Projecte llegit
Títol: Nanosatellite integration from hardware to FlatSat
Director/a: PARK, HYUK
Departament: FIS
Títol: Nanosatellite integration from hardware to FlatSat
Data inici oferta: 21-01-2019 Data finalització oferta: 08-07-2019
Estudis d'assignació del projecte:
GR ENG SIST AEROESP
| Tipus: Individual | |
| Lloc de realització: EETAC | |
| Nom del segon director/a (UPC): Joan Adrian Ruiz de Azua Ortega | |
| Departament 2n director/a: | |
| Paraules clau: | |
| nanosatellite, CubeSat, CAD, FaltSat | |
| Descripció del contingut i pla d'activitats: | |
| It is for the nanosatellite and cubesatellite integration and
test the functionality. It includes mechanical and electronical integration test based on the instrument and FlatSat platform. |
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| Overview (resum en anglès): | |
| Recent studies have shown that using global navigation satellite system reflectometry
(GNSS-R) and L-band radiometry it is possible to study soil moisture, biomass and cryospher. 3Cat-4 is an educational and scientific mission that combines the two technologies with the aim of demonstrating the potential of nano-satellites for different earth observation (EO) applications. The manufacture of a satellite consists of different phases before it is ready to be launched. First the mission is conceived, then the design of the components and their manufacture and finally their integration. Integration is the phase in which the components of the satellite as a whole are to be verified and assembled in the structure. A correct integration consists of three phases: a software model of the satellite, a FlatSat and finally the assembly of the entire satellite. These three phases have been applied in the practical case of 3Cat-4. The first of the phases is the analysis of the nano-satellite software model, as a CAD. A CAD model is a representation in dimensions and mass of each of the parts that constitute the nano-satellite. This analysis is essential to be able to predict physical collisions between components of different subsystems that would prevent performing the entire satellite assembly. This thesis presents the process used to keep the CAD model up to date. It shows examples of detected collisions that could be overcome before the day of assembly as well as certain nano-satellite pairs that had to be modified to avoid collisions. The next phase is the FlatSat. The FlatSat is based on positioning all the subsystems of the satellite on a table and by means of an interface the software and the interaction between them is tested. In this way the different parts of the satellite can be validated as a whole and you ensure that there will be no interfering errors once the satellite is integrated. The last of the phases is the assembly itself. In this chapter this document explains the different fit checks that have been carried out to verify that there are no collisions between subsystems, as well as the step-by-step procedure to follow and the equipment necessary to perform the assembly. To synthesize, in this thesis it is stated that a CAD model allows you to anticipate physical collisions between subsystems, with a FlatSat you can anticipate problems at software level and all this together with an assembly procedure that has been validated by fit checks ensures a successful satellite integration. |
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