D. Ezzat
CSU, San Bernardino,
United States
Keywords: sonic boom reduction- aerothermal management- stagnation point heating- thermal protection systems- supersonic and hypersonic flight
Summary:
This invention, developed and registered by the author, introduces a laser-induced thermal flow control attachment system engineered to attenuate sonic boom intensity and mitigate stagnation-point heating in supersonic and hypersonic aircraft operating across Mach 1-10+. The system integrates a forward-mounted tungsten attachment with precision laser heating and sensor feedback, effectively modifying the thermodynamic and aerodynamic characteristics of the incoming flow field. By reducing local air density and reshaping the shock structure, the system expands the Mach cone angle and softens overpressure levels. Statistical simulation data demonstrate that, at Mach 1, the technology reduces sonic boom intensity from 110 dB to 95 dB and lowers stagnation-point heat flux from 0.754 W/cm² to 0.650 W/cm². These reductions enable higher operational speeds, improved aerodynamic stability, smoother flow-field interactions, and quieter overland supersonic flight above urban areas while remaining within civilian noise compliance thresholds. Beyond passenger transport, this innovation has extensive civilian aerospace applications. It enhances flight stability for drones, improves aerospace safety, and mitigates atmospheric density fluctuations that can impact low-Earth orbit (LEO) satellite constellations such as Starlink, particularly during space-weather disturbances. Lightweight and modular, the system can be retrofitted onto existing platforms, providing a cost-effective solution to enhance performance, reduce environmental impact, and enable quieter, cleaner, and more resilient next-generation air and space transportation.