Results 171 to 180 of about 29,920 (238)

ML for Rocket Combustion Data

Rüttgers, Alexander, Petrarolo, Anna
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A green stabilizer for Nitrate ester-based propellants: An overview. [PDF]

Heliyon
Rusly SNA, Jamal SH, Samsuri A, Mohd Noor SA, Abdul Rahim KS.   +4 more
europepmc   +1 more source

PAH Induction upon Pyrolysis of Hydroxyl-Terminated Polybutadiene-Based Solid Rocket Fuels. [PDF]

J Phys Chem A
Karpovych V, Haiduk N, Oga E, Bala N, Kubátová A, Kozliak E, Sulkes M.   +6 more
europepmc   +1 more source

Abrupt Transition of Nanothermite Reactivity: The Roles of Loading Density, Microstructure and Ingredients. [PDF]

Molecules
Ru C, Zhang Y, Yu A, Chen L, Wang H, Zhang H, Shan Y, Jin Y.   +7 more
europepmc   +1 more source

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Hybrid rocket combustion study

29th Joint Propulsion Conference and Exhibit, 1993
The objectives of this study of 'pure' or 'classic' hybrids are to (1) extend our understanding of the boundary layer combustion process and the critical engineering parameters that define this process, (2) develop an up-to-date hybrid fuel combustion model, and (3) apply the model to correlate the regression rate and scaling properties of potential ...
L. STRAND, R. RAY, N. COHEN
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Modeling of Rocket Combustion Devices

10th AIAA/ASME Joint Thermophysics and Heat Transfer Conference, 2010
The numerical simulation of the hot-gas side within combustion devices is one important element during the development of today's rocket engines. This paper presents the Astrium hot-gas simulation tool, namely the in-house axisymmetric spray combustion code RocflamII, and shows its validation to experimental subscale data.
Manuel Frey, Thomas Aichner, Josef Görgen, Blazenko Ivancic, Björn Kniesner, Oliver Knab   +5 more
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Analysis of hybrid rocket combustion

Acta Astronautica, 1980
Abstract The problem involving flow of a turbulent boundary layer with mass injection and combustion is studied to investigate the hydrid rocket combustion. Because of the presence of combustion, the momentum equation is coupled to the energy and species equations.
Cherng, D. L., Tao, C. C.
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Bipropellant combustion in a liquid rocket combustion chamber

Journal of Propulsion and Power, 1992
A comprehensive computer simulation code is developed for the combustion-flow analysis of a bipropellant liquid rocket engine combustor. A bipropellant group combustion model is built in the computer code to facilitate the determination of various combustion modes, including the combustion of oxidizer droplets, fuel droplets and gas mixture.
Tsung Leo Jiang, Huei-Huang Chiu
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Nonlinear longitudinal combustion instability in rocket motors

11th Aerospace Sciences Meeting, 1973
A new analytical technique for the solution of nonlinear longitudinal combustion instability problems in rocket combustors is developed. Using relatively little computation time, this technique is capable of predicting the transient and limit cycle behavior of the combustion instability oscillations as well as the disturbance amplitude required to ...
MANUEL E. LORES, BEN T. ZINN
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