The invention discloses a supersonic speed aircraft overload instruction rapid tracking method based on a fuzzy variable structure; the method comprises the following steps: measuring an aircraft vertical overload error, a pitch angle speed and a pitch angle acceleration speed; using the vertical overload error signal to design an overload-angle acceleration speed-angle speed mixed sliding mode surface signal s; aiming at the sliding mode surface signal s to build a non-linear sliding mode control quantity [delta]z; building a fuzzy system, and building fuzzy adjusting rules used for controlling gains and parameters; modeling aircraft pitching channel overload control and carrying out digit simulation; determining the final supersonic speed aircraft overload instruction tracking controller parameters based on the fuzzy variable structure, thus allowing the whole aircraft pitching channel overload controller to have satisfactory stability and response speed.