Polish CanSat Launcher

SpaceUP Poland

Warsaw, November 2012

Adam Okniński

Rocketry Group Students’ Space Association Warsaw University of Technology

Key issues SpaceUP Poland

Introduction The rocket Final remarks

How did it start? Early ideas

Main subsystems Unique features

Possibilities What’s next?

Introduction

How did it start? Recent work Early ideas

Amelia 1 rocket

Youth education

Publications

Test stands, equipment …

History Rocketry 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 developments Students’ Space Association – Rocketry Group

Polish CanSat Launcher The new rocket Design Main subsystems

One-stage rocket with a non separable dart

Recovery module with 2 parachutes

Modular construction

Composite structure

CanSat Launcher ’’H1” considerations Early 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

Structure Options

Relatively easy manufacturing

Reusable

Relatively cheap

High propellant mass fraction

Smaller mass = more payload

Subscale motors being tested

The rocket motor For 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 Perchlorate Composite Propellant

High specific impulse

First developed propellants based on potasium nitrate, ammonium nitrate and ammonium perchlorate as oxidisers

Solid propellants Prepared in cooperation with the Institute of Aviation

Electronics

Main Computer

Backup Computer

Main Power Unit

Backup Power Unit

Communication Module

Payload

Camera onboard

CanSats

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: Composite motor case and nosecone, aluminum body and fins

The launcher The H1 rocket configuration

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?

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 altitude sounding capability

Possibilities

Thank you for your attention!

Adam Okniński a.m.okniński@gmail.com

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!