AAE 451 Aircraft Senior Design TEAM III Sumitero

AAE 451 - Aircraft Senior Design TEAM III Sumitero (Calvin) Darsono Charles Hagenbush Keith Higdon Seung-il Kim Matt Lewis Matt Richter Jeff Tippmann Alex Zaubi 11

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 22

Mission Statement To provide a continuous aerial coverage using an UAS that is small, light, portable and allows rapid deployment 33

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 • Market • Military Evolution XTS – L 3 BAI Aerosystems • Surveillance around temporary base • Forward reconnaissance • Law enforcement and emergency services • Surveillance in assessing hazardous situations before committing personnel 44

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 55

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 Sky. Seer Raider Marauder 66

Current Market Military • As of 2005, over 800 small UA Systems planned • Over 2500 aircraft • Market is Growing • Armed Forces to spend $20 M 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 77

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 Weight 10 lbs Endurance 4 hrs Range 5 miles Payload Weight 2 lbs Weight Fraction 0. 4 We/Wo Energy Density 350 W-hr /kg Aerovironment - Raven 88

Aircraft Concept Selection 1 5 2 3 8 99

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

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

Payload – Camera Core Camera • Photon OEM Core IR Camera • 320 x 240 Long Wavelength • Manufactured by FLIR System • Frame Rate = 30 Hz (320 X 240) • Autonomous and manual camera operations • Minimum Power Consumption ~1. 5 W • Weight (~0. 27 lbs) • Camera Core = 0. 21 lbs • Rear Cover = 0. 03 lbs • Universal Lens Holder = 0. 03 lbs • Dimensions • 2. 0 x 1. 8 in Camera Core of Photon OEM with Lens 12 12

Payload – Camera Lens • Two lens are considered • Focal Length 35. 0 mm • 20 o HFo. V f/1. 4 • Weight = 0. 194 lbs (including lens mount) • Total Camera Weight = 0. 47 lbs • Optimum for operations up to 1000 ft Projected Results Obtained from the Camera • Focal Length 50. 0 mm • 14 o HFo. V 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 35. 0 mm Lens OEM Photon with 50. 0 mm Lens 13 13

Avionics Advanced Miniature UAV Autopilots by Micro Pilots • MP 2128 LRC Long Range Communications • Weight of the chip: 0. 06 lbs • Low Power Requirement = 1 Watt • Rugged Aluminum Enclosures • Total Weight = 0. 727 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 MP 2128 Autopilot Chips MP 2128 LRC Autopilot with Aluminum Enclosures 14 14

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 15 15

Component Weight Summary Component 35 mm Lens 50 mm Lens Camera 0. 275 lbs Lens 0. 470 lbs 0. 560 lbs Avionics 0. 727 lbs Fuel Cells 4. 41 lbs Total Weight 5. 882 lbs 5. 972 lbs 0. 4118 0. 4028 Required Weight Fraction (We/Wo) 16 16

Powerplant - Motors AXI 4120/18 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 = 11 lbs AXI 4120/18 Goldline 17 17

Propeller Selection - Takeoff (9000 RPM) 18 18

Propeller Selection - Cruise (7000 RPM) 19 19

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 20 20

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 12. 13 m • Basic Assumptions Parameters ηp Vstall Units 0. 7 15. 65 kts VLoiter 30 kts VClimb 18. 8 kts Climb Rate 200 ft/min AR 6 CDo 0. 02 CLmax nmax 1. 3 2 g • Stall Speed at 15. 65 kts (18 mph) 21 21

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 10 ft 2 to 11 ft 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 22 22

Constraint Diagram 23 23

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 24 24

Questions and Comments ANY QUESTIONS OR COMMENTS? 25 25

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

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 27 27