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A parametric investigation of Dual-throat nozzle bypass channel configurations for advanced Aviation applications [PDF]
HeliyonThe Bypass Dual-Throat Nozzle (BDTN) has garnered growing attention due to its remarkable thrust vectoring capabilities. This type of nozzle boasts broad application prospects as it achieves deflection control of the jet stream merely through regulating ...
Shuai Huang +4 more
doaj +4 more sources
Numerical Investigation on the Thrust Vectoring Performance of Bypass Dual Throat Nozzle
Energies, 2023 Modern aircraft and missiles are gradually integrating thrust vector control systems to enhance their military capabilities. Bypass Dual-Throat Nozzle (BDTN) control is a new fluidic thrust vectoring technique capable of achieving superior performance ...
Saadia Afridi +6 more
doaj +6 more sources
Simulation of the Bypass Dual Throat Nozzle and investigation of parameters affecting the change of thrust vector angle [PDF]
فناوری در مهندسی هوافضا, 2023 The aim of this study was to investigate the effects of three parameters including secondary flow injection angle, secondary flow injection location and bypass section geometry on the deflection angle of the thrust vector.
Amir Mohammad Neyzan Hosseini +1 more
doaj +2 more sources
AerospaceThe bypass dual-throat nozzle is based on the dual-throat nozzle, which is a fluidic thrust vector nozzle suitable for integration into rocket motors in a symmetrical manner.
Xuefeng Xia +5 more
doaj +2 more sources
Numerical study of a trapezoidal bypass dual throat nozzle
Chinese Journal of Aeronautics, 2023 Shuai HUANG +6 more
openaire +3 more sources
Techniques of Fluidic Thrust Vectoring in Jet Engine Nozzles: A Review
Energies, 2023 Thrust vectoring innovations are demonstrated ideas that improve the projection of aerospace power with enhanced maneuverability, control effectiveness, survivability, performance, and stealth.
Saadia Afridi +5 more
doaj +1 more source
Flow Simulation of Supersonic Inlet with Bypass Annular Duct [PDF]
, 2011 A relaxed isentropic compression supersonic inlet is a new concept that produces smaller cowl drag than a conventional inlet, but incurs lower total pressure recovery and increased flow distortion in the (radially) outer flowpath.
Conners, Timothy R. +4 more
core +2 more sources
Computer code for single-point thermodynamic analysis of hydrogen/oxygen expander-cycle rocket engines [PDF]
This analysis and this computer code apply to full, split, and dual expander cycles. Heat regeneration from the turbine exhaust to the pump exhaust is allowed.
Glassman, Arthur J., Jones, Scott M.
core +1 more source
Optimization of Bypass Flow Introduction Angle in Dual-Throat Nozzle
Journal of Electrical SystemsThis research paper investigates the optimal angle for introducing a bypass jet in rocket engines for thrust vectoring. Numerical simulations using a finite-volume method were performed to test a range of bypass jet angles and their effect on flow performance.
openaire +1 more source