Download - AERONAUTICAL ENGINE M09
AERONAUTICAL ENGINE AERONAUTICAL ENGINE M09M09
By I.C.P. Srl
PROJECT PHILOSOPHY
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Side view
PROJECT PHILOSOPHY
Objectives: Realization of an aeronautical piston engine With high performances Low fuel consumption Low environmental impact Aerobatic
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PROJECT PHILOSOPHY
Top view
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PROJECT PHILOSOPHY
Characteristics: Innovative concepts application Study of new patented system Strictly aeronautical mentality Combinig engineering theory and pratical
aeronautical experience
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PROJECT PHILOSOPHY
Side view
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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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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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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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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)
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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
