Randall R. Sobczak
ABSTRACT: This article addresses the theory and design of ammonium perchlorate/hydroxyl-terminated polybutadiene (AP/HTPB) composite propellant rocket motors. A discussion of the operating principles of solid motors, including motor dynamics, the combustion process of AP composite propellants, and basic nozzle theory is presented. Several grain geometries and thrust profiles are illustrated, and requirements for various casing, nozzle and adhesive materials are compared. The propellant system itself, consisting of oxidizer, binder and fuels, plasticizers, bonding agents and burn rate modifiers, is described.
Keywords: composite propellant, ammonium perchlorate, AP, specific impulse, grain geometry, HTPB, hydroxyl-terminated polybutadiene, nozzle expansion ratio, chamber pressure
Ref: JPyro, Issue 3, 1996, pp35-45
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