Propellant Internal Mode Dis-equilibrium and Frozen Flow Losses in Arcjets

摘要

Arcjet thrusters impart directed kineti energy to a propellant by ohmically heating it and subsequently expanding it in a supersonic nozzle. The arcjet consists of an inlet plenum where the propellant is injected sometimes with swirl, a converging portion, a straight section called the constrictor, and a diverging portion or supersonic nozzle as shown in Fig. 1. The arcjet is capable of operating on a variety of different propellants such as hydrazine, ammonia, and hydrogen.