Results 1 to 10 of about 13,320 (264)
Nuclear Thermal Rocket Engine with a Toroidal Aerospike Nozzle [PDF]
AIAA Propulsion and Energy 2020 Forum, 2020 This thesis describes the coupling of a nuclear thermal rocket engine with a toroidal aerospike nozzle. The coupling of the two systems consists of two phases.
Stewart, Kyle
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Effect of scale size on a rocket engine with suddenly frozen nozzle flow [PDF]
ARS Journal, 1961 Recent analytical work by Bray indicates that single element, chemically reacting systems, e.g., H_2 ⇋ 2H, may suddenly freeze their composition at some point in a high speed nozzle and then remain at fixed composition throughout the remainder of the
Watson, Ronald
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Effect of Convergent Section Contour on the Sonic Line in Rocket Engine Nozzles
Journal of Aerospace Technology and Management, 2018 This study made a numeric evaluation of the effect of convergent geometry on the position and profile of the sonic line in rocket engine nozzles. To validate the numerical solution, two conical nozzles, from which experimental results are available in the literature, were used as reference.
Germer, Eduardo Matos, Marchi, Carlos H.
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Numerical simulations of temperature fields in the uncooled nozzle of a short-range anti-aircraft rocket engine with an insert in the critical section made of various materials [PDF]
Biuletyn Wojskowej Akademii Technicznej, 2021 . The paper presents numerical simulations of transient heat conduction in the uncooled nozzle of a short-range anti-aircraft rocket engine. The calculations were made for the configuration of the nozzle with an insert in the critical section made of ...
Mateusz Zieliński +3 more
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Wernher Von Braun’s Pioneering Work in Modelling and Testing Liquid-Propellant Rockets [PDF]
INCAS Bulletin, 2022 This paper presents a view on how Dr. Wernher Von Braun laid the basis for realistic modelling and testing liquid-propellants rockets, by his PhD Thesis – a secret document in 1934, which remained classified until 1960.
Nicolae-Florin ZAGANESCU +2 more
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Ablation performance of 3D C/SiC composite nozzles under double-component liquid power environment
Cailiao gongcheng, 2022 In order to explore the ablation characteristics of C/SiC ceramic composite nozzles in the working environment of liquid rocket engines, 3D C/SiC composite nozzle was prepared by the precursor impregnation pyrolysis(PIP) process, and the ablation test of
BAI Longteng +4 more
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Joint design and simulation of GOX-GCH4 combustion and cooling in an experimental water-cooled subscale rocket engine [PDF]
INCAS Bulletin, 2023 This paper presents the authors’ most recent research regarding the feasibility of cooling a 1 kN scaled-down experimental rocket engine, running on gaseous oxygen and gaseous methane, for a ground test.
Alexandru MEREU, Dragos ISVORANU
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Авіаційно-космічна техніка та технологія, 2023 The subject of this study is dual-bell supersonic nozzles of liquid rocket engines. The goal is to design a dual-bell supersonic nozzle that will provide maximum thrust for a liquid rocket engine in the first stage of a launch vehicle by solving an ...
Ivan Dubrovskyi
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Вестник Самарского университета: Аэрокосмическая техника, технологии и машиностроение, 2022 Modern aircraft need increased maneuverability to maintain a competitive position. One way to improve this characteristic is to use methods to adjust the thrust vectors of a jet engine nozzle.
K. O. Tishchenko +2 more
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Aerospace, 2023 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.
Daniele Cardillo +4 more
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