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The Aircraft Center of Gravity Change has influence on the aerodynamic force of the aircraft and produce strong disturbance errors. An adaptive backstepping control method is used to eliminate the influence of the disturbance errors on flight control. Firstly, a non-linear model of aircraft gravity center position and weight change is established. Then an adaptive Backstepping control law is designed to estimate the model error adaptively. Aiming at the fact that the longitudinal control moment of F16 aircraft is not an affine non-linear form, the Newton's method is used to solve the problem. Finally, the simulation verification under normal conditions, sudden change of gravity center and gradual change of gravity center is carried out. The simulation results show that the adaptive backstepping control law designed has good dynamic and steady-state performance.