LECTURE

5

–

Wing

MDOWenbin

SongSchool

of

Aeronautics

and

AstronauticsShanghai

Jiao

Tong

UniversityMultidisciplinary

Aircraft

Design（飛行器設(shè)計(jì)）?

Shanghai

Jiao

Tong

University

–

Dr.

WenbinSong

School

of

Aeronautics

and

Astronautics?

Shanghai

Jiao

Tong

University

–

Dr.

WenbinSong

School

of

Aeronautics

and

AstronauticsOverview

of

the

Course第一章

緒論（2學(xué)時(shí)）

?

第五章

飛機(jī)機(jī)翼的氣動(dòng)結(jié)構(gòu)綜合優(yōu)化第二章飛機(jī)參數(shù)設(shè)計(jì)方法（6學(xué)時(shí)+4學(xué)時(shí)）（4學(xué)時(shí)+4學(xué)時(shí)+2學(xué)時(shí)）一、重量估算二、氣動(dòng)估算三、性能分析第三章建模與仿真（4學(xué)時(shí)+4學(xué)時(shí)）一、幾何建模的數(shù)學(xué)基礎(chǔ)二、飛機(jī)外形的參數(shù)化方法三、氣動(dòng)設(shè)計(jì)的CFD方法第四章優(yōu)化方法（4學(xué)時(shí)+2學(xué)時(shí)）一、經(jīng)典優(yōu)化方法二、現(xiàn)代優(yōu)化方法三、多目標(biāo)優(yōu)化方法一、飛機(jī)機(jī)翼氣動(dòng)優(yōu)化二、飛機(jī)機(jī)翼結(jié)構(gòu)模型三、飛機(jī)機(jī)翼的氣動(dòng)結(jié)構(gòu)綜合優(yōu)化第六章飛機(jī)的環(huán)保指標(biāo)（4學(xué)時(shí)）一、概述二、飛機(jī)機(jī)體噪聲三、飛機(jī)排放第七章面向環(huán)保指標(biāo)的飛機(jī)概念優(yōu)化（0學(xué)時(shí)+4學(xué)時(shí)+2學(xué)時(shí)）一、概述二、面向環(huán)保指標(biāo)的飛機(jī)概念優(yōu)化OverviewWing

MDO發(fā)展現(xiàn)狀及需求主要研究機(jī)翼的設(shè)計(jì)要求機(jī)翼的重量模型機(jī)翼的氣動(dòng)分析機(jī)翼的結(jié)構(gòu)模型機(jī)翼MDO設(shè)計(jì)總結(jié)?

Shanghai

Jiao

Tong

University

–

Dr.

WenbinSong

School

of

Aeronautics

and

Astronautics3Wing

in

nature?

Shanghai

Jiao

Tong

University

–

Dr.

Wenbin

SongSchool

of

Aeronautics

and

AstronauticsSource:

Rolf

Hicker4?

Shanghai

Jiao

Tong

University

–

Dr.

Wenbin

SongSchool

of

Aeronautics

and

AstronauticsSomewings

designed5Spitfire

wing

–

low

wing,straight,

elliptical

planform十B787Solar

planeSource:

InternetSu-47Concord

wing

–

delta

wingwith

ogee

planformThe

wings

of

the

futureSource:http:/

/b2evolution/blog1.php/2014/mercial-aircraft-will-look-like-in-2050?

Shanghai

Jiao

Tong

University

–

Dr.

Wenbin

SongSchool

of

Aeronautics

and

Astronautics6Wing

MDO發(fā)展現(xiàn)狀和特點(diǎn)?

Shanghai

Jiao

Tong

University

–

Dr.

Wenbin

SongSchool

of

Aeronautics

and

Astronautics7隨著單一學(xué)科分析模型和數(shù)據(jù)的精度、復(fù)雜性的提高，因此需要考慮多學(xué)科（Multidisciplinary)多目標(biāo)（Multi-objective)多約束（Multiple

constraints)多層級(jí)（Multi-level）一些主要的特點(diǎn)度提高以及系統(tǒng)變量個(gè)數(shù)從幾個(gè)、十幾個(gè)發(fā)展到上百個(gè)，已有超過(guò)千個(gè)變量的問(wèn)題學(xué)科間的耦合程度強(qiáng)化計(jì)算量大大增加，但同時(shí)HPC的能力也在提升模型復(fù)雜度增加，構(gòu)建模型所需周期增加，同時(shí)需要考慮不確定性因素MDO發(fā)展現(xiàn)狀和特點(diǎn)?

Shanghai

Jiao

Tong

University

–

Dr.

WenbinSong

School

of

Aeronautics

and

Astronautics8MDO

DevelopmentsMultidisciplinaryysis

and

OptimizationStarted

from

decoupled

structural

and

aerodynamic

optimizationBased

on

the

coupling

of

CAE

tools

and

numerical

optimizationMDO

has

been

growing

since

90s

and

coupledysis

is

being

increasingly

adopted

to

tackleNonlinear

interactions

between

disciplinesIncreased

complexities

and

fidelities

of

discipline

modelsMDO

benefited

fromIncreasing

computing

powerFlexible

and

expandable

process

integration

methodMDO發(fā)展現(xiàn)狀和特點(diǎn)?

Shanghai

Jiao

Tong

University

–

Dr.

WenbinSong

School

of

Aeronautics

and

Astronautics9MDO

System

–Airbus

viewM s

an

integrated

process

building

andmanRef:

aero13510?

Shanghai

Jiao

Tong

University

–

Dr.

WenbinSong

School

of

Aeronautics

and

Astronautics?

Shanghai

Jiao

Tong

University

–

Dr.

Wenbin

SongSchool

of

Aeronautics

and

AstronauticsMDO

System –

DLR

viewTechnology

integration

for

the

Virtual

Aircraft11Ref:

aero133MDO–

ONERA

viewRef:aero133?

Shanghai

Jiao

Tong

University

–

Dr.

WenbinSong

School

of

Aeronautics

and

Astronautics12MDO–

QinetiQ

view?

Shanghai

Jiao

Tong

University

–

Dr.

Wenbin

Song13School

of

Aeronautics

and

AstronauticsA

Typical

MDO

Process

(DLR)Elements

in

MDO

process?14School

of

Aeronautics

and

Astronautics?

Shanghai

Jiao

Tong

University

–

Dr.

Wenbin

SongSchool

of

Aeronautics

and

Astronautics15Wing

Design

Process

and

TasksReview

of

the

overall

sizingprocedureWing

sizing

–

part

ofthe

overall

aircraftsizing

processFidelity

of

the

modelsare

one

of

the

keyfactorsSimplified,

calibratedmodels

provide

a

fasttool

for

sizing

andoptimization?

Shanghai

Jiao

Tong

University

–

Dr.

WenbinSong

School

of

Aeronautics

and

Astronautics16Designprocess

and

designtasksHigh

liftconfigurationsSweep

and

dihedral

angleAirfoil

designOther

planform

parametersCFD/windtunnelysisOther

tasks

(engineinstallation)Design

objectives/constraints( CL,CD,

andCM)Wing

area,

number

ofwings,vertical

and

horizontal

of

wingsMeetingrequirementsEnd?

Shanghai

Jiao

Tong

University

–

Dr.

WenbinSong

School

of

Aeronautics

and

AstronauticsSome

typical

design

requirements

for

thewing巡航阻力最小設(shè)計(jì)航程3000nm；巡航速度0.76Ma；最大使用速度0.80Ma；最大飛行高度13000m；巡航高度11000m；機(jī)翼設(shè)計(jì)：CL=0.55設(shè)計(jì)點(diǎn)俯仰力矩Mz≥-0.11；飛行形態(tài)時(shí)的最大升力系數(shù)CLWmax≥1.5(M=0.2),且外翼不能首先出現(xiàn)分離數(shù)Mdd=0.80;滿足常規(guī)抖振邊界要求；阻力發(fā)散油箱容積≥19噸；機(jī)翼后緣厚度=min（0.05%chord

，8mm）?

Shanghai

Jiao

Tong

University

–

Dr.

WenbinSong

School

of

Aeronautics

and

Astronautics18System

level

tradeoffs

in

aircraft

designBréguet

Range

Equation??

=??(??

??)??????????????????+1PropulsionAerodynamicsStructure?

Shanghai

Jiao

Tong

University

–

Dr.

WenbinSong

School

of

Aeronautics

and

Astronautics19Wing

ParametersPlanformAreaConfigurations

(numberof

wings,

vertical

andhorizontal

locations)Aspect

ratioTip

chordRoot

chordMACSpanSweep

angleHigh

lift

devicesAileronAirfoilTwist

angle

(or

washout)Incidence

angleDihedral

angle?

Shanghai

Jiao

Tong

University

–

Dr.

Wenbin

SongSchool

of

Aeronautics

and

Astronautics20Two-Level

FrameworkCollaborative

Optimization

(CO)–

Effectively

the

same

as

BLISS,

a

distributed,

bi-levelposition

of

the

original

problemA

common

definition

of

amultidisciplinaryoptimization

problem

is

given

bymin

f

(s,

l1,

l2

,

a1(s,

l1,

l2

),

a2

(s,

l1,

l2

))s,l1

,l2s.

t

.

g1

(s,

l1,

l2

,

a1(s,

l1,

l2

))

0g2

(s,

l1,

l2

,

a2

(s,

l1,

l2

))

0where,

a1

and

a2

representscoupledysis

models,

as

given

belowa1

A1(s,

l1,

a2

)a2

A2

(s,

l2

,

a1)where,

f

,

g1,

g2

are

systemlevel

objective

andconstraint

functions

including

the

coupledsubsystem

models.?

Shanghai

Jiao

Tong

University

–

Dr.

WenbinSong

School

of

Aeronautics

and

Astronautics21Wing

Weight

Model?

Shanghai

Jiao

Tong

University

–

Dr.

Wenbin

SongSchool

of

Aeronautics

and

Astronautics22Wing

weight

–

empirical

methodsEmpirical

methods

for

weight

estimation

of

aircraftcomponents

have

been

used

in

early

stages

ofaircraft

designTorenbeek

approach式中，WMZF為飛機(jī)零油重量（飛機(jī)起飛重量去除燃油重量），b為飛機(jī)機(jī)翼展長(zhǎng)，Λ1/2為機(jī)翼1/2弦長(zhǎng)后掠角，ηult為飛機(jī)最大載荷因子（飛機(jī)載荷系數(shù)的1.5倍），S為機(jī)翼參考面積，tr為機(jī)翼翼根截面厚度。1?

Shanghai

Jiao

Tong

University

–

Dr.

WenbinSong

School

of

Aeronautics

and

Astronautics232121/

2)0.3cos

WMZF)0.75

[1{6.3cos(ultr

MZF

)0.55

(bS

/

t

W)

/

b}

]

(bW

0.0017W

(cos

12Wing

Weight

–

based

on

structuralprinciplesACSYNT

(AirCraft

SYNThesis)

program

integrates

theweight

calculation

model

PDCYL,

which–

Calcula

oad-bearing

fuselage

and

wing

structural

weight

oftransport

aircraft

based

on

fundamental

structural

principlesSource:

NASA

report

110392?

Shanghai

Jiao

Tong

University

–

Dr.

WenbinSong

School

of

Aeronautics

and

Astronautics24iuA

CAE-based

approachUse

of

CAE

is

now

routine,

more

developments

are

still

requiredWeight

estimationnatural

eTime-consumingFlexibility

is

an

issKBE?

Shanghai

Jiao

Tong

University

–

Dr.

WenbinSong

School

of

Aeronautics

and

Astronautics25Wing

Aerodynamic

Model?

Shanghai

Jiao

Tong

University

–

Dr.

Wenbin

SongSchool

of

Aeronautics

and

Astronautics26Wing

Aerodynamic

ModelsDifferent

models

could

be

used

in

the

designFast,

empirical

modelsNumerical

models

of

various

fidelityLifting

line

theoryPotential

codeEULER

codeRANS

codeLES,

DES,

DNS

code–

Experimental

dataRos ,

J.

and

Lam,

C.T.E.,

Airplane

Aerodynamics

and

PerformanceTorenbeek,

Synthesis

of

Subsonic

Airplane

DesignRaymer,

Aircraft

Design:

A

Conceptual

ApproachWilliams,

Purdue

University

Aircraft

Design

Class

NotesKroo,

Stanford

University

Aircraft

Design

Class

NotesMason,

Virginia

Tech

Aircraft

Design

Class

Notes

EDET Squire

and

Young,

The

Calculation

of

the

Profile

Drag

of

Aerofoils Hoerner,

Fluid

Dynamic

Drag Nicolai,

L.,

Fundamentals

of

Aircraft

DesignThwaites, pressible

AerodynamicsSchlichting,

Boundary

Layer

Theory?

Shanghai

Jiao

Tong

University

–

Dr.

WenbinSong

School

of

Aeronautics

and

Astronautics27Fastestimation

methodsDeciding

the

CLThickness

ratioDrag

divergenceMach

NumberSweep

angleSomeexperience/historical

data

isrequired機(jī)翼的厚度參數(shù)影響飛機(jī)的油箱容積，飛機(jī)的航程決定了飛機(jī)的燃油需求可以使用Korn

方程快速估算機(jī)翼的容積。對(duì)于二維翼型來(lái)說(shuō)，Korn

方程將阻力發(fā)散 數(shù)??????

（阻力發(fā)散 數(shù)存在不同定義，例如可以采用阻力曲線斜率??????/????=0.035,0.05,0.1等值），設(shè)計(jì)升力系數(shù)????????????????

和相對(duì)厚度??/??聯(lián)系起來(lái)，其關(guān)系式為??????

=

??

?0.1

?

????????????????

?

(??/??)

(4.1)式中，??

反映出技術(shù)設(shè)計(jì)水平，與翼型的壓力分布有關(guān)，對(duì)傳統(tǒng)的

NACA6

系列翼型，??=

0.87，對(duì)于先進(jìn)的超臨界翼型，??=

0.95?？紤]經(jīng)典的后掠機(jī)翼理論機(jī)翼平均厚度，阻力發(fā)散 數(shù)，和機(jī)翼升力系數(shù)與后掠角之間的關(guān)系式可以表示為????

????????=

??

?cos(Λ)?????????????????????????

??????????????

cos2(Λ)

?

0.1

?cos(Λ)(4.2)式中，????????????????????????

不應(yīng)超過(guò)0.7，而機(jī)翼的平均厚度(??/??)????????

對(duì)于小展弦比機(jī)翼來(lái)說(shuō)，不應(yīng)該小于

3%，對(duì)大展弦比機(jī)翼則不應(yīng)小于

8%。利用

CFD

的計(jì)算結(jié)果，可以得到更為準(zhǔn)確的關(guān)系式，并且可以引入 的翼型和機(jī)翼的幾何參數(shù)建立翼型和機(jī)翼設(shè)計(jì)數(shù)據(jù)庫(kù)，服務(wù)于更加高效、準(zhǔn)確的設(shè)計(jì)方法，在飛機(jī)方案設(shè)計(jì)中應(yīng)用。?

Shanghai

Jiao

Tong

University

–

Dr.

WenbinSong

School

of

Aeronautics

and

Astronautics28?

Shanghai

Jiao

Tong

University

–

Dr.

WenbinSong

School

of

Aeronautics

and

Astronautics29Lift

requirementsAircraft

lift

requirements全機(jī)的升力系數(shù)需要滿足飛機(jī)巡航需求，而且需要考慮飛機(jī)不同的重量和重心狀態(tài)，對(duì)于長(zhǎng)航程飛機(jī)，從巡航起始和巡航結(jié)束，飛機(jī)重量和重心會(huì)發(fā)生顯著的變化。飛機(jī)的升力系數(shù)可由下式計(jì)算得出????

=

??/??????????

=

??/??????????

(4.1)飛機(jī)翼載??/??和推重比??/??的確定需要考慮對(duì)飛機(jī)性能的不同需求，通過(guò)對(duì)飛機(jī)主要性能參數(shù)的分析得到其設(shè)計(jì)范圍。Lifting

linetheorySimplest

possible

modelFor

subsonic

aircraft,

no

consideration

for–

Viscosity,

compressibility,

sweep,

unsteady

flow?

Shanghai

Jiao

Tong

University

–

Dr.

WenbinSong

School

of

Aeronautics

and

Astronautics30Downwash

and

sectional

flow?

Shanghai

Jiao

Tong

University

–

Dr.

Wenbin

SongSchool

of

Aeronautics

and

Astronautics31Wake

distribution

along

the

spanCirculationat

y

is

(y)Change

in

circulation

over

dy

isd

=

(d/dy)dyStrength

of

trailing

vortex

at

y

=

d

along

lifting

lineConsider

arbitrary

location

y0

along

lifting

lineSegment

dx

will

induce

velocity

at

y0Velocity

dw

at

y0

induced

by

semi-infinite

trailingvortex

at

y

is:?

Shanghai

Jiao

Tong

University

–

Dr.

WenbinSong

School

of

Aeronautics

and

Astronautics32Lift

and

induced

drag

from

lift

line

theory1. Lift

distribution2.

Total

Lift

and

Lift

Coefficient3. Induced

DragL

y0

V

y0

2?

Shanghai

Jiao

Tong

University

–

Dr.

WenbinSong

School

of

Aeronautics

and

Astronautics3322222bL

L

y

dyb2b2L

V

y

dyb2bL

2

y

dybDq

SVS

bCD,i

i

y

i

y

dy

bCL

q

S

V

S?

Shanghai

Jiao

Tong

University

–

Dr.

WenbinSong

School

of

Aeronautics

and

Astronautics34TotaldragestimationA

fast

estimation

method

using

drag

breakdown阻力分為零升阻力、激波阻力以及誘導(dǎo)阻力：????

=

????0

+

??????

+

??????式中，????0、??????

、??????

分別為零升阻力系數(shù)、激波阻力系數(shù)以及誘導(dǎo)阻力系數(shù)。WingprofiledragSome

form

factors

used

for

wing

profile

drag4??????????????,??

=

1+

2

??

+

60????(4.1)Torenbeek

方法中給出類似的形狀因子估算公式??????????????

,??

=

1

+

2.7

??

+

100????4其他估算方法中引入的 的機(jī)翼參數(shù)，例如

Shevell

方法為(4.2)????????????

,??

=

1

+1

?

??2

cos2

Λ1/4

??(2

?

??2)

cos

Λ1/4

??

+

100????4(4.3)Nicolai

和

Raymer

估算方法為????????????,????

=1+(??/??)??????0.6??

+

1004??????[1.34??0.18

(cos

Λ??????)0.28

](4.4)?

Shanghai

Jiao

Tong

University

–

Dr.

WenbinSong

School

of

Aeronautics

and

Astronautics35FuselageprofiledragestimationFuselage

profile

drag

estimationHoerner，Torenbeek

方法分別為(4.1)和(4.2)給出。1.5

7(4.1)????????????

,??

=

1

+

(??/??)1.5

+

(??/??)32.2

3.8????????????

,??

=

1

+

(??/??)1.5

+

(??/??)3(4.2)Jobe，Nicolai和Raymer

采用的方法如(4.3)給出。60????????????

,??

=

1

+

0.0025(??/??)

+

(??/??)3(4.3)Shevell

方法由式(4.4)給出2.8

3.8????????????

,??=

1

++(??/??)1.5

(??/??)3(4.4)?

Shanghai

Jiao

Tong

University

–

Dr.

WenbinSong

School

of

Aeronautics

and

Astronautics36Wavedragestimation誘導(dǎo)阻力計(jì)算公式：??2??????

=

??

(1+??)??????式中，????為機(jī)翼升力系數(shù)，AR為機(jī)翼展弦比，??可根據(jù)升力線理論得到????

=

??2???

Shanghai

Jiao

Tong

University

–

Dr.

WenbinSong

School

of

Aeronautics

and

Astronautics37????12Wing

Structural

Model?

Shanghai

Jiao

Tong

University

–

Dr.

Wenbin

SongSchool

of

Aeronautics

and

Astronautics38Shear,

moment,

torque&Atta ents

loads

of.

.

. main

componentseg.

Pylon,

HTPEnd-loads

of

structural

elementsLocal

pressure

loadsAtta ent

loads

of.

.

.

components

whichdoNOT

influence

a/c

behavioureg.

moveablesaerodynamic

distributioninertia

distributionExternal

and

Internal

Loads?

Shanghai

Jiao

Tong

University

–

Dr.

WenbinSong

School

of

Aeronautics

and

AstronauticsFrom

Conceptual

Design

to

Detailed

DesignEvolution

of

a

Wing

BeamModel？？？Song

School

of

Aeronautics

and

Astronautics?

Shanghai

Jiao

Tong

University

–

Dr.

WenbinSimplebeammodelWing

structure

represented

by

Euler-Bernoulli

beam

theorySmall

displacements

and

rigid

cross-sectionsDeformation

represented

byVertical

displacement

Δ??

of

the

elastic

axis

-

bendingAerodynamic

twist

??

-

defined

along

????

–

different

from

torsion

of

the

wingas

defined

along

?????

Shanghai

Jiao

Tong

University

–

Dr.

WenbinSong

School

of

Aeronautics

and

AstronauticsSource:

x3863

aero41BuildingthewingbeammodelInputsWing

elastic

axis

where

aerodynamic

forces

and

momentsappliedThe

quadratic

moment

of

inertiaYoung

modulus

(??)

and

shear

modulus

(??)

based

on

thestructural

material

(Temperature

dependent)Outputs:DeformationTorsionMethods

to

build

the

modelFrom

geometric

and

material

dataFrom

a

set

of

load

and

deformation

data

using

FE

model?

Shanghai

Jiao

Tong

University

–

Dr.

WenbinSong

School

of

Aeronautics

and

Astronautics42One

intermediate

structural

model?

Shanghai

Jiao

Tong

University

–

Dr.

Wenbin

SongSchool

of

Aeronautics

and

Astronautics43Detailed

CAE

models?

Shanghai

Jiao

Tong

University

–

Dr.

Wenbin

SongSchool

of

Aeronautics

and

AstronauticsSource:

structure_20244WING

MDO?

Shanghai

Jiao

Tong

University

–

Dr.

Wenbin

SongSchool

of

Aeronautics

and

Astronautics45

Wing

area/wing

loading

Twist

distribution

Plan

form

parameters

Aspect

ratio/span

T r

ratio

Sweepback

angle

Winglet

parameters

Airfoil

geometry

at

multiplecontrol

sectionsMajor

Wing

Parameters?

Shanghai

Jiao

Tong

University

–

Dr.

WenbinSong

School

of

Aeronautics

and

Astronautics?levelAreaSpanThicknessMore

detailed

level–

Planform

shr,

sweep,

tipsTAirfoilsTwistMulti-Level

Approach?

Shanghai

Jiao

Tong

University

–

Dr.

WenbinSong

School

of

Aeronautics

and

AstronauticsFlow

Physics

Over

Airfoil

at

Different

Mach?

Shanghai

Jiao

Tong

University

–

Dr.

WenbinSong

School

of

Aeronautics

and

AstronauticsSource:

aero382The

effect

of

camber

on

Cl

is

shownHLDs

already

make

use

of

camber

controlMilitary

jet

use

flexible

skinsEffect

of

Wing

Camber?

Shanghai

Jiao

Tong

University

–

Dr.

WenbinSong

School

of

Aeronautics

and

AstronauticsDecide

number

of

controlsurfaces

and

control

laws(synchronous/asynchronousmovement)Engineering

estimation

onaerodynamic

performanceDefinition

of

design

pointsof

flight

conditionsTypical

Wing

Planform

Configuration?

Shang