Abstract:

The key factors and uncertainties that affect the attitude movement of a hypersonic vehicle are analyged and a new scheme of hypersonic vehicle attitude control is proposed, including pressure correlation output transformation, nonlinear golden section adaptive control law Ⅲ, integrator and optional feedforward control. The new scheme solves the influence of the rapid change of aerodynamic pressure on the stability and control precision of the attitude control system during flight, and improves the robustness and adaptability of the critical parameters of the  system such as aerodynamic parameter deviation, aerodynamic damping coefficient deviation, atmospheric density deviation, inertia deviation and initial conditional deviation. The new scheme is applied to the attitude control of the dive phase of a hypersonic vehicle with the rapid variance of altitude and velocity, resulting in sharp variance of dynamic pressure. The mathematical simulation shows that the performance index satisfies the requirement and the control output satisfies the restriction.

Key words: Hypersonic vehicle, Nonlinear, Adaptive control, Integrator, Optional feed forward controller