THE USE OF GYROSCOPIC EXECUTIVE SYSTEM FOR HOMING OF THE MISSILE ON THE AERIAL TARGET
Abstract eng: 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.
Contributors:
Publisher:
Brno University of Technology, Institute of Solid Mechanics, Mechatronics and Biomechanics, Brno
Conference Title:
Conference Title:
Engineering Mechanics 2017
Conference Venue:
Svratka, CZ
Conference Dates:
2017-05-15 / 2017-05-18
Rights:
Text je chráněný podle autorského zákona č. 121/2000 Sb.
Record appears in:
Record created 2017-05-22, last modified 2017-05-22
guest ::
