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Semester Projects
Fall 2025
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
No BA Projects this semester
Design and Build of a Satellite Qualification Dispenser
MA Semester project or Bachelor project
Section : Non-specific
Description:
The EPFL Spacecraft Team aims at launching its first 3U CubeSat in mid-2027. To prepare for the environmental qualification and acceptance tests, the team requires a robust structural model of a 3U CubeSat dispenser dedicated exclusively to ground testing.
A first vibration test campaign using mass dummies revealed several issues with the current dispenser prototype. The structure was not stiff enough, resulting in natural frequencies falling inside the tested range, whereas the first modes should exceed 2000 Hz. Multiple screws ripped out their threads, and some loosened during testing, indicating insufficient strength and inadequate load paths. In addition, the CubeSat model did not slide correctly inside the dispenser due to improper tolerances. These findings clearly confirm the need for a redesigned dispenser before the official qualification and acceptance campaign.
The objective of this semester project is to design and build an improved dispenser that resolves these shortcomings. The work includes increasing structural stiffness, validating the design through FEM analysis, and correcting tolerances to ensure smooth CubeSat insertion. All interfaces to the shaker table must be redesigned so that each connection uses at least two screws for reliable load transfer. The assembly process should also be simplified to improve handling during test preparation.
The project will involve CAD modelling, structural simulation, fabrication of the redesigned dispenser, and validation testing. It will be carried out under the Structures pole, which currently manages all mechanical testing within the team.
Tasks:
• Learn about vibration tests and review the previous dispenser design
• Design a new dispenser addressing the identified shortcomings
• Verify compliance with ESA standards and shaker table constraints
• Perform FEM simulations to ensure adequate stiffness and structural integrity
• Manufacture the redesigned dispenser and participate in validation tests
Background and skills:
• Mechanical vibrations
• Finite Element Method (FEM)
• CAD design (e.g., SolidWorks, Fusion 360)
• Both Soubielle Courses
The EPFL Spacecraft Team aims at launching its first 3U CubeSat in mid-2027. To prepare for the environmental qualification and acceptance tests, the team requires a robust structural model of a 3U CubeSat dispenser dedicated exclusively to ground testing.
A first vibration test campaign using mass dummies revealed several issues with the current dispenser prototype. The structure was not stiff enough, resulting in natural frequencies falling inside the tested range, whereas the first modes should exceed 2000 Hz. Multiple screws ripped out their threads, and some loosened during testing, indicating insufficient strength and inadequate load paths. In addition, the CubeSat model did not slide correctly inside the dispenser due to improper tolerances. These findings clearly confirm the need for a redesigned dispenser before the official qualification and acceptance campaign.
The objective of this semester project is to design and build an improved dispenser that resolves these shortcomings. The work includes increasing structural stiffness, validating the design through FEM analysis, and correcting tolerances to ensure smooth CubeSat insertion. All interfaces to the shaker table must be redesigned so that each connection uses at least two screws for reliable load transfer. The assembly process should also be simplified to improve handling during test preparation.
The project will involve CAD modelling, structural simulation, fabrication of the redesigned dispenser, and validation testing. It will be carried out under the Structures pole, which currently manages all mechanical testing within the team.
Tasks:
• Learn about vibration tests and review the previous dispenser design
• Design a new dispenser addressing the identified shortcomings
• Verify compliance with ESA standards and shaker table constraints
• Perform FEM simulations to ensure adequate stiffness and structural integrity
• Manufacture the redesigned dispenser and participate in validation tests
Background and skills:
• Mechanical vibrations
• Finite Element Method (FEM)
• CAD design (e.g., SolidWorks, Fusion 360)
• Both Soubielle Courses
Stress Analysis of the CHESS CubeSat Under Launch Loads Using Finite Element Modeling
MA Semester project or Bachelor project
Section : ME
Description:
The CHESS Pathfinder-0 CubeSat has recently undergone a redesign of its internal assembly, including updated component placements, modified interfaces, and new fastener configurations. These changes, combined with issues observed during the most recent vibration campaign, require a revised and more detailed structural assessment. During testing, the satellite exhibited insufficient stiffness, unexpectedly low eigenfrequencies, and several screw joints loosened under load. This demonstrated the need for an improved model and a dedicated analysis of bolted interfaces.
The goal of this project is to develop an improved finite element model of the updated CHESS Pathfinder-0 CubeSat assembly using Ansys. The structural behaviour of the new assembly will be analysed under representative launch loads, including quasi-static accelerations, random vibrations, and shock loads. A particular focus will be placed on assessing and improving bolted joints and threaded interfaces, which were not included in previous analyses.
The student will compute stresses, deformations, safety margins, and the first eigenfrequency, and verify compliance with applicable CubeSat and launcher standards. Based on the results, the student will identify weaknesses in the current design, propose concrete design improvements, and evaluate their effectiveness through updated simulations.
Tasks:
• Gain a thorough understanding of the CHESS satellite's design and architecture.
• Model the updated Pathfinder-0 assembly in Ansys.
• Perform static, modal, and dynamic finite element analyses under representative launch loads.
• Analyse and assess bolted joints and threaded interfaces.
• Identify structural weaknesses and make recommendations for improving the next iteration of the design.
• Implement design modifications based on simulation results and evaluate their impact.
• Compile and adapt CubeSat standards and launcher requirements relevant to structural modelling.
Background and skills:
• Prior coursework in Finite Element Methods (FEM).
• Experience with Ansys, Abaqus, or similar FEA/CAD software.
• Basic understanding of structural mechanics and vibration analysis (recommended).
The CHESS Pathfinder-0 CubeSat has recently undergone a redesign of its internal assembly, including updated component placements, modified interfaces, and new fastener configurations. These changes, combined with issues observed during the most recent vibration campaign, require a revised and more detailed structural assessment. During testing, the satellite exhibited insufficient stiffness, unexpectedly low eigenfrequencies, and several screw joints loosened under load. This demonstrated the need for an improved model and a dedicated analysis of bolted interfaces.
The goal of this project is to develop an improved finite element model of the updated CHESS Pathfinder-0 CubeSat assembly using Ansys. The structural behaviour of the new assembly will be analysed under representative launch loads, including quasi-static accelerations, random vibrations, and shock loads. A particular focus will be placed on assessing and improving bolted joints and threaded interfaces, which were not included in previous analyses.
The student will compute stresses, deformations, safety margins, and the first eigenfrequency, and verify compliance with applicable CubeSat and launcher standards. Based on the results, the student will identify weaknesses in the current design, propose concrete design improvements, and evaluate their effectiveness through updated simulations.
Tasks:
• Gain a thorough understanding of the CHESS satellite's design and architecture.
• Model the updated Pathfinder-0 assembly in Ansys.
• Perform static, modal, and dynamic finite element analyses under representative launch loads.
• Analyse and assess bolted joints and threaded interfaces.
• Identify structural weaknesses and make recommendations for improving the next iteration of the design.
• Implement design modifications based on simulation results and evaluate their impact.
• Compile and adapt CubeSat standards and launcher requirements relevant to structural modelling.
Background and skills:
• Prior coursework in Finite Element Methods (FEM).
• Experience with Ansys, Abaqus, or similar FEA/CAD software.
• Basic understanding of structural mechanics and vibration analysis (recommended).
Ground segment
No BA Projects this semester
Development of an end-to-end simulation of the CHESS satellite and operations
MA Semester project
Section : Non-specific
Description:
Multiple software tools are developed at the EPFL Spacecraft Team to simulate and/or control our CHESS satellite, a 3U CubeSat. The goal of this semester project would be to interface them and build an end-to-end simulation of the satellite. This simulator will then be used to train operators that will control the satellite when it will be launched, test procedures and code before applying them to the real satellite, etc. Here, we present briefly the four tools that are currently being developed in the association and that will have to be interfaced to build this end-to-end simulation:
- Mission Control Software (MCS): See Mission Design
- 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).
- NEST: See Flight software
- Digital Twin: See Mission Design
Tasks:
• Interfacing the MCS with the Ground Segment Pipeline to book antennas from the MCS and send/receive data through the Ground Segment Pipeline;
• Interfacing NEST and the Digital Twin to send environmental data to NEST from the Digital Twin;
• Interfacing NEST and the MCS (through the Ground Segment Pipeline) to send telecommands to NEST and receive telemetry;
• Test the whole simulator, potentially with some mission scenarios.
Background and skills:
• Some basic knowledge about space missions and spacecrafts;
• Python programmation skills;
• Curiosity to learn new tools;
• Appeal for satellite operations and playing with simulations.
Multiple software tools are developed at the EPFL Spacecraft Team to simulate and/or control our CHESS satellite, a 3U CubeSat. The goal of this semester project would be to interface them and build an end-to-end simulation of the satellite. This simulator will then be used to train operators that will control the satellite when it will be launched, test procedures and code before applying them to the real satellite, etc. Here, we present briefly the four tools that are currently being developed in the association and that will have to be interfaced to build this end-to-end simulation:
- Mission Control Software (MCS): See Mission Design
- 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).
- NEST: See Flight software
- Digital Twin: See Mission Design
Tasks:
• Interfacing the MCS with the Ground Segment Pipeline to book antennas from the MCS and send/receive data through the Ground Segment Pipeline;
• Interfacing NEST and the Digital Twin to send environmental data to NEST from the Digital Twin;
• Interfacing NEST and the MCS (through the Ground Segment Pipeline) to send telecommands to NEST and receive telemetry;
• Test the whole simulator, potentially with some mission scenarios.
Background and skills:
• Some basic knowledge about space missions and spacecrafts;
• Python programmation skills;
• Curiosity to learn new tools;
• Appeal for satellite operations and playing with simulations.
Development of an End-to-End Data Acquisition Pipeline for CHESS Satellites and Telemetry Processing.
MA Semester project
Section : EE
Description:
This project is framed within the preparation of the Ground Segment (GS) for the CHESS Pathfinder-0 mission, whose main objective is to validate the performance of the SatNOGS COMMS transceiver in Low Earth Orbit (LEO). The focus is the robust implementation of the receiver's Digital Signal Processing (DSP) core, which will operate on the signal captured by an existing parabolic antenna and an SDR.
The communication strategy relies on band specialization: UHF for critical telemetry and beacons (using FSK/Baseband Mode) and S-Band for high-rate downlink (using QPSK/IQ Mode with CCSDS FEC).The project will culminate in the construction of a complete Data Acquisition Pipeline in a hybrid C/GNU Radio environment, integrating tracking and correction algorithms to maximize link margin and user data quality.
Tasks:
• Implement and test the following adaptive algorithms (DSP):
- Kalman Filter: For coherent and optimal carrier tracking and dynamic compensation of
residual Doppler rate on the QPSK link
- Adaptive LMS Equalizer: For active mitigation of Inter-Symbol Interference (ISI).
- Adaptive Notch Filter: For the mitigation of narrow-band interference (e.g., satellite spurious emissions or RFI background noise).
• Reception Pipeline Development (C/GNU Radio): Build the complete demodulation chain and integration for both bands.
• Live Validation: Functional testing of the complete DSP chain by acquiring signals from available satellites (e.g., QO-100 QPSK/DVB-S2 beacon for stability and LEO FSK satellites for Doppler validation).
Background and skills:
• Solid knowledge in DSP and Estimation/Adaptive Theory (Kalman Filters, LMS Algorithm).
• Proficiency in Python programming.
• Familiarity with Software Defined Radio (SDR) platforms and GNU Radio.
• Basic knowledge of space communication protocols (CCSDS).
This project is framed within the preparation of the Ground Segment (GS) for the CHESS Pathfinder-0 mission, whose main objective is to validate the performance of the SatNOGS COMMS transceiver in Low Earth Orbit (LEO). The focus is the robust implementation of the receiver's Digital Signal Processing (DSP) core, which will operate on the signal captured by an existing parabolic antenna and an SDR.
The communication strategy relies on band specialization: UHF for critical telemetry and beacons (using FSK/Baseband Mode) and S-Band for high-rate downlink (using QPSK/IQ Mode with CCSDS FEC).The project will culminate in the construction of a complete Data Acquisition Pipeline in a hybrid C/GNU Radio environment, integrating tracking and correction algorithms to maximize link margin and user data quality.
Tasks:
• Implement and test the following adaptive algorithms (DSP):
- Kalman Filter: For coherent and optimal carrier tracking and dynamic compensation of
residual Doppler rate on the QPSK link
- Adaptive LMS Equalizer: For active mitigation of Inter-Symbol Interference (ISI).
- Adaptive Notch Filter: For the mitigation of narrow-band interference (e.g., satellite spurious emissions or RFI background noise).
• Reception Pipeline Development (C/GNU Radio): Build the complete demodulation chain and integration for both bands.
• Live Validation: Functional testing of the complete DSP chain by acquiring signals from available satellites (e.g., QO-100 QPSK/DVB-S2 beacon for stability and LEO FSK satellites for Doppler validation).
Background and skills:
• Solid knowledge in DSP and Estimation/Adaptive Theory (Kalman Filters, LMS Algorithm).
• Proficiency in Python programming.
• Familiarity with Software Defined Radio (SDR) platforms and GNU Radio.
• Basic knowledge of space communication protocols (CCSDS).
Flight software
Development of the Embedded Software for the CubeSat Electrical Power System
MA Semester project & Bachelor Project
Section : ELE MT IN
Description:
This project focuses on developing the embedded software that operates the Electrical Power System (EPS) of a CubeSat. The EPS microcontroller is responsible for monitoring system currents and voltages, controlling the DC/DC converter, and ensuring reliable communication with the On-Board Computer (OBC). The student will design, implement, and validate the firmware architecture required for these functions, including the communication protocol and the command/telemetry interface.
Because CubeSats operate in a radiation-prone environment, the software must also include mechanisms to detect radiation-induced faults, recover from microcontroller upsets, and guarantee safe operation through watchdogs, state-machine design, and reset logic. The goal is to deliver a robust, fault-tolerant firmware running on the EPS prototype and ready for integration into the flight hardware.
Tasks:
• Study the EPS architecture and define software requirements for monitoring, control, and communication.
• Implement current and voltage monitoring routines and data acquisition.
• Develop control algorithms for the DC/DC converter fault handling.
• Implement the communication interface with the OBC (UART).
• Design telemetry and command structures for EPS–OBC interactions.
• Implement fault-tolerance features: watchdog management, error detection, safe states, and reset mechanisms for radiation-induced upsets.
• Test the firmware on the EPS prototype and perform robustness checks (noise, transient events, brown-out conditions).
• Document firmware architecture, interfaces, and test results.
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
This project focuses on developing the embedded software that operates the Electrical Power System (EPS) of a CubeSat. The EPS microcontroller is responsible for monitoring system currents and voltages, controlling the DC/DC converter, and ensuring reliable communication with the On-Board Computer (OBC). The student will design, implement, and validate the firmware architecture required for these functions, including the communication protocol and the command/telemetry interface.
Because CubeSats operate in a radiation-prone environment, the software must also include mechanisms to detect radiation-induced faults, recover from microcontroller upsets, and guarantee safe operation through watchdogs, state-machine design, and reset logic. The goal is to deliver a robust, fault-tolerant firmware running on the EPS prototype and ready for integration into the flight hardware.
Tasks:
• Study the EPS architecture and define software requirements for monitoring, control, and communication.
• Implement current and voltage monitoring routines and data acquisition.
• Develop control algorithms for the DC/DC converter fault handling.
• Implement the communication interface with the OBC (UART).
• Design telemetry and command structures for EPS–OBC interactions.
• Implement fault-tolerance features: watchdog management, error detection, safe states, and reset mechanisms for radiation-induced upsets.
• Test the firmware on the EPS prototype and perform robustness checks (noise, transient events, brown-out conditions).
• Document firmware architecture, interfaces, and test results.
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
Development of an end-to-end simulation of the CHESS satellite and operations
MA Semester project
Section : Non-specific
Description:
Multiple software tools are developed at the EPFL Spacecraft Team to simulate and/or control our CHESS satellite, a 3U CubeSat. The goal of this semester project would be to interface them and build an end-to-end simulation of the satellite. This simulator will then be used to train operators that will control the satellite when it will be launched, test procedures and code before applying them to the real satellite, etc. Here, we present briefly the four tools that are currently being developed in the association and that will have to be interfaced to build this end-to-end simulation:
- Mission Control Software (MCS): See Mission Design
- Ground Segment Pipeline: See Ground Segment
- 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.
- Digital Twin: See Mission Design
Tasks:
• Interfacing the MCS with the Ground Segment Pipeline to book antennas from the MCS and send/receive data through the Ground Segment Pipeline;
• Interfacing NEST and the Digital Twin to send environmental data to NEST from the Digital Twin;
• Interfacing NEST and the MCS (through the Ground Segment Pipeline) to send telecommands to NEST and receive telemetry;
• Test the whole simulator, potentially with some mission scenarios.
Background and skills:
• Some basic knowledge about space missions and spacecrafts;
• Python programmation skills;
• Curiosity to learn new tools;
• Appeal for satellite operations and playing with simulations.
Multiple software tools are developed at the EPFL Spacecraft Team to simulate and/or control our CHESS satellite, a 3U CubeSat. The goal of this semester project would be to interface them and build an end-to-end simulation of the satellite. This simulator will then be used to train operators that will control the satellite when it will be launched, test procedures and code before applying them to the real satellite, etc. Here, we present briefly the four tools that are currently being developed in the association and that will have to be interfaced to build this end-to-end simulation:
- Mission Control Software (MCS): See Mission Design
- Ground Segment Pipeline: See Ground Segment
- 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.
- Digital Twin: See Mission Design
Tasks:
• Interfacing the MCS with the Ground Segment Pipeline to book antennas from the MCS and send/receive data through the Ground Segment Pipeline;
• Interfacing NEST and the Digital Twin to send environmental data to NEST from the Digital Twin;
• Interfacing NEST and the MCS (through the Ground Segment Pipeline) to send telecommands to NEST and receive telemetry;
• Test the whole simulator, potentially with some mission scenarios.
Background and skills:
• Some basic knowledge about space missions and spacecrafts;
• Python programmation skills;
• Curiosity to learn new tools;
• Appeal for satellite operations and playing with simulations.
Reliability Engineering with NEST: Fault Injection, Fuzzing, and Automated System Verification
MA Semester project (12 ETCS)
Section : IN SC
Description:
Reliability is paramount in space missions. The NEST (Numerical Environment for Software Testing) simulator is the critical infrastructure developed by the EPFL Spacecraft Team to enable accessible, flexible, and reproducible software-in-the-loop testing of the CHESS (Constellation of High-performance Exospheric Science Satellites) satellites. By executing the flight software natively within a simulated environment, NEST allows for the validation of complex operational conditions that would be impossible or too costly to reproduce with real hardware.
The goal of this project is to engineer a comprehensive reliability and testing framework within the NEST ecosystem to validate the CHESS Flight Software. This framework aims to ensure the system's resilience against diverse failure modes, ranging from sensor faults to memory corruption. A central part of the project is the definition and implementation of mission-representative test scenarios and regression campaigns that will run inside the simulator and directly test the behavior and robustness of the Flight Software.
In addition, the student will leverage NEST’s modular architecture to address two engineering challenges. First, a Scenario Orchestration Engine will be developed using NEST’s commands and events features to define canonical mission phases and establish a rigorous baseline for regression testing. Second, a multi-level Fault Injection & Fuzzing strategy will be implemented. This includes Hardware-Level Fuzzing via NEST System Ports (injecting anomalies into UART, I2C, GPIO interfaces) and exploring Component-Level Fuzzing to test F’ internal logic and state machines. Finally, the framework will define test campaigns to evaluate system recovery from radiation-induced memory bit-flips (SEUs), leveraging the low-level radiation emulation features developed in parallel.
Tasks:
• Design and implementation of test scenarios and regression campaigns in NEST to evaluate the robustness of the Flight Software.
• Test Surface Definition & Fault Modeling: Create a formal taxonomy of fault models (e.g., SEU/Bit-flips, sensor drift, I2C timeouts) to guide the testing strategy
• Test coverage and edge-case analysis across all Flight Software components, ensuring robustness even under rare conditions.
• Scenario Engine Evolution: Evolve the Python scripting interface into a robust engine that supports declarative assertions and dynamic fault injection via Control Channels
• Scenario-Driven Fuzzing Strategy: Define and implement the high-level fuzzing logic within the Scenario Engine to drive the message mutation tools (developed in coordination with the NEST implementation team).
• Invariant Verification: Implement a runtime monitor within the orchestration engine to check safety properties during execution, proving the system's resilience
Background and skills:
• Systems Programming: understanding of simulation architectures, WebAssembly (WASM), and memory layouts
• Software Testing: interest in Fuzzing, Integration Testing, and System Verification
• Python Development: Proficiency in Python is required for scripting the orchestration engine and high-level test logic.
• Rust Programming: Basic knowledge is useful to understand the simulator's internal logic and potentially patch core features if needed.
• Flight Software Awareness: Ability to understand the architecture of the CHESS Flight Software to design relevant fault models and tests
Reliability is paramount in space missions. The NEST (Numerical Environment for Software Testing) simulator is the critical infrastructure developed by the EPFL Spacecraft Team to enable accessible, flexible, and reproducible software-in-the-loop testing of the CHESS (Constellation of High-performance Exospheric Science Satellites) satellites. By executing the flight software natively within a simulated environment, NEST allows for the validation of complex operational conditions that would be impossible or too costly to reproduce with real hardware.
The goal of this project is to engineer a comprehensive reliability and testing framework within the NEST ecosystem to validate the CHESS Flight Software. This framework aims to ensure the system's resilience against diverse failure modes, ranging from sensor faults to memory corruption. A central part of the project is the definition and implementation of mission-representative test scenarios and regression campaigns that will run inside the simulator and directly test the behavior and robustness of the Flight Software.
In addition, the student will leverage NEST’s modular architecture to address two engineering challenges. First, a Scenario Orchestration Engine will be developed using NEST’s commands and events features to define canonical mission phases and establish a rigorous baseline for regression testing. Second, a multi-level Fault Injection & Fuzzing strategy will be implemented. This includes Hardware-Level Fuzzing via NEST System Ports (injecting anomalies into UART, I2C, GPIO interfaces) and exploring Component-Level Fuzzing to test F’ internal logic and state machines. Finally, the framework will define test campaigns to evaluate system recovery from radiation-induced memory bit-flips (SEUs), leveraging the low-level radiation emulation features developed in parallel.
Tasks:
• Design and implementation of test scenarios and regression campaigns in NEST to evaluate the robustness of the Flight Software.
• Test Surface Definition & Fault Modeling: Create a formal taxonomy of fault models (e.g., SEU/Bit-flips, sensor drift, I2C timeouts) to guide the testing strategy
• Test coverage and edge-case analysis across all Flight Software components, ensuring robustness even under rare conditions.
• Scenario Engine Evolution: Evolve the Python scripting interface into a robust engine that supports declarative assertions and dynamic fault injection via Control Channels
• Scenario-Driven Fuzzing Strategy: Define and implement the high-level fuzzing logic within the Scenario Engine to drive the message mutation tools (developed in coordination with the NEST implementation team).
• Invariant Verification: Implement a runtime monitor within the orchestration engine to check safety properties during execution, proving the system's resilience
Background and skills:
• Systems Programming: understanding of simulation architectures, WebAssembly (WASM), and memory layouts
• Software Testing: interest in Fuzzing, Integration Testing, and System Verification
• Python Development: Proficiency in Python is required for scripting the orchestration engine and high-level test logic.
• Rust Programming: Basic knowledge is useful to understand the simulator's internal logic and potentially patch core features if needed.
• Flight Software Awareness: Ability to understand the architecture of the CHESS Flight Software to design relevant fault models and tests
Development of the Embedded Software for the CubeSat Electrical Power System
MA Semester project & Bachelor Project
Section : ELE MT IN
Description:
This project focuses on developing the embedded software that operates the Electrical Power System (EPS) of a CubeSat. The EPS microcontroller is responsible for monitoring system currents and voltages, controlling the DC/DC converter, and ensuring reliable communication with the On-Board Computer (OBC). The student will design, implement, and validate the firmware architecture required for these functions, including the communication protocol and the command/telemetry interface.
Because CubeSats operate in a radiation-prone environment, the software must also include mechanisms to detect radiation-induced faults, recover from microcontroller upsets, and guarantee safe operation through watchdogs, state-machine design, and reset logic. The goal is to deliver a robust, fault-tolerant firmware running on the EPS prototype and ready for integration into the flight hardware.
Tasks:
• Study the EPS architecture and define software requirements for monitoring, control, and communication.
• Implement current and voltage monitoring routines and data acquisition.
• Develop control algorithms for the DC/DC converter fault handling.
• Implement the communication interface with the OBC (UART).
• Design telemetry and command structures for EPS–OBC interactions.
• Implement fault-tolerance features: watchdog management, error detection, safe states, and reset mechanisms for radiation-induced upsets.
• Test the firmware on the EPS prototype and perform robustness checks (noise, transient events, brown-out conditions).
• Document firmware architecture, interfaces, and test results.
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
This project focuses on developing the embedded software that operates the Electrical Power System (EPS) of a CubeSat. The EPS microcontroller is responsible for monitoring system currents and voltages, controlling the DC/DC converter, and ensuring reliable communication with the On-Board Computer (OBC). The student will design, implement, and validate the firmware architecture required for these functions, including the communication protocol and the command/telemetry interface.
Because CubeSats operate in a radiation-prone environment, the software must also include mechanisms to detect radiation-induced faults, recover from microcontroller upsets, and guarantee safe operation through watchdogs, state-machine design, and reset logic. The goal is to deliver a robust, fault-tolerant firmware running on the EPS prototype and ready for integration into the flight hardware.
Tasks:
• Study the EPS architecture and define software requirements for monitoring, control, and communication.
• Implement current and voltage monitoring routines and data acquisition.
• Develop control algorithms for the DC/DC converter fault handling.
• Implement the communication interface with the OBC (UART).
• Design telemetry and command structures for EPS–OBC interactions.
• Implement fault-tolerance features: watchdog management, error detection, safe states, and reset mechanisms for radiation-induced upsets.
• Test the firmware on the EPS prototype and perform robustness checks (noise, transient events, brown-out conditions).
• Document firmware architecture, interfaces, and test results.
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.
In-Memory Simulation of Single-Event Upsets and Hardware Interface Fuzzing Implementation in NEST
MA Semester project (8 or 12 ETCS)
Section : IN SC
Description:
Rigorous testing of spacecraft flight software is highly critical for satellite missions and requires reproducing complex interactions between the main executable, operating system, 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.
The goal of this project is to develop two new features into NEST and design testing strategies taking advantage of these features. The first is to emulate radiation-induced single-event upset in the form of randomized (or targetted) memory bit flips directly within the memory of a live QEMU virtual machine instance. This will help evaluate the resilience of the satellite’s flight software to these events. The second is to develop a hardware interface fuzzer within NEST to send large volumes of random or adversarial data to the hardware interfaces of a live QEMU virtual machine instance. This will help find implementation bugs in the flight software and improve reliability outside of nominal operation.
Tasks:
• Emulate radiation-induced single-event upset in the form of randomized (or targeted) memory bit flips directly within the memory of a live QEMU virtual machine instance.
• Develop a hardware interface fuzzer within NEST to send large volumes of random or adversarial data to the hardware interfaces of a live QEMU virtual machine instance.
• Design testing strategies taking advantage of these features.
Background and skills:
• Proficiency in Rust.
• Experience with virtual machines and emulation.
• Interest in high-performance hardware simulation.
Rigorous testing of spacecraft flight software is highly critical for satellite missions and requires reproducing complex interactions between the main executable, operating system, 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.
The goal of this project is to develop two new features into NEST and design testing strategies taking advantage of these features. The first is to emulate radiation-induced single-event upset in the form of randomized (or targetted) memory bit flips directly within the memory of a live QEMU virtual machine instance. This will help evaluate the resilience of the satellite’s flight software to these events. The second is to develop a hardware interface fuzzer within NEST to send large volumes of random or adversarial data to the hardware interfaces of a live QEMU virtual machine instance. This will help find implementation bugs in the flight software and improve reliability outside of nominal operation.
Tasks:
• Emulate radiation-induced single-event upset in the form of randomized (or targeted) memory bit flips directly within the memory of a live QEMU virtual machine instance.
• Develop a hardware interface fuzzer within NEST to send large volumes of random or adversarial data to the hardware interfaces of a live QEMU virtual machine instance.
• Design testing strategies taking advantage of these features.
Background and skills:
• Proficiency in Rust.
• Experience with virtual machines and emulation.
• Interest in high-performance hardware simulation.
EPS (Electrical Power System)
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
Development of the Embedded Software for the CubeSat Electrical Power System
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
Development of the Embedded Software for the CubeSat Electrical Power System
Telecommunication
No BA Projects this semester
No MA Projects this semester
OBC
No BA Projects this semester
No MA Projects this semester
ADCS
Dynamic attitude simulation for the digital twin of the CHESS satellite
MA Semester project or Bachelor project
Section : Non-specific
Description:
The Mission Design pole of the EPFL Spacecraft Team has developed a numerical simulation called the digital twin. It simulates the satellite in its orbit to forecast the whole mission and how the satellite would react. For example, it takes into account modifications to the orbit (because of atmospheric drag), batteries’ charge/discharge cycles, switching between different satellite modes of operations…
The aim of this project is to implement an attitude simulation in the digital twin. For now, the attitude of the satellite is changed instantaneously when the satellite changes mode. Moreover, it is static and is not affected by outside perturbations. The precise simulations for the ADCS (Attitude Determination and Control System) subsystems for the mission are carried out using the D2S2 software. However, in an effort to have a complete end-to-end simulation of our satellite - that will be used to train future operators and simulate mission scenarios - we would like to have our own dynamic ADCS simulation.
Tasks:
• Understand how the digital twin works (a nice and clear documentation is available to help with this) and what changes would be required to add an ADCS simulation (adaptive timestep between the different subsystems);
• Implement a dynamic ADCS simulation in the digital twin;
• Implement actuators (magnetorquers and reaction wheels);
• Implement sensors (gyroscope, accelerometer, magnetometer, possibly sun and earth sensors);
• Test the simulation and compare the results with D2S2.
Background and skills:
• Some basic knowledge about space missions and spacecrafts;
• Python programmation skills;
• Curiosity to learn new tools;
• Appeal for satellite operations and playing with simulations.
The Mission Design pole of the EPFL Spacecraft Team has developed a numerical simulation called the digital twin. It simulates the satellite in its orbit to forecast the whole mission and how the satellite would react. For example, it takes into account modifications to the orbit (because of atmospheric drag), batteries’ charge/discharge cycles, switching between different satellite modes of operations…
The aim of this project is to implement an attitude simulation in the digital twin. For now, the attitude of the satellite is changed instantaneously when the satellite changes mode. Moreover, it is static and is not affected by outside perturbations. The precise simulations for the ADCS (Attitude Determination and Control System) subsystems for the mission are carried out using the D2S2 software. However, in an effort to have a complete end-to-end simulation of our satellite - that will be used to train future operators and simulate mission scenarios - we would like to have our own dynamic ADCS simulation.
Tasks:
• Understand how the digital twin works (a nice and clear documentation is available to help with this) and what changes would be required to add an ADCS simulation (adaptive timestep between the different subsystems);
• Implement a dynamic ADCS simulation in the digital twin;
• Implement actuators (magnetorquers and reaction wheels);
• Implement sensors (gyroscope, accelerometer, magnetometer, possibly sun and earth sensors);
• Test the simulation and compare the results with D2S2.
Background and skills:
• Some basic knowledge about space missions and spacecrafts;
• Python programmation skills;
• Curiosity to learn new tools;
• Appeal for satellite operations and playing with simulations.
Dynamic attitude simulation for the digital twin of the CHESS satellite
MA Semester project or Bachelor project
Section : Non-specific
Description:
The Mission Design pole of the EPFL Spacecraft Team has developed a numerical simulation called the digital twin. It simulates the satellite in its orbit to forecast the whole mission and how the satellite would react. For example, it takes into account modifications to the orbit (because of atmospheric drag), batteries’ charge/discharge cycles, switching between different satellite modes of operations…
The aim of this project is to implement an attitude simulation in the digital twin. For now, the attitude of the satellite is changed instantaneously when the satellite changes mode. Moreover, it is static and is not affected by outside perturbations. The precise simulations for the ADCS (Attitude Determination and Control System) subsystems for the mission are carried out using the D2S2 software. However, in an effort to have a complete end-to-end simulation of our satellite - that will be used to train future operators and simulate mission scenarios - we would like to have our own dynamic ADCS simulation.
Tasks:
• Understand how the digital twin works (a nice and clear documentation is available to help with this) and what changes would be required to add an ADCS simulation (adaptive timestep between the different subsystems);
• Implement a dynamic ADCS simulation in the digital twin;
• Implement actuators (magnetorquers and reaction wheels);
• Implement sensors (gyroscope, accelerometer, magnetometer, possibly sun and earth sensors);
• Test the simulation and compare the results with D2S2.
Background and skills:
• Some basic knowledge about space missions and spacecrafts;
• Python programmation skills;
• Curiosity to learn new tools;
• Appeal for satellite operations and playing with simulations.
The Mission Design pole of the EPFL Spacecraft Team has developed a numerical simulation called the digital twin. It simulates the satellite in its orbit to forecast the whole mission and how the satellite would react. For example, it takes into account modifications to the orbit (because of atmospheric drag), batteries’ charge/discharge cycles, switching between different satellite modes of operations…
The aim of this project is to implement an attitude simulation in the digital twin. For now, the attitude of the satellite is changed instantaneously when the satellite changes mode. Moreover, it is static and is not affected by outside perturbations. The precise simulations for the ADCS (Attitude Determination and Control System) subsystems for the mission are carried out using the D2S2 software. However, in an effort to have a complete end-to-end simulation of our satellite - that will be used to train future operators and simulate mission scenarios - we would like to have our own dynamic ADCS simulation.
Tasks:
• Understand how the digital twin works (a nice and clear documentation is available to help with this) and what changes would be required to add an ADCS simulation (adaptive timestep between the different subsystems);
• Implement a dynamic ADCS simulation in the digital twin;
• Implement actuators (magnetorquers and reaction wheels);
• Implement sensors (gyroscope, accelerometer, magnetometer, possibly sun and earth sensors);
• Test the simulation and compare the results with D2S2.
Background and skills:
• Some basic knowledge about space missions and spacecrafts;
• Python programmation skills;
• Curiosity to learn new tools;
• Appeal for satellite operations and playing with simulations.
Mission Design
Dynamic attitude simulation for the digital twin of the CHESS satellite
MA Semester project or Bachelor project
Section : Non-specific
Description:
The Mission Design pole of the EPFL Spacecraft Team has developed a numerical simulation called the digital twin. It simulates the satellite in its orbit to forecast the whole mission and how the satellite would react. For example, it takes into account modifications to the orbit (because of atmospheric drag), batteries’ charge/discharge cycles, switching between different satellite modes of operations…
The aim of this project is to implement an attitude simulation in the digital twin. For now, the attitude of the satellite is changed instantaneously when the satellite changes mode. Moreover, it is static and is not affected by outside perturbations. The precise simulations for the ADCS (Attitude Determination and Control System) subsystems for the mission are carried out using the D2S2 software. However, in an effort to have a complete end-to-end simulation of our satellite - that will be used to train future operators and simulate mission scenarios - we would like to have our own dynamic ADCS simulation.
Tasks:
• Understand how the digital twin works (a nice and clear documentation is available to help with this) and what changes would be required to add an ADCS simulation (adaptive timestep between the different subsystems);
• Implement a dynamic ADCS simulation in the digital twin;
• Implement actuators (magnetorquers and reaction wheels);
• Implement sensors (gyroscope, accelerometer, magnetometer, possibly sun and earth sensors);
• Test the simulation and compare the results with D2S2.
Background and skills:
• Some basic knowledge about space missions and spacecrafts;
• Python programmation skills;
• Curiosity to learn new tools;
• Appeal for satellite operations and playing with simulations.
The Mission Design pole of the EPFL Spacecraft Team has developed a numerical simulation called the digital twin. It simulates the satellite in its orbit to forecast the whole mission and how the satellite would react. For example, it takes into account modifications to the orbit (because of atmospheric drag), batteries’ charge/discharge cycles, switching between different satellite modes of operations…
The aim of this project is to implement an attitude simulation in the digital twin. For now, the attitude of the satellite is changed instantaneously when the satellite changes mode. Moreover, it is static and is not affected by outside perturbations. The precise simulations for the ADCS (Attitude Determination and Control System) subsystems for the mission are carried out using the D2S2 software. However, in an effort to have a complete end-to-end simulation of our satellite - that will be used to train future operators and simulate mission scenarios - we would like to have our own dynamic ADCS simulation.
Tasks:
• Understand how the digital twin works (a nice and clear documentation is available to help with this) and what changes would be required to add an ADCS simulation (adaptive timestep between the different subsystems);
• Implement a dynamic ADCS simulation in the digital twin;
• Implement actuators (magnetorquers and reaction wheels);
• Implement sensors (gyroscope, accelerometer, magnetometer, possibly sun and earth sensors);
• Test the simulation and compare the results with D2S2.
Background and skills:
• Some basic knowledge about space missions and spacecrafts;
• Python programmation skills;
• Curiosity to learn new tools;
• Appeal for satellite operations and playing with simulations.
Development of an end-to-end simulation of the CHESS satellite and operations
MA Semester project
Section : Non-specific
Description:
Multiple software tools are developed at the EPFL Spacecraft Team to simulate and/or control our CHESS satellite, a 3U CubeSat. The goal of this semester project would be to interface them and build an end-to-end simulation of the satellite. This simulator will then be used to train operators that will control the satellite when it will be launched, test procedures and code before applying them to the real satellite, etc. Here, we present briefly the four tools that are currently being developed in the association and that will have to be interfaced to build this end-to-end simulation:
- 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: See Ground Segment
- NEST: See Flight software
- 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…etc.
Tasks:
• Interfacing the MCS with the Ground Segment Pipeline to book antennas from the MCS and send/receive data through the Ground Segment Pipeline;
• Interfacing NEST and the Digital Twin to send environmental data to NEST from the Digital Twin;
• Interfacing NEST and the MCS (through the Ground Segment Pipeline) to send telecommands to NEST and receive telemetry;
• Test the whole simulator, potentially with some mission scenarios.
Background and skills:
• Some basic knowledge about space missions and spacecrafts;
• Python programmation skills;
• Curiosity to learn new tools;
• Appeal for satellite operations and playing with simulations.
Multiple software tools are developed at the EPFL Spacecraft Team to simulate and/or control our CHESS satellite, a 3U CubeSat. The goal of this semester project would be to interface them and build an end-to-end simulation of the satellite. This simulator will then be used to train operators that will control the satellite when it will be launched, test procedures and code before applying them to the real satellite, etc. Here, we present briefly the four tools that are currently being developed in the association and that will have to be interfaced to build this end-to-end simulation:
- 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: See Ground Segment
- NEST: See Flight software
- 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…etc.
Tasks:
• Interfacing the MCS with the Ground Segment Pipeline to book antennas from the MCS and send/receive data through the Ground Segment Pipeline;
• Interfacing NEST and the Digital Twin to send environmental data to NEST from the Digital Twin;
• Interfacing NEST and the MCS (through the Ground Segment Pipeline) to send telecommands to NEST and receive telemetry;
• Test the whole simulator, potentially with some mission scenarios.
Background and skills:
• Some basic knowledge about space missions and spacecrafts;
• Python programmation skills;
• Curiosity to learn new tools;
• Appeal for satellite operations and playing with simulations.
Dynamic attitude simulation for the digital twin of the CHESS satellite
MA Semester project or Bachelor project
Section : Non-specific
Description:
The Mission Design pole of the EPFL Spacecraft Team has developed a numerical simulation called the digital twin. It simulates the satellite in its orbit to forecast the whole mission and how the satellite would react. For example, it takes into account modifications to the orbit (because of atmospheric drag), batteries’ charge/discharge cycles, switching between different satellite modes of operations…
The aim of this project is to implement an attitude simulation in the digital twin. For now, the attitude of the satellite is changed instantaneously when the satellite changes mode. Moreover, it is static and is not affected by outside perturbations. The precise simulations for the ADCS (Attitude Determination and Control System) subsystems for the mission are carried out using the D2S2 software. However, in an effort to have a complete end-to-end simulation of our satellite - that will be used to train future operators and simulate mission scenarios - we would like to have our own dynamic ADCS simulation.
Tasks:
• Understand how the digital twin works (a nice and clear documentation is available to help with this) and what changes would be required to add an ADCS simulation (adaptive timestep between the different subsystems);
• Implement a dynamic ADCS simulation in the digital twin;
• Implement actuators (magnetorquers and reaction wheels);
• Implement sensors (gyroscope, accelerometer, magnetometer, possibly sun and earth sensors);
• Test the simulation and compare the results with D2S2.
Background and skills:
• Some basic knowledge about space missions and spacecrafts;
• Python programmation skills;
• Curiosity to learn new tools;
• Appeal for satellite operations and playing with simulations.
The Mission Design pole of the EPFL Spacecraft Team has developed a numerical simulation called the digital twin. It simulates the satellite in its orbit to forecast the whole mission and how the satellite would react. For example, it takes into account modifications to the orbit (because of atmospheric drag), batteries’ charge/discharge cycles, switching between different satellite modes of operations…
The aim of this project is to implement an attitude simulation in the digital twin. For now, the attitude of the satellite is changed instantaneously when the satellite changes mode. Moreover, it is static and is not affected by outside perturbations. The precise simulations for the ADCS (Attitude Determination and Control System) subsystems for the mission are carried out using the D2S2 software. However, in an effort to have a complete end-to-end simulation of our satellite - that will be used to train future operators and simulate mission scenarios - we would like to have our own dynamic ADCS simulation.
Tasks:
• Understand how the digital twin works (a nice and clear documentation is available to help with this) and what changes would be required to add an ADCS simulation (adaptive timestep between the different subsystems);
• Implement a dynamic ADCS simulation in the digital twin;
• Implement actuators (magnetorquers and reaction wheels);
• Implement sensors (gyroscope, accelerometer, magnetometer, possibly sun and earth sensors);
• Test the simulation and compare the results with D2S2.
Background and skills:
• Some basic knowledge about space missions and spacecrafts;
• Python programmation skills;
• Curiosity to learn new tools;
• Appeal for satellite operations and playing with simulations.
Operations planification for the CHESS satellite
MA Semester Project
Section : Non-specific
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 goal of this semester project will be to continue the work performed on operations and practically plan operations. This includes the tasks already described also, 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 (recommendations from other university teams, good practices from ESA, CHESS documentation…);
• Learning how to use F’ GDS (software that will be used to operate the satellite);
• Listing the telecommands available;
• 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;
• Curiosity to learn new tools;
• Appeal for satellite operations
• 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 goal of this semester project will be to continue the work performed on operations and practically plan operations. This includes the tasks already described also, 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 (recommendations from other university teams, good practices from ESA, CHESS documentation…);
• Learning how to use F’ GDS (software that will be used to operate the satellite);
• Listing the telecommands available;
• 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;
• Curiosity to learn new tools;
• Appeal for satellite operations
• Autonomy and ability to discuss and work with other poles.