AEROSONDE UAV Propulsion system A 26 Hour 45 min. Un-manned flight over the Atlantic 27-30 lbs weight 10 feet wing span 24 cc (1.5 inch3) engine 180 grams/hour fuel consumption Prepared by : CENGIZ CAMCI UAV propulsion class DEPARTMENT OF AEROSPACE ENGINEERING THE PENNSYLVANIA STATE UNIVERSITY

THE AEROSONDE UAV The Aerosonde UAV is developed and operated globally by Aerosonde Pty Ltd (AePL) and Aerosonde North America (AeNA). It has been undertaking operations for about 7 years, was the first UAV to cross the Atlantic Ocean, has flown for over 32 hrs in one stretch and has undertaken continuous operations with relay aircraft extending over several days.

enables deployment and command from virtually any location. The great flexibility of the Aerosonde, combined with a sophisticated command and control system, enables deployment and command from virtually any location.

Weight, wing span 27-30 lb, 10 ft Engine 24 cc, 1.2 kw, fuel injected using premium unleaded petrol Navigation GPS Operation Staff for Launch and Recovery 3 people: Controller, Technician, Pilot/Maintenance Staff for Flight Operations 1 Person for up to 3 aircraft Ground Equipment Proprietary Staging Box, personal computer (laptop), GPS antenna, aviation and local communications radios Flight Fully autonomous, under Base Command Launch and Recovery Launch from car roof rack (catapult option), land on belly, Autonomous

Weight, wing span 27-30 lb, 10 ft Engine 24 cc, 1.2 kw, fuel injected using premium unleaded petrol Navigation GPS Operation Staff for Launch and Recovery 3 people: Controller, Technician, Pilot/Maintenance Staff for Flight Operations 1 Person for up to 3 aircraft Ground Equipment Proprietary Staging Box, personal computer (laptop), GPS antenna, aviation and local communications radios Flight Fully autonomous, under base command Launch and Recovery Launch from car roof rack (catapult option), land on belly, autonomous

Standard Instrumentation Ground & air communications UHF or Satcoms (Iridium) to Aerosonde, VHF to field staff and other aircraft, internet to command center and users. Performance Speed, Climb 18 – >32 ms-1, Climb >2.5 ms-1 at sea level Range, Endurance with no additional payload >1800 miles, >30 h Altitude Range Up to 20,000 ft (medium weight) Payload Maximum 5 lb with full fuel load Standard Instrumentation Temperature, Pressure, Humidity, Wind 2 Vaisala RSS901 Sondes for temperature, pressure and humidity, and a proprietary wind system.

Standard Instrumentation Ground & air communications UHF or Satcoms (Iridium) to Aerosonde, VHF to field staff and other aircraft, internet to command center and users. Performance Speed, Climb 18 – >32 ms-1, Climb >2.5 ms-1 at sea level Range, Endurance with no additional payload >1800 miles, >30 h Altitude Range Up to 20,000 ft (medium weight) Payload Maximum 5 lb with full fuel load Standard Instrumentation Temperature, Pressure, Humidity, Wind 2 Vaisala RSS901 Sondes for temperature, pressure and humidity, and a proprietary wind system.

Weight, wing span 27-30 lb, 10 ft Engine 24 cc, 1.2 kw, fuel injected using premium unleaded petrol Navigation GPS Operation Staff for Launch and Recovery 3 people: Controller, Technician, Pilot/Maintenance Staff for Flight Operations 1 Person for up to 3 aircraft Ground Equipment Proprietary Staging Box, personal computer (laptop), GPS antenna, aviation and local communications radios Flight Fully autonomous, under Base Command Launch and Recovery Launch from car roof rack (catapult option), land on belly, Autonomous

FIRST GENERATION ENYA PROPULSION SYSTEM 400 gm/[KWh] 180 gm/hour level flight 0.45 KW 400gm/[KWh] @ 5500 rpm MAX Fuel capacity 7000 gm 5000/180= 27.8 hours Transatlantic flight took 26 H 45 min FIRST GENERATION ENYA PROPULSION SYSTEM

SFC comparison 400 gm/[KW.h] Enya four cycle IC engine First generation Enya 0.454 gm-f = 1 lb-f 1KW=0.75 HP 1 LB/(HP.h)=610 gm/[Kw-h] TF-53 helicopter engine HUEY 1400 HP (30 min.) SFC= 0.58 LB/[HP.h] = 0.58*610=353 gm/[KW.h] Second generation ENYA 245-300 gm/[KW.h]

SPECIFIC FUEL CONSUMPTION OF VARIOUS PROPULSION SYSTEMS

ALTITUDE AND FLIGHT MACH NUMBER DEPENDENCY OF VARIOUS PROPULSION SYSTEMS

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VANE PUMP DRIVEN SUPERCHARGING FOR 36,000 + feet OPERATION