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Projecte matriculat

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

Director/a: PARK, HYUK

Departament: FIS

Títol: Thermal Modeling and Analysis of CubeSat Subsystems Using ESATAN-TMS: Integration of FZPA and CuPID 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
 
Nom del segon director/a (UPC): Ksenia Osipova
Departament 2n director/a:
 
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.
 
Orientació a l'estudiant:
 
 
 
Horari d'atenció a estudiants per a l'assignació de projecte:

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