1. 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

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

3. 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

5. 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

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

7. 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

8. 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

9. 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

10. 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

11. Fuel Cell Testing
Power Output

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

13. 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

14. 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……

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

16. Questions?