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Junjie Pan, Xin Lin, Zezhong Wang, Ruoyan Wang, Kun Wu, Jinhu Liang and Xilong Yu
This study investigated combustion characteristics of composite fuel grains designed based on a modular fuel unit strategy. The modular fuel unit comprised a periodical helical structure with nine acrylonitrile?butadiene?styrene helical blades. A paraffi...
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Saleh B. Alsaidi, Jeongmoo Huh and Mohamed Y. E. Selim
The performance of two solid biomass wastes, date stone and jojoba solid waste, was experimentally examined for their potential application in combustion and propulsion systems. The fuels were tested in a hybrid rocket-like combustion environment, and th...
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Jan Erik Zeriadtke, Joël Martin and Viola Wartemann
The performance of hybrid rocket engines is significantly influenced by the fuel geometry. Burnback simulations, to determine the fuel surface and fluid volume, are therefore an important tool for preliminary design. This work presents a method for the s...
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Christopher Glaser, Jouke Hijlkema and Jérôme Anthoine
Hybrid rocket propulsion, first demonstrated by the Russian GIRD-09 rocket in 1933, combines liquid oxidizer and solid fuel for thrust generation. Despite numerous advantages, such as enhanced safety, controllability, and potential environmental benefits...
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Yang Liu, Xintong Li, Pengcheng Wang, Xiaotian Zhang, Hao Zhu and Guobiao Cai
This paper proposed a multi-objective, multi-disciplinary design optimization and multi-attribute evaluation method for the manned lunar lander descent stage. A system design model is established considering multiple disciplines such as propulsion, struc...
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Giovanni Fasulo, Luigi Federico, Adolfo Sollazzo, Luciano De Vivo and Roberto Citarella
A rocket?s turbulent jet radiates intense acoustic waves, which are an acoustic load for structural components like payload, launch structure, and rocket avionics, and impact communities near the launch site. Therefore, a careful characterization of the ...
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Hongsheng Yu, Xiaodong Yu, Hongwei Gao, Luigi T. DeLuca, Wei Zhang and Ruiqi Shen
The slow regression rate induced by the high pyrolysis difficulty has limited the application and development of hydroxyl-terminated polybutadiene (HTPB)-based fuels in hybrid rocket propulsion. Nickel oxide (NiO) shows the possibility of increasing the ...
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Ruoyan Wang, Xin Lin, Zezhong Wang, Kun Wu, Zelin Zhang, Jiaxiao Luo, Fei Li and Xilong Yu
The combustion characteristics of a swirl-radial-injection composite fuel grain were experimentally and numerically investigated. This composite grain permits swirl-radial oxidizer injection based on three hollow helical blades, each having a constant ho...
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Tomasz Palacz and Jacek Cieslik
The paper is part of the research aimed at determining if the vortex flow pancake (VFP) hybrid rocket engine is feasible as green in-space chemical propulsion. The objective of this study is to test an N2O/HDPE VFP hybrid ignited with N2O/C3H8 torch igni...
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Tsuyoshi Oishi, Mitsuru Tamari and Takashi Sakurai
Hybrid rockets are safe and inexpensive; however, boundary-layer combustion poses a problem in achieving a fuel regression rate equivalent to that of solid propellants. The fundamental combustion conditions, such as the fuel regression rate of LT421, a p...
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