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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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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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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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?

Documents

Propulsion PDR