Thesis list
@ SPLab
These these activities will be developed at the SPLab, Bovisa South campus.
PoliMi Advisor: F. Maggi
Co-advisor: Ing. J. Domaschio
Starting date: immediate availability
Availability: 2 candidates
Location: SPLab (POLIMI)
(UPDATED) Candidacy closes on April 6th
Thermite for demise is a method to use reactive materials supporting the demise of satellites. Experimental tests have demonstrated that some kinds of thermites can ignite in space and can promote the demise of spacecraft components.
Lab-scale development and testing are crucial aspects for the advancement of the technology. The candidates will cooperate in such a development. The candidates will jointly work at the preparation of these reactive materials (and their development/evolution), at the same time implementing new diagnostics based on spectroscopic measurements. Implementation of a new experimental line is part of the activity. Laboratory presence is fundamental and continuity of work is a request.
PoliMi Advisor: F. Maggi
Starting date: June 2025 (to be confirmed)
Availability: 1 / 2 candidates
Location: SPLab (POLIMI)
Water and metals can create interesting reactions, such as hydrolysis. This is a chemical reaction that produces heat and hydrogen, at the same time. The control of such reaction is a key factor for its exploitation.
The thesis aims at the characterization of how some types of materials and processes can alter the rate of this reaction. The student(s) will produce these materials, according to specific guidelines, and will test the generation capacity of the resulting materials.
PoliMi Advisor: F. Maggi
Co-advisor: A. N. Lucarno / S. Carlotti
Starting date: June 2025 (to be confirmed)
Availability: 2 candidates
Location: SPLab (POLIMI)
The production of energetic materials via UV curing can disclose new benefits to products and missions. One of the pillars of the technology consists of the printing device. The maturation og the printing capacity needs testing and improvement of existing technical solutions. The candidates will work on the current version of the printing machine. After an initial review analysis, they can apply improvements, targeting production and characterization of some material batches.
Laboratory presence is fundamental and continuity of work is a request.
PoliMi Advisor: S. Carlotti
Starting date: now
Availability: 2 candidates
Location: SPLab (POLIMI)
The topic targets the analysis of launchers with different propellants (e.g., LOX/RP1, LOX/CH4, H2O2/RP1), focusing on combustion products emission during flight. Emissions will be quantified during trajectory optimization using the NASA CEA code, combining -eventually-climatological models to evaluate atmospheric interactions using MATLAB and Cantera. Throttling and mixture ratio shifts will be analyzed, and the impact of environment-related constraints during the optimization will be assessed.
PoliMi Advisor: S. Carlotti
Starting date: now
Availability: 2 candidates
Location: SPLab (POLIMI)
The topic focuses on the development of AI-assisted robust design methodologies to enable faster optimization of liquid rocket upper stages using machine learning and simulations. The design framework will be based on synthetic or real launchers data to create multiple AI-based models, supporting both conceptual trade-off analysis and detailed design optimization.
PoliMi Advisor: S. Carlotti
Starting date: now
Availability: 2 candidates
Location: SPLab (POLIMI)
This work develops a general numerical framework able to provide a description of a packed bed reactor, along with the necessary engineering correlations for the full characterization of mass, energy, and momentum transfer. In particular, 1D pseudo-homogeneous/heterogeneous models are considered, targeting the description of both steady and transient flow. Experimental data will be provided for validation purposes.
PoliMi Advisor: S. Carlotti
Starting date: now
Availability: 1 candidate
Location: SPLab (POLIMI)
This work focuses on analysing several microencapsulation techniques and identifying suitable characterization methodologies for the resulting capsules. A preliminary experimental investigation will be carried out to assess the feasibility of the selected methodologies, assessing their effectiveness in encapsulating HTP within a protective shell or matrix to enhance its stability and control its release.
PoliMi Advisor: F. Maggi
Company Supervisor: Ing. N. Foletti
Activity begins in April/May 2025.
Availability: 2 candidate
Location: OPERA joint lab (SPLab)
(UPDATED) Candidacy closes on March 30th
Bipropellant thrusters are critical for spacecraft propulsion, requiring optimized designs to maximize thrust performance, combustion efficiency, and maneuverability. One key technology for enhancing combustion efficiency and flow stability is the use of innovative injectors design. However, existing models often lack comprehensive analysis, limiting their predictive accuracy.
This thesis aims to analyze and numerically model innovative injectors in bipropellant thrusters through three key phases. First, literature review & analytical assessment is performed to review existing analytical models, experimental studies, and numerical simulations from literature on the topic. Through the assessment of the literature, the candidate will identify research gaps and constraints on injector designs for bipropellant thrusters. Second, The candidate will develop a numerical model based on existing analytical frameworks to enhance the understanding of injector-driven flow dynamics. Within the model, computational fluid dynamics (CFD) simulations will be implemented to explore injectors behavior under various operating conditions. Finally, a parametric study & performance analysis to investigate the effects of key parameters shall be performed in order to validate model predictions against experimental or benchmark data, identifying the limitations of current analytical approaches.
Through the thesis work, the candidate will identify limitations in existing analytical models, develop numerical models capable of accurately predicting injector flow characteristics and perform a parametric analysis providing insights into how design parameters influence flow structure and combustion performances, advancing the design of bipropellant thrusters for space applications.
Proficiency in Python and MATLAB is mandatory, while previous experience through modeling and simulation courses is preferred. Experience with OpenFOAM course is required.
PoliMi Advisor: F. Maggi
Company Supervisor: Ing. N. Foletti
Activity begins in April/May 2025.
Availability: 1/2 candidates
Location: OPERA joint lab (SPLab)
(UPDATED) Candidacy closes on March 30th
Bipropellant thrusters play a critical role in spacecraft propulsion, requiring precise design to ensure optimal thrust performance, combustion efficiency, and maneuverability. One of the most effective techniques for enhancing combustion efficiency and flow stability in liquid propellant engines is the use of innovative injectors. However, achieving an accurate experimental visualization of this flow structure remains a key challenge in propulsion research.
This Master’s thesis aims to develop and apply quantitative experimental visualization techniques to gain deeper insights into innovative injector flow dynamics. The research will be structured into three main phases. First, literature review & analytical assessment is performed to conduct a comprehensive review of existing experimental techniques used to study injector-driven flow structures. The most effective visualization methods and key parameters that influence flow dynamics shall be identified. Second, and experimental setup is Developed leveraging the existing infrastructure at SPLAB. Measurement techniques
to enable high-resolution flow visualization and quantitative analysis of injector designsa shall be implemented by the candidaste during this phase. Finally, a comparative analysis & model validation to correlate experimental results with data, analytical and numerical models is performed to provide practical recommendations for optimizing combustion chambers based on the findings.
Through the thesis work, the candidate will identify a comprehensive visual dataset of injector-driven flow dynamics and identify insights on how to enhance combustion chamber design and improve propellant mixing efficiency.
Proficiency in Python and MATLAB for data analysis and numerical modeling is mandatory. CAD modeling skills for designing of experimental components is mandatory.
Corporate theses
These thesis are planned and managed by a company. These theses may bring you outside POLIMI. Not in every case. The student must be aware that, typically, financial support is not granted by the hosting institute which decides timing, and methods for thesis development.
Project @ DAER
Cooperative project laboratory involving developed at the Dept. of Aerospace Science and Technology, Bovisa South campus.
The development of reusable launch vehicles is a multidisciplinary effort, requiring advancements in several disciplines, such as materials, structures, propulsion, aerodynamic and guidance and control systems. The Reusable Launchers Thesis Lab offers students the opportunity to conduct their thesis within a collaborative research environment, contributing to the broader framework of reusable launcher design.
The laboratory will begin in April and will include regular review meetings with the supervising professor, as well as joint review sessions involving all participating students.
The selection process consists of two steps:
a. an evaluation based on GPA and attended and passed courses relevant to the chosen topic – note: students can select up to 3 topics.
b. an interview with the supervising professor for the top 5 ranked candidates in each topic.
Note that a maximum of two remaining exams is required.
The deadline for filling this form is March 28th
You can read more about the available topics and advance your candidacy HERE
Note #1: we are missing few corporate theses. They will arrive in the next days.
Note #2: candidacy for internal theses should be addressed to the advisor of the activity. Send an email with subject “CANDIDACY [FAMILY-NAME] THESIS”.
This email will have to include two PDF attachments: a CV in English and a list of exams with scores.
(UPDATED) Note #3: address the candidacy for corporate theses to Prof. Maggi by March 30th. A selection process will follow. Send an email with subject “CANDIDACY [FAMILY-NAME] CORPORATE THESIS”. This email will have to include two PDF attachments: a CV in English and a list of exams with scores.
Last Update: March 23rd, 2025