CN109857977A - Fatigue life calculation method based on frequency domain under a kind of vibration of alternating temperature - Google Patents
Fatigue life calculation method based on frequency domain under a kind of vibration of alternating temperature Download PDFInfo
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Abstract
The invention discloses the fatigue life calculation methods based on frequency domain under a kind of vibration of alternating temperature, steps of the method are: vibration stress-time load history that heat structure key position is held in acquisition is separated with temperature-time load history, resolve into two signals, by Fast Fourier Transform (FFT), the power spectral density spectrum of loading spectrum is generated；Statistics parameter conclusion is carried out, determines auto-correlation function respectively；Using Dirlik method, the rain stream amplitude probability density function of oscillating load is calculated；Temperature range is subjected to tax power according to the time interval of demarcation interval, calculate separately the fatigue damage under the rainy S-N parameter of curve of different temperatures is combined with the stream amplitude probability density function of oscillating load, and the corresponding weight of the fatigue damage under each temperature range is multiplied, it finally adds up and obtains total fatigue damage of vibrating fatigue under continuous alternating temperature.By illustrating that this method can hold the damage of heat structure to aircraft key very well and make preferable prediction with conventional Time-domain method comparing result.
Description
Technical field
The present invention relates to the fatigue life calculation methods based on frequency domain under a kind of vibration of alternating temperature, and application field is to belong to machinery
Part field.
Background technique
For hypersonic vehicle in flight course, body key structure is random by engine noise and outer layer shock wave
The coupling of the continually changing high temperature load of oscillating load and surface, Service Environment is extremely severe, thus in thermal stress and
Fatigue rupture, the serious service life for affecting hypersonic vehicle are caused under the synergy of external load power.It is superb
The main failure forms of sonic flight device key structure are that the vibrating fatigue under high temperature is destroyed, and key holds the continuous change of heat structure
Warm fatigue strength under oscillation stresses design is the important content of Intensity Design.
Vibrating fatigue life prediction under high temperature at present predominantly only considers the isothermal fatigue life prediction under steady temperature,
Damage caused by temperature change holds heat structure aircraft is ignored, there is biggish error and uncertainty.Accordingly, it is considered to warm
Influence of the degree variation to vibrating fatigue, studying the fatigue life calculation method based on frequency domain under a kind of alternating temperature vibration has important meaning
Justice.
Summary of the invention
Present invention aims to meet the needs of hypersonic vehicle key holds heat structure Intensity Design, one is proposed
Fatigue life calculation method based on frequency domain under kind alternating temperature vibration.
The technical solution adopted by the present invention is the fatigue life calculation method based on frequency domain under a kind of vibration of alternating temperature, and realizing should
Method the steps include:
Step 1): the vibration stress-time load history and temperature-time load history of heat structure key position are held in acquisition
It is separated, resolves into two signals；
Step 2): by the collected vibration stress of step 1)-time load history, by Fast Fourier Transform (FFT) (FFT),
Generate can feedback vibration feature stress rumble spectrum；
Step 3): the stress rumble spectrum that step 2) processing obtains is subjected to statistics parameter conclusion, is determined respectively from phase
Close function RX(τ), bilateral power spectral density SX(ω), one-sided power spectrum density WX(ω):
RX(τ)=E [X (t) X (t+ τ)]
Wherein τ is the time shift of vibration signal, and ω is angular frequency；
Step 4): it according to the relevant parameter in step 3), further calculates to obtain and it is expected that average forward direction wears rate ν0, it is expected that
Peak value crossing rate νp, and the bandwidth factor race α of characterization random process bandwidth characteristicm:
Wherein λ0, λ2, λ4Respectively 0 rank of random vibration signal, 2 ranks, 4 rank spectral moments can be calculated by following formula:
Step 5): it according to the relevant parameter for calculating the oscillating load power spectrum density obtained in step 4), uses
The rain stream amplitude probability density function p (s of oscillating load is calculated in Dirlik methoda):
Wherein
Step 6): by the collected temperature-time load history of step 1), it is subdivided into a series of constant temperature on a timeline
Section, as shown in Figure 2.
Step 7): temperature corresponding to each temperature range obtained according to step 6), bond material is known limited
S-N curve under a different temperatures is established using temperature as the three-dimensional system of coordinate of Z axis, and in the coordinate system, not to known two
Synthermal S-N curve does bilinear interpolation, the S-N curve under corresponding step 6) series of temperature section is obtained, such as Fig. 3 institute
Show.So that it is determined that the mechanical characteristic of material at different temperatures；
Step 8): the temperature range in step 6) is subjected to tax power according to the time interval of demarcation interval, is calculated separately not
The rain stream amplitude probability density function p (s of S-N parameter of curve and step 5) oscillating load under synthermala) combine under it is tired
Strain wound, and the corresponding weight of the fatigue damage under each temperature range is multiplied, it finally adds up and obtains under continuous alternating temperature
Total fatigue damage of vibrating fatigue:
Wherein, n is the temperature range sum after segmentation, TiFor i-th of constant temperature section, C (Ti) and k (Ti) it is i-th of constant temperature
Section TiInterior material parameter is obtained, F by bilinear interpolation in step 7)iIt causes to damage for the temperature under i-th of constant temperature section
Weight,
Compared with prior art, the present invention has the advantages that.
The present invention has the advantages that proposing the fatigue life calculation method based on frequency domain under a kind of vibration of alternating temperature.The party
Method can effectively consider damage caused by temperature change holds heat structure aircraft key, by material known limited
The bilinear interpolation of S-N curve under different temperatures obtains the material characteristic parameter of material at different temperatures under continuous alternating temperature,
And oscillating load frequency spectrum is combined, the final alternating temperature vibrating fatigue damage for calculating structure.By being verified with conventional Time-domain calculation method,
Continuous alternating temperature vibrating fatigue life prediction calculating is carried out using this method and achieves better effects.
Detailed description of the invention
Fig. 1 the method for the present invention realizes the flow chart that the vibrating fatigue service life calculates under continuous alternating temperature.
The schematic diagram that Fig. 2 the method for the present invention is finely divided Temperature-time load in time shaft.
Fig. 3 the method for the present invention is between the bilinear interpolation schematic diagram different temperatures S-N curve.
Specific embodiment
A specific embodiment of the invention is described with reference to the drawings.
The present invention is compared by using with traditional reliable heat-machine Calculation of Fatigue Life result, is made to the present invention
It further illustrates.
Fatigue life calculation method based on frequency domain under a kind of vibration of alternating temperature, specific implementation method are as follows:
Step 1): the vibration stress-time load history and temperature-time load history of heat structure key position are held in acquisition
It is separated, resolves into two signals；
Step 2): by the collected vibration stress of step 1)-time load history, by Fast Fourier Transform (FFT) (FFT),
Generate can feedback vibration feature stress rumble spectrum；
Step 3): the stress rumble spectrum that step 2) processing obtains is subjected to statistics parameter conclusion, is determined respectively from phase
Close function RX(τ), bilateral power spectral density SX(ω), one-sided power spectrum density WX(ω):
RX(τ)=E [X (t) X (t+ τ)]
Wherein τ is the time shift of vibration signal, and ω is angular frequency；
Step 4): it according to the relevant parameter in step 3), further calculates to obtain and it is expected that average forward direction wears rate ν0, it is expected that
Peak value crossing rate νp, and the bandwidth factor race α of characterization random process bandwidth characteristicm:
Wherein λ0, λ2, λ4Respectively 0 rank of random vibration signal, 2 ranks, 4 rank spectral moments can be calculated by following formula:
Step 5): it according to the relevant parameter for calculating the oscillating load power spectrum density obtained in step 4), uses
The rain stream amplitude probability density function p (s of oscillating load is calculated in Dirlik methoda):
Wherein
Step 6): by the collected temperature-time load history of step 1), it is subdivided into a series of constant temperature on a timeline
Section, as shown in Figure 2.
Step 7): temperature corresponding to each temperature range obtained according to step 6), bond material is known limited
S-N curve under a different temperatures is established using temperature as the three-dimensional system of coordinate of Z axis, and in the coordinate system, not to known two
Synthermal S-N curve does bilinear interpolation, the S-N curve under corresponding step 6) series of temperature section is obtained, such as Fig. 3 institute
Show.So that it is determined that the mechanical characteristic of material at different temperatures；
Step 8): the temperature range in step 6) is subjected to tax power according to the time interval of demarcation interval, is calculated separately not
The rain stream amplitude probability density function p (s of S-N parameter of curve and step 5) oscillating load under synthermala) combine under it is tired
Strain wound, and the corresponding weight of the fatigue damage under each temperature range is multiplied, it finally adds up and obtains under continuous alternating temperature
Total fatigue damage of vibrating fatigue:
Wherein, n is the temperature range sum after segmentation, TiFor i-th of constant temperature section, C (Ti) and k (Ti) it is i-th of constant temperature
Section TiInterior material parameter is obtained, F by bilinear interpolation in step 7)iIt causes to damage for the temperature under i-th of constant temperature section
Weight,
The present invention has the advantages that proposing the fatigue life calculation method based on frequency domain under a kind of vibration of alternating temperature.The party
Method can effectively consider damage caused by temperature change holds heat structure aircraft key, by material known limited
The bilinear interpolation of S-N curve under different temperatures obtains the material characteristic parameter of material at different temperatures under continuous alternating temperature,
And oscillating load frequency spectrum is combined, the final alternating temperature vibrating fatigue damage for calculating structure.
In order to verify the effect of vibrating fatigue Life Calculating Methods under continuous alternating temperature proposed by the present invention, this method is predicted
The lifetime results that nickel-base high-temperature alloy material GH4169 is obtained are compared with conventional Time-domain heat engine fatigue life prediction result, knot
Fruit shows that the bimetry range of the two is closer to.It is therefore proposed that continuous alternating temperature under vibrating fatigue Life Calculating Methods can
Preferable prediction is made with the damage for holding heat structure to aircraft key.
Claims (3)
1. the fatigue life calculation method based on frequency domain under a kind of vibration of alternating temperature, it is characterised in that: realize steps of the method are,
Realize the steps include: for this method
Step 1): vibration stress-time load history of heat structure key position is held in acquisition and temperature-time load history carries out
Separation, resolves into two signals；
Step 2): by the collected vibration stress of step 1)-time load history, by Fast Fourier Transform (FFT) FFT, generation can
The stress rumble spectrum of feedback vibration feature；
Step 3): the stress rumble spectrum that step 2) processing obtains is subjected to statistics parameter conclusion, determines auto-correlation letter respectively
Number RX(τ), bilateral power spectral density SX(ω), one-sided power spectrum density WX(ω):
RX(τ)=E [X (t) X (t+ τ)]
Wherein τ is the time shift of vibration signal, and ω is angular frequency；
Step 4): it according to the relevant parameter in step 3), further calculates to obtain and it is expected that average forward direction wears rate ν0, it is expected that peak value
Crossing rate νp, and the bandwidth factor race α of characterization random process bandwidth characteristicm:
Wherein λ0, λ2, λ4Respectively 0 rank of random vibration signal, 2 ranks, 4 rank spectral moments are calculated by following formula:
Step 5): according to the relevant parameter for calculating the oscillating load power spectrum density obtained in step 4), using Dirlik
The rain stream amplitude probability density function p (s of oscillating load is calculated in methoda):
Wherein
Step 6): by the collected temperature-time load history of step 1), it is subdivided into a series of constant temperature section on a timeline；
Step 7): according to step 6) obtain each temperature range corresponding to temperature, bond material it is known it is limited not
S-N curve under synthermal is established using temperature as the three-dimensional system of coordinate of Z axis, and in the coordinate system, to known two not equalities of temperature
The S-N curve of degree does bilinear interpolation, obtains the S-N curve under corresponding step 6) series of temperature section；So that it is determined that material
Mechanical characteristic at different temperatures；
Step 8): the temperature range in step 6) is subjected to tax power according to the time interval of demarcation interval, calculates separately not equality of temperature
The rain stream amplitude probability density function p (s of S-N parameter of curve and step 5) oscillating load under degreea) combine under fatigue damage
Wound, and the corresponding weight of the fatigue damage under each temperature range is multiplied, it finally adds up and obtains frequency domain under continuous alternating temperature
Total fatigue damage of vibrating fatigue:
Wherein, n is the temperature range sum after segmentation, TiFor i-th of constant temperature section, C (Ti) and k (Ti) it is i-th of constant temperature section
TiInterior material parameter is obtained, F by bilinear interpolation in step 7)iThe power of damage is caused for the temperature under i-th of constant temperature section
Value,
2. the fatigue life calculation method based on frequency domain under a kind of alternating temperature vibration according to claim 1, it is characterised in that:
The step 7) is established according to the constant temperature section after division, S-N curve of the bond material under known limited different temperatures
Using temperature as the three-dimensional system of coordinate of Z axis, and in the coordinate system, bilinearity is done to the S-N curve of known two different temperatures and is inserted
Value, thus the fatigue properties parameter of the acquisition material of fast, economical at various temperatures.
3. the fatigue life calculation method based on frequency domain under a kind of alternating temperature vibration according to claim 1, it is characterised in that:
The step 8) carries out tax power according to time interval fatigue damage caused by transformation temperature of temperature range after dividing, and will be each
The corresponding weight of fatigue damage under a temperature range is multiplied, and finally adds up and obtains frequency domain vibrating fatigue under continuous alternating temperature
Total fatigue damage.
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| CN110569614A (en) * | 2019-09-12 | 2019-12-13 | 成都大汇智联科技有限公司 | fatigue prediction method for water turbine top cover bolt |
| CN111950163A (en) * | 2020-08-20 | 2020-11-17 | 上海电气风电集团股份有限公司 | Wind blade fatigue life monitoring method |
| CN113239556A (en) * | 2021-05-21 | 2021-08-10 | 中国工程物理研究院总体工程研究所 | Fatigue damage rate multiple estimation method of random acceleration power spectral density |
| CN114444336A (en) * | 2022-04-08 | 2022-05-06 | 杭州安脉盛智能技术有限公司 | New energy automobile motor service life estimation method and system based on information fusion |
| CN115878985A (en) * | 2023-02-17 | 2023-03-31 | 湖南云箭科技有限公司 | System and method for determining vibration endurance test conditions of airborne equipment in sections |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110569614A (en) * | 2019-09-12 | 2019-12-13 | 成都大汇智联科技有限公司 | fatigue prediction method for water turbine top cover bolt |
| CN111950163A (en) * | 2020-08-20 | 2020-11-17 | 上海电气风电集团股份有限公司 | Wind blade fatigue life monitoring method |
| CN113239556A (en) * | 2021-05-21 | 2021-08-10 | 中国工程物理研究院总体工程研究所 | Fatigue damage rate multiple estimation method of random acceleration power spectral density |
| CN114444336A (en) * | 2022-04-08 | 2022-05-06 | 杭州安脉盛智能技术有限公司 | New energy automobile motor service life estimation method and system based on information fusion |
| CN114444336B (en) * | 2022-04-08 | 2022-07-26 | 杭州安脉盛智能技术有限公司 | New energy automobile motor service life estimation method and system based on information fusion |
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| CN115878985B (en) * | 2023-02-17 | 2023-06-09 | 湖南云箭科技有限公司 | Segmentation determining system and method for vibration endurance test conditions of airborne equipment |
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