Engineering Mechanics

Proceedings Vol. 23 (2017)

ENGINEERING MECHANICS 2017

Copyright © 2017 Brno University of Technology, Faculty of Mechanical Engineering, Institute of Solid Mechanics, Mechatronics and Biomechanics, Brno

 

Stefański K., Chatys R., Stefańska A.
pages 918 - 921, full text

The paper considers the possibility of use of the executive system for missile flight control in the form of fast rotating rotor, versatile suspended in the rocket body. The constrained deviations of the rotor axis (gyroscope) relative to the body axis generate the moments of force which change the missile flight direction and cause its homing on the moving target. Some of the numerical simulation results were presented in the graphic form.

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