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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.
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.
Development and research testing of a low thrust on gaseous-propellant rocket engine chamber
Musteikis A.I., Levikhin A.A., Kolosenok S.V.
Optimization of trajectory motion of the first stage of an aerospace system
Khramov A.A.
Оptimization of gas turbine aircraft engine control throughout the engine service life
Gurevich O.S., Golberg F.D., Smetanin S.A., Trifonov M.E.
Design procedure of fundamental parameters of the direct-flow detonation pulsing engine
Porshnev V.A.
Locally optimal control of space tug motion between the libration points of the Earth-Moon system
Starinova O.L., Fain M.K.
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.
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.
Development of advanced low thrust rocket engines with ecologically friendly propellants
1 1., 1 1., 1 1.
Physical workflow model in the combustion chamber LREST with a jet-centrifugal jets on hypergolic propellants
Silyutin M.V., Shustov S.A.
The usage of high power supply capacity transport spacecraft
Ivanovich S.N.
The numerical modelling of processes in combustion chambers of low thrust rocket engines
Salich V.L.
Estimation of the required thrust impulse for small spacecraft (SSC) control system with a propulsion system using fuel gas components
Titov B.A., Koltsov I.V.
Optimal program of controlling continuous low thrust in the flight between noncoplanar elliptical and geostationary orbits
Fadeenkov P.V., Ishkov 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.
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.
Research of the possibility of thermal conditions LREST using an infrared thermal imaging system
Ryzhkov V.V., Silyutin M.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.
Optimization methods of design-ballistic characteristics circumterraneous and interplanetary space vehicle with electrojet engines of low thrust
1 1., 1 1., 1 1., 1 1., 1 1., 1 1., 1 1., 1 1., 1 1.
1 - 20 of 20 Items

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