Multiparameter Optimization of Thrust Vector Control with Transverse Injection of a Supersonic Underexpanded Gas Jet into a Convergent Divergent Nozzle
نویسندگان
چکیده
The optimal design of the thrust vector control system solid rocket motors (SRMs) is discussed. injection a supersonic underexpanded gas jet into diverging part engine nozzle considered, and multiparameter optimization geometric shape parameters flow developed. turbulent viscous compressible in main simulated with Reynolds-averaged Navier–Stokes (RANS) equations shear stress transport (SST) turbulence model. An procedure automatic generation block-structured mesh conjugate gradient method applied to find problem interest. Optimization include pressure ratio injected jet, angle inclination axis nozzle, distance from throat outlet section nozzle. location varies 0.1 0.9 respect length nozzle; 30 160 degrees; an ellipse aspect that 1. computed fluid combustion chamber compared experimental computational results. dependence as function obtained, conclusions are made about effects input on coefficient.
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ژورنال
عنوان ژورنال: Energies
سال: 2021
ISSN: ['1996-1073']
DOI: https://doi.org/10.3390/en14144359