The Experts below are selected from a list of 1977 Experts worldwide ranked by ideXlab platform
Amarjit Singh - One of the best experts on this subject based on the ideXlab platform.
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Advanced Concepts of the Propulsion System for the Futuristic Gun Ammunition
2016Co-Authors: R. S. Darnse, Amarjit SinghAbstract:This review paper reports various concepts of the Gun propulsion system to meet the goal of the futuristic hypervelocity projectiles. The nonconventional concepts, such as liquid Gun Propellant, rail Gun, coil Gun, electrothermal Gun, electrothermal chemical Gun along with conventional energetic solid Gun Propellant have been discussed. Even though muzzle velocity around 2000 m/s has been claimed to be achieved using such nonconventional propulsion systems, it will take quite some time before such systems are in regular use in the battlefield. Hence, solid Gun Propellants containing novel energetic ingredients (binders, plasticisers, and oxidisers) would continue to be used in the near future and are expected to meet the requirements of the futuristic Gun ammunition
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Study of N-n-butyl-N-(2-nitroxyethyl)nitramine in RDX based Gun Propellant
Journal of Hazardous Materials, 2009Co-Authors: R.s. Damse, T K Chakraborthy, B. Omprakash, B.g. Tope, Amarjit SinghAbstract:The current trend in the development of Gun Propellant is to replace the non-energetic plasticizers with the energetic plasticizer. This leads to better energetic performance of Gun Propellant. The purpose of the present paper is to explore the possibility of enhancing the ballistic performance of RDX based Gun Propellant by incorporating an energetic plasticizer into the Propellant composition. Compositions containing N-n-butyl-N-(2-nitroxyethyl)nitramine (Bu-NENA) as an energetic plasticizer with varying percentage of RDX have been studied theoretically and experimentally. Performance in terms of ballistic parameters, sensitivity, thermal characteristics, stability and mechanical properties was evaluated and compared with the vis-a-vis compositions containing dioctylphthalate as a non-energetic plasticizer. Experimental data on comparative study indicates that Bu-NENA based Propellants are superior to DOP based Propellants in respect of ballistic performance.
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Evaluation of Energetic Plasticisers for Solid Gun Propellant
Defence Science Journal, 2008Co-Authors: R.s. Damse, Amarjit SinghAbstract:This paper reports the evaluation of four different energetic plasticisers, viz., glycidyl azidepolymer (GAP, MW = 390), 1,5-diazido-3-nitrazapentane (DANPE), ethylene-glycol-bis-azido-acetate (EGBAA) and N-n-butyl-N-(2 nitroxyethyl) nitramine (n-Bu-NENA) separately into highenergy Gun Propellant containing 28 per cent NC (13.1 N %), 65 per cent RDX, 6 per cent di-octyl-phthahate (DOP) and 1 per cent carbamite. Four different Propellant compositions based on theenergetic plasticiser have been formulated separately with the replacement of non-energeticplasticiser, DOP. The Propellants were processed by standard solvent method and evaluatedexperimentally along with the control composition to determine the ballistic parameters, cal-val,sensitivity, thermal characterisation, thermal stability and mechanical properties. The performanceof the Propellants containing the energetic plasticiser has been compared with that of thecontrol composition containing the non-energetic plasticiser, DOP so as to assess the suitabilityof the energetic plasticiser for the futuristic Gun Propellant formulations. It has been found outthat n-Bu-NENA is the superior plasticiser among the four energetic plasticisers evaluated inthis study. Defence Science Journal, 2008, 58(1), pp.86-93 , DOI:http://dx.doi.org/10.14429/dsj.58.1627
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Feasibility Study of Processing Estane-based LOVA Gun Propellant
Defence Science Journal, 2007Co-Authors: M.a.r. Shaikh, T K Chakraborthy, R R Sanghavi, S. D. Shelar, Amarjit SinghAbstract:Low vulnerability ammunition (LOVA) Propellant are currently being developed globally toreplace all types of single-base, double-base and triple-base Gun Propellants, because LOVAPropellants possess advantage like low vulnerability without compromising on ballistic properties.The objective of present study is to establish processing of thermoplastic elastomer (TPE);estane-based LOVA Gun Propellant in cord/heptatubular geometry. Keeping in view variousadvantages of TPE such as simple processing, greater dimensional stability, lower productionlosses, superior insensitivity, and mechanical properties of the Propellants, estane 5731(polyurethane-ester-MDI, aromatic polyester) is selected for feasibility study as a binder inLOVA-based Gun Propellant composition, processed by solvent and semi-solvent methods andcompared feasibility of processing as well as their evaluation wrt ballistics, vulnerability, andmechanical properties. The results indicate that Gun Propellants processed by semi-solventmethod and extruded at elevated temperatures exhibit better ballistics, mechanical, andvulnerability properties.
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HMX based enhanced energy LOVA Gun Propellant.
Journal of Hazardous Materials, 2007Co-Authors: R R Sanghavi, M.a.r. Shaikh, S. D. Shelar, P J Kamale, K. Sunil Kumar, Amarjit SinghAbstract:Abstract Efforts to develop Gun Propellants with low vulnerability have recently been focused on enhancing the energy with a further improvement in its sensitivity characteristics. These Propellants not only prevent catastrophic disasters due to unplanned initiation of currently used Gun Propellants (based on nitrate esters) but also realize enhanced energy levels to increase the muzzle velocity of the projectiles. Now, in order to replace nitroglycerine, which is highly sensitive to friction and impact, nitramines meet the requirements as they offer superior energy due to positive heat of formation, typical stoichiometry with higher decomposition temperatures and also owing to negative oxygen balance are less sensitive than stoichiometrically balanced NG. RDX has been widely reported for use in LOVA Propellant. In this paper we have made an effort to present the work on scantily reported nitramine HMX based LOVA Gun Propellant while incorporating energetic plasticizer glycidyl azide polymer to enhance the energy level. HMX is known to be thermally stable at higher temperature than RDX and also proved to be less vulnerable to small scale shaped charge jet attack as its decomposition temperature is 270 °C. HMX also offers improved impulse due to its superior heat of formation (+17 kcal/mol) as compared to RDX (+14 kcal/mol). It has also been reported that a break point will not appear until 35,000 psi for Propellant comprising of 5 μm HMX. Since no work has been reported in open literature regarding replacement of RDX by HMX, the present studies were carried out.
R.s. Damse - One of the best experts on this subject based on the ideXlab platform.
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Study of N-n-butyl-N-(2-nitroxyethyl)nitramine in RDX based Gun Propellant
Journal of Hazardous Materials, 2009Co-Authors: R.s. Damse, T K Chakraborthy, B. Omprakash, B.g. Tope, Amarjit SinghAbstract:The current trend in the development of Gun Propellant is to replace the non-energetic plasticizers with the energetic plasticizer. This leads to better energetic performance of Gun Propellant. The purpose of the present paper is to explore the possibility of enhancing the ballistic performance of RDX based Gun Propellant by incorporating an energetic plasticizer into the Propellant composition. Compositions containing N-n-butyl-N-(2-nitroxyethyl)nitramine (Bu-NENA) as an energetic plasticizer with varying percentage of RDX have been studied theoretically and experimentally. Performance in terms of ballistic parameters, sensitivity, thermal characteristics, stability and mechanical properties was evaluated and compared with the vis-a-vis compositions containing dioctylphthalate as a non-energetic plasticizer. Experimental data on comparative study indicates that Bu-NENA based Propellants are superior to DOP based Propellants in respect of ballistic performance.
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suitability of nitrogen rich compounds for Gun Propellant formulations
Journal of Hazardous Materials, 2009Co-Authors: R.s. Damse, A K SikderAbstract:This paper reports the suitability of a novel nitrogen rich compound, guanidinium-5-aminotetrazolate for RDX-based high-energy Gun Propellant formulations in respect of flame temperature as well as the burning rate characteristics. It has been found that the partial replacement of RDX with guanidinium-5-amino tetrazolate at the rate of five parts decreases the flame temperature of the Propellant by about 120 K without adversely affecting the burning rate characteristics, i.e. linear rate of burning co-efficient and pressure exponent.
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thermoanalytical screening of nitrogen rich compounds for ballistic requirements of Gun Propellant
Journal of Propulsion and Power, 2009Co-Authors: R.s. Damse, Mrinal Ghosh, Nilesh H Naik, A K SikderAbstract:This study reports the suitability of nitrogen-rich compounds for Gun-Propellant formulations in regard to flame temperature and burning-rate characteristics. Nine different nitrogen-rich compounds [guanidinium nitrate, triaminoguanidinium nitrate, triaminoguanidinium azide, guanidinium azotetrazolate, triaminoguanidinium azotetrazolate, hydrazinium azotetrazolate, 3, 3’-azobis (6-amino-1, 2, 4, 5-tetrazine), 3, 6-dihydrazino-1, 2, 4, 5tetrazine, and guanidinium-5-aminotetrazolate] have been studied on the basis of gas-phase thermal analysis to investigate the decomposition pathways. The decomposition mechanism as elucidated for each nitrogen-rich compound has been examined, discussed, and contrasted with an aim to identify the suitable candidates favoring the lower-burning-rate characteristics for the Gun-Propellant formulations. The suitability has been validated on the basis of closed-vessel testing of selected nitrogen-rich compounds from the preceding.
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role of inorganic additives on the ballistic performance of Gun Propellant formulations
Journal of Hazardous Materials, 2008Co-Authors: R.s. Damse, A K SikderAbstract:This paper explores the possibility of increasing the ballistic performance of Gun Propellant with the addition of inorganic additives viz. aluminium and ammonium perchlorate. Compositions based on Propellant NQ containing additional aluminium and ammonium perchlorate in different parts were studied theoretically and experimentally. Performance in respect of ballistic parameters, sensitivity, thermal characteristics, thermal stability and mechanical properties are evaluated and compared with that of the conventional triple base Propellant NQ. Experimental data on comparative study indicate that the compositions containing aluminium and ammonium perchlorate are superior to Propellant NQ in respect of energy.
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Evaluation of Energetic Plasticisers for Solid Gun Propellant
Defence Science Journal, 2008Co-Authors: R.s. Damse, Amarjit SinghAbstract:This paper reports the evaluation of four different energetic plasticisers, viz., glycidyl azidepolymer (GAP, MW = 390), 1,5-diazido-3-nitrazapentane (DANPE), ethylene-glycol-bis-azido-acetate (EGBAA) and N-n-butyl-N-(2 nitroxyethyl) nitramine (n-Bu-NENA) separately into highenergy Gun Propellant containing 28 per cent NC (13.1 N %), 65 per cent RDX, 6 per cent di-octyl-phthahate (DOP) and 1 per cent carbamite. Four different Propellant compositions based on theenergetic plasticiser have been formulated separately with the replacement of non-energeticplasticiser, DOP. The Propellants were processed by standard solvent method and evaluatedexperimentally along with the control composition to determine the ballistic parameters, cal-val,sensitivity, thermal characterisation, thermal stability and mechanical properties. The performanceof the Propellants containing the energetic plasticiser has been compared with that of thecontrol composition containing the non-energetic plasticiser, DOP so as to assess the suitabilityof the energetic plasticiser for the futuristic Gun Propellant formulations. It has been found outthat n-Bu-NENA is the superior plasticiser among the four energetic plasticisers evaluated inthis study. Defence Science Journal, 2008, 58(1), pp.86-93 , DOI:http://dx.doi.org/10.14429/dsj.58.1627
Jiaoxia Zhang - One of the best experts on this subject based on the ideXlab platform.
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thermomechanical investigation on the effect of nitroguanidine on the thermal expansion coefficient and glass transition temperature of double base Gun Propellant
Journal of materials research and technology, 2019Co-Authors: Jiahao Liang, Zhongliang Xiao, Jiaoxia Zhang, Mengyao Dong, Zhanhu Guo, Jincheng Fan, Tao DingAbstract:Abstract Thermal expansion coefficient (CTE) is a critical parameter of Gun Propellant because of its major role in fabrication, storage and combustion performance of the Propellant. Further, controlling the CTE of the Propellant is an effective solution to improve its loading density. Therefore, it is important to understand the thermal expansion of the Propellant. To obtain the linear CTE of insensitive Gun Propellant, different weight percentages of NQ are added to the B# double-base absorbent Propellant, the thermal mechanical analyzer (TMA) is employed to estimate their dimensional change over the temperature range of 213–323 K. The pure NQ flaky Gun Propellant exhibits a negative thermal expansion with a linear CTE of −2.006 × 10−4 mm/mm K−1. The results show that the linear CTE of the B# double-base absorbent Propellant is decreased by 53.74% as the concentration of NQ is increased to 30%, whereas the glass transition temperature increases with increasing the NQ content.
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experimental study on thermal expansion coefficient of composite multi layered flaky Gun Propellants
Composites Part B-engineering, 2019Co-Authors: Taixin Liang, Le Qi, Zhongliang Xiao, Jiaoxia Zhang, Tao Ding, Yang Wang, Na LuAbstract:Abstract Improving the burning progressivity is an effective approach to improve the muzzle velocities of projectile of a Gun. Composite multi-layered flaky Gun Propellant is a combination of a fast-burning inner layer and a slow-burning outer layer. It has an obvious burning progressivity which decreases the pressure in bore and increases the muzzle velocity, thus this characteristic is widely concerned by the research of Gun Propellant. The thermal expansion coefficient of composite multi-layered Gun Propellant has a significant influence on the combustion performance. Therefore, understanding the thermal expansion properties of the composite multi-layered Gun Propellant is important. In this study, the thermal expansion coefficients were measured by thermal mechanical analyzer (TMA) for a three-layered flaky Gun Propellant, and the influence of laminating and coating flaky Gun Propellant on thermal expansion coefficient was investigated. The results showed that the slow-burning layers had a higher thermal expansion coefficient than the faster-burning layers, the thermal expansion coefficient of slow-burning layers was 4–5 times bigger than that of fast-burning layers, and the order of magnitudes was 1 × 10−5 K−1. The laminating and coating had a great influence on the thermal expansion coefficient of flaky Gun Propellant, the thermal expansion coefficient of laminate sample was 10 times greater than that of the original sample, and the order of magnitudes for two layers and three layers Propellant reached 1 × 10−4 K−1. Furthermore, the theoretical relations between the thermal expansion coefficient of axial and the thermal expansion coefficient of the fast and slow burning layer were derived.
A K Sikder - One of the best experts on this subject based on the ideXlab platform.
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suitability of nitrogen rich compounds for Gun Propellant formulations
Journal of Hazardous Materials, 2009Co-Authors: R.s. Damse, A K SikderAbstract:This paper reports the suitability of a novel nitrogen rich compound, guanidinium-5-aminotetrazolate for RDX-based high-energy Gun Propellant formulations in respect of flame temperature as well as the burning rate characteristics. It has been found that the partial replacement of RDX with guanidinium-5-amino tetrazolate at the rate of five parts decreases the flame temperature of the Propellant by about 120 K without adversely affecting the burning rate characteristics, i.e. linear rate of burning co-efficient and pressure exponent.
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thermoanalytical screening of nitrogen rich compounds for ballistic requirements of Gun Propellant
Journal of Propulsion and Power, 2009Co-Authors: R.s. Damse, Mrinal Ghosh, Nilesh H Naik, A K SikderAbstract:This study reports the suitability of nitrogen-rich compounds for Gun-Propellant formulations in regard to flame temperature and burning-rate characteristics. Nine different nitrogen-rich compounds [guanidinium nitrate, triaminoguanidinium nitrate, triaminoguanidinium azide, guanidinium azotetrazolate, triaminoguanidinium azotetrazolate, hydrazinium azotetrazolate, 3, 3’-azobis (6-amino-1, 2, 4, 5-tetrazine), 3, 6-dihydrazino-1, 2, 4, 5tetrazine, and guanidinium-5-aminotetrazolate] have been studied on the basis of gas-phase thermal analysis to investigate the decomposition pathways. The decomposition mechanism as elucidated for each nitrogen-rich compound has been examined, discussed, and contrasted with an aim to identify the suitable candidates favoring the lower-burning-rate characteristics for the Gun-Propellant formulations. The suitability has been validated on the basis of closed-vessel testing of selected nitrogen-rich compounds from the preceding.
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role of inorganic additives on the ballistic performance of Gun Propellant formulations
Journal of Hazardous Materials, 2008Co-Authors: R.s. Damse, A K SikderAbstract:This paper explores the possibility of increasing the ballistic performance of Gun Propellant with the addition of inorganic additives viz. aluminium and ammonium perchlorate. Compositions based on Propellant NQ containing additional aluminium and ammonium perchlorate in different parts were studied theoretically and experimentally. Performance in respect of ballistic parameters, sensitivity, thermal characteristics, thermal stability and mechanical properties are evaluated and compared with that of the conventional triple base Propellant NQ. Experimental data on comparative study indicate that the compositions containing aluminium and ammonium perchlorate are superior to Propellant NQ in respect of energy.
Tao Ding - One of the best experts on this subject based on the ideXlab platform.
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thermomechanical investigation on the effect of nitroguanidine on the thermal expansion coefficient and glass transition temperature of double base Gun Propellant
Journal of materials research and technology, 2019Co-Authors: Jiahao Liang, Zhongliang Xiao, Jiaoxia Zhang, Mengyao Dong, Zhanhu Guo, Jincheng Fan, Tao DingAbstract:Abstract Thermal expansion coefficient (CTE) is a critical parameter of Gun Propellant because of its major role in fabrication, storage and combustion performance of the Propellant. Further, controlling the CTE of the Propellant is an effective solution to improve its loading density. Therefore, it is important to understand the thermal expansion of the Propellant. To obtain the linear CTE of insensitive Gun Propellant, different weight percentages of NQ are added to the B# double-base absorbent Propellant, the thermal mechanical analyzer (TMA) is employed to estimate their dimensional change over the temperature range of 213–323 K. The pure NQ flaky Gun Propellant exhibits a negative thermal expansion with a linear CTE of −2.006 × 10−4 mm/mm K−1. The results show that the linear CTE of the B# double-base absorbent Propellant is decreased by 53.74% as the concentration of NQ is increased to 30%, whereas the glass transition temperature increases with increasing the NQ content.
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experimental study on thermal expansion coefficient of composite multi layered flaky Gun Propellants
Composites Part B-engineering, 2019Co-Authors: Taixin Liang, Le Qi, Zhongliang Xiao, Jiaoxia Zhang, Tao Ding, Yang Wang, Na LuAbstract:Abstract Improving the burning progressivity is an effective approach to improve the muzzle velocities of projectile of a Gun. Composite multi-layered flaky Gun Propellant is a combination of a fast-burning inner layer and a slow-burning outer layer. It has an obvious burning progressivity which decreases the pressure in bore and increases the muzzle velocity, thus this characteristic is widely concerned by the research of Gun Propellant. The thermal expansion coefficient of composite multi-layered Gun Propellant has a significant influence on the combustion performance. Therefore, understanding the thermal expansion properties of the composite multi-layered Gun Propellant is important. In this study, the thermal expansion coefficients were measured by thermal mechanical analyzer (TMA) for a three-layered flaky Gun Propellant, and the influence of laminating and coating flaky Gun Propellant on thermal expansion coefficient was investigated. The results showed that the slow-burning layers had a higher thermal expansion coefficient than the faster-burning layers, the thermal expansion coefficient of slow-burning layers was 4–5 times bigger than that of fast-burning layers, and the order of magnitudes was 1 × 10−5 K−1. The laminating and coating had a great influence on the thermal expansion coefficient of flaky Gun Propellant, the thermal expansion coefficient of laminate sample was 10 times greater than that of the original sample, and the order of magnitudes for two layers and three layers Propellant reached 1 × 10−4 K−1. Furthermore, the theoretical relations between the thermal expansion coefficient of axial and the thermal expansion coefficient of the fast and slow burning layer were derived.