RIT Micro Air Vehicle Preliminary Design Presentation Joshua Baker - PowerPoint PPT Presentation

RIT Micro Air Vehicle Preliminary Design Presentation Joshua Baker Tzu-Chie Fu Cuong Le Mechanical Engineering Computer Engineering Computer Engineering Aaron Grilly Atul Phadnis Mechanical Engineering Electrical Engineering David Hein Aimee Lemieux Mechanical Engineering Mechanical Engineering J.E.D. Hess Victoria Schoennagel Mechanical Engineering Mechanical Engineering Brian Gillis Dr. Jeffrey Kozak Team Leader Team Advisor Mechanical Engineering Mechanical Engineering RIT MAV Team Project 05-001 2004-2005

Outline I. Background II. Design Objectives III. Work Timeline IV. Airframe Selection V. Electronics Selection VI. Propulsion Selection MAV Team 05-001 Airframe Electronics Propulsion Joshua Baker Cuong Le Aaron Grilly Aimee Lemieux Tzu-Chie Fu David Hein Victoria Schoennagel Atul Phadnis JED Hess RIT MAV Team Project 05-001 2004-2005

Background • According to DARPA, a Micro Air Vehicle (MAV) has a maximum linear dimension of 6 inches. • Primarily being researched for surveillance and reconnaissance operations. • Other possible uses include forest fire detection, Bio- Chemical detection, etc. • Annual MAV competition where various teams compete in surveillance missions and flight performance tests. RIT MAV Team Project 05-001 2004-2005

Design Objectives • Vehicle with a minimum linear dimension of 15 inches • Vehicle can be scaled down in size and still produce acceptable flight • Vehicle must be a new design, not rely on last year’s design • Airframe should be built out of composite materials if deemed reasonable • Vehicle must have GPS navigation capabilities along with video surveillance • Performance Goals – 15 Minutes of flight time – 600 Meter range • Attend International MAV Competition in Seoul, Korea • Remain within $3,000 budget (excluding travel funding) RIT MAV Team Project 05-001 2004-2005

Work Timeline RIT MAV Team Project 05-001 2004-2005

Work Timeline RIT MAV Team Project 05-001 2004-2005

Airframe Selection RIT MAV Team Project 05-001 2004-2005

Airframe Main Objectives 1. Flying Wing Configuration 2. Modular Design 3. Maximum Linear Dimension of 15 Inches 4. Research and Test Unconventional Ideas 5. Scalable Platform Upon Which to Base Future Designs RIT MAV Team Project 05-001 2004-2005

Airframe - Airfoils • MH46 • MH46 • • E174 E174 • RAF6 • RAF6 • • E186 E186 • S1210 • S1210 • S1210 • • EH2012 EH2012 • S2027 • S2027 • • EH3012 EH3012 • S4022 • S4022 • S4022 • • FX63-137 FX63-137 • S4083 • S4083 • S4083 • • • GOE417a GOE417a GOE417a • S5010 • S5010 • • M10 M10 • S5020 • S5020 • • M12 M12 • SD7080 • SD7080 • • M14 M14 XFLR5 Testing (Computer Simulation) Survived First Round of Cuts To Be Tested in the Wind Tunnel RIT MAV Team Project 05-001 2004-2005

GOE417a S1210 S4022 S4083 RIT MAV Team Project 05-001 2004-2005

XFLR5 Data - Cl vs. Angle of Attack for Airfoils at Reynolds Numbers 2.50 2.00 1.50 Cl (Dimensionless) 1.00 0.50 GOE417a, 100,000 0.00 S1210, 100,000 S4022, 100,000 -0.50 S4083, 100,000 -1.00 -10 -5 0 5 10 15 20 Angle of Attack (Degrees) RIT MAV Team Project 05-001 2004-2005

Airfoil Feasibility Assessment E v a lu a tio n o f e a c h c o n c e p t a g a in s t th e b a s e lin e : t ht gh 1 = m u c h w o rs e th a n b a s e lin e ig ei 2 = w o rs e th a n b a s e lin e We W GOE417a 3 = s a m e a s b a s e lin e FX63137 e EH2012 EH3012 SD7080 ve 4 = b e tte r th a n b a s e lin e iv S1210 S2027 S4022 S4083 S5010 S5020 MH46 RAF6 ti E174 E186 5 = m u c h b e tte r th a n b a s e lin e at M10 M12 M14 la el Re R Lo ow w R R ey y no ol ld ds s n nu u m be er r a ai ir rf fo oi il l 8 % L e n m b 3 .0 3 .0 3 .0 2 .0 1 .0 5 .0 3 .5 1 .0 2 .0 3 .0 1 .0 5 .0 3 .0 5 .0 5 .0 4 .0 5 .0 4 .0 K no ow w n p pr ri io or r u us se e o on n a an n M M A V 1 1 % K n n A V 1 .0 1 .0 3 .0 3 .0 1 .0 5 .0 1 .0 1 .0 1 .0 4 .0 1 .0 5 .0 1 .0 4 .0 5 .0 4 .0 4 .0 3 .0 M an nu uf fa ac ct tu ur ri in n g e ea as se e a an nd d a ac cc cu ur ra ac cy y 6 % M a g 3 .0 3 .0 3 .0 3 .0 3 .0 5 .0 3 .0 3 .0 3 .0 3 .0 4 .0 4 .5 3 .0 4 .5 4 .0 4 .0 3 .5 4 .0 M an nu uf fa ac ct tu ur ri in n g t ti im m e 0 % M a g e 3 .0 3 .0 3 .0 3 .0 3 .0 3 .0 3 .0 3 .0 3 .0 3 .0 3 .0 3 .0 3 .0 3 .0 3 .0 3 .0 3 .0 3 .0 R ea as so on na ab bl le e c ca am m be er r ( (1 1% % -8 8% % ) 1 1 % R e b - ) 3 .0 1 .0 1 .0 1 .0 1 .0 4 .0 1 .0 1 .0 3 .0 2 .5 1 .0 5 .0 2 .0 4 .0 5 .0 2 .0 2 .0 2 .0 So S o m m e e r re ef fl le ex x i in n d de es si ig gn n 1 4 % 1 .0 4 .0 3 .0 3 .0 1 .0 2 .0 3 .0 2 .0 3 .0 3 .0 1 .0 2 .0 2 .0 3 .0 3 .0 3 .0 4 .5 2 .0 R R ea e as so on na ab bl le e, , l lo og gi ic ca al l g gr ra ap ph hs s ( (X XF FL LR R 5) 5 ) 3 1 9 % .5 3 .0 3 .5 3 .5 3 .0 2 .0 2 .0 3 .5 3 .0 3 .0 4 .0 5 .0 3 .0 4 .0 5 .0 3 .0 3 .0 4 .0 C /C C 1 9 % C l / d 3 .5 3 .0 3 .0 3 .0 4 .8 5 .0 2 .0 2 .8 3 .2 3 .0 3 .0 5 .0 3 .5 5 .0 4 .8 3 .0 3 .0 3 .0 l d C 1 1 % C m 3 .0 1 .0 3 .0 2 .0 4 .9 3 .0 2 .0 3 .0 3 .0 3 .0 2 .5 3 .0 3 .0 4 .6 5 .0 3 .0 3 .0 3 .0 m W ei ig gh ht te ed d S Sc co or re e W e 2 .7 2 .5 2 .9 2 .7 2 .7 3 .7 2 .1 2 .3 2 .7 3 .1 2 .3 4 .3 2 .6 4 .2 4 .6 3 .1 3 .4 3 .1 N N o or rm m al a li iz ze ed d S Sc co or re e 5 8% 5 3% 6 2% 5 8% 5 8% 7 9% 4 5% 5 0% 5 9% 6 6% 5 0% 9 4% 5 7% 9 1% 1 0 0% 6 8% 7 4% 6 7% GOE417 S4083 S1210 S4022 A irfo il a N o rm alized S co re 100% 94% 91% 79% R elative R an k 1 2 3 4 RIT MAV Team Project 05-001 2004-2005

Airframe - Planform • Rectangular • Zimmerman • Inverse Zimmerman • Circle/Elliptical • Modified Inverse Zimmerman • Most Likely Design: Straight Leading Edge Approximation of the Inverse Zimmerman Planform RIT MAV Team Project 05-001 2004-2005

Airframe - Composition • Balsa Wood with Canvas • Foam (Polystyrene) • Foam with Single Fiberglass Layer • Carbon Fiber • Carbon Fiber with Lightening Holes • Composite (Kevlar, Fiberglass) • Foam and Fiberglass Combination will be Used for Testing, Composition of Final MAV Airframe Still to be Determined RIT MAV Team Project 05-001 2004-2005

Airframe – Pod Location • Mounted Above Wing • Mounted Below Wing • Between Bi-Wing • Suspended Below Wing • Most Likely Design: Mounted Below Wing RIT MAV Team Project 05-001 2004-2005

Airframe – Control Surfaces • Options Considered – Vertical Tail (and Elevator) • Single (High or Low Orientation Possible) • Double (High or Low Orientation Possible) • Angled Vertical Tail – Winglets • Vertical Winglets • Angled Winglets – Canards – Elevators – Ailerons – Elevons • Current Approach: V-Tail Protruding from Pod, Extending Beneath Wing. Elevator to be Integrated if Necessary RIT MAV Team Project 05-001 2004-2005

Future Analysis • Test Airfoils • Control Surface Sizing and Location • Airframe Prototype (March 14 th ) • Refine Design • Evaluate and Test Radical Ideas RIT MAV Team Project 05-001 2004-2005

Electronics Selection RIT MAV Team Project 05-001 2004-2005

Full System Design RIT MAV Team Project 05-001 2004-2005

Components • Onboard RF Controller/Receiver • Onboard Speed Controller • Onboard Servos (Actuators) • Onboard Video System – Video Transceiver & Camera • Passive Antenna Array • Onboard GPS System – Onboard GPS Receiver – Onboard GPS Video Overlay Board • Batteries RIT MAV Team Project 05-001 2004-2005

Onboard RF Controller/Receiver • RF Controller Selected: – Futaba 6YGE 72 MHz RF Controller • Onboard RF Receiver Selected: – GWS NARO R-6NH/V Receiver • Channels: 6 • Size: 20 x 30 x 9.5 (mm) • Weight: 8.8 g We selected the GWS NARO R-6N receiver due to its 6 channel design. This allowed for improvements in the form of additional onboard feature/control devices. Compatibility of the controller/receiver has been verified since both use the Futaba data transmission format. RIT MAV Team Project 05-001 2004-2005

Onboard Speed Controller • Onboard Speed Controller Selected: – Phoenix-10 The Phoenix-10 speed controller is the leading candidate to be chosen due to its compatibility with the DC motor that is being recommended by the propulsion subgroup. RIT MAV Team Project 05-001 2004-2005