INTEGRATION OF EXPERIMENTAL

PROPULSION SYSTEMS IN

MICRO AIR VEHICLES

Deliverable: Interim DesignNovember 9, 2010

Team # 3

Erica Cosmutto

Hunter Metzger

Joel Ware

Kristina De Armas

Michael Isaza

Santiago Baus

OVERVIEW Introduction EDF vs Propeller Final Component Selection IE Update Calculated Values Designs Center of Gravity Cost and Weight Analysis Conclusion Future Work

INTRODUCTION

Integrate an electric ducted fan into the fuselage of a Micro Air Vehicle (MAV)

Focus on:Fuselage designAir Flow Inlet/Duct design Integrating electronics and fan into the

fuselage Constraints:

10 lb max6 in diameter32 in length

EDF VS PROPELLER FAN Duct reduces losses in thrust caused by

tip vortices The Ducted fan operated at higher

velocity EDF has a smaller diameter EDFs are quieter and safer

FINAL COMPONENT SELECTION

76mm ID, 80mm OD22.2V391g55A

$129.50

TP8000-6S4PL22.2V8000mAh16C

$509.99

Smart Guide ESCUp to 44.4V100A

$120.00

IE UPDATE Lean Six Sigma Methodology

DMAIC process Define Phase Complete Measure Phase due November 30th

Define performance standardsEstablish data collection planValidate the measurement systemCollect necessary data from existing system

VALUES CALCULATED

Maximum Thrust of 2.2 kg =21.6 N Ideal Inlet Area= 5.643 in2 (FSA, Fan Sweep

Area) Ideal Exit Area=4.3 in2 (75% of FSA) Maximum Velocity Exiting Fan=52.478 m/s

DESIGN 1

Design specified by sponsor Intake from the bottom of the MAV

DESIGN 2

Intake on top and bottom Laminar flow off top surface

DESIGN 3

Maximize flow intake Simple design

DESIGN 4

Uses two side ducts Smooth intake of air

CENTER OF GRAVITY

ESC110g Battery

932gFuselage3084g

Fan391g

Desired

CG

CurrentCG

1.92 in

COST AND WEIGHT ANALYSISComponent Cost Weight

EDF $129.95 .862 lbs

Battery $509.99 2.05 lbs

Battery Charger $109.98

Woodworks LipoSack (Storage)

$34.99

ESC $120.00 .242 lbs

Transmitter/ Receiver

$179.97 .033 lbs

Industrial Strength Velcro

$7.00

TOTAL $1091.88 3.187 lbs

CONCLUSION Four fuselage designs Initial Calculations and Analysis Calculated Ideal Inlet and Outlet Areas Center of Gravity Analysis Final Component Selection The team has started work at HPMI

FUTURE WORK Continue work at HPMI Produce the first mold Receive Components Testing in Comsol and wind tunnels Measurement of Existing Model

REFERENCES Hobbypartz.com Thunderpowerrc.com Hobbytown.com “The Calculation and Design of Ducted

Fans”.Wattflyer.com www2.nlr.nl/public/facilities/AVET-Info/

Content/UK/PropBlades.html www.sterndrive.info/

400_800_cobra_propellers.html

Calculations:

Given Thrust of 2.2kg

Thrust 2.2kg g

Thrust 21.575N

Power calculations:

I 60A Volt 22.2V Assuming 100% efficient

P I Volt P 1.332 103 W

Velocity Calculations:

Thrust mdot Vel

P Thrust Vel

VelP

Thrust Vel 61.739

m

s Ideal Velocity capable from fan

electric 0.85 electric power to shaft output

Vexit electric Vel

Vexit 52.478m

s Velocity of air leaving fan

Exit Area Calculations:

As a rule when working with EDFs the exit area of the flow needs to be 70-85% of the FanSwept Area(FSA). For these calculation we use 75%.

Dfan 76mm Dhub 33.77mm

Afan

Dfan

2

2

Ahub

Dhub

2

2

FSA Afan Ahub

FSA 3.641 103 m

2 FSA 5.643in2

Aexit FSA 0.75

Aexit 2.731 103 m

2 Aexit 4.232in2

Dexit 4Aexit

Dexit 2.321in

Dexit mm

Calculations:

Inlet Area Calculations:

Ideally the inlet area would equal the Fan swept area. An ellipse would be the best intake areabecause it is very aerodynamic shape.

Aellipse FSA

Aellipse Aw Bl

Bl 2 Aw

Aellipse 2 Aw2

Aw

Aellipse

2

Aw 0.948in Bl 2 Aw Bl 1.895in

need an ellipse with a major axis of 3.79 in and a minor axis of 1.895 in, giving us 99.96% ofFSA for an inlet area.

Velocity Exiting Duct*:

To find the velocity at the end of this duct use mass conservation:

A1=area right after fan A2=exit area

A2 AexitD1 76mm

V1 VexitA1

D1

2

2

A1 7.032in2

A1 4.536 103 m

2

V1 A1 V2 A2

V2

V1 A1

A2

V2 87.185m

s *Velocity of air leaving fuselage with this geometry, if in a vaccum, at full

power, neglecting all friction and resistance.

More Realistically Closer to V.exit.

Vexit 52.478m

s