Obiekt

Tytuł odmienny:

Analiza rozkładu termicznego stałych paliw rakietowych ; Analiza rozkładu termicznego stałych paliw rakietowych

Współtwórca:

Janusz ZMYWACZYK, Piotr KONIORCZYK ; Janusz ZMYWACZYK, Piotr KONIORCZYK

Abstrakt:

The paper presents results of thermal decomposition analysis of selected solid rocket propellants. Homogeneous propellant PAC and heterogeneous propellant H2 were subjected to simultaneous thermal analysis with the use of NETZSCH STA 2500 Regulus device with five heating rates of 2.5, 5, 7.5, 10 and 15 K/min. The method combines TG, DTG and DTA analytical techniques in a single measurement. The aim of the conducted experiments was to study thermal decomposition of these energetic materials as well as to determine activation energy of the decomposition process and the preconditioning factor from the TG curves. The tested materials properties and chemical composition along with a brief description of the experimental procedure are described. The inverse procedure of calculating the activation energy, based on the Ozawa-Flynn-Wall model is described. Finally, the results of thermal decomposition of two tested solid rocket propellants are presented along with maximum decomposition rates and percentage of mass loss.
; The paper presents results of thermal decomposition analysis of selected solid rocket propellants. Homogeneous propellant PAC and heterogeneous propellant H2 were subjected to simultaneous thermal analysis with the use of NETZSCH STA 2500 Regulus device with five heating rates of 2.5, 5, 7.5, 10 and 15 K/min. The method combines TG, DTG and DTA analytical techniques in a single measurement. The aim of the conducted experiments was to study thermal decomposition of these energetic materials as well as to determine activation energy of the decomposition process and the preconditioning factor from the TG curves. The tested materials properties and chemical composition along with a brief description of the experimental procedure are described. The inverse procedure of calculating the activation energy, based on the Ozawa-Flynn-Wall model is described. Finally, the results of thermal decomposition of two tested solid rocket propellants are presented along with maximum decomposition rates and percentage of mass loss.

Miejsce wydania:

Warszawa
; Warszawa

Wydawca:

Wojskowa Akademia Techniczna ; Wojskowa Akademia Techniczna

Data utworzenia:

2010 r.0

Data złożenia:

2018-10-04 ; 2018-10-04

Data akceptacji:

2019-05-27 ; 2019-05-27

Data wydania:

2019-06-30 ; 2019-06-30

Rozmiar:

B5 ; B5

Identyfikator:

oai:ribes-88.man.poznan.pl:2547

Sygnatura:

DOI 10.5604/01.3001.0013.2115 ; DOI 10.5604/01.3001.0013.2115

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:

43 ; 43

Strona końcowa:

54 ; 54

Tom:

10 ; 10

Słowa kluczowe:

solid rocket propellants, thermal decomposition analysis, activation energy ; solid rocket propellants, thermal decomposition analysis, activation energy