CN113420366A - Method for verifying bonding strength of blade anti-icing and deicing heating assembly - Google Patents
Method for verifying bonding strength of blade anti-icing and deicing heating assembly Download PDFInfo
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Abstract
The invention belongs to the technical field of structural fatigue design of helicopters, and particularly relates to a method for verifying the bonding strength of a blade anti-icing and deicing heating assembly. The method adopts a small sample test combined with finite element stress calculation to evaluate the static strength and the fatigue life of the bonding surface, adopts the small sample test to replace a full-scale performance test, saves a large amount of test resources, effectively and uniformly applies a plurality of test loads to an assessment area through a 4-point bending fatigue loading method, and effectively evaluates the debonding inspection period of the deicing heating assembly.
Description
Technical Field
The invention belongs to the technical field of structural fatigue design of helicopters, and particularly relates to a method for verifying the bonding strength of a blade anti-icing and deicing heating assembly.
Background
In order to safely fly in an icing climate environment, an anti-icing and deicing system needs to be installed on a helicopter blade, a domestic common blade anti-icing and deicing system is an anti-icing and deicing system with an electric heating assembly, the helicopter blade anti-icing and deicing heating assembly is positioned between a blade body and a clad iron and structurally plays a connecting role, the helicopter blade anti-icing and deicing heating assembly is not a main bearing component, and the load is caused by deformation coordination between the blade and the clad iron.
The anti-icing and deicing heating assembly is mainly made of rubber materials, the bonding process is a new process, and the bonding process of the anti-icing and deicing heating assembly cannot avoid large-area debonding between the anti-icing and deicing heating assembly and the blade, so that the bonding performance of the interface of the anti-icing and deicing heating assembly needs to be measured again, and the bonding strength needs to be verified again.
At present, relevant public technologies are not searched at home and abroad, so that a method for verifying the bonding strength of the anti-icing heating assembly needs to be designed urgently to meet the delivery requirement of a system and determine the inspection and maintenance period of use.
Disclosure of Invention
The purpose of the invention is: aiming at the defects in the prior art, the invention provides a verification method for the bonding strength of a blade anti-icing and deicing heating assembly, which is characterized by planning a sample level test, measuring the strength performance of the bonding surface of the anti-icing and deicing heating assembly, evaluating the bonding strength by combining a finite element stress analysis result, designing a blade fatigue test loading method capable of coordinately loading a plurality of loads, enabling the load distribution of the bonding evaluation area of the anti-icing and deicing heating assembly to be more even than that of other loading modes, being closer to the real loading condition of the anti-icing and deicing heating assembly, and being capable of reasonably evaluating the debonding inspection period of the anti-icing and deicing heating assembly.
The technical scheme of the invention is as follows: in order to achieve the purpose, the invention provides a method for verifying the bonding strength of an anti-icing and deicing heating assembly of a blade, wherein the anti-icing and deicing heating assembly is arranged on a helicopter blade and is positioned between a blade body and a clad iron; the method comprises the following steps:
s1: defining a helicopter blade coordinate system and load;
taking the direction pointing to the blade tip as an x axis,the direction of the maximum chord length line of the blade section pointing to the trailing edge is a y-axis, and a z-axis is obtained according to the right-hand rule; centrifugal force FcPointing to the tip of the oar as positive, waving bending moment MyThe upper surface of the blade is pulled to be positive, and the moment M of the shimmy iszThe rear edge of the blade is pressed to be positive, and the torsional bending moment M isxThe front edge of the blade is bent upwards to be positive;
s2: obtaining a load spectrum through calculation or flight test, selecting and determining a helicopter blade danger section by using the load spectrum, and performing equivalent processing on the load spectrum to obtain a fatigue equivalent load;
the helicopter blades are subjected to the actions of centrifugal force, flapping bending moment, shimmy bending moment and torsional moment in the flying process, and the blade section with the harshest load under the action of the load is selected as a dangerous section; in the detailed design stage, a calculation load spectrum is compiled according to the calculation load; in the shaping stage, actually measured loads are tested according to flight tests and actually measured load spectrums are compiled;
the load spectrum can be written as the following formula (1)
Wherein F is a characteristic load and can be one of a flapping bending moment, a shimmy bending moment and a torque; fsta，iIs the static load of the i-th state, Fdyn，iDynamic load of i-th state, niIs the time proportion of the ith state, m is the total number of states, and
according to S-N curve of bonding surface of deicing heating assembly
Wherein s isdynIs a dynamic load, S∞The method is characterized in that the method adopts a Miner accumulated damage theory and loads the load according to a damage equivalence principle for the structural fatigue limit, N is the cycle number, alpha is an S-N curve parameterLoad spectrum equivalent is fatigue equivalent dynamic load FeqAs shown in the calculation formula (3)
S3: establishing a full-size finite element model of the blade with the anti-icing and heating assembly with the iron coating, applying loads of all states of the helicopter blade, analyzing a main stress form of the anti-icing and heating assembly, calculating bonding stress of the anti-icing and heating assembly in all stress states, and generating a stress spectrum;
establishing a full-size finite element model of the blade with the anti-icing heating assembly with the iron coating, applying loads of various states of the helicopter blade, analyzing main stress forms of rubber of the anti-icing heating assembly, and obtaining out-of-plane shear static stress tau of the anti-icing heating assembly in various statesstaAnd dynamic stress taudyn(ii) a The stress spectrum (tau) of the bonding surface of the deicing heating element is generated by combining the flight time ratios of the statessta，i，τdyn，i，ni) (i 1, 2.. m), according to the Miner accumulated damage theory, the stress spectrum dynamic load is equivalent to the fatigue equivalent stress tau by adopting a formula (4)eq；
S4: manufacturing a small sample of the anti-icing and deicing heating assembly, carrying out sample level test according to the main stress form of the anti-icing and deicing heating assembly obtained in the step S3, and testing and calculating the allowable static strength value and fatigue limit of the bonding surface of the anti-icing and deicing heating assembly, the iron clad and the blade body;
a4-plate shearing sample test method is planned, rubber of the anti-icing and deicing heating assembly is respectively bonded with a clad iron and a skin of a blade body, static damage and fatigue tests are respectively completed, and a static strength allowable value [ tau ] of a bonding surface is measured]And fatigue limit τ∞The calculation method is as follows;
calculating a static strength allowable value [ tau ] according to the following calculation formula (5), and taking the minimum value of all static test results:
[τ]＝min{τb1，τb2，…} (5)
τbithe shear failure stress of the i test piece shear static force test is shown;
calculating the fatigue limit tau of the single test piece according to the formula (6)∞i
τ∞i＝τdyn，i*Nα (6)
Wherein tau isdyn，iThe fatigue test shear stress is adopted, and N is the failure cycle number;
in one possible embodiment, the fatigue limit τ for all test pieces∞iCalculating the average fatigue limit tau by taking the logarithmic mean value∞；
S5: calculating the bonding strength of the anti-icing and deicing heating assembly;
the allowable stress adhesion static strength [ τ ] of the deicing heater module obtained in step S4]And fatigue limit tau∞iEvaluating the static strength and the fatigue life of the stress spectrum of the deicing heating assembly in the step S3, and calculating the bonding static strength margin and the average fatigue life of the deicing heating assembly;
the adhesion static strength margin m.s of the deicing heater module was calculated using the formula (7).
τ in equation (7)maxAll of τ in the stress spectrum of step S3sta，i+τdyn，iMaximum value of (d);
the fatigue life L of the bonding surface of the deicing heating element was calculated using the formula (8)
Wherein R is the hourly rotation speed of the rotor wing;
s6: manufacturing a full-size debonding expansion test piece;
selecting a blade which is not provided with an anti-icing and deicing heating assembly, cutting an airfoil section to transform the airfoil section into a blade airfoil section test piece, sequentially adhering an anti-icing and deicing heating assembly (3) and a coated iron (2) to the middle area of the blade airfoil section test piece, wherein the anti-icing and deicing heating assembly (3) and the blade airfoil section test piece are adhered to each other, and the adhesion surface between the anti-icing and deicing heating assembly (3) and the coated iron (2) has a debonding defect;
s7: carrying out full-size debonding and fatigue extension test
Carrying out a 4-point bending test loading scheme on the full-size debonding expansion test piece manufactured in the step S6, hinging and supporting two ends, positioning two middle loading clamping points at the outer ends of two sides of an assessment area (6), generating uniform bending moment in the assessment area in the middle of the clamping points when applying load, decomposing the bending moment into swinging and shimmy bending moments by adjusting the inclination angle of the test piece, and synchronously adding a torque loading actuator to realize the application of torque;
taking the maximum value of the actual measurement load spectrum of the waving, shimmy and torsional bending moment in the step S2 as a fatigue test load, attaching strain gauges for measuring the waving, shimmy and torsional bending moment on a test piece, judging whether the test loading load meets the requirement or not according to the calibration result of the strain gauges during loading, and checking the increase condition of the debonding area of the deicing heating assembly along with the test cycle number by a method of knocking iron during the fatigue test;
s8: calculating the service inspection period of the de-bonding expansion of the anti-ice heating assembly
The maximum allowable debonding area ratio of the deicing heating element is determined according to the use requirement, and is generally not more than 10%, and the test cycle number Nc corresponding to the maximum allowable debonding area ratio is found through the step S7, and the test load of the debonding expansion test is combined: the swing test bending moment Mytest, the shimmy test bending moment Mztest and the torsion test bending moment Mxtest are combined with the equivalent load calculated by the load spectrum in the step S2, and the formula (9) is used for calculating the corresponding debonding expansion fatigue time of the swing, shimmy and torsion bending moments respectively
The minimum value of the three is divided by the life dispersion coefficient k to obtain the service inspection period T of the anti-icing heating assembly
The life dispersion factor k ranges between 4 and 6.
The invention has the beneficial effects that: the invention relates to a verification method of the bonding strength of an anti-icing heating assembly, which adopts a small sample test combined with finite element stress calculation to evaluate the static strength and the fatigue life of a bonding surface, adopts the small sample test to replace a full-scale performance test, saves a large amount of test resources, effectively and uniformly applies a plurality of test loads to an examination area through a 4-point bending fatigue loading method, and effectively evaluates the debonding inspection period of the anti-icing heating assembly.
Drawings
FIG. 1 is a flow chart of the method of the present invention
FIG. 2 is a schematic view of the structure of the blade equipped with the deicing heater assembly of the present invention
FIG. 3 is a schematic view of a test piece and loading of the present invention
Wherein:
1 denotes an adhesion surface between the deicing heating element and the blade body, 2 denotes the blade iron, 3 denotes the internal structure of the deicing heating element, 4 denotes the blade body, F denotes a traction force applied thereto, and Mx denotes a torsional bending moment applied thereto.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the 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.
As shown in figure 1, a method for verifying the bonding strength of an anti-icing heating assembly of a blade is characterized in that as shown in figure 2, the anti-icing heating assembly is arranged on a helicopter blade and is positioned between a blade body and a clad iron; the method comprises the following steps:
s1: defining a helicopter blade coordinate system and load;
the helicopter blade is provided with an anti-icing and deicing heating assembly, and the anti-icing and deicing heating assembly is positioned between the blade body and the iron cladding;
taking the direction pointing to the tip of the blade as an x axis, taking the direction pointing to the trailing edge of the maximum chord length line of the section of the blade as a y axis, and obtaining a z axis according to a right-hand rule; centrifugal force FcPointing to the tip of the oar as positive, waving bending moment MyThe upper surface of the blade is pulled to be positive, and the moment M of the shimmy iszThe rear edge of the blade is pressed to be positive, and the torsional bending moment M isxThe front edge of the blade is bent upwards to be positive;
s2: obtaining a load spectrum through calculation or flight test, selecting and determining a helicopter blade danger section by using the load spectrum, and performing equivalent processing on the load spectrum to obtain a fatigue equivalent load;
the helicopter blades are subjected to the actions of centrifugal force, flapping bending moment, shimmy bending moment and torsional moment in the flying process, and the blade section with the harshest load under the action of the load is selected as a dangerous section; in the detailed design stage, a calculation load spectrum is compiled according to the calculation load; in the shaping stage, an actual measurement load spectrum is compiled according to the actual measurement load;
the load spectrum can be written in the form of formula (1)
(Fsta，i，Fdyn，i，ni)(i＝1，2...m) (1)
Wherein F is a characteristic load and can be one of a flapping bending moment, a shimmy bending moment and a torque; fsta，iIs the static load of the i-th state, Fdyn，iDynamic load of i-th state, niIs the ith stateIn a time ratio of m to the total number of states, and
according to S-N curve of bonding surface of deicing heating assembly
Wherein s isdynIs a dynamic load, S∞The method is characterized in that the structural fatigue limit, N and alpha are cycle times and S-N curve parameters, the Miner accumulated damage theory is adopted, and the load spectrum is equivalent to a fatigue equivalent dynamic load F according to the damage equivalent principleeqWherein F is a characteristic load, can be one of a waving bending moment, a shimmy bending moment and a torque, and has a calculation formula of
S3: analyzing the main stress form of the anti-icing and deicing heating assembly, calculating the bonding stress of the anti-icing and deicing heating assembly in each stress state, and generating a stress spectrum;
establishing a full-size finite element model of the blade with the anti-icing heating assembly with the iron coating, applying loads of various states of the helicopter blade, analyzing main stress forms of rubber of the anti-icing heating assembly, and obtaining out-of-plane shear static stress tau of the anti-icing heating assembly in various statesstaAnd dynamic stress taudyn(ii) a The stress spectrum (tau) of the bonding surface of the deicing heating element is generated by combining the flight time ratios of the statessta，i，τdyn，i，ni) (i 1, 2.. m), according to the Miner accumulated damage theory, the stress spectrum dynamic load is equivalent to the fatigue equivalent stress tau by adopting a formula (4)eq；
S4: manufacturing a small sample of the anti-icing and deicing heating assembly, carrying out sample level test according to the main stress form of the anti-icing and deicing heating assembly obtained in the step S3, and testing and calculating the allowable static strength value and fatigue limit of the bonding surface of the anti-icing and deicing heating assembly, the iron clad and the blade body;
a4-plate shearing sample test method is planned, rubber of the anti-icing and deicing heating assembly is respectively bonded with a clad iron and a skin of a blade body, static damage and fatigue tests are respectively completed, and a static strength allowable value [ tau ] of a bonding surface is measured]And fatigue limit τ∞The calculation method is as follows;
the allowable static strength value [ tau ] is taken as the minimum value of all static test results:
[τ]＝min{τb1，τb2，…} (5)
τbishear failure stress for shear static test of test piece i
Calculating the fatigue limit tau of the single-piece test piece according to the formula (6)∞iThe calculation formula is
τ∞i＝τdyn，i*Nα (6)
Wherein tau isdyn，iThe fatigue test shear stress is adopted, and N is the failure cycle number;
fatigue limit τ for all test pieces∞iCalculating the average fatigue limit tau by taking the logarithmic mean value∞；
S5: calculating the bonding strength of the anti-icing and deicing heating assembly;
the allowable stress adhesion static strength [ τ ] of the deicing heater module obtained in step S4]And fatigue limit tau∞iEvaluating the static strength and the fatigue life of the stress spectrum of the deicing heating assembly in the step S3, and calculating the bonding static strength margin and the average fatigue life of the deicing heating assembly
The adhesion static strength margin m.s of the deicing heater module was calculated using the formula (7).
τ in equation (7)maxAll of τ in the stress spectrum of step S3sta，i+τdyn，iMaximum value of
The fatigue life L of the bonding surface of the deicing heating element was calculated using the formula (8)
Wherein R is the hourly rotation speed of the rotor
S6: manufacturing full-size debonding expansion test piece
Selecting a blade which is not provided with an anti-icing and deicing heating assembly, cutting an airfoil section to transform the airfoil section into a blade airfoil section test piece, sequentially adhering an anti-icing and deicing heating assembly (3) and a coated iron (2) to the middle area of the blade airfoil section test piece, wherein the anti-icing and deicing heating assembly (3) and the blade airfoil section test piece are adhered to each other, and the adhesion surface between the anti-icing and deicing heating assembly (3) and the coated iron (2) has a debonding defect;
s7: carrying out full-size debonding and fatigue extension test
As shown in fig. 3, a test loading scheme of 4-point bending is performed on the full-size debonding expansion test piece manufactured in the step S6, two ends are hinged, the middle two loading clamping points are located at the outer ends of two sides of the assessment area (6), when a load is applied, a uniform bending moment is generated in the middle assessment area of the clamping points, the bending moment is decomposed into a waving bending moment and a shimmy bending moment by adjusting the inclination angle of the test piece, and a torque loading actuator is synchronously added to realize the application of torque;
taking the maximum value of the actual measurement load spectrum of the waving, shimmy and torsional bending moment in the step S2 as a fatigue test load, attaching strain gauges for measuring the waving, shimmy and torsional bending moment on a test piece, judging whether the test loading load meets the requirement or not through the calibration result of the strain gauges during loading, and checking the increase condition of the debonding area of the deicing heating assembly along with the test cycle number through a method of knocking iron during the fatigue test, as shown in the attached table 1 below;
attached table 1 debonding area and record of heating assembly full-size debonding extension test
S8: calculating the service inspection period of the de-bonding expansion of the anti-ice heating assembly
The maximum allowable debonding area ratio of the deicing heating element is determined according to the use requirement, and is generally not more than 10%, and the test cycle number Nc corresponding to the maximum allowable debonding area ratio is found through the step S7, and the test load of the debonding expansion test is combined: the swing test bending moment Mytest, the shimmy test bending moment Mztest and the torsion test bending moment Mxtest are combined with the equivalent load calculated by the load spectrum in the step S2, and the formula (9) is used for calculating the corresponding debonding expansion fatigue time of the swing, shimmy and torsion bending moments respectively
The minimum value of the three is divided by the life dispersion coefficient k to obtain the service inspection period T of the anti-icing heating assembly
The life dispersion coefficient k was 4.
The foregoing is merely a detailed description of the embodiments of the present invention, and some of the conventional techniques are not detailed. The scope of the present invention is not limited thereto, and any changes or substitutions that can be easily made by those skilled in the art within the technical scope of the present invention will be covered by the scope of the present invention. The protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (8)
1. A method for verifying the bonding strength of an anti-icing and deicing heating assembly of a blade is characterized in that the anti-icing and deicing heating assembly is installed on the blade of a helicopter and is positioned between a blade body and a clad iron; the method comprises the following steps:
s1: defining a helicopter blade coordinate system and load;
s2: obtaining a load spectrum through calculation or flight test, selecting and determining a blade danger section by using the load spectrum, and performing equivalent processing on the load spectrum to obtain a fatigue equivalent load;
s3: establishing a finite element model for the blade danger section in the step S2, applying a load spectrum to the finite element model, determining a main stress form of the anti-icing heating assembly through stress analysis, calculating the bonding stress of the anti-icing heating assembly in each state of the load spectrum in the step S2 to generate a stress spectrum, and performing equivalent processing on the stress spectrum to obtain fatigue equivalent stress;
s4: according to the main stress form of the anti-icing and deicing heating assembly obtained in the step S3, making a small sample of the anti-icing and deicing heating assembly, and performing sample level test to obtain the allowable static strength value and fatigue limit of the anti-icing and deicing heating assembly, the iron clad and the bonding surface of the blade body;
s5: using the allowable static strength value and the fatigue limit obtained in the step S4, performing static strength and fatigue life evaluation on the stress spectrum obtained in the step S3, and calculating the static strength margin and the fatigue life of the bonding surface of the anti-icing and deicing heating assembly; calculating the static strength margin m.s. according to equation (7):
in the formula [ tau ]]Permissible value of adhesive static strength, tau, of heating element for deicingmaxIs the stress maximum in the stress spectrum of the step S3;
the fatigue life L of the bonding surface of the deicing heating element was calculated using the formula (8)
Wherein R is the hourly rotation speed, t, of the helicopter rotor∞Is the fatigue limit, τ, measured in said step S4eqThe fatigue equivalent stress in the step S3;
s6: manufacturing a test piece; selecting a blade which is not provided with an anti-icing and deicing heating assembly, cutting an airfoil section to transform the airfoil section into a blade airfoil section test piece, adhering the anti-icing and deicing heating assembly and a clad iron to the middle area of the test piece, and connecting two ends of the test piece with two hinged joints respectively for experimental loading;
s7: performing a loading test on the test piece of the step S6; applying bending moment by adopting a 4-point bending test loading method, applying torsional bending moment at one end to complete a fatigue test, recording test load, and obtaining the change relation of the debonding expansion area of the test piece along with the cycle number;
s8: determining the maximum debonding ratio allowed by the debonding of the anti-icing heating assembly and the blade; determining the test cycle number corresponding to the maximum debonding ratio by using the change relation of the test debonding expansion area of the step S7 along with the cycle number; and calculating the inspection and maintenance period of the deicing heating assembly according to the equivalent load obtained in the step S2, the test load recorded in the step S7 and the test cycle number corresponding to the maximum debonding ratio.
2. The method for verifying the adhesion strength of a blade anti-icing heating unit according to claim 1, wherein in step S1, a coordinate system and a load of the helicopter blade are defined, the direction pointing to the tip is defined as an x-axis, the direction pointing to the trailing edge of the blade section is defined as a y-axis, and the z-axis is obtained according to the right-hand rule; the centrifugal force Fc points to the tip of the blade to be positive, the flapping bending moment My causes the upper surface of the blade to be positively pulled, the shimmy bending moment Mz causes the rear edge of the blade to be positively pressed, and the torsional bending moment Mx causes the front edge of the blade to be positively bent.
3. The method for verifying the adhesion strength of a blade deicing heater module according to claim 2, wherein in step S2, F is a characteristic load, and may be one of a flapping bending moment, a shimmy bending moment, and a torque; fsta，iIs the static load of the i-th state, Fdyn，iDynamic load of i-th state, niIs the time proportion of the ith state, m is the total number of states, and
the fatigue equivalent load FeqAccording to the S-N curve (formula 2) of the bonding surface of the deicing heating element
Combining with Miner accumulated damage theory, the fatigue equivalent load calculation formula is the formula (3)
Fea＝(∑ni(Fdyn，i)1/α)α (3)
In the formula SdynIs a dynamic load, S∞Structural fatigue limit, N cycle number, and alpha is an S-N curve parameter.
4. The method for verifying the adhesion strength of the blade anti-icing and deicing heating assembly according to claim 3, wherein in step S3, a full-scale finite element model of the blade with the anti-icing and deicing heating assembly with the iron coating is established, loads of various states of the helicopter blade are applied, the main stress form of the rubber of the anti-icing and deicing heating assembly is analyzed, and the out-of-plane shear static stress τ of the anti-icing and deicing heating assembly in each state is obtainedstaAnd dynamic stress taudynThe stress spectrum (tau) of the bonding surface of the deicing heating element is generated by combining the flight time ratios of the respective statessta.i，τdvn.i，ni) (i 1, 2.. m), stress spectrum dynamic loading and the like using Miner cumulative damage theoryEffective as fatigue equivalent stress taueqThe formula (4) is adopted to make the dynamic load of the stress spectrum equivalent to the fatigue equivalent stress taueq；
τeq＝(∑ni(τdym，i)1/α)α (4)。
5. The method for verifying the bonding strength of the blade deicing heating element as claimed in claim 4, wherein in step S4, the blade deicing heating element is mainly subjected to shearing action during the flight of the helicopter, a 4-plate shearing sample test method is planned, and the static strength [ τ ] of the bonding surface is measured]And fatigue limit τ∞The calculation method is as follows:
the allowable static strength value [ tau ] is the minimum value of all static test results:
[τ]＝min{τb1，τb2，…} (5)
τbithe shear failure stress of the i test piece shear static force test.
Calculating the fatigue limit tau of the single-piece test piece according to the formula (6)∞iThe calculation formula is
τ∞i＝τdyn，i*Nα (6)
Wherein tau isdyn，iFor fatigue test shear stress, N is the number of failure cycles. Calculating the average fatigue limit tau by taking the logarithmic average of the fatigue limits of all test pieces∞。
6. The method for verifying the adhesion strength of the blade deicing heating element according to claim 5, wherein in step S6, the deicing heating element is subjected to a debonding defect preparation during adhesion, and the position, shape and area of the debonding defect are obtained by counting the debonding position, shape and area between the blade and the deicing heating element of the blade produced by the conventional process.
7. The method for verifying the adhesion strength of a blade deicing heater module according to claim 6, wherein in step S7, the bending moment is decomposed into flap and shimmy bending moments by adjusting the inclination angle of the test piece, and the application of torque is realized by synchronously adding a torque loading actuator, and the maximum value of the load spectrum in step S2 is used as the fatigue test load; the debond extension area is determined by tapping the ladle iron.
8. The method for verifying the adhesion strength of a blade deicing heater unit according to claim 7, wherein in step S8, the maximum debonding ratio range allowed by the deicing heater unit and the blade is not more than 10%, and the inspection cycle of the deicing heater unit is determined by finding the number of test cycles Nc corresponding thereto in step S7 in combination with the test load of the debonding extension test: waving test bending moment Mytest, shimmy test bending moment Mztest and torsion test bending moment Mxtest, combining the equivalent load calculated by the load spectrum in the step S2, calculating the corresponding debonding expansion fatigue time of waving, shimmy and torsion bending moments respectively by using a formula (9):
the minimum value of the three is divided by the life dispersion coefficient k to obtain the service inspection period T of the anti-icing heating assembly
The life dispersion factor k ranges between 4 and 6.
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| CN114112352A (en) * | 2021-11-19 | 2022-03-01 | 中国直升机设计研究所 | Fatigue test method for tail-rising buffer strut joint |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080104553A1 (en) * | 2006-10-16 | 2008-05-01 | Mostafa Rassaian | Method and apparatus for integrated hierarchical electronics analysis |
| CN105760623A (en) * | 2016-03-16 | 2016-07-13 | 中国直升机设计研究所 | Method for determining allowable defects of helicopter composite main rotor blade |
| CN107941636A (en) * | 2017-11-08 | 2018-04-20 | 武汉航空仪表有限责任公司 | A kind of fatigue life test system and method for helicopter blade electric heating assembly |
| CN108120592A (en) * | 2017-11-29 | 2018-06-05 | 中国直升机设计研究所 | A kind of test method of helicopter blade static strength |
| CN109733641A (en) * | 2019-01-19 | 2019-05-10 | 北京工业大学 | A kind of aircraft full size structure part multiaxle fatigue experimental method |
| CN110186634A (en) * | 2019-05-23 | 2019-08-30 | 南京航空航天大学 | A kind of hot load fatigue test method of anti-deicing electric heating assembly of helicopter rotor blade |
| CN110789733A (en) * | 2019-10-11 | 2020-02-14 | 中国直升机设计研究所 | Method for evaluating fatigue life of flapping deformation section of tail rotor flexible beam of helicopter |
| CN110884684A (en) * | 2019-12-04 | 2020-03-17 | 中国直升机设计研究所 | Design method for strength test of helicopter after impact of bearingless tail blade |
| CN112485107A (en) * | 2020-10-30 | 2021-03-12 | 中国直升机设计研究所 | Method for verifying crack propagation endurance time of girder of metal blade |
| CN112504589A (en) * | 2020-10-30 | 2021-03-16 | 哈尔滨飞机工业集团有限责任公司 | Helicopter composite material main blade airfoil section static strength test system and method |
-
2021
- 2021-04-20 CN CN202110427337.0A patent/CN113420366B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080104553A1 (en) * | 2006-10-16 | 2008-05-01 | Mostafa Rassaian | Method and apparatus for integrated hierarchical electronics analysis |
| CN105760623A (en) * | 2016-03-16 | 2016-07-13 | 中国直升机设计研究所 | Method for determining allowable defects of helicopter composite main rotor blade |
| CN107941636A (en) * | 2017-11-08 | 2018-04-20 | 武汉航空仪表有限责任公司 | A kind of fatigue life test system and method for helicopter blade electric heating assembly |
| CN108120592A (en) * | 2017-11-29 | 2018-06-05 | 中国直升机设计研究所 | A kind of test method of helicopter blade static strength |
| CN109733641A (en) * | 2019-01-19 | 2019-05-10 | 北京工业大学 | A kind of aircraft full size structure part multiaxle fatigue experimental method |
| CN110186634A (en) * | 2019-05-23 | 2019-08-30 | 南京航空航天大学 | A kind of hot load fatigue test method of anti-deicing electric heating assembly of helicopter rotor blade |
| CN110789733A (en) * | 2019-10-11 | 2020-02-14 | 中国直升机设计研究所 | Method for evaluating fatigue life of flapping deformation section of tail rotor flexible beam of helicopter |
| CN110884684A (en) * | 2019-12-04 | 2020-03-17 | 中国直升机设计研究所 | Design method for strength test of helicopter after impact of bearingless tail blade |
| CN112485107A (en) * | 2020-10-30 | 2021-03-12 | 中国直升机设计研究所 | Method for verifying crack propagation endurance time of girder of metal blade |
| CN112504589A (en) * | 2020-10-30 | 2021-03-16 | 哈尔滨飞机工业集团有限责任公司 | Helicopter composite material main blade airfoil section static strength test system and method |
Non-Patent Citations (3)
| Title |
|---|
| YUNSHIWU 等: "Study on the Vibration Characteristics and Fatigue Life of the Blade Disc System", 《2020 IEEE INTERNATIONAL CONFERENCE ON ARTIFICIAL INTELLIGENCE AND COMPUTER APPLICATIONS (ICAICA)》 * |
| 汪振兴 等: "直升机复合材料开孔对桨叶疲劳寿命的影响", 《中国科技信息》 * |
| 熊旋: "基于扩展有限元的大功率船用螺旋桨疲劳裂纹扩展研究", 《中国优秀博硕士学位论文全文数据库(硕士) 基础科学辑》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114112352A (en) * | 2021-11-19 | 2022-03-01 | 中国直升机设计研究所 | Fatigue test method for tail-rising buffer strut joint |
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