Model predictive control applied to a wing-flap system in hypersonic (Mach 6) flow

Model predictive control applied to a wing-flap system in hypersonic (Mach 6) flow

Hypersonic vehicles are maturing, and are now considered for air-breathing access to space, high speed transport, and gliding planetary entry. Model predictive control (MPC) can allow these vehicles to accurately track precomputed flight trajectories while respecting aero-thermal loading, structural loading, and actuation constraints. However, hypersonic aerodynamics are fundamentally complex, resulting in unavoidable discrepancies between the models used for control and real flight aerodynamics. Simulation studies indicate that MPC shows promise despite these modelling challenges, but few experimental studies have been performed. This paper proposes an MPC scheme for a hypersonic wing-flap system (representative of a hypersonic vehicle’s inner control loop) that is used in experimental campaigns. Control is implemented via online relinearization of an analytical low-order aerodynamics model. The performance of the controller is analyzed via hardware in the loop simulations using a truth model which is calibrated to computational fluid dynamics results. Results indicate good closed-loop performance even in the presence of model error, highlighting the applicability of MPC for inner-loop control of hypersonic vehicles, and demonstrating the readiness of the proposed controller for experimental testing.

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