- citations in SCIndeks: 0
- citations in CrossRef:0
- citations in Google Scholar:[
 ]
- visits in previous 30 days:4
- full-text downloads in 30 days:3
|
|
|
2020, vol. 70, iss. 2, pp. 22-28
|
|
Combustion stability analysis of composite propellants with octogen
Analiza stabilnosti sagorevanja kompozitnih raketnih goriva sa oktogenom
Ključne reči: čvrsto kompozitno raketno gorivo; oktogen; balistika; nestabilnost sagorevanja
Abstract
Research of operating pressure levels with irregular combustion and the effect on combustion instability of composite solid propellants with different quantity of octogen (HMX) are presented in this paper. The content of HMX increased in relation to the oxidant, ammonium perchlorate (AP). Combustion stability of the propellants was improved by adding titanium (IV) oxide powder and through the optimal projected ratio of two oxidizer fractions. Parameters of burning rate laws were determined and p-t diagrams were observed and compared.
Sažetak
U ovom radu prikazano je istraživanje u oblasti sagorevanja čvrstog kompozitnog raketnog goriva sa različitim udelom oktogena (NMH) odnosno izvršena je analiza kako bi se utvrdilo pri kojem nivou radnog pritiska dolazi do pojave nepravilnog sagorevanja goriva i koji su njegovi efekti. Udeo NMH povećavan je u sastavu goriva u poređenju sa oksidatorom, amonijum-perhloratom (AR). Stabilnost sagorevanja raketnih goriva poboljšana je dodatkom titan(IV)-oksida u sastave uz održavanje optimalno definisanog odnosa dve frakcije korišćenog oksidatora. Određeni su parametri u zakonu brzine sagorevanja, p-t dijarami su analizirani i međusobno poređeni.
|
|
|
|
References
|
|
|
*** (1997) SORS 7572/97 Brizantni (sekundarni) eksplozivi - oktogen, ciklotetrametilenetetranitramin. Beograd: Odeljenje za standardizaciju, metrologiju i nomenklaturu u SMO, Savezno ministarstvo odbrane
|
|
  
|
Beckstead, M.W. (2006) Recent progress in modeling solid propellant combustion. Combustion, Explosion, and Shock Waves, 42(6): 623-641
|
|
|
Kalman, J., Essel, J. (2017) Influence of particle size on the combustion of CL-20/HTPB propellants. Propellants, Explosives, Pyrotechnics, 42(11), 1261-1267
|
|
|
Kubota, N. (2015) Combustion of composite propellants: Combustion of composite propellants. in: Propellants and Explosives, Thermochemical Aspects of Combustion, Weinheim, Germany: Wiley-VCH Verlag GmbH & Co. KGaA
|
|
1
|
Lengellé, G., Duterque, J., Trubert, J.F. (2002) Combustion of solid propellants. in: RTO/VKI Special Course on 'Internal Aerodynamics in Solid Rocket Propulsion', Rhode-Saint-Genèse, Belgium, 27-31 May 2002, RTO-EN-023, pp 43-58
|
|
|
Rastogi, R.P., Singh, H.J., Deepak, D., Srivastava, A.K. (1978) Pressure dependence of burning rate of composite solid propellants. AIAA Journal, 16(5), 534-536
|
|
|
Rodić, V., Bogosavljević, M., Milojković, A., Brzić, S., Fidanovski, B., Gligorijević, N. (2017) Preliminary research of composite rocket propellants including octogene. Scientific Technical Review, vol. 67, br. 1, str. 3-12
|
|
|
Rodić, V., Dimić, M., Brzić, S., Gligorijević, N. (2015) Cast composite solid propellants with different combustion stabilizers. Scientific Technical Review, vol. 65, br. 2, str. 3-10
|
|
|
Rodić, V., Bogosavljević, M., Milojković, A., Mijatov, S. (2018) Preliminary research of composite rocket propellants with hexogen and titanium oxide powder. Scientific Technical Review, vol. 68, br. 2, str. 36-47
|
|
|
Yin, P., Zhang, J., Mitchell, L.A., Parrish, D.A., Qne, J.M. (2016) Shreeve Angew. Chem, 128, 13087 -13089 T 2016
|
|
|
|
|