Aldric Parent

TYPE

Academic Project

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CONTEXT

Space system specialization

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YEAR

2025

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DURATION

1 month

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LOCATION

Paris, FRANCE

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LINK

ProjeCT DETAILS

Context and Objectives

During September 2025, I completed an advanced astrodynamics laboratory project within the Master’s program in Space Tools and Systems at the Paris Observatory - PSL. This practical work focused on the detailed analysis and simulation of METEOSAT 9’s geostationary orbit insertion using PSIMU software developed by CNES. The main objective was to determine the ΔV budget required for the satellite’s transition from the Geostationary Transfer Orbit (GTO) to its final operational circular orbit, while accounting for fuel tank constraints and propellant management limitations

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PROJECT DETAILS

Methodological Approach

The project combined orbital mechanics theory with specialized space mission design software to simulate the complete orbital insertion sequence. My approach integrated three complementary methodologies: precise characterization of the initial GTO orbit based on Ariane 5 user manual specifications, theoretical calculation and simulation of circularization and radial correction maneuvers, and analysis of fuel management constraints related to the satellite’s four spherical propellant tanks. The work required mastering PSIMU’s complex parameter configuration for satellite modeling (mass distribution, propulsion systems, tank architecture) and implementing a multi-phase maneuver strategy to respect the 244 kg capacity limitation of each fuel tank

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PROJECT DETAILS

Work Completed

GTO characterization and initial setup : Configured METEOSAT 9’s detailed specifications in PSIMU, established the standard Ariane 5 GTO parameters (250 km perigee, 35,943 km apogee, 6° inclination), and implemented the TNW coordinate system for optimal maneuver calculations.
Circularization maneuver analysis : Calculated the primary ΔV requirement of 1,477.6 m/s for orbit circularization at GTO apogee, validated theoretical calculations against manufacturer specifications (83% of total propellant for orbit insertion, yielding 1,574 m/s via Tsiolkovsky equation), and segmented the maneuver into four sequential phases to accommodate individual tank limitations.
Orbital corrections and final positioning : Identified a 313 km altitude discrepancy after initial circularization, implemented strategic longitude drift exploitation to reach the operational position at 45.5°E longitude before executing radial corrections, and performed two-phase orbital radius correction (11.4 m/s total ΔV) achieving final precision within 2 km of target altitude.

PROJECT DETAILS

Skills Developed

Technical/Scientific : Advanced orbital mechanics modeling using industry-standard software (PSIMU), comprehensive understanding of geostationary orbit insertion sequences and multi-phase maneuver strategies, satellite propulsion system analysis including fuel tank management and ΔV budget optimization.
Computational : Python programming for trajectory visualization and data analysis from PSIMU outputs, numerical optimization and constraint handling for complex orbital mechanics problems, interpretation of orbital elements and ephemeris data for mission planning applications.
Methodological & Soft Skills : Critical analysis of space mission design trade-offs between maneuver capability and operational autonomy, autonomous project management balancing theoretical calculations with practical simulation constraints, technical documentation and results presentation for aerospace engineering applications.

PROJECT DETAILS

Personal Assessment and Perspectives

This astrodynamics laboratory provided invaluable hands-on experience with professional space mission design tools and methodologies used in the European space industry. The project successfully bridged theoretical orbital mechanics concepts with practical engineering constraints, demonstrating the precision and complexity required for successful geostationary satellite operations. The experience reinforced my interest in space systems engineering and provided concrete foundations for advanced studies in spacecraft mission design and orbital dynamics applications.

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