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Projecte llegit

Títol: Implementation and validation of the Attitude and Determination Control System of a pico-satellite

Estudiants que han llegit aquest projecte:

Director/a: PARK, HYUK

Departament: FIS

Títol: Implementation and validation of the Attitude and Determination Control System of a pico-satellite

Data inici oferta: 06-02-2023     Data finalització oferta: 06-10-2023


Estudis d'assignació del projecte:
    GR ENG SIST AEROESP
Tipus: Individual
 
Lloc de realització: EETAC
 
Nom del segon director/a (UPC): Adriano Camps
Departament 2n director/a:
 
Paraules clau:
CubeSat, NanoSat, Space Engineering, Attitude Control
 
Descripció del contingut i pla d'activitats:
Objectives:
This work will be part of a research project of a pico-satellite
developed by NanoSat Lab. There are different subsystems that
work together to achieve the operation of pico-satellites. Among
these subsystems, the ADCS is in charge of controlling the
position of our picosatellite with respect to the earth
This system, object of the study, is based on sensors that will
take the measurements and carry out the control calculations.
In this TFG you will study:
- Development of attitude control algorithms (nadir pointing)
- Development of attitude determination algorithms based on
magnetometers and photodiodes
-Implementation of algorithms in C
- Characterization of photodiodes
-System test on the Helmholt Coils
Methodology:
The method or tool that we will use mainly for this type of
development will be Matlab and its code generator.
Through a simulator of the determination system (where and how I
am oriented) and the control system (what do I have to do to
orient myself as I want). The control is done by means of
magnetic actuators (magnetorquers). The simulator should include
detumbling (if I'm rotating fast and I want to stop) and "nadir
pointing" (satellite pointing towards the surface). It will also
include the effects of different disturbances. Once the control
system has been satisfactorily simulated in Matlab, the
validation will be carried out using a physical model in the
Helmholtz coils (they simulate the Earth's magnetic field) and a
light box (it simulates darkness and sunlight in the space).
During the test campaign, both the determination (magnetic field
readings, gyroscopes and sun-sensors) and the performance
(detumbling and nadir pointing) will be validated at the
SUBSYSTEM level (that is, only the control system, not the entire
satellite).
Expected results:
The expected result will be to contribute to the studies for the
future development of a validated determination and control
algorithm for its implementation at the system level in
PocketQubes, integrated into the satellite software.
 
Overview (resum en anglès):
This end-of-degree project focuses on the software development of a pico-satellite Attitude Determination and Control System, using MATLAB, as well as its subsequent integration in C. The software carried out will be implemented in a 5 cm sided pico-satellite, called PocketQube.
The research project will form part of the IEEE Open PocketQube Kit mission developed in the NanoSat laboratory belonging to the UPC.
The pico-satellite attitude system can be broken down into two distinct branches, attitude determination and attitude control. Attitude determination involves the process of determining the orientation of the satellite using the measurements acquired by its sensors (they include photodiodes, gyroscopes, and magnetometers). On the other hand, attitude control is the process by which the orientation of the pico-satellite is controlled using specific control algorithms (such as detumbling and nadir pointing) and actuators, (such as magnetorquers). To analyse and understand the attitude of the pico-satellite, a model is developed that allows simulating the environment in which the satellite is located. This model encompasses pico-satellite dynamics, a model that describes orbital dynamics, and another that represents the various perturbation forces that affect the pico-satellite. In this way, it is possible to describe the orbit followed by the pico-satellite, including its position, speed and the external forces that influence and affect its behaviour during the orbital flight.
Once the modelling of the simulation environment is complete, the determination and control algorithms are implemented, as well as the mathematical models that describe the behaviour of the sensors and actuators. These algorithms and models are designed with the aim of meeting the requirements established for the Determination and Control System. Subsequently, an exhaustive analysis of the results obtained during the simulation is carried out. The purpose of this analysis is to verify if the previously established requirements for the Attitude Determination and Control System are met.
The conclusion of this work allows to start the test campaigns of this system in the PocketQube hardware, as well as to check if the results obtained in the simulations correspond to reality.

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