Results 311 to 320 of about 863,762 (375)
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2012
The hybrid rocket engine utilizes a combination of solid rocket and liquid rocket technology to meet some flight mission applications. In terms of performance, cost, availability of materials and safety, the hybrid approach does potentially have some advantages.
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The hybrid rocket engine utilizes a combination of solid rocket and liquid rocket technology to meet some flight mission applications. In terms of performance, cost, availability of materials and safety, the hybrid approach does potentially have some advantages.
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Volume 4: 20th Design for Manufacturing and the Life Cycle Conference; 9th International Conference on Micro- and Nanosystems, 2015
This paper presents both experiment and simulation of alumina molten flow in a solid rocket motor (SRM), when the propellant combusts, the aluminum is oxidized into alumina (Al2O3) which, under the right flow conditions, tends to agglomerate into molten droplets, impinge on the chamber walls, and then flow along the nozzle wall.
Ryoichi S. Amano, Yi-Hsin Yen
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This paper presents both experiment and simulation of alumina molten flow in a solid rocket motor (SRM), when the propellant combusts, the aluminum is oxidized into alumina (Al2O3) which, under the right flow conditions, tends to agglomerate into molten droplets, impinge on the chamber walls, and then flow along the nozzle wall.
Ryoichi S. Amano, Yi-Hsin Yen
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Chemical Mechanism of MMH/NTO and Simulation in a Small Liquid Rocket Engine
Combustion Science and Technology, 2018A reaction mechanism called Mech23 for gas-phase monomethylhydrazine and nitrogen tetroxide (MMH/NTO) containing 23 species and 20 reactions is developed and validated and then introduced into the numerical simulation of a small MMH/NTO liquid rocket ...
Lingyun Hou, Pengfei Fu, Ya-dong Ba
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Three-dimensional numerical modeling of a rocket engine with solid fuel
Acta Astronautica, 2021A. Kushnirenko +4 more
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Sea-Level Static Tests of Rocket–Ramjet Combined Cycle Engine Model
, 2020A rocket–ramjet combined cycle engine model, embedding twin rocket chambers driven with gaseous hydrogen and oxygen on the top wall side of a scramjet flowpath, was tested in its ejector-mode opera...
S. Tomioka +5 more
semanticscholar +1 more source
Thomas/Alford Force on a Partial-Admission Turbine for the Rocket Engine Turbopump
Journal of Fluids Engineering, 2018This paper describes an imbalanced torque force, called the Thomas/Alford force, of a partial-admission turbine for the rocket engine turbopump. The Thomas/Alford force is a destabilizing force imposed on the rotor that could cause rotor dynamic ...
K. Yada, M. Uchiumi, K. Funazaki
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, 2017
The pintle injector is a promising candidate for propellant-injection systems for various rocket engines. However, fundamental studies focusing on the pintle injector are rather limited, and the effects of key design parameters on combustion behaviors of
Kazuki Sakaki +7 more
semanticscholar +1 more source
The pintle injector is a promising candidate for propellant-injection systems for various rocket engines. However, fundamental studies focusing on the pintle injector are rather limited, and the effects of key design parameters on combustion behaviors of
Kazuki Sakaki +7 more
semanticscholar +1 more source
2012
The air-breathing rocket engine exploits the availability of atmospheric air as an oxidizer to enhance the overall efficiency of the engine’s performance over the course of a flight mission. The early basis for this rocket propulsion approach is the ramjet engine, which is discussed in some detail in this chapter.
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The air-breathing rocket engine exploits the availability of atmospheric air as an oxidizer to enhance the overall efficiency of the engine’s performance over the course of a flight mission. The early basis for this rocket propulsion approach is the ramjet engine, which is discussed in some detail in this chapter.
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International Journal of Aeronautical and Space Sciences, 2020
Byungil Yu, H. Kwak, Hong-Jip Kim
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Byungil Yu, H. Kwak, Hong-Jip Kim
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Instrumentation for Nuclear Rocket Engines
IEEE Transactions on Nuclear Science, 1969The NERVA program presents many difficult instrumentation design problems. Gamma fluxes reach 109 rads(C)/hr and neutron fluences approach 1018 n/cm2 (E>l.0 Mev), while temperatures range from 40 to 4500°R. A summary of these problems and their solutions is discussed.
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