Accession Number : AD0377143
Title : CHARACTERIZATION OF BARRIER MATERIALS AND IGNITION SYSTEMS FOR SELECTABLE-IMPULSE MOTORS,
Corporate Author : ROHM AND HAAS CO HUNTSVILLE ALA REDSTONE RESEARCH LABS
Personal Author(s) : Anderson,S. E.
Report Date : 21 NOV 1966
Pagination or Media Count : 31
Abstract : An investigation of barrier material ablation under igniter gas flow was extended and several more important variables were identified. The initial work showed that the barrier ablation rate was controlled by the igniter mass flux when chamber length and main nozzle size were held constant. In this extension, the main nozzle size and motor length were allowed to vary and effects were noted. Barrier installation methods were evaluated for their applicability to different propellant systems. For plastisol nitrocellulose composite propellants, epoxy-based barriers sprayed on the mandrel for the outer grain were best, but for composite propellant barriers based on propellant binder and sprayed directly on the outer grain were most attractive.
Descriptors : (*ROCKET ENGINES, MATERIALS), MANUFACTURING, IGNITION, PRESSURE, GAS FLOW (U) *SOLID PROPELLANT ROCKET ENGINES), ROCKET IGNITERS, ABLATION, THERMAL INSULATION, EPOXY RESINS, FAILURE(MECHANICS), BONDING, ROCKET NOZZLES, NITROCELLULOSE, ALUMINUM, ACRYLIC RESINS
Subject Categories : Rocket Engines
Solid Propellant Rocket Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE