AUSROC III
The Ausroc III Program is one of the most advanced initiatives of its type in the world. It is by
far the most ambitious high technology education and development program ever undertaken in
Australia. The methods by which the Program is being advanced are revolutionary. The vehicle
being developed is an order of magnitude more sophisticated than any other rocket previously
developed in this country. From humble beginnings, the Ausroc Program is maturing into a
pathfinder for the re-entry of Australia into the global space industry.
Advancement of the Ausroc Program relies upon the continuing support of government,
industry and the Australian public generally.
The Ausroc III vehicle is a liquid fuelled sounding rocket designed to launch a 150 kilogram payload module to an altitude of 500 kilometres on a sub-orbital trajectory. Unlike most sounding rockets in commercial use today, the vehicle will incorporate active guidance which means that its trajectory will be controllable during flight. The payload module will achieve approximately 6 minutes of weightlessness before re-entry and recovery via a steerable gliding parachute recovery system. These capabilities compare favourably with those of sounding rockets in commercial use today.
For even more in depth history and information on AUSROC III please feel free to download the PDF below.
[wpdm_package id=’623′]
For even more in depth history and information on AUSROC III please feel free to download the PDF below.
[wpdm_package id=’623′]
Physical Characteristics
| Length | 8400 mm |
| Diameter | 700 mm |
| Stabilization | Thrust Vectoring (Strongring, Thrust Frame and Gimbal Unit) |
| Recovery System | Parachute |
Propellant Characteristics
| Propellant mass | 1200 kg |
| Dry mass | 220 kg |
| Fueled Mass | 1570 kg |
| Fuel | Kerosine (JA-1) |
| Fuel Mass | 130 kg |
| Oxidizer | Liquid Oxygen |
| Oxidizer Volume | 800 l |
| Mass ratio | 0.85 |
| Mixture Ratio | 2.4 (LOX/Kerosine) |
| Propellant Feed Method | Regulated pressurisation system (Plain He or Tridyne) |
| Ignition Method | Pyrotechnic Ignition |
| Pressurisation Gas | Helium/Tridyne |
| Tank Pressure | 30 MPa |
Motor Characteristics
| Thrust | 35,000 N sl - 42,600N vac |
| Burn Time | |
| Specific Impulse | 241sec sl - 293 sec vac |
| Chamber Pressure | 2 MPa |
Payload
| Sensors | - 128 Sensors - 16 Data formatters - 8 Data acquisition modules - Multiplexer - Video Transmitter |
| Transmitter | 500 kHz |
| Payload Module Mass | 150 kg |
| Payload Module Components | - Avionics - Recovery System - Flight Experiments - Heat Shield |