The three-dimensional multiple constrained guidance problem for a hypersonic gliding vehicle (HGV) against a stationary ground target in dive phase is investigated. A coupled nonlinear dynamic model is established on account of the bank-to-turn control scheme adopted by the HGV, which formulates the relation between line-of-sight angles and trajectory control variables. On this basis, a finite-time nonlinear disturbance observer is introduced to estimate the lumped uncertainty. Utilizing the estimation as feedforward compensation, a guidance law based on the adaptive multivariable super-twisting sliding mode control is designed to realize precise strike with designated impact angles. The finite-time stability of closed-loop guidance system is proven through the Lyapunov technique. Numerical simulations are executed to validate the mission adaptiveness and the robustness of the presented guidance scheme.

The maintenance of the nominal multirevolution elliptic halo orbit, whose special features can benefit mercurial explorations, is first investigated through Monte-Carlo simulations in the elliptic Sun-Mercury model, and then validated in the high-fidelity ephemeris model. The receding horizon control strategy solved by the indirect Radau pseudospectral method demonstrates that the orbit can be maintained robustly with respect to very large initial deviations. Moreover, the result proves that the elliptic Sun-Mercury model is an accurate approximation.

This paper develops a comprehensive methodology to address the attitude control problem of hypersonic vehicles in the presence of matched model uncertainties and external disturbances. Initially, a nonlinear dynamic model was established dedicated to attitude control. Afterward, a multivariable disturbance observer was constructed to estimate the lumped disturbance for compensation. Moreover, the dynamic inversion technique was adopted to cancel the nonlinear dynamics for decreasing complexity of controller design. To proceed, a novel fuzzy fast terminal sliding mode control strategy was designed to achieve a significant performance of attitude command tracking with the integrated consideration of robustness, chattering alleviation, and actuator saturation rejection. The finite-time stability of the closed-loop system was proven by means of the finite-time bounded function method and the Lyapunov theory. Simulation results demonstrated that the proposed synthetic scheme showed preferable performance and strong robustness in view of attitude command tracking.