Results 61 to 70 of about 304 (185)

Energetic Compositions Application for the Reduction of the Environmental Pollution Because of Space Vehicle Launches

Eurasian Chemico-Technological Journal, 2017
Technogeneous impact of rocket and space activities on the environment is one of the most actual problems of practical cosmonautics. This technogeneous impact is not only the pollution of near Earth space with space debris (worked-off stages of space ...
V. Trushlyakov, D. Lempert, Yuan- jie Shu   +2 more
doaj   +1 more source

The problem of combustion instability in liquid rocket engines

Challenges and Issues of Modern Science
The purpose of this work is to carry out an overview on combustion instability in liquid propellant rocket engines, its classification, the main principles of occurrence as well as ways to prevent the phenomena while designing of the prospective engine.
Samir Vekilov, Volodymyr Lipovskyi, Roman Pustovyi   +2 more
doaj  

Analysis of the Combustion Process in the Engine Zamstic [PDF]

فناوری در مهندسی هوافضا, 2017
In liquid rocket engine design, because of the combustion due to the high temperatures and high rates of heat transfer (1MW/m2 to about 160MW/m2) of hot gases to the chamber walls, the cooling thrustchamber is of utmost importance.
Koros nekofar, Andisheh Tiregar, seyed Amir Hosseini   +2 more
doaj  

A novel heat transfer modeling methodology for regenerative cooling in liquid propellant rocket engines

Case Studies in Thermal Engineering
Liquid propellant rocket engines operate at extremely high temperatures and commonly rely on regenerative cooling to protect chamber walls and maintain structural integrity.
T. Gândara, V. Costa, J. Dias
doaj   +1 more source

Development of Solid Gas Generating Compositions to Ensure Non Explosiveness of Spent Orbital Stages of Liquid Rocket of Space Launch Vehicles

Eurasian Chemico-Technological Journal, 2017
The choice is discussed of solid gas generating compositions for venting by hot combustion products a fuel tank of the spent orbital stage of a space launch vehicle with a main liquid rocket engine.
V. I. Trushlyakov, K. I. Zharikov, D. B. Lempert   +2 more
doaj   +1 more source

Mathematical model for heat transfer in variable thickness fins for rocket engines

Challenges and Issues of Modern Science
Purpose. 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  

Spectroscopic Quantification of Metallic Element Concentrations in Liquid-Propellant Rocket Exhaust Plumes

Aerospace
Accurate quantification of metallic contaminants in rocket exhaust plumes serves as a critical diagnostic indicator for engine wear monitoring. This paper develops a hybrid method combining atomic emission spectroscopy (AES) theory with a genetic ...
Siyang Tan, Song Yan, Xiang Li, Tong Su, Qingchun Lei, Wei Fan   +5 more
doaj   +1 more source

Simulation Study on Outflow Characteristics of Cryogenic Propellant during Rocket Ascent

Zhileng xuebao, 2020
At the rocket launching stage, it is very important to supply sufficient and vapor-free liquid propellant to maintain the functioning of the main engine.
Huang Xiaoning, Wang Lei, Mao Hongwei, Xue Liangjiang, Li Yanzhong   +4 more
doaj  

Modeling of Shutdown Process in Liquid Propellant Rocket Engines [PDF]

فصلنامه علوم و فناوری فضایی, 2014
The effects of liquid propellant rocket engines thrust termination transients are important in achieving the launch vehicle’s desired final velocity with the required precision.
M. Shafiey Dehaj, R. Ebrahimi, H. Karimi, A. Jalali, M. Naderi   +4 more
doaj  

Mixture Ratio Stabilizer for Liquid Propellant Rocket Engine

Journal of the Korean Society for Aeronautical & Space Sciences, 2008
There is provided a mixture ratio stabilizer for a liquid propellant rocket engine which comprises: a body internally having a chamber and a fuel supply hole communicating with an end of the chamber to receive fuel from a fuel supply pump, an oxidizer inlet, and a fuel outlet; a spool guide in the chamber and including a plurality of first orifices for
openaire   +2 more sources