Piston type aircraft engine

A propulsion assembly suitable for placement in an aircraft for propelling the aircraft, the assembly comprising:

• (A) a four stroke internal combustion engine, the engine comprising
• (1) four to eight cylinders disposed in a V configuration, the cylinders having a total displacement of about 2.5 to about 5.4 liters;
• (2) a crankshaft operatively connected to the cylinders, the crankshaft rotating at a speed of about 4500 to about 5500 revolutions per minute when the engine is operating under normal conditions;
• (3) a closed loop cooling system constructed and arranged to provide cooling at least to the cylinders;
• and
• (4) a fuel injection system operatively connected to the cylinders to provide fuel for combustion,
• the engine having a total power output of about 180 to about 350 horsepower, and a total wet installed weight of less than about 1.0 kilogram per horsepower produced;
• (B) a gear box operatively connected to the crankshaft;
• (C) a propeller shaft operatively connected to the gear box, the propeller shaft rotating at a speed of about 2000 to about 2200 revolutions per minute when the engine is operating under normal conditions;
• and
• (D) an electronic control unit, the electronic control unit electrically connected to the engine and configured to monitor and control at least one operating parameter of the engine,
• wherein the propulsion assembly satisfies RTCA DO-160d, RTCA DO-178b, and US FAA FAR 33 guidelines.

A propulsion assembly suitable for placement in an aircraft for propelling the aircraft, the assembly comprising:

• (A) an internal combustion engine, the engine comprising
• (1) one to twelve cylinders;
• (2) a crankshaft operatively connected to the cylinders;
• and
• (3) an internal generator operatively connected to the crankshaft;
• (B) a propeller shaft operatively connected to the engine;
• and
• (C) an electronic control unit connected to the engine and configured to monitor and control at least one operating parameter of the engine,
• wherein the internal generator is connected to the electronic control unit and provides power to the electronic control unit and to the engine when the crankshaft is rotating, and
• wherein the propulsion assembly satisfies RTCA DO-160d, RTCA DO-178b, and US FAA FAR 33 guidelines.