CHEMICAL ENGINEERING JOURNAL
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2022
·
IF 16.744
Haifeng Yang,Chuanhao Xu,Weimiao Wang,Pengfei Tang,Xiaodong Li,Shanshan He,Hebin Bao,Shuaishuai Man,Deyun Tang,Xueming Li,Guangcheng Yang,Zhiqiang Qiao
Micro-propulsion underwater technology has been an extensively concerned topic in advanced marine energy systems because of its wide prospects in high-precision prospecting and positioning. Wherein, the design and selection of propellant in energy-supply systems are the key issues to greatly explore its future application. Here, the hydrophobic thermite sticks which contain hydrophobic polytetrafluoroethylene nanoparticles and modified aluminum coated with 1H, 1H, 2H, 2H-perfluorodecyltriethoxysilane shells, were fabricated via a simple direct-writing approach. The modified thermite sticks exhibit stable underwater combustion and self-sustained propagation with a small diameter size (0.94 ± 0.05 mm). In-situ observation shows that the underwater reaction process could be divided into three steps: laser-induction, organic decomposition-dissolution, and thermite reaction. The aging results indicate that the thermite sticks demonstrate an excellent storage stability wherever in air or underwater environments. Simultaneously, it is found that its critical energy required to sustain stable underwater combustion is higher than that in air. Most notably, it not only can be used as the fuels for controllable miniature underwater propulsion, but also can be applied as the energy-delivery materials to expand thrust capacity of vehicles by igniting higher impulse explosives, such as CL-20.
研究领域:
材料科学
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海洋工程
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能源技术
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DOI
高影响因子
ACS Applied Materials & Interfaces
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2020
·
IF 8.758
Xiaoxia Ma,Ke Cao,Xiaona Huang,Shaoran Yang,Yinghua Ye,Ruiqi Shen,Guangcheng Yang,Kaili Zhang
Integrating energetic materials with a microelectromechanical system (MEMS) to achieve miniaturized integrated smart energetic microchips is promising. The potential applications include actuation in lab-on-a-chip devices, ignition in automobile airbags, propulsion and attitude control of micro-/nano-satellites, and miniaturized electro-explosive devices. In this work, a new type of MEMS-compatible energetic arrays was in situ realized on a copper substrate, which comprised a new energetic coordination polymer (ECP; Cu1.5C2N8O2·H2O) with tunable nanostructures and a nano-aluminum (nano-Al) covering layer. The composition, morphology, and energetic characteristics of the energetic arrays can be easily tuned by adjusting the reaction time. The maximum heat release of 1850.2 J/g in thermal analysis and the intense flame in open burning experiment proved its excellent exothermic and combustion performance. A closed-bomb experiment further revealed that the ECP@nano-Al energetic arrays supported on Cu(OH)2 nanorods had a peak pressure (5.5 MPa) and a pressure duration (0.5 s) more than twice those of nanoscale Al/CuO powder because of the introduction of gas elements (e.g., C, H, and N). A preliminary impulse experiment was also conducted through the torsion pendulum method. The displacement of the torsion pendulum in the micrometer scale proved the potential application of the energetic arrays in micropropulsion systems. Overall, this work can serve as a reference for the synthesis and applications of ECPs.
研究领域:
材料科学
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能源工程
✓ 已验证
产品关联
DOI
PubMed
高影响因子
Journal of Energetic Materials
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2016
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IF 1.017
Daolun Liang,Jianzhong Liu,Junhu Zhou,Yang Wang,Yuxin Yang
A microthruster is used for the operation tracking and posture control of microsatellites. In this work, the combustion characteristics and propulsive performance of a boron/ammonium perchlorate (B/AP) propellant mixture for a microthruster were investigated. Amorphous B and AP were used in different mass ratios to prepare the propellant samples. A laser-ignition solid micropropulsion test system was set up, and a differential scanning calorimeter was used. The solid combustion products of the samples with good performance were collected. Microstructural and component analyses of the combustion products were performed. Various performance parameters, including the combustion temperature, combustion velocity, spectral intensity, ignition delay time, thrust, specific impulse, density specific impulse, and heat flow, changed with the fuel–oxidant ratio. The optimal fuel–oxidant mass ratio of the propellant samples was 40%, with a density specific impulse of 0.474 kg/m2•s and a maximum heat flow of 4.4913 mW/mg. Analysis of the combustion products revealed that the clearance between particles significantly diminished after combustion. During combustion, the AP completely decomposed, and a large amount of H3BO3, B2O3, and HBO2 was generated.
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
JOURNAL OF ALLOYS AND COMPOUNDS
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2025
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IF 6.3
Yuxuan Zhou,Keer Ouyang,Yongqi Da,Lingyan Shen,Zhengwu Dong,Zhuotao Song,Jingjie Wang,Xiaoxue Tan,Xiaohong Jiang,Xuran Xu,A.V. Rogachev,D.G. Piliptsou,A.A. Rogachev,M.A. Yarmolenko,Jianbing Xu,Yinghua Ye,Ruiqi Shen
Energetic interfacial films represent a promising encapsulation material for micro- thruster arrays in near-Earth orbit, where their combustion performance under low- pressure or vacuum conditions is critical for practical application. Herein, a uniformly dispersed layered energetic composite film suitable for scalable array encapsulation has been designed via electrospinning technology. The ternary composite energetic film consists of interwoven polyvinylidene fluoride/aluminum/copper oxide (PVDF/Al/CuO) nanofibers. Morphological analysis confirms the effective loading of nanoparticles (Al and CuO) onto the fibers. Energetic films fabricated by this method significantly suppress particle agglomeration. Thermal analysis reveals atmosphere-dependent exothermic pathways. Constant-volume combustion experiments demonstrate that energy release is modulated by film thickness. The evolution of the film ablation flow field has been investigated. Crucially, transient resistance thermometry has for the first time reported the phenomenon of increasing ignition temperature of energetic materials with decreasing pressure under low-pressure conditions. At 1 kPa, the ignition temperature is significantly elevated compared to that at atmospheric pressure. Propagation velocity characterization uncovered a counterintuitive phenomenon: below 10 kPa, 610 μm-thick films exhibit a 42% lower propagation velocity than 270 μm-thick films, a phenomenon termed the thickness-compensation failure effect. An asymmetric heat transfer-dissipation theory is proposed to explain this inversion through geometric thermal management. This work provides crucial experimental evidence and a theoretical foundation for guiding the design of energetic films for vacuum-operating micro-thruster array encapsulation.
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DOI
高影响因子
Micromachines
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2023
·Vol. 14
·期 6
·1219
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IF 3.4
Baosheng Du,Yongzan Zheng,Chentao Mao,Haichao Cui,Jianhui Han,Luyun Jiang,Jifei Ye,Yanji Hong
The transmissive mode laser micro-ablation performance of near-infrared (NIR) dye-optimized ammonium dinitramide (ADN)-based liquid propellant was investigated in laser plasma propulsion using a pulse YAG laser with 5 ns pulse width and 1064 nm wavelength. Miniature fiber optic near-infrared spectrometer, differential scanning calorimeter (DSC) and high-speed camera were used to study laser energy deposition, thermal analysis of ADN-based liquid propellants and the flow field evolution process, respectively. Experimental results indicate that two important factors, laser energy deposition efficiency and heat release from energetic liquid propellants, obviously affect the ablation performance. The results showed that the best ablation effect of 0.4 mL ADN solution dissolved in 0.6 mL dye solution (40%-AAD) liquid propellant was obtained with the ADN liquid propellant content increasing in the combustion chamber. Furthermore, adding 2% ammonium perchlorate (AP) solid powder gave rise to variations in the ablation volume and energetic properties of propellants, which enhanced the propellant enthalpy variable and burn rate. Based on the AP optimized laser ablation, the optimal single-pulse impulse (I)~9.8 μN·s, specific impulse (Isp)~234.9 s, impulse coupling coefficient (Cm)~62.43 dyne/W and energy factor (η)~71.2% were obtained in 200 µm scale combustion chamber. This work would enable further improvements in the small volume and high integration of liquid propellant laser micro-thruster.Keywords:laser micro-ablation;ammonium dinitramide;near-infrared dye;ammonium perchlorate;energy deposition;energy conversion;laser micro-thruster
研究领域:
航空航天工程
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推进技术
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激光物理
✓ 已验证
产品关联
DOI
PubMed
高影响因子
危险品化学品经营许可证（带存储）