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Katalityczny efekt nanocząstek Fe₂O₃ na spalanie heterogenicznego stałego paliwa rakietowego PBAN/NH₄ClO₄/HMX/Al

Florczak B., Cudziło S.

Biuletyn Wojskowej Akademii Technicznej

2009

Vol. 58, nr 4

187-195

W artykule przedstawiono wyniki badań heterogenicznego paliwa rakietowego PBAN/NH₄ClO₄/HMX/Al zawierającego nano i mikrocząstki Fe₂O₃ lub ferrocen w roli katalizatora. Nanoproszek Fe₂O₃ był otrzymywany przez redukcję azotanu żelaza za pomocą alkoholu poliwinylowego w warunkach niskotemperaturowej syntezy spaleniowej. Zbadano morfologię i mikrostrukturę składników. Przeprowadzono obliczenia termodynamiczne i zmierzono prędkość spalania w bombie Crawforda. Stwierdzono, że katalityczny wpływ nanoproszku Fe₂O₃ na liniową prędkość spalania jest porównywalny z wpływem ferrocenu.

In the present work, aluminized PBAN/AP/HMX composite propellants containing nanometer and micrometer sized Fe₂O₃ as well as ferrocene as catalysts were tested. Fe₂O₃ nanopowders were prepared by the sol-gel auto-combustion method using polyvinyl alcohol as a gelating agent (and fuel) and iron nitrate as an oxidizer and a precursor of iron oxide. The morphology and microstructure of the components and propellant samples were determined. Thermodynamic calculations were performed and burning rates were measured using the Crawford strand burning technique. It was stated that the catalytic effect of the F₂O₃ nanopowder on the burning rate is comparable with that of ferrocene.

Investigation of an Aluminized Binder/AP Composite Propellant Containing FOX-7

Florczak B.

Central European Journal of Energetic Materials

2008

Vol. 5, nr 3-4

65-75

This paper presents the results of thermodynamical calculations and investigations of the thermochemical and balistic properties of aluminized composite solid propellants Binder/AP/A1 containing FOX-7. The calculation was conducted by using ICT-Thermodynamic Code. The heat of combustion was determined in a stationary bomb calorimeter IKA C 4000. The breakdown temperatures were taken with the DTA 551 Ex measuring apparatus and the burning rate was measured in a subscale rocket motor utilizing the ESAM v. 3.3.0 system. It was revealed that the introduction of FOX -7 into the propellant composition causes a reduction of the energetic characteristics and the burning rate of the propellant.

A Comparison of Properties of Aluminized Composite Propellants Containing HMX and FOX-7

Florczak B.

Central European Journal of Energetic Materials

2008

Vol. 5, nr 3-4

103-111

Modern rocket propellants contain inter alia nitroamines (i.e. RDX, HMX). Therefore, the detonation properties of composite solid propellants are very important for good functioning of rocket motors and for storage. One of the new materials of that kind, with low sensitivity, is FOX-7 which was applied here as one of the components of composite solid propellant. This paper presents the thermodynamical calculations and thermochemical research results as well as the results of a study of transition into detonation of an aluminized composite propellant containing HMX. The said properties were compared with those of a propellant containing FOX-7.