A longitudinal integrated guidance and control scheme for the hypersonic vehicle in glide phase was designed based on the dynamic surface control method and the sliding mode control theory. The translational rotational dynamic and kinematical equations in the longitudinal plane were denoted; the desired velocity slope angle was derived based on the predictor corrector of the longitudinal range; the relations of the velocity slope angle, angle of attack, and the pitch rate were established. The dynamic surface control, the terminal sliding model and the second-order sliding mode control methods were adopted to implement the longitudinal integrated guidance and control scheme; the commanded angle of attack and elevon fins were analytically solved by using the GHV’s aerodynamic model having partial derivative matrix forms. The effectiveness and robustness of the newly proposed longitudinal integrated guidance and control scheme was validated. Moreover, the characteristics of flight phases before and after the quasi equilibrium glide phase were discussed and the problems with respect to the guidance and control system design were analyzed.