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Projecte llegit

Títol: Small Satellite Mission Analysis and its principal subsystems


Estudiants que han llegit aquest projecte:


Director/a: PARK, HYUK

Departament: FIS

Títol: Small Satellite Mission Analysis and its principal subsystems

Data inici oferta: 18-01-2019     Data finalització oferta: 18-09-2019



Estudis d'assignació del projecte:
    GR ENG SIST AEROESP
Tipus: Individual
 
Lloc de realització: EETAC
 
Nom del segon director/a (UPC): Jordi Castellvi
Departament 2n director/a:
 
Paraules clau:
Satellite, mission analysis, simulation
 
Descripció del contingut i pla d'activitats:
Nowadays the number of satellites in orbit performing space
missions is increasing due to the useful applications and
advantages that they can bring us. A space mission has a very
high difficulty as it is composed of lots of subsystems and all
of them have to work properly and in the most efficient way
during launch and in the space environment. Furthermore,
putting a satellite into orbit and the technology used to build
it are very expensive.
Therefore, in order to ensure safety and reduce the risk of the
mission, tests and simulations must be performed and analysed
to improve and adjust as much as possible the satellite system.
The idea of this thesis is to perform and improve a software
simulating an Earth Observation Mission with Small Satellite,
that takes into account the different main subsystems of the
satellite and studies its behaviour in the space environment
conditions in order to obtain a simulation as close as possible
to the real mission.
The simulation software developed will be a very useful tool
for companies to test the parameters of their own products and
see the viability of the mission before performing any
experiment or test and in this way, safe large quantities of
money and time.
The principal subsystems of the satellite that could be
developed are the power system, thermal system, data budget,
communication system and payload. Also, many different
important concepts about a space mission and space environment
can be investigated: duty cycle, revisit time, access time,
eclipses of the satellite depending on its orbit, types of
payloads and orbital propagators.
 
Overview (resum en anglès):
The aim of this final degree project is to study and improve an existing satellite mission
simulator software developed using Matlab for Earth observation purposes.
Firstly, the characteristics and structure of the existing software is analyzed so that everything
is properly understood in order to define appropriate improvements.
These improvements are applied to the orbital propagator, the different subsystems of the
satellite (power, thermal, data ...), its modes and other important concepts about a satellite
mission, so that the simulator is as much approximated as possible to the scenario of a
real mission.
Once the software improvements are implemented and validated a final satellite mission
analysis example is elaborated. This mission consists in observing a geographical zone of
the Earth with a real objective and constraints...
Finally, the result of the project is a GUIDE application from the Matlab software so that
satellite mission analysis simulations can be programmed and studied from it. By analyzing
the mission objectives and constraints, the user can try different satellite designs, orbits,
modes, ground stations... and realize a comparison between them to obtain the best
possible result to achieve their objectives.
The methodology used to develop the project is, firstly to develop a study of space mission
typical parameters and concepts related to satellites from books and research papers so
that a big theoretical background is achieved. With this knowledge acquisition, the existing
software can be understand and improved by implementing them to the Matlab Software
in the best possible way.
The validation of this project is done by comparing the results of every new implementation,
by itself and on the whole, with the first version of the simulator and with the theoretical
background studied to check its reliability.


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