passenger aircraft.pptx

8/14/2019 PASSENGER AIRCRAFT.pptx

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PASSENGER AIRCRAFT


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BASIC V-n DIAGRAM

Load factor is the ratio of Lift divided by theaircraft weight.

Highest load occurs during manoeuvring andflight into vertical gust.

The airframe and also the passengers mustwithstand the loads.

No permanent deformation must beproduced.


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BASIC V-n DIAGRAM

Manoeuvre loads are exerted during Steady turns Pull ups

Maximum load factor (+ve) for transportcategory aircraft above 50000 kg is

As given in FAR 25.337

maxn 2.50


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BASIC V-n DIAGRAM

Cruise speed: Passenger aircraft are usuallydesigned for optimum performance at thisspeed.

Dive speed : Maximum airspeed the airframeis designed to resist.


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BASIC V-n DIAGRAM

Formula used Load factor

Dive speed

2

2 LmaxV SC Ln

W W

D CV 1.4 V


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BASIC V-n DIAGRAM

-2

-1.5

-1

-0.5

0

0.5

1

1.5

2

2.5

3

3.5

0 50 100 150 200 250 300 350

L o a d

f a c t o r ( n )

Velocity m/s


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GUST V-N DAGRAM

Gust: Upward and downward currents of air Causes changes in

Airspeed Angle of attack Lift generated


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GUST V-N DAGRAM

Gust load factor

V V Sn 12

g gust air K W

Where, V gust gust velocity (m/s)Vair Air speed (m/s)S Wing area (m 2)W Aircraft weight (N) Air density (kg/m 3)


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GUST V-N DAGRAM

-1

-0.5

0

0.5

1

1.5

2

2.5

3

0 50 100 150 200 250 300 350 400

L o a d

f a c t o r ( n

)

Velocity m/s


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COMBINED V-n DIAGRAM

-2

-1.5

-1

-0.5

0

0.5

1

1.5

2

2.5

3

3.5

0 50 100 150 200 250 300 350

L o a d F a c t o r ( n

)

Velocity(m/sec )


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LOAD ESTIMATION ON WINGFEATURE VALUE

WING AREA 300 m2

WING SPAN 49.3 m

AIRCRAFT WEIGHT 230 ton

ROOT CHORD 7.23 m

TIP CHORD 5.06 m


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LOAD ESTIMATION ON WING

0.000

500.000

1000.000

1500.000

2000.000

2500.000

3000.000

3500.000

4000.000

4500.000

5000.000

0 5 10 15 20 25 30 35 40

B e n

d i n g M o m e n t

( N m

)

Distance from Centerline (m)

Bending Moment at Station


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STATIC MARGIN(stick fixed)

The distance of the center of gravity ahead ofthe neutral point divided by the wing meanchord.

Neutral point is the furthest aft position of theC.G for which the aircraft is statically stable.


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Formula

Hn = hn-h

h n is the distance between neutral point andleading edge of the aircraft. h is the distance between center of gravity and

leading edge of the aircraft.


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CATIA MODELINGORTHOTROPIC VIEW OF WING


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CATIA MODELINGISOMETRIC VIEW WING


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CATIA MODELINGISOMETRIC VIEW OF FUSELAGE


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CATIA MODELLINGORTHOTROPIC VIEW OF AIRPLANE


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CATIA MODELINGISOMETRIC VIEW OF AIRPLANE


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THANK YOU

passenger aircraft.pptx

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