To solve the problem of severe matching/non-matching uncertainty of hypersonic vehicles in the process of climbing

a new adaptive super-twisting sliding mode control method was proposed to suppress the matching uncertainty of the ascent phase

and the method was combined with a sliding mode differentiator to resolve the non-matching uncertainty of the ascent phase. Firstly

the sliding mode differentiator was used to estimate the derivatives of the velocity and height in the feedback linearization model to narrow the gap between the feedback linearization model and the original model. Secondly

on the basis of the traditional super-twisting sliding mode

a linear term was added to increase the convergence speed. Then

the discontinuous symbolic functions in integral terms were made continuous to ensure the smoothness of the control input

which eliminated or attenuated the chattering to a greater extent. Lastly

since the upper bound of the composite disturbance was unknown

an adaptive law was designed to ensure that the parameters were not overestimated and the initial value could be chosen to ensure the convergence speed. Simulation results show that the improved control method can meet the control requirements

and compared with the traditional super-twisting sliding mode control algorithm

the improved control method had smoother control input and faster convergence speed

which verifies the effectiveness and advancement of the proposed method.