aluminum in aerospace and automobile parts in aerospace...aa2013 alloy developed by uacj 4．...

©2016 UACJ Corporation. All rights reserved.

9th/ Aug./ 2017

TADASHI MINODA

Research & Development Division

UACJ Corporation

Aluminum in Aerospace and Automobile Parts


Co

nte

nts

１．Introduction of UACJ Group

２．Variety of Wrought Aluminum Alloys

３．Variety and Features of Aluminum Alloys for Aircrafts

・Development of Aluminum Alloys for Aircrafts

・Applications of Aluminum Alloys

・Future development of aircraft materials

・AA2013 alloy developed by UACJ

４．Applications for Automotive Parts

・Heat Exchangers (Laying pipe, Hose joints, MFC)

・Automotive panel materials

・Bumper

・Truck tilt

・Forgings

・Compressor Wheel for Turbo Charger

５．Summary

1


Intr

od

uc

tio

n o

f U

AC

J G

rou

p

UACJ Corporation

Fu

ruk

aw

a-S

ky

Alu

min

um

Co

rp.

Su

mit

om

o L

igh

t M

eta

l

Merged on1st/ Oct./ 2013

2


Fla

t R

olle

d P

rod

uc

ts (

Sh

ee

ts a

nd

Co

ils

) B

us

ine

ss

3


Ex

tru

sio

n a

nd

Fo

il B

us

ine

ss

es

4


Th

e o

the

r B

us

ine

ss

es

5


Re

se

arc

h &

De

ve

lop

me

nt

6


Fla

tFla

tFla

tFla

t- ---ro

lled a

lum

inum

(sh

eets

and c

oils

) ro

lled a

lum

inum

(sh

eets

and c

oils

) ro

lled a

lum

inum

(sh

eets

and c

oils

) ro

lled a

lum

inum

(sh

eets

and c

oils

) pro

duction c

apac

ity

ranki

ngs

pro

duction c

apac

ity

ranki

ngs

pro

duction c

apac

ity

ranki

ngs

pro

duction c

apac

ity

ranki

ngs

(ki

lo-to

ns/

yr)

•U

AC

J m

ee

ts t

he

ne

ed

s o

f a

va

rie

ty o

f in

du

str

ies

th

an

ks

to its

co

mp

reh

en

siv

e a

bilit

ies

.

•U

AC

J is

a W

orl

d C

las

s M

an

ufa

ctu

rer

of

Fla

t R

olle

d

Pro

du

cts

.

Ou

r S

tre

ng

ths

7


Glo

ba

l N

etw

ork

of

UA

CJ

(S

he

et)

8

Japan –3 locations

•Nagoya

•Fukaya

•Fu

ku

i (A

ero

sp

ace m

ate

ria

l)

Japan –3 locations

•Nagoya

•Fukaya

•Fu

ku

i (A

ero

sp

ace m

ate

ria

l)

Thailand

•Rayong

Thailand

•Rayong


Japan

World

Head Office

Chubu Branch

Kansai Branch

Oya

ma

Co

rpo

rati

on

Gu

nm

a C

orp

ora

tio

n

Na

go

ya

Co

rpo

rati

on

Na

go

ya

W

ork

s

An

joW

ork

s

Sh

iga

Co

rpo

rati

on

Glo

ba

l N

etw

ork

of

UA

CJ

Ex

tru

sio

n G

rou

p

Pro

du

cin

g a

ero

sp

ace m

ate

ria

l

9


10

①China

③Thailand

②IndonesiaMPE , Pipe, Bar, &Shape

MPE , Pipe, Bar, &Shape

MPE , Pipe, Bar, &Shape

UA

CJ

Ex

tru

sio

n G

rou

p in

As

ia

10


Ro

jan

aIn

du

str

ial P

ark

Ay

utt

ha

ya

Pla

nt

70

km

fro

m B

an

gk

ok

Rayong

304 Industrial Park

Pra

ch

inb

uri

Pla

nt

14

0 k

m f

rom

Ba

ng

ko

k

Lo

ca

tio

n o

f U

AC

J E

xtr

us

ion

(T

ha

ila

nd

)

11


Co

nte

nts











・Bumper

・Truck tilt

・Forgings


５．Summary

13


Aluminum alloys are classified into 7 series.

�1xxx : Pure aluminum (include Fe, Siimpurities)

�2xxx : Al＋Cu（＋Mg）

・・・Duralumin (A2017)

�3xxx

：Al＋Mn

�4xxx

：Al＋Si

�5xxx ：Al＋Mg

�6xxx

：Al＋Mg＋Si

�7xxx

：Al＋Zn＋Mg（＋Cu）

・・・Extra Super Duralumin

�8xxx ：Other elements (Ex. Fe)

Va

rie

ty o

f A

lum

inu

m A

llo

ys

(A7075)

14


Va

rie

ty o

f A

lum

inu

m A

llo

ys

Fig. Tensile strength ranges of aluminum alloys.

0

100

200

300

400

500

600

700

800

Ultimate Tensile Strength, σB/ MPa

1xxx

2xxx

3xxx

4xxx

5xxx

6xxx

7xxx

Strain hardening alloys

Age hardening alloys

Middle strength

Hig

he

r c

orr

osio

n r

esis

tan

ce

=> Automobile structure

Hig

h s

tre

ng

th

Lower corrosion resistance

=> Aircraft structure

15


DC

DB

DC

C7000

(Cu≧0.5%)

B-D

AD

BC

BB

7000

(Cu≦0.3%)

-A

B-C

C-D

A-B

A-B

A5000

-B

D-

-B

C4000

CB-D

DB

CC

D2000

DA-

Forging

A

A-BA

Brazing

CA-BA

Form-

ability

A-BAA

Corro-

sion

AC

A6000

AD

A3000

AD

A1000

Welding

(Argon)

Cutting

SCC

Alloy

Va

rie

ty o

f A

lum

inu

m A

llo

ys

General properties of aluminum alloys

A; Good �

D; Worse

16


Co

nte

nts











・Bumper

・Truck tilt

・Forgings


５．Summary

18


Hardness

Aging time (h)

Hardness

After 4 days

As quenched

Quenching temperature (

˚C)

Age hardening of Al-3.5Cu-0.5Mg alloy. (Wilm)

1906: Development of

“D

ura

lum

in”by Wilm

(Germany)

・Quench test of Al-3.5Cu-0.5Mg. (2xxx alloy)

An assistant measured the hardness on Saturday.

The hardness was measured again on Monday.

=> Development of age hardening.

・The patent was transferred to DurenerMetallwekeA.G.

“Duralumin”was a contraction of Durenerand Aluminium.

-1930:

“S

up

er-

Du

ralu

min

, S

D”

・ALCOA Al-Cu-High Mg (2xxx alloy)

1936:

“E

xtr

a-S

up

er-

Du

ralu

min

, E

SD

”

・Requirement of new alloy with 600MPa strength.

=>

De

ve

lop

me

nt

of

Al-

Zn

-Mg

-Cu

all

oy b

y D

r. I

ga

ras

hi

an

d M

r. K

ita

hara

in J

ap

an

. (7xxx alloy)

(Improvement of SCC by Cr and Mnaddition)

・1938Application for Zero-fighter

・1943Registration of similar alloy as 7075 (USA)

Th

e e

arl

iest

ag

e h

ard

en

ing

cu

rve

wh

ich

wa

s p

ub

lish

ed

by

Wilm

De

ve

lop

me

nt

of

Alu

min

um

All

oy

s f

or

Air

cra

fts

19

A. Wilm


“E

SD

”was developed in Japan, and it was applied to spars

in Main wing in the Zero-fighter.

Ap

plic

ati

on

of

“E

SD

”fo

r Z

ero

-fig

hte

r

De

ve

lop

me

nt

of

Alu

min

um

All

oy

s f

or

Air

cra

fts

20


Map

of

de

velo

pm

en

t a

nd

im

pro

vem

en

t

of

hig

h s

tre

ng

th a

lum

inu

m a

llo

ys

Map

of

de

velo

pm

en

t a

nd

im

pro

vem

en

t

of

hig

h s

tre

ng

th a

lum

inu

m a

llo

ys

2014

2014

2014

2014

2017

2017

2017

2017

Du

ralu

min

Du

ralu

min

Du

ralu

min

Du

ralu

min

7075

7075

7075

7075

　Extr

a S

upe

r D

ura

lum

in　

Extr

a S

upe

r D

ura

lum

in　

Extr

a S

upe

r D

ura

lum

in　

Extr

a S

upe

r D

ura

lum

in

　　

　　

　　

Al-

5.6

Zn-2.5

Mg-

1.6

Cu-0.2

Cr

Cu+，

Mｇ

x2024

2024

2024

2024

Su

per

Du

ralu

min

Su

per

Du

ralu

min

Su

per

Du

ralu

min

Su

per

Du

ralu

min

7175

7175

7175

7175

Fe,S

i -

Zn+　

Str

engt

h

Weld

abili

ty7475

7475

7475

7475

Hig

h t

ough

ness

Fe,S

i-　

Tough

ness

Fe,S

i -

2124

2124

2124

2124

Fe,S

i -

Zn,C

u+，

Zr+

Hig

h t

ough

ness

2224

2224

2224

2224

Hig

h t

ough

ness

Str

engt

h, to

ugh

ness

Mg+

2324

2324

2324

2324

Fe,S

i -

Fe,S

i -　

Hig

h s

trengt

h2524

2524

2524

2524

Hig

h s

trengt

hH

igh t

ough

ness

Ni+

Zn+, M

g-Zn+

Heat

resi

stan

ce

Hig

h s

trengt

hH

ighest

str

engt

h

Al-

4C

uA

l-4C

uA

l-4C

uA

l-4C

u

2419

2419

2419

2419

Al-

4.4

Cu-0.5

Mg-

0.8

Si

Al-

4C

u-0.5

Mg

Al-

4C

u-1.5

Mg

2219

2219

2219

2219

2519

2519

2519

2519

2618

2618

2618

2618

7049

7049

7049

7049

7149

7149

7149

7149

7050

7050

7050

7050

7150

7150

7150

7150

7085

7085

7085

7085

7055

7055

7055

7055

De

ve

lop

me

nt

of

Alu

min

um

All

oy

s f

or

Air

cra

fts

+ ; Increased

-; Decreased

2xxx alloys have higher

fati

gu

e s

tre

ng

th

7xxx alloys have higher

sta

tic s

tre

ng

th

21


Dir

ecti

on

of

new

all

oy d

evelo

pm

en

t

De

ve

lop

me

nt

of

Alu

min

um

All

oy

s f

or

Air

cra

fts

22

7351


Co

mp

ari

so

n o

f p

rop

ert

ies o

f ty

pic

al a

lum

inu

m a

llo

ys f

or

air

cra

fts

Co

mp

ari

so

n o

f p

rop

ert

ies o

f ty

pic

al a

lum

inu

m a

llo

ys f

or

air

cra

fts

Thin

Thic

k

T3, T351, T4

DD

AA

D

T81, T851

CC

DC

B

2124

T851

―C

CC

B

2324

T39

―B

AA

D

T6, T651

AB

DC

D

T76, T7651

BC

CC

C

T73, T7351

CD

BB

A

7175

T74

AB

BB

B

T61, T651

AB

AA

D

T761

B―

AA

C

T7351

CC

AA

AA

T76, T7651

AA

BB

C

T7451

―A

BB

B

T6151

AAA

CC

D

T7751

―AA

CC

C

7055

T7751

―AA

CC

C-D

Bett

er

: AA＞

A＞

Ｂ＞

Ｃ＞

Ｄ : W

ors

e

7150

2024

7075

7475

7050

SC

CSta

tic s

trengt

hAllo

yFra

ctu

reto

ugh

ness

Cra

ck

propa

gati

on

Tem

per

De

ve

lop

me

nt

of

Alu

min

um

All

oy

s f

or

Air

cra

fts

23


De

ve

lop

me

nt

of

Alu

min

um

All

oy

s f

or

Air

cra

fts

Registration flow of new alloys for aerospace

①Registration in AA (Aluminum Association)

・Alloy Number

・Heat Treatment (Temper)

②Publication of AMS (Aerospace Material Standards)

・Alloy specifications (Tensile properties, Corrosion resistance, etc.)

③Registration of material properties into MMPDS(Metallic Materials Properties

Development & Standardization)

・Physical properties

・Static strength

・High temperature strength

・Fatigue crack propagation

・Fracture toughness

The materials which are used for aerospace structure need above registrations.

24


Body structure

Ap

plic

ati

on

s o

f A

lum

inu

m A

llo

ys

25


2024

2024

2024

2024

Ap

plic

ati

on

s o

f A

lum

inu

m A

llo

ys

Boein

g 747

Boein

g 747

Boein

g 747

Boein

g 747 (

Rela

tive

ly o

ld p

lane)

Boein

g 747

Boein

g 747

Boein

g 747

Boein

g 747 (

Rela

tive

ly o

ld p

lane)

Main

win

g

Up

per

pla

te (

7075-T

651)

Lo

wer

pla

te (

2024-T

351)

Vert

ical

sta

bil

izer

(7075-T

65

1)

Str

ing

er

(7075-T

65

1)

Main

fra

me

(7075-T

73)

Fra

me

(7075-T

73)

Ou

ter

pan

el

(2024-T

35

1) Co

wli

ng

(2024-T

42)

Ma

in w

ing

sp

ar

(7075-T

65

1)

26


Allo

yTem

per

Pro

duct

Form

Thic

kness

(in

ch)

Fty

(M

Pa)

Ftu

(M

Pa)

7075

T6

Sheet

0.1

26～

0.2

49

47

653

8　

T7

6Sheet

0.0

63～

0.2

49

42

750

3　

T7

351

Pla

te0

.250～

1.0

00

39

347

67475

T6

51

Pla

te0

.500～

1.5

00

46

953

8　

T7

61/T76

51

Sheet　

/　

Pla

te0

.040～

0.4

99

41

449

0　

T7

351

Pla

te0

.250～

1.5

00

41

449

07050

T7

6511

Extr

usi

on

0.5

00～

1.0

00

46

253

1　

T7

451

Pla

te0

.250～

2.0

00

44

151

0　

T7

3511

Extr

usi

on

≦1.0

00

39

346

97010

T7

651

Pla

te0

.250～

2.0

00

45

552

4　

T7

451

Pla

te0

.250～

2.0

00

42

749

67150

T7

7511

Extr

usi

on

0.5

00～

0.7

49

54

557

2T7

751

Pla

te0

.500～

0.7

49

53

157

2

Ap

plic

ati

on

s o

f A

lum

inu

m A

llo

ys

Boein

g 777

Boein

g 777

Boein

g 777

Boein

g 777 (

Rela

tive

ly n

ew

pla

ne)

Boein

g 777

Boein

g 777

Boein

g 777

Boein

g 777 (

Rela

tive

ly n

ew

pla

ne)

27


Alu

min

um

allo

ys f

or

air

cra

fts

Alu

min

um

allo

ys f

or

air

cra

fts

Shap

eY

S-1

1Y

S-1

1Y

S-1

1Y

S-1

1B

727

B7

27

B7

27

B7

27

B7

47

B7

47

B7

47

B7

47

B7

77

B7

77

B7

77

B7

77

Upp

er

Pla

te7075-T

67178-T

651

7075-T

651

7055-T

7751

Low

er

Pla

te2024-T

32024-T

351

2024-T

351

2324-T

39

Spa

rExt

ru.

2024-T

32024-T

351

7075-T

651

7055-T

7751

Oute

rPla

te2024-T

32024-T

351

2024-T

351

2524-T

3

Fra

me

Pla

te7075-T

6 7

075-T

6 7

075-T6

7150-T

7751

Forg

.2014-T

6 7

079-T

6 7

075-T73

7050-T

74

Forg

ings

Airpl

ane

Body

Mai

nw

ing

Mai

n w

ing:

Upper

Mai

n w

ing:

Upper

Mai

n w

ing:

Upper

Mai

n w

ing:

Upper

– –––C

om

pre

ssio

n s

tress

[Sta

tic s

trengt

h]

=> 7

xxx

allo

ysC

om

pre

ssio

n s

tress

[Sta

tic s

trengt

h]

=> 7

xxx

allo

ysC

om

pre

ssio

n s

tress

[Sta

tic s

trengt

h]

=> 7

xxx

allo

ysC

om

pre

ssio

n s

tress

[Sta

tic s

trengt

h]

=> 7

xxx

allo

ys

（（（（C

laddin

g of

Al

Cla

ddin

g of

Al

Cla

ddin

g of

Al

Cla

ddin

g of

Al- ---

1%Zn a

lloy;

Resi

sta

nt

to c

orr

osi

on)

1%Zn a

lloy;

Resi

sta

nt

to c

orr

osi

on)

1%Zn a

lloy;

Resi

sta

nt

to c

orr

osi

on)

1%Zn a

lloy;

Resi

sta

nt

to c

orr

osi

on)

Low

er

Low

er

Low

er

Low

er

– –––T

ensi

on s

tress

[Fat

igue s

trength

] => M

ainly

2xx

x al

loys

Tensi

on s

tress

[Fat

igue s

trength

] => M

ainly

2xx

x al

loys

Tensi

on s

tress

[Fat

igue s

trength

] => M

ainly

2xx

x al

loys

Tensi

on s

tress

[Fat

igue s

trength

] => M

ainly

2xx

x al

loys

(Cla

ddin

g of

pure

alu

min

um

; R

esi

stan

t to

corr

osi

on)

(Cla

ddin

g of

pure

alu

min

um

; R

esi

stan

t to

corr

osi

on)

(Cla

ddin

g of

pure

alu

min

um

; R

esi

stan

t to

corr

osi

on)

(Cla

ddin

g of

pure

alu

min

um

; R

esi

stan

t to

corr

osi

on)

Body:

Oute

r pla

te

Body:

Oute

r pla

te

Body:

Oute

r pla

te

Body:

Oute

r pla

te – –––

Tensi

on s

tress

[Fatigu

e s

trengt

h]

=> M

ainly

2xx

x al

loys

Tensi

on s

tress

[Fatigu

e s

trengt

h]

=> M

ainly

2xx

x al

loys

Tensi

on s

tress

[Fatigu

e s

trengt

h]

=> M

ainly

2xx

x al

loys

Tensi

on s

tress

[Fatigu

e s

trengt

h]

=> M

ainly

2xx

x al

loys

(Sam

e a

s ab

ove

)(S

ame a

s ab

ove

)(S

ame a

s ab

ove

)(S

ame a

s ab

ove

)

Fra

me, Str

inge

r Fra

me, Str

inge

r Fra

me, Str

inge

r Fra

me, Str

inge

r – –––

[Sta

tic s

trength

] => 7

xxx

allo

ys[S

tatic s

trength

] => 7

xxx

allo

ys[S

tatic s

trength

] => 7

xxx

allo

ys[S

tatic s

trength

] => 7

xxx

allo

ys

Ap

plic

ati

on

s o

f A

lum

inu

m A

llo

ys

28


Bo

dy p

an

el, W

ing

pa

nel

Milli

ng

of

bo

dy s

kin

Body panel

Wing panel

Maximum 7 steps

Tier strap

Max. 7.2m

Max.

2.3m

Thickness before milling : 5.1mm

Fig. Example of body skin miling

Shear tie

Skin

Stringer

Frame

Stringer clip

Ap

plic

ati

on

s o

f A

lum

inu

m A

llo

ys

29


Ap

plic

ati

on

s o

f A

lum

inu

m A

llo

ys

Seat frame

Galley and container

Cargo container

Secondary structures and others

30


Th

e m

ax.

takeo

ff w

eig

ht;

400 t

on

s

Co

mp

osit

eC

om

po

sit

e

Th

e c

om

po

sit

e r

ati

o is i

ncre

asin

g i

n m

idd

le a

nd

larg

e s

ize a

ircra

fts.

1969

1994

2009

Fu

ture

de

ve

lop

me

nt

of

air

cra

ft m

ate

ria

ls

Co

mp

osit

e

350 t

on

s245 t

on

s

31


In r

ece

nt

air

cra

fts,

Al-

Li all

oys a

re a

lso

use

d.

Air

bu

s A

35

0X

WB

Th

e m

ax

. ta

ke

off

weig

ht;

25

0 t

on

s

Co

mp

osit

es

52%

Al, A

l-L

i

20%

Ti 14%

Fu

ture

de

ve

lop

me

nt

of

air

cra

ft m

ate

ria

ls Fe 7

%

Oth

ers

7%

32


Fu

ture

de

ve

lop

me

nt

of

air

cra

ft m

ate

ria

ls

<A

dva

nta

ges a

nd

wea

kn

esse

s o

f A

l-L

i a

llo

ys>

1. Lower density; The density decrease 3% with 1%Li addition.

2. Higher young’s modulus; The modulus increase 6% with 1%Li addition

3. Risk; Li is extremely active

・Melting; Eating of refractory

・Casting; Risk of “explosion”by contact of molten metal with water

・Heat treatment; Surface oxidation by Li

・Recycle; Reaction of machined chip with moisture, acid and alkali.

Difficult to re-melt by existing facilities.

1950

1960

1970

1980

1990

2000

2010

1st generation

＜Typical alloy＞

・2020（Alcoa）

・1420（Russia）

2nd generation

＜Typical alloy＞

・2090（Alcoa）

・2195（Reynolds, MM）

・8090（Alcoa, Alcan）

・8091（Alcan, Pechiney）

3rd generation

＜Typical alloy＞

・2050（Alcan）

・2196（Alcan）

・2099（Alcoa）

・2397（Alcoa）

0.0

1.0

2.0

3.0

1980

1990

2000

2010

Decrease of Li

Li content (mass%)

Registration year

33


AA

20

13

allo

y d

ev

elo

pe

d b

y U

AC

J

UACJ developed AA2013-T6511 alloy to replace 2024-T3

�Strength: Equal or superior

�Improved corrosion

resistance

�Excellent extrudability

�Lower density

(even slightly)

�Lower material costs

Integrated structure

Lower maintenance cost

Lighter

Lower

manufacturing

cost

Back

gro

un

d t

o t

he D

evelo

pm

en

t

34


AA

20

13

allo

y d

ev

elo

pe

d b

y U

AC

J

Alloy

Si

Fe

Cu

Mn

Mg

Cr

Zn

Ti

Al

2013

0.6-

1.0

0.40

1.5-

2.0

0.25

0.8-

1.2

0.04-

0.35

0.25

0.15

Rem.

6013

0.6-

1.0

0.50

0.6-

1.1

0.20-

0.8

0.8-

1.2

0.10

0.25

0.10

Rem.

6061

0.40-

0.8

0.7

0.15-

0.40

0.15

0.8-

1.2

0.04-

0.35

0.25

0.15

Rem.

2024

0.50

0.50

3.8-

4.9

0.30-

0.9

1.2-

1.8

0.10

0.25

0.15

Rem.

Compared with 6013 alloy,

2013

Copper was increased to improve strength.

Transition element changed from Mnto Cr for grain control.

2013 alloy was designed for the extrusion process.

35


AA

20

13

allo

y d

ev

elo

pe

d b

y U

AC

J

Sta

tic

Pro

pe

rtie

s

Strength

Tension

Com-

pressionShear

Bearing

(e/D=2.0)

Bearing

（e/D=1.5)

Fty

Ftu

Fcy

Fsu

Fbry

Fbru

Fbry

Fbru

Average (MPa)390411

389

293

711

950

607

745

A v

alu

e (

MP

a)

36

540

036

528

366

291

056

571

7

2024-T3511

A value (MPa)

290393

234

200

490

745

421

579

Comparison with

2024-T3511

1.3

1.0

1.6

1.4

1.2

-1.4

*1

2013 a

lloy

is s

uperior

to 2

024 in s

tatic s

trengt

h.

A value; At least 99% of population equals or exceeds value with95% confidence

or the specification minimum when it is lower.

*1A basis of tensile elongation is 8 pct.

36


AA

20

13

allo

y d

ev

elo

pe

d b

y U

AC

J

Ex

am

ple

s o

f In

teg

rate

d S

tru

ctu

res

(Unit: mm)

Thin wall hollow shapes can be extruded with 2013 alloy.

37


AA

20

13

allo

y d

ev

elo

pe

d b

y U

AC

J

①Ele

ctr

onic

dev

ice

rack

of

airc

raft

②Em

erg

ency

ladder

for

trai

n

Ap

pli

ca

tio

n e

xa

mp

les

of

AA

20

13

all

oy

38


Co

nte

nts











・Bumper

・Truck tilt

・Forgings


５．Summary

40


Layi

ng

pip

e f

or

auto

Layi

ng

pip

e f

or

auto

Layi

ng

pip

e f

or

auto

Layi

ng

pip

e f

or

auto

- ---m

otive a

ir c

onditio

ner

motive a

ir c

onditio

ner

motive a

ir c

onditio

ner

motive a

ir c

onditio

ner

（（（（LW

CLW

CLW

CLW

C））））

7072 a

lloy

7072 a

lloy

7072 a

lloy

7072 a

lloy

3003 a

lloy

3003 a

lloy

3003 a

lloy

3003 a

lloy

7072 a

lloy

7072 a

lloy

7072 a

lloy

7072 a

lloy

Cro

ss s

ection o

f 3

Cro

ss s

ection o

f 3

Cro

ss s

ection o

f 3

Cro

ss s

ection o

f 3- ---la

yer

laye

r la

yer

laye

r cla

d p

ipe (

cla

d p

ipe (

cla

d p

ipe (

cla

d p

ipe (

φ φφφ17 x

t1)

17 x

t1)

17 x

t1)

17 x

t1)

Fig

. L

ayo

ut

of

auto

motive

air c

onditio

ner

.Fig

. L

ayo

ut

of

auto

motive

air c

onditio

ner

.Fig

. L

ayo

ut

of

auto

motive

air c

onditio

ner

.Fig

. L

ayo

ut

of

auto

motive

air c

onditio

ner

.

La

yin

g P

ipe

fo

r A

uto

mo

bil

e A

ir C

on

dit

ion

er

Liquid tube

Cooling unit

Low-pressure

hose

Condenser

Receiver

High-pressure

hose

Compressor Low-pressure

pipe

UACJ alloy and feature

3-layer clad alloy (outer and inner;7072, core;3003).

2-layer clad alloy (outer;7072, core;3003).

Excellent corrosion resistance.

Feature

O3003

403S

O-

CT209

O-

CT201

Temper

AA

Alloy

Example of expanding (ϕ8 x t1)

41


Alu

min

um

pip

es

for

connecting

Alu

min

um

pip

es

for

connecting

Alu

min

um

pip

es

for

connecting

Alu

min

um

pip

es

for

connecting

com

pre

ssor

and r

ubber

hose

. com

pre

ssor

and r

ubber

hose

. com

pre

ssor

and r

ubber

hose

. com

pre

ssor

and r

ubber

hose

.

Ho

se

jo

int

for

au

tom

ob

ile

air

co

nd

itio

ne

r

Fig

. L

ayo

ut

of

auto

motive

air c

onditio

ner

.Fig

. L

ayo

ut

of

auto

motive

air c

onditio

ner

.Fig

. L

ayo

ut

of

auto

motive

air c

onditio

ner

.Fig

. L

ayo

ut

of

auto

motive

air c

onditio

ner

.

Liquid tube

Cooling unit

Low-pressure

hose

Condenser

Receiver

High-pressure

hose

Compressor Low-pressure

pipe

Be

nd

sa

mp

les

Fin

ish

ed

pro

du

ct


Excellent corrosion resistance.

Excellent corrosion resistance, surface treatment and extrudability.

Feature

T83, T4

6063

63S

O3004

204SA

Temper

AA

Alloy

42


MF

C (

Mu

lti F

low

Co

nd

en

se

r T

ub

e)

Zｎ溶

射材

コア

プレ

ート

材使

用

ＭＦ

Ｃ（押

出材

）

ＭＦＣ

断面

図

クラ

ッド

フィ

ン材

（板

材）

エバ

ポレ

ータ

コン

デン

サ

MFC (Extrusion)

Cross-section

Clad fin sheet

Zn spraying

Use core

plate

Evaporator

Compressor

Gas

Fluid

Inside

Heat

radiation

Endothermic

Outside

air

Condenser

MFC


Excellent workability, corrosion resistance, brazing and heat conduction.

Feature

H112

3021

CA105

Temper

AA

Alloy

43


Au

tom

oti

ve

Pa

ne

l M

ate

ria

ls

Door inner panel

Roof

Rear door

Trunk

Door panel

Front fender

Hood

Coils and sheets (longitudinal circular sheets also possible)

Shapes

Can be coated with various types of lubricant

Lubricants

Dull or milled finished

Surface finishes

Type 5000 or 6000 rolled sheet alloy

Material

Acid washing possible

Description

Surface treatments

Specification

Features of UACJ materials

44


For “Corporate Average Fuel Economy (CAFE)

Standards”in North America, Ford adopted

aluminum alloys to the upper body of F150,

which is the most mass production model.

Au

tom

oti

ve

Pa

ne

l M

ate

ria

ls

45


Bu

mp

er


High strength and corrosion resistance

Feature

T7

7046

ZK170

Temper

AA

Alloy

46


Tru

ck

Tilt

ﾛｱｰ

ﾚｰ

ﾙ

ミド

ルﾚｰ

ﾙ

ｱｯﾊ

ﾟｰﾚｰ

ﾙ

アオ

リ構

造（嵌

合式

）ア

オリ

構造

（嵌

合式

）ア

オリ

構造

（嵌

合式

）ア

オリ

構造

（嵌

合式

）

Lower

Middle

Upper

Inla

id s

tru

ctu

re o

f ti

lt

Alloy; 6063

47

アオ

リア

オリ

アオ

リア

オリ

Tilt


Fo

rgin

gs

Alloy; Al-Mg-Si, Al-Si

48


Co

mp

res

so

r W

he

el fo

r T

urb

o C

ha

rge

r

<Form>

Casting / Extrusion (Milling)

49


Co

nte

nts











・Bumper

・Truck tilt

・Forgings


５．Summary

51


Su

mm

ary

Aluminum alloys have been used for aerospace structures.

・2xxx alloys; higher fatigue strength => Main wing lower and Bodyouter plate

・7xxx alloys; higher static strength => Main wing upper, Body frame and stringer

Integrated structure by milling have been applied.

The newest aircrafts use composites over 50% in weight.

The aluminum alloys which are used for aerospace structures needAA and AMS

registrations and MMPDS data.

The manufacturer need AS9100 (ISO 9100/ JIS Q 9100) quality control system to

produce aerospace materials or parts.

For automotive uses, aluminum alloys are widely used for their laying pipes and

for heat exchangers.

Also, Aluminum automotive body materials, bumpers, compressor wheel for turbo

charger is increasing.

52


Thank you for your attention !!

53

aluminum in aerospace and automobile parts in aerospace...aa2013 alloy developed by uacj 4．...

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