Integration of experimental propulsion systems in micro air vehicles

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Presentation transcript:

Integration of experimental propulsion systems in micro air vehicles Deliverable: Interim Design November 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 design Air Flow Inlet/Duct design Integrating electronics and fan into the fuselage Constraints: 10 lb max 6 in diameter 32 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 OD 22.2V 391g 55A $129.50 TP8000-6S4PL 22.2V 8000mAh 16C $509.99 Smart Guide ESC Up to 44.4V 100A $120.00

IE Update Lean Six Sigma Methodology Define Phase Complete DMAIC process Define Phase Complete Measure Phase due November 30th Define performance standards Establish data collection plan Validate the measurement system Collect 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 1.92 in Desired CG Current CG ESC 110g Fan 391g Battery 932g Fuselage 3084g

Cost and Weight Analysis Component 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_propell ers.html

Calculations: