Integrated guidance and control for hypersonic vehicles in dive phase with multiple constraints

An adaptive integrated guidance and control (IGC) scheme for hypersonic vehicle in dive phase is proposed in this paper. The three dimensional (3D) coupling relative dynamics and the explicit relations between line-of-sight (LOS) angles and the angle of attack and sideslip angle are described based on analytical aerodynamic models of the hypersonic vehicle. A coupling and full states IGC design model in strict feedback form is derived by combing the 3D relative dynamics and the equations of the rotational loop. In the deduction of the novel IGC scheme, the 3D impact angles and constraints of the normal overload, commands of Euler angles and three-channel body rates are accounted for. The solution of a ten-order, nonlinear, and uncertain IGC frame control system is converted into an output tuning problem. Pseudo-inputs associated with rotational motion are depicted using adaptive dynamic surface control theory. The desired control surface fin deflections are derived based on the block dynamic surface approach. The Lyapunov function consisted of dynamic surfaces, errors of the filters, and estimation errors is conducted, states of the IGC closed-loop system are proved to be uniformly ultimate bounded. Finally, the effectiveness and robustness of the adaptive IGC scheme are investigated and verified using six-degree-of-freedom (6DoF) nonlinear simulation studies.