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Automated thermovacuum firing test facility for testing and research of workflow in low-thrust rocket engine on hypergolic propellants
Galperin R.N., Ivashin Y.S., Nigodjuk V.E., Ryzhkov V.V., Sulinov A.V.
Experimental researches of possible low-thrust rocket adaptation developed by FSUE R&DIME for bipropellant MON-3+MMH providing tolerable thermal state thrusters
Beshenev Y.A., Buldashev S.A., Kazankin F.A., Lemskiy N.V., Semkin Y.V.
Experimental research of thermal yet influence of staff LTRE upon the construction models of airspace devices
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.
Experimental research of staff LTRE with hypergolic propellant under impulse engaging conditions
Shustov S.A.
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.
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.
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.
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.
1 - 10 of 10 Items

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