AEROSONDE UAVPropulsion 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) engine180 grams/hour fuel consumption

Prepared by : CENGIZ CAMCIUAV propulsion class

DEPARTMENT OF AEROSPACE ENGINEERINGTHE PENNSYLVANIA STATE UNIVERSITY

SMALL PROPULSION SYSTEMSFOR

UNMANNED AND MODEL AIRCRAFT

CONVENTIONAL INTERNAL

COMBUSTIONRUBBER

POWERED

ELECTRIC MOTOR

POWERED

GAS TURBINE/JET POWERED SYSTEMS

EXOTIC SYSTEMS

TWOSTROKEENGINES

FOUR STROKE ENGINES

CONVENTIONALFOUR CYCLE

OTTOENGINE

ROTARYENGINE

Wankel engine

ROTATING CYLINDER VALVE

ENGINE

MIGRATING COMBUSTION

CHAMBER

TURBO-JET SYSTEMSFOR

JET RPOPULSION

TURBO-SHAFT SYSTEMSFOR PROPELLER

ANDROTOR DRIVEN SYSTEMS

TURBO-SHAFT GAS TURBINE DRIVEN

A SINGLE DC ELECTRIC

GENERATOR &

DISTRIBUTED ELECTRIC MOTORS

CO2 ENGINESPULSE JETS

MICRO-ROCKET LASER DRIVEN

THEAEROSONDE

UAVThe 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.

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

OperationStaff 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

OperationStaff 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

Ground & air communications

UHF or Satcoms (Iridium) to Aerosonde, VHF to field staff and other aircraft, internet to command

center and users.PerformanceSpeed, Climb 18 – >32 ms-1, Climb >2.5 ms-1 at

sea levelRange, 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 InstrumentationTemperature,

Pressure, Humidity, Wind

2 Vaisala RSS901 Sondes for temperature, pressure and

humidity, and a proprietary wind system.

Ground & air communications

UHF or Satcoms (Iridium) to Aerosonde, VHF to field staff and other aircraft, internet to command

center and users.PerformanceSpeed, Climb 18 – >32 ms-1, Climb >2.5 ms-1 at

sea levelRange, 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 InstrumentationTemperature,

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

OperationStaff 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

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

400 gm/[KW.h] Enya four cycle IC engineFirst generation Enya

0.454 gm-f = 1 lb-f1KW=0.75 HP1 LB/(HP.h)=610 gm/[Kw-h]

TF-53 helicopter engine HUEY1400 HP (30 min.)SFC= 0.58 LB/[HP.h] = 0.58*610=353 gm/[KW.h]

Second generation ENYA 245-300 gm/[KW.h]

SFC comparison

SPECIFIC FUEL CONSUMPTION OF VARIOUS PROPULSION SYSTEMS

ALTITUDE AND FLIGHT MACH NUMBER DEPENDENCY

OF VARIOUS PROPULSION SYSTEMS

VSC001 VSC001-SC

VANE PUMP DRIVEN SUPERCHARGING FOR 36,000 + feet OPERATION