Fuel Cell UAV 2016 PROJECT ADVISORS DR. ZHANG AND DR. DEMUREN TEAM LEAD MARYAM AMER MAE TEAM MEMBERS MITCH DEIGHAN COREY GUILBAULT KRISTA SAUNDERS JOHN SHAW RYAN DUDLEY GASTON GATETE COLBY HENSON BRADLEE GARANT GEORGE PORTILLIO

Overview Project Background Project Schedule Project Budget Design Summary Airframe Catapult Fuel Cell Flight Management Flight Tests Future Work

Project Background Limited Life Expectancy of Battery during flight Fuel cells provide the potential for long range flight performance Proof of Concept Mission -Traditional aircrafts are loud. -Batteries are heavy and to get longer duration, you need a larger battery. A fuel cell allows you to increase duration by increasing the amount of hydrogen -On a small scale it is more difficult to use a fuel cell due to the initial weight of the fuel cell. On a larger scale the weight of the fuel cell has less of an effect on performance. -This proof of concept mission allows us to show that a fuel cell is also relevant for small UAVs and can increase the flight duration of UAVs

Project Budget Proposal : $3625 Received: $1000 from College of Engineering $190 from Electrical and Computer Engineering $250 from Mechanical and Aerospace Engineering Budgeted Spent Remaining Airframe 740 $722.73 $17.27 Fuel Cell 500 $261.52 $238.48 Catapult 200 $157.44 $42.56 Total Budget $1,440.00 $298.31

Design– Airframe Skywalker X8 Flying Wing High Volume Fuselage No tail, theoretically more efficient than tradition planform. Could it work?

Design– Airframe Unique airframe and airfoil shape Published data limited Resorted to modeling XFLR5 (Airfoil, Wing theory) Helpful, but to many shortcomings No Drag No Dimensions CFD (Navier-Stokes based) Better drag estimate Accurate model

Design– Airframe Internal Layout Conclusion: flight feasible Based on L/D ratio Airflow to Fuel Cell Cooling Stability Conclusion: flight feasible ~130 Watts sustained 3 Purchased and Assembled

Design– Catapult Purpose: Provide power to support added weight Consistent launch for pilot convenience Iterative design process Prototype Design and initial build Test Launch unweighted and weighted airframe Analyze Identified improvement areas Support Material Reinforcement at joints Power Launch mechanism Refine

Fuel Cell Horizon H-100 Fuel Cell 100 W Weigth: 1.8 kg Capacity: 10 L 1 HydroSTIK = 10 AA batteries Venom 20C 3s Battery and E-flight 3s for flow rate controller

Fuel Cell Testing Power Output

Hybrid System Design Power Management (Fuel Cell and battery will run in parallel)

Design – Flight Management Initial Pilot Training Started with Parrot AR Drone Quadricopter 2.0 Transitioned to ParkZone Ember 2 RTF Aircraft Controlled flight Piloting in confined space Practiced landing Helped us gain a greater feel for the controls Practiced with Phoenix RC Pro Simulator Quadcopter Ember Drone Delta Wing Simulator Delta Wing

Flight Tests Summary Basic Testing Catapult Launch Testing Accurate Load Catapult Testing Fuel Cell Integration Testing Flight Demo Basic Testing Simple hand launch Catapult Launch Testing Stable take off Accurate Load Testing Flight handling Fuel Cell Integration Testing Data Experimentation Final Flight Demonstration Performed flight tests with hand launching Simplicity Performed flight tests with catapult launching Steady take off Performed flight tests with added weight to simulate the additional weight of the Fuel Cell The fuel cell and required components would add …..grams to the planes weight. Weight was incrementally added by using……

Future Work Catapult Airframe Fuel Cell Flight Management Potential Larger Motor? Using thrust stand data Potential Test Parachute Fuel Cell Flight Management

Questions?