Сalculated analysis of the influence of operation and design factors on the parameters of oxygen-hydrogen low-thrust rocket engines
Ryzhkov V.V., Morozov I.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.
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.
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.
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.
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.
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.
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.
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.
The structure of knowledge base to support the development of low-thrust liquid-propellant rocket engines based on computer technologies
Ryzhkov V.V.
1 - 11 of 11 Items

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