Theory is developed for internal aerodynamics of nozzle, to be employed as thrust vector control device of solid propellant rockets; theory is based on three-dimensional, small-perturbation treatment of originally undistributed supersonic source flow; nozzle scaling, pivot point location for minimum actuation power, splitline geometry effects, thrust-vector-deflection amplification and suppression, and implications of designing for low actuation torques are considered; comparison with experiment.
Theory of aerodynamics of supersonic splitline gimbaled nozzle
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 4 , n 2
1967
8 pages
Article (Journal)
English
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Gimbaled, partially submerged rocket nozzle Patent
NTRS | 1965
|Gimbaled, Partially Submerged Rocket Nozzle
NTIS | 1965
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