Optimization of Spacecraft Formations about Lagrange Points for the Next Generation Space Weather Prediction Mission

<p>This thesis’s work serves as proof of concept for the Next Generation Space Weather Prediction Mission, a multi-spacecraft mission at various libration points whose objective is to forecast Space Weather hazards with a 12day warning time. This thesis deals with the design and control of orbits of spacecraft formations at different libration points. The systems studied are SunEarth, SunVenus, SunMercury, and SunMars. The orbit design and formation keeping control of the spacecraft are solved simultaneously using an optimization software called DIDO. Initial conditions are obtained through two different strategies. The first one, by placing the spacecraft in a tetrahedral formation and using Monte Simulations to find the initial velocities. The second strategy suggests holding velocities fixed while initial locations of the spacecraft are chosen randomly. All results are verified and validated by applying Pontryagin’s principle to the optimal control problem by “hand”, and then comparing the results with the outputs from the optimization software.</p> <p>L4 and L5 points of any systems are the easiest to work with due to their inherent stability. In most cases, the use of the L1norm of control as the cost function yields the lowest station-keeping cost. The culminating remark is that the Next Generation Space Weather Prediction Mission is feasible from an astrodynamics perspective.</p>

Name thesis:degree_name

Master of Science in Aerospace Engineering

Level thesis:degree_level

Thesis - Open Access

Discipline thesis:degree_discipline

Aerospace Engineering

Year

2020

Author dc:creator

• Rangel, Roberto Cuéllar

• spacecraft
• Lagrange points
• space weather
• Aerospace Engineering
• Oceanography and Atmospheric Sciences and Meteorology
• Space Vehicles

Repository record dc:identifier

https://commons.erau.edu/edt/539

OAI identifier oai:identifier

oai:commons.erau.edu:edt-1542