Study on cook-off behavior of HTPE propellant in solid rocket motor

Ye, Qing; Yu, Yonggang; Li, Wenfeng

doi:10.1016/j.applthermaleng.2019.114798

Cited by 30 publications

(8 citation statements)

References 8 publications

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“…The advent of technological innovations has led to the increased use of high-performance solid rocket engines, which are equipped with solid propellants of higher density and larger aspect ratios [2,17,18]. In comparison to traditional engines, the alterations in the mesoscopic structure of propellants in these advanced engines, notably the increase in microcracks and micropores, exert a more profound impact on their macroscopic mechanical properties.…”

Section: Introductionmentioning

confidence: 99%

Analysis of thermomechanical coupled accelerated aging of HTPB propellants

Zeng,

Huang,

Chen

et al. 2024

Propellants Explo Pyrotec

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This study employed macroscopic uniaxial compression tests at low and medium strain rates, coupled with microscopic electron microscopy, to extensively analyse the impact of thermomechanical coupled aging on the accelerated aging of Hydroxyl‐terminated Polybutadiene (HTPB) propellants, contrasting it with the effects of isolated factors such as heat and dynamic reciprocating force. Results indicate that at various environmental temperatures (323 K, 343 K, and 363 K), thermomechanical coupled aging more significantly affects HTPB propellants than isolated factors. This effect is macroscopically evident in increased ease of deformation, permanent deformation during aging, continual increase in dissipated energy, and a decrease in average stress and ultimate strain post‐aging. Microscopically, the effect predominantly arises from the interplay between matrix thermal degradation and particle fragmentation, which rapidly accumulate and substantially impact the material's macroscopic mechanical properties. Furthermore, as the aging temperature rises, the alterations in both macroscopic mechanical properties and microscopic morphology of HTPB propellants become more pronounced. However, overly high temperatures may swiftly result in substantial material performance deterioration. Consequently, while elevating temperature effectively accelerates thermomechanical aging, the potential adverse effects on material performance must be judiciously considered. This underscores the necessity of balancing temperature regulation with aging efficiency enhancement in HTPB propellants to ensure effective control and quantitative assessment of the aging process, while minimizing material degradation.

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Section: Introductionmentioning

confidence: 99%

Analysis of thermomechanical coupled accelerated aging of HTPB propellants

Zeng,

Huang,

Chen

et al. 2024

Propellants Explo Pyrotec

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“…Document [5,6] deals specifically with the issues of chemistry and technologies of resin mixtures fabrication for the internal heat-protective rocket solid fuel engine. However, some research papers on thermal protection materials for rocket engines only provide a method of material selection without providing an optimal solution when used on a solidfuel rocket engine [7,8]. Numerous studies have mentioned methods of determining defects for thermal protective coatings, studying materials used to make thermal protective coatings [9][10][11][12].…”

Section: Introductionmentioning

confidence: 99%

Thermal Protection Solution for Solid Fuel Rocket Engines

Phu,

Bien,

Hai

2023

adeletters

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This paper presents a new approach to the thermal protection of solid-fuel rocket engines. The method of thermal protection using coatings not only reduces the risk of damage to the engine casing but also increases the engine’s efficiency in working. Parameters such as thrust and the mass per square meter of the engine casing are used to compare the differences between engines with and without thermal protection coating. Numerical calculation applied to the cruise engine of the rocket 9M39. Calculation results show that the thickness of the thermal protective coating and the thickness of the combustion chamber have been optimized regarding rocket weight. The survey results showed that the mass per square meter of the engine casing decreased by 2.5 times, and the engine’s impulse total increased by 1.13% when using the thermal protective coating. These results are used as data to develop methods to improve the performance of solid propellant rocket engines.

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“…Solid propellants play an important role in the aerospace industry and the military, 1,2 and oxidants, as one of the important components, not only provide the oxygen required in the combustion process but also regulate the combustion rate of solid propellants to ensure their full combustion for high propulsion. 3 Ammonium perchlorate (AP), which is currently the most widely used oxidizer in solid propellants, has excellent characteristics, such as high oxygen content, high gas generation, and high enthalpy of generation, and is low cost; its content can account for more than 70% of the total mass of the propellant, and therefore, its thermal decomposition performance has a great impact on the combustion characteristics of solid propellants.…”

Section: Introductionmentioning

confidence: 99%