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Increasing the efficiency and stability of fuel supply to the combustion chamber of a liquid rocket engine by spray nozzles
Ageenko Y.I., Bubnova A.S.
Creation of promising technologies for producing holes in parts of a high-frequency ion engine
Ryazantsev A.Y., Yukhnevich S.S., Shirokozhuhova A.A.
Development and research testing of a low thrust on gaseous-propellant rocket engine chamber
Musteikis A.I., Levikhin A.A., Kolosenok S.V.
Comparative results of computational and theoretical study of the annular nozzle with a flat central body
Kirshina A.A., Levikhin A.A., Kirshin A.Y.
Research of influence of the thermal stream from the mid-flight liquid rocket engine on parameters of operating liquid rocket engines of small draught in the conditions of perspective razgonnogo's propulsion system of the block
Ageenko Y.I., Galperin R.N., Ivashin Y.S., Nigodjuk V.E., Ryzhkov V.V., Sulinov A.V.
Analysis of low-thrust liquid rocket engines with a methane air pump unit
Ivanov A.I., Kositsin I.P., Borisov V.A.
Assessing the efficiency of flights to high near-earth orbits using boosters with chemical and electro-rocket engines
Ishkov S.A., Fadeenkov P.V., Balakin V.L.
Mathematical model of small-thrust rocket engine with gaseous oxygen and hydrogen in pulse operation
1 1.
Development of improved performance electromagnetic valve for liquid rocket engine
Igolkin A.A., Chubenko T.A., Maksimov A.D.
The numerical modelling of processes in combustion chambers of low thrust rocket engines
Salich V.L.
Method of transient simulation of combustion processes in a low-thrust rocket engine operating on gaseous hydrogen and oxygen
Zubanov V.M., Shabliy L.S., Stepanov D.V.
CFD-modeling of processes in a high-pressure oxidizer pump for the turbopump assembly of a liquid rocket engine
Zubanov V.M., Shabliy L.S.
Мethod of design calculation of centrifugal emulsive duplex fuel nozzle
1 1.
Working process of gaseous fuel metallizator
Pervyshin A.N., Ryazanov A.I.
Technology of computational analysis of the working process parameters of low-thrust rocket engines running on gaseous oxygen-hydrogen fuel with the use of ANSYS CFD
Ryzhkov V.V., Morozov I.I.
Research of the influence of design parameters of a 400 N-thrust low-thrust liquid rocket engine on its energy efficiency
Ageenko Y.I., Ilyin R.V., Pegin I.V.
Developing an electronic reference book on thermogasodynamic properties of rocket engine fuel combustion products taking into account non-ideal character of the working process
Silyutin M.V.
Test bench for investigation of thrusters intra-chamber working processes
Pervyshin A.N., Ryazanov A.I.
Numerical simulation of low liquid flow in a mixer consisting of two centrifugal swirlers
Semkin E.V.
Experience in the development of 11Д58MФ liquid rocket engines
Smolentsev A.A.
Experimental verification of the possibility of improving the liquid propelant rocket engine performance for the “Vega” launcher upper stage
Kovalenko A.N., Pereverzev V.G., Marchan R.A., Blishun Y.V.
Definition of directions of developing methods, technical decisions and means of decreasing the technogenic influence on the environment for the omplementation on board of space launch vehicles
Shatrov Y.T., Baranov D.A., Trushlyakov V.I., Kudentsov V.Y.
Experimental analysis of flow separation in low thrust rocket engine nozzles with a profiled supersonic part of the nozzle
Shustov S.A.
Aspects of the numerical method calculating thermogazodynamic lrest based on not perfect passing of workflows in the combustion chamber
Silyutin M.V., Shustov S.A.
Experimental research on the development of an “oxygen (gas) + kerosene” – fueled thruster
Salich V.L.
Modeling of intrachamber processes in an oxygen-hydrogen thruster
Vaulin S.D., Salich V.L.
Development of turbopump unit design for hydrogen liquid-propellant rocket engines without generators developed at the design bureau of chemical automation
Dmitrenko A.I., Ivanov A.V., Rachuk V.S.
Investigation of energy parameters of small-thrust liquid rocket engines with the geometric expansion ratio of the nozzle F=200
Ageenko Y.I., Nigodyuk V.E., Ryzhkov V.V., Sulinov A.V., Shustov S.A.
Gas-dynamic losses in the flow part of the channel charge of a solid-propellant rocket engine
A. N. Sabirzyanov A.N., Khamatnurova C.B., Kuzmin V.V.
Research of the possibility of thermal conditions LREST using an infrared thermal imaging system
Ryzhkov V.V., Silyutin M.V.
Proposals for improving the efficiency and service life of the turbines of turbo-pump assemblies in liquid-propellant rocket engines by using double-sided crest-type radial labyrinth seals
Levochkin P.S., Chvanov V.K., Vasiliev V.S., Timushev S.F.
Development of thruster chamber operating on oxygen-hydrogen fuel
Salich V.L.
Oxygen-hidrogen liquid rocket engine using turbo-pump developed for aviation hidrogen liquid two-spool turbo-jet
Ivanov A.I., Borisov V.A.
Experimental determination of the side forces acting on the combustion chamber in the altitude chamber at startup
, , , ,
The usage of high power supply capacity transport spacecraft
Ivanovich S.N.
Physical workflow model in the combustion chamber LREST with a jet-centrifugal jets on hypergolic propellants
Silyutin M.V., Shustov S.A.
Multi-purpose high-precision thermal vacuum testing bench and someresults of firing tests of non-hypergolic low-thrust rocket engines
Ryzhkov V.V., Verjasov Y.N., Galperin R.N., Gulyaev Y.I., Ivashin Y.S.
Examination of the theoretical possibility of creating a vernier electrorocket engine
Baigaliev B.E., Chernoglazova A.V., Tumakov E.A., Temnikova S.V.
Influence of high technologies on production technological prototypes of missile engines
Kodencev S.N., Suhochev G.A.
Experimental development of the LRE with CCCM nozzle’s extension
,
The structure of knowledge base to support the development of low-thrust liquid-propellant rocket engines based on computer technologies
Ryzhkov V.V.
Method of design calculation jet-centrifugal gas-liquid duplex fuel nozzle with internal mixing
Egorychev V.S.
Research of liquid outflow from low-emission swirl injectors of a low-thrust liquid rocket engine
Semkin Y.V.
Results of hot tests of an oxygen preburner of a liquid-propellant engine 11D58MF
Barsukov O.A., Strizhenko P.P.
Development liquid roket engine on component fuel liquefied natural gas and oxygen for reusable space launching systems
Efimochkin A.F., Khrisanfov S.P., Golubyatnik V.V., Kafarena P.V., Yeliseyev A.V.
Development of advanced low thrust rocket engines with ecologically friendly propellants
1 1., 1 1., 1 1.
Parametric study of the influence of location and extension height of the rod interceptor on jet engine nozzle characteristics
Tishchenko K.O., Brykov N.A., Belyaeva A.S.
Method of design calculation gas-liquid jet duplex fuel nozzle with internal mixing
Egorychev V.S.
Results of experimental studies of parameters of low-thrust rocket engines operating on gaseous oxygen-hydrogen fuel
Ageenko Y.I., Lapshin E.A., Morozov I.I., Pegin I.V., Ryzhkov V.V.
1 - 49 of 49 Items

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