Results 231 to 240 of about 16,009 (301)
Atomistic Insights into the Influence of High Concentration H2O2/H2O on Al Nanoparticles Combustion: ReaxFF Molecules Dynamics Simulation. [PDF]
MoleculesYu X, Zhang P, Zhang H, Yuan S.
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Anomaly Detection Method for Rocket Engines Based on Convex Optimized Information Fusion. [PDF]
Sensors (Basel)Sun H, Cheng Y, Jiang B, Lu F, Wang N.
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Combustion Enhancement of Gel Propellant Containing High Concentration Aluminum Particles Based on Carbon Synergistic Effect. [PDF]
GelsChen J, Zhao H, Li W, Liu H.
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Synthesis, Structure, Properties, and Applications of Fluorinated Polyurethane. [PDF]
Polymers (Basel)Li D +7 more
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Fundamental Concepts of Liquid-Propellant Rocket Engines [PDF]
, 2020 The engine of a rocket vehicle is a machine which produces thrust by accelerating a gas flowing through the machine. The reaction to this acceleration is the force which drives the vehicle. The amount of thrust generated depends on the mass flow rate of the gas moving through the engine and on the exit velocity of the gas from the nozzle. The gas flow,
Alessandro de Iaco Veris
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Liquid Propellant Rocket Motors
The Journal of the Royal Aeronautical Society, 1953It has been said that a rocket motor is the simplest “ prime mover.” This is correct in theory, since fundamentally a rocket consists of a chamber containing a gas under pressure, having a nozzle at one end through which the gas expands, forming a propulsive jet. Since the pressure ratio of the rocket is always greater than the critical pressure ratio,
D. L. Lofts +2 more
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Electric Feed Systems for Liquid-Propellant Rockets
Journal of Propulsion and Power, 2013Liquid-propellant rocket feed systems based on electric pumps are compared with the more classical pressure–gas and turbopump systems. The design parameters entering in the definition of the system mass are highlighted, and a careful choice of the figures of merit is performed, in particular for the electric motors and batteries.
P. A. Pavlov Rachov +2 more
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Flowfield characteristics in a liquid propellant rocket
29th Joint Propulsion Conference and Exhibit, 1993Measurements of LOX drop size and velocity in a uni-element liquid propellant rocket chamber are presented. The use of the Phase Doppler Particle Analyzer in obtaining temporally averaged probability density functions of drop size in a harsh rocket environment has been demonstrated.
M. D. Moser +4 more
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