Results 111 to 120 of about 63,703 (327)
Research on the comparative analysis of thrust and specific impulse performance - different cycle types of liquid rocket engines [PDF]
, 2023 Mingyu Mao
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Cryostatless high temperature supercurrent bearings for rocket engine turbopumps [PDF]
The rocket engine systems examined include SSME, ALS, and CTV systems. The liquid hydrogen turbopumps in the SSME and ALS vehicle systems are identified as potentially attractive candidates for development of Supercurrent Bearings since the temperatures ...
Dill, James F., Rao, Dantam K.
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, 1981 The system includes reusable turbojet propelled booster vehicles releasably connected to a reusable rocket powered orbit vehicle. The coupled orbiter-booster combination takes off horizontally and ascends to staging altitude and speed under booster power
Jackson, L. R. +3 more
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A Study on the Regenerative-Cooling Nozzle with Liquid Oxygen for Hybrid Rocket Engine - Part 1
, 2023 Young Il Park +6 more
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Determination of the effects of nozzle nonlinearities upon nonlinear stability of liquid propellant rocket motors [PDF]
The research is reported concerning the development of a three-dimensional nonlinear nozzle admittance relation to be used as a boundary condition in the nonlinear combustion instability theories for liquid propellant rocket engines.
Padmanabhan, M. S. +2 more
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Dual-fuel, dual-mode rocket engine [PDF]
, 1989 The invention relates to a dual fuel, dual mode rocket engine designed to improve the performance of earth-to-orbit vehicles. For any vehicle that operates from the earth's surface to earth orbit, it is advantageous to use two different fuels during its ...
Martin, James A.
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Launch vehicle performance using metallized propellants [PDF]
Metallized propellant propulsion systems are considered as replacements for the solid rocket boosters and liquid sustainer stages on the current launch vehicles: both the Space Transportation System (STS) and the Titan 4.
Palaszewski, Bryan A., Powell, Richard
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Mathematical model for heat transfer in variable thickness fins for rocket engines
Challenges and Issues of Modern SciencePurpose. This article aims to develop a mathematical model for a fin in the cooling system of liquid propellant rocket engines. The objective is to enable calculations for fins with arbitrary thickness variation. The developed mathematical model will be
Volodymyr Sliusariev, Valerii Bucharskyi
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Авіаційно-космічна техніка та технологіяThe subject matter of this study is the thermophysical processes occurring in the cooling channels of liquid-propellant rocket engines. The goal of this research is to create an algorithm for optimizing cooling channels. The tasks include formulating the
Iurii Vorobiov +2 more
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THERMO-STRENGTH ANALYSIS OF UNCOOLED COMPOSITE NOZZLE OF A LIQUID ROCKET ENGINE
, 2022 М. M. Dron’, K. I. Zharikov
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