Aircraft Design : Business Jet: Design of Wing spar, Power plant System & Engine mount design

M INISTRY O F EDUCATIO N AND SCIENCE o f UK RAINE

N AT I O N A L A E R O S PA C E U N I V E R S I T YN a m e d b y N . E Z h u k o v s k y

“ < < K h a r k o v A v i a t i o n I n s t i t u t e ”

Ai rp lane Des ign ing Facu l tyA i rp lane and he l i copte r Des ign Cha i r

Theame o f Bache lo r Work“Bus iness- Jet A i rp lane: Des ign ing of wing Spar,

Power P lant and Eng ine Mount”

By: - Mit ta l Praku lGr : - 10E4-1

Superv isor : - Prof. A . I . RyzhenkoAdvisors : - Prof. A .A . Pav lenko

Prof. L .N . Korn i lovProf. V. Yu . Ko loskov

Kharkov 2011

Part 1: Statistical Design of theAircraft Shape

Technical TaskLong range Business-Jet

Vcr = 850 Km/hRange = 6500 KmHcr = 12 KmPassenger = upto 15

PROTOTYPES

Hawker 4000 Bombardier 300Hawker 850

Gulfstream GV Bombardier C850

GENERAL VIEW

LOAD CARRING STRUCTURE

PART 2 . AERODYNAMICAnd Flight Performance

GRAPH OF Cymax AGAINST MACH NUMBER

0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.90

1

2

3

4

5

6

Cya0Cya3Cya6Cya11Cymax

Mach

Cya,C

yam

ax

SPEED OF LEVEL FLIGHT WITH ALTITUDE

0 0.02 0.04 0.06 0.08 0.1 0.12 0.140

0.2

0.4

0.6

0.8

1

1.2

1.4

Polar Graph

H=0H=3H=6H=11

Cxa

Cya

50 100 150 200 250 3000

2

4

6

8

10

12

14

V contVminVmaxVoptVmin.per

Speed

Graph of Thrust vs Mach Number

0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 10

20000

40000

60000

80000

100000

120000

140000

160000

180000

200000

Preq0

Preq3

Preq6

Preq11

Pavb0

Pavb3

Pavb6

Pavb11

Mach

Thru

st

(N)

Part 3. Determination of wingStatic condition

0 0.2 0.4 0.6 0.8 1 1.2

-20

-10

0

10

20

30

40

50 Distributed Load

qa,qfqt

Z

qa,q

f,qt

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1 1.1

-200

-190

-180

-170

-160

-150

-140

-130

-120

-110

-100

-90

-80

-70

-60

-50

-40

-30

-20

-10

0

10

20

Q dQcQt

Z

Qd,Q

c,Q

t

Graph of Shear force

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1 1.1

-850

-800

-750

-700

-650

-600

-550

-500

-450

-400

-350

-300

-250

-200

-150

-100

-50

0

50 Bending Moment

McMdMtot

Z

Mc,M

d,M

tot

0 0.2 0.4 0.6 0.8 1 1.2

-500

-400

-300

-200

-100

0

100Reduced Moment

MztotMrdMrc

Z

Mrc

,Mrd

,Mto

t

Part4. Aircraft AssemblyParts and unit structure

Spar Design

FUEL SYSTEM DESIGNING

Engine Mount Designing

Part 5. Technological section

Punch

PART. 6ECONOMICAL SECTION

S.No ArticlesExpenses

(in million $)1 Materials and Raw Materials

0.19862 Purchased devices , onboard equipments

1.7413 Manufacturing Repair of special technological equipment

1.1084 Wage

0.96

5 Indirect Shop expenses 0.416

6 Indirect Manufacturing expenses 0.298

7 Taxes 0.0252

8 Total ( Manufacturing expenses) 3.889

9 Outside Manufacturing expenses 0.1942

10 Total Manufacturing Cost Price 4.079

11 Profit (Planned) 0.612

12 Wholesale Price 4.6911

13 Value Added Tax 0.938

14 Wholesale Price with VAT 5.63

Part 7. Labor Protection

Personal protective system

Artificial Lightning system

= 1438 lm (According to our work shop parameters )

SO we had chosen CFL bulbs as they had efficiency and low power consumption We had recommended GE 23 watt which produce 1600 lm

Thank you for your attention

Спасибо за внимание