Open Theses

You found a topic you are interested in?

Do not hesitate to contact us. We can tell you more about your chosen topic and will tell you what your next steps are going to be.

Write us an e-mail to:
thesis@aris-space.ch 

New predefined topics for ETH, HLSU, ZHAW and HSR students

This project pool has been suggested by ARIS alumni and active members based on their knowledge from previous years. They element things to improve, gadgets to develop and parts to be newly designed.

Supersonic pitot tube

 
 A pitot tube can be used to measure the indicated air apeed which gives us more precise data than any accelerometer and barometer.
The task is to design and manufacture a pitot tube using additively manufacturing sponsored by our indutry partners. Additionally, a respective data interpretation alogrithm should be written.
It will be integrated into the EULER rocket and and thus be flying at the SPAC 2020 in New Mexico, USA.

Separation mechanism

  Currently the separation works by building up pressure in the rocket structure, which breaks shear pins located at the site of separation. However experience has shown, that this system is both big and not the most reliable. Changing to a system which mechanically locks both parts of the rocket together (akin to a camera bayonett for example) and ideally also performs the separation via mechanical / electrical or magnetical force.
(e.g. Piston Actuated Separation, Mechanical actuated separation, Electromagnetical Separation (Usage of electro (permanent) magnet to fixate and separate the rocket at apogee))

Additively manufactured fins

Design, analysis and testing of additively manufactured plastic fins for transonic and supersonic flights (+ strain gauges)

Thrust Vectoring 1

  Thrust vectoring becomes interesting when the burn time of our own developped
engines is long enough to get influenced. On our ways to orbit we need to direct the rockets with the help of thrust vectoring to stay on track. Therefore, a controlling for the related thrust vectoring mechanism needs to be established.

Thrust Vectoring 2

 Thrust vectoring becomes interesting when the burn time of our own developped
engines is long enough to get influenced. On our ways to orbit we need to direct the rockets with the help of thrust vectoring to stay on track. Therefore, a test stand to test the influence of vectoring mechanism and the mechanism itself should be designed. The thrusting mechanism can be realised by changing the direction of the nozzle exit or by including flaps to redirect the exhaust stream. The test itself can be conducted with pressurized gases enabling simpler testing.

Aerospike Nozzle

The aerospike engine is a type of rocket engine that maintains its aerodynamic
efficiency across a wide range of altitudes. It belongs to the class of altitude compensating nozzle engines. A vehicle with an aerospike engine uses 25–30% less fuel at low altitudes, where most missions have the greatest need for thrust. 
 

Launching ramp for HRE

Design, manufacture and test a launch ramp for 30’000 ft+ class rockets. The ramp must be light-weight, i.e. likely made primarily from aluminium including fluid supply system filling line needed for an HRE. The challenge of this assignment lies in designing for operability, manufacturability and cost. In the process of manufacturing, the student becomes proficient in the use of a TIG welding machine which is an exceptionally useful skill for prototyping work in dynamic environment. The ramp must be able to accomodate other ground support equipment, like swinging cameras, power and fluid connections – manufacture of this equipment is however not part of this task.The ramp must be able to be taken apart and transported on the roof of a family car. It must be able to be launch ready within 15 min by a team of 6 people. It must be transportable to the US via air freight.

Staging- & Separation Mechanism

Investigating study on staging of a rocket (2 stages). Therefore, different staging
mechanism should be investigated and the most effective one (in terms of weight, reliability, price, manufacturability,…) shoud be chosen to design and manufacture a small scale prototype.
Temperature sensoring

The metallic leading edge of the fins can be used to track temperature gradients and course of the rocket. Since resistance is changing with temperature, these data be used to analyse the temperature change during flight duration. The aim of this study should be on a feasiblity study, followed by the question on how to implement this temperature tracking system.

ROCKET PROJECT

 EULER 

Project EULER is going to be ARIS’ first supersonic rocket. At the SPAC in June 2020 in New Mexico, USA, EULER is aiming for a height of 30’000ft.

GET TO KNOW MORE ABOUT PROJECT EUER
HYBRID ROCKET ENGINE PROJECTS

RHEA and IRIDE

Project RHEA was the first generation of hybrid rocket engines in ARIS. Apart from creating the first-ever student-built test engine facility enabling us to do our own test firings, a 1’200N test engine has been manufactured as well.

Using RHEA as a basis, project IRIDE is designing a 5000N hybrid rocket engine that will be implemented in the rocket by 2021.

GET TO KNOW MORE ABOUT PROJECT RHEAGET TO KNOW MORE ABOUT PROJECT IRIDE

Done so far

Looking back to the two-year-old existence of ARIS, several projects have been finished, and some of them have successfully been implemented into our rockets.

FINISHED THESES

PUBLISHED PAPERS

Predefined Topics
REVIEWS

Make use of the possibility to join review with our industrial partners who support with their knowledge. Get feedback and suggestions from experienced experts and implement it in your system 

PROTOTYPING

Use our workspace and the facilities of the Student Project House to build the first prototypes. Step by step, you come closer to your final outcome.

ARIS COACH

To give you the optimal support, we provide you wtih the knowledge of an ARIS member, who is an expert on your field of study.

Our partner universities

The right mixture makes the difference