Results 141 to 150 of about 14,137 (299)

A numerical study on the influence of multiple nozzles on the infrared radiation signatures of liquid rocket exhaust plumes

Case Studies in Thermal Engineering
A numerical study was conducted to examine the relationship between the infrared radiation characteristics of liquid rocket engine exhaust plumes under the same thrust conditions and the number and expansion degree of nozzles.
Panpan Yan, Wenqiang Gao, Xiaying Meng, Hongli Wang, Qinglin Niu, Shikui Dong   +5 more
doaj  

Flow processes in overexpanded chemical rocket nozzles. Part 3: Methods for the aimed flow separation and side load reduction [PDF]

Methods aimed at reduction of overexpansion and side load resulting from asymmetric flow separation for rocket nozzles with a high opening ratio are described. The methods employ additional measures for nozzles with a fixed opening ratio.
Schmucker, R. H.
core   +1 more source

Orbital escape device Patent [PDF]

, 1967
Development and characteristics of inflatable structure to provide escape from orbit for spacecrews under emergency ...
Johnson, C. C.
core   +1 more source

Experimental and Numerical Studies of Secondary Injection in Nozzle Divergence for Thrust Augmentation

Journal of Applied Fluid Mechanics, 2019
Thrust augmentation in rocket engines using secondary injection in the diverging part of a nozzle is an innovative extension of after burners. This technique finds application in single stage to orbit propulsion devices, where the nozzle has to work at ...
G. Anugrah, P. Raja, M. Deepu, R. Sadanandan   +3 more
doaj  

Vapor liquid separator Patent [PDF]

, 1968
Vapor-liquid separator design with vapor driven pump for separated liquid pumping for application in propellant ...
Ward, W. D.
core   +1 more source

Temperature-Dependent Modal Test/Analysis Correlation of X-34 FASTRAC Composite Rocket Nozzle [PDF]

, 2002
Andrew M. Brown
openalex   +1 more source

Experimental Study on Submerged Nozzle Damping Characteristics of Solid Rocket Motor

Aerospace
Acoustic instabilities in solid rocket motors (SRMs) can lead to severe performance deterioration and structural damage. Nozzle damping accounts for the main acoustic dissipation source, and it is highly dependent on geometric parameters and operating ...
Xinyan Li, Zhenglong Chen, Xiaosi Li, Bo Xu, Shengnan Wang   +4 more
doaj   +1 more source

Electric propulsion engine test chamber Patent [PDF]

, 1965
Electric propulsion engine test ...
Childs, J. H., Grobman, J., Rayle, W. D.
core   +1 more source

Ablation Characteristics Research in Solid Rocket Motor's Combustion Chamber Produced by 3D Printing. [PDF]

Materials (Basel), 2023
Hui W, Hu Y, Liu Y, Cai Q, Zhao W.
europepmc   +1 more source

Multiple exhaust nozzles for nuclear rocket engines

, 1965

openalex   +2 more sources