Performance analysis of hypersonic vehicles based on aerodynamic /thrust vector control

The aircraft using thrust vector control uses the engine to produce thrust through the nozzle deflection to get extra control moment to realize the attitude control of the flight vehicle. Its outstanding characteristic is that it is closely related to the engine torque control, and is not under the influence of the vehicle attitude itself. The equivalent rudder yaw-angle provided by thrust vector can substitute for some aerodynamic rudder yaw-angle; this is advantageous for reducing resistance and heat shielding of vehicles. The primary job of this paper concerns hypersonic vehicles based on aerodynamic/thrust vector control in near space. By establishing the dynamics and kinematics model and designing aerodynamic/thrust vector controller, the required rudder yaw-angle can be provided by aerodynamic and thrust vector. A six DoF mathematical model is built and simulated in matlab and simulink. When the required rudder yaw-angle is small, it can all be provided by thrust vector; nevertheless, when the required rudder yaw-angle is big, it should be provided by aerodynamic and thrust vector. The resalts and their analysis show preliminarily that the control methods are correct, and all the methods are useful for engineering application.