Abstract A method and results of calculating the laser radiation power values necessary to place an artificial earth satellite in orbit are presented; the values depend on the initial vehicle mass, velocity of the working fluid efflux from the laser rocket engine nozzle, velocity of vehicle motion, optimal values of thrust-to-weight ratio taking into account irreversible energy losses in the rocket engine jet. The possibility of creating a spacecraft with small initial mass is substantiated. A layout scheme of the propulsive system is proposed that makes it possible to divide total laser radiation power and to use atmospheric air as a working fluid.
A concept of a spacecraft with small initial mass placed in the near-earth orbit by a laser rocket engine
Russian Aeronautics (Iz VUZ) ; 51 , 2 ; 166-172
2008-06-01
7 pages
Article (Journal)
Electronic Resource
English
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