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    Wyświetlanie 1-3 z 3
    Tytuł:
    Numerical Simulation of the Deflagration to Detonation Transition in Granular High-Energy Solid Propellants
    Autorzy:
    Zhen, Fei
    Wang, Liqiong
    Wang, Zhuoqun
    Powiązania:
    https://bibliotekanauki.pl/articles/951503.pdf
    Data publikacji:
    2019
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Przemysłu Organicznego
    Tematy:
    deflagration to detonation transition
    two-phase reactive flow model
    WENO
    solid volume fraction
    pressure exponent
    Opis:
    This paper describes a one-dimensional code developed for analyzing the two-phase deflagration to detonation transition (DDT) phenomenon in granular high-energy solid propellants. The deflagration to detonation transition model was established based on a one-dimensional two-phase reactive flow model involving basic flow conservation equations and constitutive relations. The whole system was solved using a high resolution 5th-order WENO (Weighted Essentially Non-Oscillatory) scheme for spatial discretization, coupled with a 3rd-order TVD Runge-Kutta method for time discretization, to improve the accuracy and prevent excessive dispersion. An inert two-phase shock tube problem was carried out to access the developed code. The DDT process of high-energy solid propellants was simulated and the parameters of detonation pressure, run distance to detonation and time to detonation were calculated. The results show that for a solid propellant bed with solid volume fraction 0.65, the run distance to detonation was about 120 mm, the detonation induced time was 28 μs, and the detonation pressure was 18 GPa. In addition, the effects of solid volume fraction (φs) and pressure exponent (n) on the deflagration to detonation transition were also investigated. The numerical results for the DDT phenomenon are in good agreement with experimental results available in the literature.
    Źródło:
    Central European Journal of Energetic Materials; 2019, 16, 4; 504-519
    1733-7178
    Pojawia się w:
    Central European Journal of Energetic Materials
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    Viscoelastic Characterization of Different Solid Rocket Propellants Using the Maxwell Spring-Dashpot Model
    Autorzy:
    Shekhar, H.
    Kankane, D. K.
    Powiązania:
    https://bibliotekanauki.pl/articles/358207.pdf
    Data publikacji:
    2012
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Przemysłu Organicznego
    Tematy:
    damping coefficient
    Maxwell model
    rocket propellants
    spring constant
    tensile test
    viscoelastic properties
    Opis:
    A single spring and a single dashpot in series was utilized to simulate the stress-strain curve for different classes of solid rocket propellants, namely extruded double base propellants (EDBP) and composite propellants (CP), in the uniaxial tensile mode in a constant rate of travel machine. The propellant behaves as a viscoelastic material and invariably exhibits stress relaxation, which cannot be simulated by elastic mechanical property parameters. In order to generate a complete stress-strain curve of a solid rocket propellant under tensile testing, different classes of solid rocket propellants were evaluated and the stress-strain curve generated was modelled using the single spring-single dashpot Maxwell fluid model. Using two constants, called the spring constant (K) and the damping factor (D), it was possible to generate a complete stress-strain curve. Mathematical formulation gives the stress (σ) - strain (ε) relation as….[wzór]. Additionally the physical nature of the spring constant resembles that of the elastic constant and the damping coefficient gives the contribution of the viscous part of the load bearing capacity of solid rocket propellants. The development of a general mathematical formulation, the calculation of constants for different classes of propellants and insight into the viscoelastic nature of propellants are the main themes of this article. For all classes of propellants, two ratios are defined. The first is a dimensionless parameter 'H', which is the ratio of the spring constant to the initial elastic modulus. The second is the ratio of the damping coefficient to the spring constant depicted by parameter 'S'. The spring constant is higher than the initial elastic modulus and the value of 'H' is always higher than 1. For brittle propellants (extruded double base propellants, EDBPs, with a high elastic modulus), the spring constant is numerically very close to the spring constant (H is around 1.75). As the ductility (percentage elongation) of the solid rocket propellants increases (from cartridge loaded composite propellants, CLCPs, to case-bonded composite propellants, CBCPs), the value of parameter 'H' also increases (H ~ 10 for CP). For EDBPs the parameter 'S' is smaller (~ 1.24), but for CLCPs and CBCPs, it is high (S ~ 5 to 8). Both of these ratios are basic properties of the polymeric matrix. The first ratio depicts the departure of the actual stress-strain curve from linearity, while the second ratio is another way of expressing the relaxation time. A higher 'H' indicates a softer and more ductile propellant, while a higher 'S' indicates a shorter relaxation time for the propellant. A lower 'S' indicates that the propellant recovers faster on removal of strain.
    Źródło:
    Central European Journal of Energetic Materials; 2012, 9, 3; 189-199
    1733-7178
    Pojawia się w:
    Central European Journal of Energetic Materials
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
    Tytuł:
    A Study on Creep Behavior of Composite Solid Propellants Using the Kelvin-Voigt Model
    Autorzy:
    Bihari, B. K.
    Rao, N. P. N.
    Gupta, M.
    Murthy, K. P. S.
    Powiązania:
    https://bibliotekanauki.pl/articles/358395.pdf
    Data publikacji:
    2017
    Wydawca:
    Sieć Badawcza Łukasiewicz - Instytut Przemysłu Organicznego
    Tematy:
    mechanical properties
    viscoelasticity
    propellant
    creep
    DMA
    Opis:
    A Kelvin-Voigt model consisting of a spring and a dashpot in parallel was applied for the viscoelastic characterization of solid rocket propellants. Suitable values of spring constants and damping coefficients were employed by a least squares fit of the errors to generate creep curves using a Dynamic Mechanical Analyzer (DMA) for composite solid propellants. Three different composite propellant formulations based on HTPB/AP/Al having burning rates of 5 mm/s, 15 mm/s and 20 mm/s were tested under different stress levels varying from 0.1 MPa to 3 MPa and at different temperatures varying from 35 °C to 85 °C. Creep behavior with recovery was studied and analyzed to evaluate the viscoelastic properties. The change in spring constants, representing elastic deformation, was very small compared to the damping coefficients for the propellants studied. For a typical propellant formulation, when the stress level was increased, the spring and damping coefficient both increased significantly whereas for an increase in temperature, they remained nearly constant. However, the ratio E/η was observed to be constant and independent of stress level. It was also observed that the variation of E and η varied linearly with increase in stress whereas their ratio showed a logarithmic variation. A mathematical correlation was developed to evaluate the viscoelastic properties during creep of composite propellants.
    Źródło:
    Central European Journal of Energetic Materials; 2017, 14, 3; 742-756
    1733-7178
    Pojawia się w:
    Central European Journal of Energetic Materials
    Dostawca treści:
    Biblioteka Nauki
    Artykuł
      Wyświetlanie 1-3 z 3

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