CBL - Campus del Baix Llobregat

Projecte llegit

Títol: Solar Panel Options for Small Satellites

Estudiants que han llegit aquest projecte:

Director/a: GUTIÉRREZ CABELLO, JORDI

Departament: FIS

Títol: Solar Panel Options for Small Satellites

Data inici oferta: 22-10-2025     Data finalització oferta: 22-05-2026


Estudis d'assignació del projecte:
    GR ENG SIST AEROESP
Tipus: Individual
 
Lloc de realització: Fora UPC    
 
        Supervisor/a extern: Josep Pino
        Institució/Empresa: Aistech Space
        Titulació del Director/a: Enginyer Electrònic
 
Paraules clau:
Small satellites, solar panels, hinge, deployment mechanism
 
Descripció del contingut i pla d'activitats:
Modern solar panel technology offers a broad array of possibilities in terms of materials, configurations, sizes, and geometries, making it a critical component in the design of small satellite platforms. This Final Degree Thesis is dedicated to the exploration and evaluation of state-of-the-art solar panel solutions tailored for integration with a small satellite bus in the 50-kg class.

The primary objectives of this work are twofold. First, the student will conduct a comprehensive analysis of current commercial off-the-shelf (COTS) solar panel technologies, assessing their performance characteristics, compatibility with space environment conditions, and suitability for deployment on small satellites. Key factors such as power output, efficiency, mass, volume, deployment mechanisms, and integration complexity will be thoroughly examined.

Second, based on the findings from the technology assessment, the student will develop a conceptual design for a solar panel, its hinge and the deployment mechanism optimized for the selected satellite platform. The design will take into account mechanical constraints, reliability, ease of manufacturing, and launch compatibility.

This thesis aims to contribute to the growing field of small satellite engineering by identifying viable solar energy solutions and proposing a functional, compact release mechanism that can support future missions in low Earth orbit (LEO) and beyond.
 
Overview (resum en anglès):
Modern solar panel technology offers a broad array of possibilities in terms of materials, configurations, sizes, and geometries, making it a critical component in the design of small satellite platforms. This Final Degree Thesis presents the exploration and evaluation of state-of-the-art solar panel solutions tailored for integration with a small satellite bus in the 50-kg class.

The primary objectives of this work were addressed through a comprehensive analysis of current commercial off-the-shelf (COTS) solar panel technologies, assessing their performance characteristics, compatibility with space environment conditions, and suitability for deployment on small satellites. Key factors such as power output, efficiency, mass, volume, deployment mechanisms, and integration complexity were thoroughly examined.

Based on the findings from the technology assessment, a conceptual design for a solar panel and its hinge was developed and optimized for the selected satellite platform. The design addresses mechanical constraints, reliability, ease of manufacturing, and launch compatibility.

This thesis contributes to the growing field of small satellite engineering by identifying viable solar energy solutions and proposing a functional, compact release mechanism capable of supporting future missions in low Earth orbit (LEO) and beyond.

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