CN109885852A - A kind of aircraft auricle parameterization design method - Google Patents
A kind of aircraft auricle parameterization design method Download PDFInfo
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Abstract
The present invention relates to a kind of aircraft auricle parameterization design method, aircraft auricle parameterization design method of the present invention analyzes auricle various features parameter, determines driving parameter and driven parameter；The important parameter in parameter will be driven to be determined as auricle key parameter and auricle parameter factors, build the mathematical model between auricle key parameter and auricle parameter factors, auricle strength character；The geometrical relationship of setting driving initial parameter value, logical over-driving parameter and driven parameter quickly obtains driven parameter value.Determine whether the safety margin in driven parameter meets Intensity Design target, if being unsatisfactory for Intensity Design target, carries out resetting auricle key parameter, iteration optimization, until obtaining the auricle design scheme for meeting Intensity Design.The present invention can quickly obtain the auricle relative dimensions parameter for meeting strength character and use demand, have easy to implement, as a result reliably, greatly shorten the design cycle, reduce design cost, and significant improve auricle design efficiency and quality.
Description
Technical field
The invention belongs to airplane structural design technologies, and in particular to a kind of aircraft auricle fast parameter design method.
Background technique
In aeroplane structure design, there are a large amount of structure types using the connection of auricle connector at the position for transmitting concentrfated load.Than
The rudder face jointing of dorsal fin jointing, elevator that such as fuselage is connect with empennage.Whether the dimensional parameters of auricle are reasonable
Directly determine bearing capacity, weight, manufacturing process and the cost of auricle.
However auricle design at present is mainly designer according to design experiences, carries out repeatedly dimensional parameters adjustment, Cha Feiji
Design manual correlation graph and formula calculate etc., lack the Parameters Optimal Design means of system, and often single parameter is repaired
Change, uncertain influence is brought on other parameters, is difficult to be predicted, therefore coordination optimization difficulty is big between each parameter, design
Period is long, and heavy workload, repetitive operation are more, and the mistake that design cost is higher and design process is not intuitively, in design is not allowed yet
Easily discovery.So urgently needing a kind of efficient, succinct Parameters design.
Summary of the invention
The purpose of the present invention is: propose a kind of efficient, succinct, reliable aircraft auricle parameterization design method.
The technical scheme adopted by the invention is as follows: a kind of aircraft auricle parameterization design method, to auricle various features parameter
It is analyzed, determines driving parameter and driven parameter；Will drive parameter in important parameter be determined as auricle key parameter and
Auricle parameter factors build auricle key parameter and auricle parameter factors, auricle load-carrying efficiency coefficient, between auricle strength character
Mathematical model；The geometrical relationship of setting driving initial parameter value, logical over-driving parameter and driven parameter quickly obtains driven ginseng
Numerical value；Whether meet Intensity Design target according to the safety margin in driven parameter, carries out auricle key parameter iteration optimization, directly
To the auricle design scheme for obtaining meeting strength character.
The aircraft auricle parameterization design method comprising following steps:
Step 1: determining the relevant parameter of design object
Different stage is divided by parameter by design feature to auricle, and then various features parameter is analyzed, is determined
Drive parameter and driven parameter；
Step 2: choose a certain auricle driving parameter as auricle key parameter, other driving parameters as auricle parameter because
Son establishes its relationship between the load-carrying efficiency coefficient of auricle, builds auricle key parameter and auricle parameter factors and auricle
Model between strength character；
Step 3: giving driving initial parameter value, drive the relationship of parameter and driven parameter quickly to obtain with step 2 driven
Parameter.
Step 4: determining whether safety margin meets Intensity Design target, if being unsatisfactory for Intensity Design target, repeat step
3,4, until meeting Intensity Design target.
Step 5: obtaining after meeting the auricle of Intensity Design, by finely tuning auricle key parameter, fast implement auricle design
Further amendment optimization.Keep auricle construction weight lighter.
Step 6: by step 5, determining the auricle size for meeting intensity and construction weight, pass through CATIA software parameter
Design, realization is accurate, quick, reliable to obtain the auricle model of meet demand.
The driving parameter of auricle includes earhole diameter, auricle height at least one.
Relationship between auricle parameter and auricle strength character:
(1) auricle bears axial load
When auricle bears axial load, is destroyed and required according to auricle shearing-extruding, shearing-extruding efficiency of auricle
COEFFICIENT KbrIt is associated with P, obtain auricle key parameter P and Kbr、KtRelational expression:
Kbr=-0.2516P3+0.2796P2+0.9865P+0.0953
Kt=-0.006P4+0.065P3-0.244P2+0.336P+0.845
Wherein, Kbr- shear extrusion efficiency factor；
P-auricle key parameter, P are the important parameter for evaluating auricle design level；
Kt- draw efficiency coefficient；
(2) auricle bears transverse load
When auricle bears transverse load, the horizontal limit load to weight ratio COEFFICIENT K of auricletru, the lateral yield load of auricle
Efficiency factor KtryFor judgement basis, the shape of auricle is must be taken into consideration in ultimate load and yield load, has obtained auricle parameter P
With Ktru、KtryRelational expression；
Ktru=-0.2414P3+0.2696P2+0.9465P+0.0955
Ktry=0.330p3-1.045p2+1.141p+0.102
Wherein, KtruThe efficiency factor of-horizontal limit load；
KtryThe efficiency factor of-transverse direction yield load；
(3) relationship between auricle key parameter and strength character
Iteration auricle key parameter, the safety margin for making to obtain auricle meet auricle strength character design requirement.
Iteration auricle key parameter P and auricle parameter: smallest radial cross-sectional width b, auricle thickness t, auricle width W are cut
Relationship between the ratio s of face:
B=P2*D/(S-0.8)
T=P*D/S
W=(((sqrt (2)/4*`D`*tan (90-` β `))+((0.5*`D`+b) * sin (90-` β `) * tan (90-` β
`)))+(((0.5*`D`+b)*cos(`β`))))*2
Wherein, D-earhole center to Edge Distance, unit mm；β-auricle angle, unit angle；P-auricle key ginseng
Number；S-section ratio, S >=3.3；B-smallest radial cross-sectional width, unit mm；T-auricle thickness, unit mm；W-auricle is wide
Degree, unit mm.
The utility model has the advantages that auricle parametric modeling method of the present invention establish the auricle critical size factor and auricle dimensional parameters,
Relationship between auricle strength character quickly obtains meeting strength character and uses need by the iteration auricle key parameter factor
The auricle relative dimensions parameter asked, have it is easy to implement, as a result reliably, auricle design efficiency and quality can greatly be improved,
It efficiently solves prior art auricle and quickly designs cumbersome, the problem of design cycle length, with great practical application value.
Detailed description of the invention
Fig. 1 is auricle Parametric designing flow diagram of the present invention；
Fig. 2 is auricle scale diagrams.
Specific embodiment
Further illustrate a specific embodiment of the invention with reference to the accompanying drawings of the specification.
Referring to Fig. 2, the method process of aircraft auricle Parametric designing of the present invention is as follows: firstly, to auricle various features
Parameter is analyzed, and determines driving parameter and driven parameter；It is closed secondly, the important parameter in parameter will be driven to be determined as auricle
Bond parameter and auricle parameter factors establish its relationship between the load-carrying efficiency coefficient of auricle, build auricle key parameter and
The mathematical model of auricle parameter factors and auricle strength character；Again, setting driving initial parameter value, lead to over-driving parameter with from
The geometrical relationship of dynamic parameter quickly obtains driven parameter value.Determine whether the safety margin in driven parameter meets Intensity Design mesh
Mark carries out resetting auricle key parameter, iteration optimization, until meeting Intensity Design target if being unsatisfactory for Intensity Design target
Until.Finally, obtaining after meeting the auricle of Intensity Design, auricle key parameter is finely tuned, fast implements the further of auricle design
Amendment optimization, obtains making determining and meets intensity and the lighter auricle design scheme of construction weight.It is set with CATIA software parameter
Meter, realization is accurate, quick, reliable to obtain the auricle model of meet demand.
Example 1:
A monaural piece is designed, as shown in Fig. 2, the center of circle is concentric inside and outside auricle, auricle is with a thickness of uniform thickness.Auricle material is
7050-T7451.Horizontal limit load F suffered by auricle is 15133N.Auricle height H is 30mm.Strength margin value is less than 0.2
And it is greater than 0.
Determine that a monaural piece has reasonable size, for strength margin value less than 0.2 and greater than 0, auricle construction weight is lighter.
And Parametric designing is convenient for passing through CATIA rapid modeling.
Specific embodiment the following steps are included:
Step 1: determining the relevant parameter of design object
Auricle structural characteristic parameter is analyzed, determines driving parameter and driven parameter；
Drive parameter:
H-auricle height, unit mm.
D-auricle bore dia, unit mm.
P-auricle key parameter.P is the important parameter for evaluating auricle design level.
S-S >=3.3 are section ratio.
Ftuy--- auricle material grains horizontal limit tensile strength, unit MPa.
Fty,y--- the stretching yield stress of auricle material grains transversely, unit MPa.
ρ --- density of material, unit g/cm3
Driven parameter:
D-earhole center to Edge Distance, unit mm
β-auricle angle, unit are degree.
B-smallest radial cross-sectional width, unit mm.
T-auricle thickness, unit mm.
W-auricle width, unit mm.
N-auricle width and earhole diameter ratio.
Ktru--- horizontal limit load to weight ratio coefficient.
Abr--- auricle compressive plane projected area, unit mm2。
Aav--- the average value of partial cross-section area.
ktry--- the efficiency factor of transverse load (surrender).ktryIt is about AbrAnd AavParameter.
A1、A2、A3、A4The area in hole radially about section, unit mm2。
V-volume of part, unit m3。
M-pts wt, unit kg.
Step 2: choosing auricle driving parameter H, d, S is the auricle key parameter factor, and P is auricle key parameter, is taken respectively
Build the relationship between auricle key parameter and load-carrying efficiency coefficient and auricle strength character.
(1): auricle drives the relationship between parameter and the auricle key parameter factor:
B=P2*D/(S-0.8)
T=P*D/S
W=(((sqrt (2)/4*`D`*tan (90-` β `))+((0.5*`D`+b) * sin (90-` β `) * tan (90-` β
`)))+(((0.5*`D`+b)*cos(`β`))))*2
Wherein, D-earhole center to Edge Distance, unit mm；β-auricle, unit angle；P-auricle key parameter；
S-section ratio, S >=3.3；B-smallest radial cross-sectional width, unit mm；T-auricle thickness, unit mm；W-auricle width, it is single
Position mm.
(2): the relationship between auricle key parameter P and auricle strength character:
Limit of rupture load p is squeezed when i. determining transverse loadtru:
Ptru=ktru·Ftu,y·Abr
Wherein, Ktru- horizontal limit load to weight ratio coefficient
Ktru=-0.2414P3+0.2696P2+0.9465P+0.0955
Ftuy- auricle material grains horizontal limit tensile strength.
Abr- auricle compressive plane projected area
Abr=DT.
Ii. yield load P allowable when transverse load is determinedy:
Py=ktry·Fty,y·Abr
Wherein:
Py--- the yield load allowable of auricle；
Abr--- compressive plane projected area；
Fty,y--- the stretching yield stress of auricle material grains transversely；
ktry--- the efficiency factor of transverse load (surrender).ktryIt is about AbrAnd AavParameter.
Ktry=0.330p3-1.045p2+1.141p+0.102
Iii. auricle ground safety margin under action of lateral load:
M.S --- it is safety margin
Pcr——min(Ptru, Py), it takes and squeezes limit of rupture load ptruWith yield load P allowableyMinimum in the two
Value.
Step 3: giving driving parameter (auricle key parameter, auricle parameter factors) initial value, drive parameter with step 2
Driven parameter is quickly obtained with the relationship of driven parameter.
Drive parameter:
Auricle key parameter initial value: P=1.165
Auricle parameter factors initial value: H=30mm, d=15mm, S=3.3
Ftuy=423Mpa
Fty,y=327Mpa
ρ=2.8 × 10-9g/cm3。
Driven parameter:
D=30mm, β=65 °, b=22.5mm, t=3mm, W=60.5mm, n=4, Ktru=1.15, Abr=90mm2、Aav
=121mm2、ktry=0.534, A1=137mm2、A2=105mm2、A3=92.3mm2、A4=137mm2, V=3.97, ρ=2.8,
M=1.2kg, MS=1.87.
Step 4: determining whether safety margin meets Intensity Design target, if being unsatisfactory for Intensity Design target, repeat step
3,4, until meeting Intensity Design target.
MS=1.87 < 2 meet Intensity Design target.
Step 5: obtaining after meeting the auricle of Intensity Design, by finely tuning auricle key parameter, fast implement auricle design
Further amendment optimization.Keep auricle construction weight lighter.
Iteration 1: as p=1.2, MS=1.87 < 2 meet Intensity Design target.Weight M is 1.2kg at this time.
Iteration 2: as p=0.88, MS=0.13 < 2 meet Intensity Design target.Weight M is 0.59kg at this time.
Iteration 3: as p=1.1, MS=0.97 < 2 meet Intensity Design target.Weight M is 1.1kg at this time.
Iteration 4: as p=0.87, MS=0.05 < 2 meet Intensity Design target.Weight M is 0.67kg at this time.
Iteration 5: as p=0.95, MS=0.43 < 2 meet Intensity Design target.Weight M is 0.76kg at this time.
Step 6: by step 5, determining the auricle size for meeting intensity and construction weight, pass through CATIA software parameter
Design, realization is accurate, quick, reliable to obtain the auricle model of meet demand.
I. determine that p is 0.88, weight M is 0.59kg at this time, relatively small.
Ii. auricle relative dimensions H=30, d=15, D=30mm, β=76 °, b=15mm, t=3mm, W=63mm.
Iii. auricle size is designed by CATIA software parameterization, obtains the auricle model of meet demand.
In conclusion the method for aircraft auricle Parametric designing of the present invention can by the optimization design of auricle key parameter
To realize that auricle quickly designs, it can satisfy the needs of engineering design, while the auricle design cycle can be shortened, improve effect
Rate reduces production cost, the accuracy and reliability of auricle model has been effectively ensured, and provides for the design of aircraft auricle strong
Tool.
Claims (5)
1. a kind of aircraft auricle parameterization design method, it is characterised in that: analyze auricle various features parameter, determine
Drive parameter and driven parameter；The important parameter in parameter will be driven to be determined as auricle key parameter and auricle parameter factors, taken
Build auricle key parameter and auricle parameter factors, auricle load-carrying efficiency coefficient, the mathematical model between auricle strength character；Setting
Initial parameter value is driven, logical over-driving parameter and the geometrical relationship of driven parameter quickly obtain driven parameter value；According to driven ginseng
Whether the safety margin in number meets Intensity Design target, carries out auricle key parameter iteration optimization, until meeting auricle intensity
Design performance.
2. aircraft auricle parameterization design method according to claim 1, characterized by the following steps:
Step 1: determining the relevant parameter of design object
Different stage is divided by parameter by design feature to auricle first, and then various features parameter is analyzed, is determined
Drive parameter and driven parameter；
Step 2: choose a certain auricle driving parameter as auricle key parameter, other driving parameters as auricle parameter factors,
Its relationship between the load-carrying efficiency coefficient of auricle is established, auricle key parameter and auricle parameter factors and auricle intensity are built
Relationship between performance；
Step 3: giving driving initial parameter value, quickly obtain driven parameter with the relationship of step 2 driving parameter and driven parameter；
Step 4: determine whether safety margin meets Intensity Design target, if being unsatisfactory for Intensity Design target, repeats step 3,4,
Until meeting Intensity Design target；
Step 5: obtain after meeting the auricle of Intensity Design, by finely tune auricle key parameter, fast implement auricle design into
The amendment optimization of one step, obtains the most light scheme of auricle construction weight；
Step 6: by step 5, determining the auricle parameter for meeting intensity and construction weight, then meet demand is obtained by emulation
Auricle threedimensional model.
3. aircraft auricle parameterization design method according to claim 2, it is characterised in that: the driving parameter of auricle includes
Earhole diameter, auricle height at least one.
4. aircraft auricle parameterization design method according to claim 3, it is characterised in that: auricle parameter and auricle intensity
Relationship between performance:
(1) auricle bears axial load
When auricle bears axial load, is destroyed and required according to auricle shearing-extruding, shearing-extruding efficiency coefficient of auricle
KbrIt is associated with P, obtain auricle key parameter P and Kbr、KtRelational expression:
Kbr=-0.2516P3+0.2796P2+0.9865P+0.0953
Kt=-0.006P4+0.065P3-0.244P2+0.336P+0.845
Wherein, Kbr- shear extrusion efficiency factor；
P-auricle key parameter, P are the important parameter for evaluating auricle design level；
Kt- draw efficiency coefficient；
(2) auricle bears transverse load
When auricle bears transverse load, the horizontal limit load to weight ratio COEFFICIENT K of auricletru, the lateral yield load efficiency of auricle
COEFFICIENT KtryFor judgement basis, the shape of auricle is must be taken into consideration in ultimate load and yield load, obtained auricle parameter P with
Ktru、KtryRelational expression；
Ktru=-0.2414P3+0.2696P2+0.9465P+0.0955
Ktry=0.330p3-1.045p2+1.141p+0.102
Wherein, KtruThe efficiency factor of-horizontal limit load；
KtryThe efficiency factor of-transverse direction yield load；
(3) relationship between auricle key parameter and strength character
Iteration auricle key parameter, the safety margin for making to obtain auricle meet auricle strength character design requirement.
5. aircraft auricle parameterization design method according to claim 3, it is characterised in that: iteration auricle key parameter P
With auricle parameter: smallest radial cross-sectional width b, auricle thickness t, relationship between auricle width W, section ratio s:
B=P2*D/(S-0.8)
T=P*D/S
W=(((sqrt (2)/4*`D`*tan (90-` β `))+((0.5*`D`+b) * sin (90-` β `) * tan (90-` β `)))+
(((0.5*`D`+b)*cos(`β`))))*2
Wherein, D-earhole center to Edge Distance, unit mm；β-auricle angle, unit angle；P-auricle key parameter；
S-section ratio, S >=3.3；B-smallest radial cross-sectional width, unit mm；T-auricle thickness, unit mm；W-auricle width, it is single
Position mm.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112052530A (en) * | 2020-09-25 | 2020-12-08 | 中国直升机设计研究所 | Design method for foldable oblique beam butt joint of helicopter |
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2018
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