INTEGRATION OF EXPERIMENTAL

PROPULSION SYSTEMS IN

MICRO AIR VEHICLES

Deliverable: Interim DesignNovember 9, 2010

Team # 3Erica CosmuttoHunter Metzger

Joel WareKristina De Armas

Michael IsazaSantiago 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 WeightEDF $129.95 .862 lbsBattery $509.99 2.05 lbsBattery Charger $109.98Woodworks LipoSack (Storage)

$34.99

ESC $120.00 .242 lbsTransmitter/ 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 2.2kgThrust 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

ms

Ideal Velocity capable from fan

electric 0.85 electric power to shaft output

Vexit electric Vel

Vexit 52.478ms

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

AfanDfan2

2

AhubDhub2

2

FSA Afan Ahub

FSA 3.641 10 3 m2 FSA 5.643in2

Aexit FSA 0.75

Aexit 2.731 10 3 m2 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

AwAellipse2

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 areaA2 AexitD1 76mm

V1 VexitA1D12

2

A1 7.032in2 A1 4.536 10 3 m2

V1 A1 V2 A2

V2V1 A1

A2

V2 87.185ms

*Velocity of air leaving fuselage with this geometry, if in a vaccum, at fullpower, neglecting all friction and resistance.

More Realistically Closer to V.exit.

Vexit 52.478ms