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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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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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Calvin Nguyen and James C. Thomas
Hybrid rocket engine (HRE) performance is dependent on fuel/oxidizer selection and fuel grain geometry. A literature review was performed to identify key trends and findings related to the application of the additive manufacturing (AM) of fuel systems fo...
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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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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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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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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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Francesco Barato
Hybrid rockets using specific oxidizer?fuel combinations are considered a green alternative to current propulsion systems, as they do not release very toxic or polluting exhausts, but only much less harmful substances such as carbon monoxide/dioxide and ...
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