Alan Soto
Alan Soto
Aerospace Engineer | Engineering Physicist
[MATLAB] [Orbital Mechanics] [ADCS] [STK] [Flight Dynamics] [GNC]
[Mathematical Modelling] [Simulation] [Propagation Models]
Embedded Files
(UPAEP | NASA | AEM)
(UPAEP | NASA | AEM)
[MATLAB] [ADCS] [Control] [CubeSat] [TLE] [J2 Orbit Propagator] [4th Order Runge-Kutta] [Ground Track] [Quaternions] [Gravity Gradient] [IGRF Geomagnetic Field Model] [B-dot Algorithm] [Sensor Modelling] [Magnetorquer] [Gyroscope] [NASA Systems Engineering Handbook]
Project Description:
AzTechSat-1 was a 1U CubeSat developed by the Universidad Popular Autónoma del Estado de Puebla (UPAEP) in collaboration with NASA and Mexico's Space Agency (AEM) with the objective of demonstrating inter-satellite communications between the CubeSat and an existing network of telecommunications satellites. More info:
https://www.nasa.gov/centers-and-facilities/ames/what-is-aztechsat-1/
My Role:
I was the student leader of the Attitude Determination and Control Subsystem (ADCS). Our main objective was to model the satellite's attitude to identify the optimal fligth configuration that maximized the CubeSat's antenna pointing towards the telecommunications network and the integration of a detumbling maneuver to reduce its angular velocity as required. These goals where achieved through a MATLAB simulation that incorporated a J2 orbit propagation model from the ISS TLE, the IGRF geo-magnetic field model, a b-dot controller for detumbling and an axis-bias control mode for pointing towards the satellite network.
(Independent Initiative)
(Independent Initiative)
[Mission Analysis] [Ansys Systems Tool Kit (STK)] [Orbit Propagation] [STK Coverage] [Coverage Analysis] [Hyperspectral Remote Sensing] [Age of Data Analysis] [Sensor Modelling]
Project Description:
NSATMX-ER1 was a collaborative effort by representatives of multiple academic institutions in Mexico with the main objective of developing a payload to be installed in the BARTOLOMEO platform on board of the ISS. The payload was to be conformed by an hyperspectral camera that would cover the national territory to identify potential areas for the implementation of renewable energy sources.
My Role:
My main task was as a mission analyst and a supporting member of the communications subsystem. I was responsible for creating the scenario and propagating the orbit of the ISS using STK, along with modeling the integration of the camera to identify the optimal pointing angle according to the expected coverage of the focus area and the age-of-data requirements of the mission. I also worked on the initial release of the objectives, constraints and requirements (OCR) document for the COMMS subsystem.
[In Progress] [MATLAB] [CR3BP] [Synodic & Sidereal Reference Frames] [Lagrange Points] [Trojan Asteroids] [Interplanetary Trajectories] [Python]
Project Description:
The circular restricted three-body problem (CR3BP) is a simplification of the three-body problem where two masses (m1 and m2) rotate around their center of mass as a result of the interaction between their mutual gravitational attraction forces. A third body (m3) is introduced to the system and is affected by the attraction forces of the main two, but does not influence them. The CR3PB has been historically used in space missions design to represent complex systems such as the Earth-Moon, Sun-Jupiter, Jupiter-Ganymede and Jupiter-Europe.
The final objective of this project is to use support vector machines (SVM) to classify orbits in one CR3BP as either stable (remain within the system) or transit (escape the system) to identify possible transition trajectories that allow an m3 object to transition between one system to another.
My Role:
I'm the main researcher of this project. My work so far has focused in understanding the definitions, implications and limitations of the CR3BP along with its more common definitions in both the synodic (rotating) and sidereal (fixed) unitless coordinate systems. The CR3BP has been successfully solved numerically with MATLAB and the following steps will utilize this model to create a comprehensive dataset that can be used to train an SVM to classify the orbits as either stable or transit based only in the initial vector state definition of m3.
(Mexico's LX National Congress of Physics)
(Mexico's LX National Congress of Physics)
[MATLAB] [GUI] [Orbital Mechanics] [Rocket Launch] [Mass-variable Systems] [Systems of Differential Equations] [Non-inertial Reference Frames] [Apogee Manoeuvre] [Orbit Propagation] [Perifocal Coordinate System] [Orbital Elements] [Lagrange Coefficients] [Hohmann Transfer]
Project Description:
Using a classical mechanics approach, the positioning of a 1U CubeSat was analyzed through a MATLAB simulation of the launch of a multi-stage rocket (mass-variable system), followed by the calculation of an apogee kick and a set of orbit propagations for the determination of a parking, transfer, and final orbits defined by their orbital elements in the perifocal coordinate system. Orbits were propagated by the Lagrange Coefficients algorithm from Curtis, H. D. (2013) "Orbital mechanics for engineering students" and orbit transitions were acheived through Hohmann transfers . At the final stage, a simplified simulation of the satellite’s attitude was added, along with the integration of all the stages into a graphical user interface.
My Role:
I was part of the research team from the early stages of the project until its final presentation at the Mexico's LX National Congress of Physics. My main focus was on the integration of the mathematical models to MATLAB and their validation with both numerical and visualization tools.
Page updated
Google Sites
Report abuse