bipol 1 handout 7a - warsaw university of...
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![Page 1: BIPOL 1 handout 7A - Warsaw University of Technologyitlims-zsis.meil.pw.edu.pl/pomoce/BIPOL/BIPOL_1_handout_7A.pdf · 8 Detailed mass analysis Masses should be calculated according](https://reader030.vdocuments.net/reader030/viewer/2022021710/5c77cd6209d3f229578c39ed/html5/thumbnails/1.jpg)
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Training aeroplane
TLiA 6/1973Stinton „The Design of the aeroplane”
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17-20transport
11-15fighter
11-20commercial
5-10general
ααααF [°]Aircraft type
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(((( )))) a85,0rV 22max ⋅⋅⋅⋅<<<<⋅⋅⋅⋅ωωωω++++
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332211 xmxmxmxm ++++⋅⋅⋅⋅++++⋅⋅⋅⋅====⋅⋅⋅⋅
Center of gravity of the whole aeroplane should be located between 25-35% mac, so
1. center of gravity of basic masses (engine, pilot, payload) should be located between 0-25% mac if most of other masses are to be located behind CG;
2. center of gravity of basic masses (engine, pilot, payload) should be located between 30-45% mac if most of other masses are to be located in front of CG.
SCa
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SC
SCal
SS HH
H ⋅⋅⋅⋅====κκκκ
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bl
SS VV
V ⋅⋅⋅⋅====κκκκ
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Detailed mass analysis
Masses should be calculated according to:Raymer „Aircraft Design, a Conceptual Approach”Corke „Design of Aircraft”Danilecki „Projektowanie samolotów”
1,2,14,15
6
3
4
95
1011
1213
8
7
Z
X
SCa
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37-42% SCaW
30% SCaH,V
37-42% SCa
Positions of component’s Centers of Gravity
Positions of component’s Centers of Gravity
0,4L
L 0,26L
L
0,39L
0,45-0,5L
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0.0804.2545600mTO less payloadIV
0.0404.2516300Maximum takeoff weight (mTO)III
003.41220Fuel in fuselage19
0.175.64.61440Fuel in right wing18
0.17-5.64.61440Fuel in left wing17
-0.1104.2652200Full aeroplane less fuelII
-0.206.4200Payload (bay C)16
-0.504.6250Payload (bay B)15
002.1250Payload (bay A)14
-0.0504.2851500Empty weightI
00465Other equipment13
0.106.750Avionics12
004.3150Electrical installation11
004.665Control system10
01.054.4270Right engine9
0-1.054.4270Left engine8
003.1170Fuselage 7
-0.751.34.570Right leg of landing gear6
-0.75-1.34.570Left leg of main landing gear5
-0.900.735Nose leg of landing gear4
0.706.635Vertical stabilizer3
0.1554.4125Right wing2
0.15-54.4125Left wing1
Z (m)Y (m)X (m)Weight (kg)
Where: A - point, where ¼ mac is located
CG
CG
CGCG
CG
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Long range commercial aeroplanefor 200 passengers
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18.1427.2218.14kgBaggage/passenger
0.030.00.230.03m³Galley volume/passenger
50402010Passenger/lavatories
503610Passenger/cabin
1.521.931.93mAisle height
0.380.710.51mAisle width
1.651.65mHeadroom
0.810.761.020.86mSeat pitch
0.460.410.710.43mSeat width
Short rangeLong range
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18.1427.2218.14kgBaggage/passenger
0.030.00.230.03m³Galley volume/passenger
50402010Passenger/lavatories
503610Passenger/cabin
1.521.931.93mAisle height
0.380.710.51mAisle width
1.651.65mHeadroom
0.810.761.020.86mSeat pitch
0.460.410.710.43mSeat width
Short rangeLong range
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Shock absorber extended
min 5°
min 0,5mmin 0,15m
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18.1427.2218.14kgBaggage/passenger
0.030.00.230.03m³Galley volume/passenger
50402010Passenger/lavatories
503610Passenger/cabin
1.521.931.93mAisle height
0.380.710.51mAisle width
1.651.65mHeadroom
0.810.761.020.86mSeat pitch
0.460.410.710.43mSeat width
Short rangeLong range
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18.1427.2218.14kgBaggage/passenger
0.030.00.230.03m³Galley volume/passenger
50402010Passenger/lavatories
503610Passenger/cabin
1.521.931.93mAisle height
0.380.710.51mAisle width
1.651.65mHeadroom
0.810.761.020.86mSeat pitch
0.460.410.710.43mSeat width
Short rangeLong range
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ΛΛΛΛLE
ΛΛΛΛt/c
M
McosΛΛΛΛLE
Meff=M∞cos(ΛΛΛΛLE)
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Center of gravity of the whole aeroplane should be located between 25-35% mac, socenter of gravity of basic masses (engine, fuel, payload) should be located near ~20% of mac to allow for CG shift caused by empennage mass.
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AoACL=0,9CLmax+3°
AoACL=CLmax or more
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less then 60°
CG
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bl
SS VV
V ⋅⋅⋅⋅====κκκκ
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SCal
SS HH
H ⋅⋅⋅⋅====κκκκγγγγw
γγγγHγγγγw < γγγγH
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Detailed mass analysis
Masses should be calculated according to:Raymer „Aircraft Design, a Conceptual Approach”Corke „Design of Aircraft”Danilecki „Projektowanie samolotów”