A380 Aircraft prototype design

8/16/2019 A380 Aircraft prototype design

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MINISTRY OF EDUCATION AND SCIENCE OFUKRAINE

National Aerospce University

N.E. Z!"ovs"y # Kar"ov Aviation Instit!te #

Depart$ent %&'

(o$etas" No. % )

#Desi*n o+ ,on* ran*e passen*er Aircra+t in Zero

Appro-i$ation

(o$etas" No./ )

,oa0 carryin* str!ct!re o+ passen*er aircra+t

K%&' &&.&&1&&.&&.&&.EN 2345

E-planatory Note

S!67ect) 3eneral Arran*e$ent o+ Aircra+t

8acelor 0irection 9&:%%&% #Aircra+ts an0 Roc"eten*ineerin*

Developed by:

Student of 140F group, Bidre Shivadas Adithya Das

Checed by :

Senior !eacher , "r#

Danov #A#S


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$harov %01&


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Abstract

Desi*n o+ ;assen*er Aircra+t In ZeroAppro-i$ation

Das Hometask 1 , National Aerospace University

Kharkov 2014 - pages.

n this home task !esign a "assenger Aircra#t $ith %ero

appro&imation. n these parts $e !etermine 'ake o## mass in

(ero appro&imation. Accor!ing to statically analysis )elect

engine, !etermine *eometrical parameters an! +inally Dra$ a

*eneral vie$ o# Aircra#t.

'he prpose o# !esign o# a aircra#t in %ero appro&imation is

creation o# a strctre $ith nie characteristics, $hich ensres

more e##ective #l#illment o# tasks, $hich may e tra!itional #or

the given aircra#t type or ne$ tasks, $hich cannot e #l#ille!

$ith other metho!s. 'he prpose o# !esign is to !evelop a

pro/ect an! reali%ation o# $hich eing limite! to a certain e&tent,

$ol! ensre the most e##icient reaching o# the !e#ine! goals o#

the !esign.

+igre , 'ales , iliography .

Key $or!s - ass , +el , 'hrst.


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Content

Hometask 1

TASK INTRODUCTION

%.STATISTICA, DATA ANA,YSIS%.%.;ROTOTY;ES ANA,YSATION < DESCRI;TION%./.STATISTICA, DATA TA8,E < CONC,USIONSFOR

C(ARECTERISTICS OF AIRCRAFTS

/.TACTICA, TEC(NICA, DATA'.SE,ECTION OF RE,ATI4E ;ARAMETERS

=. DETERMINATION OF MASS ;ARAMETERS:. DETERMINATION OF EN3INE ;ARAMETERS

9.3EOMETRICA, DATA >.%.DETERMINATION OF ?IN3 ;ARAMETERS>./.DETERMINATION OF FUSE,A3E ;ARAMETERS>.'.DETERMINATION OF TAI, UNIT ;ARAMETERS

@.DETERMINATION OF ,ANDIN3 3EAR;ARAMETERS DESCRI;TION CONC,USION


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8I8,IO3RA;(Y


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(o$etas" /

/.% Deter$ination o+ 3eneral Arran*e$entso+ Airplane !nits

/./ ,oa0 carryin* str!ct!re o+ in*

/./.% Deter$ination o+ loa0 carryin*str!ct!re o+ a in*

/./.%.% concept o+ conventional spar2spar ratio5

/./.%./ Criterion o+ loa0 $o$ent intensity

/./.%.' Deter$ination o+ 0istance6eteen ri6s an0 strin*ers

/.' ,oa0 carryin* str!ct!re o+ +!sela*e

/.= ,oa0 carryin* str!ct!re o+ tail !nit

section/.: ;osition an0 p!rpose o+ stron* ri6s an0+ra$es in aircra+t str!ct!re

/.: ,oa0 carryin* str!ct!re o+ lan0in* *ear


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!as

!he develop'ent of an aircraft pilot pro(ect

co'prises the follo)ing parts: statistical

for'ing of the aircraft*s appearance,

calculation of +ight and aerodyna'ic

characteristics of a aircraft, calculations of

provision of regular one ele'ents static

capacity, develop'ent of unit asse'bly

structures -)ing spars, panels etc#., loadbearing ele'ents of engine fastening

syste's, calculations of centre of 'ass and

o/set angle of landing gear for the safety of

the aircraft# And specically saying the 'ain

ob(ective of tas is to design passenger

aircraft in ero approi'ation )ith para'etersaround 'y 'ain prototype Airbus A230#

npass ,' 5cr,' 6cr,'7hr tor,'

400 10,000 13,000 900 2,950


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Intro0!ction

'his is the e&planatory note o# the Home task #or

!esigning long range "assenger aircra#t in %ero

appro&imation an! also its 3oa! carrying strctre. y

main prototype is A50 $hich is 6orl!7s largest

8ommercial airliner $hich has capaility o# carrying

more than 900 passengers. 'his task consist o# 9 parts

$here !o statical analysis o# aircra#t $ith other : prototypes, an! select the engine, !etermine the

geometrical parameters o# aircra#t . +inally y the vales

that calclate! , !ra$ the general vie$ o# my aircra#t .


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%#Statistical Data Analysis :

%#1#8rototypes:

My Aircraft is Non maneuverable subsonic passenger aircraft.

Here is rototypes ! too" for my aircraft #esign$


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Airbus A380

Airbus 340


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Boeing 747


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Antonov 124


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Lockheed c5 Galax


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/./.Statistical Data)Table 2.2.1 Statistical parameter table.

Sl.No

Name ofAircraft

A380 A340 B747 LockheedC- !ala"#

Antono$1%4

&'%%

1 %,"m 15,200

% Mac& 0.'9

3 Mo ma(,)onnes

5*5

4 M% ma(,tonnes

39+

(7

9o#

Na$e o+ Airplane

Air6!sA'@&

Air6!sA'=&

8oein*8>=>

T!polev T!/&=

8oein* >:>

1 V CR,'7h

00 32 3;1 0< 3=>1'&&

Air6!s

A'=&1:&&

8oein

*>>>1/&&

T!polev T!/&=

8oein* >:>

2 m0 max ,g


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0 % 0 & 0< Mc 3% &10


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4$a-

K$B

4cr

K$B

Hcr

m

,to

$

L

kmN)ass Ncr

)0

N*m%

4< 0010&0

0

%<

0

100

00400 10

&&00

+. -election of elative an# /eometrical arameters

Ta6le =.%) ;ara$eters o+ te pro7ecte0 airplane.

+ C 6G SA, F DF H

$

3#3 22#<4#2

2

0#1

%

0#14

2

0#1

;11 , s)eep angle ? H taper ratio @ , airfoil

thicness ratio C , +ap chord ratio b + b+7b, +ap angles

-taeo/ and landing positions. F, ailerons relative area SA SA7S#

= F!sela*e : aspect ratio >F, dia'eter DF#

= Tail !nit : the relative area of horiontal surface S(SH the

relative area of vertical surface - -, aspect ratio of horiontal

surface >5S, aspect ratio of vertical surface >6S, s)eep angle

of horiontal surface ?5S, s)eep angle of vertical surface ?6S,

airfoil thicness ratio of horiontal surface C5S, airfoil


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thicness ratio vertical surface C6S, taper ratio of horiontal

surface @5S, taper ratio of vertical surface @6S#

:.Deter$ination o+ te airplane ta"e1oJ $assin ero appro-i$ation

!he sie and shape of the other parts of the airplane depends

highly on the taeo/ 'ass of the airplane#

!aeo/ 'ass of the airplane for ero approi'ation is

deter'ined by the for'ula 'entioned belo)# !he necessary

para'eters are obtained fro' the statistical data#

m0 mC + mC / (1-( mF + mPP + mEQ + mK )) (5.1)

)here m0 E taeo/ 'ass of the airplane in eroapproi'ation mC E 'ass of cargo or payload mC E 'ass ofcre) m$ E 'ass ratio of the airplane structure m88 E 'ass ratio of the po)erplant mGH E 'ass ratio of the eIuip'ent mF E 'assratio of fuel#

"ass of cargo mC is deter'ined provided that the 'ass of

one passenger )ith luggage is 0g# !herefore 'ass of cargo for

our airplane is deter'ined by such eIuation:

mC43000 -


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6alue of 'ass ratio of fuel mF is deter'ined by the for'ula:

mF a J #L/V !" (5.#)

mF 0.033 0.033 410000 9006

mF 0.+'+

)here L E +ight range, ' V C E cruising speed of +ight, '7h#

Factors a and 6 have values for airplanes )ith turbo(et engines:

a 0#022

6 0#022

"ass ratio of structure m$ , po)erplant m88, eIuip'ent mGH forthe pro(ected airplanes are obtained fro' table# 4 as follo)s:

= m$ 0#2

= m88 0#10

= mGH 0#10

= mF 0#4

Fro' !able %#3 of Kdevelop'ent of a pilot pro(ect of an

aircraftL


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!hen taeo/ 'ass of the airplane in ero approi'ation is

calculated by for'ula of m0#

$oL 2$c $cr5B%12$" $pp$E$+ 5P

$oL +''000 7g

!hen the values "ass of structure m$ and its co'ponents-'assof )ing m), fuselage mF, tailunit m !M, landing gear mN., 'ass offuel mF, 'ass po)erplant m88, eIuip'ent mGH for the pro(ectedairplanes are calculated#

"ass of )ing, fuselage, tailunit, landing gear is deter'ined#

According to this table 'ass ratio of the airplane units is sho)n inshare of total structural 'ass m$ #

6alues of units 'ass are found by the for'ula

mi mim$ -


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!he total su' of units 'ass ratio mi for designed airplane 'ustbe eIual to 1, that is Qmi 1#

"ass of structure

m$ m$ m0 0#2O433000 14&400 g

"ass of po)erplant

m88 m88 m0 0#10O433000 43300 g

"ass of eIuip'ents

mGH mGH m00#10O433000 43300 g

"ass of fuel

mF mF m0 0#4O433000 1


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!hus, the respective 'asses are calculated accordingly:

= 'ass of )ing m)m) m$ 0.39' 14&400 &23;3#&31&g

= 'ass of the fuselage mFMSmFMS m$ 0#22% 14&400


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0 14&400

!able#


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>. 3eo$etrical Data

>.% Deter$ination o+ in*para$eters.

!he )ing surface area of the pro(ected plane is.

S m0.'/p0 , (.1)

(#0002.)/(330010)

4%, S&n' a%a , m0ta6 *7 ma$$ 8K'9 , P0&n'

*a:&n' at ta6 *7 ma$$8N/m; 9

Qhere ' #3 '7c%, p0 &&00 97'%

S 1.15m;

Qing span L , S.


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K @.3

Qing 'ean aerodyna'ic chord -"AC. is calculated by the

for'ula

A % . 2o . % 1 * 3 . . 1

%/14.44%=%5B2'=2=%55

A 10.0'

Coordinate of "AC along a )ing span is deter'ined by the

relation

B A L . % * ( . 1 7.

7.44%*(541

B A 15.''

Coordinate of "AC nose along an ais 0x

C LE @0

x A B A. tanC LE (.3)

15.tan @0

C LE &$ ta6n %*m ta #.1

)here C is the s)eep angle of the )ing*s Iuarterchord line

thus x A .02


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>./.F!sela*e ;ara$eters !he 'ain para'eters needed to start constructing the

fuselage section are as follo)s:

LF-Tverall fuselage length. >F #DF11UF #-3##12..

DF-Dia'eter of the fuselage. 3.5#m

LN -Fuselage nose length. >9 #DF 1#;U #-1#;V%# ! #DF 2U+6

elative an# geometrical parameters are ta"en from table +.1

Qhere >F, >9, > ! are the aspect ratio of fuselage, nose part, rear

part respectively#

!he statistic data are fro' !able ; of Senior teacher, "#9

Fedotov*s NAA part 2

>.'.Tail1!nit para$eters

!he tailunit of an airplane consists of the horiontal

stabilier and the vertical stabilier# !he geo'etrical calculations

that involves for constructing the tailunit are the sa'e as that of

the )ing#

Distance fro' the airplane centre of 'ass up to the

horiontal tailunit centre of pressure L5S #Distance fro' thevertical tailunit centre of pressure up to the airplane centre of

'ass L6S in ero approi'ation 'ay be considered such )hich iseIual to the distance of horiontal tailunit, )here L6S L5S#


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>.'.% (oriontal tail !nit

!he surface area the horiontal stabilier is:

SS GSS . S 0.;51.15(.)

SS 1*9.2'

)here SS is the ratio of surface area of the horiontal stabilier tothe )ing*s area#

5S %#


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-%72U10#1&-%#


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oot -on ais of airplane sy''etry. 0 VS and tip K VS chordsare deter'ined proceeding fro' the values SVS , =VS , LVS >

0 VS (SVS /LVS ).( ;=VS /=VS+1)

(.1#)

(15./;5.;).(;;.5/;.5+1)

0 VS 2.;m

K VS 0 VS /=VS

K VS 2#02

)here value =VS %#;< ,

!he 'ean aerodyna'ic chord -"AC. is calculated by the for'ula

A VS {(;/@)0 VS(=VS; + =VS +1)} / H=VS(=VS+ 1)I , (.15)

((;/@).@#(;.5J;+;.5+1)/(;.5(;.5+1)

AVS 2.1#

Coordinate of "AC along a 6ertical stabilier is deter'ined

by the relation

B A VS (LVS /@) .(=VS+;)/(=VS+1)(;5.;/@)(;.5+;)/(;.5+1)

B AVS 10.3#

Coordinate of "AC nose along an ais 0x x A VSB AVS.tanC LE(VS) (.13)

C LE(VS) #0

thus, x A VS .@


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>.= Deter$ination o+ te position o+ centre o+ $ass o+ teairplane

8osition of the airplane*s centre of 'ass is deter'ined

relative to nose part of the )ing*s 'ean aerodyna'ic chord-"AC.#

!he reco''ended distance for the centre of 'ass fro' nose

part of the 'ean aerodyna'ic chord for our )ing is:

M (0.;30.@0) A (.1)(%*m D?*pmnt * p&*t p%*ct)

0#%3 . A

0#%3 10#03

;.;m

>.: Distance +ro$ te airplane centre o+ $ass !p tote oriontal tail1!nit centre o+ press!re 2LS5

LS %#0 bA

%U10#03

LS ;0.13m

@.,an0in* *ear para$eters

!he 'ain para'eters reIuired to construct a tricycle or three

strut landing gear are as follo)s:

= anding gear )heelbase, b

= anding gear )heel trac, B

= T/set or the horiontal distance bet)een the centre of

gravity and 'ain landing gear, e

= 5eight of landing gear, h

= 5eight of airplane*s centre of 'ass, 5


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Derivatives of these para'eters )ill be:

= Angle of offset for )heels of 'ain struts, W

= Angle of overturning, X

anding gear )heelbase:

(0.@0.#) 0#20 LF (.1)

0#22 ;1#4

;@.53 m

T/set

(0.030.1;) (.;)

0#0 0#0 %2#


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@./ Calc!lation o+ ei*t o+ airplane centre o+ $ass 25 2#%;

@.' Calc!lation o+ te ei*t o+ lan0in* *ear

DF


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So generally saying for this pro(ect P gone through these

stages and the results are above published in KdescriptionL #so P

successfully gone thought these steps of designing of an aircraft

and this is ' eplanatory note of 'y pro(ect#


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Bibliography :

1#Fedotov "#9# KNeneral Arrange'ents of AircraftL !hesu''ary of lectures# E $harov: 9#Ze# [huovsy 9ationalAerospace Mniversity K$hAPL, %00 %4< p# part 2

%#KDevelop'ent of a pilot pro(ect of an aircraftL E A#$"yalitsa,#A "alasheno, A#N Nrebeniov

2#8aul \acson K \anes All !he Qorld*s AircraftL , %004%00

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A380 Aircraft prototype design