COMBUSTION AND FLAME
·
2021
·
IF 4.185
Ke-Juan Meng,Haorui Zhang,Shuai-Zhong Wang,Yi Wang,Qinghua Zhang,Qi-Long Yan
Owing to the novel insensitive high-energy-density material 2,4,6-triamino-5-nitropyrimidine-1,3-dioxide (ICM-102) has lower sensitivity and higher energy(see in Table S1, Supporting Information), it has great advantages in the application of low-vulnerability propellants. In this paper, the evaluation of ICM-102-containing composite propellants has been carried out, where the decomposition and combustion performances of these propellants have been comprehensively investigated. It has been shown that the main exothermic decomposition peak temperature can be increased from 235 ºC to 350 ºC, when 6 to 10 wt% of ICM-102 was used to replace RDX, but heat release rate was largely increased. Moreover, the burning rate of ICM-102 containing propellants at 3 MPa is in the range of 6.97–7.75 mm• s − 1, depending on its content. The pressure exponent (0.5–3 MPa) is between 0.34–0.44. Compared with the typical propellants with RDX, the burn rate and the flame temperature of ICM-102- containing propellants are higher. In addition, the particle size distributions of condensed combustion products of ICM-102 propellants are narrower and smaller than that of RDX-based one. It also shows that extra products such as aluminum carbide (Al20C) and aluminum oxide nitride (Al5O6N) were produced once ICM-102 was used.
研究领域:
材料科学
·
化学工程
✓ 已验证
产品关联
DOI
高影响因子
COMBUSTION AND FLAME
·
2025
·
IF 6.2
Xiaohui Xue,Tuanwei Xu,Bozhi Hu,Wenke Zhang,Jianzhong Liu
In this study, the agglomeration behavior, gaseous combustion products flow velocity and characteristics of condensed combustion products (CCPs) from a HTPB-based solid propellant were systematically investigated under low-pressure and low-temperature conditions. Furthermore, the underlying mechanisms of these environmental effects were discussed. High-speed microscopic imaging was employed to observe and quantify the agglomeration behavior near the burning surface. Meanwhile, the gaseous combustion product stream velocity in this region was analyzed using both kinetic modeling and theoretical calculations. Experimental results show that when pressure decreases from 1 atm to 0.5 atm, the agglomerate occurrence frequency drops by 90.2 %, the average particle size increases by 14.4 %, and the gaseous product velocity rises by 52.1 %. When reducing the ambient temperature from 20 °C to −40 °C leads to an 18.1 % decrease in agglomerate frequency and a 6.5 % reduction in average particle size, while its effect on gaseous velocity remains inconclusive. Characterization of CCPs reveals that both low pressure and low temperature significantly alter the particle size distribution and reduce the combustion efficiency of solid propellants. Within the experimental conditions of this study (0.3 atm to 1 atm, −40 °C to 20 °C), the impact of pressure changes is greater than that of temperature.
研究领域:
航空航天工程
·
燃烧科学
·
材料科学
·
推进技术
✓ 已验证
产品关联
DOI
高影响因子
FUEL
·
2024
·
IF 6.7
Yuhuai Shi,Xuefang Cao,Qiaoni Ren,Tengyue Song,Yuhao Wu,Zhixian Wei,Xiong Cao
This study explores the potential of energetic metal–organic frameworks (E-MOFs) to enhance the combustion performance of solid propellants. A {[Bi 6 O 3 (tza) 5 (NO 3 ) 2 (OH) 5 ]·H 2 O} n (Bi-MOF) incorporating the energetic ligand tetrazole-1-acetic acid (Htza) was synthesized and evaluated for structural characteristics and properties. The catalytic thermal decomposition of cyclotrimethylene trinitramine (RDX) and cyclotetramethylene tetranitramine (HMX) by mixed systems was investigated. These systems consisted of Bi-MOF and copper-iron hetero-metallic compound ({[CuFe 3 O(tza) 6 (H 2 O) 3 ]·Cl·(NO 3 ) 2 ·4H 2 O} n , CuFe-MOF), previously reported by our group in different ratios. The effect of the mixed system with the highest synergy index on the combustion performance of composite modified double-base propellant (RDX-CMDB) and nitrate ester plasticized polyether propellant (HMX-NEPE) was investigated. The impact of varying carbon black (CB) contents on the catalytic performance of the mixed system was also examined. The results showed that Bi-MOF exhibits good thermal stability ( T dec = 226.9 °C) and insensitivity ( IS >40 J, FS >360 J). The mixed system, comprising Bi-MOF and CuFe-MOF in a 2:1 ratio (M 2 ), exhibited the highest synergistic indices (3.35 and 3.24) on thermal decomposition for RDX and HMX. RDX-CMDB and HMX-NEPE propellant formulations containing M 2 and a small amount of CB exhibited significant improvements in combustion performance. RDX-CMDB propellant exhibited up to an 80.6 % increase in burning rate and up to a 59.6 % reduction in pressure index. The pressure indices of NEPE without and with aluminum were reduced from 0.65 and 0.50 to 0.38 and 0.40, respectively (10–20 MPa, 1–20 MPa). These findings highlight the promise of the mixed system, formed by Bi-MOF and CuFe-MOF, as a potential combustion catalyst for RDX-CMDB and HMX-NEPE propellants.
研究领域:
材料科学
·
推进剂化学
·
燃烧学
·
无机功能材料
·
能源材料
·
应用化学
✓ 已验证
DOI
高影响因子
NEW JOURNAL OF CHEMISTRY
·
2020
·Vol. 44
·期 44
·19184-19191
·
IF 3.288
Jing Tu,Heng Xu,Li Liang,Pingyun Li,Xiaode Guo
The problem of debonding the interface between propellant grain and propellant coating has been a tricky problem that has puzzled many scholars. Self-healing adhesives are expected to solve this problem. Herein, we studied the most widely used HTPB system in composite propellants. By adopting free radical polymerized HTPB as the soft segment of the adhesive and introducing aromatic disulfides, we successfully prepared a self-healing polyurethane adhesive. The adhesive can self-heal at a safe temperature of 80 °C, with an elongation at break of more than 700% and a self-healing efficiency of up to 97%, and has excellent thermal stability. The interface self-healing experiment showed that the adhesive can recover the debonding damage at the interface. Our results will provide a new insight into the rebonding of the interface between propellant grain and coating.
研究领域:
材料科学
·
航空航天工程
✓ 已验证
产品关联
DOI
高影响因子
COMBUSTION AND FLAME
·
2020
·
IF 4.57
De-Yun Tang,Zhi-Min Fan,Guangcheng Yang,Yinglei Wang,Pei-Jin Liu,Qi-Long Yan
Aluminum (Al) has been widely used in solid composite propellants (SCPs) to increase the specific impulse. However, Al always subjects to coalescence , sintering to large agglomerations during combustion of SCPs resulting in larger two-phase flow losses. Herein, core-shell μ-Al@M(IO 3 ) x composites have designed and synthesized as a replacement for micron-sized Al (μ-Al) in the Al/AP/RDX/HTPB propellant with tunable combustion behavior. The results show the thermal reactivity and heat releases of SCP are largely enhanced by using these novel metal-based composites. With the inclusion of μ-Al@EGCG@Fe(IO 3 ) 3 (EGCG: Epigallocatechin gallate), the major exothermic peak is reduced by 29.1 °C compared to the reference propellant with a heat release increase up to 5475 J g −1 , exceeding that of the reference sample (86 J g −1 higher). The burn rates are increased with the inclusion of μ-Al@(MIO 3 ) x , while the pressure exponent is higher. The SCP-1 (0.3), SCP-2 (0.18) and SCP-4 (0.25) that have relatively low pressure exponent and high burn rates are good candidates for future applications. The major condensed combustion products (CCPs) of these SCPs are Al 2 O 3 , Al 2.81 O 3.56 N 0.44 , Al 4 C 3 , Al 2 OC, AlN and C 7 H 18 ClN. The agglomeration can be reduced with a minor inclusion of μ-Al@M(IO 3 ) x due to the enhanced interfacial reactions, and the average CCP sizes (0.5 μm for SCP-1 and SCP-4) are even smaller than that of initial μ-Al (1.2 μm).
研究领域:
材料科学
·
燃烧学
✓ 已验证
产品关联
DOI
高影响因子
SURFACE & COATINGS TECHNOLOGY
·
2023
·
IF 5.4
Jiao Li,Jian Zhang,Hongyu Zhang,Xuwen Wang,Taojie Lu,Jiayan Liang,Yulin Yang,Kaifeng Lin,Debin Xia
Interface modification of aluminum particles plays a crucial part in reducing the agglomeration during the combustion of solid propellants . In this study, the aluminum (Al) particles are pretreated with gallic acid (GA) to get Al@GA with an adhesion-favorable surface, which facilitates the further coating procedure. One new fluorine-containing organic substance is prepared, namely p-HFBA. The p-HFBA further coats the Al@GA to produce Al@GA/p-HFBA. The interface between Al@GA and the coating layer p-HFBA forms Al F bonds and induces a pre-ignition reaction with an aluminum oxide shell. Hence, the agglomerate size of propellants containing Al@GA/p-HFBA significantly decreases from 176.30 μm to 84.72 μm. The agglomerates volume is reduced by approximately 97 %. Additionally, more gaseous products investigated by TG-MS provide the Al particles with greater impetus (aerodynamic forces, F ae ), enabling them to leave the burning surface and reduce the residence time. The rise in F ae and drop in adhesion force ( F ad ) effectively reduce the agglomeration intensity according to the skeleton layer model. This work proves that interface modification can effectively enhance the combustion performance of aluminized solid propellants .
研究领域:
材料科学
·
燃烧学
·
化学工程
✓ 已验证
产品关联
DOI
高影响因子
JOURNAL OF PHOTOCHEMISTRY AND PHOTOBIOLOGY A-CHEMISTRY
·
2025
·
IF 4.7
Xueying Sun,Lina Xie,Wenlong Huo,Kaifeng Lin,Yulin Yang,Xuhui Chi,Chengyuan Zhao,Fengtao Zhang,Junzhuo Li,Debin Xia,Jian Zhang
In this study, an organic molecular probe containing an imine (C=N) linkage was synthesized and embedded in a polymethylmethacrylate (PMMA)/polyethylene glycol (PEG) matrix to fabricate a porous optical film for NO 2 gas detection via solid-state UV spectroscopy. Upon exposure to NO 2 , the film exhibited significant spectral changes, with a detection limit as low as 26.45 ppm. Mechanistic investigations revealed that NO 2 induced non-covalent interactions with the probe, triggering structural reorganization and enhanced π-conjugation. Density Functional Theory (DFT) calculations further supported these findings by confirming changes in electronic structure and energy levels. Additionally, preliminary tests demonstrated the feasibility of applying this probe film for aging detection of NEPE propellants, offering a promising non-destructive approach for monitoring propellant health.
研究领域:
材料科学
·
化学
·
环境监测
✓ 已验证
产品关联
DOI
高影响因子
PROPELLANTS EXPLOSIVES PYROTECHNICS
·
2019
·Vol. 45
·期 3
·493-502
·
IF 1.634
Zhicheng He,Zhixun Xia,Jianxin Hu,Likun Ma,Yang Li
To study the mechanical properties of lithium-perchlorate/polyvinyl alcohol-based aluminized electrically controlled solid propellant (LP/PVA-Al-ECSP), the effects of Al particle size, grading, and content on the mechanical properties of the propellant at various temperatures were investigated. The uniaxial tensile experiments were conducted over the temperature range from −40 °C to +50 °C using universal testing machine with a crosshead speed of 100 mm min −1 . A scanning electron microscope (SEM) was employed to observe the fracture surface morphologies of the specimens. The results indicate that Al powder and temperature greatly affects the mechanical properties of the composite propellant. From experiments in which the size and the fine-to-coarse ratio of Al were changed at constant solid loading, the tensile strength and initial modulus of the propellant are improved with the increase of Al particle size and coarse-to-fine ratio at 25 °C. The increase in Al content improves the tensile strength and initial modulus of the propellant, whereas reduces the elongation. The results of experiments in which the temperature changed indicate that the tensile strength and initial modulus of the propellant are improved at low temperatures, whereas the mechanical properties of the propellants deteriorate at high temperatures. The elongation of the propellants is greatly reduced at low temperatures. The stress−strain curve of ECSP shows three regions at low temperatures and five regions at room temperature and high temperatures. The LP/PVA-Al-ECSP has poor tensile strength and initial modulus, whereas its elongation is extremely high at room temperature. The propellant with 5 μm Al to 65 μm Al ratio of 3/7 exhibits the best comprehensive mechanical properties.
研究领域:
材料科学
·
航空航天工程
✓ 已验证
产品关联
DOI
高影响因子
COMBUSTION AND FLAME
·
2017
·
IF 3.663
Yanjing Yang,Fengqi Zhao,Huixiang Xu,Qing Pei,Hanyu Jiang,Jianhua Yi,Chunlei Xuan,Sanping Chen
The reaction mechanisms of metal hydrides in the combustion of solid propellants are closely related to their effects on the energetic and combustion properties of propellants. Here, we report a first attempt to investigate the reaction mechanisms of ZrH 2 , a promising candidate for fuels, in the combustion of HTPB propellants using ammonium perchlorate (NH 4 ClO 4 , AP) as the oxidizer . ZrH 2 is determined to possess a good resistance to the direct oxidation by AP. Thus, it would dehydrogenate independently to generate H 2 and metallic Zr , which is believed to be very favorable for decreasing the gaseous molecular masses . On the other hand, due to the attachment of gaseous reactants to it, ZrH 2 was found to tune the decomposition behaviors of AP by enhancing the generation of NO in the high-temperature decomposition stage. More interestingly, the hydrogen released from ZrH 2 is evaluated to promote the combustion reactions in gaseous phases and be responsible for the two-stage combustion behaviors of the corresponding propellant, which are distinct from those when metallic Al is used as the fuel. The findings in this work validate the potential of ZrH 2 as a fuel for high-energy solid propellants.
研究领域:
推进剂化学
·
燃烧科学
✓ 已验证
DOI
高影响因子
COMBUSTION EXPLOSION AND SHOCK WAVES
·
2017
·Vol. 53
·期 1
·55-64
·
IF 0.889
Liu J.,Liang D.,Xiao J.,Chen B.,Zhang Ya.,Zhou J.,Cen K.
Primary combustion products of boron-based propellants are incomplete combustion products that are emitted from the gas generator of a solid ducted rocket. Studying the composition of primary combustion products provides valuable information about the primary combustion process and also helps to better understand the secondary combustion process. The particle size of the primary combustion products is analyzed by a laser particle size analyzer. The qualitative analysis of the sample composition is performed by using x-ray diffraction, x-ray photoelectron spectroscopy, and thermogravimetry–differential scanning calorimetry experiments. Based on these results, an integrated quantitative analysis of the sample composition is conducted. The quantitative analysis methods include tube furnace heating, ion chromatography, infrared spectroscopy, and inductively coupled plasma chromatography. In addition, scanning electron microscopy and energy dispersive spectrometry are also used to analyze the micro-morphology and distribution of different components in the sample. The primary combustion products mainly contain B, C, B
m
C
n
, H 3 BO 3 , B 2 O 3 , BN, Mg, MgCl 2 , and NH 4 Cl. B
m
C
n
(22–24%), H 3 BO 3 (20%), and B (16.8%) are the three major components, while B
m
C
n
, B, and C (9.8–11.8%) are the three combustible components present in the highest amounts. The oxidant NH 4 ClO 4 is completely consumed during the primary combustion, while the metal additive Mg does not show much reactivity. The micro-morphology and distribution of B
m
C
n
, H 3 BO 3 (or B 2 O 3 ), B, Mg, and C in the sample are investigated. Some components in the primary combustion products are found to be agglomerated, while some components are dispersed. Large particles in the sample mainly include B and Mg, while B
m
C
n
, H 3 BO 3 (or B 2 O 3 ), and C particles are small. In general, the combustion completeness of the primary combustion products is rather low. Therefore, better understanding and controlling of the secondary combustion process is very important to improve the performance of B-based propellants.
研究领域:
化学工程
·
航空航天工程
✓ 已验证
DOI
高影响因子
RSC Advances
·
2023
·Vol. 13
·期 37
·25853-25861
·
IF 3.9
Wenzhe Ma,Yanjing Yang,Yuxin Jia,Dongxiao Fu,Fengqi Zhao,Kangzhen Xu
Metal organic complexes are regarded as a series of promising combustion catalysts for solid rocket propellants. Their effects on the combustion performance of propellants are closely related to the reaction mechanism. Here, the metal–organic complex Cu(Salen) was investigated as a candidate material for the combustion catalyst of the HMX-added composite modified double-base propellant (HMX-CMDB). The combustion performance of the propellant was found to be evidently enhanced in the presence of Cu(Salen) compared with the propellant samples containing Benzoic-Cu or without catalyst. The addition of Cu(Salen) can improve the burning rate and combustion efficiency of the propellant – and greatly reduce the burning rate pressure index. Analysis shows that the addition of Cu(Salen) can increase the combustion area, flame brightness and combustion surface uniformity of the propellant to a higher degree. The sample can spray more beams of bright filaments on the flat combustion section, and the amount of gas generated by decomposition also greatly increases. In addition, Cu(Salen) shows amazing advantages in improving the surface of the propellant and the temperature gradient of the combustion flame.
研究领域:
材料科学
·
燃烧化学
✓ 已验证
产品关联
DOI
PubMed
高影响因子
Polymers
·
2022
·Vol. 14
·期 6
·1124
·
IF 4.967
Chen Shen,Shi Yan,Yapeng Ou,Qingjie Jiao
In this study, fluorinated polyurethane (FPU) was prepared from dialcohol-terminated perfluoropolyether as a soft segment; isophorone diisocyanate (IPDI) as a curing agent; 1,2,4-butanetriol (BT) as a crosslinker; and 1,4-butanediol (BDO) as a chain extender. Fourier transform infrared spectroscopy (FTIR) and1H NMR were used to characterize the structure of the FPU. The mechanical properties of the FPUs with different BDO and BT contents were also measured. The tensile strength and breaking elongation of the optimized FPU formula were 3.7 MPa and 412%, respectively. To find out the action mechanism of FPU on Al, FPU/Al was prepared by adding Al directly to FPU. The thermal decomposition of the FPU and FPU/Al was studied and compared by simultaneous differential scanning calorimetry-thermogravimetry-mass spectrometry (DSC-TG-MS). It was found that FPU can enhance the oxidation of Al by altering the oxide-shell properties. The combustion performance of the FPU propellant, compared with the corresponding hydroxyl-terminated polyether (HTPE)-based polyurethane (HPU) propellant, was recorded by a high-speed video camera. The FPU propellants were found to produce smaller agglomerates due to the generation of AlF3in the combustion process. These findings show that FPU may be a useful binder for tuning the agglomeration and reducing two-phase flow losses of aluminized propellants.
研究领域:
材料科学
·
推进剂研究
✓ 已验证
DOI
高影响因子
危险品化学品经营许可证（带存储）