This paper presents a multi-variable sliding mode controller based on the model of flight environment and aerodynamics. The problem is for the hypersonic missile to solve the strong coupling, serious non-linear and strong real-time in the re-entry. We first build a flight environment model to online estimate atmosphere density and dynamic pressure. We then use an aerodynamic model to calculate aerodynamic parameters by dynamic pressure and slipstream angles. Next we design a variable structure controller to reduce its dependence on aerodynamic and structural parameters. Simultaneously, the controller's update could efficiently reduce the sliding surface's initial error. Finally, we synthesize a semi-physical simulation system to represent missile's attitude control process and flight performance. The simulation results show the practicality of the proposed method.
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