1 1 1 AAE Aircraft Senior Design TEAM III Sumitero (Calvin) Darsono Charles Hagenbush Keith Higdon Seung-il Kim Matt Lewis Matt Richter Jeff Tippmann Alex Zaubi

2 2 2 Presentations Outline 1. Mission Statement 2. Business Case and Target Markets 3. Concept of Operations 4. Major Design Requirements 5. Aircraft Concept Selections 6. Components – Camera, Avionics, Fuel Cell 7. Power Plant 8. Aircraft Sizing: Constraint Diagram 9. Conclusion

3 3 3 Mission Statement To provide a continuous aerial coverage using an UAS that is small, light, portable and allows rapid deployment

4 4 4 Market Military Surveillance around temporary base Forward reconnaissance Law enforcement and emergency services Surveillance in assessing hazardous situations before committing personnel UAS Providing Continuous Coverage for Small Operations Business Case Small portable UAS Rapid deployment and coverage Multiple aircraft in system Little support equipment Product is entire system # of planes Laptops Communication equipment Visual or IR Sensors Storage equipment Evolution XTS – L3 BAI Aerosystems

5 5 5 Description of Customer - Military Military Highlights Deployed with squadron Launched from location by hand Monitor area of interests around operations, 5-10 mile range Recognize vehicles and enemy combatants Do not need high resolution of plate numbers, faces 2-4 planes Design to be transported by backpack, though Humvee will probably be sufficient Elbit Skylark IV (Israel) Aerovironment Raven

6 6 6 Description of Customer – Law Enforcement Law Enforcement Highlights Deployed with SWAT team Launched from location by hand Monitor area of interests around operations, 5-10 mile range Recognize vehicles, people Do not need high resolution of plate numbers, faces Chemical Spill/ Radiation Monitor Search for suspect drug manufacturing Monitor hazardous chemical spill/ radiations Crowd control Monitor peaceful protest 1-2 to planes Designed to be transported in vehicle Octran SkySeer Raider Marauder

7 7 7 Current Market Military As of 2005, over 800 small UA Systems planned Over 2500 aircraft Market is Growing Armed Forces to spend $20M a year for the next 3 years on small UA Systems Canada and Great Britain looking to obtain similar systems Law Enforcement Ideally, each police station could have one UAV “It (UAV) provides several things that we can't get other ways,” quoted Commander Heal of Los Angeles Sheriff Department

8 8 8 Major Design Requirement Small and light weight aircraft - limited by hand launch requirement, payload weight Endurance – limited by the battery, powerplants Range – limited by battery and communication relay, power plant Payload Weight – limited camera, lens, avionics Power - Fuel cell Energy Density depends on the weight of the aircraft. Fuel cell will be used due to lower weight and higher energy density available Parameters Units Weight10lbs Endurance4hrs Range 5miles Payload Weight 2 lbs Weight Fraction0.4 W e /W o Energy Density350 W-hr /kg Aerovironment - Raven

9 9 9 Aircraft Concept Selection

10 Aircraft Concept Selection Hybrid 1 V-Tail, 2-props Note: Aircraft is not drawn to scale

11 Aircraft Concept Selection Hybrid 2 V-Tail, forward prop Note: Aircraft is not drawn to scale

12 Payload – Camera Core Camera Photon OEM Core IR Camera 320x240 Long Wavelength Manufactured by FLIR System Frame Rate = 30 Hz (320X240) Autonomous and manual camera operations Minimum Power Consumption ~1.5W Weight (~0.27 lbs) Camera Core = 0.21 lbs Rear Cover = 0.03 lbs Universal Lens Holder = 0.03 lbs Dimensions 2.0 x 2.0 x 1.8 in Camera Core of Photon OEM Photon OEM with Lens

13 Payload – Camera Lens Lens Two lens are considered Focal Length 35.0mm 20 o HFoV f/1.4 Weight = lbs (including lens mount) Total Camera Weight = 0.47 lbs Optimum for operations up to 1000 ft Focal Length 50.0mm 14 o HFoV f/2.0 Weight = 0.28 lbs (including lens mount) Total Camera Weight = 0.56 lbs For operations greater than 1000 ft OEM Photon with 50.0mm Lens OEM Photon with 35.0mm Lens Projected Results Obtained from the Camera

14 Avionics Advanced Miniature UAV Autopilots by Micro Pilots MP2128LRC Long Range Communications Weight of the chip: 0.06 lbs Low Power Requirement = 1 Watt Rugged Aluminum Enclosures Total Weight = lbs Range of up to 30 miles GPS waypoint navigations with altitude and airspeed hold 3 different modes autopilot, manually pilot, emergency direct servo control Hand launch take off mode available MP2128 Autopilot Chips MP2128LRC Autopilot with Aluminum Enclosures

15 Power– Fuel Cells Procore Fuel Cell Manufactured by Protonex High Net Power Output = 50 to 200 Watts Output Voltage = 20 to 30 Voltages Output Current = 1 to 10 Amperes High Energy = 770 W-h Weight = 4.4 lbs Emission Hydrogen and Water Protonex Procore Fuel Cells Protonex Procore Inside a Model UAV

16 Component Weight Summary Component35 mm Lens50 mm Lens Camera0.275 lbs Lens0.470 lbs0.560 lbs Avionics0.727 lbs Fuel Cells4.41 lbs Total Weight5.882 lbs5.972 lbs Required Weight Fraction (W e /W o )

17 Powerplant - Motors AXI4120/18 Goldline Brushless motor with neodymium magnets Manufactured by Model Motors s.r.o, Czech Republic RPM/V = 515 RPM/V Maximum Efficiency = 86% Dimensions = 2 in (d) x 2.2 in Suggested Max Aircraft Weight = 11lbs AXI4120/18 Goldline

18 Propeller Selection - Takeoff (9000 RPM)

19 Propeller Selection - Cruise (7000 RPM)

20 Propeller Selection Based off comparison of thrust produced and power required at given speeds. Diameter = 10 inches Pitch = 7 inches Takeoff Velocity: 17 kts Efficiency: 50% Thrust: 2.3 lbs Power: 195 W Cruise Velocity: 30 kts Efficiency: 77% Thrust:.9 lbs Power: 82 W Two blades and four blades propellers

21 Constraint Diagram For the UAV to satisfy the military and law enforcement CONOPS, 5 Constraints will be needed: Hand launch take off requirement at 1.1 Vstall (17.22 kts) Climb 200 ft/min at 18.8 kts Climb to 1000 ft at approximately 5 minutes Loiter at 30 kts for 4 hours Perform a 2-g turn at 30 kts Turn radius of approximately m Stall Speed at kts (18 mph) Basic Assumptions Parameters Units ηpηp 0.7 V stall kts V Loiter 30kts V Climb 18.8kts Climb Rate200ft/min AR6 C Do 0.02 C Lmax 1.3 n max 2g

22 Constraint Diagrams The Crucial Limiting Factors: 2 g turns – important for maneuverability Stall Speed Important for landing requirements Deep stall landing is proposed Approximate design point Wing loading 1 to 1.1 lb/ft 2 Approximately 10ft 2 to 11ft 2 of wing area for 10 lbs of aircraft Power requirement 15 to 17 watt/lbs Approximately 150 to 170 Watts for 10 lbs of aircraft

23 Constraint Diagram

24 Next Steps More on sizing code Carpet Plots Aerodynamics Airfoil Selections Aircraft Drag Polar Aircraft Performance Structures Basic structure layout and components placement Stability of Control Estimations of aircraft c.g Estimations of aircraft static margin

25 Questions and Comments ANY QUESTIONS OR COMMENTS?

26 Appendix I: CONOPS - Military Reconnaissance, Security, and Patrol Missions

27 Appendix II: QFD Two separate scoring for each customer Military Customer Important Attributes TOGW Operative Cost Payload Weight Number of Aircraft Law Enforcement Customer Importance Attributes TOGW Number of Aircraft Acquisition Cost Operative Cost Payload Weight