Hybrid rocket-ramjet AEROSPACE ENGINE

摘要

1. A hybrid rocket and ramjet engine aerospace, characterized in that it comprises thruster (RD) for fuel in the form of aluminum nanopowder not larger than 25 nm in a liquid aqueous phase, designed to create thrust at start and at the initial stage of the flight, and for production of fuel consumed aligned with them ramjet engine (ramjet) cruising flight at the molecular hydrogen formed during the combustion of aluminum nanopowder, and characterized in that it comprises a cylindrical ical shroud at one end of which entrance for air flow, and on the other - an outlet nozzle, central axisymmetric or wedge-shaped body, the edges of which is realized a system of shock waves, arranged in the shell, a combustion chamber for burning aluminum nanopowder in water vapor, which is simultaneously chemical reactor for producing hydrogen, arranged in the wedge-shaped body, its associated outlet and the nozzle adapted to form the combustion zone by reacting the hydrogen flowing from the nozzle and n stepping potoka.2 air. The hybrid rocket and ramjet aerospace engine according to claim 1, characterized in that in the combustion zone and the oxidant is molecular hydrogen are in a stoichiometric ratio (fuel / oxidizer φ = 1) or form a lean mixture (ratio φ 1) .3 . The hybrid rocket and ramjet aerospace engine according to claim 1 or 2, characterized in that the running at a speed equal to the Mach number M = 0-24.4. The hybrid rocket and ramjet aerospace Motor