The Starfixers project addresses the urgent challenge of space debris mitigation in Low Earth Orbit (LEO), where inactive satellites from mega-constellations such as Starlink threaten sustainable space operations. Our mission is to design a cost-effective and environmentally responsible Active Debris Removal (ADR) spacecraft capable of de-orbiting at least ten failed satellites within one year.
The selected removal method employs plume impingement: a novel, contactless technique in which high-momentum gas jets are directed at target satellites to induce controlled trajectory changes. This avoids complex capture mechanisms and enables re-entry without requiring physical contact. The mission architecture ensures each target is individually approached and guided toward a controlled re-entry trajectory, before the "shepherd" spacecraft returns to the initial orbit for the next operation. The complete mission concept involves performing numerous controlled approach manoeuvres with each target debris gradually changing its trajectory using a custom-developed momentum transfer and transfer efficiency simulations until the debris reaches an elliptical orbit with a 381km perigee. At its final orbit the debris passively de-orbits within 7.5 months. The developed strategy is proven to be viable for debris ranging from 250- 500 kg and altitudes of 550-630 km. However, the detailed subsystem design is performed for 10 Starlink v1 satellites at 600 km circular orbit as this scenario was deemed most common for an ADR mission considering the abundance of Starlink. The mission is scheduled for deployment in January 2030 and is designed to stay within a 100 million total budget, covering all subsystem development, testing, and launch operations.
Subsystems have been developed in detail: the propulsion subsystem uses bi-propellant thrusters on a two-axis gimbal for precise plume control; the GNC and ADCS subsystems combine LIDAR, IR cameras, reaction wheels, and IMUs for autonomous attitude control, tracking, and detumbling. Power is provided by solar arrays and lithium-ion batteries to operate in the eclipse. Communication is handled via the ESA Estrack network, and all systems are designed for modularity and sustainability. During the final weeks of the DSE exercise, the team will finalise all subsystem designs, refine the plume-based and orbital targeting control algorithms, and integrate all components into a fully verified and validated spacecraft configuration.