Experimental Study of Liquid Rocket Simulation of Solid Propellant Rocket Exhaust Characteristics

摘要

A substantial cost saving can be realized if a small liquid propellant rocket engine, using cheap propellants, can be used to screen nozzle materials for eventual use with large solid rocket motors using costly propellants. Work was completed in which the nozzle erosion experienced in a solid rocket motor using AHH propellant was simulated by a liquid propellant engine using white fuming nitric acid and benzene. The work was conducted at a one-to-one scale ratio and the approach taken was to simulate erosion by simulating nozzle environment. Approximate simulation of nozzle erosion was achieved. Additional work is recommended to perform simulation of aluminized propellants and study scaling effects. (Author)