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.
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.
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.
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.
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.
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.
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.
Oxygen-hidrogen liquid rocket engine using turbo-pump developed for aviation hidrogen liquid two-spool turbo-jet
Ivanov A.I., Borisov V.A.
Analysis of low-thrust liquid rocket engines with a methane air pump unit
Ivanov A.I., Kositsin I.P., Borisov V.A.
Procedure of validated CFD-modeling of a two-stage screw-centrifugal pump
Zubanov V.M., Shabliy L.S., Krivtsov A.V., Ivanov A.I., Kositsin I.P., Baturin N.V.
Development of improved performance electromagnetic valve for liquid rocket engine
Igolkin A.A., Chubenko T.A., Maksimov A.D.
Bringing spacecraft into solar-oriented attitude by the measurements of a single-axis angular-rate sensor and an optical solar sensor
Shipov M.G., Steklova A.A., Davydov A.A.
Analysis of nonstationary thermal state of low-thrust liquid rocket engine with high-concentration hydrogen peroxide and kerosene propellant with film cooling
Vorobiev A.G., Borovik I.N., Ha S.
Numerical simulation of low liquid flow in a mixer consisting of two centrifugal swirlers
Semkin E.V.
Analysis of nonstationary thermal state of a low-thrust liquid rocket engine taking into account injection, evaporation and combustion of liquid fuel droplets
Vorobiev A.G., Borovik I.N., Ha S.
Influence in a constructive and regime parameters antechamber by operation-in the combustion chamber liquid-propellant rocket engine thrusters on hypergolic liquid propellants
Nigodjuk V.E., Sulinov A.V.
Mixing parameters investigations and methods of approach to calculations and development of the thrusters with a spray-centrifugal scheme of NT and NDMH mixing on the confusion chamber wall in considered
1 1.
Research of the possibility of thermal conditions LREST using an infrared thermal imaging system
Ryzhkov V.V., Silyutin M.V.
Increasing the energy efficiency of liquid rocket engine of small thrust (0,1-1,0) N with jet scheme of mixing
Nigodjuk V.E., Sulinov A.V.
Physical workflow model in the combustion chamber LREST with a jet-centrifugal jets on hypergolic propellants
Silyutin M.V., Shustov S.A.
Oxyhydrogen propulsion device base on water electrolysis and lrest on component H2 + O2 for control system SS
1 1., 1 1., 1 1., 1 1., 1 1.
Features of calculation of hydraulic characteristics of capillary spray jets of is liquid-stnyh rocket engines of small pull-rod
1 1., 1 1., 1 1.
Peculiarities of the working process of low-thrust hypergolic-propellant liquid rocket engines with a thrust of less than 1 N
Nigodjuk V.E., Sulinov A.V.
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 determination of the side forces acting on the combustion chamber in the altitude chamber at startup
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Experimental development of the LRE with CCCM nozzle’s extension
1 - 26 of 26 Items

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