Are you an EPFL student and looking for a semester credited, Bachelors or Masters Project ? Look no further! We have something for you!
If you can’t find your dream project down here, but have an idea or would like to suggest your own project to do with us, we are open to suggestions! Feel free to contact us and we can talk about it.
SPRING 2025
COMPETITION PROJECT
Structure
PROJECT DESCRIPTION
In order to dimension the structural parts of its rockets, the EPFL Rocket Team mainly uses structural simulations based on the Finite Element Method (FEM). Simulating an entire structural segment (like the one in the image below) is a difficult task, in part because the contacts between all of the different parts introduce a lot of nonlinearities. Moreover, using destructive testing to verify/validate simulations can be very expensive.
A common method used in aerospace engineering to verify/validate large coupled FE models is to compare simulated and experimental modal analysis. By experimentally extracting the modal frequencies and mode shapes and correcting the FE models until the simulation results match with the experiment, it is possible to verify and correct large coupled FE models in a non-destructive manner.
Figure: Side view of a segment of the rocket internal structure, its 4 carbon rods (3 visible), and its aluminum anti buckling rings. The entire rocket is composed of multiple structural segments like this one.
This project has three goals: to establish a procedure/methodology to conduct experimental modal analysis, to establish a methodology to update FE models to match with experimental results, and to apply both methodologies on a rocket structural segment as a case study. The experimental modal analysis can be done using accelerometers and impulse excitation (hammer). The finite element model to validate will be created in ANSYS, which will also be used for the simulated modal analysis.
Figure: Modal Assurance Criterion (MAC) matrix typically used to compare experimental and simulated modes[1]
PROJECT UNFOLDING:
- [2 weeks]: Literature review
- [5 weeks]: Setting up experiment
- [2 weeks]: Experimental analysis
- [4 weeks]: FE Model correction
- [1 week]: Documentation
SKILLS INVOLVED:
- Structural dynamics
- Modal analysis
- Practical testing
- FE Simulations
- ANSYS (Mechanical)
STUDENT GAIN :
- Gaining experience on practical testing
- Gaining experience on simulation validation
- Gaining experience on structural dynamics
- Opportunity to work on a complex and very advanced structural engineering topic
Contacts: michael.fuser@epfl.ch
Supervisor: Villanueva
Number of students: Available
Reference links:
PROJECT DESCRIPTION
The EPFL Rocket Team is currently developing a new class of rockets aimed at launching at an altitude of 9 km during the EuRoC 25 student rocketry competition and to launch at an altitude of 30 km in 2026. These launch vehicles are propelled by a biliquid engine. Two cylindrical aluminum tanks are located along the rocket length to store the propellant and oxidizer.
The in-flight accelerations experienced by the rocket can cause the fluid located inside the tanks to ‘move around’ (see image). This phenomenon is called sloshing and can lead to flight instabilities due to the movement of the center of mass of the rocket.
Additionally, vortices can sometimes appear at rocket tank outlets, just like in bathtubs or sinks when they are being emptied. These vortices can lead to instabilities in the mass outflow rate, which can have undesired effects on the propulsion system.
This project has three goals: to determine whether the current tanks design can experience sloshing, to determine whether they can experience vortex buildup at the outlet, and to identify mitigations to counter these phenomena.
To do this, experiments will be conducted under the supervision of the EPFL SCI-STI-MF group. Mockup tanks of the currently planned dimensions will be constructed and used for tests.
What the student will do :
- Construct the mockup tanks used for tests
- Perform the experimental test campaign
- Suggest and possibly test potential mitigations
Figure: Typical mitigation sometimes employed in rocket tanks to prevent vortex buildup at the outlet.
STUDENT GAIN:
- Practical prototyping experience
- Experience as a test engineer
- Experience on notoriously difficult aerospace engineering/fluid mechanics problem
SKILLS INVOLVED:
- Prototyping
- Testing
- Fluid mechanics/dynamics
- Problem solving
PROJECT UNFOLDING:
- [2 weeks]: Literature review
- [3 weeks]: Mockup tank production
- [8 weeks]: Test campaign
- [1 week]: Documentation
Contacts: michael.fuser@epfl.ch
Supervisor: Villanueva
Status: Available
PROJECT DESCRIPTION
The association plans to launch a sounding rocket named FIREHORN, that will fly at an altitude of 9 km in October 2025 and at 30km in October 2026. Many of the parts used in these rockets are made of carbon composite, and can be very expensive to produce. An innovative solution was tested last semester using 3D-printed molds. This type of production proved promising and merits further research and improvement.
The aim of this project is to improve the production process using 3D printed molds. Students will start by researching the different materials available for 3D printing, and then look for the right parameters to obtain a satisfactory mold. They will continue with manufacturing and testing.
What the student will do :
- Literature review
- Conception of the parts and manufacturing method
- Materials selection
- Mechanical tests
SKILLS INVOLVED:
- Literature review, CAD, FEM
- Composite manufacturing, machining
- Traction, Flexion, Modal
PROJECT UNFOLDING:
- [5 weeks]: Conception
- [3 weeks]: Tooling Manufacturing
- [6 weeks]: Parts Manufacturing
Contacts: michael.fuser@epfl.ch
Supervisor: TBD
Status: Available
Reference links:
- Quick overview of different CFRP manufacturing techniques: https://element6composites.com/carbon-fiber-manufacturing-methods/
- Research article on overview of different manufacturing techniques for carbon fiber reinforced thermoplastics: https://www.sciencedirect.com/science/article/pii/S0142941823001095
- Quick overview of molds made using 3D printing: Making a Composite Mould from a 3D Printed Pattern – Easy Composites
PROJECT DESCRIPTION
The association plans to launch a sounding rocket named FIREHORN, that will fly at an altitude of 9 km in October 2025 and at 30km in October 2026. The firehorn structure is made up of different modules, each of which is made up of a coupling system linked by 4 carbon rods. In order to guarantee resistance to load and buckling in particular, the structure has aluminium parts called “Anti-buckling rings” placed in each module according to their size. 
This structure was studied during the previous year, and it was deduced that there is potential in the search for lighter, more resistant materials for this type of part.
The aim of this project is to improve the ABRs between the 9km and 30km flights. The students will start by studying previous work on the subject, then look for different candidate materials for this type of part. Non-linear buckling simulations will then be carried out, followed by prototype fabrication and testing.
What the student will do :
- Materials selection
- Non-linear buckling simulations
- Manufacture of composite parts
- Test procedure
- Buckling tests
- Results comparison with numerical models
- Writing a general methodology for mechanical tests
SKILLS INVOLVED:
- Anisotropic solid mechanics
- Composites (CFRP)
- Lab work
- Static simulations
- Experiments planning
PROJECT UNFOLDING:
- [2 week]: Literature review
- [2 weeks]: Simulations
- [2 weeks]: Testing samples production
- [6 weeks]: Mechanical tests
- [2 weeks]: Results analysis and reports
Contacts: michael.fuser@epfl.ch
Supervisor: TBD
Status: Available
Reference links:
- eBook-Ensuring-Compliance-with-ASTM-FINAL.pdf (shimadzu.com)
- Tensile strength of unidirectional CFRP laminate under high strain rate: Advanced Composite Materials: Vol 16, No 2 (tandfonline.com)
Recovery
PROJECT DESCRIPTION
The EPFL Rocket Team’s goal is to fly a rocket that will reach the Karman line by 2030. One critical stage of the mission is the rocket’s recovery. The rocket team has been working on recovery systems since it first started; however, our target apogee has never been above 9km. Given that the target apogee altitude is considerably higher than any previous missions, the operational environment requirements have also changed.
Following the change of requirements, several assemblies of the recovery subsystem’s design will need to change. Thus we would like to start the mission analysis, needs identification and feasibility study (ECSS Project Phase 0 and A) for the recovery subsystem.
The project aims to provide the first iteration of the systems engineer’s responsibilities during phase 0 and phase A (as defined by ECSS) of a project. The deliverables include: preliminary technical requirements specifications, work breakdown structure and function tree, risk assessment document and preliminary concept of operations document.
What the student will do :
- Characterisation of mission
- Establish the needs, expected performance and dependability and safety goals
- Assessment of operating constraints
- Identification of possible system concepts
- Picking a system concept
- Modeling the chosen system concept
- Establish a preliminary list of requirements
STUDENT GAIN:
- Systems engineering
- Requirement engineering
- Interface management
- System modeling
PROJECT UNFOLDING:
- [3 weeks]: General research and state of the art analysis
- [3 weeks]: Identification and characterization of the mission needs, expected performance, dependability and safety goals and mission operating constraints
- [4 weeks]: Establish function tree, system modeling
- [3 weeks]: Establish technical requirement specification
Contacts: kelan.solomon@epfl.ch
Supervisor: Volker Gass
Number of students: Available
Reference links:
- ECSS-M-ST-10C: Space project management, Project planning and implementation (http://everyspec.com/ESA/download.php?spec=ECSS-M-ST-10C.048180.pdf)
- ECSS-E-ST-10C: Space engineering, System engineering general requirements (http://everyspec.com/ESA/download.php?spec=ECSS-E-ST-10C.047801.pdf)
- ECSS-E-ST-10-06C: Space engineering, Technical requirements specification (http://everyspec.com/ESA/download.php?spec=ECSS-E-ST-10-06C.048163.pdf)
- SpaceX Dragon Recovery (https://www.youtube.com/live/-ufAVMRGf9Q?si=ZCul_P2TxpztfvEJ&t=174)
ICARUS PROJECT
PROJECT DESCRIPTION
The EPFL Rocket Team is developing a Vertical Takeoff, Vertical Landing (VTVL) Hopper named Icarus. Its aim is to perform “hops” : brief, low-altitude (maximum 5 metres), vertical trajectories with hovering time at the apogee. In order to achieve thrust vectoring capabilities, Icarus has developed a gimbal system to redirect the engine’s thrust, thereby enabling control over the yaw and pitch of the vehicle. This, however, leaves roll – rotations around the vertical axis – completely unchecked.
Render of the Icarus Hopper
The objective of this semester project is to test the reaction control wheel on a drone version of the Hopper which is already built. This allows for low impact testing – if the drone crashes, it can easily be repaired. Data from these tests would provide insights into the wheel’s torque generation, response time, and impact on overall stability, allowing for fine-tuning and optimization before implementation on the actual Hopper.
A sizing tool will be developed in order to find the correct mass, inertia, actuator power and battery capacity relative to the launch vehicle’s inertia and desired control authority over the vehicle’s roll.
WHAT THE STUDENT(s) WILL DO:
- Literature review
- Actuator dimensioning & selection
- Mechanical design
- Manufacturing of the wheel and motor mount
- Simple Controller coding
- Test procedure & testing
- Preliminary design of a reaction wheel for the Hopper
- Documentation
SKILLS INVOLVED:
- Mechanical design
- Quick prototyping
- Testing
TASKS UNFOLDING:
- [4 weeks]: Design and prototyping
- [3 weeks]: Manufacturing
- [3 weeks]: Assembly & Integration
- [2 weeks]: Testing
- [2 weeks]: Documentation
Contacts: guillaume.hueber@epfl.ch
Supervisor: TBD
Number of students: TAKEN
PROJECT DESCRIPTION
The EPFL Rocket Team’s goal is to fly a rocket that will reach the Karman line (100km altitude) by 2030. The Icarus project has the aim of providing active control to this rocket.
The goal of this project is to design and implement a set of controllable canards that can adjust the rocket’s pitch, yaw, and roll in real-time, providing critical stability and directionality during ascent and descent. Unlike traditional fins, which offer only passive stabilization, these actively controlled canards will allow for dynamic adjustments to compensate for environmental disturbances and flight path deviations.
Description of different parts of a rocket (with canards)
The objective of this semester project is to develop a preliminary design for an active canard control system for a suborbital rocket. This includes setting the system requirements, determining the optimal canard size, selecting appropriate actuators for the vehicle’s specifications, and creating an initial mechanical design. These foundational steps will define the canard system’s feasibility and readiness for future development phases, ensuring the design meets stability and control requirements for suborbital flight.
It should be noted that Grid Fins could replace the canards architecture if necessary.
WHAT THE STUDENT(s) WILL DO:
- Establish the needs, expected performance and safety goals
- Establish a list of requirements
- Make a risk analysis, a design structure matrix and a budget plan
- Hold and defend a Systems Requirements Review (SRR)
- Create a sizing tool for the canards and actuators combination
- Mechanical design of the Canards Bay to fit current rocket architecture
- Hold and defend a Preliminary Design Review (PDR)
- Small-scale prototype of the design
SKILLS INVOLVED:
- System Engineering
- Documentation
- Mechanical Design
- Fluid Dynamics
TASKS UNFOLDING:
- [3 weeks]: General research and state of the art analysis
- [4 weeks]: Establish technical requirement and deliverables
- [2 weeks]: Create Sizing Tool
- [4 weeks]: Mechanical Design
Contacts: guillaume.hueber@epfl.ch
Supervisor: TBD
Number of students: TAKEN
Reference links:
- Past ERT semester project on the PID controller for a canard configuration:
ERT-Active_attitude_control-Aurélien_Soenen.pdf
PROJECT DESCRIPTION
The EPFL Rocket Team is developing a Vertical Takeoff, Vertical Landing (VTVL) Hopper named Icarus. Its aim is to perform “hops” : brief, low-altitude (maximum 5 metres), vertical trajectories with hovering time at the apogee. To achieve precise thrust vectoring, Icarus is equipped with a gimbal system that redirects the engine’s thrust, allowing for stabilized control during flight. Given this setup, understanding the vehicle’s vibrational behavior is critical for ensuring the integrity of the structure, the performance of the gimbal, and the reliability of the avionics system.
Render of the Icarus Hopper
The objective of this semester project is to design, manufacture and program a standalone multi-point vibration sensing system for the Icarus Hopper.
By deploying a distributed network of sensors, the system will collect vibration data throughout the vehicle’s structure, gimbal mechanism, and avionics system during flight.
WHAT THE STUDENT(s) WILL DO:
- Literature review
- Sensors selection
- Power dimensioning
- PCB design and assembly
- Testing
- Documentation
SKILLS INVOLVED:
- PCB design
- Programming
- Signal processing
- Quick Prototyping
- Testing
TASKS UNFOLDING:
- [4 weeks]: Design and prototyping
- [3 weeks]: Manufacturing
- [3 weeks]: Assembly & Integration
- [2 weeks]: Testing
- [2 weeks]: Documentation
Contacts: axel.juaneda@epfl.ch
Supervisor: TBD
Number of students: Available
Reference links:
- Past ERT semester project on the PID controller for a canard configuration:
ERT-Active_attitude_control-Aurélien_Soenen.pdf
HYPERION PROJECT
P-Class
PROJECT DESCRIPTION
The Hyperion Plasma team works on electric space propulsion. The Team developed one thruster and is in the process of making another one. In order to test the thrusters in vacuum condition, they need to be put in vacuum chambers with specific interfaces.
The test bench is already built but the electric interfaces and plumbing interfaces need to be adapted to the team needs. This includes cable management, gas feed into the chamber and vacuum compatibility of all the components. The project also includes a thorough literature review to ensure the interface meets international aerospace standards.
WHAT THE STUDENT(s) WILL DO:
- Design the electrical interface
- Design the plumbing
- Design the user interface for testing
SKILLS INVOLVED:
- CAD
- Electricity
- Rocketry plumbing
- Manufacturing
TASKS UNFOLDING:
- [2 weeks]: Literature review
- [3 weeks]: Electric interface
- [3 weeks] : Plumbing interface
- [ 4 weeks] : Testing
Contacts: matthieu.tonneau@epfl.ch
Supervisor: TBD
Number of students: Available
Reference links:
- A guide to preparing your vacuum system for thruster testing chambers: https://www.leybold.com/en-ie/knowledge/blog/vacuum-systems-for-thruster-testing
PROJECT DESCRIPTION
The Hyperion Plasma team works on electric space propulsion. The Team developed one thruster and is in the process of making another one. In order to qualify those thrusters, they need to be put in vacuum chambers and in stringent conditions. This poses some challenges namely to feed the various energy and fluid supplies into the thruster. To alleviate some of that challenge, the team would like to place the thruster control and power electronics directly into the vacuum chamber next to the thrusters. However this poses some challenges with regards to the circuit design. This project aims to convert an existing power processing unit (PPU) design for vacuum use.
The student will first delve into what it means for electronic systems to be “vacuum compatible” by doing a thorough literature review and documenting all relevant findings. Once the scope of the project is more understood, the student will then review the current PPU board and identify key improvement points. After rigorously planning and detailing all the necessary changes, the student will move onto the manufacturing and/or improvement of the design hands-on.
WHAT THE STUDENT(s) WILL DO:
- Review and understand existing hardware
- Review general design for vacuum guidelines
- Iterate on the current design
- Implement the changes
SKILLS INVOLVED:
- Electronics
- Power electronics
- Design for vacuum
- Design for space applications
- Electric space propulsion
PROJECT UNFOLDING:
- [2 weeks]: Literature review
- [2 weeks]: Current design review
- [8 weeks]: Design exploration and modification planning
- [2 weeks]: implementation of the necessary changes.
Contacts: matthieu.tonneau@epfl.ch
Supervisor: TBD
Number of students: Available
Reference links:
PROJECT DESCRIPTION
The Hyperion Plasma Team focuses on electric propulsion. The Team has done research on the overall concept of the Hall Effect thruster (HET) and has come down to a preliminary design. In order to make a functional thruster, the plumbing (gas delivery system) and the design of the gas injector has to be done.
The goal of the project is to to design the plumbing of the thruster responsible for the gas injection into the chamber. The gas delivery system is constrained by weight and size limitations as well as material choices. The injector is also to be designed to maximize the gas volume in the chamber of the thruster.
WHAT THE STUDENT(s) WILL DO:
- Develop the plumbing of the thruster
- Design the gas injector
SKILLS INVOLVED:
- Fluid mechanics
- CAD
- Plumbing knowledge
- Prototyping
PROJECT UNFOLDING:
- [2 weeks]: Literature review
- [3 weeks]: Develop the gas injector
- [3 weeks]: Develop a preliminary plumbing
- [3 weeks] : Prototyping
- [3 weeks] : Testing and iteration
Contacts: matthieu.tonneau@epfl.ch
Supervisor: TBD
Number of students: Available
Reference links:
- Overview of Hall Effect thrusters : https://en.wikipedia.org/wiki/Hall-effect_thruster
- Review of Hall Thruster Neutral Flow Dynamics : https://pepl.engin.umich.edu/pdf/IEPC-2007-038.pdf
PROJECT DESCRIPTION
Through the Hyperion plasma class (H-PC) project, the EPFL Rocket Team endeavors to develop, test and qualify thrusters for space applications. A first set of technologies were selected: a pulsed plasma thruster (PPT) and a hall-effect thruster (HET).
A Hall-effect thruster (HET) is an advanced electric propulsion device commonly used in satellites. It operates by ionizing a neutral gas, typically xenon, with an electric field. The ions are then accelerated by a combination of electric and magnetic fields, creating thrust as they exit the thruster. A magnetic field traps electrons in a circular path (the “Hall effect”), maintaining ionization while allowing efficient acceleration of ions. This design provides high efficiency and specific impulse, making it ideal for long-duration space missions.
With the initial study of the Hall-Effect thruster coming to an end, a particular care now has to be put into creating the auxiliary systems, namely the fluid distribution and power electronics. This project focuses on the latter.
The student will first define the general architecture of the circuit. He/She will then move onto selecting the specific electronic components using the most up-to-date performance specifications. Finally, after reception of the components, the project will move to the assembly phase where the student is expected to build and qualify the PCB for use with the Hall-Effect thruster. The student is also expected to thoroughly document his/her work for posterity and future developments.
SKILLS INVOLVED:
- Power electronics
- PCB design
- Design for space applications
PROJECT UNFOLDING:
- [4 weeks]: Circuit architecture definition
- [4 weeks]: Components selection and order
- [6 weeks]: Assembly and qualification
Contacts: matthieu.tonneau@epfl.ch
Supervisor: TBD
Number of students: Available
Reference links:
PROJECT DESCRIPTION
The Hyperion Plasma team works on electric propulsion. The Team developed a first version of a pulsed plasma thruster which is currently undergoing testing. It is expected that the lessons learned from this first campaign will reveal some improvement perspectives which the students are expected to take advantage of.
The goal of the project is to improve the design of the thruster based on the feedback from the test. The manufacturability has to be taken into account as well as the material choices. While the improvements will remain at the conceptual stage, the students are expected to end up with a comprehensive CAD model that encompasses all of the improvements. If time allows, the students may begin part of the manufacturing.
WHAT THE STUDENT(s) WILL DO:
- Improve mechanical design
- Improve manufacturing process
- Select materials
- Testing
SKILLS INVOLVED:
- CAD
- Data analysis
- Manufacturing knowledge
PROJECT UNFOLDING:
- [2 weeks]: Literature review
- [4 weeks]: Translating test data into design flaws
- [ 6 weeks ] : Improving the design
Contacts: matthieu.tonneau@epfl.ch
Supervisor: TBD
Number of students: Available
Reference links:
- Pulsed Plasma Thruster : https://en.wikipedia.org/wiki/Pulsed_plasma_thruster
- Design and Testing of a Small Inductive Pulsed Plasma Thruster : https://electricrocket.org/IEPC/IEPC-2015-50_ISTS-2015-b-50.pdf
Testing Facility
PROJECT DESCRIPTION
The EPFL Rocket team (ERT) is currently developing a new generation of rockets and rocket engines aiming, among other goals, at a spaceshot in the coming years. To support this, a new testing facility has been built for the upcoming testing of these engines. This facility is currently designed and built for engines of up to 15kN, which corresponds to the thrust needed for the Firehorn II rocket, which will be launched at the end of 2026. However, the safety analyses have only been made for the current disposition (engine power of only 5kN). This Bachelor Project aims at furthering the EPFL Rocket Team’s capabilities in terms of safety analyses and at adapting the current safety plan to the 15kN configuration.
This Bachelor Project will focus on creating new simulations for the safety analyses of the Testing Facility, and on using both these simulation results and the characteristics of Firehorn II to update our safety analyses. These updates will enable us to make new safety recommendations and to adapt our current procedures, our operations and other technical aspects of the system.
WHAT THE STUDENT(s) WILL DO:
- Discovery of the safety aspects of a complex system
- Simulations
- Safety analyses
- Recommendations following the knowledge gained
SKILLS INVOLVED:
- Simulations
- Computations related to safety analyses
- Understanding of risk management
- Ability to make assessments and recommendations
TASKS UNFOLDING:
- [2 weeks]: Understanding the current state of analysis
- [3 weeks]: Create a set-up for simulations of explosions
- [3 weeks]: Refine the set-up by real life testing of different scenarios
- [2 weeks]: Simulate & derive new and better parameters for our analyses
- [3 weeks]: Adaptation of all safety analyses to the FH II rocket configuration + with these new parameters
- [1 week]: Report & presentation
Contacts: damien.delespaul@epfl.ch
Supervisor: TBD
Number of students: Available
Reference links:
- Guidelines for quantitative risk assessment
- Method for the calculation of physical effects: PGS 2
- Methods for determining and processing probabilities
PROJECT DESCRIPTION
eSpace is actively researching and developing methods and products in space sustainability. This large topic includes work on space debris risks, life cycle assessment of space systems, mitigations of environmental impacts, and decision-making support tools to include sustainable aspects in the early design phase of space missions and systems.
The assessment of the environmental impacts of rocket engine exhausts in the atmosphere is not yet backed by solid scientific knowledge. There is no accepted method to translate the emission of a given amount of exhaust species (like CO2, CO, H2O, HCl, black carbon, or else) at high altitude into an impact (like CO2 equivalent). What can be done already is to quantify the emissions of propulsion systems, so as to understand which particles and gases are generated and exhausted by the engine and in what quantity during tests.
The EPFL Rocket Team is developing and testing new propulsion systems, with engines using different types of propellant, and based on new design, in preparation for its future rockets. The medium-term goal of the ERT is to fly to 100 km altitude.
The topic is and large companies in Europe. Many are interested in measuring emissions of their engines during ground tests and directly in the atmosphere, to understand the chemistry that takes place at different altitude level. Several projects are ongoing or will soon start, through ESA or directly with industrial entities.
The main goal of the project is to prepare a measurement campaign of the exhaust gases and particles generated by rocket engines used by the EPFL Rocket Team.
The test bench used by the team will require adaptations to accommodate sensors needed for the measurements. The measurements can possibly be carried out during ignition tests, and static fire tests.
It is also in the scope to investigate the feasibility to conduct another test campaign during low altitude launches by the EPFL Rocket Team.
WHAT THE STUDENT(s) WILL DO:
- A report including
- The state-of-knowledge regarding launchers’ exhausts.
- The state-of-affair regarding sensing method for the species of interest.
- A list of selected gas / particle sensors and measurement instruments adapted to the task.
- Computer-Aided Drawings of the ERT’s test bench adaptations, needed for exhaust measurements.
- Recommendations for future studies.
- A comprehensive test procedure to conduct a measurement campaign.
- (optional, if time allows) Results of some measurements made on the ERT propulsion system, in a format easy to use for future students.
TASKS UNFOLDING:
- Phase 1:
- Literature review on launchers’ exhausts depending on their propulsion type.
- Searching for the best suited sensors to perform measurements of interest.
- Phase 2 (after ordering some sensors):
- Drawing CAD adaptation for the test bench.
- Writing a test procedure to use for a measurement campaign.
- Implement changes on the test bench (and if time allows, perform sets of measurement using the sensors).
- Phase 3:
- Searching for the best suited sensors and measurement scenario(s) to perform in-flight data collection of emissions of interest. Ideas include but should not be limited to: on-board sensors, air balloons, second rocket with sensors, satellite imaging, etc.
- Deeper investigation and systems architecture for a subset of selected potential solutions.
Contacts: mathieu.udriot@epfl.ch leonard.bongiovanni@epfl.ch
Supervisor: TBD
Number of students: Available
A-Class
PROJECT DESCRIPTION
The EPFL Rocket Team is developing “Icarus,” a Vertical Takeoff, Vertical Landing (VTVL) hopper designed for controlled, low-altitude (up to 5 meters) vertical “hops” with hovering capability. As a technology demonstrator, Icarus will advance control systems critical for stable rocket flight, supporting future missions like the Firehorn rockets. A core feature is the integration of Cold Gas Thruster (CGT) technology, a low-thrust system that stabilizes the vehicle through radial gas expulsion. Commonly used in satellite control and by SpaceX, CGT will help Icarus maintain stability in vertical maneuvers, enhancing our team’s future space-bound capabilities.
Render of the Icarus Hopper and Picture of a Cold Gas Thruster on F9 rocket
- The primary objective of this project is to design a Cold Gas Thruster (CGT) system that can be integrated seamlessly into the Hopper’s structure. Students will be tasked with selecting appropriate components, performing calculations to achieve precise thrust control, designing the plumbing architecture, and creating a full CAD model of the system.
- The second objective focuses on manufacturing to ensure that the design complies with the specified requirements and operates reliably within the system. Students will be responsible for assembling all components of the CGT system, ensuring that the final assembly adheres to design specifications and avoids any potential issues.
- The third objective is to test the system and analyze its significance for future vehicles. Students will develop a testing procedure, conduct tests, and evaluate whether the system meets the defined performance criteria, providing essential insights for the development of subsequent rockets.
WHAT THE STUDENT(s) WILL DO:
- Literature review
- Components choice
- Actuator dimensioning & selection
- Plumbing architecture
- Simple Controller coding
- Mechanical design & assembly
- Integration to Hopper’s structure
- Test procedure & testing
- Documentation
SKILLS INVOLVED:
- Mechanical design
- Plumbing knowledge
- Hardware coding
- Quick Prototyping
- Testing
TASKS UNFOLDING:
- [2 weeks]: Litterature review
- [4 weeks]: System design
- [3 weeks]: Assembly & Integration
- [3 weeks]: Testing
- [2 weeks]: Documentation
Contacts: leonard.bongiovanni@epfl.ch
Supervisor: TBD
Number of students: TAKEN
Reference links:
- Wikipédia – Cold Gas Thruster: https://en.wikipedia.org/wiki/Cold_gas_thruster
B-Class
PROJECT DESCRIPTION
In the context of the Hyperion project, the EPFL Rocket Team is currently in the process of developing a pump-fed rocket engine known as DEMO-B2.
In a previous project, we focused on optimizing the pump’s geometry to ensure it met the engine’s requirements. The objective for this semester’s project is to verify the validity of a Barske geometry to assess if it could simplify the manufacturing process while still ensuring compliance with the necessary requirements, and compare the performance with the previous geometry.
Barske geometry
WHAT THE STUDENT(s) WILL DO:
- Verify the results of past studies
- Simulate the model on a CFD software
- Prepare the documentation for production and testing
SKILLS INVOLVED:
- CAD/Mechanical design
- Fluids mechanics
- FEM
TASKS UNFOLDING:
- [3 weeks]: State of the art, analysis of past studies
- [8 weeks]: Simulations and FEM study
- [3 weeks]: CAD modifications and documentation for production
Contacts: leonard.bongiovanni@epfl.ch
Supervisor: TBD
Number of students: TAKEN
Reference links:
- Gerhart, Gerhart & Hochstein, Munson’s Fluid Mechanics, Global Edition, 8th
- Past semester projects from the Hyperion project on this topic
C-Class
PROJECT DESCRIPTION
The EPFL Rocket Team’s Hyperion project has to supply a bi-liquid rocket engine capable of propelling a rocket to an altitude of 30km.
The project involves designing DEMO-C1, the engine for the Firehorn 30 rocket, with a thrust of 15kN. The engine will be regeneratively cooled for thermal efficiency, and will use ethanol and liquid oxygen as propellants. Students will build on previous work on the DEMO-B1 engine, which will propel the FH9 rocket with a thrust of 5kN.
The DEMO-C1 engine will have to be designed with 3D printing in mind, and post manufacturing constraints will also have to be taken into account.
WHAT THE STUDENT(s) WILL DO:
- Design a regeneratively cooled rocket engine, based on an actual design of a 5kN engine
- Simulate the cooling inside the channels
- Dimension the combustion chamber to meet the engine’s performance requirements
SKILLS INVOLVED:
- CAD
- Mechanical design
- Fluid mechanics
- Simulations
TASKS UNFOLDING:
- [3 weeks]: State of the art and analysis of past projects
- [8 weeks]: CAD design of the engine and simulations
- [3 weeks]: Documentation
Contacts: leonard.bongiovanni@epfl.ch
Supervisor: TBD
Number of students: TAKEN
Reference links:
- Huzel and Huang, Design Of Liquid Propellant Rocket Engines. NASA, 1967
- Rocket Propulsion Elements 9th Edition by Oscar Biblarz George P. Sutton
MANAGEMENT
PROJECT DESCRIPTION
Since the start of the 2024-2025 academic year, the association has observed a substantial rise in the volume of internally produced documents and externally gathered publications and other resources by the engineering teams. This increase correlates with a renewed approach to systems engineering by the ERT, now more closely aligned with current space industry standards compared to prior years.
This project serves as the first step to provide the EPFL Rocket Team with an LLM-based solution for interacting with the full repository of resources accumulated and generated by the team. This solution will support various functions, ranging from training newly recruited members to answering queries from lead engineers on topics such as the ECSS standards.
WHAT THE STUDENT(s) WILL DO:
- Select a fitting model and approach LLM for the present use case.
- Build a proof-of-concept using the document repository.
- Deliver a written report on the process and outcomes.
SKILLS INVOLVED:
- Data Processing
- Machine Learning
- Large Language Models
- Python, R, …
TASKS UNFOLDING:
- [3 weeks]: Literature Review
- [3 weeks]: Model Selection
- [6 weeks]: Development of the PoC
- [2 weeks]: Writing of the report
Contacts: samuel.wahba@epfl.ch
Supervisor: TBD
Number of students: TAKEN