Abstract:

To improve the instantaneity and robust ness, a referencetrajectory guidance scheme for the reentry is introduced. The trajectory tracking problem based on the obtained reference-trajectory is converted into a trajectory state regulation problem which is actually an optimal control problem of a linear time varying system. And a robust guidance law combines the benefits of the indirect Legendre pseudo-spectral method and the receding horizon control method is applied to the problem. The three degree of freedom guidance for the reentry of suborbital reusable launch vehicle (SRLV) is implemented. Finally, numerical results indicate that the guidance scheme is robust to the presence of a wide range of initial uncertainties and aerodynamic parameters disturbance.