Precise Regulation of Combustion Characteristics of High-Energy Composite Propellants by Incorporation of CL-20 Crystals Intercalated with Energetic Burn Rate Modifiers

Nie, Hongqi; Wang, Zikangping; Zhang, Xue-Xue; Yang, Su-Lan; Ren, Zhi; Yan, Qi-Long

doi:10.1021/acs.langmuir.3c01240

Cited by 4 publications

(2 citation statements)

References 35 publications

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“…In comparison with conventional oxidizers like AP, RDX, and HMX in solid propellants, hexanitrohexaazaisowurtzitane (CL-20) stands out due to its unique cage molecular structure accommodated with six nitro groups, resulting in a higher density and formation heat. − These properties enhance the performance of CL-20-based propellants, with reported burning rates and specific impulse ( I sp ) significantly exceeding those of HMX- and RDX-based propellants by 35–110%. , However, the CL-20-based aluminized propellants have a very large n which is unfavorable to the stable combustion in rocket motors, and the combustion efficiency is also limited . Therefore, improvement of their combustion performances using the aforementioned fuel/oxidizer interfacial control strategy is significantly necessary.…”

Section: Introductionmentioning

confidence: 99%

Preparation and Reactivity of Core–Shell Al@CL-20 Composites Embedded with Graphene-Based Complexes as Catalysts

Feng,

Yu,

et al. 2024

Langmuir

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Section: Introductionmentioning

confidence: 99%

Preparation and Reactivity of Core–Shell Al@CL-20 Composites Embedded with Graphene-Based Complexes as Catalysts

Feng,

Yu,

et al. 2024

Langmuir

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“…For instance, the insensitive composite of core−shell HMX@GO was synthesized using the solvent−nonsolvent method, resulting in a remarkable reduction in impact sensitivity; e.g., the probability of initiation was reduced from 100% to 10%. 20 Additionally, our research group has demonstrated that modifications of CL-20 using materials such as GO@PDA (polydopamine) 21 and GO-TAGP (a two-dimensional high-nitrogen energetic polymer) 22 would result in largely reduced mechanical sensitivity with maintained energy density. The GO-based materials exert a two-dimensional growth control effect on nitramines, so that the morphology could be well tuned by experimental conditions.…”

Section: Introductionmentioning

confidence: 99%

Functionalized Carbon Nanotube Guided Growth of HMX Crystals with Improved Thermal Stability and Reduced Sensitivity

Wang,

Xiong,

Xue

et al. 2023

Crystal Growth & Design

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This study focuses on the crystal growth of hybrid HMX crystals guided by functionalized carbon nanotubes (F-CNTs) acting as nucleation centers, leading to improved thermal stability and sensitivity. It has been shown that HMX would grow in a form of distinctive needle-like hybrid crystals due to strong interaction with one-dimensional F-CNTs. Notably, under the effect of 0.5 wt % of carbonyl functionalized CNTs, HMX crystals are formed with a length-diameter ratio of 23. Meantime, its decomposition E a is 248.1 kJ•mol −1 , 43% higher than that of HMX. Due to high conductivity and strength of CNTs, the resulting hybrid HMX crystals have 131% higher impact initiation energy compared to the pure ones. Hybrid crystal doped with 0.5 wt % fluorinated carbon nanotube demonstrates the highest heat release values at 1267 J•g −1 , with an approximate 32% increase compared to pure HMX, and follows a random chain scission model (L2).

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Research Progress of Burning Rate Inhibitors in Solid Heterogeneous Propellants

Hu,

Chen,

et al. 2024

Propellants Explo Pyrotec

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The advancement of solid rocket technology has increased demand for high‐performing propellants, particularly in the aerospace industry. Solid propellants are an essential component of rocket engines, and their stable combustion and adjustable burning rate throughout a wide pressure range significantly affect the performance of motors. The burning rate modifiers include catalysts and inhibitors. Solid rocket motors for different purposes require propellants with different burning rates. Using propellants that burn at a slower rate is beneficial for the smooth release of propellant energy, reducing the loss of energy in the process of high burning rate release and improving the endurance time of missile engines. Therefore, it is necessary to decrease the burning rate of propellant. This article summarizes the development of burning rate inhibitors (BRIs) and analyzes the mechanisms and behaviors of different BRIs, including amide‐based compounds, metal salts, and cationic surfactants, that affect the combustion of propellants.

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Precise Regulation of Combustion Characteristics of High-Energy Composite Propellants by Incorporation of CL-20 Crystals Intercalated with Energetic Burn Rate Modifiers

Cited by 4 publications

References 35 publications

Preparation and Reactivity of Core–Shell Al@CL-20 Composites Embedded with Graphene-Based Complexes as Catalysts

Preparation and Reactivity of Core–Shell Al@CL-20 Composites Embedded with Graphene-Based Complexes as Catalysts

Functionalized Carbon Nanotube Guided Growth of HMX Crystals with Improved Thermal Stability and Reduced Sensitivity

Research Progress of Burning Rate Inhibitors in Solid Heterogeneous Propellants

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