AUSROC 2.5

What is Ausroc 2.5 ?

The Ausroc 2.5 rocket represents an intermediate stage between Ausroc II and Ausroc III, and is intended to incorporate as many elements of Ausroc III as possible while retaining a rocket which can be readily designed and fabricated.

This rocket currently represents the main focus of current activities within the Ausroc program.

The objectives of the project are :

• To launch a rocket with a 10kg payload to an altitude of 20km on a ballistic trajectory and recover the vehicle intact.
• To prove design concepts in propulsion , avionics, recovery and launch technologies to use in future Ausroc programs.
• To further develop operational procedures and experience in launching high powered rocketry.

The Ausroc 2.5 will be designed and fabricated in accordance with the ASRI Project Management framework, as a collaboration between ASRI members, students, Universities and other interested individuals, organisations and sponsors.

Now Seeking Volunteers

The AUSROC 2.5 project is currently looking for new members to assist with ongoing manufacturing, integration and testing activities. This is a great opportunity to get involved in hands on rocketry (contact Andrew Barton).

Team

The Ausroc 2.5 team presently includes the following leaders :

• Project Manager and Propulsion Team Lead : John August
• Deputy Project Manager : Chris Barton
  
• System Engineer : Mark Blair
• Recovery Team Lead and Administrator : Belo Ferreira
• Structures Team Lead : Ian Bryce (assisted by Andrew Barton)
• Avionics Team Lead : Bernard Davison
• Configuration & CAD Management : Ivan Vuletich

We also anticipate contributions from the Swiss Propulsion Laboratory.

Specifications

The Ausroc 2.5 rocket is fuelled by Liquid Oxygen and Kerosene, and will have a mass of 350 to 400 kg. The Ausroc 2.5 motor will have the same dimensions and geometry as the Ausroc III motor, but will be ablative rather than regeneratively cooled in order to ease fabrication.

The Ausroc 2.5 rocket has the following specifications :

• Launch Elevation: Between 70 and 80 degrees
• Propellant: Kero/Lox, Mixture ratio 2.4 (Lox/Fuel)
• Thrust at lift-off: 35kN
• Specific Impulse at sea level: 230s
• Combustion Chamber Pressure: 2MPa
• Launch Acceleration: 6-10 g
• Length : 7.2m
• Diameter : 305 mm (12")
• Control: 3 stabiliser fins (no guidance system)
• Mass fraction: > 0.5
• Burn time: 10-15 seconds
• Fuel System: Regulated flow tank pressurisation system (using tridyne pressurant)
• Drag Coefficient: < 0.8

Documentation

Images

A plan view and some three dimensional views of the rocket are illustrated below :

Current Status

Date: Feb 12, 2007

The engineering drawings for release 0.3 have been completed.

The major elements of the Propulsion subsystem have been defined. Detailed drawings have been completed for the engine components. Many of the parts used for plumbing have been aquired. The pressurisation parts will soon be integrated into the pressurisation fairing.

The detailed design for most units in the structures subsystem is complete and a qualification test of the standard body joint (to be used at most of the fairing joints of the rocket) has been successfully completed. Custom tooling to assist in integration of the body joints has been fabricated. The standard hatches and backing plates have been fabricated. A prototype fin has been tested but was found to have insufficient strength. An updated design and qualificiation test for the complete fin unit is currently being planned. Work is still needed for the separation ring. The Kerosene Tank ends have been machined. Efforts are underway to commission welding of the tank ends to the tank walls, which have already been prepared.

Detailed design is still underway for the Avionics Subsystem.

The configuration of the Recovery subsystem has been frozen. The parachutes (main nose cone) and drogue are being procured.