The invention discloses an integrated design method for guidance and control of a hypersonic aerocraft. The method comprises steps that firstly, a nonlinear dynamic model of the hypersonic aerocraft is established, based on the singular perturbation theory, the nonlinear dynamic model is divided into a slow time-varying guidance loop and a fast time-varying control loop, secondly, a nominal controller and a linear time-varying feedback controller of the two loops are designed separately, actual control input of the two loops is calculated, and lastly, control output of the two loops is calculated based on the mapping relationship. The method is advantaged in that aiming at the complex flight mission profile of the hypersonic aerocraft and a flight control problem along the trajectory, thecharacteristics of the hypersonic vehicle with strong coupling, strong nonlinearity and fast time-varying are considered, in the case of large system perturbation and external disturbance in the model, based on the trajectory linearization control method, integrated strategy design of guidance control is completed, the method is simple for realization and easy for engineering application in the hypersonic aircraft, and the method has better control performance and robust performance.