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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