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 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 of the satellite including at least the first manoeuvre related to the selected first lowest overall probability (P g) of collision.