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A method of estimating the service life of carbon-fibre composite wing spar is presented. Firstly by the finite element analysis of UAV in static balance, the area of stress concentration to carbon-fibre composite airfoil is acquired. Aiming at the droner flight parameters which is collected from feeder links to earth, the angle of attack and side slip angle can be deduced on the equivalent circuit of the linear induction motor through reasonable assumption, then the weight overload spectrum in dynamic load is inversed by kinetic and the dynamic load about airfoil is drew up in any flight profile. Static and fatigue test is carried out by carbon-fibre composite wing spar and then got the S-N curves. Finally, aiming at Miner theory, the life assessment of wing spar in UAV has been finished. The method aiming at the droner' flight parameters draws up the dynamic load of wing spar, it is convenient and suitable for acquiring dynamic load of UAV in small and medium size.