Pesquisa

Edição
Título
Autores
The capacity of burners for combustion chambers with reduced nitrogen oxide content in combustion products of the NK-16ST gas turbine engine
Baklanov A.
The choice of the energy parameters of an oxygen-hydrogen propellant expander cycle rocket engine
Belyakov V.
Development of the two-fuel combustion chamber and calculation of processes for the theory of turbulent burning
Baklanov A.
INCREASE OF EFFICIENCY OF GAS DISTRIBUTION IN THE ACCELERATINGCHANNEL OF AN ELECTROJET ENGINE
Gopanchuk V., Zhasan V., Potapenko M., Gopanchuk V., Zhasan V., Potapenko M.
Development of an experimental unit and methodology for ground-based experimental testing of two-phase thermoregulation systems for spacecrafts
Khodenkov A., Delkov A.
SPACECRAFT THERMAL VACUUM OPTIMIZATION: DEVELOPMENT OF NEW TENDENCIES
Krat S., Khristich V., Krat S., Hristkh V.
Concentration of carbon dioxide in products of combustion of GTE NK-16ST and NK-16-18ST
Baklanov A.
INFLUENCE OF FILLING PROCESSES FOR MIXING HEAD OF GAS GENERATORS ON DYNAMICS OF LIQUID ROCKET ENGINE WITHOUT STARTER DEVICE
Belayev E., Vorobyev A.
Modeling of the stress-strain state of rocket-space technology structural elements manufactured by using additive technologies
Ushakova E.
CAMERA-TO-TOUCHSCREEN DESIGN
Likhonina R., Kohout L., Kadlec J.
Modeling of the stress-strain state of rocket-space technology structural elements manufactured by using additive technologies
Ushakova E.
The Method of CALCULATION OF THERMAL STATE OF CHAMBER FOR steady state IMPULSE operation OF LIQUID ROCKET ENGINE OF SMALL THRUST
Vorobyev A., Vorobyeva S.
The influence of the method of fuel supply into the combustion chamber on the quality of mixing and on the carbon oxide formation
Baklanov A.
The possibility of using methane-hydrogen fuel in converted gas turbine engines for power plants
Baklanov A.
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