The unmanned aerial vehicle with folding wing can serve in multiple mission profiles，the flight environment is complex and susceptible to low-altitude gusts. A new parameterized aeroelastic model with non-intrusive characteristics was developed to quickly calculate discrete gust response cha-racteristics of Z-shaped folding wing at different folding angles. Firstly，structural and aerodynamic enhancement design was made to the existing Z-shaped folding wing. Secondly，based on the Nastran input file for the flutter calculation of the folded wing in the extended state，the parameterized aeroelastic model under any folding angle was reconstructed. Finally，the effects of parameters such as folding angle，flight speed，gust velocity amplitude and hinge damping between different wing segments on the gust response characteristics of the folding wing were examined. The results show that increasing folding angles can effectively alleviate the gust responses， the increase in flight speed and gust velocity amplitude significantly contributes to the responses of wing tip acceleration and wing root bending moment， the presence of hinge-damping parameters can alleviate the acceleration response of the wing tip，but it also increases the bending moment response of the wing root.