During the lifetime of a satellite, the evaluation of the number of imminent events and avoidance manoeuvresrequires the knowledge of the object propagation that can cause conjunction events. Determination of a suitableavoidance manoeuvre includes the estimation of a delta-V, one constraint and the cost function. This paper is topresent a satellite collision avoidance strategy for a spacecraft in order to perform an appropriate manoeuvre to avoidcollision with another spacecraft or space debris taking into account of propellant fuel reduction. As a case study, thepossible collision avoidance manoeuvre of the controllable Irridium33 satellite to avoid colliding whit Russiannonoperational Cosmos2251 satellite is described. In order to determine the collision risk level, crucial closestapproaches have to be detected and this process is performed based on the TLEs and SGP4 propagation model. Inthis paper, the best closest distance between the two satellites was predicted at about 1.6 km. Then the probability ofcollision is computed, and finally the possible collision avoidance manoeuvre to move Irridium33 satellite awayfrom Cosmos2251 satellite and is evaluated and the results are discussed.
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