passenger aircraft.pptx
TRANSCRIPT
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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