1. Rocketry Group
Students’ Space Association
Warsaw University of Technology
Polish CanSat Launcher
Adam Okniński
SpaceUP Poland
Warsaw, November 2012

2. Key issues
SpaceUP Poland
Introduction The rocket Final remarks
How did it start? Main subsystems Possibilities
Early ideas Unique features What’s next?

3. Introduction
How did it start?
Recent work
Early ideas

4. History
Rocketry Group at WUT
 Amelia 1 rocket
 Youth education
 Publications
 Test stands, equipment …

5. Recent developments
Students’ Space Association – Rocketry Group
 Amelia 2 rocket
 New launch tower
 Developed computer software:
- solid rocket motor optimization
- interior ballistics simulations
- composite case optimization
 Propellant production:
- mixer (for casting)
- mill
- elements to extrude
grains
 CFD & FEM analyses

6. Polish CanSat
Launcher
The new rocket
Design
Main subsystems

7. CanSat Launcher ’’H1” considerations
Early ideas
One-stage rocket with a non
separable dart
Recovery module with 2 parachutes
Modular construction
Composite structure

8. Aerothermodynamics
Analyses in ANSYS Fluent – main body
Analyses in ANSYS Fluent – nose geometry
Loads calculated on basis of the last model
Comparison of different rocket configurations
Final analysis of the whole rocket - to be done
Prediction of highest temperatures

9. Structure
Options
Monoque structure
Stringers and bulheads structure

10. The rocket motor Mass fraction (for chamber length/chamber diameter = 8)
For the H1 rocket
Relatively easy manufacturing
Reusable
Relatively cheap Diameter [mm]
High propellant mass fraction
Smaller mass = more payload • Over 6 kg of solid rocket propellant
• Composite structure > 70%
Subscale motors being tested
• Design mass fraction

11. Solid propellants
Prepared in cooperation with the Institute of Aviation
Ammonium Perchlorate
Composite Propellant
High specific impulse
First developed propellants based on
potasium nitrate, ammonium nitrate
and ammonium perchlorate as
oxidisers

12. Payload, electronics
Electronics
Main Computer
Backup Computer
Main Power Unit
Backup Power Unit
Communication Module
Payload
Camera onboard
CanSats
Payload

13. Recovery
Parachute deceleration and recovery
One parachute
Two stage opening
Attempts to minimize snatch force and opening shock values
About 10 m2 of fabric
Parachute shot out from the side of the rocket body

14. The launcher
The H1 rocket configuration
One stage rocket
Height: 2000 mm
Diameter: 100 mm
Mass at liftoff: 17 kg
Ceiling: 8 km
Materials: Composite
motor case and nosecone,
aluminum body and fins
H1 and Amelia 2 rockets
of the Rocketry Group,
Students’ Space Association

15. Key technologies being developed
• Solid rocket
motor composite
case
manufacturing
• Solid rocket
motor
insulations
tested
• Composite
rocket elements
manufacturing
• Composite
and metal
bonding

16. Possible difficulties
Recovery
Aeroelastic phenomena
- flutter
- divergence
High Mach numbers flight
http://fy.chalmers.se/~f3amj/Pics/notrock.gif

17. Final remarks
Conclusion
What’s next?

18. What’s next?
Future plans
Possibilities
Connecting the idea of
building the two-stage
Amelia 2 and the one
stage CanSat
Launcher

19. Conclusion
Development of Cheap low altitude
equipment needed to sounding capability
build larger rockets
Possibilities
Development of advanced
Possibilty of launching
solid rocket motor
CanSat experiments
technology

20. Thank you for your attention!
The presented materials consist of work done
by the members of the Rocketry Group including:
Bartosz Bartkowiak, Damian Kaniewski, Błażej Marciniak,
Jan Matyszewski, Mateusz Sochacki…
Thank you for your help! Adam Okniński
a.m.okniński@gmail.com