• AUSROC Nano is a small, transportable liquid fuelled rocket designed to carry small payloads to Low Earth Orbit (LEO).
– Can be transported by road to any approved launch destination
– Can be launched from any approved launch destination
• The initial proposed payloads are nano-satellites of 10kg with an orbit of 300km above Earth.
Nano is a three-stage bi-propellant liquid fuelled orbital launch vehicle with a solid fuelled third stage. It features a fully composite airframe, advanced avionics and flight control systems, as well as high reliability propulsion hardware. It has been designed to launch the payload to an equatorial or polar orbit with an altitude of 300 kilometres. The Nano launch system is intended to be road transportable in two standard 40 ft shipping containers, from anywhere in Australia, making it a versatile, mission specific launch vehicle. A key requirement of the project is the utilisation of Commercial-Off-The-Shelf (COTS) technology to ensure system reliability and minimal development time.
The vehicle has gone through a number of changes since the concept was originally developed. These changes include; increased vehicle capability, focus on the development of a System Requirement Specification (SRS), a matured vehicle concept, and matured launch and operations concept.
At present, the AUSROC Nano project team is currently completing the SRS. The next key phase of the project will be to develop, finalise and package key project documentation such as the Operational Concept Documents and finalise high-level project schedules and projected operational costs. This will provide ASRI with the ability to seek initial funding in order to validate the mission concepts that have evolved from the vehicles design.
|Launch Weight||2255 kg|
|Orbital Insertion Altitude||300 km|
|Lifting Capability||10 kg (3U CubeSat)|
|Propulsion System||- 35 kN LOX/JA-1 Liquid Fueled Engine
- Tube wall construction
- 109 second burn time
|Construction||Filament wound liner-less Composite tanks and fairings|
|Propulsion System||– 10 kN LOX/JA-1 Liquid Fueled Engine
– Tube wall construction (yet to be determined)
– 160 second burn time
|Construction||Filament Wound Liner-less Composite tanks and fairings|
|Propulsion System||– 8 kN Solid Motor (Ammonium Perchlorate, Aluminum Powder, HTPB)
– 40 second burn time
|Construction||Filament Wound Case|
|Satellite Release Mechanism||PPOD Mk-III Satellite Launcher|