JOURNAL OF ALLOYS AND COMPOUNDS
·
2025
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IF 6.3
Huanhuan Gao,Jianzhong Liu,Zhihao Sun,Fan Zhang
In-situ assembly of three molecular perovskite energetic materials (DAP-2, DAP-4, and DAN-2) with ammonium perchlorate as the energetic eutectic oxidizer, the performance mechanism of hydroxyl-terminated polybutadiene propellant was investigated. This comprehensive study examined the thermal decomposition behavior and combustion-agglomeration characteristics of the eutectic oxidizers at pressures of 0.1–8.0 MPa. Experimental results demonstrated that the synthesized molecular perovskite energetic eutectic oxidizers exhibited significant redox reactions during thermal decomposition and combustion within the propellant. The reactions were accompanied by releasing superoxide ions, which notably enhanced combustion performance and energy release. The eutectic core-shell structure improved interfacial contact, leading to increased heat and mass transfer efficiency. As a result, shorter combustion times and increased burning rates were observed, with DAP-4 demonstrating the best overall performance among the five energetic materials. Additionally, the average agglomerate sizes ( D 50 ) for RDX, HMX, DAP-2, DAP-4, and DAN-2-based propellants near the burning surface were 161.11 μm, 92.51 μm, 40.64 μm, 30.30 μm, and 41.16 μm, respectively. The agglomeration degree of the propellants based on molecular perovskite energetic materials was significantly lower than that of the RDX and HMX-based propellants. This reduction in agglomeration is attributed to the thin molten skeleton layer and the high-temperature oxidizing gases produced by the molecular perovskite energetic eutectic oxidizers, which effectively suppressed aluminum particle agglomeration near the burning surface. This dual mechanism ultimately resulted in a significant enhancement in propellant performance.
研究领域:
材料科学
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推进剂工程
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热化学
✓ 已验证
产品关联
DOI
高影响因子
ACTA ASTRONAUTICA
·
2024
·
IF 3.1
Yi-min Luo,Teng Ma,Hong-wei Zhao,Nian Yang,Sen Xu,Wen-fang Zheng
Slow-burn propellants are crucial for aerospace advancement. This study focuses on the development of slow-burn propellants by replacing a small amount of AP (3–9 %) with various amine-based burning rate suppressants (BRSs). The consistency between thermal analysis and combustion test results indicates a direct link between the main exothermic decomposition process and combustion performance, with changes in onset temperature positively correlated with decreases in combustion parameters. Upon adding 3 % oxamide, the onset temperature of the main decomposition peak in DSC shifted backward by 16.2 °C, significantly higher than the formulations containing ammonium sulfate at 2.6 °C and ammonium oxalate at −0.8 °C. As the content of oxamide further increased from 3 to 9 %, the ignition delay time increased simultaneously by 0.300–1.638 s, atmospheric burning rate decreased by 14.01–45.45 %. These values represent the maximum among formulations with the same content of the BRSs, mainly attributed to its higher heat absorption capacity .
研究领域:
航空航天工程
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材料科学
✓ 已验证
DOI
高影响因子
PROPELLANTS EXPLOSIVES PYROTECHNICS
·
2018
·Vol. 43
·期 7
·637-641
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IF 1.749
Naimeng Song,Jianchao Liu,Guoying Zhang,Zhenzhan Yan,Hongxu Gao,Li Yang
This paper describes the preparation of two combustion catalysts Tannin-Fe (Ta−Fe) and Phloroglucinol-Fe (Ph−Fe) by spray drying. The particle size and morphology of the particles are observed by scanning electron microscopy (SEM). The results of SEM image show that the particles are regular spherical and very good dispersion. The diameter of most spherical particles is about 1 μm. The effects of Ta−Fe and Ph−Fe on the thermal decomposition of RDX and AP were tested by differential scanning calorimeter (DSC). DSC dates show that Ta−Fe and Ph−Fe can advance the high temperature exothermic peak of AP 18.0 °C and 16.1 °C, respectively. The burning rates illustrates that both Ta−Fe and Ph−Fe can significantly increase the combustion rate of HTPB propellants. The formulation with 2 mass% Ta−Fe shows an average 21.31 % increase in burning rate and has a low value of the exponent n=0.48. The formulation with 2 mass%Ph−Fe has a burning rate 20 to 60 % larger than that of the initial AP/HTPB/Al formulation, and has a lowest exponent n=0.45.
研究领域:
材料科学
·
燃烧与推进
✓ 已验证
产品关联
DOI
高影响因子
COMBUSTION AND FLAME
·
2024
·
IF 5.8
Ming Zhang,Fengqi Zhao,Jiankan Zhang,Ying Wang,Xueli Chen,Ting An,Zhao Qin,Haixia Hao
Graphene iron tannate and graphene iron gallate nanocomposites (G-D-Fe and G-M-Fe) were designed, synthesized and characterized to deal with the performance requirement of AP-HTPB propellent. Effects of the G-D-Fe and G-M-Fe on the thermal decomposition of AP, laser ignition, combustion and safety characteristics of AP-HTPB propellant were explored. By taking Catocene as the benchmark (156.80 mJ), the G-D-Fe improves the safety performance of propellant, and the ignition energy ( E 50 ) is increased by 17.25 mJ. Besides, the G-D-Fe and G-M-Fe have positive effects on enhancing the burning rate and the reducing the pressure exponent of propellant, and the influence of G-D-Fe is more significant. The burning rate enhances from 13.87 to 16.92 mm·s −1 at 15 MPa and the pressure exponent reduces from 0.47 to 0.32 in 4∼15 MPa after the introduction of G-D-Fe. The catalytic mechanism of G-D-Fe were analyzed on the basis of flame morphology, combustion wave structure, in-situ FTIR and gas-phase FTIR-MS. The outstanding catalytic property of G-D-Fe is due to its promotion effect on AP pyrolysis and the formation of stable products, which is conductive to the intense reactions of gas products and the thermal transmission between burning surface and gas phase, and reflecting in the significant enhanced burning rate.
研究领域:
材料科学
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燃烧学
·
推进剂工程
✓ 已验证
产品关联
DOI
高影响因子
FUEL
·
2021
·
IF 6.609
Ming Zhang,Fengqi Zhao,Ying Wang,Xueli Chen,Qing Pei,Huixiang Xu,Haixia Hao,Yanjing Yang,Hui Li
A novel graphene-ferrocene nanocomposite (G-792-Fe) was designed, prepared and characterized systemically using SEM, EDS, FTIR, XPS and RAMAN methods. The as-synthesized G-792-Fe was used as a multifunctional combustion catalyst in ammonium perchlorate-hydroxyl terminated polybutadiene (AP-HTPB) propellant, and the combustion, anti-migration, safety and mechanical performances of AP-HTPB propellant were revealed. The results showed that anchoring on the surface of graphene can effectively inhibit the migration and volatilization of ferrocene compounds in AP-HTPB propellant. The excellent combustion catalytic performance of G-792-Fe on AP-HTPB propellant (burning rate of AP-HTPB propellant containing G-792-Fe increases from 13.87 mm·s −1 to 17.28 mm·s −1 at 15 MPa) is attributed to its positive effect on AP decomposition, which generates more gas-phase products beneficial to the combustion surface thermal feedback and the gaseous REDOX reaction. Additionally, the G-792-Fe presents positive effects on reducing the electrostatic sensitivity and improving the mechanical properties of AP-HTPB propellant. The ignition energy ( E 50 ) and the maximum tensile strength (σ m ) of AP-HTPB propellant containing G-792-Fe were increased by 24.4 mJ and 0.75 MPa respectively, compared with AP-HTPB propellant containing catocene (156.8 mJ and 1.26 MPa). The positive effects of G-792-Fe on safety and mechanical performances of AP-HTPB propellant can be due the outstanding electrical and mechanical properties of graphene-based material. Results of this study have implications concerning design and application of multifunctional combustion catalyst, which can improve the combustion performance, anti-migration performance, safety performance and mechanical properties of AP-HTPB propellant.
研究领域:
材料科学
·
推进剂工程
·
催化化学
✓ 已验证
产品关联
DOI
高影响因子
Surfaces and Interfaces
·
2025
·
IF 6.3
Hongqi Nie,Ruixuan Xu,Xin Li,Yuruizhi Lin,Suhang Chen,Kangzhen Xu,Jia-Rong Zhang,Qi-Long Yan
The combustion characteristics and energy output properties of solid propellants play a decisive role in rocket engine and propulsion system performance. Particularly for HTPB propellant systems incorporating CL-20 as the high-energy oxidizer, achieving wide-range burn rate regulation and maintaining low pressure exponents constitute fundamental requirements for practical implementation. Through advanced interfacial control methodology, this study successfully constructed two types of aluminum/oxidizer integrated composites (Al@AP and Al@CL-20), while employing precise catalysis to accurately distribute C 3 N 4 burn rate modifiers within the target oxidizer. This innovative approach has demonstrated significant enhancement in aluminum combustion efficiency within the composite propellant system. The strategic incorporation of C 3 N 4 , coupled with the optimized interfacial architecture between fuel and oxidizer components, establishes a new paradigm for performance modulation in solid propellant formulations. Thermal analysis (DSC/TGA) results reveal that both Al@AP/CN and Al@CL-20/CN composites exhibit concentrated exothermic characteristics, yet demonstrate fundamentally distinct heat release profiles. By strategically exploiting these differential energy release features, propellant formulations with tailored interfacial compositions and precisely engineered catalytic sites were developed. The modified propellants displayed markedly different combustion behaviors: the Al@CL-20/CN-based formulation achieved a 33% reduction in pressure exponent ( n =0.18) with significantly enhanced low-pressure burning rates, while the Al@AP/CN-modified system maintained ultra-low burning rates (<5 mm·s -1 ) but with high combustion efficiency across broad pressure ranges with an exceptionally low pressure exponent of 0.23. Complementary analysis of condensed combustion products (CCPs) confirmed substantial improvements in combustion completeness, showing a 78% reduction in micron-sized aluminum agglomerates and significantly refined CCPs particle size distribution. These findings collectively demonstrate that the synergistic combination of interfacial modification and precision catalysis effectively optimizes aluminum combustion efficiency and tunability of burn rate of high-energy HTPB propellants.
研究领域:
航空航天工程
·
推进系统
·
材料科学
·
含能材料
·
燃烧化学
✓ 已验证
产品关联
DOI
高影响因子
危险品化学品经营许可证（带存储）