The invention relates to a dynamic modeling and stability control method for a folding wing aircraft, which comprises the following steps: firstly, an aircraft with folding wings is taken as a multi-rigid-
body system, and a multi-rigid-body dynamic model of the aircraft is established; secondly, the function relation between aerodynamic parameters and folding angles in the wing folding process iscalculated; thirdly, decoupling is conducted according to the decoupling conditions in combination with a
kinematics equation, a dynamics equation and a navigation equation of the aircraft, a longitudinal motion equation of the aircraft is obtained, and dynamic characteristics of the aircraft are analyzed; finally, a nonlinear term, a
coupling term and a parameter time-varying term existing in theaircraft longitudinal nonlinear
kinetic model are regarded as total disturbance inside and outside the
system, real-
time estimation and compensation are conducted on the total disturbance, a PD controller is designed for the compensated
system, and decoupling control over a speed channel and a height channel is achieved. According to the method, the modeling process is simplified, and derivationof rotational
inertia is avoided; the controller is strong in anti-interference capability, high in control precision and suitable for deformation stability control of various variant aircrafts.