Results 31 to 40 of about 13,320 (264)
Energies, 2021 The optimal design of the thrust vector control system of solid rocket motors (SRMs) is discussed. The injection of a supersonic underexpanded gas jet into the diverging part of the rocket engine nozzle is considered, and multiparameter optimization of ...
Vladislav Emelyanov +2 more
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Applied Sciences, 2023 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.
Giovanni Fasulo +4 more
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Conceptual design: Dependence of parameterization on design performance of three-stage hybrid rocket
Journal of Fluid Science and Technology, 2014 The subject of this paper is to improve on parameterization for conceptual design method of three stage hybrid rocket. Multi-Objective Genetic Algorithm (MOGA) is employed to solve multi-disciplinary design exploration of a three-stage launch vehicle ...
Masahiro KANAZAKI +5 more
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Aerospace, 2023 An essential part of the design of a liquid rocket engine is the thermal analysis of the thrust chamber, which is a component whose operative life is limited by the maximum allowable wall temperature and heat flux.
Matteo Fagherazzi +3 more
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Numerical Simulation of Reactive Flows in Overexpanded Supersonic Nozzle with Film Cooling
International Journal of Aerospace Engineering, 2015 Reignition phenomena occurring in a supersonic nozzle flow may present a crucial safety issue for rocket propulsion systems. These phenomena concern mainly rocket engines which use H2 gas (GH2) in the film cooling device, particularly when the nozzle ...
Mohamed Sellam, Amer Chpoun
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Вестник Самарского университета: Аэрокосмическая техника, технологии и машиностроение, 2019 The paper presents the description of a mathematical model of the working process of a low-thrust rocket engine operating on gaseous oxygen-hydrogen fuel and some fragments of the technology of computational analysis of distribution of gas-dynamic ...
V. V. Ryzhkov, I. I. Morozov
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A Coupled Heat Transfer Calculation Strategy for Composite Cooling Liquid Rocket Engine
Aerospace, 2023 To better understand the characteristics of coupled heat transfer in liquid rocket engines, a calculation scheme is proposed in this paper. This scheme can simulate the coupled heat transfer processes, including combustion and flow in the thrust chamber,
Bo Xu +4 more
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Aerospace, 2022 Internal flow field ablation is an important issue in thermal protection materials for rocket engines and hypersonic vehicles. In this paper, a new multiphase flow ablation test system, with an Al2O3 particle delivery device based on an oxygen-kerosene ...
Qingdong Su +6 more
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Novell Application of CFD for Rocket Engine Nozzle Optimization
Periodica Polytechnica Transportation Engineering, 2018 Numerical analyses, validation and geometric optimization of a converging-diverging nozzle flows has been established in the present work. The optimal nozzle contour for a given nozzle pressure ratio and length yields the largest obtainable thrust for the conditions and thus minimises the losses.
Csaba Jéger, Árpád Veress
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New Contour Design Method for Rocket Nozzle of Large Area Ratio
International Journal of Aerospace Engineering, 2019 A rocket engine for space propulsion usually has a nozzle of a large exit area ratio. The nozzle efficiency is greatly affected by the nozzle contour.
Dechuan Sun, Tianyou Luo, Qiang Feng
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