Results 101 to 110 of about 29,920 (238)

Study of the Amplitude of Pressure and Thrust Oscillations in a Lab-Scale Hybrid Rocket [PDF]

, 2000
Hybrid rockets are being studied as a potential replacement for the solid rocket boosters on the NASA space shuttle. One physical characteristic of hybrid rockets that must be understood and overcome is potentially severe pressure oscillations during ...
Alford, Brian, Dunn, Lawrence, Hudson, M. Keith, Patton, Justin, Wright, Ann   +4 more
core   +1 more source

Numerical simulation study of aluminum particle evaporation combustion process based on SPH method

AIP Advances
A large variety of metal fuels is usually added to the modern solid rocket propellants to improve the propellant energy and motor specific impulse and to suppress high frequency unstable combustion. Among them, aluminum is the most common additive.
Du-dou Wang, Hong-fu Qiang, Zhen-sheng Sun, Xue-ren Wang   +3 more
doaj   +1 more source

Application of Ablation to a High Chamber Pressure Rocket Engine [PDF]

Ablation cooling in rocket engine with combustion chamber liner and nozzle constructed of silica phenolic ablative ...
Brecheisen, A. W., Ehresman, C. M.
core   +1 more source

Heat exchanger [PDF]

, 1978
A heat exchanger, as exemplified by a rocket combustion chamber, is constructed by stacking thin metal rings having microsized openings therein at selective locations to form cooling passages defined by an inner wall, an outer wall and fins.
Sokolowski, D. E.
core   +1 more source

Injector element characterization methodology [PDF]

Characterization of liquid rocket engine injector elements is an important part of the development process for rocket engine combustion devices. Modern nonintrusive instrumentation for flow velocity and spray droplet size measurement, and automated ...
Cox, George B., Jr.
core   +1 more source

Designing and Testing of HDPE–N₂O Hybrid Rocket Engine

Engineering Proceedings
Hybrid Rocket Engines (HREs) combine the advantages of solid and liquid propellants, offering thrust control, simplicity, safety, and cost efficiency.
Triyan Pal Arora, Noah Buttrey, Peter Kirman, Sanmukh Khadtare, Eeshaan Kamath, Dario del Gatto, Adriano Isoldi   +6 more
doaj   +1 more source

Steady state aerothermochemistry for liquid bipropellant rocket motors [PDF]

Model and theoretical equations describing liquid propellant droplet ballistics and combustion gas behavior in bipropellant rocket motors ...
Agosta, V. D., Burstein, S. Z.
core   +1 more source

Evaluation of N,N,N′,N′-Tetramethylethylenediamine (TMEDA) as an Alternative Fuel for a Hypergolic Bipropellant Rocket Engine

Fuels
Experimental research was conducted to characterize the ignition delay time and combustion performance of non-toxic reactants as a possible replacement for highly toxic fuels, such as hydrazine.
Joshua M. Hollingshead, Makayla L. L. Ianuzzi, Jeffrey D. Moore, Grant A. Risha   +3 more
doaj   +1 more source

Nonlinear combustion instability in liquid-propellant rocket motors Quarterly report [PDF]

Fluid dynamic pancake model and droplet evaporation and combustion analysis related to nonlinear combustion instability in liquid propellant rocket ...
Burstein, S. Z., Chinitz, W.
core   +1 more source

Tripropellant combustion process [PDF]

The addition of small amounts of hydrogen to the combustion of LOX/hydrocarbon propellants in large rocket booster engines has the potential to enhance the system stability.
Carroll, R. G., Kmiec, T. D.
core   +1 more source