Propulsion Systems
Pushing the Limits of Micro Gas Turbine Technology
Aurora Labs is redefining how compact jet propulsion is developed, manufactured, and deployed. Our additive-first approach merges advanced design, precision metal 3D printing, and aerospace-grade engineering to create next-generation micro turbines for unmanned systems and specialized aircraft.
We focus on engineered adaptability—offering propulsion systems that scale across mission profiles, from loitering munitions to ISR drones and high-manoeuvrability UAVs.
This is propulsion innovation, built in Australia for the evolving battlespace.
Propulsion Engineering Capabilities
Vertical integration for streamlined and rapid development of novel engine concepts.
In-house aerodynamic and structural simulation capability to optimise engine performance.
In-house engine characterisation and testing capabilities.
Manufacturing Capability & Scalability
Three custom designed powder bed fusion machines.
Refined and optimised post processing capabilities for printed components.
In-house machining
Soon to receive a state-of-the-art CNC machine and lathe for boosted production capacity.
Engine Product Family
Compact, high-thrust design
Aurora’s turbojet engine family is purpose-built for ISR drones, loitering munitions, and tactical UAVs
Sovereign capability
Designed, printed, and assembled in Australia with local IP
Reusability-ready architecture
Overhaul and modular servicing pathways in development
Long Range Missions
The Micro Turbofan is the first of its kind in the world, providing improved fuel efficiency over turbojet engines for long range missions
AU2 Turbojet Engine
| Function | Value (Note: All Values ±5% / At SSL Conditions) | Units |
| Maximum Thrust | 220 | N |
| Maximum Shaft Speed | 118,000 | RPM |
| Idle Thrust | 12 | N |
| Idle Shaft Speed | 38,000 | RPM |
| Fuel Compatibility | JP5, JetA, JetA1, Diesel | |
| Fuel Consumption (Max. thrust) | 0.67 | Kg/min |
| Thrust Specific Fuel Consumption | 0.18 | Kg/N/hr |
| Maximum Exhaust Gas Temperature | 800 | °C |
| Power for ECU | 14.8 (4S Lipo) | V |
| Weight (inc. MGT + fuel pump, does not inc. battery) | 2 | Kg |
AU4 Turbojet Engine
| Function | Value (Note: All Values ±5% / At SSL Conditions) | Units |
| Maximum Thrust | 220 | N |
| Maximum Shaft Speed | 118,000 | RPM |
| Idle Thrust | 12 | N |
| Idle Shaft Speed | 38,000 | RPM |
| Fuel Compatibility | JP5, JetA, JetA1, Diesel | |
| Fuel Consumption (Max. thrust) | 0.67 | Kg/min |
| Thrust Specific Fuel Consumption | 0.18 | Kg/N/hr |
| Maximum Exhaust Gas Temperature | 800 | °C |
| Power for ECU | 14.8 (4S Lipo) | V |
| Weight (inc. MGT + fuel pump, does not inc. battery) | 3.6 | Kg |
| Max. Operating Altitude | 8000 (26,000) | m (ft) |
Future Engine Developments
Optimisation and commercialisation of the AU2 and AU4 turbojet engines
Extremely high thrust to weight ratio and relative low-cost make the engines well suited for small drones and one-way effectors.
Continued development and scalability of the micro turbofan engine to optimise performance for platform integration
Investigate cost reduction methods, such as direct drive which permits removal of the gearbox for one-way systems.
Incorporation of the AU-4 as the gas generator to increase thrust output.
Engine is well suited for high speed and long-range reconnaissance, long range precision strike, and attritable tactical UAVs and drones.
| Engine Parameter | Value |
| Maximum Thrust | 800 N |
| Fuel Consumption | 1.1 kg/min |
| Total Engine Weight | 18 kg |
| Thrust Specific Fuel Consumption | 0.09 kg/N/hr |
