CN109933938A - The design method of interface at a kind of airplane wheel boss bolt aperture - Google Patents
The design method of interface at a kind of airplane wheel boss bolt aperture Download PDFInfo
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- CN109933938A CN109933938A CN201910222444.2A CN201910222444A CN109933938A CN 109933938 A CN109933938 A CN 109933938A CN 201910222444 A CN201910222444 A CN 201910222444A CN 109933938 A CN109933938 A CN 109933938A
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Abstract
The design method of interface at a kind of airplane wheel boss bolt aperture, by the contact area for reducing wheel hub interface at bolt, make to be changed to contactless state by conventional contact condition at boss bolt aperture, the moment of flexure received at wheel hub bolt when tools for bolts ' pretension increases, bending stress increases, so that the stress received at wheel hub interface structural bolts aperture when tools for bolts ' pretension is higher than the stress received at conventional wheel hub interface structural bolts aperture.And the stress under fatigue load effect at conventional wheel hub interface structural bolts aperture is equal to the stress at wheel hub interface structural bolts aperture of the present invention.Compared with the prior art, minimum stress at one fatigue and cyclic lower hub bolt of wheel hub interface that the present invention designs increases, maximum stress at boss bolt aperture remains unchanged, to reduce the Fatigue Stress Amplitude at boss bolt aperture, improves the fatigue life at boss bolt aperture.
Description
Technical field
The present invention relates to airplane wheel design fields, are related to the design of interface at a kind of airplane wheel boss bolt aperture
Method.
Background technique
With the continuous improvement that modern aircraft wheel life requires, opposite opened structure airplane wheel is increasingly used in
The main wheel of domestic military secret and civil aircraft, especially preceding wheel and civil aircraft mostly uses greatly opposite opened structure.By to a variety of both at home and abroad
The statistics at opposite opened wheel hub fatigue fracture position finds most opposite opened structure wheel hub fracture locations mostly in machine
At the bolt for taking turns wheel hub.Currently, the airplane wheel wheel hub interface of the domestic opposite opened structure used connects for two planes,
Two planes are bonded completely, generally use rounding or chamfering in the intersection of interface and bolt, general although structure is simple
The problem of store-through mouthful is easy to appear fatigue cracking at bolt hole.It is non-that, which there are opposite opened structure airplane wheel wheel hub interface in foreign countries,
Plane connects, and fatigue life is relatively high at bolt, but does not disclose the specific design method of the structure.
Summary of the invention
Fatigue fracture, the present invention easily occur at bolt to overcome the shortcomings of wheel hub existing in the prior art
Propose the design method of interface at a kind of airplane wheel boss bolt aperture.
It is cancave cambered surface around interior half wheel hub docking bolt hole, outer half wheel hub is to connecting bolt in the airplane wheel wheel hub
It is also cancave cambered surface around hole；Half wheel hub interface and outer half wheel hub interface structure are full symmetric in described.It is characterized in that, tool
Body process is:
Step 1, stress S when tools for bolts ' pretension at boss bolt aperture is determinedminWith the stress S under fatigue loadmax:
Tools for bolts ' pretension lower hub bolt minimum is calculated to obtain by Finite Element Static Analysis method using Abaqus software
Stress SminWith fatigue load lower hub bolt maximum stress Smax。
Stress S at the determining boss bolt aperture when tools for bolts ' pretensionminWith the stress S under fatigue loadmaxIt is specific
Process is as follows:
I imports the threedimensional model of wheel hub and bolt in Abaqus software；
The three-dimensional model gridding of II wheel hub and bolt divides；
The definition of the material properties of III wheel hub and bolt:
The material properties include the elasticity modulus of materials of wheel hub and the elastic properties of materials mould of Poisson's ratio and bolt
Amount and Poisson's ratio.
Contact surface attribute definition between IV wheel hub and bolt:
The contact surface attribute is the contact type and coefficient of friction, interior half wheel in wheel between half wheel hub and outer half wheel hub
Contact type and coefficient of friction between hub and bolt between contact type and coefficient of friction and outer half wheel hub and bolt.
V model analysis step definition:
The model analysis step includes two steps, and the type of analysis step is static(al) Gneral analysis: wherein the first step is for dividing
Bolt pretightening is analysed, second step is used for the bolt stress analysis under fatigue load.
VI Model load boundary definition:
Constraint is fixed to contact surface between the wheel hub and outer race in analysis step.
The fixed constraint is the six-freedom degree to nodes all in the contact surface between wheel hub and outer race
It is completely fixed, the value of the six degree of freedom of all nodes is 0 in the contact surface.
In the first step, apply bolt axial tension at bolt axis；In second step, wheel hub wheel rim fillet to tire
Apply tire outer expansion force Q, the force direction of tire outer expansion force Q and the axis of undercarriage axis at surface S1 at wheel hub combination diameter
In parallel, and deviate from web.
Apply fatigue load P at the contact surface S2 of 5 ° of lines of wheel rim and tire, the direction of fatigue load P be vertically to
Under.
VII submission model is calculated, and the calculated result that the first step is extracted in Abaqus calculated result obtains boss bolt
Stress S at aperturemin；The calculated result that second step is extracted in Abaqus calculated result obtains answering at boss bolt aperture
Power Smax。
Step 2, the Fatigue Stress Amplitude N at boss bolt aperture is determined；
Step 3, the stress S needed at the boss bolt aperture for meeting life requirements is determined:
The Fatigue Property Curve S-N curve of boss material is obtained by aeronautical material handbook.According to obtained boss material
Fatigue Property Curve S-N curve on corresponding hub fatigue stress amplitude N0, looking for can satisfy airplane wheel service life of rising and falling and wants
The N asked0。
The stress S needed at boss bolt aperture passes through formula S≤Smin+2(N-N0) determine, and with the hub stud holes
Mouthful place stress S as the stress at bolt be design object value.
Step 4, the radius R of the cancave cambered surface and depth capacity H of the cancave cambered surface at half wheel hub interface in determining:
The depth capacity of the cancave cambered surface refer to cancave cambered surface arc bottom vertex C horizontal extension line and interior half wheel hub interface
Docking plane between vertical range.
Optimized by dimensional parameters, determines that the radius R of cancave cambered surface and the maximum of the cancave cambered surface are deep at interior half wheel hub interface
Spend H.
In the determination at half wheel hub interface the depth capacity H of the radius R and cancave cambered surface of cancave cambered surface specific steps
It is as follows:
I establishes the optimization flow of task of wheel assemblies tools for bolts ' pretension finite element analysis in Isight software, if interior half takes turns
The maximum initial depth of cancave cambered surface is Hx at hub interface, initial by the maximum to cancave cambered surface at the interior half wheel hub interface
Depth H x optimizes to obtain the depth capacity H of the cancave cambered surface.If the initial radium of cancave cambered surface is rx at interior half wheel hub interface,
It is recessed at the interior half wheel hub interface by optimizing to obtain to the initial radium rx for setting cancave cambered surface at interior half wheel hub interface
The radius R of cambered surface.
II distinguishes the initial radium rx of cancave cambered surface at the maximum initial depth Hx and interior half wheel hub interface of the setting
It inputs in the Isight software, the initial stress values Sx at bolt is calculated by Isight software.
The stress design target value S at initial stress values Sx and bolt compared.When Sx is less than S, respectively
Increase the initial radium of cancave cambered surface at the maximum initial depth Hx and interior half wheel hub interface of cancave cambered surface at interior half wheel hub interface
rx；When Sx is greater than S, the maximum initial depth Hx and interior half wheel hub interface of cancave cambered surface at interior half wheel hub interface are respectively reduced
Locate the initial radium rx of cancave cambered surface.The amplitude of the increase and reduced amplitude are true according to the default value of the Isight software
It is fixed.
By the sight software to concave arc at the maximum initial depth Hx and interior half wheel hub interface after increasing or reducing
The initial radium rx in face continues to calculate, and obtains the stress value Sx at revised bolt.Amendment will be obtained obtaining again
Stress value Sx at bolt afterwards is compared with the stress design target value S at bolt, and is repaired according to described
Correction method carries out the initial radium rx of cancave cambered surface at the maximum initial depth Hx and interior half wheel hub interface after increasing or reducing
It corrects again.
Repeat above-mentioned comparison -- amendment -- iterative process of calculating, until stress value at obtained bolt and
The error between stress design target value S at bolt is less than 0.05~0.1Mpa.At this point, Hx=H, rx=R.
Step 5 chooses the dimensional parameters progress wheel hub interface structure design after optimization
So far, the design of the airplane wheel wheel hub and its interface of low stress width is completed.
The present invention is made at boss bolt aperture by the contact area of wheel hub interface at reduction bolt by routine
Contact condition is changed to contactless state, and the moment of flexure received when tools for bolts ' pretension at wheel hub bolt increases, and bending stress increases.
In the prior art, wheel hub interface is contact condition, the boss bolt in tools for bolts ' pretension at the bolt
Stress at aperture is as shown in Figure 5.In figure, G is clamped point, and M1 is the bolt moment of flexure suffered in tools for bolts ' pretension, and F is spiral shell
Bolt pre-tightens the axial tension generated, and H1 is length of the clamped point to stress point.
In the present invention, as shown in figure 4, G is clamped point in figure, M2 is the stress in tools for bolts ' pretension at wheel hub bolt
The bolt moment of flexure suffered in tools for bolts ' pretension, H2 are length of the clamped point to stress point.As seen from the figure, Conventional contact
Moment M 1=F × H1 caused by bolt pretightening under state, and it is curved caused by bolt pretightening under technical solution of the present invention
Square M2=F × H2, due to H1 > H2,2 > M1 of moment M caused by bolt pretightening under technical solution of the present invention, so that
The stress received at wheel hub interface structural bolts aperture of the present invention when tools for bolts ' pretension is higher than conventional wheel hub interface structural bolts
The stress received at aperture.And the stress under fatigue load effect at conventional wheel hub interface structural bolts aperture is equal to this hair
Stress at paddle wheel hub interface structural bolts aperture.
Therefore, wheel hub interface structure of the present invention is compared to conventional wheel hub interface structure, a fatigue and cyclic lower hub
Minimum stress (suffered stress when tools for bolts ' pretension) at bolt increases, the maximum stress (fatigue at boss bolt aperture
Suffered stress under load) it remains unchanged, to reduce the Fatigue Stress Amplitude at boss bolt aperture, improve hub stud holes
Fatigue life at mouthful.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of conventional wheel hub interface；
Fig. 2 is the structural schematic diagram of conventional interior half wheel hub；
Fig. 3 is the structural schematic diagram of wheel hub interface proposed by the present invention；
Fig. 4 is half wheel hub interface structural schematic diagram in proposed by the present invention；
Fig. 5 is stress diagram at conventional wheel hub interface structural bolts aperture；
Fig. 6 is stress diagram at wheel hub interface structural bolts aperture of the present invention；
Fig. 7 is Model load boundary definition schematic diagram；
Fig. 8 is dimensional parameters optimization design variable schematic diagram；
Fig. 9 is conventional wheel hub interface structural bolts pre-tight stress cloud atlas；
Figure 10 is that conventional hub fatigue loads act on Stress Map at lower bolt；
Figure 11 is wheel hub interface structural bolts pre-tight stress cloud atlas of the present invention；
Figure 12 is that fatigue load of the present invention acts on Stress Map at lower bolt；
Figure 13 is flow chart of the invention.
In figure: half wheel hub in 1.；2. outer half wheel hub；3. pair connecting bolt.
Specific embodiment
The present embodiment is a kind of airplane wheel wheel hub for aircraft, including interior half wheel hub 1 and outer half wheel hub 2.Institute
Half wheel hub 1 and outer half wheel hub 2 are connected by connection bolt 3 in stating, to bear airplane wheel external load function power.
Half wheel hub is obtained after improving interior half wheel hub in the prior art in described；It is described to the improvement is that, interior half
The interface of wheel hub is integrally in plane, is cancave cambered surface around docking bolt hole.Outer half wheel hub is also in the prior art
Outer half wheel hub improve after obtain；Described to the improvement is that: the interface of outer half wheel hub is integrally in plane, in docking bolt hole
Surrounding is cancave cambered surface.Interior half wheel hub interface and outer half wheel hub interface structure are full symmetric.
Half of cancave cambered surface at the radius of cancave cambered surface in described at half wheel hub interface and the outer half wheel hub interface
Diameter R is 300mm.It is connected between the cancave cambered surface and interior half hub plane by knuckle, the radius r of the knuckle
For 10mm.The horizontal extension line of cancave cambered surface arc bottom vertex C is 0.2mm with the vertical range H docked between plane.
What the present embodiment proposed, which designs a kind of detailed process of low stress width airplane wheel wheel hub interface, is:
Step 1, stress S when determining tools for bolts ' pretension at boss bolt apertureminWith the stress S under fatigue loadmax。
Bolt shown in Fig. 1 is calculated by conventional Finite Element Static Analysis method using Abaqus software in the present embodiment
Pre-tighten lower hub bolt minimum stress SminWith fatigue load lower hub bolt maximum stress Smax.Specific steps are such as
Under:
I imports the threedimensional model of wheel hub and bolt in Abaqus software；
The three-dimensional model gridding of II wheel hub and bolt divides；The grid cell of wheel hub and bolt in the present embodiment
It is hexahedron non-coordinating elements.
The definition of the material properties of III wheel hub and bolt；Wheel hub material is 2A14-T6 aluminium alloy in the present embodiment,
Elasticity modulus of materials 71GPa, Poisson's ratio 0.33.Bolt material is 40CrNiMoA structural steel, elasticity modulus of materials 197GPa, pool
Loose ratio 0.295.
Contact surface attribute definition between IV wheel hub and bolt；
The contact surface attribute is the contact type and coefficient of friction, interior half wheel in wheel between half wheel hub and outer half wheel hub
Contact type and coefficient of friction between hub and bolt between contact type and coefficient of friction and outer half wheel hub and bolt.
In the present embodiment, the contact type of the contact surface in wheel between half wheel hub and outer half wheel hub, interior half wheel hub and spiral shell
The contact type of contact surface between the contact type of contact surface between bolt and outer half wheel hub and bolt is limited sliding
Contact.The coefficient of friction of contact surface is 0.18 between interior half wheel hub and outer half wheel hub；Contact surface between interior half wheel hub and bolt
The coefficient of friction of contact surface is 0.2 between coefficient of friction and outer half wheel hub and bolt.The bolt is for interior half wheel hub and outside
Connection bolt between half wheel hub.
V model analysis step definition；
The model analysis step includes two steps, and the type of analysis step is static(al) Gneral analysis: wherein the first step is for dividing
Bolt pretightening is analysed, second step is used for the bolt stress analysis under fatigue load.
VI Model load boundary definition；In the present embodiment, to the wheel hub and bearing in the first static(al) Gneral analysis step
Constraint is fixed in contact surface between outer ring；To the second static(al) Gneral analysis step in wheel hub and outer race it is indirectly
Constraint is fixed in touching surface；The fixed constraint is carried out completely to the six-freedom degree of nodes all in the contact surface
Fixed, the value of the six degree of freedom of all nodes is 0 in the contact surface
In first static(al) Gneral analysis step, apply bolt axial tension 120kN at bolt axis；General point of second static(al)
In analysis step, apply 1522.67kN tire outer expansion force Q at the surface S1 at the wheel rim fillet to bead seat combination diameter of wheel hub,
The force direction of tire outer expansion force Q is parallel with the axis of undercarriage axis, and deviates from web.
Apply the fatigue load P of 104kN at the contact surface S2 of 5 ° of lines of wheel rim and tire, the direction of fatigue load P is
Straight down.As shown in Figure 5.
VII submission model is calculated, and the calculated result of the first static(al) Gneral analysis step is extracted in Abaqus calculated result
Obtain the stress S at boss bolt aperturemin；The calculating knot of the second static(al) Gneral analysis step is extracted in Abaqus calculated result
Fruit obtains the stress S at boss bolt aperturemax.Stress S in the present embodiment when tools for bolts ' pretension at wheel hub boltmin=
82.067MPa, the stress S under fatigue load at boltmax=357.924MPa, as shown in Figure 7.
Step 2, the Fatigue Stress Amplitude N at boss bolt aperture is determined；Fatigue stress in the present embodiment at bolt
Width N=(Smax-Smin)/2=137.93MPa.
Step 3 determines the stress S needed at wheel hub bolt when meeting the tools for bolts ' pretension of life requirements.
The Fatigue Property Curve S-N curve of boss material 2A14-T6 is obtained by aeronautical material handbook.According to obtained wheel
Corresponding hub fatigue stress amplitude N on the Fatigue Property Curve S-N curve of hub material 2A14-T60, searching can satisfy aircraft
Wheel 4500 rises and falls the N of life requirements0, the hub fatigue stress amplitude N0=123MPa.
It therefore meets stress S≤S at the boss bolt aperture of airplane wheel life requirementsmin+2(N-N0)=82.037
+ 2 × 14.93=111.897Mpa.Meet the stress S at the boss bolt aperture of airplane wheel life requirements as bolt using this
Stress at aperture is design object value.
Step 4 determines the radius R of the cancave cambered surface and depth capacity H of the cancave cambered surface at interior half wheel hub interface.
The depth capacity of the cancave cambered surface refer to cancave cambered surface arc bottom vertex C horizontal extension line and interior half wheel hub interface
Docking plane between vertical range.
The present embodiment uses Isight software, is optimized by conventional dimensional parameters, determines recessed at interior half wheel hub interface
The radius R of the cambered surface and depth capacity H of the cancave cambered surface.Specific step is as follows:
I establishes the optimization flow of task of wheel assemblies tools for bolts ' pretension finite element analysis in Isight software, if interior half takes turns
The maximum initial depth of cancave cambered surface is Hx at hub interface, initial by the maximum to cancave cambered surface at the interior half wheel hub interface
Depth H x optimizes to obtain the depth capacity H of the cancave cambered surface.If the initial radium of cancave cambered surface is rx at interior half wheel hub interface,
It is recessed at the interior half wheel hub interface by optimizing to obtain to the initial radium rx for setting cancave cambered surface at interior half wheel hub interface
The radius R of cambered surface.
II distinguishes the initial radium rx of cancave cambered surface at the maximum initial depth Hx and interior half wheel hub interface of the setting
It inputs in the Isight software, the initial stress values Sx at bolt is calculated by Isight software.The present embodiment
In, the initial stress values Sx=82.037Mpa at the bolt.
The stress design target value S at initial stress values Sx and bolt compared.When Sx is less than S, respectively
Increase the initial radium of cancave cambered surface at the maximum initial depth Hx and interior half wheel hub interface of cancave cambered surface at interior half wheel hub interface
rx；When Sx is greater than S, the maximum initial depth Hx and interior half wheel hub interface of cancave cambered surface at interior half wheel hub interface are respectively reduced
Locate the initial radium rx of cancave cambered surface.The amplitude of the increase and reduced amplitude are true according to the default value of the Isight software
It is fixed.
By the sight software to concave arc at the maximum initial depth Hx and interior half wheel hub interface after increasing or reducing
The initial radium rx in face continues to calculate, and obtains the stress value Sx at revised bolt.Amendment will be obtained obtaining again
Stress value Sx at bolt afterwards is compared with the stress design target value S at bolt, and is repaired according to described
Correction method carries out the initial radium rx of cancave cambered surface at the maximum initial depth Hx and interior half wheel hub interface after increasing or reducing
It corrects again.
Repeat above-mentioned comparison -- amendment -- iterative process of calculating, until stress value at obtained bolt and
The error between stress design target value S at bolt is less than 0.05~0.1Mpa.At this point, Hx=H, rx=R.
The depth capacity H that the interior half wheel hub cancave cambered surface for meeting life requirements is obtained in the present embodiment, after optimization is 0.2mm,
The radius R of cancave cambered surface is 300mm at interior half wheel hub interface.
Step 5 chooses the dimensional parameters progress wheel hub interface structure design after optimization, obtains as shown in Figure 4 interior half
Wheel hub interface structure.The radius R of cancave cambered surface at interior half wheel hub interface is 300mm, the cancave cambered surface and interior half hub plane
Between be connected by knuckle, the radius a of the knuckle is 10mm.The arc bottom of cancave cambered surface at the interior half wheel hub interface
It is 0.2mm that the horizontal extension line of vertex C, which docks the vertical range H between plane with interior half wheel hub,.
So far, the design of the airplane wheel wheel hub and its interface of low stress width is completed.
The aircraft design method through this embodiment, after wheel hub interface structural modification, boss bolt
Aperture is in stress 139.467MPa when tools for bolts ' pretension, the stress 359.191MPa under fatigue load, as shown in figure 8, spiral shell
Fatigue Stress Amplitude 109.86MPa at keyhole mouth.The fatigue life of wheel assemblies is risen and fallen to improve to 6000 or more by 2000 and be risen and fallen,
Show that the airplane wheel wheel hub interface structure can reduce the Fatigue Stress Amplitude at bolt, improves airplane wheel wheel hub and use
Service life.
Claims (3)
1. the design method of interface at a kind of airplane wheel boss bolt aperture, in the airplane wheel wheel hub, interior half is taken turns
It is cancave cambered surface around bolt hole that hub, which docks, is also cancave cambered surface around outer half wheel hub docking bolt hole；Half wheel hub interface in described
It is full symmetric with outer half wheel hub interface structure；It is characterized in that, detailed process is:
Step 1, stress S when tools for bolts ' pretension at boss bolt aperture is determinedminWith the stress S under fatigue loadmax:
Tools for bolts ' pretension lower hub bolt minimum stress is calculated to obtain by Finite Element Static Analysis method using Abaqus software
SminWith fatigue load lower hub bolt maximum stress Smax；
Step 2, the Fatigue Stress Amplitude N at boss bolt aperture is determined；
Step 3, the stress S needed at the boss bolt aperture for meeting life requirements is determined:
The Fatigue Property Curve S-N curve of boss material is obtained by aeronautical material handbook；According to the tired of obtained boss material
Corresponding hub fatigue stress amplitude N on labor performance curve S-N curve0, looking for can satisfy airplane wheel and rises and falls life requirements
N0；
The stress S needed at boss bolt aperture passes through formula S≤Smin+2(N-N0) determine, and with the boss bolt aperture at
Stress S is design object value as the stress at bolt；
Step 4, the radius R of the cancave cambered surface and depth capacity H of the cancave cambered surface at half wheel hub interface in determining:
The depth capacity of the cancave cambered surface refers to the horizontal extension line of cancave cambered surface arc bottom vertex C and pair of interior half wheel hub interface
Connect the vertical range between plane；
Optimized by dimensional parameters, determines the radius R of the cancave cambered surface and depth capacity H of the cancave cambered surface at interior half wheel hub interface；
Step 5, the dimensional parameters after choosing optimization carry out the design of wheel hub interface structure；
So far, the design of the airplane wheel wheel hub and its interface of low stress width is completed.
2. the design method of interface at airplane wheel boss bolt as described in claim 1 aperture, which is characterized in that described true
Stress S at fixed wheel hub bolt when tools for bolts ' pretensionminWith the stress S under fatigue loadmaxDetailed process is as follows:
I imports the threedimensional model of wheel hub and bolt in Abaqus software；
The three-dimensional model gridding of II wheel hub and bolt divides；
The definition of the material properties of III wheel hub and bolt:
The material properties include the elasticity modulus of materials of wheel hub and the elasticity modulus of materials of Poisson's ratio and bolt and
Poisson's ratio；
Contact surface attribute definition between IV wheel hub and bolt:
The contact surface attribute be contact type between half wheel hub and outer half wheel hub and coefficient of friction in wheel, interior half wheel hub with
Contact type and coefficient of friction between bolt between contact type and coefficient of friction and outer half wheel hub and bolt；
V model analysis step definition:
The model analysis step includes two steps, and the type of analysis step is static(al) Gneral analysis: wherein the first step is for analyzing spiral shell
Bolt pretightning force, second step are used for the bolt stress analysis under fatigue load；
VI Model load boundary definition:
Constraint is fixed to contact surface between the wheel hub and outer race in analysis step；
The fixed constraint is carried out to the six-freedom degree of nodes all in the contact surface between wheel hub and outer race
It is completely fixed, the value of the six degree of freedom of all nodes is 0 in the contact surface；
In the first step, apply bolt axial tension at bolt axis；In second step, wheel hub wheel rim fillet to bead seat
In conjunction with tire outer expansion force Q is applied at the surface S1 at diameter, the force direction of tire outer expansion force Q and the axis of undercarriage axis are flat
Row, and deviate from web；
Apply fatigue load P at the contact surface S2 of 5 ° of lines of wheel rim and tire, the direction of fatigue load P is straight down；
VII submission model is calculated, and the calculated result that the first step is extracted in Abaqus calculated result obtains boss bolt aperture
The stress S at placemin；The calculated result that second step is extracted in Abaqus calculated result obtains the stress at boss bolt aperture
Smax。
3. the design method of interface at airplane wheel boss bolt as described in claim 1 aperture, which is characterized in that described true
Specific step is as follows by the depth capacity H of the radius R of cancave cambered surface and the cancave cambered surface at half wheel hub interface in fixed:
I establishes the optimization flow of task of wheel assemblies tools for bolts ' pretension finite element analysis in Isight software, if interior half wheel hub pair
The maximum initial depth of cancave cambered surface is Hx at junction, passes through the maximum initial depth to cancave cambered surface at the interior half wheel hub interface
Hx optimizes to obtain the depth capacity H of the cancave cambered surface；If the initial radium of cancave cambered surface is rx at interior half wheel hub interface, pass through
The initial radium rx for setting cancave cambered surface at interior half wheel hub interface is optimized to obtain cancave cambered surface at the interior half wheel hub interface
Radius R；
II inputs the initial radium rx of cancave cambered surface at the maximum initial depth Hx and interior half wheel hub interface of the setting respectively
In the Isight software, the initial stress values Sx at bolt is calculated by Isight software；
The stress design target value S at initial stress values Sx and bolt compared；When Sx is less than S, increase respectively
At interior half wheel hub interface at the maximum initial depth Hx and interior half wheel hub interface of cancave cambered surface cancave cambered surface initial radium rx；When
When Sx is greater than S, respectively reduce recessed at the maximum initial depth Hx and interior half wheel hub interface of cancave cambered surface at interior half wheel hub interface
The initial radium rx of cambered surface；The amplitude of the increase and reduced amplitude are determined according to the default value of the Isight software；
By the sight software to cancave cambered surface at the maximum initial depth Hx and interior half wheel hub interface after increasing or reducing
Initial radium rx continues to calculate, and obtains the stress value Sx at revised bolt；It will obtain revised again
Stress value Sx at bolt is compared with the stress design target value S at bolt, and according to the amendment side
Method carries out again the initial radium rx of cancave cambered surface at the maximum initial depth Hx and interior half wheel hub interface after increasing or reducing
Amendment；
Above-mentioned comparison -- amendment -- iterative process of calculating is repeated, until stress value and bolt at obtained bolt
The error between stress design target value S at aperture is less than 0.05~0.1Mpa；At this point, Hx=H, rx=R.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113511030A (en) * | 2021-05-27 | 2021-10-19 | 西安航空制动科技有限公司 | Brake wheel hub capable of preventing hub and wheel rim from rotating relatively and design method thereof |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2006256525A (en) * | 2005-03-18 | 2006-09-28 | Topy Ind Ltd | Wheel for dual tire |
| KR20110127009A (en) * | 2010-05-18 | 2011-11-24 | 학교법인 두원학원 | Power transmission apparatus for a compressor |
| CN108750138A (en) * | 2018-05-07 | 2018-11-06 | 西安航空制动科技有限公司 | A kind of wheel hub interface structure |
| CN109002676A (en) * | 2018-10-11 | 2018-12-14 | 安徽合力股份有限公司 | A kind of emulation modelling method of wheel rim |
-
2019
- 2019-03-22 CN CN201910222444.2A patent/CN109933938B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2006256525A (en) * | 2005-03-18 | 2006-09-28 | Topy Ind Ltd | Wheel for dual tire |
| KR20110127009A (en) * | 2010-05-18 | 2011-11-24 | 학교법인 두원학원 | Power transmission apparatus for a compressor |
| CN108750138A (en) * | 2018-05-07 | 2018-11-06 | 西安航空制动科技有限公司 | A kind of wheel hub interface structure |
| CN109002676A (en) * | 2018-10-11 | 2018-12-14 | 安徽合力股份有限公司 | A kind of emulation modelling method of wheel rim |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113511030A (en) * | 2021-05-27 | 2021-10-19 | 西安航空制动科技有限公司 | Brake wheel hub capable of preventing hub and wheel rim from rotating relatively and design method thereof |
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