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dc.contributorSoria Guerrero, Manel
dc.contributorRuiz De Azúa Ortega, Juan Adrián
dc.contributor.authorMatabosch Montobbio, Xavier
dc.contributor.otherUniversitat Politècnica de Catalunya. Departament de Física
dc.date.accessioned2020-05-22T12:08:19Z
dc.date.issued2018-09
dc.identifier.urihttp://hdl.handle.net/2117/188671
dc.descriptionIntroduction This TFM is involved in the ³Cat-4 project from the Nano-Satellite and Payload Laboratory. This project aims at designing, implementing, testing, and operating a 1U CubeSat for Earth Observation. This project is also involved in the Fly Your Satellite! II program of the ESA Academy.-Understand the thermal balance of a CubeSat in LEO (conduction, thermal contact resistance, PCB anisotropy, transient heat generation, short wave and long wave radiation, Earth albedo and long wave emission, etc). -Develop a numerical model of a CubeSat. Implement it in Matlab and validate it. -Implement a CubeSat thermal model in ThermalDesktop. -Compare both models. -Highlight the thermal particularities of the ³Cat-4 spacecraft.
dc.description.abstractThermal control is one of the most critical parts in the design of a satellite. Indeed, the Thermal Control System(TCS) provides the spacecraft with the necessary means to survive in the extreme space environment conditions. This task becomes specially challenging when the requirements of a nanosatellite are added. The need of a thermal control system mainly based on passive mechanisms make thermal analysis and the development of an accurate thermal model key aspects to make the correct design decisions. In this work, the1U CubeSat3Cat-4 thermal control system has been designed and analyzed. Thermal models have been built and successfully simulated initially with MATLAB and later with Thermal Desktop in more precise models.The thermal analyses have been used to determine the outer coating of the spacecraft and the painting of the internal PCBs. The results from the simulations, however, showed that the available passive mechanisms are insufficient to meet all temperature requirements. Using the heater placed in the EPS the results during the worst cold cases improved by leaving only the COMMS/AOCS subsystems board out of design temperatures. During the worst hot case, the batteries in the EPS showed to exceed their upper temperature limit.Actions have been proposed to improve the thermal model and eventually update the TCS design.
dc.language.isoeng
dc.publisherUniversitat Politècnica de Catalunya
dc.subjectÀrees temàtiques de la UPC::Física::Astronomia i astrofísica
dc.subject.lcshArtificial satellites
dc.subject.lcshTemperature control
dc.titleStudy: CubeSat thermal control system design and analysis
dc.typeMaster thesis
dc.subject.lemacSatèl·lits artificials
dc.subject.lemacTemperatura -- Control
dc.identifier.slug205-1687
dc.rights.accessRestricted access - author's decision
dc.date.lift10000-01-01
dc.date.updated2019-10-24T11:03:09Z
dc.audience.educationlevelMàster
dc.audience.mediatorEscola Superior d'Enginyeries Industrial, Aeroespacial i Audiovisual de Terrassa
dc.audience.degreeMÀSTER UNIVERSITARI EN ENGINYERIA AERONÀUTICA (Pla 2014)


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