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Additively manufactured aluminium nested composite hybrid rocket fuel grains with breathable blades 期刊论文
VIRTUAL AND PHYSICAL PROTOTYPING, 2023, 卷号: 18, 期号: 1, 页码: e2235680
作者:  Qu DD(屈丹丹);  Lin X(林鑫);  Zhang K(张坤);  Li ZY(李志永);  Wang ZZ(王泽众);  Liu GL(刘国亮);  Meng Y(孟洋);  Luo GX(罗耕星);  Wang RY(王若岩);  Yu XL(余西龙)
Adobe PDF(4980Kb)  |  收藏  |  浏览/下载:160/0  |  提交时间:2023/09/05
Hybrid rocket engine  additive manufacturing  three-dimensional printing  breathable blade  composite fuel grain  mechanical and combustion properties  porous structure  >  
Combustion Characteristics of a Swirl-Radial-Injection Composite Fuel Grain with Applications in Hybrid Rockets 期刊论文
AEROSPACE, 2023, 卷号: 10, 期号: 9, 页码: 19
作者:  Wang RY(王若岩);  Lin X(林鑫);  Wang ZZ(王泽众);  Wu K(吴坤);  Zhang ZL(张泽林);  Luo JX(罗家枭);  Li F(李飞);  Yu XL(余西龙)
Adobe PDF(8125Kb)  |  收藏  |  浏览/下载:77/2  |  提交时间:2023/10/30
hybrid rocket engine  swirl-radial injection  regression rate  flame images  combustion efficiency  
基于多角度辐射成像的固液火箭发动机燃烧特性实验研究 学位论文
硕士论文,北京: 中国科学院大学, 2023
作者:  罗家枭
Adobe PDF(6018Kb)  |  收藏  |  浏览/下载:66/1  |  提交时间:2023/07/06
固液火箭发动机  燃烧特性  多角度辐射成像  模态分解方法  复合式燃料  
Charactering Catalytic Ignition and Combustion for the Ninety Percent Hydrogen Peroxide/Paraffin Based Hybrid Rocket Engine 期刊论文
JOURNAL OF PROPULSION AND POWER, 2023
作者:  Wang ZZ(王泽众);  Lin X(林鑫);  Wu K(吴坤);  Zhang ZL(张泽林);  Fang SH(方思晗);  Meng DD(孟东东);  Li F(李飞);  Yu XL(余西龙)
Adobe PDF(712Kb)  |  收藏  |  浏览/下载:59/2  |  提交时间:2023/04/20
Hybrid Rocket Engines  Propellant  Thermocouples  Numerical Analysis  Catalysis  Absorption Spectroscopy  Combustion Products  decomposition efficiency  Paraffin Fuel  Ignition Systems  
Effects of swirl injection on the combustion of a 11el composite hybrid rocket fuel grain 期刊论文
ACTA ASTRONAUTICA, 2022, 卷号: 199, 页码: 174-182
作者:  Zhang ZL(张泽林);  Lin X(林鑫);  Wang ZZ(王泽众);  Wu K(吴坤);  Luo JX(罗家枭);  Fang SH(方思晗);  Zhang CY;  Li F(李飞);  Yu XL(余西龙)
Adobe PDF(9227Kb)  |  收藏  |  浏览/下载:118/29  |  提交时间:2022/10/23
Hybrid rocket engine  Swirl injection  11el composite fuel grain  Regression rate  Oxidizer-to-fuel ratio  
Effects of swirl injection on the combustion of a novel composite hybrid rocket fuel grain 期刊论文
ACTA ASTRONAUTICA, 2022, 卷号: 199, 页码: 174-182
作者:  Zhang ZL(张泽林);  Lin X(林鑫);  Wang ZZ(王泽众);  Wu K(吴坤);  Luo JX(罗家枭);  Fang SH(方思晗);  Zhang CY(张春元);  Li F(李飞);  Yu XL(余西龙)
Adobe PDF(9227Kb)  |  收藏  |  浏览/下载:97/9  |  提交时间:2022/11/08
Hybrid rocket engine  Swirl injection  Novel composite fuel grain  Regression rate  Oxidizer-to-fuel ratio  
Three-dimensional printed metal-nested composite fuel grains with superior mechanical and combustion properties 期刊论文
VIRTUAL AND PHYSICAL PROTOTYPING, 2022, 卷号: 17, 期号: 3, 页码: 437-450
作者:  Lin X(林鑫);  Qu DD(屈丹丹);  Chen XD(陈雪冬);  Wang ZZ(王泽众);  Luo JX(罗家枭);  Meng DD(孟东东);  Liu GL(刘国亮);  Zhang K(张坤);  Li F(李飞);  Yu XL(余西龙)
Adobe PDF(3694Kb)  |  收藏  |  浏览/下载:111/24  |  提交时间:2022/10/23
Hybrid rocket engine  additive manufacturing  metal-nested composite fuel grain  mechanical properties  combustion properties  optical emission spectroscopy  
基于金属燃料添加方法的固液火箭发动机药柱 专利
发明专利. 基于金属燃料添加方法的固液火箭发动机药柱, 专利号: ZL202110711172.X, 申请日期: 2021-06-25, 授权日期: 2022-06-21
发明人:  林鑫;  王泽众;  张泽林;  李飞;  余西龙
Adobe PDF(769Kb)  |  收藏  |  浏览/下载:94/30  |  提交时间:2022/10/17
Determining the time-resolved mass flow rates of hybrid rocket fuels using laser absorption spectroscopy 期刊论文
ACTA ASTRONAUTICA, 2021, 卷号: 188, 页码: 110-120
作者:  Wang ZZ(王泽众);  Lin X(林鑫);  Li F(李飞);  Peng JL(彭锦龙);  Liu, Yan;  Zhang ZL(张泽林);  Fang SH(方思晗);  Yu XL(余西龙)
Adobe PDF(6496Kb)  |  收藏  |  浏览/下载:274/50  |  提交时间:2021/11/01
Hybrid rocket engine  Fuel mass flow rate  Tunable diode laser absorption spectroscopy  Temperature  Partial pressure  
Characterizing combustion of a hybrid rocket using laser absorption spectroscopy 期刊论文
EXPERIMENTAL THERMAL AND FLUID SCIENCE, 2021, 卷号: 127, 页码: 9
作者:  Fang SH(方思晗);  Wang ZZ(王泽众);  Lin X(林鑫);  Li F(李飞);  Li RJ(李仁杰);  Li, Jing;  Zhang, Zhedian;  Liu, Yan;  Yu XL(余西龙)
Adobe PDF(4367Kb)  |  收藏  |  浏览/下载:515/62  |  提交时间:2021/08/03
Tunable diode laser absorption spectroscopy  Hybrid rocket motor  Temperature  Partial pressure  Combustion efficiency