000021444 001__ 21444
000021444 005__ 20170522124355.0
000021444 04107 $$aeng
000021444 046__ $$k2017-05-15
000021444 100__ $$aStefański, K.
000021444 24500 $$aTHE USE OF GYROSCOPIC EXECUTIVE SYSTEM FOR HOMING OF THE MISSILE ON THE AERIAL TARGET

000021444 24630 $$n23.$$pEngineering Mechanics 2017
000021444 260__ $$bBrno University of Technology, Institute of Solid Mechanics, Mechatronics and Biomechanics, Brno
000021444 506__ $$arestricted
000021444 520__ $$2eng$$aThe 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.

000021444 540__ $$aText je chráněný podle autorského zákona č. 121/2000 Sb.
000021444 653__ $$aHoming, Missile, Control, Rotor, Gyroscope, Target.

000021444 7112_ $$aEngineering Mechanics 2017$$cSvratka, CZ$$d2017-05-15 / 2017-05-18$$gEM2017
000021444 720__ $$aStefański, K.$$iStefańska, A.$$iChatys, R.
000021444 8560_ $$ffischerc@itam.cas.cz
000021444 8564_ $$s838209$$uhttps://invenio.itam.cas.cz/record/21444/files/0918.pdf$$yOriginal version of the author's contribution in proceedings, page 918, section DYN.
000021444 962__ $$r21225
000021444 980__ $$aPAPER