Preliminary research of composite rocket propellants with hexogen and titanium oxide powder

Composite solid propellants based on ammonium perchlorate/hydroxyl-terminated polybutadiene/isophorone dyisocyanate including two levels of hexogen (RDX) are presented in this paper. The mass of RDX increased in relation to oxidant, with constant bimodal fraction ratio. Combustion of the propellants...

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Bibliographic Details
Published in:Scientific Technical Review
Main Authors: Rodić Vesna, Bogosavljević Marica, Milojković Aleksandar, Mijatov Slavko
Format: Article
Language:English
Published: Military Technical Institute, Belgrade 2018-01-01
Subjects:
composite solid propellant
ammonium perchlorate
hydroxyl-terminated polybutadiene
hexogen
titanium (iv)oxide
ballistic characteristics
thermochemical parameters
Online Access:https://scindeks-clanci.ceon.rs/data/pdf/1820-0206/2018/1820-02061802036R.pdf
Description
Summary:Composite solid propellants based on ammonium perchlorate/hydroxyl-terminated polybutadiene/isophorone dyisocyanate including two levels of hexogen (RDX) are presented in this paper. The mass of RDX increased in relation to oxidant, with constant bimodal fraction ratio. Combustion of the propellants was improved by adding of titanium (IV) oxide powder as stabilizer. Parameters of burning rate laws and apparent viscosity values were determined and compared for the propellants of the same total solid phase. Calculations of thermochemical parameters are also given in this research.
ISSN:1820-0206
2683-5770

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