A Scalable, Modular Flight Dynamics System for Heterogeneous Constellations with Electric Propulsion

CUCCHIETTI V. 1, JOLLY G. 1, JOURNOT M. 1, DEBOUT V. 1

1 CS Group, Toulouse, France

Current commercial missions aim to deploy constellations of a few to numerous, potentially heterogeneous satellites over extended timeframes, driving a growing need for scalable and generic flight-dynamics solutions. Additionally, these platforms increasingly rely on electric propulsion, which is significantly more complex than traditional chemical systems and often demands advanced algorithms that new mission operators may not yet have.

By contrast, FDS has traditionally been designed, developed, and maintained for a single mission, resulting in long development cycles, higher costs, and extensive validation effort. Because FDS systems are critical for operating active satellites, any failure can disrupt upcoming ground-station passes and jeopardize essential maneuver-upload opportunities.

To address these challenges and building on the experience CS Group gained from ANGELS and previous FDS developments, CS Group has created a modular, generic Flight Dynamics (OREFLIDS). OREFLIDS uses the open-source Orekit library as its core and provides primary flight-dynamics services such as orbit propagation and orbit determination. It also includes advanced algorithms for planning low-thrust station-keeping maneuvers, orbital transfers, and collision-avoidance actions under operational constraints. Implemented in a containerized, cloud-native environment and orchestrated through Kubernetes, OREFLIDS enables the seamless integration of mission-specific algorithms with minimal development effort, while providing high availability, redundancy, and scalability.

OREFLIDS is therefore well suited for multiple satellite platforms and large constellations. It has demonstrated its robustness during the ADRAS-J mission and is currently supporting another mission involving deorbiting with a very low-thrust (< 1 mN) , while meeting strict operational constraints such as per-orbit thrust-time limits and attitude restrictions. Its advanced orbit-transfer algorithm is used to generate the deorbiting maneuver plan spanning several months, further validating the FDS maturity and operational readiness.