FIELD: aircraft engineering.
SUBSTANCE: invention relates to active thermal protection of hypersonic drone heat-beat leading edges. Proposed device comprises heat carrier and heat protection ply generation means. Drone nose accommodates cylindrical gas-jet resonator arranged between its leading edge and combustion chamber and provided with the system of control valves located at resonator sidewall. Resonator open inlet is aligned with the drone leading edge and directed toward incident flow. Resonator outer surface supports container with heat carrier composed of methane hydrate and methane hydrate transformer into the mix of steam and methane. The latter is kept under pressure in pulse mode at frequency over 100 Hz with the help of gas-jet resonator to produce protective ply at resonator open inlet to protect the drone leading edge against peak hear loads.
EFFECT: decreased heat loads, higher fuel efficiency.
1 dwg
