Rocketry GroupStudents’ Space AssociationWarsaw University of Technology Polish CanSat Launcher Adam Okniński SpaceUP Poland Warsaw, November 2012
Key issues SpaceUP Poland Introduction The rocket Final remarksHow did it start? Main subsystems PossibilitiesEarly ideas Unique features What’s next?
IntroductionHow did it start?Recent workEarly ideas
HistoryRocketry Group at WUT Amelia 1 rocket Youth education Publications Test stands, equipment …
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
Polish CanSatLauncherThe new rocketDesignMain subsystems
CanSat Launcher ’’H1” considerationsEarly ideasOne-stage rocket with a nonseparable dartRecovery module with 2 parachutesModular constructionComposite structure
AerothermodynamicsAnalyses in ANSYS Fluent – main bodyAnalyses in ANSYS Fluent – nose geometryLoads calculated on basis of the last modelComparison of different rocket configurationsFinal analysis of the whole rocket - to be donePrediction of highest temperatures
StructureOptions Monoque structure Stringers and bulheads structure
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
Solid propellantsPrepared 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
Payload, electronics Electronics Main Computer Backup Computer Main Power Unit Backup Power Unit Communication Module Payload Camera onboard CanSats Payload
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
The launcherThe 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
What’s next?Future plans Possibilities Connecting the idea of building the two-stage Amelia 2 and the one stage CanSat Launcher
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
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
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