An elasto-viscoplastic analysis of direct extrusion of a double base solid propellant

Kalaycıoğlu, Barış; Dirikolu, M. Hüsnü; Çelik, Veli Onur

doi:10.1016/j.advengsoft.2010.07.001

Cited by 24 publications

(7 citation statements)

References 11 publications

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“…Two types of HTPB-AP samples were fabricated: one without a binding agent (Sample 1) and the other with a binding agent Tepanol (Sample 2). Several researchers have used viscoelastic [38,39] as well as elasto-viscoplastic [40,41] constitutive models for energetic materials. Especially, viscoplastic models are used frequently [42][43][44], including Perzyna's viscoplastic model [41], for high strain rate loading conditions.…”

Section: Experimental Measurement Of Constitutive Propertiesmentioning

confidence: 99%

“…Several researchers have used viscoelastic [38,39] as well as elasto-viscoplastic [40,41] constitutive models for energetic materials. Especially, viscoplastic models are used frequently [42][43][44], including Perzyna's viscoplastic model [41], for high strain rate loading conditions. In this work, the constitutive mechanical behavior of the materials, HTPB, AP, and the HTPB-AP interface were modeled using a strain rate dependent power law viscoplastic model.…”

Section: Experimental Measurement Of Constitutive Propertiesmentioning

confidence: 99%

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Simulation guided experimental interface shock viscosity measurement in an energetic material

Prakash

Gunduz

Tomar

2019

Modelling Simul. Mater. Sci. Eng.

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Experimental measurements of interface shock viscosity in hydroxyl-terminated polybutadiene (HTPB)-ammonium perchlorate (AP) material system are performed using mechanical Raman spectroscopy (MRS) combined with laser pulse shock loading. First, HTPB-AP interface level shock wave propagation is studied using the cohesive finite element method. The difference in the shock behavior of the analyzed HTPB-AP interfaces from that of the bulk AP and HTPB material is highlighted by numerical simulations of impacting a single AP particle in an HTPB-AP sample in three different ways: (1) a flyer plate is used to impact the whole HTPB-AP sample; (2) a flat impacter is used to impact the middle of AP particle embedded in HTPB matrix directly; and (3) a HTPB-AP interface is directly impacted with an impacter of radius 1 μm. Shock wave rise time at the interface is shown to differ for the three different impact modes. Based on the simulation results, a combined MRS and pulse laser-induced particle impact test is used for measuring shock viscosity at HTPB-AP interfaces. It is observed that by changing the chemical composition of the interface, shock viscosity can be altered. A modified finite element model with viscous stress based on shock viscosity values added to the stress equation is then used for the shock impact simulation of an HTPB-AP material system. A power law relation was obtained between shock wave rise time and the shock viscosity.

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Section: Experimental Measurement Of Constitutive Propertiesmentioning

confidence: 99%

Section: Experimental Measurement Of Constitutive Propertiesmentioning

confidence: 99%

Simulation guided experimental interface shock viscosity measurement in an energetic material

Prakash

Gunduz

Tomar

2019

Modelling Simul. Mater. Sci. Eng.

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“…Kalaycioglu B et-al carried out a study [60] in which three-dimensional modeling of extrusion forming of a double base solid rocket propellant is performed on a commercially available finite element analysis program. Considering the contact effects and the time dependent viscous and plastic behaviour, the solid propellant is assumed to obey the large deformation elasto-viscoplastic material response during direct extrusion process.…”

Section: Recent Advancesmentioning

confidence: 99%

Desirability and Assessment of Mechanical Strength Characteristics of Solid Propellant for Use in Multi Barrel Rocket Launcher

Bose¹,

Pandey²

2012

IJCEA

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Solid fuel is the first choice to propel the rockets for the area weapon Multi Barrel Rocket Launcher (MBRL) due to ease of design, manufacturing, handling, packaging, transportability and deployability. It also has the capability of prolonged storage without noticeable degradation of its quality. It is also quite safe and does not pose safety hazards. Tactically it suits the requirement of very fast response time and generates high thrust for small duration. Composite modified double base propellant (CMDB) is preferred in MBRL due to wide range of favorable mechanical properties including superior strain capability. Properties of composite propellant may be tailor made by changing the compositions and compound rate. Various failure modes of this propellant are found to be thermal cycling, handling and transport vibrations, ignition shock and pressure loading, launch and flight acceleration, flight maneuver, high speed maneuver, environmental condition etc. All these causes unsymmetrical stress distribution and may lead to failure. Bond strength within the propellant and between the propellant and inhibitor material is very important parameter to control mechanical failure. For safe design the bond strength should be more than the ultimate tensile strength of the propellant. This criterion is satisfied in the present case for the CMDB propellant of MBRL. Index Terms-Composite modified double base propellant, debonding, load-Elongation plot and MBRL.

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“…One of the main operational (ballistic) characteristics of extruded double base propellants, is their high specific impulse and burning rate which could be up to 220 s and 40 mm/s, respectively [10,11]. Furthermore, the extruded DB propellants can be assembled in rocket motor as free standing grains; thus high burning surface area can be achieved [12]. The burning rate and the specific impulse are the main parameters which need to be precisely optimized and evaluated during combustion process to meet specific propulsion requirements (booster, sustainer, or dual thrust rocket motor) [13].…”

Section: Introductionmentioning

confidence: 99%

Certain Ballistic Performance and Thermal Properties Evaluation for Extruded Modified Double-base Propellants

Fahd¹,

Mostafa²,

Elbasuney³

2017

Cent. Eur. J. Energ. Mater.

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Abstract:The main advantages of modified double-base (MDB) propellants are wide range of burning rates, high energy output, as well as enhanced thrust. This study reports on the effect of potential oxidizers − potassium perchlorate (KP) or ammonium perchlorate (AP), stoichiometric binary mixture of the oxidizer (KP or AP) with metal fuel (Al), and energetic nitramine (HMX) on combustion characteristics of MDB propellants. MDB propellant formulations based on these additives, constituting 10 wt.% of total mass of the MDB formulation, were manufactured by solventless extrusion process. The impact of these additives on ballistic performance particularly the burning rate as well as on the characteristic exhaust velocity of gaseous product (C * ), was evaluated using small-scale ballistic evaluation test motor. KP and AP exhibit different effects; KP positively impacts the burning rate, AP positively impacts C * . Stoichiometric binary mixture of AP/ Al positively impacts both the burning rate and C * ; HMX substantially enhances C * . These energetic additives could alter the combustion mechanism, by thinning the induction zone, allowing the luminous flame zone to be more adjacent to the burning surface. Therefore, the combustion reaction could proceed faster. The developed MDB propellant formulations were found to be more energetic with an increase in calorific value in comparison to reference formulation (using bomb calorimeter); they exhibited similar ignition temperature by means of cook off test. DSC measurements demonstrated similar onset and maximum decomposition temperature of developed MDB propellant formulations to reference DB propellant formulation but with an increase in total heat released (J/g).

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An elasto-viscoplastic analysis of direct extrusion of a double base solid propellant

Cited by 24 publications

References 11 publications

Simulation guided experimental interface shock viscosity measurement in an energetic material

Simulation guided experimental interface shock viscosity measurement in an energetic material

Desirability and Assessment of Mechanical Strength Characteristics of Solid Propellant for Use in Multi Barrel Rocket Launcher

Certain Ballistic Performance and Thermal Properties Evaluation for Extruded Modified Double-base Propellants

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