Bonding agensi za kompozitna raketna goriva / Bonding agents for composite rocket propellants

• Main Author: Mirjana Petrić
• Format: Article
• Language: English
• Published: University of Defence in Belgrade 2003-01-01
• Series: Vojnotehnički Glasnik
• Subjects: kompozitna goriva; HTPB; mehaničke osobine; bonding agensi; hidantoin; composite propellants; mechanical properties; bonding agents; hydantoine
• Online Access: http://scindeks-clanci.ceon.rs/data/pdf/0042-8469/2003/0042-84690301051P.pdf
• ISSN: 0042-8469; 2217-4753

U radu je analiziran uticaj bonding agensd na mehaničke karakteristike i viskozitet kompozitnih raketnih goriva na bazi hidroksiterminiranog polibutadiena i toluendiizocijanata, odnosno izoforondiizocijanata. Komparirana je efikasnost bonding agensd (BA) različite strukture trietilentetramina (TET), tris-(2-metil aziridinil) fosfin oksida (MAPO) i N,N-di (2-hidroksietil)-4,4-dimetilhidantoina (DHE). Efikasnost delovanja bonding agensa utvrdenaje na osnovu parametara dobijenih iz testa jednoosnog zatezanja uzoraka (σm - zatezna čvrstoća pri maksimalnoj sili, εm relativno izduženje pri maksimalnoj sili i εp - relativno izduženje pri prekidu). Mehaničke karakteristike merene su u temperaturskom području od -50°C do 50°C. Analiziran je uticaj BA na brzinu promene viskoziteta goriva. / The paper analyzes the effects of bonding agents on mechanical properties and viscosity of composite rocket propellants based on hydroxiterminated polybutadiene and toluendiizocyanate, i.e. izophorondiizocyanate. The efficiency of bonding agents (BA) of different structure has been compared including triethylentetramine (TET), tris-(2-methyl azyrinidile) phosphine oxide (MAPO) and N, N-di (2-hydroxiethyl)-4,4-dimethylhydantoine (DHE). The BA efficiency has been determined on the basis of parameters obtained by uniaxial tensile tests (σm - tensile strength at maximum force, εm - relative allongation at maximum force and εp - relative allongation at fracture). The mechanical properties have been measured at the temperature range from -50°C to 50°C. The BA effects on propellant viscosity change rates have been analyzed.