Investigation of Mechanical Properties of AP/Al/HTPB-Based Propellants using 2-D Digital Image Correlation at Large and Small Scales

Jarocki, Christopher; Manship, Timothy D.; Son, Steven F.

doi:10.2514/6.2022-1896

Cited by 4 publications

(3 citation statements)

References 5 publications

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“…Mcdonald et al [11] observed the aging samples with a scanning electron microscope (SEM), measured the burning rate of the HTPB propellant through a burning test, and studied the aging performance of the HTPB propellant. Christopher M. Jarocki [12] studied the aging behavior of HTPB propellant through 2D digital images and mechanical properties.…”

Section: Introductionmentioning

confidence: 99%

Research on the Aging Properties of HTPB Propellant under Vacuum

Tang

Liao

Deng

et al. 2023

J. Phys.: Conf. Ser.

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The space environment has high vacuum, rapid temperature alternations and other extreme conditions, which can affect the energy, ignition rate and ignition performance of solid propellants in the space environment. In order to obtain the space aging performance of HTPB propellant, this paper investigates the aging performance of HTPB propellant in vacuum environment and compares it with atmospheric pressure, and analyses the oxidative cross-linking, degradation chain scission and “dehumidification” behaviour based on the mechanical properties, cross-sectional state and infrared spectra of propellant before and after aging. The research results show that the anhydrous environment under vacuum prevents the occurrence of the chain scission degradation of HTPB propellant, and HTPB propellant is basically only affected by the oxidative cross-linking reaction, where the reaction rate is slow. The mechanical properties show that the breaking strength increases slightly in the first stage, in the later stage of aging, the oxidative cross-linking reaction was intensified due to the decomposition of AP, and the breaking strength increased obviously compared with the initial value. Under the atmosphere, the HTPB propellant was mainly affected by oxidative cross-linking reaction in the early stage of aging, and the breaking strength increased. In the later stage of aging, due to the chain scission degradation of OA moisture absorption, the breaking strength showed an opposite trend and decreased. In addition, an obvious “dehumidification” phenomenon occurs inside the propellant after aging, which is more obvious under a vacuum.

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Section: Introductionmentioning

confidence: 99%

Research on the Aging Properties of HTPB Propellant under Vacuum

Tang

Liao

Deng

et al. 2023

J. Phys.: Conf. Ser.

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“…The use of the J-integral to evaluate the fracture properties of propellants was proposed. Jarocki et al [12] used noncontact two-dimensional digital images to measure the solid response and temperature of HTPB propellant at different strain rates. Hamidpour et al [13] used the DIC method to measure the fracture behavior of linear viscoelastic materials, using this method to verify his proposed meshless method of analyzing the fracture of viscoelastic materials.…”

Section: Introductionmentioning

confidence: 99%

Study on the Stress–Strain Relationships and Deterioration Modes of HTPB Propellant with Prefabricated Cracks

Gao

2022

Advances in Polymer Technology

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Penetrating cracks with different crack angles were prefabricated in viscoelastic hydroxyl-terminated polybutadiene propellant specimens. Microphotography was performed while tensile tests were conducted on a universal testing machine at tensile rates of 2 mm/min, 10 mm/min, and 500 mm/min. Specimen measurements were obtained by digital image correlation (DIC). The strain fields on the surfaces and around the cracks were studied, and the crack propagation trends for precracked specimens with angles of 0°, 45°, and 75° with respect to the horizontal plane were investigated. Stress–strain curves, tensile microscopic images (50x magnification), and fracture microscopic images (100x magnification) were obtained for different prefabricated crack angles and different stretching rates. It was observed that under low-rate stretching, the propellant crack growth exhibited three stages: a linear stage, a yield stage, and a failure stage. However, the crack propagation in the propellant under high-speed stretching had no yield stage. When there were no prefabricated cracks, a greater tensile rate led to a greater ultimate strain. The maximum strains at the crack tips measured by DIC decreased from group C1 to groups C2, C3, and S. The specimens corresponding to different crack inclination angles are pulled off. It was seen that the closer a crack was to positive breaking, the straighter was the edge notch of the specimen.

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“…A typical solid rocket manufacturing process is divided into three stages: mixing the solid propellant slurry, casting the slurry in the solid rocket motor case, and curing the solid propellant [5]. Because of their desirable mechanical and performance characteristics, AP/Al/HTPBbased solid propellants are widely used in solid rockets [6]. Solid propellants have a wide variety of applications, both military and civil.…”

Section: Introductionmentioning

confidence: 99%

Numerical Study of the AP/Al/HTPB Composite Solid Propellant based Combustion Process in a Small Retro Rocket Motor

Izzat Nazmi Mohd Yaacob,

Balbir Singh,

Norkhairunnisa Mazlan

et al. 2022

ARFMTS

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A numerical investigation of the composite solid propellant-based Combustion Process is performed to characterize the combustion behavior of ammonium perchlorate and Hydroxyl-terminated polybutadiene (HTPB) propellants in a small retro rocket motor. In this analysis, the combustion process is carried out inside the chamber with 71% oxidizer, 15% aluminum, and 14% binder. The effects of using 15% aluminum, particularly focusing on the substantially increased burning rate and composition and sizes of combustion residues are studied. A small solid-propellant-based retro rocket motor with a C-D Nozzle is studied computationally. Consistency is maintained in the boundary conditions and dimensions of the nozzle. The results clearly show a decrease in the temperature, as there is a drop in pressure along the length of the nozzle. On the other hand, due to the energy conservation, the fluid velocity marks a significant increase along the length of the nozzle. This analysis provides an outline of the combustion for small solid rocket internal flow predictions. The computation results show that the combustor carries sustained combustion throughout the process, with a steep rise in temperature near the nozzle exit. There is also a significant decrease in density near the nozzle exit due to the temperature rise. The turbulent kinetic energy also plays a major role here.

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Investigation of Mechanical Properties of AP/Al/HTPB-Based Propellants using 2-D Digital Image Correlation at Large and Small Scales

Cited by 4 publications

References 5 publications

Research on the Aging Properties of HTPB Propellant under Vacuum

Research on the Aging Properties of HTPB Propellant under Vacuum

Study on the Stress–Strain Relationships and Deterioration Modes of HTPB Propellant with Prefabricated Cracks

Numerical Study of the AP/Al/HTPB Composite Solid Propellant based Combustion Process in a Small Retro Rocket Motor

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