Obiekt

Współtwórca:

Dariusz SOKOŁOWSKI,Zbigniew LEWANDOWSKI ; Dariusz SOKOŁOWSKI,Zbigniew LEWANDOWSKI

Abstrakt:

This paper discusses analytical method for realization of preliminary missile stability design calculations. Action has been taken to estimate influence of replacing massive blocks of analogue electronics with compact solutions of digital electronics in missiles remaining in operation. On an example of a short-range 9M33M3 missile from 9K33 „OSA” set and its previously analysed aerodynamic characteristics, the analysis of the centre of gravity location impact was carried out to determine maximum loads occurring in the two most interesting phases of flight: after booster engine burnout and directly after cruise engine burnout. The suggestion for modification suggestion of flight parameters’ optimization is presented which defines stability and its critical impact of these parameters on aeronautical engineering. For the tested missile, the methodology suggestions for the modification is discussed with the comparison of serially produced copies to define the ability of improving the flight parameters. The paper includes visualizations and quantity analysis of: maximal loads on the fuselage, minimal turn radius, and control wing inclination angle as missile’s angle of attack function.
; This paper discusses analytical method for realization of preliminary missile stability design calculations. Action has been taken to estimate influence of replacing massive blocks of analogue electronics with compact solutions of digital electronics in missiles remaining in operation. On an example of a short-range 9M33M3 missile from 9K33 „OSA” set and its previously analysed aerodynamic characteristics, the analysis of the centre of gravity location impact was carried out to determine maximum loads occurring in the two most interesting phases of flight: after booster engine burnout and directly after cruise engine burnout. The suggestion for modification suggestion of flight parameters’ optimization is presented which defines stability and its critical impact of these parameters on aeronautical engineering. For the tested missile, the methodology suggestions for the modification is discussed with the comparison of serially produced copies to define the ability of improving the flight parameters. The paper includes visualizations and quantity analysis of: maximal loads on the fuselage, minimal turn radius, and control wing inclination angle as missile’s angle of attack function.

Miejsce wydania:

Warszawa
; Warszawa

Wydawca:

Wojskowa Akademia Techniczna ; Wojskowa Akademia Techniczna

Data utworzenia:

2010 r.0 ; 2010 r.0

Data złożenia:

2018-09-21 ; 2018-09-21

Data akceptacji:

2020-08-20 ; 2020-08-20

Data wydania:

2020-09-30 ; 2020-09-30

Rozmiar:

B5 ; B5

Identyfikator:

oai:ribes-88.man.poznan.pl:2588

Sygnatura:

DOI 10.5604/01.3001.0014.3704 ; DOI 10.5604/01.3001.0014.3704

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:

9 ; 9

Strona końcowa:

18 ; 18

Tom:

11 ; 11

Słowa kluczowe:

flight mechanics, short-range missile, missile stability ; flight mechanics, short-range missile, missile stability