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Projecte llegit

Títol: Thermal Modelling and Analysis of CubeSat Subsystems Using ESATAN-TMS: Integration of FZPA in the 3Cat-8 Mission

Estudiants que han llegit aquest projecte:

Director/a: PARK, HYUK

Departament: FIS

Títol: Thermal Modelling and Analysis of CubeSat Subsystems Using ESATAN-TMS: Integration of FZPA in the 3Cat-8 Mission

Data inici oferta: 21-07-2025     Data finalització oferta: 21-03-2026


Estudis d'assignació del projecte:
    GR ENG SIST AEROESP
Tipus: Individual
 
Lloc de realització: EETAC
 
Segon director/a extern: Ksenia Osipova
 
Paraules clau:
CubeSat, thermal control, ESATAN-TMS, space environment, thermal modeling, subsystem integration, passive thermal strategies
 
Descripció del contingut i pla d'activitats:
Thermal analysis is a crucial aspect of satellite design, particularly for CubeSats, which are subjected to extreme space environmental conditions while operating under strict mass, volume, and power constraints. The increasing reliance on commercial CubeSat missions requires efficient, accurate, and cost-effective thermal modeling practices capable of predicting subsystem behavior and ensuring mission reliability. This thesis builds on two existing thermal studies focused on the subsystems onboard the 3Cat-8 mission: the Fresnel Patch Antenna (FZPA) and the CubeSat PocketQube Integrated Deployer (CuPID). The objective is to integrate and simulate the two subsystems using ESATAN-TMS, a state-of-the-art tool for spacecraft thermal analysis. In addition to replicating and improving previous models, the thesis introduces new sections dedicated to design optimization, sensitivity analysis, and reliability assessment to expand the scope and technical value of the work.



The work plan is structured as follows:

1. Literature Review and Theoretical Background: Provide an overview of the thermal environment in low Earth orbit (LEO), focusing on radiative and conductive heat transfer mechanisms and the absence of convection. Review the thermal control techniques currently used in small satellites and justify the use of ESATAN-TMS as a modeling platform.

2. Subsystem Description and Mission Requirements: Extensive description of the FZPA and CuPID systems onboard the 3Cat-8 satellite, including their mechanical structure, material properties, and mission thermal requirements. Analyze constraints such as permissible temperature ranges, orientation profiles, and orbital parameters.

3. Geometry and Material Modeling in ESATAN-TMS: Generate or refine CAD geometries, define surface and conductive nodes, and assign thermo-optical properties. Implement contacts and boundary conditions based on each subsystem configuration. Validate the model configuration by comparing it to previously published results.

4. Thermal Case Definition and Simulations: Define representative orbital cases (e.g., total solar exposure, eclipse, beta angle variations). Configure ESATAN sub-cases for steady-state and transient thermal analysis. Generate temperature histories and surface maps for each scenario.

5. Sensitivity Analysis and Design Optimization: Conduct parametric studies on key design variables such as surface coatings, thermal conductance, and component placement. Explore passive thermal strategies, including heat sinks and insulation.

6. Thermomechanical and Reliability Considerations: Introduce a preliminary analysis of thermally induced mechanical stresses and material fatigue due to thermal cycling. Analyze potential test procedures, such as thermal vacuum chamber validation, and compare results with simulations.

7. Results and Evaluation: Compare simulation results of the two sub-systems, identifying thermal extremes and risk areas. Evaluate whether components are within operational temperature margins and suggest design corrective actions if necessary.

8. Conclusions and Future Work: Summarize the results, reflect on the limitations of the current model, and propose improvements, such as integration into a full CubeSat system model, experimental validation, or automated design iterations for future missions.
 
Overview (resum en anglès):
The objective of this project is the realization of the Thermal Analysis of a specific subsystem inside the 3Cat-8 Mission, which is being developed by UPC Nanosat Lab, the Fresnel Zone Plate Antenna (FZPA), whose purpose on the mission is to serve as a technology demonstrator for the use of this type of antennas in remote sensing applications.

The project follows a structured approach that starts with the definition of a theoretical background, in which key variables and role players regarding satellite thermal behavior are described, providing the base knowledge which would fuel technical justifications along the realization of the work.

The methodology regarding the practical aspect of the project involved a proper understanding of the 3Cat-8 architecture, with special emphasis in the treated subsystem, the FZPA, as well as the selection of a suitable thermal analysis software, ESATAN-TMS. The model geometry was simplified via SolidWorks to a Minimum Constraints Topology (MCT), only depicting the critical geometry aspects that played significant roles in thermal behavior. This model was then converted and rebuilt in the ESATAN-TMS, where it was subjected to a meshing process which defined the computational elements' size that would be used during the simulation. The processed geometry was then assigned material bulk and optical properties to the corresponding components.

Simulations were finally ran via defining the conductive interfaces of the resulting model, and specifying orbital parameters fueled by the theoretical background understanding, which resulted in the culmination on radiative simulations and ultimately the expected thermal analysis.

The results met with the expected criteria and made physical sense within the spacecraft's environment. At last, a sensitivity analysis was performed, making special emphasis in the parts more prone to be subjected to thermal fatigue, and appliable thermal control strategies were discussed, ending with an evaluation of the project's environmental, social, and economic sustainability.

Future work expects possible component-specific analysis towards a more defined version of ESATAN-TMS or the realization of an analysis in conjunction with other satellite subsystems.

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