polish cansat launcher
TRANSCRIPT
Polish CanSat Launcher
SpaceUP Poland
Warsaw, November 2012
Adam Okniński
Rocketry GroupStudents’ Space AssociationWarsaw University of Technology
Key issuesSpaceUP Poland
Introduction The rocket Final remarks
How did it start?Early ideas
Main subsystemsUnique features
PossibilitiesWhat’s next?
Introduction
How did it start?Recent workEarly ideas
Amelia 1 rocket
Youth education
Publications
Test stands, equipment …
HistoryRocketry Group at WUT
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
Recent developmentsStudents’ Space Association – Rocketry Group
Polish CanSat LauncherThe new rocketDesignMain subsystems
One-stage rocket with a non separable dart
Recovery module with 2 parachutes
Modular construction
Composite structure
CanSat Launcher ’’H1” considerationsEarly ideas
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
Aerothermodynamics
Monoque structure
Stringers and bulheads structure
StructureOptions
Relatively easy manufacturing
Reusable
Relatively cheap
High propellant mass fraction
Smaller mass = more payload
Subscale motors being tested
The rocket motorFor the H1 rocket
Mass fraction (for chamber length/chamber diameter = 8)
Diameter [mm]
• Over 6 kg of solid rocket propellant• Composite structure• Design mass fraction > 70%
Ammonium PerchlorateComposite Propellant
High specific impulse
First developed propellants based on potasium nitrate, ammonium nitrate and ammonium perchlorate as oxidisers
Solid propellantsPrepared in cooperation with the Institute of Aviation
Electronics
Main ComputerBackup ComputerMain Power UnitBackup Power UnitCommunication Module
Payload
Camera onboardCanSats
Payload, electronics
Payload
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
Recovery
Parachute deceleration and recovery
One stage rocket
Height: 2000 mm
Diameter: 100 mm
Mass at liftoff: 17 kg
Ceiling: 8 km
Materials: Compositemotor case and nosecone,aluminum body and fins
The launcherThe H1 rocket configuration
H1 and Amelia 2 rocketsof the Rocketry Group,
Students’ Space Association
Key technologies being developed
• Solid rocket motor composite case manufacturing
• Solid rocket motor insulations tested
• Composite rocket elements manufacturing
• Composite and metal bonding
Possible difficulties
Recovery
Aeroelastic phenomena - flutter- divergence
High Mach numbers flight
http://fy.chalmers.se/~f3amj/Pics/notrock.gif
Final remarks
ConclusionWhat’s next?
Connecting the idea of building the two-stage Amelia 2 and the one stage CanSat Launcher
Possibilities
What’s next?Future plans
Conclusion
Possibilty of launching CanSat experiments
Development of equipment needed to build larger rockets
Development of advanced solid rocket motor
technology
Cheap low altitudesounding capability
Possibilities
Thank you for your attention!
Adam Oknińskia.m.okniń[email protected]
The presented materials consist of work doneby the members of the Rocketry Group including:
Bartosz Bartkowiak, Damian Kaniewski, Błażej Marciniak,Jan Matyszewski, Mateusz Sochacki…
Thank you for your help!