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Títol: Structural Validation and Antenna Deployment Mechanisms Design for the PoCat-LEKTRON PocketQube

Estudiants que han llegit aquest projecte:

Director/a: PARK, HYUK

Departament: FIS

Títol: Structural Validation and Antenna Deployment Mechanisms Design for the PoCat-LEKTRON PocketQube

Data inici oferta: 03-02-2026     Data finalització oferta: 03-10-2026


Estudis d'assignació del projecte:
    GR ENG SIST AEROESP
Tipus: Individual
 
Lloc de realització: EETAC
 
Segon director/a extern: Roger Almirall
 
Paraules clau:
Satellite, NanoSat Lab, PocketQube, Antenna, COMMS, L-Band, Structural, ANSYS, FEA, Vibration, Fundamental Frequency
 
Descripció del contingut i pla d'activitats:
1. Project Objectives
1.1. General Objective
To perform a structural analysis of a PocketQube through Finite Element Analysis and experimental
vibration testing, and to design and verify two new antenna deployment systems, from L-Band and
COMMS.
1.2. Specific Objectives
A. Structural Validation:
' FEA Simulation: Perform Modal, Quasi-static, Random Vibration, and Shock analysis on the
current design.
' Experimental Correlation: Perform a Shaker Test to validate the integrity of the design and
correlate the natural frequencies with the simulation.
B. Mechanism Design:
' L-Band Antenna: Design a completely new deployment mechanism in compliance with ESA's
requirements.
' Comms Antenna: Design a reliable deployment solution ensuring compatibility with the
updated structural requirements.
C. Verification of Mechanisms:
' Verify the structural viability of the new mechanisms via simulation.
' Ensure no mechanical interference occurs between the existing model and the new antenna
modules.
2. Methodology
The project is divided into two parallel workflows: Validation of structure and Design of the antennas.
1. Baseline Review: Analysis of the provided PocketQube CAD model and definition of launch
loads (ESA's requirements).
2. Structural:

' Pre-Test Analysis: Running FEA simulations on Ansys on the existing model to
predict mode shapes and stress points.
' Testing: Performing a Sine Sweep and Random Vibration test on a shaker to extract
real eigenmodes and check for possible structural failure.
' Correlation: Observe if there is a match in experimental data.
3. Design:
' Concept Generation: Proposing mechanisms for L-Band and Comms that fit within
the remaining volume of the validated chassis.
' Detailed CAD: Modeling the new deployment systems in SolidWorks.
' Virtual Validation: Simulating the deployed stiffness and ensuring the mechanisms
can survive the launch loads.
3. Detailed Scope of Analyses
3.1. Chassis Structural Analysis & Testing
Since the design exists, the focus is on verification:
' Modal Analysis: Identify fundamental frequencies. The Shaker test will confirm if the real
structure meets the >100 Hz requirement.
' Random Vibration: Simulate the PSD curve in Ansys. Expose the prototype to random
vibration to check for screw loosening or fatigue.
' Shock Analysis: Numerical evaluation of the chassis response to separation shock.
3.2. Antenna Deployment Design (L-Band & Comms)
The original antennas are being replaced. The new design process involves:
' Volumetric Feasibility: Ensuring the new folded antennas follow ESA's requirements.
' Mechanism Design: Selection of elements such as screws, springs, resistor for burning, etc.
4. Tools and Software
' CAD: SolidWorks.
' FEA: Ansys Workbench.
' Experimental: UPC Nanosatlab's Shaker.
' Documentation: LaTeX.
5. Time Planification
' January: Conceptual design of new antennas and familiarisation with Tools (done).
' February: Start of detailed CAD for new antennas. Creation of the model and check
requirements for structural.
' March: Experimental Shaker Test. And first structural simulation.
' April: Correlation of FEA vs. Test data. Completion of Antenna CAD.
' May: Integration of new antennas into the correlated model. Analysis of final refined results
structural.
' June: Documentation and finish thesis writing.
 
Overview (resum en anglès):
This thesis addresses two open problems for the PoCat LEKTRON mission, developed at the UPC NanoSat Lab within the ESA Fly Your Satellite! programme: the structural verification of the satellite chassis, and the design of two redundant deployment mechanisms for its COMMS tape antenna and L-Band helical payload.
A finite element model of the chassis was built in Ansys Mechanical. Two model simplifications - small-feature removal and component mass smearing - were independently validated through sensitivity studies before being applied globally. Modal, random vibration, sinusoidal, and quasi-static analyses were performed against the ESA AIV-ENV requirements. The stowed satellite exhibits a fundamental frequency of 701.11 Hz, a sevenfold margin over the 100 Hz launcher-coupling requirement, and positive safety margins across all load cases, with the structural fasteners identified as the design's limiting component (MoS = +9.6% under random vibration).
Both antenna deployment mechanisms rely on a non-pyrotechnic, redundant thermal-knife architecture severing a pre-tensioned Dyneema retention line. The COMMS mechanism was redesigned following an ESA preliminary design review that identified an unprotected external cable routing as a premature-severance risk, the revised architecture routes the line entirely through an internal kinematic path. The L-Band mechanism required a three-dimensional routing strategy to pass surface constraints while resisting the axial compressive load of its helical spring actuator. Complete assembly, integration, and verification procedures were defined for both mechanisms and for the chassis vibration test campaign.
The results demonstrate that a qualified, redundant, and low-cost deployment architecture is achievable within the constraints of a 1P PocketQube, providing a validated baseline for the mission's upcoming physical test campaign.

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