Development of the airspace laser-propulsion engine operating both in RP and CW modes of thrust production is validated. The engine is considered as a basic unit for creation of HPLP. The aerospace laser device differs sufficiently as compared with other laser-propulsion engines by its design, and it consists of two principal units, namely, laser beam concentrator and jet nozzle. Such type of the device allows optimizing both units of the engine independently on other one, taking into account only laser beam parameters and gas-dynamic effects.

    The ASLPE engine was tested experimentally by the use of the RP and CW types of CO2 lasers. The engine model demonstrated thrusts of 1.5–2.0 N at the laser power of 5–20 kW, which corresponded to momentum coupling coefficient of 10–20 dynes/W.

    In the chapter, thermal and mechanical loads on the device construction are analyzed to optimize design of the engine units, too. The proposals for increasing the efficiency of thrust production by the engine are considered.


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