AERONAUTICAL ENGINE M09
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Transcript of AERONAUTICAL ENGINE M09
AERONAUTICAL ENGINE AERONAUTICAL ENGINE M09M09
By I.C.P. Srl
PROJECT PHILOSOPHY
I.C.P. Srl
Side view
PROJECT PHILOSOPHY
Objectives: Realization of an aeronautical piston engine With high performances Low fuel consumption Low environmental impact Aerobatic
I.C.P. Srl
PROJECT PHILOSOPHY
Top view
I.C.P. Srl
PROJECT PHILOSOPHY
Characteristics: Innovative concepts application Study of new patented system Strictly aeronautical mentality Combinig engineering theory and pratical
aeronautical experience
I.C.P. Srl
PROJECT PHILOSOPHY
Side view
I.C.P. Srl
THE PROJECT: Component FEM verification One piece crankcase Design that simplifies assembly and installation Easy bolt on installation Light weight (160 Lbs Ready To Fly) 115 Hp
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FEM ANALYSISMAIN CRANKCASE
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FEM ANALYSIS
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ENGINE ATTACHEMENT
FEM ANALYSIS
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ATTACHEMENT DETAILS CRANKCASE
CRANKCASEmaximum strenght at a minimum weight
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MAIN CRANKCASE
CRANKCASE
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GEAR BOX CRANKCASE
ARCHITECTURE
V 90° cylinder Displacement 75 cu inch 4-stroke Integrated oil tank Small front section to allow a more
aerodynamic cowling
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ARCHITECTURE
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Narrow angle combustion chamber, angled chamber roof
Twin spark plug Best surface/volume ratio of the
combustion chamber to improve combustion and fuel consumption
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ARCHITECTURE
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I.C.P. Srl
TIMING SYSTEM
Double overhead camshaft (4 valves per cylinder) with Morse-tec chain
Differential rate gear reduction system Automatical mechanical tensioner Chain wear indicator (I.C.P. patent pending) Automatic decompressor (for easy start) of the
exhaust valve
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I.C.P. Srl
4 VALVES FOR CYLINDER
TIMING SYSTEM
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TIMING SYSTEM
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TIMING SYSTEM
COOLING SYSTEM
Liquid cooled Centrifugal pump Regulating thermostat Water/oil heat exchanger incorporated in
the oil tank
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I.C.P. Srl
COOLING SYSTEM
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COOLING SYSTEM
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INVERTED FLIGHT
LUBRICATION
Dry sump Inertial oil suction (I.C.P. patent pending), to
Guarantee oil flow in all flight attitude Integrated oil tank and lubrication circuit 3 coaxial pumps ( 2 scavenger and 1 delivery) 2 oil filters: replaceable cartridge and a fixed
plastic mesh at inertial oil suction
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LUBRICATION
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LUBRICATION GULLIES
LUBRICATION
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ALL TANK WITH INERTIAL OIL SUCTION
LUBRICATION
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OIL FILTERS
PLASTIC MESH
CARTRIDGE FILTER
LUBRICATION
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OIL PUMPS
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LUBRICATION SYSTEM
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INVERTED FLIGHT
FUEL SYSTEM
Administrated directly by CAN line also connected to the cockpit engine monitor
2 redundant system with continous self - diagnosis
Primary system: Magneti Marelli electronic injection with two Lamba probe
Secondary system: mechanical injection carburator installed into the throttle body (I.C.P. patent pending)
I.C.P. Srl
I.C.P. Srl
THROTTLE BODY AND INJECTORS
FUEL SYSTEM
GEAR REDUCTION SYSTEM
Gears with “long addendum” profile Dampener Overload clutch Gear reduction ratio 1:2.95
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I.C.P. Srl
GEAR REDUCTION SYSTEM
Starter with rare earth magnetos Free wheel clutch Automatic exhaust valve compressor at
start
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IGNITION SYSTEM
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STARTER SYSTEM
GENERATOR
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32 Amp three-phase generator