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Rocketry Group
Students’ Space Association
Warsaw University of Technology




         Polish CanSat Launcher
                      Adam Okniński




                    SpaceUP Poland




                  Warsaw, November 2012
Key issues
       SpaceUP Poland


   Introduction          The rocket        Final remarks




How did it start?       Main subsystems   Possibilities
Early ideas             Unique features   What’s next?
Introduction

How did it start?
Recent work
Early ideas
History
Rocketry 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 CanSat
Launcher
The new rocket
Design
Main subsystems
CanSat Launcher ’’H1” considerations
Early ideas




One-stage rocket with a non
separable dart


Recovery module with 2 parachutes

Modular construction


Composite structure
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
Structure
Options



    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 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
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 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
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
Conclusion
What’s next?
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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Polish CanSat Launcher

  • 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
  • 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