Abstract: Finite element model of composite wing on unmanned aerial vehicle of a particular type was established based on large-scale commercial software MSC.Patran. Three typical damages including skin delamination, debond between skin, beam and rib and crack on the beam were simulated in the wing. The effects of location and size of damage on vibration performance of wing were analyzed through comparing with the natural vibration frequency of undamaged wing. The results show that the three typical damages cannot induce the change of vibration modals of each order generally, but affect the vibration frequencies of each order. The effects on vibration frequencies of each order are not only concerned with the damage location, but also with the damage degree of major load-carrying structures. When skin delamination or crack on the beam appears in the root segment of the wing, the influence on the vibration frequency of wing is most obvious.