A rocket motor (300) comprising propellant (308) enclosed by a casing (306) having a closed forward end and an aft assembly (310) including a closure member (312) with an opening (322) secured to said casing, a piston assembly (316) slidably retained within said casing (306) so as to be movable between an at rest position adjacent said aft assembly (310) and a maximum pressure position forward thereof in which the propellant is axially compressed to radially expand the propellant toward said casing, a nozzle assembly (314) slidably mounted within said piston assembly movable between a forward vent path (398) defining position and an aft vent path closing position, an igniter (318) and a burn path structure including a sheet insulator (420) positioned between the propellant (308) and said piston assembly so that abnormal propellant burns will propagate along an aft interface of said insulator (420) and normal propellant burns will propagate along a forward interface of said insulator (420).
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