The Influence of Magnetic Fields on the Combustion Processes of Heterogeneous Solid Rocket Propellants

Wolszakiewicz, T.; Gawor, T.; Zalewski, Robert

doi:10.22211/cejem/65025

Cited by 4 publications

(3 citation statements)

References 10 publications

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“…Extensive literature exists on the rate-dependent and temperature-dependent mechanical properties of various propellants. Han [5], Zalewski [6] and Duncan [7] et al studied the quasi-static (< 10 -1 s -1 ) mechanical properties of solid propellants at various temperatures. Long [8] and Ho [9,10] et al examined the mechanical properties of solid propellants at high strain rates (> 10 2 s -1 ).…”

Section: Introductionmentioning

confidence: 99%

Experimental study on self-heating phenomena of CMDB/HTPB propellant under intermediate strain rate compression load

Wang

Zhang

et al. 2023

J. Phys.: Conf. Ser.

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Self-heating behaviour of solid propellants under intermediate strain rate compressive loading have been studied. Effects of two intermediate strain rate (1 s-1 and 150 s-1) of the CMDB/HTPB propellants were investigated. The compression test was conducted using a hydraulic testing machine and the self-heating temperatures were measured by an infrared camera. The results show the following: (1) For CMDB propellant, the surface temperature of specimens rapidly increased at the initial period, then decreased due to the movement of the high temperature region caused by deformation, and then increased again. Finally, the surface temperature slowly decreased due to heat transfer to the surroundings. Infrared thermography showed the formation of a hot spot. Cracks were initiated and gradually expanded to the interior area during compression. (2) For HTPB propellant, the surface temperature of specimens increased slightly. Compared with CMDB specimens, there was no significant damage to HTPB specimens. (3) For both CMDB and HTPB propellants, the temperature distribution of specimens was non-homogeneous. At the centre of the specimen surface, the temperature is the highest. The self-heating temperatures of propellant increased with increasing the strain rate. However, the difference is slight for HTPB propellant, whereas it is considerable for CMDB propellant.

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Section: Introductionmentioning

confidence: 99%

Experimental study on self-heating phenomena of CMDB/HTPB propellant under intermediate strain rate compression load

Wang

Zhang

et al. 2023

J. Phys.: Conf. Ser.

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“…The proportion of solid granules can reach 75 %-80 %, resulting in high impact sensitivity [42]. Moreover, compared to other high-energy solid propellants, the mechanical properties of polymer composite propellants show an obvious strain rate dependency [43][44][45][46][47][48][49]. For instance, Yang et al [7] found that with increasing strain rates, the yield stress improves considerably under dynamic compression of the propellant.…”

Section: Introductionmentioning

confidence: 99%

Low/intermediate speed impact‐induced ignition and damage of a novel high‐energy solid propellant

Chen

et al. 2023

Propellants Explo Pyrotec

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The damage and ignition response of a novel propellant is investigated using a modified split Hopkinson pressure bar (SHPB). The mechanical response of the propellant exhibits strong strain rate dependency following a power law. The whole process from mechanical damage to onset of ignition, deflagration and potential deflagration to detonation transition (DDT) under different strain rates (1000–5000 s−1) is captured via high‐speed photography and digital image correlation (DIC). To clarify the onset and extent of the resulting reaction in terms of the mechanical damage caused by impact, meso‐scale analysis is used to evaluate the propellant before and after dynamic impact loading. The ignition response under impact loading is mainly caused by shear flow, and ignition after multiple impacts due to the reflection of stress waves. Dense debris clouds produced by the first impact are observed in the case of a strain rate of 5000 s−1 leading to DDT when the second impact initiated ignition.

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“…In the course of manufacturing, storage, transportation, ignition, and flight, solid rocket motor (SRM) grain was exposed to stresses such as heat, impact, vibration, acceleration, and ignition pressure [1][2][3]. If the grain's stress and strain levels exceeded acceptable levels, damages like grain fracture, deformation, and other things could happen.…”

Section: Introductionmentioning

confidence: 99%

Biaxial Tensile Mechanical Properties of HTPB Solid Propellant

Jin,

Fang,

Yan

et al. 2023

International Journal of Aerospace Engineering

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The purpose of this work is to study the effects of different loading rate ratios and loading speeds on the biaxial tension of hydroxyl-terminated polybutadiene (HTPB) solid propellant. A proper kind of biaxial tensile specimen with which the stresses in its central part can be obtained with the loads acted on each loading direction is designed and used in the study, and the strains in its central parts are obtained with the digital image correlation (DIC) method. The stress and strain relationship at each direction can be obtained by experiments. The uniaxial stress vs. strain curves and the biaxial stress vs. strain curves were obtained, and it was found that the loading speed remarkably influenced the biaxial tensile behaviors of HTPB propellant. The Mises equivalent stress and strain could be used to describe the biaxial tension stress and strain state, and the exponential constitutive model obtained in the study could be used to predict the stress vs. strain curve under different test conditions.

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The Influence of Magnetic Fields on the Combustion Processes of Heterogeneous Solid Rocket Propellants

Cited by 4 publications

References 10 publications

Experimental study on self-heating phenomena of CMDB/HTPB propellant under intermediate strain rate compression load

Experimental study on self-heating phenomena of CMDB/HTPB propellant under intermediate strain rate compression load

Low/intermediate speed impact‐induced ignition and damage of a novel high‐energy solid propellant

Biaxial Tensile Mechanical Properties of HTPB Solid Propellant

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