Studies on the role of iron oxide and copper chromite in solid propellant combustion

Ishitha, Kumar; Ramakrishna, P. A.

doi:10.1016/j.combustflame.2014.03.015

Cited by 81 publications

(26 citation statements)

References 51 publications

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“…The pressure index of mix 4 was the highest and it is close to those observed with double base propellants [1,9]. This propellant had 1 % IO and Ishitha and Ramakrishna [10] have reported that with the use of 1 % IO in the propellant the pressure index increased. Similar results with the use of catalysts (IO, CC, Cu 2 O, CuO) or dopant (potassium) have been reported by many other investigators [1,[19][20][21].…”

Section: Resultssupporting

confidence: 69%

“…He has observed an increase of more than twofold when bimodal AP of particle sizes 350 and 200 mm was replaced with bimodal AP of 15 and 3 mm particle sizes in a non-aluminized propellant of 80 % solid loading. In recent times, Ishitha and Ramakrishna [10] have presented an extensive review of literature available on the catalysts [primarily iron oxide (IO) and copper chromite (CC)] used to enhance the burn rates of composite solid propellants. They have also carried out systematic experiments to understand the role of catalyst (IO/CC) in enhancing the burn rates of propellant and concluded that catalyst is only effective when in contact with AP particle.…”

Section: Introductionmentioning

confidence: 99%

“…However, Mukunda [1] has reported that, for a solid propellant composition having aluminum, addition of catalyst (IO) increases the temperature sensitivity and it continues to increase with increase in mass fraction of catalyst. Ishitha and Ramakrishna [10] observed that with the addition of 1 % catalyst (IO), the thermal conductivity of the solid propellant increases. They have also reported that with increase in thermal conductivity of propellant, the pressure indices of the propellant increases.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Enhancement of Aluminum Reactivity to Achieve High Burn Rate for an End Burning Rocket Motor

Marothiya

Ramakrishna

2017

Propellants Explo Pyrotec

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Aluminum is used in solid propellants to increase the specific impulse (Isp). It is desirable to have high propellant loading in any stage as it reduces the structural coefficient and an end burning grain is known to be the one with the highest propellant loading. As aluminum combustion is a slow process, the time available for aluminum combustion in an end burning configuration will be very small at the start of the combustion process. This demands an increase in the reactivity of the aluminum. This study is built on the fact that mechanical activation of aluminum powder with PTFE (poly‐tetra‐flouro‐ethylene) enhances the reactivity of aluminum powder. This study also deals with the use of this activated aluminum powder in conjunction with various other methods to enhance the burn rates of the solid propellant. The temperature sensitivity was also measured. Based on these results, new designs with end burning grains for the third stage of Polar Satellite Launch Vehicle (PSLV) and for the second and third stage of Pegasus launch vehicle have been proposed to increase the payload capacity. With this new design, it is seen that the payload can be increased by 12.7 % and 17.6 % for PSLV and Pegasus, respectively. The novelty of this design is that with no changes to any other hardware of the above two systems the increase in payload can be achieved.

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Section: Resultssupporting

confidence: 69%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Enhancement of Aluminum Reactivity to Achieve High Burn Rate for an End Burning Rocket Motor

Marothiya

Ramakrishna

2017

Propellants Explo Pyrotec

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“…A solid propellant burning rate is often modified by the addition of burning rate modifiers to its composition in small quantities ( 3 %). [1] Nowadays, the main burning rate modifiers are transition metal oxides, nano-metal particle, metal chelates, ferrocene and its derivatives etc. [2] Ammonium perchlorate (AP) and cyclotrimethylenetrinitramine (RDX) are used as the most common oxidizer and hydroxyl-terminated polybutadiene (HTPB) as the fuel binder.…”

Section: Introductionmentioning

confidence: 99%

Catalytic Action of Submicrometer Spherical Ta/Ph‐Fe on Combustion of AP/HTPB Propellant

Song

Liu

Zhang

et al. 2018

Propellants Explo Pyrotec

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This paper describes the preparation of two combustion catalysts Tannin‐Fe (Ta−Fe) and Phloroglucinol‐Fe (Ph−Fe) by spray drying. The particle size and morphology of the particles are observed by scanning electron microscopy (SEM). The results of SEM image show that the particles are regular spherical and very good dispersion. The diameter of most spherical particles is about 1 μm. The effects of Ta−Fe and Ph−Fe on the thermal decomposition of RDX and AP were tested by differential scanning calorimeter (DSC). DSC dates show that Ta−Fe and Ph−Fe can advance the high temperature exothermic peak of AP 18.0 °C and 16.1 °C, respectively. The burning rates illustrates that both Ta−Fe and Ph−Fe can significantly increase the combustion rate of HTPB propellants. The formulation with 2 mass% Ta−Fe shows an average 21.31 % increase in burning rate and has a low value of the exponent n=0.48. The formulation with 2 mass%Ph−Fe has a burning rate 20 to 60 % larger than that of the initial AP/HTPB/Al formulation, and has a lowest exponent n=0.45.

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“…Usualmente, para motores-cohete con granos compuestos por Nitrato de Potasio y Sorbitol (KNSB), se emplean mezclas con relaciones 65/35; es decir, se obtienen mezclas con 65% en masa de oxidante y 35% en masa de combustible (Singh, 2013). En algunos diseños se suelen adicionar otras sustancias en proporciones cercanas al 1% de la masa total de la mezcla, tales como óxido de hierro y manganeso, con el fin de aumentar la tasa de quema y mejorar el desempeño general del proceso de combustión (Ishitha, 2014).…”

Section: Introductionunclassified

Optimización de un motor de combustible sólido tipo KNSB para cohetería experimental

Moreno

2016

Ciencia y Poder Aéreo

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Este artículo muestra de manera general el proceso de optimización para un motor de combustible sólido basado en una mezcla de Nitrato de Potasio y Sorbitol (KNSB) con una configuración de grano tipo Bates, generalmente usada en cohetería experimental de baja potencia. En este proceso, el máximo empuje es seleccionado para la menor cantidad de masa requerida, indicando el tamaño estimado del motor más eficiente mediante múltiples iteraciones, donde a partir de un rango inicial de valores de empuje se calcula la cantidad de masa de propelente necesaria. Adicionalmente, a través de la estimación gráfica de la segunda derivada de la relación de empuje con respecto a la masa, se establece un límite de eficiencia donde el aumento de la cantidad de propelente debe representar al menos un incremento superior al 0.5% en la pendiente de dicha relación. Finalmente se propone un modelo con el ensamble del motor esquematizado mediante software de diseño asistido por computador.

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Studies on the role of iron oxide and copper chromite in solid propellant combustion

Cited by 81 publications

References 51 publications

Enhancement of Aluminum Reactivity to Achieve High Burn Rate for an End Burning Rocket Motor

Enhancement of Aluminum Reactivity to Achieve High Burn Rate for an End Burning Rocket Motor

Catalytic Action of Submicrometer Spherical Ta/Ph‐Fe on Combustion of AP/HTPB Propellant

Optimización de un motor de combustible sólido tipo KNSB para cohetería experimental

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