A method for adjusting the orbital path of a satellite to limit a risk of collision with a cloud of space debris (d 1 , d i ), each piece of debris (d 1 , d i ) including a date of closest passage (TCA 1 , TCA i ) with the satellite , the method including the steps of: (a) determining a reference path of the orbit (X ref ) of the satellite from an initial time instant (t 0 ) until the date of closest passage (TCA 1 , TCA i ) furthest from the initial time instant (t 0 ); (b) determining an ephemeris of state transition matrix ( φ (t, t 0 )) representative of the reference path of the orbit (X ref ) of the satellite ; (c) propagating , according to the determined ephemeris of the state transition matrix φ (t, t 0 ), at least one first alternative orbit (X 1i ) of the reference orbit (X ref ) of the satellite according to at least one first avoidance manoeuvre (ΔV. d ) related to the satellite performed during at least one free manoeuvre time slot (Sl 1 ), and from at least one manoeuvre time instant (t_Sl 1 ) of the at least one free manoeuvre time slot (Sl 1 ) until the date of closest passage (TCA i ) furthest from the initial time instant (t 0 ); (d) analytically determining an individual probability (P i ) of collision on each date of closest passage (TCA 1 , TCA i ) for each piece of debris (d 1 , d i ) according to the at least one first alternative orbit (X 1i ) of the satellite ; (e) determining at least one overall probability (P g ) of collision according to all the individual probabilities (P i ) of collision determined according to the at least one first alternative orbit (X 1i ) of the satellite related to the at least one first avoidance manoeuvre (ΔV. d ); (f) selecting at least one first lowest overall probability (P g ) of collision among the at least one overall probability (P g ) obtained according to step (e) ; (h) determining a command (C) of the satellite including at least the first manoeuvre related to the selected first lowest overall probability (P g ) of collision. (a) determining a reference path of the orbit (X ref ) of the satellite from an initial time instant (t 0 ) until the date of closest passage (TCA 1 , TCA i ) furthest from the initial time instant (t 0 ); (b) determining an ephemeris of state transition matrix ( φ (t, t 0 )) representative of the reference path of the orbit (X ref ) of the satellite ; (c) propagating , according to the determined ephemeris of the state transition matrix φ (t, t 0 ), at least one first alternative orbit (X 1i ) of the reference orbit (X ref ) of the satellite according to at least one first avoidance manoeuvre (ΔV. d ) related to the satellite performed during at least one free manoeuvre time slot (Sl 1 ), and from at least one manoeuvre time instant (t_Sl 1 ) of the at least one free manoeuvre time slot (Sl 1 ) until the date of closest passage (TCA i ) furthest from the initial time instant (t 0 ); (d) analytically determining an individual probability (P i ) of collision on each date of closest passage (TCA 1 , TCA i ) for each piece of debris (d 1 , d i ) according to the at least one first alternative orbit (X 1i ) of the satellite ; (e) determining at least one overall probability (P g ) of collision according to all the individual probabilities (P i ) of collision determined according to the at least one first alternative orbit (X 1i ) of the satellite related to the at least one first avoidance manoeuvre (ΔV. d ); (f) selecting at least one first lowest overall probability (P g ) of collision among the at least one overall probability (P g ) obtained according to step (e) ; (h) determining a command (C) of the satellite including at least the first manoeuvre related to the selected first lowest overall probability (P g ) of collision. <EOS>