Effect of AP Particle Size on the Physical Properties of HTPB/AP Propellant

Yim, Yoo Jin; Park, Eun Ji; Kwon, Tae Ha; Choi, Seong Han

doi:10.6108/kspe.2016.20.1.014

Cited by 12 publications

(5 citation statements)

References 2 publications

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“…It was noted that at the end of this reaction propellant was found to be much less viscous with better tensile strength and the ratio was found to be 70:30 [46].…”

Section: Combustion Of First Stage Propellantmentioning

confidence: 95%

Study on geosynchronous satellite launch vehicle propellants and combustion mechanism of each stage

Sangwan

Banik

2023

E3S Web Conf.

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GSLV is a “geosynchronous satellite launch vehicle” which aims at launching space objects into GTO- Geosynchronous transfer orbit. This paper provides a brief idea of the chemistry of propellants used in all three stages and strap-on motors of geosynchronous satellite launch vehicles and their combustion mechanism. It includes all series of GSLVs launched till now and a description of criteria for choosing fuel. This paper also includes a brief description on hydrazine which is a basic part of so many propellant combinations. Furthermore, it includes basic reasons which result in unsuccessful ignition especially at cryogenic. It also emphasizes on reasons for modification in fuels over time and advancement in efficiency obtained due to respective modified fuels, further, giving an overview of future ideas in the development of propellants.

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“…It was noted that at the end of this reaction propellant was found to be much less viscous with better tensile strength and the ratio was found to be 70:30 [46].…”

Section: Combustion Of First Stage Propellantmentioning

confidence: 95%

Study on geosynchronous satellite launch vehicle propellants and combustion mechanism of each stage

Sangwan

Banik

2023

E3S Web Conf.

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“…If the hardening reaction is too quick, the viscosity of the liner increases rapidly. This can lead to a high chance of nonconformity occurrence due to the difficulty of removing bubbles inside the liner when it is spread [8,9].…”

Section: Introductionmentioning

confidence: 99%

The Curing Reaction Rate of the Rocket Motor Liner Based on the Aging of a Curing System

Park

2021

Propellants Explo Pyrotec

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In this study, the hardening reaction speed of a rocket motor liner based on the Aging of a curing system comprised of a hardener and hardening catalyst was investigated. With the increasing Aging time of the curing system, the liner viscosity build-up was accelerated. The raw material having the biggest impact on the hardening reaction of the curing system's liner was triphenylbismuth (TPB). Stirring isophorone diisocyanate and TPB form an ac-tivated complex, and the activated complex facilitates the urethane reaction. If TPB is ligand bound with isocyanate, it forms a TPB-isocyanate complex. This is a type of TPB's oxide, and the formation of the activated complex is visible through changes in its color. In addition, lining hardening time can be adjusted by the Aging period of the curing system through used in this study, and the adhesive strength with the liner and propellant can be improved.

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“…In this case, if defects, such as pores and cracks, exist inside propellant grains, an explosion may accidentally occur owing to an undesired increase in the specific area available for burning [3,4]. Therefore, a low viscosity is preferred for propellants to prevent such defects after mixing the raw materials and to ensure excellent casting quality during the casting process [5,6].…”

Section: Introductionmentioning

confidence: 99%

“…Thus, increasing the input quantities of the solid raw materials is important. In general, APs with two or three different particle sizes are mixed and used, and their mixing ratio is essential for both increasing the input quantities and decreasing viscosity [3,5,6,7]. The AP mixing ratio is also adjusted to change the burn rate of the propellant.…”

Section: Introductionmentioning

confidence: 99%

Effects of Ammonium Perchlorate Particle Size, Ratio, and Total Contents on the Properties of a Composite Solid Propellant

Park

Choi

Kim

et al. 2020

Propellants Explo Pyrotec

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In this study, ammonium perchlorates (APs) with two or more different particle sizes were mixed to optimize the viscosity of the propellant slurry and the burn rate of the resulting solid composite propellants at various mixing ratios. First, to investigate the characteristics of bimodal AP, APs with 200 and 6 μm particles were used. The experimental results showed that the viscosity of the propellant mixture was excellent when the AP‐200 content, i. e., the AP with 200 μm particles, ranged from 55 to 70 wt%, and the burn rate increased with the increasing AP‐6 content. To investigate the characteristics of trimodal AP, three types of APs with 400, 200, and 6 μm particles were used. The findings revealed that the mixing ratio of the three types of APs most favorable to the rheological properties was approximately 1 : 1 : 1. In addition, although adjusting the ratio between large and small particles was desirable for changing the burn rate, varying the ratio between AP‐400 and AP‐200 did not significantly change the burn rate. Adjusting the AP‐6 ratio effectively changed the burn rate. The method of adjusting the AP contents, i. e., the solid contents of propellant, can effectively alter the viscosity and burn rate of propellant. When the total AP content was reduced, the burn rate decreased, but the overall propellant performance degraded. However, the performance parameters of the propellant, such as its density and specific impulse, could be improved by adding solid fuels, such as aluminum.

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Effect of AP Particle Size on the Physical Properties of HTPB/AP Propellant

Cited by 12 publications

References 2 publications

Study on geosynchronous satellite launch vehicle propellants and combustion mechanism of each stage

Study on geosynchronous satellite launch vehicle propellants and combustion mechanism of each stage

The Curing Reaction Rate of the Rocket Motor Liner Based on the Aging of a Curing System

Effects of Ammonium Perchlorate Particle Size, Ratio, and Total Contents on the Properties of a Composite Solid Propellant

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