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Beeswax–EVA/Activated-Charcoal-Based Fuels for Hybrid Rockets: Thermal and Ballistic Evaluation
Energies, 2022 Beeswax (C46H92O) is a naturally derived substance that has the potential to be used as a solid fuel for hybrid rocket applications and as a substitute for paraffin wax fuel in hybrid rockets.
Sri Nithya Mahottamananda +3 more
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Optimization design in single wagon-wheel fuel grain of hybrid rocket motor
FirePhysChem, 2021 The grain design of hybrid rocket motor is a design of proper fuel grain geometry and flow adjustment scheme based on the total impulse, thrust, chamber pressure, length and outer diameter of combustion chamber.
Wei Tianfang +5 more
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Aerospace, 2023 This study deals with the mathematical modeling and numerical simulation of chemical propulsion systems (CPSs). For this, we investigate and summarize a comprehensive collection of the simulation modeling developments of CPSs in academic works ...
Jihyoung Cha
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FirePhysChem, 2022 This paper discusses the potential use of hydrogen peroxide as oxidizer for solid rocket propulsion. While hydrogen peroxide is a liquid in normal conditions, it may be used in solid rocket motor grains.
Wioleta Kopacz +5 more
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AerospaceHybrid rocket motors have great development potential due to their outstanding thrust adjustment flexibility and long-term operation ability. However, nozzle erosion during the motor operation can cause an increase in the throat area of the nozzle, which
Xiangyu Meng +5 more
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Numerical Simulations of Flow and Fuel Regression Rate Coupling in Hybrid Rocket Motors [PDF]
INCAS Bulletin, 2017 The hybrid propulsion offers some remarkable advantages like high safety and high specific impulse and thus it is considered a promising technology for the next generation launchers and space systems. The purpose of this work is to validate a design tool
Marius STOIA-DJESKA +2 more
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METALIZED FUEL HYBRID ROCKET MOTOR PARAMETRIC STUDY [PDF]
International Conference on Aerospace Sciences and Aviation Technology, 2015 The objective of this paper is to study theoretically and experimentally the effects of different design parameters on hybrid rocket motor (HRM). HRM propellant constituents are Polyethylene (PE) with Al powder additive as solid fuel and gaseous oxygen (GO2) as oxidizer.
openaire +1 more source
Modified Regression Rate Formula of PMMA Combustion by a Single Plane Impinging Jet
International Journal of Aerospace Engineering, 2017 A modified regression rate formula for the uppermost stage of CAMUI-type hybrid rocket motor is proposed in this study. Assuming a quasi-steady, one-dimensional, an energy balance against a control volume near the fuel surface is considered. Accordingly,
Tsuneyoshi Matsuoka +3 more
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Comprehensive Data Reduction for N2O/HDPE Hybrid Rocket Motor Performance Evaluation
Aerospace, 2019 Static firing tests of a hybrid rocket motor using liquid nitrous oxide (N2O) as the oxidizer and high-density polyethylene (HPDE) as the fuel are analyzed using a novel approach to data reduction that allows histories for fuel mass consumption, nozzle ...
Landon Kamps +3 more
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Design of a Mars Ascent Vehicle Using HyImpulse’s Hybrid Propulsion
Aerospace, 2023 The recent growth in maturity of paraffin-based hybrid propulsion systems reassesses the possibility to design an alternative Mars Ascent Vehicle (MAV) propelled by a European hybrid motor.
Maël Renault, Vaios Lappas
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