Aerodynamic derivatives of the model of the jettisonable module of the emergency rescue system at hypersonic velocities
N.P. Adamov1, L.N. Puzyrev1, A.M. Kharitonov1, E.A. Chasovnikov1, A.A. Dyadkin2, and A.N. Krylov2
1 Khristianovich Institute of Theoretical and Applied Mechanics SB RAS, Novosibirsk, Russia
2 Korolev Rocket and Space Corporation “Energia”, Korolev, Moscow Region, Russia
E-mail: khar@itam.nsc.ru
Keywords: jettisonable module model, free oscillations, oscillation frequency, damping decrement, aerodynamic derivatives
Pages: 729–738
Abstract
The model, experimental equipment, and test program are briefly described. A method of determining the aero-dynamic characteristics of the model on the facility with free oscillations is presented. Aerodynamic derivatives of the pitching moment of the model are obtained for two positions of the axis of rotation and Mach numbers M∞ = 2, 4, and 6. At M∞ = 2, the model with the rear position of the axis of rotation is not balanced at low angles of attack, whereas irregular self-sustained oscillations of the model with the frontal position of the axis of rotation arise.
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