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.okniński@gmail.com

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!