Rocketry GroupStudents’ Space AssociationWarsaw University of Technology         Polish CanSat Launcher                   ...
Key issues       SpaceUP Poland   Introduction          The rocket        Final remarksHow did it start?       Main subsys...
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 co...
Polish CanSatLauncherThe new rocketDesignMain subsystems
CanSat Launcher ’’H1” considerationsEarly ideasOne-stage rocket with a nonseparable dartRecovery module with 2 parachutesM...
AerothermodynamicsAnalyses in ANSYS Fluent – main bodyAnalyses in ANSYS Fluent – nose geometryLoads calculated on basis of...
StructureOptions    Monoque structure    Stringers and bulheads structure
The rocket motor                  Mass fraction (for chamber length/chamber diameter = 8)For the H1 rocket  Relatively eas...
Solid propellantsPrepared in cooperation with the Institute of Aviation   Ammonium Perchlorate   Composite Propellant   Hi...
Payload, electronics            Electronics               Main Computer               Backup Computer               Main P...
Recovery   Parachute deceleration and recovery  One parachute  Two stage opening  Attempts to minimize snatch force and op...
The launcherThe H1 rocket configuration                                One stage rocket                                Hei...
Key technologies being developed• Solid rocketmotor compositecasemanufacturing• Solid rocketmotorinsulationstested• Compos...
Possible difficulties      Recovery      Aeroelastic phenomena      - flutter      - divergence      High Mach numbers fli...
Final remarksConclusionWhat’s next?
What’s next?Future plans               Possibilities                  Connecting the idea of                  building the...
Conclusion     Development of                          Cheap low altitude   equipment needed to                      sound...
Thank you for your attention!     The presented materials consist of work done   by the members of the Rocketry Group incl...
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Polish CanSat Launcher

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Polish CanSat Launcher

  1. 1. Rocketry GroupStudents’ Space AssociationWarsaw University of Technology Polish CanSat Launcher Adam Okniński SpaceUP Poland Warsaw, November 2012
  2. 2. Key issues SpaceUP Poland Introduction The rocket Final remarksHow did it start? Main subsystems PossibilitiesEarly ideas Unique features What’s next?
  3. 3. IntroductionHow did it start?Recent workEarly ideas
  4. 4. HistoryRocketry Group at WUT Amelia 1 rocket Youth education Publications Test stands, equipment …
  5. 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. 6. Polish CanSatLauncherThe new rocketDesignMain subsystems
  7. 7. CanSat Launcher ’’H1” considerationsEarly ideasOne-stage rocket with a nonseparable dartRecovery module with 2 parachutesModular constructionComposite structure
  8. 8. 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
  9. 9. StructureOptions Monoque structure Stringers and bulheads structure
  10. 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. 11. 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
  12. 12. Payload, electronics Electronics Main Computer Backup Computer Main Power Unit Backup Power Unit Communication Module Payload Camera onboard CanSats Payload
  13. 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. 14. 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
  15. 15. Key technologies being developed• Solid rocketmotor compositecasemanufacturing• Solid rocketmotorinsulationstested• Compositerocket elementsmanufacturing• Compositeand metalbonding
  16. 16. Possible difficulties Recovery Aeroelastic phenomena - flutter - divergence High Mach numbers flight http://fy.chalmers.se/~f3amj/Pics/notrock.gif
  17. 17. Final remarksConclusionWhat’s next?
  18. 18. What’s next?Future plans Possibilities Connecting the idea of building the two-stage Amelia 2 and the one stage CanSat Launcher
  19. 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. 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
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