@misc{Konrad_STEFAŃSKI_An_2018-12-30,
 author={Konrad STEFAŃSKI and Konrad STEFAŃSKI},
 copyright={Wojskowa Akademia Techniczna},
 copyright={Wojskowa Akademia Techniczna},
 address={Warszawa},
 address={Warszawa},
 howpublished={online},
 year={2018-12-30},
 year={2018-12-30},
 publisher={Wojskowa Akademia Techniczna},
 publisher={Wojskowa Akademia Techniczna},
 language={angielski},
 language={angielski},
 abstract={An analysis of application feasibility of a special method for surface-to-air missile (SAM) control during homing on an airborne target was carried out in this paper. A prior implementation of the method was motion control for a gyroscope axis with three degrees of freedom [1, 2] at the stages of spatial seeking and tracking of a detected target. The positive results obtained during that research led to a conclusion that the proposed control method would be appropriate for the determination of the control forces for missile guidance. This method consists in the application of the phase trajectories of control errors. Switching over of the control forces at suitable phase plane points reduced the control errors to zero and facilitated a proper flight path of the SAM. This paper presents a switching algorithm, equations of the kinematics and dynamics of SAM flight, and a number of examples of numerical simulations of the problem contemplated herein. The simulation results were represented in a graphic format.},
 abstract={An analysis of application feasibility of a special method for surface-to-air missile (SAM) control during homing on an airborne target was carried out in this paper. A prior implementation of the method was motion control for a gyroscope axis with three degrees of freedom [1, 2] at the stages of spatial seeking and tracking of a detected target. The positive results obtained during that research led to a conclusion that the proposed control method would be appropriate for the determination of the control forces for missile guidance. This method consists in the application of the phase trajectories of control errors. Switching over of the control forces at suitable phase plane points reduced the control errors to zero and facilitated a proper flight path of the SAM. This paper presents a switching algorithm, equations of the kinematics and dynamics of SAM flight, and a number of examples of numerical simulations of the problem contemplated herein. The simulation results were represented in a graphic format.},
 type={artykuł},
 type={artykuł},
 title={An Application of a Special Method for Designating the Control Forces for the Homing of an Anti-Aircraft Missile on an Aerial Target by Use of a Method of Proportional Navigation},
 title={An Application of a Special Method for Designating the Control Forces for the Homing of an Anti-Aircraft Missile on an Aerial Target by Use of a Method of Proportional Navigation},
 keywords={Samonaprowadzanie pocisku rakietowego na cel, Samonaprowadzanie pocisku rakietowego na cel},
}