Title

New Additives For Modifying The Burn Rate Of Composite Solid Propellants

Abstract

The ability of nano-particle additives to tailor the burning rate of composite solid rocket propellants is being explored in the authors' laboratories. In the present study, two different nano-particles and two separate styles of mixing in the additive were investigated. These variations were tested on a typical HTPB/AP composite rocket propellant with varying characteristics. After a baseline study was completed without additives, a Taguchi L8 matrix was designed to fully test the effect of six different mixture variables and the two different additives on the burning rate. The propellants were tested in a strand bomb at pressures ranging from approximately 34 to 136 atm, and some representative data are provided. The results thus far indicate that small levels of nano-particle additives (∼1 wt %) can have significant effects on the magnitude and pressure dependence of the composite propellant.

Publication Date

12-1-2006

Publication Title

Collection of Technical Papers - AIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference

Volume

8

Number of Pages

6014-6018

Document Type

Article; Proceedings Paper

Personal Identifier

scopus

Socpus ID

34249064702 (Scopus)

Source API URL

https://api.elsevier.com/content/abstract/scopus_id/34249064702

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