In order to describe the flow field in a repetitively pulsed laser propulsion rocket nozzle, the detonation wave model and the blast wave model are considered. In the blast wave model the deposition of laser energy is made only at the apex of the cone nozzle. In the detonation wave model the deposition of laser energy is made at the wave front which is sustained by a laser. The similarity method and the finite difference method are used. The specific impulse, thrust and energy conversion efficiency are determined on the basis of the two models. The laser pulse of short duration gives rise to the blast wave, while the laser pulse of long duration gives rise to the detonation wave. The total deposition energy of the laser may be given by (duration time) times (power). If the total energy is the same, the short and strong laser pulse leads to performance higher than the long and weak laser pulse. That is to say, the former excels 1.11 times in the thrust and the specific impulse, and 1.33 times in the energy conversion efficiency compared to the latter.
Thrust and Specific Impulse of Repetitively-Pulsed-Laser Propulsion Rocket
1987
20 pages
Report
Keine Angabe
Englisch
Electric & Ion Propulsion , Detonation waves , Flow distribution , Laser propulsion , Rocket thrust , Spacecraft propulsion , Laser outputs , Mathematical models , Power transmission (Lasers) , Pulse duration , Pulsed lasers , Rocket nozzles , Shock waves , Finite difference theory , Similarity theorem , Foreign technology
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