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Wyszukujesz frazę "Mehilal, -" wg kryterium: Wszystkie pola

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    Wyświetlanie 1-7 z 7
    Tytuł:
    Application of Twin Screw Extrusion for Continuous Processing of Energetic Materials
    Autorzy:
    Dombe, G.
    Mehilal, D.
    Bhongale, C.
    Singh, P. P.
    Bhattacharya, B.
    Powiązania:
    https://bibliotekanauki.pl/articles/358044.pdf
    Data publikacji:
    2015
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Przemysłu Organicznego
    Tematy:
    twin screw extruder
    energetic materials
    rheology
    safety
    residence time distribution
    Opis:
    Continuous processing of energetic materials using a twin screw extruder is gaining importance as it is a safe and cost-effective alternative to conventional batch processing. The continuous process based on a twin screw extruder combines the capabilities of intensive mixing and high pressure extrusion. It is used for processing a variety of energetic materials, such as gun and rocket propellants, plastic bonded explosives, pyrotechnics, thermo-baric explosives, etc. The twin screw extruder process demands various safety features for the processing of energetic materials. Therefore, exhaustive characterisation of the energetic materials in terms of safety and rheology, coupled with characterisation of the mechanical components of the extruder, are essential for designing a safe continuous process. In this article, a technological overview of continuous processing for energetic materials is presented, along with its various features, process design methodology and safety issues.
    Źródło:
    Central European Journal of Energetic Materials; 2015, 12, 3; 507-522
    1733-7178
    Pojawia się w:
    Central European Journal of Energetic Materials
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Various Methods for the Determination of the Burning Rates of Solid Propellants : an Overview
    Autorzy:
    Gupta, G.
    Jawale, L.
    Mehilal, D.
    Bhattacharya, B.
    Powiązania:
    https://bibliotekanauki.pl/articles/358413.pdf
    Data publikacji:
    2015
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Przemysłu Organicznego
    Tematy:
    burning rate
    composite solid rocket propellant
    acoustic emission system
    erosive burning
    Opis:
    The burning rate of propellants plays a vital role among the parameters controlling the operation of solid rocket motors, therefore, it is crucial to precisely measure the burning rate in the successful design of a solid rocket motor. In the present review, a brief description of the methods for the determination of the burning rate of solid rocket propellants is presented. The effects of various parameters on the burning rate of solid propellants are discussed and reviewed. This review also assesses the merits and limitations of the existing different methods for the evaluation of the burning rate of solid rocket propellants.
    Źródło:
    Central European Journal of Energetic Materials; 2015, 12, 3; 593-620
    1733-7178
    Pojawia się w:
    Central European Journal of Energetic Materials
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Evaluation of Potassium Perchlorate as a Burning Rate Modifier in Composite Propellant Formulations
    Autorzy:
    Jain, S.
    Mehilal, D.
    Singh, P. P.
    Bhattacharya, B.
    Powiązania:
    https://bibliotekanauki.pl/articles/358405.pdf
    Data publikacji:
    2016
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Przemysłu Organicznego
    Tematy:
    composite propellant
    burning rate
    ammonium perchlorate
    potassium perchlorate
    Opis:
    The burning rate of a solid composite propellant is one of its most important ballistic properties. To achieve a specified burning rate, transition metal oxides are used as burning rate modifiers. However, addition of transition metal oxides creates inertness in the composition. To avoid such inertness, an attempt has been made to incorporate potassium perchlorate (KP) as a burning rate modifier by partially replacing ammonium perchlorate (AP), up to the 10% level, and the composition was then studied in detail for its mechanical, thermal and ballistic properties. The data revealed that no change occurred in the case of the mechanical properties, however, the thermal stability decreased as the KP content was increased. The burning rate data revealed that on incorporation of 10% KP, there was an enhancement in the burning rate of up to 35% in comparison to the original composite propellant formulation, but beyond this no enhancement in burning rate was observed, indicating that the optimum content for KP in the composition had been reached.
    Źródło:
    Central European Journal of Energetic Materials; 2016, 13, 1; 231-245
    1733-7178
    Pojawia się w:
    Central European Journal of Energetic Materials
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Studies on the Effect of Nano-MnO2 in HTPB-based Composite Propellant Formulations
    Autorzy:
    Kshirsagar, D. R.
    Jain, S.
    Bhandarkar, S.
    Vemuri, M.
    Mehilal, -
    Powiązania:
    https://bibliotekanauki.pl/articles/951478.pdf
    Data publikacji:
    2017
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Przemysłu Organicznego
    Tematy:
    composite propellant
    nano-manganese dioxide
    pressure exponent
    burning rate
    Opis:
    Various propellant compositions were prepared incorporating fully characterized nano-sized manganese dioxide, from 0.25 wt.% to 1.0 wt.%, in HTPB/AP/Al-based composite propellant formulations having 86 wt.% of solid loading, and its effects on the viscosity build-up, thermal, mechanical and ballistic properties were studied. The findings revealed that on increasing the percentage of nano-MnO2 in the composition, there was an increase in the end of mix viscosity, the modulus and tensile strength, while the elongation decreased accordingly. The data on the thermal properties revealed a reduction in the decomposition temperature of ammonium perchlorate (AP) as well as of the formulations based on it. The data on the ballistic properties revealed that there is an enhancement in the burning rate from 6.11 mm/s (reference composition) to 7.54 mm/s at 6.86 MPa (a 23% enhancement in the burning rate) and an increase in the pressure exponent from 0.35 (reference composition) to 0.42 with 1.0 wt.% nano-MnO2.
    Źródło:
    Central European Journal of Energetic Materials; 2017, 14, 3; 589-604
    1733-7178
    Pojawia się w:
    Central European Journal of Energetic Materials
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Studies on High Burning Rate Composite Propellant Formulations using TATB as Pressure Index Suppressant
    Autorzy:
    Mehilal, -
    Jawalkar, S.
    Kurva, R.
    Sundaramoorthy, N.
    Dombe, G.
    Singh, P. P.
    Bhattacharya, B.
    Powiązania:
    https://bibliotekanauki.pl/articles/951502.pdf
    Data publikacji:
    2012
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Przemysłu Organicznego
    Tematy:
    composite propellant
    ammonium perchlorate
    TATB
    pressure index suppressant
    Opis:
    High burning rate propellant compositions are generally used in gas generators to eject missile from canister. Because of high burning rate, pressure index of the composition increases during burning. To reduce the pressure index, a high burning rate composite propellant formulations (~20 mm/s) based on AP/HTPB/Al have been prepared by incorporating TATB and studied in detail for viscosity build-up, thermal and mechanical properties, sensitivity as well as burning rate and pressure index (n). The data indicate that there is a decrease in end of mix viscosity on increasing the percentage of TATB. The same trend was also observed with mechanical properties while significant improvement in overall thermal stability was clearly observed. The sensitivity data indicate that impact and friction values show decreasing trend infer better safe to handle. The burn rate data reveal that on addition of TATB from 0.5 to 2% decrease in burning rate was not observed while on addition of further TATB up to 5% and beyond this significant decrease in burning rate was observed. The data on pressure index (n) also reveal that TATB is very effective in reducing the 'n' value up to 2% and beyond this 'n' value increases close to standard composition. The data on 'n' value reveal that it reduces from 0.47 to that of standard composition to 0.36 for the compositions containing TATB up to 2.0% in the pressure range of 60-90 kg/cm2.
    Źródło:
    Central European Journal of Energetic Materials; 2012, 9, 3; 237-249
    1733-7178
    Pojawia się w:
    Central European Journal of Energetic Materials
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Experimental Approaches to Develop a High Thrust Ratio in a Single Chamber Dual Thrust Motor Using a Composite Propellant Formulation Based on HTPB/AP/Al
    Autorzy:
    Kurva, R.
    Ukey, S.
    Modgi, M.
    Mehilal, -
    Powiązania:
    https://bibliotekanauki.pl/articles/951488.pdf
    Data publikacji:
    2017
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Przemysłu Organicznego
    Tematy:
    dual thrust ratio
    single chamber
    composite propellant
    high burning rate
    burning surface area
    Opis:
    A high thrust ratio in a single chamber dual thrust motor is required to reach a peak velocity very quickly. To achieve a high thrust ratio in a single chamber dual thrust motor, a composite propellant grain, which acts both as booster and sustainer, based on HTPB/AP/Al (84% solid loading) with low aluminum content and having a burning rate of 25±0.5 mm/s at 7 MPa, was successfully developed. This was studied for viscosity build-up, mechanical and ballistic properties, followed by casting and curing as a single type propellant grain. The high burning surface area was created by making grooves of 3 mm width and 60 mm depth over the surface of the nozzle side of the grain while casting and a prototype, thus obtained, was static tested. The data revealed that a grain with one groove demonstrated a thrust ratio of 8, while two grooves, realized a thrust ratio of 30. The experimental thrust ratio values achieved are also in agreement with the predicted values of the thrust ratio of the same composition.
    Źródło:
    Central European Journal of Energetic Materials; 2017, 14, 4; 917-932
    1733-7178
    Pojawia się w:
    Central European Journal of Energetic Materials
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Composite Propellant Formulation of Poly (16-, 32- and 64-) Azido Dendritic Esters as Energetic Plasticizer and Evaluation of Properties
    Autorzy:
    Yamajala, Kanaka Durga Bhaskar
    Singh, Hema
    Kurva, Ramesh
    Maurya, Mehilal
    Banerjee, Shaibal
    Powiązania:
    https://bibliotekanauki.pl/articles/1062788.pdf
    Data publikacji:
    2020
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Przemysłu Organicznego
    Tematy:
    azido dendrimers
    energetic plasticizer
    composite propellant
    burning rate
    Opis:
    16-, 32- and 64-Polyazido hyperbranched dendrimers were synthesized from hydroxy terminated dendritic ester by following two steps namely, tosylation and azidation. The poly azido dendrimers were incorporated in composite propellant formulations as an energetic plasticizer. The physical, thermal sensitivity and ballistic properties of these composite propellants such as burning rate, Cal-val, density, ignition/decomposition temperature (AET), DSC-TGA, mechanical properties, impact and friction sensitivity were evaluated experimentally while the specific impulse (Isp) and characteristic velocity (C*) were obtained theoretically. A significant enhancement in heat release was noted in the propellant formulation having 16-azido dendritic ester as an energetic plasticizer compared to 32- and 64-azido dendritic esters and a reference composition.
    Źródło:
    Central European Journal of Energetic Materials; 2020, 17, 4; 506-522
    1733-7178
    Pojawia się w:
    Central European Journal of Energetic Materials
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
      Wyświetlanie 1-7 z 7

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