spaceup paris
TRANSCRIPT
Amelia 2 Two-Stage Test Rocket
SpaceUP Paris
Paris, May 2013
Adam Okniński
Rocketry Group Students’ Space Association Warsaw University of Technology
Key issues SpaceUP Paris
Introduction The rocket Final remarks
How did it start? Early ideas
The idea Main subsystems
Possibilities What’s next?
Introduction
How did it start? Recent work
Amelia 1 rocket
PW-Sat – first Polish satellite
SCOPE 2 Experiment
Martian Rovers
History Students’ Space Association, Rocketry Group
Amelia 2 rocket
’’H1” CanSat Launcher
Smaller test rockets
Propellant production: - mixer (for casting) - mill, etc.
Launch pads
Test stands
Composite structure production equipment
Recent developments Students’ Space Association – Rocketry Group
Amelia 2 rocket
The idea Design methodology Main subsystems
Two-stage test rocket powered by two rocket motors
Both stages equiped with parachute recovery modules
Simple, low-cost rocket testing the possiblity of developing the full scale two-stage sounding rocket
Amelia 2 The idea
Mission profile
Two stage rocket
Height: 2214 mm
Diameter: 94 mm
Mass at liftoff: 7,2 kg
Ceiling: 3 km
Materials: composites, duraluminum
Amelia 2 The Amelia 2 rocket data Amelia 2 rocket
of the Rocketry Group, Students’ Space Association
Amelia 2 Rocket configuration
I stage rocket motor
II stage rocket motor
Place for an optional larger rocket motor
I stage recovery module
II stage recovery module
Electronics and payload bay
Onboard camera
GPS Tracker
Aerothermodynamic analyses in ANSYS Fluent – main body
All elements modeled in CATIA
Loads calculated analitycaly, use of FEM (ANSYS)
Developed computer software: - solid rocket motor optimization - interior ballistics simulations - composite case optimization
Design methodology
First stage: monoque structure
Second stage: stringers and bulkheads
Structure Amelia 2 rocket
The same rocket motors in both stages during the first flight (simplicity)
Self-developed technology - reusable composite solid rocket motors
Ammonium Perchlorate composite propellant
Specific Impulse - 225 s
Rocket motors For the Amelia 2 rocket
• 0,43 kg of solid rocket propellant • Composite structure • Propellant mass fraction > 45%
Electronics
Main Computer
Main Power Unit
Payload
Camera onboard
GPS Tracker
Possible small experiment
Payload, electronics, recovery
Payload
Recovery, stage seperation
Parachute recovery for both stages
Pyrogen expulsion
Final remarks
Conclusion What’s next?
Using the knowledge
earned during the
development of the
two-stage Amelia 2
and the simultaneously
developed one stage
CanSat Launcher
Possibilities
What’s next? Future plans
Conclusion
Launching small experiments
Demonstrating the capability to build
reusable staged rockets
Development of advanced solid rocket motor
technology
Cheap low altitude sounding capability
Possibilities
Thank you for your attention!
Adam Okniński a.m.okniń[email protected]
The presented materials consist of work done by the members of the Rocketry Group including:
Bartosz Bartkowiak, Dawid Cieśliński, Tadeusz Górnicki, Damian Kaniewski, Błażej Marciniak, Jan Matyszewski,
Mateusz Sochacki; Thank you for your help!