Object

Współtwórca:

Berko ZECEVIC, Mario BASKARAD,Alan CATOVIC, Sabina SERDAREVIC-KADIC ; Berko ZECEVIC, Mario BASKARAD,Alan CATOVIC, Sabina SERDAREVIC-KADIC

Abstrakt:

A modular computer program named SPPMEF has been developed which is intended for purposes of predicting internal ballistic performances of solid propellant rocket motors. The program consists of the following modules: TCPSP (Calculation of thermo-chemical properties of solid propellants), NOZZLE (Dimensioning of nozzle and estimation of losses in rocket motors), GEOM (This module consists of two parts: a part for dimensioning of the propellant grain and a part for regression of burning surface) and ROCKET (This module provides prediction of an average delivered performance, as well as mass flow, pressure, thrust and impulse as functions of burning time). The program is verified with experimental results obtained from standard ballistic rocket test motors and experimental rocket motors. Analysis of results has shown that the established model enables high accuracy in prediction of solid propellant rocket motors features in cases where influence of combustion gases flow on burning rate is not significant.
; A modular computer program named SPPMEF has been developed which is intended for purposes of predicting internal ballistic performances of solid propellant rocket motors. The program consists of the following modules: TCPSP (Calculation of thermo-chemical properties of solid propellants), NOZZLE (Dimensioning of nozzle and estimation of losses in rocket motors), GEOM (This module consists of two parts: a part for dimensioning of the propellant grain and a part for regression of burning surface) and ROCKET (This module provides prediction of an average delivered performance, as well as mass flow, pressure, thrust and impulse as functions of burning time). The program is verified with experimental results obtained from standard ballistic rocket test motors and experimental rocket motors. Analysis of results has shown that the established model enables high accuracy in prediction of solid propellant rocket motors features in cases where influence of combustion gases flow on burning rate is not significant.

Miejsce wydania:

Warszawa
; Warszawa

Wydawca:

Wojskowa Akademia Techniczna ; Wojskowa Akademia Techniczna

Data utworzenia:

2010 r.0

Data wydania:

2011-12-30 ; 2011-12-30

Rozmiar:

B5 ; B5

Identyfikator:

oai:ribes-88.man.poznan.pl:2338

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:

7 ; 7

Strona końcowa:

26 ; 26

Tom:

2 ; 2

Słowa kluczowe:

rocket motors, solid propellant, burning rate, internal ballistic performances prediction, losses, computer program ; rocket motors, solid propellant, burning rate, internal ballistic performances prediction, losses, computer program