Results 61 to 70 of about 838 (233)

Investigation of the existing methods for designing pre-combustion chambers in hybrid rocket engines

Авіаційно-космічна техніка та технологія
Hybrid propellant rocket engines (HPRE) have been under development and advancement since the beginning of rocket propulsion research, alongside liquid and solid propellant rocket motors.
Maurício Sá Gontijo
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  

Numerical Analysis of a Supercritical Heat Transfer of Cryogenic Methane in Regeneratively Cooled Rocket Engine [PDF]

INCAS Bulletin
A comparative study of supercritical heat transfer in a regeneratively cooled rocket engine was conducted using three-dimensional numerical simulations for two channel geometries: rectangular and square. Various constant heat fluxes, flow velocities, and
Mohammed Amine DJEFFAL, Nabil BENAMARA, Abdelkader LAHCENE, Ali BENOUAR, Abdelkader BOULENOUAR, Mohammed MERZOUG   +5 more
doaj   +1 more source

Modelling of the processes inside the nozzle of resistojet and arcjet with molecular propellant

Авіаційно-космічна техніка та технологія
The first sample of the resistojet, which together with the arcjet belongs to the class of electrothermal thrusters, was developed in 1929-33 by the Ukrainian designer Valentyn Hlushko.
Serhii Nesterenko, Peng Shuai
doaj   +1 more source

ON THE STABILITY OF THE STABILIZED MOTION OF A CARRIER ROCKET WITH A LIQUID-PROPELLANT JET ENGINE AND AN ONBOARD DIGITAL COMPUTER IN THE STABILIZATION LOOP

, 2022
Eugene Aleksandrov, Тетяна Александрова, Iryna Kostianyk, Yaroslav Morgun   +3 more
openalex   +2 more sources

Peculiarities of the working process of low-thrust hypergolic-propellant liquid rocket engines with a thrust of less than 1 N

Вестник Самарского университета: Аэрокосмическая техника, технологии и машиностроение, 2016
The article presents the results of theoretical and experimental studies of the peculiarities of the working process of low-thrust hypergolic- propellant liquid rocket engines (LTLRE) with the thrust of less than 1 N.
V. E. Nigodjuk, A. V. Sulinov
doaj   +1 more source

Factors Affecting Characteristic Length of the Combustion Chamber of Liquid Propellant Rocket Engines

Mehran University Research Journal of Engineering and Technology, 2019
Optimum characteristic length of the combustion chamber of liquid rocket engine is very important to get higher energy from the liquid propellants. Characteristic length is defined by the time required for complete burning of fuel.
Tajwali Khan, Ihtzaz Qamar
doaj  

Research of the Capillary Phase Separator for Fuel Tanks of Liquid Propellant Rocket Engines at Evaporation of Cryogenic Components [PDF]

, 2015
Н.И. Авраамов, Ф.В. Пелевин, В.Б. Сапожников, А.Л. Синцов, В.Б. Сапожников, ООО Научно-технический внедренческий центр «Энергетические, информационные, технологические достижения для установок и комплексов космического и оборонного назначения», А.Л. Синцов, МГТУ им. Н.Э. Баумана   +7 more
openalex   +1 more source

Propellant Flow Uniformity Analysis of 3 Tonf Liquid Rocket Engine Manifold Using Fluent

, 2023
Dongho Yun, Hyeontaek Jo, H.J. Jang, Seongyoon Hyun, Jintaeg Jung, Yong‐Gi Hong, Yuongbin Yoon   +6 more
openalex   +1 more source

Optimal Output Tracking Control Simulation for Thrust Control of an Open-cycle Liquid Propellant Rocket Engine

, 2020
Jihyoung Cha, Woo‐Sung Cho, Sangho Ko
openalex   +1 more source