RIT MAV System Review (P08121) Dr. Jeffrey Kozak – Faculty Guide Michael Reeder – Team Leader Kevin Hand – Lead Engineer Todd Fernandez – ME Susan Bieck – ME Jeremy Teets – ME Cody Rorick – ME Adam Bosen – CE …where the sky is only the beginning… …and the ground is likely the end… Sponsored By:

Re-Introduction of Team Members Mike Reeder Kevin Hand Sue Bieck Jeremy Teets Adam Bosen Todd Fernandez Cody Rorick

Project Description/Customer Needs Primary Objective:  Create a Micro Aerial Vehicle, expandable in nature for future RIT research  Simple, robust and stable in design  Capable of reading back information regarding the vehicle’s speed, angle of attack, pitch, yaw and roll rates  Flight Dynamics competition (held internationally) establishes target specifications (engineering metrics) Max linear dimension is 80 cm Max weight is 1 kg Required flight time is 4 minutes Secondary Objective:  Compete in international Flight Dynamics competition

Objective of RIT MAV Platform design decided upon Engineering metrics/product specifications completed List of components and materials compiled 3-D CAD model of plane created (XFOIL, Pro-E, etc.) Foam model built based on concept generations Experiments designed to test components’ proper functionality Components ordered/in team’s possession Components in possession are in test process Foam plane is built and glide tested

Objective of RIT MAV

Selected Concept

Selected Concept – Airfoil Selig S1210 airfoil chosen for:  Weight range ( g)  Efficiency at various AOA’s  Speed range (15mph+)

Selected Concept – Propulsion System Esskay 400XT  1.5 oz brushless motor  Allows for several prop sizes to achieve various speeds Thunder Power TP9103  3 cell configuration  910 mAh **Several props will be bought and tested to determine optimal speed of the MAV**

Selected Concept – MAV Design MAV design based on:  Brainstorming sessions  Feasibility analyses  Flight dynamics calculations (reference) Chosen design utilizes  Stream-lined cylindrical fuselage  Fuselage designed to incorporate airfoil into body  Symmetrical rear airfoil

Selected Concept – Flight Dynamics Flight dynamics calculations led to a series of calculations to determine stability of aircraft Calculations also aided in determining proper rear tail dimensions  Horizontal tail span – 10 in  Vertical tail span – 5 in  Horizontal & vertical tail chord – 4 in  Moment arm of the tail – 17 in

Selected Concept – CAD Generated Model

Selected Concept - Controls Main component to be used is O-Navi microcontroller  Contains angular accelerometer, GPS, among others  Use of microcontroller will enable complex information to be sent to and received from MAV  Paparazzi considered for software architecture Pressure transducers (velocity, AOA) Servos (flight control)

Selected Concept – Design of Experiments Differential pressure sensor used in conjunction with a pitot tube to determine aircraft velocity One differential pressure sensor on each wing to determine pressure difference which will yield AOA experimentally Angular/Linear accelerometers used to determine pitch, roll and yaw of aircraft during flight LabVIEW, LabVIEW, LabVIEW!!!

Selected Concept – User Interface Utilize LabVIEW to create interface:  Altitude  Velocity  Pitch  Roll  Yaw Example shown

Risk Assessment

Tentative Bill of Materials (BOM) Tentative BOM is shown to the right Impact Technologies has generously donated $1, to the MAV Senior Design effort for 2008.

Completed Objectives – MSD I Platform design decided upon – COMPLETED Engineering metrics/product specifications completed – COMPLETED List of components and materials compiled – COMPLETED 3-D CAD model of plane created (XFOIL, Pro-E, etc.) – COMPLETED Foam model built based on concept generations – COMPLETED (1 st run model) Experiments designed to test components’ proper functionality – WIP Components ordered/in team’s possession – WIP Components in possession are in test process – WIP Foam plane is built and glide tested – WIP (airfoil creation)

Tentative Schedule for MSD II - Completion of blank plane (red) - Component testing (yellow) - System integration of components (orange) - Integration of system into ground model (green) - Flight tests (light blue and blue) - Base station data retrieval (purple) - MAV system integration (light green) - Completed project flight testing (gray)

Remember…

Q & A