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Projecte llegit

Títol: Study of Material Behavior in Space and Thermal Analysis of a Space-Exposed Structure

Estudiants que han llegit aquest projecte:

Director/a: PARK, HYUK

Departament: FIS

Títol: Study of Material Behavior in Space and Thermal Analysis of a Space-Exposed Structure

Data inici oferta: 03-02-2025     Data finalització oferta: 03-10-2025


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:
Satellite, Space Environment, Thermal Control
 
Descripció del contingut i pla d'activitats:
Study of Material Behavior in Space and Thermal Analysis of a Space-Exposed Structure
Objectives:

This project aims to analyze the behavior of materials in space environments and assess the thermal performance of a designed structure under space conditions. The study is divided into two parts:
Theoretical Study:
Investigate how space conditions (vacuum, temperature variations, radiation, and microgravity) affect materials.Review commonly used materials in space applications and their degradation mechanisms.Identify suitable materials for structures exposed to space conditions.

Practical Analysis:
Design a simple space-exposed structure using SolidWorks.Conduct a thermal analysis using finite element analysis (FEA) tools to simulate extreme temperature conditions in space.Evaluate whether the structure can withstand temperature variations and suggest possible improvements.

Methodology

Literature Review:
Study scientific papers and space agency reports (NASA, ESA) on material performance in space.Identify key factors affecting material selection for spacecraft and satellites.Material Analysis:
Compare different materials based on their thermal expansion, conductivity, radiation resistance, and mechanical properties.Select a set of materials for the practical study.Structural Design & Simulation:
Model a simple structure in SolidWorks, considering real-world space applications.Perform thermal FEA simulations using software like ANSYS or SolidWorks Simulation to analyze heat transfer and deformation under space temperature cycles.Evaluation & Conclusion:
Interpret the simulation results to determine whether the selected materials can survive space conditions.Propose improvements in design or material selection.

Expected Results

A comprehensive understanding of material behavior in space, including thermal expansion, radiation resistance, and durability.A simulated thermal analysis of a designed structure under extreme space conditions, identifying potential material failures.

Recommendations for improving the design and material selection for future space applications.This project will provide valuable insights into space material science and thermal engineering, contributing to aerospace structural design studies.
 
Overview (resum en anglès):
The main objective of this project is to study the thermal behavior of a subsystem that is related with a real space mission developed by the NanoSat Lab at the Universitat Politècnica de Catalunya. The analyzed component is the FZPA deployable antenna, that is in the 3Cat-8 cubesat system, designed to operate in Low Earth Orbit (LEO). Since it presents a mechanical and electronic nature, the thermal performance of this subsystem can directly affect its functionality in a space environment that presents extreme radiation and temperature conditions. Therefore, this study aims to explore if its thermal response remains within operational limits throughout the complete orbital cycle.
The used methodology follows a structured approach, starting with the CAD geometry preparation using SolidWorks, followed by the definition of physical and optical properties of materials using Excel, and finishing with a finite element thermal simulation using Siemens NX. This workflow included geometry simplification, creation of equivalent materials, and application of realistic boundary conditions such as heat flux, radiation to deep space, and internal heat generation. To provide a response, two key orbital conditions were simulated, on one hand direct sunlight exposure and on the other hand eclipse, in both transient environments. Finally, a simplified outer structure representing the actual satellite enclosure was incorporated to improve the realism of the global thermal exchange.
The results show that the antenna experiences significant temperature gradients between the different subcases, especially in more exposed or poorly insulated areas, such as the fiberglass telescopic arms. Meanwhile, internal components such as the PCB boards have good thermal inertia due to their position and material properties. The addition of the outer box allowed for a more accurate simulation of shielding and conduction effects, improving the results precision. In addition, in order to validate Siemens NX as a perfect thermal simulation tool within the lab, this project has established an adaptable procedure applicable to future analysis.

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