Abstract

A crankcase for a UAV internal combustion engine, comprising a crankcase housing comprising a crankcase chamber, a fuel injection port extending through said crankcase housing to said crankcase chamber, and a fuel diverter comprising a diverting surface disposed within said crankcase chamber and aligned with said fuel injection port.

IPC Classes  ?

• F02M 37/00 - Apparatus or systems for feeding liquid fuel from storage containers to carburettors or fuel-injection apparatusArrangements for purifying liquid fuel specially adapted for, or arranged on, internal-combustion engines
• F02B 61/04 - Adaptations of engines for driving vehicles or for driving propellersCombinations of engines with gearing for driving propellers
• F02B 75/02 - Engines characterised by their cycles, e.g. six-stroke
• F02M 61/14 - Arrangements of injectors with respect to enginesMounting of injectors

Abstract

A crankcase for a UAV internal combustion engine, comprising a crankcase housing comprising a crankcase chamber, a fuel injection port extending through said crankcase housing to said crankcase chamber, and a fuel diverter comprising a diverting surface disposed within said crankcase chamber and aligned with said fuel injection port.

IPC Classes  ?

• F02B 17/00 - Engines characterised by means for effecting stratification of charge in cylinders
• F02B 15/00 - Engines characterised by the method of introducing liquid fuel into cylinders and not otherwise provided for
• F04B 39/12 - CasingsCylindersCylinder headsFluid connections
• B64U 10/25 - Fixed-wing aircraft
• B64U 20/96 - Cooling using air
• B64U 50/11 - Propulsion using internal combustion piston engines

Abstract

A UAV propulsion system is disclosed that utilizes a crankcase having a first crankcase compartment and a second crankcase compartment. Each crankcase compartment includes a corresponding cylinder assembly and piston, with each piston being interconnected with a rotatable crankshaft. A first airflow path extends from an exterior of the UAV propulsion system to the first crankcase compartment, and a separate second airflow path extends from the exterior of the UAV propulsion system to the second crankcase compartment. A first rotary valve may be mounted on and rotate with the crankshaft to control the airflow along the first airflow path to the first crankcase compartment, while a second rotary valve may be mounted on and rotate with the crankshaft to control the airflow along the second airflow path to the second crankcase compartment.

IPC Classes  ?

• F02B 75/18 - Multi-cylinder engines
• F04B 39/12 - CasingsCylindersCylinder headsFluid connections
• B64C 39/02 - Aircraft not otherwise provided for characterised by special use
• B64C 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings

Abstract

An engine assembly having an improved mounting system or assembly is disclosed. Features of this mounting system include having crankcase arms that are integrally formed with a crankcase of the engine assembly, having multiple mounting legs that each have a dedicated vibration damping subassembly and where the stiffness of at least two of the mounting legs is different (by varying the configurations of the corresponding vibration damping subassemblies), and using a mounting ring or base with having differently oriented mounting pads for securement of the corresponding mounting leg relative thereto.

IPC Classes  ?

• F02F 7/00 - Casings, e.g. crankcases
• B64D 27/04 - Aircraft characterised by the type or position of power plants of piston type
• B64D 27/26 - Aircraft characterised by construction of power-plant mounting
• F02B 61/04 - Adaptations of engines for driving vehicles or for driving propellersCombinations of engines with gearing for driving propellers
• B64C 39/02 - Aircraft not otherwise provided for characterised by special use

Abstract

A cooling shroud assembly for an engine is disclosed. This cooling shroud assembly includes a shroud body. There is an inlet door or flap to an interior of this shroud body, along with an outlet door or flap from this shroud body. When installed on an engine that is incorporated by a moving vehicle (e.g., aircraft, unmanned aerial vehicle, radio-controlled aircraft, watercraft), airflow through the shroud body from an inlet to an outlet. The position of the inlet and outlet doors may be adjusted (e.g., simultaneously) to change the airflow through the shroud body, and to thereby change the dissipation of heat from the operating engine via this airflow.

IPC Classes  ?

• F01P 7/14 - Controlling of coolant flow the coolant being liquid
• H02K 7/14 - Structural association with mechanical loads, e.g. with hand-held machine tools or fans
• F01P 1/02 - Arrangements for cooling cylinders or cylinder heads, e.g. ducting cooling-air from its pressure source to cylinders or along cylinders
• F01P 3/02 - Arrangements for cooling cylinders or cylinder heads
• F01P 7/02 - Controlling of coolant flow the coolant being cooling-air
• B63H 21/38 - Apparatus or methods specially adapted for use on marine vessels, for handling power plant or unit liquids, e.g. lubricants, coolants, fuels or the like
• B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
• B63H 21/14 - Use of propulsion power plant or units on vessels the vessels being motor-driven relating to internal-combustion engines

Abstract

An internal combustion engine has both a primary fuel system and a starting fuel intake assembly. The primary fuel system and the starting fuel intake assembly provide separate flow paths to a common chamber of the internal combustion engine. An external starting fuel source is fluidly connectable with the starting fuel intake assembly of the internal combustion engine, for instance when exposed to a low ambient temperature environment. The internal combustion engine is started while a starting fuel is flowing into a combustion chamber for the internal combustion engine. A primary fuel may also be flowing into the combustion chamber at this time. After the primary fuel is being consistently ignited in the combustion chamber, the flow of starting fuel to the combustion chamber may be terminated and the external starting fuel source may be fluidly disconnected from the starting fuel intake assembly of the internal combustion engine.

IPC Classes  ?

• F02D 19/06 - Controlling engines characterised by their use of non-liquid fuels, pluralities of fuels, or non-fuel substances added to the combustible mixtures peculiar to engines working with pluralities of fuels, e.g. alternatively with light and heavy fuel oil, other than engines indifferent to the fuel consumed
• F02B 61/04 - Adaptations of engines for driving vehicles or for driving propellersCombinations of engines with gearing for driving propellers
• F02B 75/16 - Engines characterised by number of cylinders, e.g. single-cylinder engines
• B64C 39/02 - Aircraft not otherwise provided for characterised by special use
• B64D 27/04 - Aircraft characterised by the type or position of power plants of piston type

Abstract

A muffler for an engine assembly is disclosed. This muffler is arcuately-shaped and may be configured so as to not protrude beyond an outermost perimeter of an engine assembly that uses this muffler. The muffler may include a lower chamber, an intermediate chamber, and an upper chamber that are disposed in a common stack. Exhaust inlet and outlet ports to the muffler may be located at a common end of the muffler body. The exhaust inlet port may lead into the lower chamber. Multiple exhaust outlet ports out of the upper chamber may be utilized to allow the muffler to be used with different vehicle configurations, for instance to direct exhaust out of the muffler in different directions.

IPC Classes  ?

• F01N 13/00 - Exhaust or silencing apparatus characterised by constructional features
• F01N 1/08 - Silencing apparatus characterised by method of silencing by reducing exhaust energy by throttling or whirling

Abstract

An engine assembly having an improved mounting system or assembly is disclosed. Features of this mounting system include having crankcase arms that are integrally formed with a crankcase of the engine assembly, having multiple mounting legs that each have a dedicated vibration damping subassembly and where the stiffness of at least two of the mounting legs is different (by varying the configurations of the corresponding vibration damping subassemblies), and using a mounting ring or base with having differently oriented mounting pads for securement of the corresponding mounting leg relative thereto.

IPC Classes  ?

• F02F 7/00 - Casings, e.g. crankcases
• B64D 27/04 - Aircraft characterised by the type or position of power plants of piston type
• B64D 27/26 - Aircraft characterised by construction of power-plant mounting
• F02B 61/04 - Adaptations of engines for driving vehicles or for driving propellersCombinations of engines with gearing for driving propellers
• B64C 39/02 - Aircraft not otherwise provided for characterised by special use

Abstract

An engine with an acoustic emissions valve or reflector for an exhaust system is disclosed. This reflector is disposed outside of the exhaust system—the reflector is disposed in the atmosphere into which the exhaust system discharges. The reflector is moved between a reflecting position (where the reflector reflects or obstructs acoustic emissions from the exhaust system) and a non-reflecting position (where the reflector does not obstruct the bulk exhaust gas flow from the exhaust system) by rotation of the crankshaft.

IPC Classes  ?

• F02B 75/28 - Engines with two or more pistons reciprocating within same cylinder or within essentially coaxial cylinders
• F01N 1/18 - Silencing apparatus characterised by method of silencing by using movable parts having rotary movement

Abstract

A muffler providing a compact and low-profile form factor for small two-stroke engines is described, particularly useful for aerodynamic radio controlled aircraft. The muffler comprises a tuned internal header eliminating the need for an external header to mount the inventive muffler to the exhaust port of a two-stroke engine while maintaining enhanced engine performance, obviating the need for a conventional tuned-pipe exhaust.

IPC Classes  ?

• F01N 1/10 - Silencing apparatus characterised by method of silencing by reducing exhaust energy by throttling or whirling in combination with sound-absorbing materials
• F01N 1/24 - Silencing apparatus characterised by method of silencing by using sound-absorbing materials
• F01N 1/12 - Silencing apparatus characterised by method of silencing by reducing exhaust energy by throttling or whirling using spirally- or helically-shaped channels
• F01N 13/16 - Selection of particular materials

Abstract

A muffler providing a compact and low-profile form factor for small two-stroke engines is described, particularly useful for aerodynamic radio controlled aircraft. The muffler comprises a tuned internal header eliminating the need for an external header to mount the inventive muffler to the exhaust port of a two-stroke engine while maintaining enhanced engine performance, obviating the need for a conventional tuned-pipe exhaust.

IPC Classes  ?

• F01N 1/24 - Silencing apparatus characterised by method of silencing by using sound-absorbing materials