Development of a Mathematical Model for Hypersonic Aircraft Scramjet Engine Dynamics

This study proposes a methodology to obtain several critical parameters of scramjet engine propulsion for a generic hypersonic aircraft mathematical model. Using available variables from the existing model, additional variables were computed in real time during simulations. The perturbation in the thrust force along the x-axis direction (ΔXT) was applied as the fuel flow rate input to the mathematical model. Dynamic stability was maintained by the controlled aircraft, provided that the engine time constant did not exceed 0.07 s. The integration of the scramjet engine mathematical model within the generic hypersonic aircraft model exhibited a negligible effect on closed-loop stability.