GNC architecture for the e.Deorbit mission

Abstract

The GNC architecture presented in this paper has been developed in the frame of e.Deorbit phase B1. The architecture is dedicated to approach and capture the uncooperative target satellite Envisat, comprising ascent from launch orbit to the target orbit, rendezvous with the target satellite, capture and stabilisation of the coupled system and de-orbiting. The homing and closing trajectories are based on e/i separation allowing a passively safe approach until the proximity operations begin. The chaser has to synchronise its motion with the target due to its large dimensions. The safety monitoring concept is briefly discussed. The propellant budget and the GNC performance requirements are consolidated by Monte Carlo simulations.