Development of a Mathematical Model for Hypersonic Aircraft Scramjet Engine Dynamics
DOI:
https://doi.org/10.70112/arme-2025.14.1.4286Keywords:
Hypersonic Aircraft, Scramjet Engine, Fuel Flow Rate, Dynamic Stability, Mathematical ModellingAbstract
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.
References
[1]F. R. Chavez and D. K. Schmidt, “Analytical aero propulsive/aeroelastic hypersonic-vehicle model with dynamic analysis,” J. Guid. Control Dyn., vol. 17, no. 6, pp. 1308-1319, 1994, doi: 10.2514/3.21349.
[2]D. K. Schmidt and J. Velapoldi, “Flight dynamics and feedback guidance issues for hypersonic airbreathing vehicles,” in Proc. AIAA Guid., Navig., Control Conf. Exhibit., Portland, OR, USA, 1999,Paper AIAA-1999-4122, doi: 10.2514/6.1999-4122.
[3]D. McLean and Z. A. Zaludin, “Stabilization of longitudinal motion of a hypersonic transport aircraft,” Trans. Inst. Meas. Control, vol.21, no. 2-3, pp. 99-105, 1999, doi: 10.1177/014233129902100206.
[4]Z. A. Zaludin, “Regaining loss in dynamic stability after control surface failure for an air-breathing hypersonic aircraft flying at Mach 8.0,” Asian Rev. Mech. Eng., vol. 10, no. 2, pp. 1-9, 2021, doi:10.51983/arme-2021.10.1.2961.
[5]D. L. Raney, M. R. Phillips, and L. H. Person, “Investigation of piloting aids for manual control of hypersonic maneuvers,” NASA,VA, USA, Tech. Rep. NASA TP-3525, 1995. [Online]. Available:https://ntrs.nasa.gov/citations/19960002013
[6]D. L. Raney and F. J. Lallman, “Control integration concept for hypersonic cruise-turn maneuvers,” NASA, VA, USA, Tech. Rep. NASA TP-3136, 1992. [Online]. Available:https://ntrs.nasa.gov/citations/19920010953
[7]Z. A. Zaludin, “Mathematical model of an aircraft flying over a range of hypersonic speeds and heights,” Aeronautics and Astronautics Department, Southampton Univ., Southampton, U.K., Tech. Rep.AASU 98/01, 1998.
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