A. DE VITTORI; C. COLOMBO; M. OMODEI; J. LUIS GONZALO; M. MAESTRINI; P. DI LIZIA; P. G. PADRENY; M. TORRAS RIBELL; Á. GALLEGO TORREGO; D. ESCOBAR ANTÓN; R. ARMELLIN
DOI Number: 10.13009/EUCASS2023-061
In this paper an analytical and a semi-analytical technique to compute low thrust Collision Avoidance Manoeuvres (CAMs) are presented and tested against a large dataset of Conjunction Data Messages (CDMs). Such CDMs simulate real conjunctions and they are derived from a screening against a background Two-Line Element population in different orbit scenarios: early Geostationary transfer and insertion into GEO, GEO graveyard, Low Earth Orbit (LEO) to high-LEO transfer, and typical station keeping activities in LEO and GEO. A standard and an improved operational concept are simulated to manage the large uncertainty associated to the long-thrusting arcs present in the different orbit scenarios considered. On all these cases, the Close Approach (CA) is first analysed, in terms of miss distance, relative velocity and position on the b-plane, and the probability of collision at time of close approach. Then, the focus shifts to how CAM influences the displacement in the b-plane, expense for the manoeuvre and efficacy of it. For each of them, different Accepted Collision Probability Level (ACPL) thresholds and conjunction notification times are tested for CAM design. We analyse the convergence of the proposed methods and the capabilities to achieve the required ACPL for a given operational scenano.