Orbital Australia Pty Limited

Orbital Engine Company (australia) Pty Limited

Geoffrey Paul Cathcart

John Howard Tubb

Donald Andrew Railton

Callan Murray Bleechmore

Terran Ambrose Barber

David Richard Worth

David James Caley

Mario Charles Muscat

Stephen John Karay

Robert Walter Frew

Rodney Alexander Houston

Nicholas Coplin

Koon Chul Yang

Pouria Mehrani

Hugh William Carlisle

Christian Chandrakumar Zavier

Richard Albert George Woolford

Michael Moore

Andrew Michael Tilmouth

John Roy McGrath

Simon C Brewster

John William Paluch

A muffler () devised particularly for use with an engine of the type used on unmanned aerial vehicles (UAVs), and a UAV () having an engine () fitted with the muffler (). The muffler () comprises a body () having an interior chamber (). The muffler body () has a first end section () and a second end section (). The first end section () is adapted for mounting onto the engine () by way of a first mount (), with the interior chamber () in communication with an exhaust outlet of the engine () to receive exhaust flow therefrom. The second end section () is adapted to be mounted by way of a second mount () in a manner resisting movement with respect to the engine (). In one arrangement, the second mount () is configured to yieldingly resist movement with respect to the engine (). In another arrangement, the second mount () is configured to mount the second end section () under a preload resisting movement of the second end section with respect to the engine ().

Muffler for small engines

A dual fluid injection system which comprises a liquid fuel metering device, a fluid delivery device, and apparatus providing an interface therebetween. The interface conveys liquid fuel along a flow path from the metering device to a mixing zone for mixing with air from a pressurized supply to provide an air-fuel mixture for injection by the fluid delivery device into a combustion chamber of an internal combustion engine. The flow path may involve a directional change by way of a turn section. The flow path is sized such that liquid fuel is retained therein by virtue of capillary action, whereby a quantity of liquid fuel is retained after a delivery event such that the flow path remains substantially filled with liquid fuel in readiness for the next delivery event during operation of the engine.

Fuel injection system

A control system and method relating to operation of an internal combustion engine, particularly an engine for powering an unmanned aerial vehicle. The engine has a combustion chamber and a throttle for regulating fluid flow to the combustion chamber, the throttle being operable under the control of an electronic control unit. With the control system and method there are first and second modes optionally available for operation of the engine. In the first mode the engine is operable at a throttle setting set by a request from a first remote controller (e.g. a ground-based controller) via a second on-board controller. In the second mode the engine is operable at a prescribed minimum throttle setting asserted by the electronic control unit which limits the authority of the on-board controller. The engine is caused to operate in the second mode if a particular throttle setting determined from a request of the remote controller is less than the prescribed minimum throttle setting.

Engine control system and method

An unmanned aerial vehicle has an internal combustion engine, and a fuel and lubrication system comprising a fuelling system for fuelling the engine and a lubrication system for delivering lubricating oil to the engine. The fuelling system comprises a fuel reservoir from which fuel can be delivered to the engine. The fuel reservoir comprises a main tank and a header tank. The lubrication system comprises an oil tank. The oil tank is accommodated internally within the main tank to provide an integrated assembly. The arrangement provides for warming of lubrication oil for the UAV engine using several available heat sources. Further, the arrangement facilitates a configuration and layout intended to minimise or negate any undesirable moments of inertia for the UAV during flight as fuel and oil is consumed.

UAV fuel and lubrication system

A system and method for delivering lubrication oil to an internal combustion engine. The engine lubrication system () comprises a lubrication oil reservoir (), a pump () to deliver lubrication oil to the engine from the reservoir (), and a pressurization system () for pressurizing oil received by the pump from the reservoir for delivery to the engine. The pressurization establishes a positive pressure at the pump inlet to assist delivery of oil having entrained vapor cavities to the engine for lubrication thereof. The pump () comprises a solenoid actuated positive displacement pump, whereby operation of the pump may be selectively controlled by the manner in which the solenoid is operated. The engine lubrication system () further comprises a pressure release system () comprising pressure relief valve () for relieving excess fluid pressure within the oil reservoir ().

Engine lubrication system

For an unmanned aerial vehicle (UAV) engine, an exhaust gas temperature control method is provided during operation of the UAV engine to protect exhaust components, particularly lightweight aluminium components, from overheating or melting. The engine is operated with a leaner than stoichiometric air-fuel ratio during low or part engine load conditions. Transition to a richer than stoichiometric air-fuel ratio is made as engine load or engine speed, or both engine load and engine speed, increase(s). At sufficiently low engine loads, the air-fuel ratio can be maintained in a lean ratio region. As demand on the engine causes engine speed and load to increase, the amount of excess air available reduces. The ability to operate lean is reduced and the exhaust gas temperature increases as the mixture becomes richer. In order to obtain the demand power, and keep exhaust temperature below an exhaust gas temperature limit, the air-fuel ratio is transitioned to a richer than stoichiometric region. As engine load and speed demand decreases, the air-fuel ratio can be transitioned back to a leaner region.

UAV engine exhaust gas temperature control

A method of operation of a dual fluid fuel injection system arranged to supply fuel to a cylinder of an internal combustion engine, the dual fluid fuel injection system being controllable to effect fuel metering events and fuel delivery events. The method comprises operating the dual fluid fuel injection system so as to have at least one fuel delivery event during each engine cycle and to have fewer than one fuel metering event, on average, per engine cycle. An electronic control unit for implementing the method is also described. The method and control unit allow dynamic range of a fuel metering injector, where included within the dual fluid fuel injection system, to be extended.

Method of injecting fuel into an engine

An unmanned aerial vehicle (UAV) engine () lubrication system and lubrication oil heating strategy uses a solenoid actuated electric oil pump () to deliver lubrication oil to the engine from a lubrication oil reservoir () by energizing and de-energizing the solenoid () to operate a pump mechanism of the electric oil pump. A controller (ECU) () can control operation of the electric oil pump, the solenoid maintained energized for a required period of time to cause heating of the oil without continuously pumping the oil. An electric oil pump control strategy can maintain engine speed dependent minimum oil delivery rates, can heat the electric oil pump and oil through extended energized (ON) time of the solenoid, and, by varying the turn on time of the electronic oil pump based on sensed ambient temperature, long time periods can be used to ensure oil delivery for cold temperatures, and shorter times are permitted when necessary in order to reach maximum oil flow rate.

UAV engine lubrication system incorporating an electric oil pump and lubrication oil heating capability

A fuel injector () for liquid phase injection of liquefied gaseous fuels for combustion chambers of an internal combustion engine. The fuel injector () comprises a nozzle portion () having an end () from which gaseous fuel can be delivered through an outlet (), the end () being configured to prevent or at least inhibit formation of ice thereon upon delivery of gaseous fuel through the outlet.

Fuel injector icing

This disclosure describes a method of controlling operation of an unmanned aerial vehicle (UAV) having a flight control system comprising: a flight controller for implementing a flight control strategy; and an engine control unit interfaced with the flight controller for controlling engine operation. An engine speed target is set for the flight control system in response to one or more signals communicated by the flight controller to the engine control unit which controls engine operation to achieve the engine speed target by closed loop control over fueling without requiring throttle position control.

Method of controlling operation of an unmanned aerial vehicle

A method for controlling controlled-auto-ignition operation in an eternal combustion engine is described. The method includes the injection of air into a combustion cylinder at an appropriate time in the combustion cycle in response to measured conditions. The injection of air acts to alter the CAI-phasing, thus providing the ability to extend the CAI operation further into a vehicle speed/load range.

Control of controlled-auto-ignition (CAI) combustion process

An injector nozzle for a fuel injected internal combustion engine, said injector nozzle including a port () having an internal valve seat surface () and a valve member () having an external seating surface (), said valve member being movable relative to the port to respectively provide a passage between the valve seat surface and the external seating surface for the delivery of fuel therethrough or sealed contact therebetween to prevent said delivery of fuel, the port further including an outer port surface () surrounding and located adjacent the valve seat surface and external to the port, wherein the angle between the valve seat surface and the outer port surface of the port is less than 90 degrees.

Deposit control in fuel injector nozzles

A method of treating NOx emmissions in the exhaust gas of an internal combustion engine having catalyst means including at least a first catalyst converter capable of treating NOx, the method including operating the engine in a first mode to promote a first set of conditions and in a second mode to promote a second set of conditions, wherein the first mode of operation includes operating the engine with a lean air-fuel ratio, and the second mode of operation includes operating the engine with a stoichiometic air-fuel ratio.

Exhaust gas treatment method and device

A method of operating a direct injected combustion engine having an exhaust system with a conventional three-way catalytic converter, the method including operating the engine with a stoichiometric air/fuel ratio at least substantially across the entire engine operating load range, such that emissions of NOx from the engine are minimised.

Direct injected engine control strategy

Disclosed is an internal combustion engine comprising at least one cylinder with a reciprocating piston to provide said engine with at least one combustion chamber, said combustion chamber further comprising a delivery injector for injecting fuel directly into said combustion chamber, said engine further comprising at least one valved inlet air duct for delivering combustion air into said combustion chamber, wherein at least said inlet air duct and/or its valve is arranged to provide a low tumble inlet port to said at least one combustion chamber, said combustion chamber, in use, having low in-cylinder tumble gas motion of said combustion air and wherein said low in-cylinder tumble gas motion of said combustion air reduces over-enleanment of fuel in end gas regions of said combustion chamber.

Growing community of inventors

Mount Lawley, Australia

Geoffrey Paul Cathcart