Integrated Design and Modeling of Passenger Aircraft

MINISTRY OF EDUCATION AND SCIENCE OF THE UKRAINENATIONAL AEROSPACE UNIVERSITY

NAMED BY N.E ZHUKOVSKIYI KHARKIV AVIATION INSTITUTE

FACULTY OF AIRCRAFT AND HELICOPTER DESIGN

PASSENGER AIRCRAFT INTEGRATED DESIGNING AND MODEL ANALYSIS

COMPELLED BY KIRUBAGARAN MAZHALAI PRIYAN

SUPERVISOR PROFESSOR TURBOYEV

AIRCRAFTS INTENDED PURPOSE - COMMERCIAL

USAGE

PAYLOAD CATEGORY - PASSENGERS

TYPE - REGIONAL

JET

RANGE - SHORT-RANGE

MODE OF CLASS - ECONOMY

CLASS

PURPOSE OF THE DESIGNING AIRCRAFT

DESIGN CONFIGURATION

AERODYNAMIC CONFIGURATION

WING CONFIGURATION

TAIL CONFIGURATION

POWERPLANT TYPE

FUSELAGE SHAPE

LANDING GEAR TYPE

NORMAL

LOW WING

T-TAIL

TURBOFAN

CYLINDRICAL

TRICYCLE

TACTICAL TECHNICAL REQUIREMENTS

DESIGN CHART

PROTOTYPES SELECTED ACCORDING TO THE PURPOSE, DESIGN CONFIGURATION AND TTR

EMBRAER 145 BOEING 717-200

TUPOLEV 134 BOMBARDIER CRJ 100

PROCESSING THE CALCULATIONSFROM STATISTICAL DATA

SELECTION OF MAIN RELATIVE PARAMETERS

MASSES OF THE AIRCRAFT IN ZERO

APPROXIMATION

DESIGN OPTIMIZATION

GROUNDS OF AIRCRAFT CONFIGURATION

MASS CALCULATION BY SEMI-EMPIRICAL,

STATISTICAL AND GRAPHICAL METHOD

FINAL MASS OF THE AIRCRAFT

STRUCTURAL GROUP MASS

POWERPLANT MASS

FUEL MASS GROUP 

EQUIPMENT MASS

FURNISHING

PAYLOAD MASS

MISCELLANEOUS GROUP

CONSUMABLES

13984 kg

3924 kg

7900 kg

4676 kg

1449 kg

4230 kg

977.75 kg

470 kg

DETERMINATION OF CG OF AIRCRAFT

Xm = 18.1 mYm = 2.2 m

AIRCRAFT GENERAL VIEW

DESIGN STRUCTUTRAL CONFIGURATION

= 2mm

= 5.8369 Mpa

AERODYNAMIC CHARACTERISTICS OF DESIGNED AIRCRAFT

-15 -10 -5 0 5 10 15 20 250

0.2

0.4

0.6

0.8

1

1.2

1.4

1.6

1.8

2

2.2

2.4

2.6

2.8

3

3.2

For flightFor take-offFor landing

Cy

α

0 0.2 0.4 0.6 0.8 1 1.2 1.40

0.02

0.04

0.06

0.08

0.1

0.12

0.14

For take - offFor landing

Cya

Cxa

WING LOAD CALCULATION

Qf at tank number

Qf at tank two

5811.2

1280.7

LINEAR LOAD

3-D MODEL OF THE DESIGNED AIRCRAFT

Two independent hydraulic system

Operating pressure is 3000 psi

Hydraulic fluid used is skydrol 500B-4

Each Hydraulic system consists of Reservoir, manifold,

shut-off valve, accumulator, priority valve, one engine and

electric motor driven pump

HYDRAULIC SYSTEM OF THE DESIGNED AIRCRAFT

SCHEMATIC LAYOUT OF HYDRAULIC SYSTEM

Always release the system pressure before removing a component from the A/C

Never does any maintenance work on airplane with any other specified oil other than the recommended one.

Carry out the patch test on the system to prevent the contamination of oil. This can be carried out using Millipore patch test kit.

Never mix different grade of hydraulic oil to service the A/C.

MAINTENACE PROCEDURES OF DESIGNED HYDRAULIC SYTEM

PRODUCTION METHOD OF PARTS OF RIB

Rib web

Stiffener

Lightening holes

Caps

Forming process

Bending process

Drill bits and form blocks

Milling

ASSEMBLY METHOD

Co-ordinate template method - Increased accuracy and low labor input.

VERTICAL RIB ASSEMBLY – SEQUENTIAL SCHEME

For the assembly of the given rib section of the aircraft, it is recommended to use the vertical

RIB

UPPE

R CA

P

LOW

ER C

AP

RIB

WEB

SIDE

CA

P

ATTA

CHM

ENT

PATE

STIF

FENE

RS

FAST

ENER

S

MOUNTING

ASSE

MBL

Y DE

VICE

THE DESIGNED VERTICAL RIB IN CATIA &GENERAL ASSEMBLY JIG LAYOUT

VERTICAL RIB ASSEMBLY JIG

ECONOMIC EFFICIENCY

Expense for one airplane

Total manufacturing

expense

Wholesale Price

Wholesale price + VAT

11.067 million $

13.10593 million $

15.674700 million $

18.809640 million $

INTERIOR CABIN LAYOUT

Seating type

Number of rows

Comfort level

Seat width

Seat pitch

Cabin diameter

Maximum floor height

Floor width

3 Abreast

16 + 1

High Level Comfort

0.45 m

0.8277m

2.27 m

1.85 m

0.44 m

Cross-section Layout of the fuselage

Total length of the passenger cabin = 18.14m Total length of the cockpit = 1.90m

SEATING ARRANGEMENT

Thus the designed aircraft is processed starting from the initial geometrical parameters following its aerodynamic characteristics, the loads acting on unit structure, integrated designing , manufacturing techniques, the hydraulic system, and even its economical valuation s are done each step by step according to the valuable lectures given by my professors and with the help of their textbooks. At last the designed aircrafts seating layout is considered and cabin length are found and sketched.

CONCLUSION

THANKYOU