Cataloging objects from INTELSAT 33E fragmentation using optical sensors
As the number of objects in orbit continues to grow, space surveillance is becoming increasingly important for the space sector. This growth heightens the need for collision avoidance and raises the risk of fragmentation. In 2024, two significant events occurred in geostationary orbit, a critical region for military and telecommunications missions. These events were fragmentations: the first happened in early September and involved a Rocket Body (Atlas V Centaur). The second involved Intelsat 33E in October, a telecommunications satellite, due to a power loss issue. The resulting debris poses significant challenges for the space environment, as objects in geostationary orbit (GEO) remain in place indefinitely.
For space activities, cataloging as much debris as possible is essential to ensure the safety and sustainability of satellites. However, due to a lack of information about this event—such as the size of the debris cloud and the number of objects—it was difficult to assess the full extent of the issue.
This paper presents how the French project 'OSMOSE', managed by CNES (Centre National d'Etudes Spatiales) and operated by CS Group, successfully programmed observations, cataloged objects, and determined orbits. We begin by discussing the actions taken on the day of the event, including analyzing images from three French optical sensors and detecting objects. Next, we describe the strategy for the following days, which involved tracking the main body or its remnants and the fragmentation point, while propagating the orbits of Intelsat before the event. Subsequently, each day focused on analyzing images to detect new objects for cataloging and ensuring continuous tracking to better understand their trajectories. Additionally, efforts were made to determine whether the new objects were part of the fragmentation. Due to the challenges in understanding the physics of these objects, some parameters of the orbit determination algorithm—such as running orbit determination on a 30-day rolling window for the measurement arc—were adjusted to improve knowledge of the objects (mass, volume, solar radiation pressure coefficient, etc.)