000021393 001__ 21393
000021393 005__ 20170522124352.0
000021393 04107 $$aeng
000021393 046__ $$k2017-05-15
000021393 100__ $$aNocoń, Ł.
000021393 24500 $$aMODIFICATIONS OF CONTROL ACTUATION SYSTEMS OF ATGM

000021393 24630 $$n23.$$pEngineering Mechanics 2017
000021393 260__ $$bBrno University of Technology, Institute of Solid Mechanics, Mechatronics and Biomechanics, Brno
000021393 506__ $$arestricted
000021393 520__ $$2eng$$aThe paper presents the modifications of missile control actuation systems. The control actuation system was modified by adding a swiveling nozzle of the rocket engine. In that way, a hybrid control system consisting of aerodynamic rudders and gasodynamic rudders (i.e. change of the direction of the rocket engine thrust). The control effectiveness with the use of aerodynamic rudders alone was compared with ATGM control effectiveness with the use of the hybrid control actuation system. The results of the research are shown in a graphical form.

000021393 540__ $$aText je chráněný podle autorského zákona č. 121/2000 Sb.
000021393 653__ $$aAnti-tank guided missile, Engine thrust vectorization, Control actuation systems, Homing.

000021393 7112_ $$aEngineering Mechanics 2017$$cSvratka, CZ$$d2017-05-15 / 2017-05-18$$gEM2017
000021393 720__ $$aNocoń, Ł.$$iKoruba, Z.
000021393 8560_ $$ffischerc@itam.cas.cz
000021393 8564_ $$s939633$$uhttps://invenio.itam.cas.cz/record/21393/files/0714.pdf$$yOriginal version of the author's contribution in proceedings, page 714, section DYN.
000021393 962__ $$r21225
000021393 980__ $$aPAPER