Iron oxide as solid propellant catalyst: A detailed characterization

The purpose of this paper is the investigation of the catalytic effect of graphene oxide–copper oxide nanocomposite (GCNC) on the thermal comportment and decomposition reaction kinetics of a double‐base propellant (DBP) formulation. Differential scanning calorimetry (DSC) was used to conduct the thermal analysis. Using well‐known iso‐conversional kinetics methods, namely, Vyazovkin's nonlinear integral with compensatory effect (VYA/CE), Kissinger–Akahira–Sunose (KAS), and Flynn–Wall–Ozawa (FWO), the thermokinetic parameters for the investigated propellant, including activation energy and frequency factor, were estimated. Additionally, based on the results obtained from the kinetic analysis, the critical ignition temperature was calculated. The results showed that after the addition of GCNC, the activation energy barrier is lowered by 18%, and the critical ignition temperature is reduced.

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“…The DSC curves of propellants shown in Figure 6 show a single exothermic degradation peak, which is consistent with published data 57,58 …”

Section: Resultssupporting

confidence: 90%

Decomposition reaction kinetics of double‐base propellant catalyzed with graphene oxide–copper oxide nanocomposite

Louafi

Boulkadid

Belgacemi

et al. 2023

Int J of Chemical Kinetics

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“…The latter enables the regressing surface tracking during the combustion, thus providing the quasi-steady burning rate. For a given propellant, experimental results are reduced according to the standard Vielle's law [28]:…”

Section: Methodsmentioning

confidence: 99%

Preparation and Characterization of Al/HTPB Composite for High Energetic Materials

et al. 2020

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Nanosized Al (nAl) powders offer increased reactivity than the conventional micron-sized counterpart, thanks to their reduced size and increased specific surface area. While desirable from the combustion viewpoint, this high reactivity comes at the cost of difficult handling and implementation of the nanosized powders in preparations. The coating with hydroxyl-terminated polybutadiene (HTPB) is proposed to improve powder handling and ease of use of nAl and to limit its sensitivity to aging. The nAl/HTPB composite can be an intermediate product for the subsequent manufacturing of mixed high-energy materials while maintaining the qualities and advantages of nAl. In this work, experimental studies of the high-energy mixture nAl/HTPB are carried out. The investigated materials include two composites: nAl (90 wt.%) + HTPB (10 wt.%) and nAl (80 wt.%) + HTPB (20 wt.%). Thermogravimetric analysis (TGA) is performed from 30 to 1000 °C at slow heating rate (10 °C/min) in inert (Ar) and oxidizing (air) environment. The combustion characteristics of propellant formulations loaded with conventional and HTPB-coated nAl are analyzed and discussed. Results show the increased burning rate performance of nAl/HTPB-loaded propellants over the counterpart loaded with micron-sized Al.

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“…This increase in pressure exponent is likely due to more agglomerates less than 10 microns corresponding to kinetically limited combustion [51]. In contrast, non-energetic catalysts, such as iron oxide, can increase the burning rate by 1.5 to 2 times the original value depending on the size of catalyst particles and the amount added [52][53][54]. Because these catalysts do not contribute to the reaction's overall energy, there will also be a decrease in Isp.…”

Section: Combustion Experimentsmentioning

confidence: 99%

On the Use of Fluorine‐Containing Nano‐Aluminum Composite Particles to Tailor Composite Solid Rocket Propellants

Uhlenhake

Yehia

Noel

et al. 2022

Propellants Explo Pyrotec

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The burning rate of solid propellants is an important factor for optimizing rocket motors and improving performance. The enhanced burning rate can increase thrust and reduce a propulsion system's overall size and weight. In this study, a novel nano-aluminum/THV composite additive was prepared and introduced into a solid ammonium perchlorate/polybutadiene composite solid rocket propellant to enhance its burning rate. The morphology of the composite particle additive and its effects on combustion were characterized. The use of small quantities (< 15 wt.%) of the additive resulted in a burning rate enhancement of up to 2.1 times that of the conventional coarse aluminized propellant with a specific impulse loss of only 3 seconds, and as much as 4.7 times enhancement with a predicted loss of 22 seconds in theoretical specific impulse. Some of this loss may be recovered by the improved combustion efficiency in smaller rocket motors because the additive was shown to significantly reduce the aluminum agglomeration at the propellant burning surface and reduce the size of reaction products which may reduce two-phase flow losses. The additive also provides wide burning rate tailorability, favorable for motor, grain, and thrust curve design. The burning rate enhancement mechanism is thought to be a physical cratering mechanism governed by the burning rate disparity between the binder/oxidizer system and the nano-aluminum/fluoropolymer additive and not a chemical catalytic effect.

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Iron oxide as solid propellant catalyst: A detailed characterization

Cited by 22 publications

References 29 publications

Decomposition reaction kinetics of double‐base propellant catalyzed with graphene oxide–copper oxide nanocomposite

Decomposition reaction kinetics of double‐base propellant catalyzed with graphene oxide–copper oxide nanocomposite

Preparation and Characterization of Al/HTPB Composite for High Energetic Materials

On the Use of Fluorine‐Containing Nano‐Aluminum Composite Particles to Tailor Composite Solid Rocket Propellants

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