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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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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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Shuyuan Liu, Yu Zhang, Limin Wang, Zhengchun Chen and Songqi Hu
The effect of mixing on coupled heat release and transfer performance of a novel segregated solid motor is numerically evaluated with a transient two-dimensional combustion model. The results show that vortex structures are formed and evolved in the comb...
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Sholpan G. Giniyatova, Rafael I. Shakirzyanov, Yuriy A. Garanin, Nurzhan A. Sailaukhanov, Artem L. Kozlovskiy, Natalia O. Volodina, Dmitriy I. Shlimas and Daryn B. Borgekov
Ceramics based on zirconium dioxide are very important compounds for dental, implant, and structural material applications. Despite the fact that tetragonally stabilized YSZ has been well studied, the search for new compositions of zirconia-based ceramic...
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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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Daniele Cardillo, Francesco Battista, Giuseppe Gallo, Stefano Mungiguerra and Raffaele Savino
Firing test campaigns were carried out on a 200 N thrust-class hybrid rocket engine, using gaseous oxygen as an oxidizer and a paraffin-wax-based fuel. Different fuel grain lengths were adopted to extend the fuel characterization under different operatin...
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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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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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Tianfang Wei, Guobiao Cai, Hui Tian, Yuanjun Zhang, Chengen Li and Xiangyu Meng
This study investigated reconstruction techniques for building the instantaneous fuel regression rate of the hybrid rocket motor (HRM). Specifically, an experiment in a laboratory 500 N-class hybrid rocket motor with single-port wagon wheel fuel grain, o...
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