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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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