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Hydrogen Peroxide as a High Energy Compound Optimal for Propulsive Applications

Rarata G., Rokicka K., Surmacz P.

Central European Journal of Energetic Materials

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2016

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Vol. 13, no. 3

778--790

EN

This paper presents the authors’ experience in the field of the safe preparation and utilisation of HTP (98%+), a storable propellant that is finding use in various engineering applications. Brief characterisations of the material as well as examples of its potential use within relevant industries are provided. Additionally, some of the existing data and current research are included to demonstrate the full potential of this material which meets most of the needs of the propulsion industry. The laboratory technique for obtaining the substance that has been developed recently at the Institute of Aviation is briefly described. Utilisation of the method based on a special glass apparatus allows reproducible amounts of the substance to be obtained with relatively little risk.

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Towards New Directions in Oxidizers/Energetic Fillers for Composite Propellants: an Overview

Dey A., Sikder A. K., Talawar M. B., Chottopadhyay S.

Central European Journal of Energetic Materials

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2015

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Vol. 12, no. 2

377--399

EN

There is continued interest in the development of safe and reliable composite propellant formulations using modern energetic ingredients such as energetic oxidizers/energetic ingredients, energetic binders, and energetic ballistic modifiers. There are continued efforts by energetic materials researchers, scientists, technologists and engineers to design composite propellant formulations with better ballistic properties than conventional formulations. The efforts in many research and development (R & D) laboratories all over the world are aimed at utilizing modern oxidizers/ energetic fillers for the development of composite propellant formulations for both space and defence applications. Composite propellants are considered to be the major source of chemical energy for rockets and missiles. Energetic oxidizers/fillers play vital roles in the preparation or manufacture of composite propellant formulations. Various energetic oxidizers/fillers have been developed during the last five decades to address environmental safety, high energy and processing conditions. In this article, the authors have reviewed the characteristic properties of the energetic oxidizers/fillers used in the preparation of composite propellants. The characteristic properties of the energetic ingredients play an important role in the preparation of composite propellant formulations with the desired mechanical properties. The advantages and disadvantages of various energetic oxidizers/ingredients for specific and potential propellant applications are also highlighted throughout the course of this review article. The future direction in composite propellant formulations calls for the development of green propellant formulations. Efforts will continue to seek alternative and more energetic oxidizers/fillers in comparison to conventional oxidizers. There is an urgent need to replace conventional oxidizers such as ammonium perchlorate with eco-friendly ingredients.

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Investigation of the Oxidizer Charge Impact Onto Energetic Characteristics Demonstrated by the Stream of Gunpowder Gas Ejected by Solid-Propellant Missile Engines

Pietraszek M., Klemba T.

Prace Naukowe Instytutu Technicznego Wojsk Lotniczych

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2013

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nr 33

203–219

EN

The study discloses outputs from examinations devoted to charges of oxidizers and their impact on behaviour of missile engine operation with particular attention to measures that are undertaken to counteract stall of a helicopter engine. Homogenous solid propellant for missile engines exhibits a negative oxygen balance. When a series of rocket missiles driven by means of such fuel is launched from the helicopter board there is a hazard of the engine stall effect that may lead to killing its engines. Admixture of potassium (II) sulphate (VI) that is added into the combustion chamber of a missile engine as an inhibitor of the combustion reaction favourably alters characteristics of the engine output power and, at the same time, is irrelevant to the available thrust of the engine. Application of the oxidizer as an insert into the engine substantially improves flight safety when rocket missiles are launched from an aircraft and makes it possible to avoid significant changes in the engine design. The paper outlines the results from investigations when a charge of K2SO4 was introduced into the Mk66 missile engine as a compressed bar and the working parameters of the engine were measured. The investigations on a vertical workbench comprised measurements of the engine thrust and temperature in the stream of exhaust gases. The measurement results were compared against figures sourced from the original data sheets of engines.