Abstract: The dynamic response of morphing aircraft in the wing morphing process was simulated, and the additional forces and moments induced by wing morphing were analyzed. The result would be taken as reference for flight control of morphing aircraft. Based on Newton-Euler equations, the extended motion equations suitable for morphing aircraft were developed, in which 4 additional forces and moments were added due to the wing morphing. Vortex lattice method was used to find out the aerodynamic properties of variable wing configurations. The modeling and simulation methodology was applied to M-wing aircraft, and the dynamic response of the aircraft was analyzed with the wing changes symmetrically or asymmetrically. The result shows that the aircraft was affected significantly by the additional forces and moments.