Abstract
Designing robust control for hypersonic vehicles in reentry is difficult, due to the features of the vehicles including strong coupling, nonlinearity, and multiple constraints. This paper proposed a characteristic model-based robust model predictive control (MPC) for hypersonic vehicles with reentry constraints. Firstly, the hypersonic vehicle is modeled by a characteristic model composed of a linear time-varying system and a lumped disturbance. Then, the identification data are regenerated by the accumulative sum idea in the grey theory, which weakens effects of the random noises and strengthens regularity of the identification data. Based on the regenerated data, the time-varying parameters, and the disturbance are on-line estimated according to the grey identification. At last, the mixed H2/H∞ robust predictive control law is proposed based on linear matrix inequalities(LMI) and receding horizon optimization techniques. Using active tackling system constraints of MPC, the input and state constraints are satisfied in the closed-loop control system. The validity of the proposed control is verified theoretically according to Lyapunov theory and illustrated by simulation results.
Highlights
Hypersonic vehicle, a type of aircrafts with a flying speed of over 5 Mach, is a hot research topic due to its importance in national defense and military affairs
In Section “Mixed H2/H∞ Robust Predictive Control,” the mixed H2/H∞ robust predictive control law is proposed based on linear matrix inequalities (LMIs) and receding horizon optimization techniques
The original complicated reentry kinetics and dynamics are simplified by identification of the time-varying parameters in the characteristic model-based gray identification
Summary
Hypersonic vehicle, a type of aircrafts with a flying speed of over 5 Mach, is a hot research topic due to its importance in national defense and military affairs. Since there exist thermal and mechanical constraints in safety boundaries of reentry flight corridors, the hypersonic reentry control system must satisfy strict input and state constraints (Lu, 1999; Shen and Lu, 2003), including the constraints on aerodynamic angles, angular velocities, and control moments. If these complex physical demanding constraints are violated, the performance and stability of the control system will be deteriorated, the safety and reliability of reentry flight can be affected seriously
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