Solid fuel gas generator for ducted rocket engine
First Claim
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1. A solid fuel gas generator for ducted rocket engine comprising a range in weight percent of the following ingredients:
- i. an energetic nitramine prepolymer binder in the amount from 60-85 weight percent of the gas generator composition;
ii. a curing and crosslinking agent selected from the group of curing and crosslinking agents consisting of hexamethylene diisocyanate, a polyfunctional isocyanate which is the reaction product of hexamethylene and water, and isophorone diisocyanate 5-15 weight percent of the gas Generator composition;
iii. ZrH2 fuel additive and ignition aid of about, 0.5-10 weight percent of the gas generator composition;
iv. carbon black fuel element of about 0-30 weight percent of the gas generator composition; and
, v. a curing catalyst of dibutyl tin dilaurate 0.01 weight percent of the gas generator composition.
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Abstract
In the development of new minimum signature ducted rocket technology, the U.S. Army MICOM Propulsion Directorate has conducted studies for the development of fuel-rich gas generators for ducted rockets. The propellant formulation goals of this study include increasing burning rate, pressure exponent, and combustion efficiency without significantly decreasing fuel value. Formulations described in this application contain an energetic nitramine-prepolymer, a range of curing agents, and zirconium hydride (ZrH2) fuel element and carbon (C) as an optional fuel element.
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3 Claims
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1. A solid fuel gas generator for ducted rocket engine comprising a range in weight percent of the following ingredients:
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i. an energetic nitramine prepolymer binder in the amount from 60-85 weight percent of the gas generator composition;
ii. a curing and crosslinking agent selected from the group of curing and crosslinking agents consisting of hexamethylene diisocyanate, a polyfunctional isocyanate which is the reaction product of hexamethylene and water, and isophorone diisocyanate 5-15 weight percent of the gas Generator composition;
iii. ZrH2 fuel additive and ignition aid of about, 0.5-10 weight percent of the gas generator composition;
iv. carbon black fuel element of about 0-30 weight percent of the gas generator composition; and
,v. a curing catalyst of dibutyl tin dilaurate 0.01 weight percent of the gas generator composition. - View Dependent Claims (2, 3)
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Specification