Abstract

A solid rocket motor includes a combustion chamber bounded by an outer casing, a propellant grain within the combustion chamber, and an igniter within the outer casing for igniting the propellant grain. A nozzle is coupled to the combustion chamber for releasing hot gasses evolved from burning the propellant grain to provide thrust for propelling the solid rocket motor. The propellant grain is a self-extinguishing propellant grain that includes at least one fuel, at least one oxidizing agent, at least one binder, and at least one surfactant that imparts the self-extinguishing property. The propellant grain provides a burning rate as a function of pressure that includes a negative pressure dependence portion, wherein the burning rate in the negative pressure dependence portion decreases with increasing pressure until a cutoff pressure is reached which results in the extinguishment of the propellant grain.

Document Type

Patent

Patent Number

US 8,336,287 B1

Application Serial Number

12/413,284

Issue Date

12-25-2012

Current Assignee

UCFRF

Assignee at Issuance

UCFRF

College

Advanced Materials Processing & Analysis Center (AMPAC)

Department

Advanced Materials Processing & Analysis Center (AMPAC)

Allowance Date

11-7-2012

Filing Date

3-27-2009

Assignee at Filing

UCFRF

Filing Type

Nonprovisional Application Record

Donated

no

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