Effects of Different Nano-Sized Metal Oxide Catalysts on the Properties of Composite Solid Propellants

In the present study, nano and micron‐sized barium titanate (BaTiO3) were characterized and evaluated in HTPB/AP/Al composite propellant. Different compositions were prepared by incorporating BaTiO3 from 0.5 % to 2 % in a standard composition. The BaTiO3 reduces thermal decomposition temperature of ammonium perchlorate and also of standard composition. Other propellant processing and performance parameters like viscosity, mechanical and ballistic properties were also measured. The ballistic properties results revealed that there was more than 22 % and 12 % (at 6.86 MPa) enhancement in burning rate with 2 % nano and micro‐ BaTiO3, respectively.

Section: Propellant Sensitivity Datasupporting

confidence: 92%

Barium Titanate: A Novel Perovskite Oxide Burning Rate Modifier for HTPB/AP/Al Based Composite Propellant Formulations

Jain

Khire

Kandasubramanian

2019

“…Nanooxides could also form the grains of thermite couples with aluminum (for example Al+CuO) that could produce additional heat for the combustion wave . The data on the burning regularities of metalized propellants combustion is rather limited and, in general, includes a qualitative description of appearing effects, like increased rate of n‐Me oxidation in comparison with μ‐Me, large agglomerates in burning products, etc.…”

Section: Introductionmentioning

confidence: 62%

“…The complex chemical mechanism of nitramines decomposition and possible interactions between formed gaseous products and metal additives resulted in the domination of quasi‐equilibrium approach for their description. But such experimental works focused only on a very limited number of substances like Al , Cu , Ni , Al 2 O 3 , TiO 2 , Fe 2 O 3 (more detailed review of such studies is provided in Table ).…”

Section: Introductionmentioning

confidence: 99%

“…Apart from the catalytic action of nano‐sized additives on nitramine decomposition, they could initiate the combustion of larger micron‐sized Al particles. Such effects were reported while using nano‐aluminum (n‐Al) powder and some other additives . Nanooxides could also form the grains of thermite couples with aluminum (for example Al+CuO) that could produce additional heat for the combustion wave .…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Characterization of Aluminum Powders: III. Non‐Isothermal Oxidation and Combustion of Modern Aluminized Solid Propellants with Nanometals and Nanooxides

Gromov

Sergienko

Popenko

et al. 2020

Aluminum powders were comprehensively described as the prospective ingredients of the modern propellants. The paper also studied the influence of micro-and nanopowders of metals (μ-Me and n-Me) and metal oxides (μ-MeO and n-MeO) on the burning process of modern aluminized propellant with HMX, CL-20, AP, and active binder. The following metal additives were used: Al, B, Zn, Ni, Co, and Mo. The effect of the following oxides CoO, V 2 O 5 , MnO 2, and Fe 2 O 3 was studied together with LiF. The combustion tests of modified propellant compositions were carried out in the Vielle bomb in a pressure range 2-10 MPa. n-Me addition resulted in an increase in the burning rate by 10 % for n-B, by 30-40 % for n-Ni and n-Mo in the studied pressure range. The introduction of n-Cu caused a burning rate to increase fivefold. n-Zn additive resulted in increasing of the propellant burning rate by 130 % and 260 % at 4 and 10 MPa, respectively. It was probably caused by the catalytic activity of those metals in the gaseous phase. The effect of complex additive was observed to be insignificant for additives with μ-Co 3 O 4 , μ-V 2 O 5 , μ-Fe 2 O 3 and n-Fe 2 O 3 . The burning rate of propellant with n-CuO additive value was higher by a factor of 4 in comparison with the basic formulation in the studied pressure range.

“…The findings revealed that by increasing the percentage of nano-Co 3 O 4 in the composition,t he end of mix viscosity,t he modulus and the tensile strength increased, whereast he elongation decreased accordingly.T he thermal property data envisaged ar eduction in the decomposition temperature of ammonium perchlorate( AP) as well as formulations based on AP.T he ballistic property data revealed an enhanced burning rate from 6.11mms À1 (reference composition) to 8.99 mm s À1 at 6.86 MPa and am arginal increase in pressure exponent from 0.35 (reference composition) to 0.42 with 1% nano-cobalt oxide. viz.,C o 3 O 4 ,C uO, Fe 2 O 3 ,a nd PbO were investigatedo na luminized AP composite propellant combustion flame structure [17].T he effect of various nanoscale metal oxides on thermal decompositiono fA Ph as also beene xperimentally investigated [18]. Furthermore, the green synthesis of Co 3 O 4 nanoparticle and its application in thermal decomposition of AP as well as kinetics of slow and rapid decompositionh as also been investigated [19].T he effect of mixedo xides of Ni, Cu, Zn, and Cd as MCo 2 O 4 on thermal decomposition of AP,N TO, and HMX has beens tudied by different researchers and reported enhancement in the rate of decomposition [20,21] Because of advantage in reduction of decomposition temperature of ammonium perchlorateb yi ncorporation of nano-cobalt oxide, which ist he main ingredient of ac omposite propellant formulation,a ne xhaustive literature search reveals thatd etailed study has not been carriedo ut on incorporation of nano-Co 3 O 4 in composite propellant formulations.…”

mentioning

confidence: 99%

Evaluation of Nano‐Co₃O₄ in HTPB‐Based Composite Propellant Formulations

Kshirsagar

Jain

Jawalkar

et al. 2016

[a] 1IntroductionComposite propellants are composed of an elastomeric polymeric binder,i nw hich solid particles, such as oxidizer, fuel, and additivesa re incorporated.R ockets and missiles are propelled by composite propellants.T hey basically contain an oxidizer,m ainly ammonium perchlorate (AP), ab inder such as hydroxyl terminated polybutadiene (HTPB), and am etallic fuel like aluminum powder along with certain process aids as well as ballistic modifiers [1]. The burning rate of composite propellants is considered to be one of the most important properties governing the ballistic performance of solid rocket motors,w hich in turn dependsm ostly on particle characteristics of oxidizers, burning rate catalystsa nd metallic fuel [2].T oa chieve the desired burning rate of composite propellant formulations, the amount of oxidizer,p article size of oxidizer,a nd burning rate modifiers are used as variables. AP is used in composite propellantf ormulationsa st he major ingredient (oxidizer) [3] in different size fractions to enhance the burning rate. However,f ine and superfine particle fractions of AP increase the burning rate as well as the propellant slurry viscosity thus casting of slurry becomes difficult [4].Therefore, to cope with suchp roblems, burning rate modifiersa re preferred. The burning rate modifiers are transition metal oxides (TMOs) or their complexes. The burning rate modifiers added in small quantities affect the burning rate by lowering the thermald ecomposition temperature of AP and binder [5].T he effect of transition metal oxides on thermal decomposition of ammonium perchlorate has been studieda nd reviewed in literature [5,6].M any researchersh ave studied in detail the effect of TMOss uch as Fe 2 O 3 ,C uO, Co 2 O 3 ,N iO, and Cr 2 O 3 over ballistic properties of propellant mainly on burning rate behavior and found substantial increase in burning rate [7,8] [16].A lso, the number of nanoscale catalyst, Abstract:D ifferentp ropellant compositions were prepared by incorporatingn ano-sizedc obalt oxide from 0.25 %t o 1% in HTPB/AP/Al-based composite propellant formulations with 86 %s olid loading. The effects on viscosity buildup, thermal, mechanical and ballistic properties were studied. The findings revealed that by increasing the percentage of nano-Co 3 O 4 in the composition,t he end of mix viscosity,t he modulus and the tensile strength increased, whereast he elongation decreased accordingly.T he thermal property data envisaged ar eduction in the decomposition temperature of ammonium perchlorate( AP) as well as formulations based on AP.T he ballistic property data revealed an enhanced burning rate from 6.11mms À1 (reference composition) to 8.99 mm s À1 at 6.86 MPa and am arginal increase in pressure exponent from 0.35 (reference composition) to 0.42 with 1% nano-cobalt oxide.