50,2The respectively logarithmic mean value of prototype and improvement type test, calculates according to formula (5)
The service life of type is improved out.
In the specific use process, according to the calculation method preferred embodiment in model structure service life provided by the invention
Step calculates the structural life-time of prototype.
S1: it on the basis of prototype, is determined according to the difference for improving type usage mode and improves the typically used as task of type
Section.The basic spectrum block of one of certain prototype loading spectrum (is flown comprising several using the specific of mission profile by 15 typical subjects
Row), totally 90 compositions that rise and fall, represented for 120.833 pilot time, be shown in Table 1.
The typically used as mission profile of certain prototype of table 1
For modified compared with prototype, subject 2 is divided into subject 2 and subject 2-1, remaining flight subject is identical, but flies
Section's purpose ratio is different, is shown in Table 2: where flight damages the flight ratio of biggish subject 6,7,8,9 compared with prototype
Greatly, illustrate that the use intensity of modified aircraft is larger, loading spectrum will overweight prototype.
Table 2 improves the typically used as mission profile of type
S2: according to the typically used as mission profile of the modified aircraft of table 2, loading spectrum is worked out, Fig. 3 gives modified and flies
The overload of machine loading spectrum surmounts number curve and compared with prototype, the curve of type is improved in figure on prototype, into one
The loading spectrum that step demonstrates improvement type overweights prototype.
S3: determining the structural key position for improving type, according to the geometry of key position, material characteristics, designs and presses phase
The type testing part of comparative trial of life-span is used for technique processing and manufacturing.According to the analysis of the structural life-time of prototype and longevity assessment
Work determines outer aileron edge strip, middle outer wing jointing strip plate, central wing lower wall panels, rises and falls and set a roof beam in place, hang down for housing construction
The structural key position at the positions such as 2 beam of tail, stabilizer torque tube.For improving type, since structure type is close, above-mentioned position
It is still structural key position for improving type.Type testing is designed by the geometrical parameters of above-mentioned key position, material etc.
Part, testpieces quantity are shown in Table 3, and structure type is shown in Fig. 2, Fig. 4~Fig. 6.
Table 3 is used for the testpieces quantity of comparative trial of life-span
S4: being equally divided into two groups for the testpieces of same specification, carries out prototype respectively and improves under type loading spectrum
Fatigue test, log.
In addition for aileron edge strip testpieces, table 4 is set forth the outer aileron edge strip of prototype and improves the test of type
As a result.
4 test result of table
S5: longevity of the structural key position for improving type in the case where two kinds of different loads are composed is calculated in analysis test result
Order relativity.
S5-1, parameter Estimation
According to formula (1), the intermediate value initiating life of two test results is calculated.
5 liang of test crack initiation life estimation of distribution parameters results of table
S5-2, error analysis
Project analysis error delta=5% is taken, corresponding t is calculated by formula (2)1-γ, and further acquire confidence level γ
(looking into the t function distribution table in mathematical statistics book), is shown in Table 6.
6 error analysis of table
Error analysis the result shows that: have 99.9% or more assurance say the logarithm intermediate value test life of above two test with
Within 5%, the precision of median life estimated value is acceptable the error of logarithm median life true value in engineering.
S5-3, homogeneity test of variance
Take significance α=0.05, amphitypy Typical Aircraft testpieces the ratio between service life variance under different loads spectrum(8,7 be the test number of packages of two groups of tests, 8-1,7-1 F
The freedom degree of two variable of function, the F function table by consulting mathematical statistics obtain 5.70 numerical value) show two test results not
With homogeneity of variance.
S5-4, t distribution inspection
Significance α=0.05 is taken, by formula (3), is had:
Show that its freedom degree is ν by formula (4)t=9.
Show that two test results have notable difference.
S5-5, two comparison of test results
According to S5-3、S5-4Calculating analysis, since two test results do not have homogeneity of variance, t inspection has also indicated that obvious
Difference, therefore, according to formula (5), the service life ratio of modified and the outer aileron edge strip type testing part of prototype are as follows:
S6: the comparative trial of life-span analysis of comprehensive multiple key positions is as a result, provide the service life quantitative relationship for improving type.
According to above-mentioned test and analytical procedure, comparative trial of life-span and the calculating of total Test part listed by table 3 are completed
Analysis, obtains the service life ratio of each testpieces as shown in table 7.
The service life ratio of each key position of 7 modified of table and prototype
| Serial number | Position | The service life ratio k of comparative trial of life-span |
| 1 | 1 the foot of a wall subordinate's edge strip of outer wing | 0.87 |
| 2 | Middle outer wing is to 14 auricle of band plate Φ | 0.85 |
| 3 | Middle outer wing is to 12.5 auricle of band plate Φ | 0.82 |
| 4 | Middle outer wing is to band plate and vertical wall connecting portion | 0.80 |
| 5 | Central wing lower wall panels titanium alloy welding position | 0.80 |
| 6 | It rises and falls and sets a roof beam in place | 0.83 |
| 7 | 2 beam of vertical fin and siding connecting portion | 0.88 |
The service life ratio of the test result of each key position in consolidated statement 7, modified and prototype is 0.85 or so, lower than original
The index of aging of type machine for the sake of guarding, takes the minimum service life than 0.8, that is, improves to guarantee that it is safe that the flight for improving type uses
The service life of type and prototype ratio is 0.8.
It is described in detail above in conjunction with the calculation method specific embodiment in model structure service life of the invention, but is not
Limitation of the present invention, any simple modification made to the above embodiment belongs to this according to the technical essence of the invention
The technical scope of invention, it is also necessary to explanation, the model of the calculation method technical solution in model structure service life according to the invention
Farmland includes any combination between each part mentioned above.
Claims (5)
1. a kind of calculation method in model structure service life, which is characterized in that obtain the knot for improving type by comparative trial of life-span
In the structure service life, include the following steps:
S1 is determined according to the difference for improving type usage mode on the basis of prototype and is improved the typically used as mission profile of type；
S2 works out the fatigue load spectrum for improving type longevity assessment；
S3 determines the structural key position for improving type, according to the geometry of key position, material characteristics, designs and presses identical work
Skill processing and manufacturing is used for the type testing part of comparative trial of life-span；
The type testing part of same specification is equally divided into two groups by S4, is carried out prototype respectively and is improved under type loading spectrum
Fatigue test, log；
S5 analyzes test result, and service life pair of the structural key position for improving type in the case where two kinds of different loads are composed is calculated
The relationship of ratio；
S6, the comparative trial of life-span analysis of comprehensive multiple key positions provide improvement as a result, based on prototype longevity assessment conclusion
The service life quantitative relationship of type.
2. the calculation method in model structure service life as described in claim 1, it is characterised in that: typically used as mission profile in S1
For the typically used as situation for improving type, taking off, climbing, cruising including aircraft, maneuvering flight, attack, downslide and landing.
3. the calculation method in model structure service life as described in claim 1, it is characterised in that: the typical examination of same specification in S3
The quantity for testing part processing is 14-20.
4. the calculation method in model structure service life as described in claim 1, which is characterized in that include that following calculate walks in S5
It is rapid:
S5-1, parameter Estimation
According to fatigue statisic principle, fatigue life obeys logarithm normal distribution, remembers x=logN, then the probability density function of x isRelevant parameter estimated value is
In formula,Average value after taking logarithm for all test results,
It is the standard deviation of type testing part fatigue test results with s,
N50For logarithmic mean value；
S5-2, error analysis
Confidence level γ is taken, corresponding t distribution quantile is t1-γ, logarithm median life estimated valueWith logarithm median life true value
Relative error be
In formula, n is type testing part number；
S5-3, homogeneity test of variance；
The Typical Aircraft testpieces of comparison prototype and improvement type the ratio between service life variance under different loads spectrumWith Fα/2(ν2,
ν1) judge whether two test results have homogeneity of variance,
In formula, ν2=n2- 1, ν1=n2- 1 is the freedom degree of two groups of type testing parts of respective function, n2、n1It is tried for two groups of typical cases
Test the number of part；
S5-4, t distribution inspection
Construct t distribution function
Its freedom degree is
In formula,For the t distribution function of corresponding two groups of type testing parts,
WithRespectively two groups of test results take the average value after logarithm,
s1And s2The logarithm standard deviation of respectively two groups test results,
n1And n2The type testing number of packages amount of respectively two groups tests,
νtFor the freedom degree of t distribution function,
Show that two test results are not significantly different, on the contrary, showing that two test results have notable difference；
S5-5, two comparison of test results
By the homogeneity of variance and t inspection result that compare two test results judge to improve type index of aging and prototype whether
It is identical.
5. the calculation method in model structure service life as described in claim 1, which is characterized in that improve type and prototype in S6
Type testing part service life ratio is
The service life for improving type, in formula, N are calculated according to formula (5)50,1And N50,2Respectively prototype and improvement type test
Logarithmic mean value.
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| CN108120589B (en) * | 2016-11-28 | 2021-06-08 | 成都飞机工业（集团）有限责任公司 | Spar web service life extension simulation test method based on outfield service life |
| CN114216674B (en) * | 2021-09-29 | 2024-06-14 | 中国航发湖南动力机械研究所 | Gear fatigue test piece and manufacturing method thereof |
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