Obiekt

Tytuł odmienny:

Zastosowanie specjalnego sposobu wyznaczania sił sterujących do realizacji samonaprowadzania na cel powietrzny przeciwlotniczego pocisku rakietowego z wykorzystaniem metody proporcjonalnej nawigacji ; Zastosowanie specjalnego sposobu wyznaczania sił sterujących do realizacji samonaprowadzania na cel powietrzny przeciwlotniczego pocisku rakietowego z wykorzystaniem metody proporcjonalnej nawigacji

Abstrakt:

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.
; 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.

Miejsce wydania:

Warszawa
; Warszawa

Wydawca:

Wojskowa Akademia Techniczna ; Wojskowa Akademia Techniczna

Data utworzenia:

2010 r.0

Data złożenia:

2018-12-18 ; 2018-12-18

Data wydania:

2018-12-30 ; 2018-12-30

Rozmiar:

B5 ; B5

Identyfikator:

oai:ribes-88.man.poznan.pl:2532

Sygnatura:

DOI 10.5604/01.3001.0012.7339 ; DOI 10.5604/01.3001.0012.7339

ISSN elektroniczny:

2720-5266 ; 2720-5266

ISSN drukowany:

2081-5891 ; 2081-5891

Język:

angielski ; angielski

Właściciel praw:

Wojskowa Akademia Techniczna ; Wojskowa Akademia Techniczna

Strona początkowa:

149 ; 149

Strona końcowa:

162 ; 162

Tom:

9 ; 9

Słowa kluczowe:

mechanics, control, phase trajectories, homing, target ; mechanics, control, phase trajectories, homing, target