An internal combustion engine for an aircraft can include a crankshaft configured to drive a propeller; a camshaft coupled to the crankshaft; and an ignition controller coupled to the camshaft and including a visual indicator, the visual indicator configured to produce a visual signal at a predetermined angular position of the engine. An ignition controller for an internal combustion engine can include a housing and a P-lead connection extending from the housing, the ignition controller configured to selectively supply or cut main electrical power from the engine via the P-lead connection, the ignition controller also configured to selectively supply its own power.
F02P 1/00 - Installations having electric ignition energy generated by magneto- or dynamo-electric generators without subsequent storage
F02P 5/06 - Advancing or retarding electric ignition sparkControl therefor automatically, as a function of the working conditions of the engine or vehicle or of the atmospheric conditions using mechanical means dependent on engine speed
B64D 27/04 - Aircraft characterised by the type or position of power plants of piston type
F02P 3/00 - Other electric spark ignition installations characterised by the type of ignition power generation storage
An internal combustion engine for an aircraft can include a crankshaft configured to drive a propeller; a camshaft coupled to the crankshaft; and an ignition controller coupled to the camshaft and including a visual indicator, the visual indicator configured to produce a visual signal at a predetermined angular position of the engine. An ignition controller for an internal combustion engine can include a housing and a P-lead connection extending from the housing, the ignition controller configured to selectively supply or cut main electrical power from the engine via the P-lead connection, the ignition controller also configured to selectively supply its own power.
F02P 1/00 - Installations having electric ignition energy generated by magneto- or dynamo-electric generators without subsequent storage
F02P 5/06 - Advancing or retarding electric ignition sparkControl therefor automatically, as a function of the working conditions of the engine or vehicle or of the atmospheric conditions using mechanical means dependent on engine speed
B64D 27/04 - Aircraft characterised by the type or position of power plants of piston type
F02P 3/00 - Other electric spark ignition installations characterised by the type of ignition power generation storage
An internal combustion engine for an aircraft can include a crankshaft configured to drive a propeller; a camshaft coupled to the crankshaft; and an ignition controller coupled to the camshaft and including a visual indicator, the visual indicator configured to produce a visual signal at a predetermined angular position of the engine. An ignition controller for an internal combustion engine can include a housing and a P-lead connection extending from the housing, the ignition controller configured to selectively supply or cut main electrical power from the engine via the P-lead connection, the ignition controller also configured to selectively supply its own power.
F02P 1/00 - Installations having electric ignition energy generated by magneto- or dynamo-electric generators without subsequent storage
F02P 5/06 - Advancing or retarding electric ignition sparkControl therefor automatically, as a function of the working conditions of the engine or vehicle or of the atmospheric conditions using mechanical means dependent on engine speed
B64D 27/04 - Aircraft characterised by the type or position of power plants of piston type
F02P 3/00 - Other electric spark ignition installations characterised by the type of ignition power generation storage
An internal combustion engine for an aircraft includes a crankshaft configured to drive a driven element; a first camshaft coupled to the crankshaft; a second camshaft coupled to the crankshaft; a fuel flow control system including a fuel pump and a fuel control actuator communicating with the fuel pump and configured to restrict fuel flow downstream to a plurality of fuel injectors; and a turbocharger control system including a wastegate, a wastegate actuator configured to partially or completely open or close the wastegate, and an electronic controller; the electronic controller operatively connected to the wastegate actuator and configured to cause movement of the wastegate actuator in response to a turbocharger discharge pressure.
An internal combustion engine for an aircraft includes a crankshaft configured to drive a driven element; a camshaft coupled to the crankshaft; and an ignition controller coupled to the camshaft and including a visual indicator, the visual indicator configured to produce a visual signal at a predetermined angular position of the ignition controller. An ignition controller for an internal combustion engine includes a housing and a P-lead connection in electrical communication with both a battery of the aircraft and an ignition switch of the aircraft, the P-lead connection extending from the housing, the ignition controller configured to selectively supply or cut main electrical power from the battery of the aircraft via the P-lead connection, the ignition controller also configured to selectively supply its own power.
F02B 33/10 - Engines with reciprocating-piston pumpsEngines with crankcase pumps with reciprocating-piston pumps other than simple crankcase pumps with the pumping cylinder situated between working cylinder and crankcase, or with the pumping cylinder surrounding working cylinder
F02B 75/00 - Other engines, e.g. single-cylinder engines
An internal combustion engine for an aircraft includes a crankshaft configured to drive a driven element; a camshaft coupled to the crankshaft; and an ignition controller coupled to the camshaft and including a visual indicator, the visual indicator configured to produce a visual signal at a predetermined angular position of the ignition controller. An ignition controller for an internal combustion engine includes a housing and a P-lead connection in electrical communication with both a battery of the aircraft and an ignition switch of the aircraft, the P-lead connection extending from the housing, the ignition controller configured to selectively supply or cut main electrical power from the battery of the aircraft via the P-lead connection, the ignition controller also configured to selectively supply its own power.
F01L 1/344 - Valve-gear or valve arrangements, e.g. lift-valve gear characterised by the provision of means for changing the timing of the valves without changing the duration of opening changing the angular relationship between crankshaft and camshaft, e.g. using helicoidal gear
B60K 6/24 - Arrangement or mounting of plural diverse prime-movers for mutual or common propulsion, e.g. hybrid propulsion systems comprising electric motors and internal combustion engines the prime-movers consisting of electric motors and internal combustion engines, e.g. HEVs characterised by apparatus, components or means specially adapted for HEVs characterised by the combustion engines
B60W 10/08 - Conjoint control of vehicle sub-units of different type or different function including control of propulsion units including control of electric propulsion units, e.g. motors or generators
F01B 9/02 - Reciprocating-piston machines or engines characterised by connections between pistons and main shafts, not specific to groups with crankshaft
An internal combustion engine for an aircraft includes a crankshaft configured to drive a driven element; a camshaft coupled to the crankshaft; and an ignition controller coupled to the camshaft and including a visual indicator, the visual indicator configured to produce a visual signal at a predetermined angular position of the ignition controller. An ignition controller for an internal combustion engine includes a housing and a P-lead connection in electrical communication with both a battery of the aircraft and an ignition switch of the aircraft, the P-lead connection extending from the housing, the ignition controller configured to selectively supply or cut main electrical power from the battery of the aircraft via the P-lead connection, the ignition controller also configured to selectively supply its own power.
An internal combustion engine for an aircraft can include a crankshaft configured to drive a propeller; a camshaft coupled to the crankshaft; and an ignition controller coupled to the camshaft and including a visual indicator, the visual indicator configured to produce a visual signal at a predetermined angular position of the engine. An ignition controller for an internal combustion engine can include a housing and a P-lead connection extending from the housing, the ignition controller configured to selectively supply or cut main electrical power from the engine via the P-lead connection, the ignition controller also configured to selectively supply its own power.
F02P 5/06 - Advancing or retarding electric ignition sparkControl therefor automatically, as a function of the working conditions of the engine or vehicle or of the atmospheric conditions using mechanical means dependent on engine speed
B64D 27/04 - Aircraft characterised by the type or position of power plants of piston type
A system, apparatus and method for maintaining power in an internal combustion typically turbocharged aircraft engine is disclosed. During descent, air pressure and temperature in the manifold can fall to dangerous levels. This is because engine power is low and likewise turbocharger output is also low. The system and method provide for a bypass of the heat radiator during low power periods, or with low ambient temperature or both. A parameter is measured, often manifold pressure or temperature and the degree of bypass is adjusted commensurately.
F28F 27/02 - Control arrangements or safety devices specially adapted for heat-exchange or heat-transfer apparatus for controlling the distribution of heat-exchange media between different channels
F24F 11/02 - Arrangement or mounting of control or safety devices
(1) Internal combustion engines for general power application; complete industrial power units for general power application; each unit comprising an internal combustion engine mounted in a frame with cooling fluid and fuel tanks; replacement and spare parts for such engines and power units, namely carburetors, induction manifold parts, fuel economizers for the carbureters and manifolds, engine superchargers, govenors and engine speed controlling mechanisms; gearing and transmission assemblies and clutches, libricant pressure and scavenge pumps for same; fuel pumps and fuel injecting mechanisms, accessery mountings and accessery driving machanisms, and engine vibration dampers.
