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Published in:
2017 | OriginalPaper | Chapter
Transverse Jet Injection into a Supersonic Nozzle Flow
Authors : V. Emelyanov, K. Volkov, M. Yakovchuck
Published in: 30th International Symposium on Shock Waves 1
Publisher: Springer International Publishing
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Abstract
Thrust vectoring technique can deflect the mean flow of an engine jet from the centerline in order to transfer some force to the aimed axis. The secondary injection thrust vector control is particularly attractive for thrust vectoring in large boosters (especially solid propellant rocket) where large side thrust is generated. Injection of a secondary fluid into the divergent section of the nozzle causes an asymmetrical distortion of the exhaust gas flow. In addition to providing a propulsive force to a flying vehicle or a rocket, a rocket propulsion system can also provide certain control mechanisms to change vehicle’s attitude and trajectory via thrust vector control systems. On contrary to mechanically operating thrust vector control systems, such as gimbaled nozzles and jet vanes, which require actuators to deflect mechanical parts, secondary injection does not require any moving parts and regulated by the fluid injection, which reduces axial thrust force losses while changing the direction of the vector.