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Semester Projects
Fall 2026
Embark on an exciting journey with the EPFL Spacecraft team! Our semester projects offer you the unique chance to apply your academic knowledge to real-world challenges in spacecraft design and exploration. Step into the frontier of space technology, and shape the future of space travel with us!
Note: Various projects are specific to Masters/Bachelors students only, so make sure to check both tabs!
System engineering
No BA Projects this semester
No MA Projects this semester
Structure
Structural model analysis and test preparation for the Pathfinder-0 mission (TAKEN)
MA Semester project or Bachelor project
Section : GM
Description:
The Pathfinder-0 mission is a 3U CubeSat developed by the EPFL Spacecraft Team and currently scheduled for launch in 2027. As part of the Assembly, Integration and Verification (AIV/MAIV) campaign, a vibration test campaign will first be conducted using a Structural Model (STM) representative of the flight configuration. The objective of this campaign is to validate the structural behaviour of the spacecraft, verify assembly procedures, and reduce risks before performing the protoflight test campaign on the flight satellite.
This project focuses on the preparation and analysis of the STM vibration campaign at system level. The student will contribute to the definition of the mechanical configuration of the satellite, the preparation of test hardware and interfaces, and the analysis of the structural response of the spacecraft during testing. Particular attention will be given to the correlation between numerical predictions and experimental results, as well as to the verification of assembly and integration procedures.
The project provides hands-on experience in spacecraft structural engineering, vibration testing, finite element analysis, and system-level integration activities within a real CubeSat development program.The Pathfinder-0 mission is a 3U CubeSat scheduled to launch in 2027. A part of the MAIV plan, a vibration campaign will be conducted with a representative structural model, in order to derisk the system level vibration test of the satellite.This project includes the analysis and preparation of the STM testing.
Tasks:
- Perform system level analysis of the Pathfinder-0 satellite
- Finalize all mechanical interfaces and fastening procedures of the system level assembly
- Design mass dummies for all components of the satellite and perform mock assemblies to ensure proper assembly procedures
- Prepare the test specifications and procedures, including test instrumentation, MGSE
- Perform the post processing of the test, analyzing the data provided by the facility
Background and skills:
- Mechanical vibrations
- Finite Element Method (FEM)
- Experience with Ansys, Abaqus, or similar FEA/CAD software.
- Both Soubielle Courses
-Basic understanding of structural mechanics, vibration and thermal analysis (recommended).
- CAD design (e.g., SolidWorks, Fusion 360)
The Pathfinder-0 mission is a 3U CubeSat developed by the EPFL Spacecraft Team and currently scheduled for launch in 2027. As part of the Assembly, Integration and Verification (AIV/MAIV) campaign, a vibration test campaign will first be conducted using a Structural Model (STM) representative of the flight configuration. The objective of this campaign is to validate the structural behaviour of the spacecraft, verify assembly procedures, and reduce risks before performing the protoflight test campaign on the flight satellite.
This project focuses on the preparation and analysis of the STM vibration campaign at system level. The student will contribute to the definition of the mechanical configuration of the satellite, the preparation of test hardware and interfaces, and the analysis of the structural response of the spacecraft during testing. Particular attention will be given to the correlation between numerical predictions and experimental results, as well as to the verification of assembly and integration procedures.
The project provides hands-on experience in spacecraft structural engineering, vibration testing, finite element analysis, and system-level integration activities within a real CubeSat development program.The Pathfinder-0 mission is a 3U CubeSat scheduled to launch in 2027. A part of the MAIV plan, a vibration campaign will be conducted with a representative structural model, in order to derisk the system level vibration test of the satellite.This project includes the analysis and preparation of the STM testing.
Tasks:
- Perform system level analysis of the Pathfinder-0 satellite
- Finalize all mechanical interfaces and fastening procedures of the system level assembly
- Design mass dummies for all components of the satellite and perform mock assemblies to ensure proper assembly procedures
- Prepare the test specifications and procedures, including test instrumentation, MGSE
- Perform the post processing of the test, analyzing the data provided by the facility
Background and skills:
- Mechanical vibrations
- Finite Element Method (FEM)
- Experience with Ansys, Abaqus, or similar FEA/CAD software.
- Both Soubielle Courses
-Basic understanding of structural mechanics, vibration and thermal analysis (recommended).
- CAD design (e.g., SolidWorks, Fusion 360)
Redesign and verification of the HDRM for the CHESS nanosatellite(TAKEN)
MA Semester project or Bachelor project
Section : GM
Description:
The Pathfinder-0 mission is developing an in-house HDRM, purposed for the Solar Panels of the mission. Some initial deployment tests in ambient conditions and in vacuum revealed some required redesign changes, due to power restrictions, deployment duration and structural integrity.The purpose of this semester project is to implement the changes, prototype the mechanism in ambient conditions, resulting in an Environmental Qualification of the HDRM.
Tasks:
- Redesign of the HDRM, including the modification of the current design to use dyneema and burn resistors
- Design of the electronics parts (PCB and cables) and the mechanical parts of the mechanism, and prototyping in order to optimize the mechanism in respect to deployment duration, power and temperature
- Definition of re-arming procedure
- Qualification of the model in ambient temperature & environmental conditions (based on ECSS standards)
- Environmental qualification of the model, as part of the Structural Model EVT performed by the team, including test specifications and procedures
Background and skills:
- CAD design (e.g., SolidWorks, Fusion 360)
- Experience in testing (recommended)
- Both Soubielle Courses
- Basic understanding of structural mechanics and thermal analysis (recommended).
The Pathfinder-0 mission is developing an in-house HDRM, purposed for the Solar Panels of the mission. Some initial deployment tests in ambient conditions and in vacuum revealed some required redesign changes, due to power restrictions, deployment duration and structural integrity.The purpose of this semester project is to implement the changes, prototype the mechanism in ambient conditions, resulting in an Environmental Qualification of the HDRM.
Tasks:
- Redesign of the HDRM, including the modification of the current design to use dyneema and burn resistors
- Design of the electronics parts (PCB and cables) and the mechanical parts of the mechanism, and prototyping in order to optimize the mechanism in respect to deployment duration, power and temperature
- Definition of re-arming procedure
- Qualification of the model in ambient temperature & environmental conditions (based on ECSS standards)
- Environmental qualification of the model, as part of the Structural Model EVT performed by the team, including test specifications and procedures
Background and skills:
- CAD design (e.g., SolidWorks, Fusion 360)
- Experience in testing (recommended)
- Both Soubielle Courses
- Basic understanding of structural mechanics and thermal analysis (recommended).
Structural model analysis and test preparation for the Pathfinder-0 mission (TAKEN)
MA Semester project or Bachelor project
Section : GM
Description:
The Pathfinder-0 mission is a 3U CubeSat developed by the EPFL Spacecraft Team and currently scheduled for launch in 2027. As part of the Assembly, Integration and Verification (AIV/MAIV) campaign, a vibration test campaign will first be conducted using a Structural Model (STM) representative of the flight configuration. The objective of this campaign is to validate the structural behaviour of the spacecraft, verify assembly procedures, and reduce risks before performing the protoflight test campaign on the flight satellite.
This project focuses on the preparation and analysis of the STM vibration campaign at system level. The student will contribute to the definition of the mechanical configuration of the satellite, the preparation of test hardware and interfaces, and the analysis of the structural response of the spacecraft during testing. Particular attention will be given to the correlation between numerical predictions and experimental results, as well as to the verification of assembly and integration procedures.
The project provides hands-on experience in spacecraft structural engineering, vibration testing, finite element analysis, and system-level integration activities within a real CubeSat development program.The Pathfinder-0 mission is a 3U CubeSat scheduled to launch in 2027. A part of the MAIV plan, a vibration campaign will be conducted with a representative structural model, in order to derisk the system level vibration test of the satellite.This project includes the analysis and preparation of the STM testing.
Tasks:
- Perform system level analysis of the Pathfinder-0 satellite
- Finalize all mechanical interfaces and fastening procedures of the system level assembly
- Design mass dummies for all components of the satellite and perform mock assemblies to ensure proper assembly procedures
- Prepare the test specifications and procedures, including test instrumentation, MGSE
- Perform the post processing of the test, analyzing the data provided by the facility
Background and skills:
- Mechanical vibrations
- Finite Element Method (FEM)
- Experience with Ansys, Abaqus, or similar FEA/CAD software.
- Both Soubielle Courses
-Basic understanding of structural mechanics, vibration and thermal analysis (recommended).
- CAD design (e.g., SolidWorks, Fusion 360)
The Pathfinder-0 mission is a 3U CubeSat developed by the EPFL Spacecraft Team and currently scheduled for launch in 2027. As part of the Assembly, Integration and Verification (AIV/MAIV) campaign, a vibration test campaign will first be conducted using a Structural Model (STM) representative of the flight configuration. The objective of this campaign is to validate the structural behaviour of the spacecraft, verify assembly procedures, and reduce risks before performing the protoflight test campaign on the flight satellite.
This project focuses on the preparation and analysis of the STM vibration campaign at system level. The student will contribute to the definition of the mechanical configuration of the satellite, the preparation of test hardware and interfaces, and the analysis of the structural response of the spacecraft during testing. Particular attention will be given to the correlation between numerical predictions and experimental results, as well as to the verification of assembly and integration procedures.
The project provides hands-on experience in spacecraft structural engineering, vibration testing, finite element analysis, and system-level integration activities within a real CubeSat development program.The Pathfinder-0 mission is a 3U CubeSat scheduled to launch in 2027. A part of the MAIV plan, a vibration campaign will be conducted with a representative structural model, in order to derisk the system level vibration test of the satellite.This project includes the analysis and preparation of the STM testing.
Tasks:
- Perform system level analysis of the Pathfinder-0 satellite
- Finalize all mechanical interfaces and fastening procedures of the system level assembly
- Design mass dummies for all components of the satellite and perform mock assemblies to ensure proper assembly procedures
- Prepare the test specifications and procedures, including test instrumentation, MGSE
- Perform the post processing of the test, analyzing the data provided by the facility
Background and skills:
- Mechanical vibrations
- Finite Element Method (FEM)
- Experience with Ansys, Abaqus, or similar FEA/CAD software.
- Both Soubielle Courses
-Basic understanding of structural mechanics, vibration and thermal analysis (recommended).
- CAD design (e.g., SolidWorks, Fusion 360)
Redesign and verification of the HDRM for the CHESS nanosatellite
MA Semester project or Bachelor project
Section : GM
Description:
The Pathfinder-0 mission is developing an in-house HDRM, purposed for the Solar Panels of the mission. Some initial deployment tests in ambient conditions and in vacuum revealed some required redesign changes, due to power restrictions, deployment duration and structural integrity.
The purpose of this semester project is to implement the changes, prototype the mechanism in ambient conditions, resulting in an Environmental Qualification of the HDRM.
Tasks:
- Redesign of the HDRM, including the modification of the current design to use dyneema and burn resistors
- Design of the electronics parts (PCB and cables) and the mechanical parts of the mechanism, and prototyping in order to optimize the mechanism in respect to deployment duration, power and temperature
- Definition of re-arming procedure
- Qualification of the model in ambient temperature & environmental conditions (based on ECSS standards)
- Environmental qualification of the model, as part of the Structural Model EVT performed by the team, including test specifications and procedures
Background and skills:
- CAD design (e.g., SolidWorks, Fusion 360)
- Experience in testing (recommended)
- Both Soubielle Courses
- Basic understanding of structural mechanics and thermal analysis (recommended).
The Pathfinder-0 mission is developing an in-house HDRM, purposed for the Solar Panels of the mission. Some initial deployment tests in ambient conditions and in vacuum revealed some required redesign changes, due to power restrictions, deployment duration and structural integrity.
The purpose of this semester project is to implement the changes, prototype the mechanism in ambient conditions, resulting in an Environmental Qualification of the HDRM.
Tasks:
- Redesign of the HDRM, including the modification of the current design to use dyneema and burn resistors
- Design of the electronics parts (PCB and cables) and the mechanical parts of the mechanism, and prototyping in order to optimize the mechanism in respect to deployment duration, power and temperature
- Definition of re-arming procedure
- Qualification of the model in ambient temperature & environmental conditions (based on ECSS standards)
- Environmental qualification of the model, as part of the Structural Model EVT performed by the team, including test specifications and procedures
Background and skills:
- CAD design (e.g., SolidWorks, Fusion 360)
- Experience in testing (recommended)
- Both Soubielle Courses
- Basic understanding of structural mechanics and thermal analysis (recommended).
Thermal Analysis of CHESS Pathfinder 0(TAKEN)
MA Semester project
Section : GM
Description:
During the development of the CubeSat, the payload configuration was modified, requiring significant changes to the internal assembly and structural layout of the satellite. The updated configuration introduced new component placements, modified thermal interfaces, and changes in power dissipation distribution.While previous thermal analyses existed for the original configuration, no complete thermal analysis has yet been performed for the updated assembly. As thermal behaviour is strongly influenced by geometry, material interfaces, operational modes, and internal dissipation, a new thermal model is required to verify that all components remain within their operational and non-operational temperature limits throughout the mission.
The objective of this semester project is to develop and validate a thermal model of the updated CHESS Pathfinder 0 configuration using lumped-parameter thermal analysis methods in Systema Thermica. The student will analyse the thermal behaviour of the spacecraft under representative orbital conditions, evaluate the thermal performance of critical subsystems and payload components, and investigate possible mitigation solutions in case thermal limits are exceeded.The final goal is to ensure that the redesigned CubeSat configuration satisfies mission thermal requirements and to provide recommendations for future design iterations.
The Pathfinder-0 mission is developing an in-house HDRM, purposed for the Solar Panels of the mission. Some initial deployment tests in ambient conditions and in vacuum revealed some required redesign changes, due to power restrictions, deployment duration and structural integrity.
The purpose of this semester project is to implement the changes, prototype the mechanism in ambient conditions, resulting in an Environmental Qualification of the HDRM.
Tasks:
- Review the current CHESS Pathfinder 0 mechanical and electrical configuration
- Update the thermal model geometry and nodal network in Systema Thermica
- Define conductive interfaces and radiative couplings between components
- Implement internal power dissipation profiles for different operational modes
- Perform transient thermal simulations for representative hot and cold orbital cases
- Analyse temperature evolution of critical subsystems and payload elements
- Compare results with operational and non-operational temperature limits
- Investigate potential thermal mitigation solutions if required
- Document the modelling assumptions, simulation methodology, and obtained results
- Present recommendations for future thermal design improvements
Background and skills:
- Knowledge of Heat Transfer and Thermodynamics
- Experience Numerical Simulation
- Experience with Systema Thermica
During the development of the CubeSat, the payload configuration was modified, requiring significant changes to the internal assembly and structural layout of the satellite. The updated configuration introduced new component placements, modified thermal interfaces, and changes in power dissipation distribution.While previous thermal analyses existed for the original configuration, no complete thermal analysis has yet been performed for the updated assembly. As thermal behaviour is strongly influenced by geometry, material interfaces, operational modes, and internal dissipation, a new thermal model is required to verify that all components remain within their operational and non-operational temperature limits throughout the mission.
The objective of this semester project is to develop and validate a thermal model of the updated CHESS Pathfinder 0 configuration using lumped-parameter thermal analysis methods in Systema Thermica. The student will analyse the thermal behaviour of the spacecraft under representative orbital conditions, evaluate the thermal performance of critical subsystems and payload components, and investigate possible mitigation solutions in case thermal limits are exceeded.The final goal is to ensure that the redesigned CubeSat configuration satisfies mission thermal requirements and to provide recommendations for future design iterations.
The Pathfinder-0 mission is developing an in-house HDRM, purposed for the Solar Panels of the mission. Some initial deployment tests in ambient conditions and in vacuum revealed some required redesign changes, due to power restrictions, deployment duration and structural integrity.
The purpose of this semester project is to implement the changes, prototype the mechanism in ambient conditions, resulting in an Environmental Qualification of the HDRM.
Tasks:
- Review the current CHESS Pathfinder 0 mechanical and electrical configuration
- Update the thermal model geometry and nodal network in Systema Thermica
- Define conductive interfaces and radiative couplings between components
- Implement internal power dissipation profiles for different operational modes
- Perform transient thermal simulations for representative hot and cold orbital cases
- Analyse temperature evolution of critical subsystems and payload elements
- Compare results with operational and non-operational temperature limits
- Investigate potential thermal mitigation solutions if required
- Document the modelling assumptions, simulation methodology, and obtained results
- Present recommendations for future thermal design improvements
Background and skills:
- Knowledge of Heat Transfer and Thermodynamics
- Experience Numerical Simulation
- Experience with Systema Thermica
Ground segment
No BA Projects this semester
No MA Projects this semester
Flight software
No BA Projects this semester
Fault Detection Isolation and Recovery (FDIR) design and implementation for the Flight Software
MA Semester project
Section : IC SC RO
Description:
Satellite on-board software must be able to detect abnormal situations, react appropriately, and recover from failures whenever possible, sometimes without ground intervention. This is the role of Fault Detection, Isolation and Recovery (FDIR).
The goal of this project is to design and implement the FDIR architecture of the CHESS Flight Software based on existing best practices and standards (SOURCE paper, ECSS standard, ESA Savoir FDIR handbook, ESA Engineering Guidelines for CubeSat Projects, internal CHESS FDIR documentation). The Flight Software is based on the F´ framework developed by NASA and runs on a redundant on-board computer architecture composed of two CPUs. When the Flight Software heartbeat is lost, the system switches to the backup CPU.
The project will focus on integrating FDIR concepts into the existing Flight Software architecture and the mechanisms already provided by the F´ framework. The student will also work closely with subsystem teams (EPS, ADCS, Telecom, Payloads, etc.) to define fault detection and recovery behaviors matching the constraints of each subsystem.
Finally, the implementation will be validated through dedicated fault injection and recovery scenarios executed inside the NEST simulation framework developed by the Flight Software Team.
Tasks:
- Design and implementation of the FDIR architecture for the Flight Software.
- Implementation of hierarchical fault handling and heartbeat supervision mechanisms:
1) monitoring the health of individual Flight Software components
2) attempting local recovery when possibleescalating only when recovery fails
3) aggregating component health into a global Flight Software heartbeat
4) triggering a switch from CPU A to CPU B if the global heartbeat is lost
5) distinguishing recoverable and irrecoverable failures
- Design of the FDIR architecture around existing F´ mechanisms/components and clean integration with the current Flight Software architecture.
- Extension and improvement of the current TlmMonitor work for telemetry monitoring and fault detection.
- Coordination with subsystem teams to define subsystem-specific fault detection and recovery behaviors.
- Implementation of telemetry filtering mechanisms to avoid reacting to short telemetry spikes or inconsistent readings.
- Design of mechanisms to persist critical information across reboots:
1) reboot cause
2) safe Mode state
3) current state during LEOP sequence
- Development of validation scenarios in NEST to test the FDIR implementation.
- Production of an FDIR architecture document.
Background and skills:
• Good knowledge of embedded C/C++ programming
• Experience with microcontrollersUnderstanding of digital communication protocols
• Basic understanding of power electronics or willingness to learn
• Familiarity with debugging tools (JTAG/SWD, logic analyzer, oscilloscopes)
• Interest in reliable and fault-tolerant embedded systems for space applications
Satellite on-board software must be able to detect abnormal situations, react appropriately, and recover from failures whenever possible, sometimes without ground intervention. This is the role of Fault Detection, Isolation and Recovery (FDIR).
The goal of this project is to design and implement the FDIR architecture of the CHESS Flight Software based on existing best practices and standards (SOURCE paper, ECSS standard, ESA Savoir FDIR handbook, ESA Engineering Guidelines for CubeSat Projects, internal CHESS FDIR documentation). The Flight Software is based on the F´ framework developed by NASA and runs on a redundant on-board computer architecture composed of two CPUs. When the Flight Software heartbeat is lost, the system switches to the backup CPU.
The project will focus on integrating FDIR concepts into the existing Flight Software architecture and the mechanisms already provided by the F´ framework. The student will also work closely with subsystem teams (EPS, ADCS, Telecom, Payloads, etc.) to define fault detection and recovery behaviors matching the constraints of each subsystem.
Finally, the implementation will be validated through dedicated fault injection and recovery scenarios executed inside the NEST simulation framework developed by the Flight Software Team.
Tasks:
- Design and implementation of the FDIR architecture for the Flight Software.
- Implementation of hierarchical fault handling and heartbeat supervision mechanisms:
1) monitoring the health of individual Flight Software components
2) attempting local recovery when possibleescalating only when recovery fails
3) aggregating component health into a global Flight Software heartbeat
4) triggering a switch from CPU A to CPU B if the global heartbeat is lost
5) distinguishing recoverable and irrecoverable failures
- Design of the FDIR architecture around existing F´ mechanisms/components and clean integration with the current Flight Software architecture.
- Extension and improvement of the current TlmMonitor work for telemetry monitoring and fault detection.
- Coordination with subsystem teams to define subsystem-specific fault detection and recovery behaviors.
- Implementation of telemetry filtering mechanisms to avoid reacting to short telemetry spikes or inconsistent readings.
- Design of mechanisms to persist critical information across reboots:
1) reboot cause
2) safe Mode state
3) current state during LEOP sequence
- Development of validation scenarios in NEST to test the FDIR implementation.
- Production of an FDIR architecture document.
Background and skills:
• Good knowledge of embedded C/C++ programming
• Experience with microcontrollersUnderstanding of digital communication protocols
• Basic understanding of power electronics or willingness to learn
• Familiarity with debugging tools (JTAG/SWD, logic analyzer, oscilloscopes)
• Interest in reliable and fault-tolerant embedded systems for space applications
Extending NEST for Hardware-in-the-Loop Satellite Simulation
MA Semester project (8 or 12 ETCS)
Section : ELE MT IN SC RO
Description:
Rigorous testing of spacecraft systems is highly critical for satellite missions and requires reproducing complex interactions between the flight software, on-board computer and other satellite subsystems under realistic space conditions. For student missions, this process is constrained by the high cost and limited availability of hardware testbeds, as well as the difficulty of introducing representative hardware faults or environmental effects. To address these challenges, we are developing NEST (Numerical Environment for Software Testing)—a modular simulation framework that allows the flight software to execute natively and transparently inside a simulated embedded environment replicating real hardware interactions.
So far, the scope of NEST has been limited to flight software testing. However, as the project matured, we realized the potential of the framework for testing hardware components as well, by integrating them inside the simulation and replacing emulated components with their physical counterparts. The goal of this project is to extend NEST to support hardware-in-the-loop simulations and gradually transition from purely software-based simulations to flatsat setups. It will involve developing a specialized NEST component in Rust to communicate with the native hardware interfaces of the host computer, and then prototype a circuit board to provide additional hardware interfaces to the host computer and communicate with NEST over USB. In both cases, the focus will be on UART, I2C and GPIO interfaces. Finally, the student will experiment with hardware-in-the-loop simulations to validate their successful implementation and test satellite subsystems in isolation.
Tasks:
• Develop a NEST component in Rust to communicate with native UART, I2C and GPIO hardware interfaces of the host computer (Linux).
• Prototype a PCB to provide additional UART, I2C and GPIO hardware interfaces to the host computer and communicate with NEST over USB.
• Experiment with hardware-in-the-loop simulations and show that emulated components can transparently be replaced by their physical counterparts.
Background and skills:
• Familiarity with Rust (or motivation to learn).
• PCB design (note that our team has very limited experience in the topic and will not be able to provide much assistance, however the OBC team may provide assistance when needed).
• Interest in high-performance hardware simulation.
Rigorous testing of spacecraft systems is highly critical for satellite missions and requires reproducing complex interactions between the flight software, on-board computer and other satellite subsystems under realistic space conditions. For student missions, this process is constrained by the high cost and limited availability of hardware testbeds, as well as the difficulty of introducing representative hardware faults or environmental effects. To address these challenges, we are developing NEST (Numerical Environment for Software Testing)—a modular simulation framework that allows the flight software to execute natively and transparently inside a simulated embedded environment replicating real hardware interactions.
So far, the scope of NEST has been limited to flight software testing. However, as the project matured, we realized the potential of the framework for testing hardware components as well, by integrating them inside the simulation and replacing emulated components with their physical counterparts. The goal of this project is to extend NEST to support hardware-in-the-loop simulations and gradually transition from purely software-based simulations to flatsat setups. It will involve developing a specialized NEST component in Rust to communicate with the native hardware interfaces of the host computer, and then prototype a circuit board to provide additional hardware interfaces to the host computer and communicate with NEST over USB. In both cases, the focus will be on UART, I2C and GPIO interfaces. Finally, the student will experiment with hardware-in-the-loop simulations to validate their successful implementation and test satellite subsystems in isolation.
Tasks:
• Develop a NEST component in Rust to communicate with native UART, I2C and GPIO hardware interfaces of the host computer (Linux).
• Prototype a PCB to provide additional UART, I2C and GPIO hardware interfaces to the host computer and communicate with NEST over USB.
• Experiment with hardware-in-the-loop simulations and show that emulated components can transparently be replaced by their physical counterparts.
Background and skills:
• Familiarity with Rust (or motivation to learn).
• PCB design (note that our team has very limited experience in the topic and will not be able to provide much assistance, however the OBC team may provide assistance when needed).
• Interest in high-performance hardware simulation.
EPS
Design, Testing, and Integration of the Electrical Power System for a CubeSat
MA Semester project & Bachelor Project
Section : EL MT
Description:
This project focuses on the development and validation of the Electrical Power System (EPS) for a CubeSat platform. The EPS includes a DC/DC converter that operates as both a battery charger and a solar array power controller capable of tracking the Maximum Power Point (MPP) of the photovoltaic panels. The system also incorporates a Power Distribution Unit (PDU) responsible for routing regulated voltages to the satellite subsystems.
The student will debug and test the current EPS engineering model, characterize its performance, and ensure stable operation under representative conditions. The project also includes the integration of the EPS with the CubeSat battery pack and the verification of safe charging, discharging, and protection features. After validating the prototype, the final objective is to design and implement a flight-format version of the EPS with CubeSat-compatible dimensions (10 × 10 cm).
Tasks:
• Study and understand the architecture and functional requirements of a CubeSat Electrical Power System.
• Analyze the existing EPS prototype, including the DC/DC converter, MPP tracking algorithm, and PDU.
• Debug hardware and firmware issues related to the converter and solar array controller.
• Perform laboratory testing: efficiency measurements, thermal behavior, stability analysis, MPP tracking validation, and battery-charging characterization.
• Integrate the EPS with the CubeSat battery pack and verify protection mechanisms.
• Implement improvements based on test results and ensure system reliability.
• Design and layout the final CubeSat-format EPS board (10×10 cm) suitable for integration into the satellite structure.
• Document the full development process, test results, and design decisions.
Background and skills:
• Basic to intermediate knowledge of analog and digital electronics
• Understanding of DC/DC converters, power electronics, or photovoltaic systems Familiarity with PCB design tools ( KiCad)
• Experience with laboratory instruments (oscilloscope, power supplies, electronic loads)
• Programming skills (embedded C) are an asset
• Motivation to work with space-system engineering constraints
This project focuses on the development and validation of the Electrical Power System (EPS) for a CubeSat platform. The EPS includes a DC/DC converter that operates as both a battery charger and a solar array power controller capable of tracking the Maximum Power Point (MPP) of the photovoltaic panels. The system also incorporates a Power Distribution Unit (PDU) responsible for routing regulated voltages to the satellite subsystems.
The student will debug and test the current EPS engineering model, characterize its performance, and ensure stable operation under representative conditions. The project also includes the integration of the EPS with the CubeSat battery pack and the verification of safe charging, discharging, and protection features. After validating the prototype, the final objective is to design and implement a flight-format version of the EPS with CubeSat-compatible dimensions (10 × 10 cm).
Tasks:
• Study and understand the architecture and functional requirements of a CubeSat Electrical Power System.
• Analyze the existing EPS prototype, including the DC/DC converter, MPP tracking algorithm, and PDU.
• Debug hardware and firmware issues related to the converter and solar array controller.
• Perform laboratory testing: efficiency measurements, thermal behavior, stability analysis, MPP tracking validation, and battery-charging characterization.
• Integrate the EPS with the CubeSat battery pack and verify protection mechanisms.
• Implement improvements based on test results and ensure system reliability.
• Design and layout the final CubeSat-format EPS board (10×10 cm) suitable for integration into the satellite structure.
• Document the full development process, test results, and design decisions.
Background and skills:
• Basic to intermediate knowledge of analog and digital electronics
• Understanding of DC/DC converters, power electronics, or photovoltaic systems Familiarity with PCB design tools ( KiCad)
• Experience with laboratory instruments (oscilloscope, power supplies, electronic loads)
• Programming skills (embedded C) are an asset
• Motivation to work with space-system engineering constraints
Design Review, Assembly, and Validation of a CubeSat Battery Pack
MA Semester project & Bachelor Project
Section : MT GM
Description:
This project focuses on the development and qualification of the battery subsystem for a CubeSat. The current battery-pack concept requires a complete engineering review to ensure compliance with mission requirements, safety constraints, and thermal conditions encountered in orbit. The student will evaluate the existing design, verify cell configuration, protection circuitry, mechanical integration, interface, and thermal management strategy—including the selection and sizing of the heater element.
After the review phase, the student will update the design as needed, assemble the battery pack using space-compatible processes, and carry out functional and environmental validation tests. The final outcome is a fully assembled and tested battery pack ready for integration into the CubeSat Electrical Power System.
Tasks:
• Review the current battery pack design (cells, topology, protection circuits, connectors, mechanical structure).
• Evaluate the thermal requirements and validate the heater selection and positioning.Identify necessary improvements in electrical, mechanical, and thermal aspects.
• Update schematics, wiring diagrams, and mechanical drawings.
• Assemble the battery pack with appropriate safety procedures and handling of Li-ion cells.
• Perform validation tests: capacity measurement, charge/discharge behavior, balancing, protection verification, and thermal-performance evaluation.
• Prepare documentation for integration with the CubeSat EPS and overall satellite structure.
Background and skills:
• Knowledge of basic to intermediate electronics and battery technologiesUnderstanding of Li-ion cell safety, charging profiles, and protection circuits
• Familiarity with mechanical integration and wiring practices
• Experience with laboratory testing (battery cycler, thermal chamber, oscilloscope, etc.) is an asset
• Ability to follow safe handling procedures for energy-storage systems
• Motivation to work with space-mission constraints and safety-critical hardware
This project focuses on the development and qualification of the battery subsystem for a CubeSat. The current battery-pack concept requires a complete engineering review to ensure compliance with mission requirements, safety constraints, and thermal conditions encountered in orbit. The student will evaluate the existing design, verify cell configuration, protection circuitry, mechanical integration, interface, and thermal management strategy—including the selection and sizing of the heater element.
After the review phase, the student will update the design as needed, assemble the battery pack using space-compatible processes, and carry out functional and environmental validation tests. The final outcome is a fully assembled and tested battery pack ready for integration into the CubeSat Electrical Power System.
Tasks:
• Review the current battery pack design (cells, topology, protection circuits, connectors, mechanical structure).
• Evaluate the thermal requirements and validate the heater selection and positioning.Identify necessary improvements in electrical, mechanical, and thermal aspects.
• Update schematics, wiring diagrams, and mechanical drawings.
• Assemble the battery pack with appropriate safety procedures and handling of Li-ion cells.
• Perform validation tests: capacity measurement, charge/discharge behavior, balancing, protection verification, and thermal-performance evaluation.
• Prepare documentation for integration with the CubeSat EPS and overall satellite structure.
Background and skills:
• Knowledge of basic to intermediate electronics and battery technologiesUnderstanding of Li-ion cell safety, charging profiles, and protection circuits
• Familiarity with mechanical integration and wiring practices
• Experience with laboratory testing (battery cycler, thermal chamber, oscilloscope, etc.) is an asset
• Ability to follow safe handling procedures for energy-storage systems
• Motivation to work with space-mission constraints and safety-critical hardware
Design, Testing, and Integration of the Electrical Power System for a CubeSat
MA Semester project & Bachelor Project
Section : EL MT
Description:
This project focuses on the development and validation of the Electrical Power System (EPS) for a CubeSat platform. The EPS includes a DC/DC converter that operates as both a battery charger and a solar array power controller capable of tracking the Maximum Power Point (MPP) of the photovoltaic panels. The system also incorporates a Power Distribution Unit (PDU) responsible for routing regulated voltages to the satellite subsystems.
The student will debug and test the current EPS engineering model, characterize its performance, and ensure stable operation under representative conditions. The project also includes the integration of the EPS with the CubeSat battery pack and the verification of safe charging, discharging, and protection features. After validating the prototype, the final objective is to design and implement a flight-format version of the EPS with CubeSat-compatible dimensions (10 × 10 cm).
Tasks:
• Study and understand the architecture and functional requirements of a CubeSat Electrical Power System.
• Analyze the existing EPS prototype, including the DC/DC converter, MPP tracking algorithm, and PDU.
• Debug hardware and firmware issues related to the converter and solar array controller.
• Perform laboratory testing: efficiency measurements, thermal behavior, stability analysis, MPP tracking validation, and battery-charging characterization.
• Integrate the EPS with the CubeSat battery pack and verify protection mechanisms.
• Implement improvements based on test results and ensure system reliability.
• Design and layout the final CubeSat-format EPS board (10×10 cm) suitable for integration into the satellite structure.
• Document the full development process, test results, and design decisions.
Background and skills:
• Basic to intermediate knowledge of analog and digital electronics
• Understanding of DC/DC converters, power electronics, or photovoltaic systems Familiarity with PCB design tools ( KiCad)
• Experience with laboratory instruments (oscilloscope, power supplies, electronic loads)
• Programming skills (embedded C) are an asset
• Motivation to work with space-system engineering constraints
This project focuses on the development and validation of the Electrical Power System (EPS) for a CubeSat platform. The EPS includes a DC/DC converter that operates as both a battery charger and a solar array power controller capable of tracking the Maximum Power Point (MPP) of the photovoltaic panels. The system also incorporates a Power Distribution Unit (PDU) responsible for routing regulated voltages to the satellite subsystems.
The student will debug and test the current EPS engineering model, characterize its performance, and ensure stable operation under representative conditions. The project also includes the integration of the EPS with the CubeSat battery pack and the verification of safe charging, discharging, and protection features. After validating the prototype, the final objective is to design and implement a flight-format version of the EPS with CubeSat-compatible dimensions (10 × 10 cm).
Tasks:
• Study and understand the architecture and functional requirements of a CubeSat Electrical Power System.
• Analyze the existing EPS prototype, including the DC/DC converter, MPP tracking algorithm, and PDU.
• Debug hardware and firmware issues related to the converter and solar array controller.
• Perform laboratory testing: efficiency measurements, thermal behavior, stability analysis, MPP tracking validation, and battery-charging characterization.
• Integrate the EPS with the CubeSat battery pack and verify protection mechanisms.
• Implement improvements based on test results and ensure system reliability.
• Design and layout the final CubeSat-format EPS board (10×10 cm) suitable for integration into the satellite structure.
• Document the full development process, test results, and design decisions.
Background and skills:
• Basic to intermediate knowledge of analog and digital electronics
• Understanding of DC/DC converters, power electronics, or photovoltaic systems Familiarity with PCB design tools ( KiCad)
• Experience with laboratory instruments (oscilloscope, power supplies, electronic loads)
• Programming skills (embedded C) are an asset
• Motivation to work with space-system engineering constraints
Design Review, Assembly, and Validation of a CubeSat Battery Pack
MA Semester project & Bachelor Project
Section : MT GM
Description:
This project focuses on the development and qualification of the battery subsystem for a CubeSat. The current battery-pack concept requires a complete engineering review to ensure compliance with mission requirements, safety constraints, and thermal conditions encountered in orbit. The student will evaluate the existing design, verify cell configuration, protection circuitry, mechanical integration, interface, and thermal management strategy—including the selection and sizing of the heater element.
After the review phase, the student will update the design as needed, assemble the battery pack using space-compatible processes, and carry out functional and environmental validation tests. The final outcome is a fully assembled and tested battery pack ready for integration into the CubeSat Electrical Power System.
Tasks:
• Review the current battery pack design (cells, topology, protection circuits, connectors, mechanical structure).
• Evaluate the thermal requirements and validate the heater selection and positioning.Identify necessary improvements in electrical, mechanical, and thermal aspects.
• Update schematics, wiring diagrams, and mechanical drawings.
• Assemble the battery pack with appropriate safety procedures and handling of Li-ion cells.
• Perform validation tests: capacity measurement, charge/discharge behavior, balancing, protection verification, and thermal-performance evaluation.
• Prepare documentation for integration with the CubeSat EPS and overall satellite structure.
Background and skills:
• Knowledge of basic to intermediate electronics and battery technologiesUnderstanding of Li-ion cell safety, charging profiles, and protection circuits
• Familiarity with mechanical integration and wiring practices
• Experience with laboratory testing (battery cycler, thermal chamber, oscilloscope, etc.) is an asset
• Ability to follow safe handling procedures for energy-storage systems
• Motivation to work with space-mission constraints and safety-critical hardware
This project focuses on the development and qualification of the battery subsystem for a CubeSat. The current battery-pack concept requires a complete engineering review to ensure compliance with mission requirements, safety constraints, and thermal conditions encountered in orbit. The student will evaluate the existing design, verify cell configuration, protection circuitry, mechanical integration, interface, and thermal management strategy—including the selection and sizing of the heater element.
After the review phase, the student will update the design as needed, assemble the battery pack using space-compatible processes, and carry out functional and environmental validation tests. The final outcome is a fully assembled and tested battery pack ready for integration into the CubeSat Electrical Power System.
Tasks:
• Review the current battery pack design (cells, topology, protection circuits, connectors, mechanical structure).
• Evaluate the thermal requirements and validate the heater selection and positioning.Identify necessary improvements in electrical, mechanical, and thermal aspects.
• Update schematics, wiring diagrams, and mechanical drawings.
• Assemble the battery pack with appropriate safety procedures and handling of Li-ion cells.
• Perform validation tests: capacity measurement, charge/discharge behavior, balancing, protection verification, and thermal-performance evaluation.
• Prepare documentation for integration with the CubeSat EPS and overall satellite structure.
Background and skills:
• Knowledge of basic to intermediate electronics and battery technologiesUnderstanding of Li-ion cell safety, charging profiles, and protection circuits
• Familiarity with mechanical integration and wiring practices
• Experience with laboratory testing (battery cycler, thermal chamber, oscilloscope, etc.) is an asset
• Ability to follow safe handling procedures for energy-storage systems
• Motivation to work with space-mission constraints and safety-critical hardware
Telecommunication
UHF Command Execution Firmware for SatNOGS COMMS
Bachelor project
Section : IC SC ELE
Description:
The mission will use the SatNOGS COMMS transceiver as the UHF communication subsystem. The transceiver hardware already provides the required radio capabilities, but mission-specific firmware is needed so that the transceiver MCU can execute the commands required by the Flight Software.The goal of this project is to develop firmware that allows the transceiver to receive command requests from the onboard computer, perform the corresponding UHF radio actions, and return status, telemetry, or error responses.
The work will focus on the UHF part of the transceiver. Typical commands include enabling/disabling the UHF radio, selecting receive and transmit profiles, starting reception, transmitting downlink frames, sending beacons, reading received frames, reporting health/status information, and recovering from basic radio faults.
Tasks:
- Study the SatNOGS COMMS firmware and control library.
- Define the firmware structure needed to receive and execute UHF command requests.
- Implement command handling for the main UHF operations, such as enabling UHF, starting/stopping reception, transmitting frames, sending beacons, and stopping RF activity.
- Implement status and telemetry responses, including transceiver state, UHF status, health data, and link statistics.
- Implement basic fault handling and recovery commands, such as resetting the UHF radio and entering/exiting safe mode.
- Test the implemented firmware using a simple demo or test setup.
- Document the implemented commands, expected inputs/outputs, and firmware behavior.
Background and skills:
- Interest in embedded firmware and spacecraft communication systems.
- Basic knowledge of C/C++ programming.Familiarity with microcontrollers, state machines, and communication interfaces.
- Interest in radio communication concepts such as UHF links, modulation, data rate, RX/TX modes, and beaconing.
- Experience with Git and reading existing codebases is useful.
The mission will use the SatNOGS COMMS transceiver as the UHF communication subsystem. The transceiver hardware already provides the required radio capabilities, but mission-specific firmware is needed so that the transceiver MCU can execute the commands required by the Flight Software.The goal of this project is to develop firmware that allows the transceiver to receive command requests from the onboard computer, perform the corresponding UHF radio actions, and return status, telemetry, or error responses.
The work will focus on the UHF part of the transceiver. Typical commands include enabling/disabling the UHF radio, selecting receive and transmit profiles, starting reception, transmitting downlink frames, sending beacons, reading received frames, reporting health/status information, and recovering from basic radio faults.
Tasks:
- Study the SatNOGS COMMS firmware and control library.
- Define the firmware structure needed to receive and execute UHF command requests.
- Implement command handling for the main UHF operations, such as enabling UHF, starting/stopping reception, transmitting frames, sending beacons, and stopping RF activity.
- Implement status and telemetry responses, including transceiver state, UHF status, health data, and link statistics.
- Implement basic fault handling and recovery commands, such as resetting the UHF radio and entering/exiting safe mode.
- Test the implemented firmware using a simple demo or test setup.
- Document the implemented commands, expected inputs/outputs, and firmware behavior.
Background and skills:
- Interest in embedded firmware and spacecraft communication systems.
- Basic knowledge of C/C++ programming.Familiarity with microcontrollers, state machines, and communication interfaces.
- Interest in radio communication concepts such as UHF links, modulation, data rate, RX/TX modes, and beaconing.
- Experience with Git and reading existing codebases is useful.
No MA Projects this semester
OBC
No BA Projects this semester
No MA Projects this semester
ADCS
No BA Projects this semester
Verification & Validation (V&V) of ADCS architecture
MA Semester project
Section : RO, MT, ME, EL
Description:
Verification & Validation (V&V) is a critical process in a space mission. Pathfinder 0 is our next 3U CubeSat aimed to be launched in Q3 of 2027, and lacks proper V&V on the Attitude Determination and Control System (ADCS) side.
This project aims at validating the designed ADCS architecture. While the sensor and actuator (S&A) layout has been frozen, their testing in real conditions is yet to be done. This includes individual sensor and actuator testing to validate requirements, but also Hardware-In-the-Loop (HIL) testing with the complete ADCS layout. The results will be used to calibrate the system prior to launch (DC gain removal), and to assess noise distributions for minimal Extended Kalman Filter (EKF) mismatch.
This project is especially practical-oriented, offering hands-on experience on space systems. The student will work on real, professional systems and is expected to produce a rigorous, scientific analysis to mitigate in-operation failure.
Tasks:
- Individual Testing of S&A:
1) Magnetorquer: polarity, magnetic moment, linearity and remnant fields
2) Reaction Wheels: Torque, vibration and jitter, time constant
3) Sun sensors: Sensitivity, precision and accuracy
4) Earth Horizon (infrared) Sensor: Sensitivity, precision and accuracy
5) Magnetometer: Sensitivity, precision and accuracy
- ADCS performance as HIL:
1) Testing in Helmotz Cage
2) Testing on air-bearing, with sun simulator
Background and skills:
- Signal Processing
- Data Analysis
- Control/Autonomous Systems
- System Identification is a plus
Verification & Validation (V&V) is a critical process in a space mission. Pathfinder 0 is our next 3U CubeSat aimed to be launched in Q3 of 2027, and lacks proper V&V on the Attitude Determination and Control System (ADCS) side.
This project aims at validating the designed ADCS architecture. While the sensor and actuator (S&A) layout has been frozen, their testing in real conditions is yet to be done. This includes individual sensor and actuator testing to validate requirements, but also Hardware-In-the-Loop (HIL) testing with the complete ADCS layout. The results will be used to calibrate the system prior to launch (DC gain removal), and to assess noise distributions for minimal Extended Kalman Filter (EKF) mismatch.
This project is especially practical-oriented, offering hands-on experience on space systems. The student will work on real, professional systems and is expected to produce a rigorous, scientific analysis to mitigate in-operation failure.
Tasks:
- Individual Testing of S&A:
1) Magnetorquer: polarity, magnetic moment, linearity and remnant fields
2) Reaction Wheels: Torque, vibration and jitter, time constant
3) Sun sensors: Sensitivity, precision and accuracy
4) Earth Horizon (infrared) Sensor: Sensitivity, precision and accuracy
5) Magnetometer: Sensitivity, precision and accuracy
- ADCS performance as HIL:
1) Testing in Helmotz Cage
2) Testing on air-bearing, with sun simulator
Background and skills:
- Signal Processing
- Data Analysis
- Control/Autonomous Systems
- System Identification is a plus
Robust State-Estimation for Fault Detection, Isolation and Recovery (FDIR)(TAKEN)
MA Semester project
Section : RO, ME, EL
Description:
Proper State Estimation is crucial for autonomous systems, and additional robustness is typically required for systems navigating in harsh and inaccessible environments like our 3U CubeSat, Pathfinder 0. In the past years, Fault Detection, Isolation and Recovery (FDIR) has been paired with state-estimation in state-of-the-art methods in aerospace [1,2] and we think our satellite could benefit from it in the same manner.
This project aims at developing and implementing a robust yet low-resource state-estimation scheme for our next mission aimed to be launched in Q3 of 2027. While our Attitude Determination and Control System (ADCS) is a Component-Off-The-Shelf (COTS), we want to be able to perform our own state-estimation algorithms on the On Board Computer (OBC) in parallel, in addition to what is already provided. By integrating a robust state-estimation process on-board, we will be able to compare, validate and extend results obtained by COTS algorithms. In addition, this is an opportunity to qualify it for further use in the missions (flight heritage).
This project includes coding and control theory, but also aims at giving hands-on experience on space systems by integrating it on real hardware. The student will work on real, professional systems and is expected to produce a rigorous, robust pipeline for smooth integration into the Flight Software (FS).
Tasks:
- Literature/Industry Review for selection of promising robust, low-resource state-estimation techniques
- Code highlighted approaches and assess performances (accuracy, computation time/load, …)
- Integrate into the FS
- Additional: Test in Hardware In the Loop (HIL) conditions
Background and skills:
- Control/State Estimation theory
- Signal Processing
- MATLAB/Simulink, Python
Proper State Estimation is crucial for autonomous systems, and additional robustness is typically required for systems navigating in harsh and inaccessible environments like our 3U CubeSat, Pathfinder 0. In the past years, Fault Detection, Isolation and Recovery (FDIR) has been paired with state-estimation in state-of-the-art methods in aerospace [1,2] and we think our satellite could benefit from it in the same manner.
This project aims at developing and implementing a robust yet low-resource state-estimation scheme for our next mission aimed to be launched in Q3 of 2027. While our Attitude Determination and Control System (ADCS) is a Component-Off-The-Shelf (COTS), we want to be able to perform our own state-estimation algorithms on the On Board Computer (OBC) in parallel, in addition to what is already provided. By integrating a robust state-estimation process on-board, we will be able to compare, validate and extend results obtained by COTS algorithms. In addition, this is an opportunity to qualify it for further use in the missions (flight heritage).
This project includes coding and control theory, but also aims at giving hands-on experience on space systems by integrating it on real hardware. The student will work on real, professional systems and is expected to produce a rigorous, robust pipeline for smooth integration into the Flight Software (FS).
Tasks:
- Literature/Industry Review for selection of promising robust, low-resource state-estimation techniques
- Code highlighted approaches and assess performances (accuracy, computation time/load, …)
- Integrate into the FS
- Additional: Test in Hardware In the Loop (HIL) conditions
Background and skills:
- Control/State Estimation theory
- Signal Processing
- MATLAB/Simulink, Python
Mission Design
No BA Projects this semester
Validation, Refinement and Testing of the CHESS End-to-end Simulator(TAKEN)
MA Semester project (8 or 12 ECTS)
Section : IC, RO, SC
Description:
An initial end-to-end simulator of the CHESS satellite has been developed by interfacing multiple software tools within the EPFL Spacecraft Team. This simulator enables a closed-loop simulation of satellite operations, and connects:
- Mission Control Software (MCS): Built using F’ GDS, this software provides a web interface that will be directly used by operators to control the satellite (sending telecommands, viewing telemetry…).
- Ground Segment Pipeline: This software is used to control the ground segment antennas (book a time slot to use antennas to communicate with the satellite, send and receive data with the antennas). It is developed by the Ground Segment pole;
- NEST: This simulator emulates the inside of the satellite (flight software and different sub-systems) and can simulate faults to observe how the satellite would react. It is developed by the Flight Software pole
- Digital Twin: It is a simulation of the satellite orbiting the Earth, and returning data about its position, orientation, functioning state, power level of the battery… It is developed by the Mission Design pole.
While the simulator architecture has been defined in a previous semester project, it has not yet been used for operator training or mission validation.The goal of this semester project is to transition the simulator to a usable operational tool. This includes refining the current interface implementation, validating the full simulation chain, and developing realistic operational scenarios.
Additionally, all four interfaced tools are under active development. Hence, the simulator must be designed in a way that ensures compatibility and adaptability to new updates.
The simulator will ultimately serve three main purposes:
- Training operators for real mission operations.
- Validating nominal mission procedures.
- Testing and analysing anomaly scenarios.
This project lies at the interface between Mission Design, Ground Segment, and Flight Software poles, and requires a system-level understanding of the full mission architecture.
Tasks:
- Analyse the current end-to-end simulator architecture and identify limitations, inconsistencies, and failure points between:
1) MCS and Ground Segment Pipeline,
2) Ground Segment Pipeline and NEST,
3) NEST and Digital Twin.
- Define and test a set of reference operational scenarios, including:
1) Nominal operations (e.g., communication passes, periodic measurements).
2) Anomaly scenarios (e.g. communication loss, power issues).
- Perform validations to ensure correctness and robustness of the simulation results.
- Ensure maintainability of the simulator with respect to evolving software tools (clear documentation, update strategy).
Background and skills:
- Python and/or C++ programming knowledge.
- Autonomy and ability to work across multiple domains.
- Interest in satellite operations and simulation environments.
An initial end-to-end simulator of the CHESS satellite has been developed by interfacing multiple software tools within the EPFL Spacecraft Team. This simulator enables a closed-loop simulation of satellite operations, and connects:
- Mission Control Software (MCS): Built using F’ GDS, this software provides a web interface that will be directly used by operators to control the satellite (sending telecommands, viewing telemetry…).
- Ground Segment Pipeline: This software is used to control the ground segment antennas (book a time slot to use antennas to communicate with the satellite, send and receive data with the antennas). It is developed by the Ground Segment pole;
- NEST: This simulator emulates the inside of the satellite (flight software and different sub-systems) and can simulate faults to observe how the satellite would react. It is developed by the Flight Software pole
- Digital Twin: It is a simulation of the satellite orbiting the Earth, and returning data about its position, orientation, functioning state, power level of the battery… It is developed by the Mission Design pole.
While the simulator architecture has been defined in a previous semester project, it has not yet been used for operator training or mission validation.The goal of this semester project is to transition the simulator to a usable operational tool. This includes refining the current interface implementation, validating the full simulation chain, and developing realistic operational scenarios.
Additionally, all four interfaced tools are under active development. Hence, the simulator must be designed in a way that ensures compatibility and adaptability to new updates.
The simulator will ultimately serve three main purposes:
- Training operators for real mission operations.
- Validating nominal mission procedures.
- Testing and analysing anomaly scenarios.
This project lies at the interface between Mission Design, Ground Segment, and Flight Software poles, and requires a system-level understanding of the full mission architecture.
Tasks:
- Analyse the current end-to-end simulator architecture and identify limitations, inconsistencies, and failure points between:
1) MCS and Ground Segment Pipeline,
2) Ground Segment Pipeline and NEST,
3) NEST and Digital Twin.
- Define and test a set of reference operational scenarios, including:
1) Nominal operations (e.g., communication passes, periodic measurements).
2) Anomaly scenarios (e.g. communication loss, power issues).
- Perform validations to ensure correctness and robustness of the simulation results.
- Ensure maintainability of the simulator with respect to evolving software tools (clear documentation, update strategy).
Background and skills:
- Python and/or C++ programming knowledge.
- Autonomy and ability to work across multiple domains.
- Interest in satellite operations and simulation environments.
Operations planification for the CHESS satellite
MA Semester Project (8 ECTS)
Section : SC, RO
Description:
The EPFL Spacecraft Team aims at launching its first 3U CubeSat in mid-2027. For this, we have to develop plans regarding the operations of the satellite (i.e., how the satellite will be controlled from the ground). The Mission Design pole has started to work on this subject and will transition more and more towards an Operations pole. We have started to lay down the basis for the work that should be done before the launch: making a list of the telecommands available, preparing procedures to control the satellite and execute specific tasks, anticipate potential issues with the satellite and plan counter-measures… This work is especially important because, being a student association, continuity between team members, and here, operators, is very critical.
The current work done involves an ongoing list of high-level procedures that would need to be done during different mission phases:
- Launch and Early Operations Phase: Subsystems boot up and key components are prepared (e.g. antenna deployment, detumbling, solar panel deployment,...).
- In-Orbit Commissioning Phase: Subsystems (now operational) are checked, calibrated and validated before mission operations start (e.g. are solar panels receiving as much solar energy as expected, is the signal strength as expected,...?).
- Nominal Operations Phase: Main operations starts (e.g. measurements, communication passes with our ground station,...).
- End of Life Phase: Mission ends, and we ensure a safe satellite disposal (e.g. batteries are fully discharged).
The goal of this semester project will be to continue the work performed on operations. This includes the tasks already described, but also more technical work. For example, a critical point is to know precisely how much data can be exchanged with the satellite during a communication window to know which procedures can be executed. This project will see lots of interaction with the Telecommunication, Flight Software and Ground Segment poles. A part of the project will also involve tests with part of the satellites, such as testing a portable ground segment and planning for future mission tests.
Tasks:
- Getting acquainted with the work already done regarding operations (CHESS documentation, OPS-SAT writing guidelines,...)
- Listing the telecommands available for operators
- Planning operational procedures, taking into account the duration of communication windows
- Testing communication and some procedures with the FlatSat and a portable ground station.
Background and skills:
- Some basic knowledge about space missions and spacecrafts
- Ability to think creatively and rationally on possible commands and anomalies
- Autonomy and ability to discuss and work with other poles
The EPFL Spacecraft Team aims at launching its first 3U CubeSat in mid-2027. For this, we have to develop plans regarding the operations of the satellite (i.e., how the satellite will be controlled from the ground). The Mission Design pole has started to work on this subject and will transition more and more towards an Operations pole. We have started to lay down the basis for the work that should be done before the launch: making a list of the telecommands available, preparing procedures to control the satellite and execute specific tasks, anticipate potential issues with the satellite and plan counter-measures… This work is especially important because, being a student association, continuity between team members, and here, operators, is very critical.
The current work done involves an ongoing list of high-level procedures that would need to be done during different mission phases:
- Launch and Early Operations Phase: Subsystems boot up and key components are prepared (e.g. antenna deployment, detumbling, solar panel deployment,...).
- In-Orbit Commissioning Phase: Subsystems (now operational) are checked, calibrated and validated before mission operations start (e.g. are solar panels receiving as much solar energy as expected, is the signal strength as expected,...?).
- Nominal Operations Phase: Main operations starts (e.g. measurements, communication passes with our ground station,...).
- End of Life Phase: Mission ends, and we ensure a safe satellite disposal (e.g. batteries are fully discharged).
The goal of this semester project will be to continue the work performed on operations. This includes the tasks already described, but also more technical work. For example, a critical point is to know precisely how much data can be exchanged with the satellite during a communication window to know which procedures can be executed. This project will see lots of interaction with the Telecommunication, Flight Software and Ground Segment poles. A part of the project will also involve tests with part of the satellites, such as testing a portable ground segment and planning for future mission tests.
Tasks:
- Getting acquainted with the work already done regarding operations (CHESS documentation, OPS-SAT writing guidelines,...)
- Listing the telecommands available for operators
- Planning operational procedures, taking into account the duration of communication windows
- Testing communication and some procedures with the FlatSat and a portable ground station.
Background and skills:
- Some basic knowledge about space missions and spacecrafts
- Ability to think creatively and rationally on possible commands and anomalies
- Autonomy and ability to discuss and work with other poles
Development of a Retrieval-Augmented Generation Assistant for EST Documentation
MA Semester Project (8 ECTS)
Section : SC, RO, IC
Description:
The EPFL Spacecraft Team develops a full spacecraft mission through contributions from multiple technical poles, including Mission Design, Flight Software, Telecommunications, ADCS, Ground Segment and many others. Over time, each pole generates a large volume of documentation, designing rationales, requirements, procedures, and reports stored in a shared drive structure.
While this drive is organized, the increasing volume of documents makes it difficult for new and existing members to efficiently obtain relevant information. Common questions such as “Why was this parameter chosen?”, “Where is this requirement defined?”, or “What is the procedure for this subsystem?” often require manual browsing across multiple folders and files, leading to time inefficiencies.
The goal of this semester project is to design and implement an AI-powered Retrieval-Augmented Generation (RAG) system that enables natural language access to the association’s internal documentation. The system will allow users to write their queries in plain language and receive grounded answers supported by the relevant EST documents.
The system is expected to index structured and unstructured documents from shared drives, perform semantic search over embeddings, and generate responses using a large language model constrained by the stored context. Special attention will be given to traceability of answers, including explicit citation of source documents and robustness against hallucinated information.
Tasks:
- Familiarise with existing documentation structure (shared drive, subsystem repositories, technical reports…).
- Design a knowledge ingestion pipeline for various document formats (PDF, Google sheets, Google docs,...), including automatic periodic updates of the RAG knowledge base every X days.
- Implement document preprocessing and chunking strategies suitable for engineering content.
- Explore different types of retrieval such as graph search, semantic, lexical or a hybrid approach. Then, use a vector database for embedding.
- Integrate a large language model with retrieval (RAG architecture) to generate grounded answers and implement source attribution (citations linking responses to original documents).
- Evaluate system performance and accuracy on representative technical questions.
- Deploy a usable prototype interface (ideally web-based) for EPFL Spacecraft Team members.
Background and skills:
- Basic knowledge of machine learning and natural language processing.
- Familiarity with Python programming.
- Interest in information retrieval, embeddings, and large language models.
- Ability to work with unstructured data and software systems.
- Autonomy and capacity to interact with multiple technical teams and adapt to their documentation practices.
The EPFL Spacecraft Team develops a full spacecraft mission through contributions from multiple technical poles, including Mission Design, Flight Software, Telecommunications, ADCS, Ground Segment and many others. Over time, each pole generates a large volume of documentation, designing rationales, requirements, procedures, and reports stored in a shared drive structure.
While this drive is organized, the increasing volume of documents makes it difficult for new and existing members to efficiently obtain relevant information. Common questions such as “Why was this parameter chosen?”, “Where is this requirement defined?”, or “What is the procedure for this subsystem?” often require manual browsing across multiple folders and files, leading to time inefficiencies.
The goal of this semester project is to design and implement an AI-powered Retrieval-Augmented Generation (RAG) system that enables natural language access to the association’s internal documentation. The system will allow users to write their queries in plain language and receive grounded answers supported by the relevant EST documents.
The system is expected to index structured and unstructured documents from shared drives, perform semantic search over embeddings, and generate responses using a large language model constrained by the stored context. Special attention will be given to traceability of answers, including explicit citation of source documents and robustness against hallucinated information.
Tasks:
- Familiarise with existing documentation structure (shared drive, subsystem repositories, technical reports…).
- Design a knowledge ingestion pipeline for various document formats (PDF, Google sheets, Google docs,...), including automatic periodic updates of the RAG knowledge base every X days.
- Implement document preprocessing and chunking strategies suitable for engineering content.
- Explore different types of retrieval such as graph search, semantic, lexical or a hybrid approach. Then, use a vector database for embedding.
- Integrate a large language model with retrieval (RAG architecture) to generate grounded answers and implement source attribution (citations linking responses to original documents).
- Evaluate system performance and accuracy on representative technical questions.
- Deploy a usable prototype interface (ideally web-based) for EPFL Spacecraft Team members.
Background and skills:
- Basic knowledge of machine learning and natural language processing.
- Familiarity with Python programming.
- Interest in information retrieval, embeddings, and large language models.
- Ability to work with unstructured data and software systems.
- Autonomy and capacity to interact with multiple technical teams and adapt to their documentation practices.