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MINIATURE UNMANNED AERIAL VEHICLE. Team MUAV 2. The Project. Goals: To design and manufacture a relatively cheap, feasible and revolutionary aircraft with versatile control capabilities. Flight Lift off & Landing Propulsion for added flight time Stability & Control
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The Project • Goals: To design and manufacture a relatively cheap, feasible and revolutionary aircraft with versatile control capabilities. • Flight • Lift off & Landing • Propulsion for added flight time • Stability & Control • Powerful Maneuverability • Air Flow through counter-rotating ducted fans • Gear & Cam System • Wireless/Remote Control System • User Friendly GUI • - Integration of Electronic Devices
Limitations • Monetary • - Knowledge & Experience • - Facilities (construction & testing) • - TIME
Current Project Status • As of this date, we feel that we have studied the pros and cons of different MUAV designs enough to decide on a particular design. • This design is to be considered our current Frozen design. • We have purchased the pusher and tractor props for the MUAV and will be obtaining our engine within this week. • We are currently working towards developing a complete mathematical analysis of each sub-assembly. • This is to enable us to understand the innermost working of the different assemblies.
Front View Tail View
Exploded Design Views – Different Sub-Assemblies LGA CFA SWA RFA
Central Fan Assembly - CFA CFA standalone shaft CFA standalone shaft explosion
(m, U, p, A)1 3 4 (m, U, p, A)4 Central Fan Assembly - CFA Basic Principles and Assumptions • Isentropic Flow • Incompressible Flow (except at fan) • MUAV is moving at relatively low speeds • Exit flow exhausts to ambient pressure • Change in temperature is negligible • Change in height is negligible • There is no heat addition Control Volume 1 2
Conclusion • By substituting equation (8) into equation (5) for V4 we get thrust as a function of power, if the density, exit area and mass flow rate are known. (9)
MINIATUREUNMANNEDAERIALVEHICLE Central Fan Assembly - CFA Theory – Vibration Analysis & Stability m1 F CM l1 g θ l2 m2 g
MINIATUREUNMANNEDAERIALVEHICLE Central Fan Assembly - CFA Theory – Vibration Analysis & Stability Linear Momentum Equation: Angular Momentum Equation: Frequency of Oscillations:
MINIATUREUNMANNEDAERIALVEHICLE Central Fan Assembly - CFA Theory – Vibration Analysis & Stability • Conclusion: • As m2l2 m1l1, motion ∞ • Stability m1l1 m2l2
Central Fan Assembly - CFA Gearing Calculations
MINIATUREUNMANNEDAERIALVEHICLE Central Fan Assembly - CFA Gearing Calculations Bevel Gears Tooth Load: W = SFY 600 (.75) P 600 + V S = Safe Material Stress F = Face Width (in.) Y = Tooth Form Factor P = Diametral Pitch D = Pitch Diameter V = Pitch Line Velocity Safe Horsepower : HP = W V 33,000 Gear Thrust : T = 126,050 x HP tan a cos b RPM x D
MINIATUREUNMANNEDAERIALVEHICLE Central Fan Assembly - CFA Gearing Calculations Maximum Values
Rear Fan Assembly - RFA Stepper Motor Rudder Shaft Rear ducted Fan Rudder
Rear Fan Assembly - RFA Weight: 73 gramsDuct Diameter: 63.9mm (2.52") Info from http://www.balsapr.com
(0, r, 0) (z) (0, 0, 0) (y) (0, -r, 0) (x) (r, 0, -h) (2r) (h) Rear Fan Assembly - RFA Incoming air into duct
Rear Fan Assembly - RFA • The length and rudder curvature calculations were performed on the semi-cylindrical portion of the external add-on duct. • Using the three point form of the equation of a plane, the equation of the frustrum is derived to be hx + rz = 0 • Finally parametrizing the curve and placing the curved surface such that it is located in a amore convenient plane, we get:
Rear Fan Assembly - RFA L • The length of the tongue (measured down the center of the face) could then be obtained by setting t = r. Further calculations would provide the best duct to rudder fit contour to prevent the loss of thrust due to loss of air moving through the rudder cross-section.
Landing Gear Assembly - LGA • Engine Support • Holds the engine in place • Prevents vibration • 222 Fiberglass Composite • 1/4 “ Foam Core • Attached to vehicle with strong composite adhesive
Landing Gear Assembly - LGA • Vehicle Support • Supports entire vehicle • Balsa wood rods wrapped in 222 Fiberglass composite • Flat Composite plate at end for attachment • Spongy Material at bottom end for cushioned landing • 3 rods spaced 120 degrees apart at equal distances • Attached to vehicle with strong composite adhesive
Stress calculation in vehicle support Landing Gear Assembly - LGA W 15o 7/16” Dia L Wy Cross-section Wx 75o R
Landing Gear Assembly - LGA Wy Resolve weight and reaction forces into axial components for stress analysis Wx L Rx Ry
Landing Gear Assembly - LGA Material Choices
Shroud & Wing Assembly - SWA Shroud Aerodynamics
Shroud & Wing Assembly - SWA Shroud Aerodynamics • Test to find the experimental lift and drag coefficients of the outer shroud.
Shroud & Wing Assembly - SWA Shroud Aerodynamics • Summary of Lift and Drag data collected for an angle of attach of zero at different free-stream velocities and Reynolds numbers.
Shroud & Wing Assembly - SWA Materials • Carbon-Fiber composite for outer body • will withstand tensile and bending loads • provide an outer aerodynamic surface • Foam for inner body • will withstand shear forces • will also hold the internal components in place
Communications Circuitry Camera Assembly Microcontroller Circuitry
MINIATUREUNMANNEDAERIALVEHICLE We Got Power!! • Battery Supply #1 (Onboard Electronics) • VARTA 9V Ni-MH Rechargeable • 150 mAh, 46 grams • Battery Supply #2 (Rear Fan Assembly) • Kokam 7.4V Li-Poly Pack • 1500mAh, 81grams AMAZING!!! • Can deliver up to 12A continuously • Sensors • MAX 1259 Battery Monitor • Power Control • 7800 Series Regulators • 7805 for electronics (+5V) • 7812 for communication devices (+12V) • Maintenance • Battery Charger NB:- A small circuit board will incorporate all IC’s and other electronic components.
Engine is Fuel Powered 2 Separate Battery Packs High Flexibility. Best suited for ECE & MAE Teams MINIATUREUNMANNEDAERIALVEHICLE The Power Grid
Feedback Device - Camera St 100
Forward Thrust Back Flaps to the left Back Flaps to the right Up Down User Interface
Plan and Schedule • Major Tasks Completed • Concept of Final Design • Final Design CAD Drawings • Components • Thrust Factor • Hand-drawn Sketches of Final Design • Sponsorship Letter • Acquisition of room for MUAV Design Project purposes • Minor Tasks Completed • Updated Budget • Updated Gantt Chart
Plan and Schedule • Major Upcoming Tasks • Acquire sponsorships • Completed Mathematical Model • Acquire parts • Building of Prototype MUAV craft • Minor Upcoming Tasks • Machine Shop Training