Balu, R and Marathe, AG and Paul, PJ and Mukunda, HS (1991) Analysis of performance of a hot gas injection thrust vector control system. In: Journal of Propulsion and Power, 7 (4). pp. 580-585.
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The complex three-dimensional flowfield produced by secondary injection of hot gases in a rocket nozzle for thrust vector control is analyzed by solving unsteady three-dimensional Euler equations with appropriate boundary conditions. Various system performance parameters like secondary jet amplification factor and axial thrust augmentation are deduced by integrating the nozzle wall pressure distributions obtained as part of the flowfield solution and compared with measurements taken in actual static tests. The agreement is good within the practical range of secondary injectant flow rates for thrust vector control applications.
|Item Type:||Journal Article|
|Additional Information:||Copyright of this article belongs to American Institute of Aeronautics and Astronautics.|
|Department/Centre:||Division of Mechanical Sciences > Aerospace Engineering (Formerly, Aeronautical Engineering)
Division of Mechanical Sciences > Mechanical Engineering
|Date Deposited:||09 Nov 2010 07:58|
|Last Modified:||24 Feb 2012 06:52|
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