Download - Propulsion PDR
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Propulsion PDR
AAE 451Fall 2006
Team Whishy Washy
Tung Tran Mark KochMatt Drodofsky Matt Lossmann
Ravi Patel Ki-bom KimHaris Md Ishak Andrew Martin
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Summary
• Revisit Sizing
• Selection Procedure
• Define Advanced ratio and Propeller parameters
• Propeller selection
• Motor, Gear Box, Speed controller selection
• Battery analysis
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Review of Vehicle Sizing
0 1 2 3 4 5 6 7 8 9 100
0.5
1
1.5
2
2.5
Weight~lbf
W-W
e an
d W
b+W
p~lb
f
Estimated aircraft weight is 5.2103 pounds.
Weight estimation using historical weight data
Estimated battery weight is 0.22002 pounds.
Payload weight is 1 pound.
Historical data
Estimated weight
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Review of Vehicle Sizing
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Selection Procedure
• Find the best endurance flight speed– Happens at (Cd/Cl3/2)min
• Size Propeller for flying at Max endurance speed– Adjust RPM’s and diameter for optimum propeller
efficiency
• Gear box and motor were sized off of max speed– Gear box sized for optimum propeller efficiency – Motor sized by power required and motocalc
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6
Advanced Ratio on Thrust Coefficient
nD
VJ
42Dn
TCt
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Advance Ratio On Power Coefficient
nD
VJ
53Dn
inPCp
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Advanced Ratio on Propeller Efficiency
nD
VJ
inPoutP
p
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Endurance Flight
• Clendurance = 1.38
• Cdendurance = .0960
• Vendurance = 30.8 ft/s
0.02 0.04 0.06 0.08 0.1 0.12 0.14 0.16 0.180
0.2
0.4
0.6
0.8
1
1.2
1.4
1.6
1.8
2Cl vs Cd
Cd
Cl
Cdo
=0.024
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Endurance Flight
• (Cd/Cl3/2)min = .0960
0.02 0.03 0.04 0.05 0.06 0.07 0.08 0.09 0.10
0.05
0.1
0.15
0.2
0.25
0.3
0.35
0.4
0.45
0.5Cd/Cl (3/2) vs. Cd
Cd
Cd
/ C
l (3/2
)
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Endurance Flight
• Venduracne = 31 ft/s
• Power = 11.1 ft-lbf/s• Cl = 1.37
0 10 20 30 40 50 600
5
10
15
20
25
30
35
Velocity (ft/sec)
Po
we
r re
qu
ire
d (
ft-l
bf/
se
c)
Aircraft Power required vs trim speed for a turn radius of 100 ft
Minimum power of 10.9465 ft-lbf/sec is achieved at a speed of 28 ft/sec.
The lift coefficient at this minimum power condition is 1.6553.
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Endurance Flight• D = 16in• RPM = 2355• Pitch = 10 deg
• ηp = .77
• Pout = 11.1 ft-lbf/s• Pin = 14.04 ft-lbf/s• CT = .0293• CP = .0227• J = .6
0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.80
0.05
0.1
Th
rus
t C
oe
f, C
T
Data for hypothetical propeler with tau=p/D=.631
CT*= 0.0293 for J*= 0.6
0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.80
0.02
0.04
Po
we
r C
oe
f, C
P
CP*= 0.0227 for J*= 0.6
0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.80
0.5
1
Eff
icie
nc
y,
eta
Advace ratio, J=V/(nD)
Eta*= 0.77445 for J*= 0.6
X is the selected operating point
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High Speed Flight
• Vmax = 130 ft/s
• Power = 268.5 ft-lbf/s• Cl = .4
0 20 40 60 80 100 120 1400
50
100
150
200
250
300
350
Velocity (ft/sec)
Po
we
r re
qu
ire
d (
ft-l
bf/
se
c)
Aircraft Power required vs trim speed for a turn radius of 100 ft
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High Speed Flight
• D = 10 in• RPM = 15217• Pitch = 6.25 deg
• ηp = .77
• Pout = 268.5 ft-lbf/s
• Pin = 334.9 ft-lbf/s
• CT = .0293• CP = .0227• J = .6
0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.80
0.05
0.1
Thr
ust
Coe
f, C
T
Data for hypothetical propeler with tau=p/D=.631
CT*= 0.0293 for J*= 0.6
0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.80
0.02
0.04
Pow
er C
oef,
CP
CP*= 0.0227 for J*= 0.6
0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.80
0.5
1
Eff
icie
ncy,
eta
Advace ratio, J=V/(nD)
Eta*= 0.77445 for J*= 0.6
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15
Motor Selection
• Kontronik Fun 480-42 40A Brushless Motor – Diameter: 1.1 in– Length: 1.9in– Weight: 5.1oz – Number of Cells Input: 6-
12 – RPM/Volt: 4200 – Max RPM: 60,000 – Max Constant Current: 40A
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Speed Controller
• Kontronik Jazz 40-6-18 Brushless ESC– Number of Cells Input: 6-18
– Max Constant Current: 40A
– Max Surge Current: 50A
– Length: 1.9" (49mm)
– Width: 1" (25mm)
– Thickness: 0.29" (7.5mm)
– LiPo cut off voltage: 3V/cell
– Weight: 1.16oz (33g)
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17
Gear Box
• Gear Ratio of 2.33• Gear efficency of .96
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Mission Analysis
• Prelimary battery weight - .22lbs
• Necessary Battery– Lipo 3000 mAh– 1.2 V per cell– 2 cells– Weight .3lbs– Range 17min
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Mission Analysis
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• Questions?