Results 91 to 100 of about 25,209 (263)

Integrated modular design and analysis of liquid propellant rocket engine working on liquid methane-oxygen expander cycle

, 2022
Rajkumar P Desai, Biju T. Kuzhiveli
openalex   +1 more source

ADN – THE NEW OXIDIZER AROUND THE CORNER FOR AN ENVIRONMENTALLY FRIENDLY SMOKELESS PROPELLANT. doi:10.5028/jatm.2009.0102153160

Journal of Aerospace Technology and Management, 2011
The search for a smokeless propellant has encouraged scientists and engineers to look for a chlorine-free oxidizer as a substitute for AP (ammonium perchlorate).
Márcio Y. Nagamachi, José Irineu S. Oliveira, Aparecida M. Kawamoto, Rita de Cássia L. Dutra   +3 more
doaj  

A compressible two-phase flow framework for Large Eddy Simulations of liquid-propellant rocket engines

Applied Mathematical Modelling, 2020
C. Le Touze, L. Dorey, N. Rutard, A. Murrone   +3 more
semanticscholar   +1 more source

Synthesis of calculational methods for the design and analysis of radiation shields for nuclear rocket systems. Volume II. Analysis of radiation measurements in a nuclear rocket propellant tank mockup using simulated liquid hydrogen

, 1968
R.K. Disney, R.G. Soltesz, L. D. Stephenson, Stacey Zeigler   +3 more
openalex   +1 more source

Analysis of liquid rocket propellant in nitroglycerin injector reactors

, 2023
Maryono Maryono, Muhammad Akhlis Rizza
openalex   +2 more sources

The Present Status of Propellant Feed Pumps for Liquid Rockets

, 1985
Kenjiro Kamijo
openalex   +2 more sources

ANALYSIS OF THE INFLUENCE OF THE DESIGN PARAMETERS OF THE UPPER STAGE LIQUID PROPELLANT ROCKET ENGINE PUMP ON ITS CAVITATION CHARACTERISTICS

, 2023
Г.В. Назаренко
openalex   +2 more sources

An Experimental and Analytical Study of High-Energy-Density Propellants for Liquid Rocket Engines

, 2005
Timothy S. Kokan, John Olds
openalex   +2 more sources

Performance Prediction of Liquid Rocket Thrust Chambers with Nonuniform Propellant Mixing

, 2006

openalex   +2 more sources

A Reliable Method for Predicting the Specific Impulse of Chemical Propellants

Journal of Aerospace Technology and Management, 2018
The specific impulse (Isp) is an important performance parameter that describes energy efficiency of propellant combustion and is intimately related to the rocket engine thrust.
Dany Frem
doaj