Data-driven stability analysis in a multi-element supercritical Liquid Oxygen-methane combustor [PDF]
Physics of Fluids, 2025Thermoacoustic instability (TAI) is a pressing problem in rocket combustors. TAI can cause significant damage to a combustor, resulting in mission failure. Therefore, stability analysis is crucial during the design and development phases of a rocket combustor. Stability analysis during the design phase can be substantially aided by the rocket combustor'
arxiv +1 more source
Prediction of explosive yield and other characteristics of liquid propellant rocket explosions Final report [PDF]
Explosive hazards and yield predictions for liquid rocket ...
Bonzon, C. F. +2 more
core +1 more source
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
doaj
Bipropellant droplet burning rates and lifetimes in a combustion gas environment [PDF]
Liquid rocket propellant droplet burning rate and lifetimes in combustion ...
Faeth, G. M., Lazar, R. S.
core +1 more source
Cold solid propellant motor has stop-restart capability [PDF]
, 1966 Solid propellant rocket is kept and fired at low temperatures in launch vehicles or spacecraft. The motor is capable of developing a specific impulse comparable to that of liquid propellant motors, is started, stopped, and restarted, and is stored in ...
Hendel, F. J.
core +1 more source
Discussion: “Liquid-Propellant Rocket Power Plants” (Zucrow, M. J., 1947, Trans. ASME, 69, pp. 847–856) [PDF]
, 1947 J. H. Wyld
openalex +1 more source
Simple Learning-Based Robust Nonlinear Control of an Electric Pump for Liquid-Propellant Rocket Engines [PDF]
, 2023 Mohammad Jafari +2 more
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Assessing Hypothetical Gravity Control Propulsion [PDF]
arXiv, 2006 Gauging the benefits of hypothetical gravity control propulsion is difficult, but addressable. The major challenge is that such breakthroughs are still only notional concepts rather than being specific methods from which performance can be rigorously quantified.
arxiv
Liquid-hydrogen rocket engine development at Aerojet, 1944 - 1950 [PDF]
This program demonstrated the feasibility of virtually all the components in present-day, high-energy, liquid-rocket engines. Transpiration and film-cooled thrust chambers were successfully operated.
Coplen, H. L. +3 more
core +1 more source
ADN – The new oxidizer around the corner for an environmentally friendly smokeless propellant [PDF]
Journal of Aerospace Technology and Management, 2009 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 +3 more
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