Unit impulse input tests of a system of the «Frigate» upper-stage rocket - PDF (Russian)
Copyright (c) 2015 VESTNIK of the Samara State Aerospace University
Copyright (c) 2015 VESTNIK of the Samara State Aerospace University
ISSN 2542-0453 (Print)
ISSN 2541-7533 (Online)
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Keywords
Combustion chamber
Gas turbine engine
Mathematical model
Spacecraft
algorithm
blade
combustion chamber
design
efficiency
endurance limit
experiment
finite element method
gas turbine engine
mathematical model
modeling
optimization
residual stresses
simulation
spacecraft
structure
turbine
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Keywords
Combustion chamber
Gas turbine engine
Mathematical model
Spacecraft
algorithm
blade
combustion chamber
design
efficiency
endurance limit
experiment
finite element method
gas turbine engine
mathematical model
modeling
optimization
residual stresses
simulation
spacecraft
structure
turbine
Copyright (c) 2015 VESTNIK of the Samara State Aerospace University