Possibility of Aluminium/Magnesium Exchange in Composite Rocket Propellants

 

Vesna Rodić

Marica Bogosavljević

Saša Brzić

Bojana Fidanovski

 

Composite solid propellants based on ammonium perchlorate/hydroxyterminated polybutadiene/isophorone dyisocyanate including two metal components: aluminium and magnesium with different contents have been represented in this paper. The mass of metal powder has increased in relation to oxidant, with constant bimodal fraction ratio and total solid phase. Parameters of burning rate laws, apparent viscosity, uniaxial mechanical characteristic, density and energetic values have been determined and compared in accordance to the propellants of the smoke reduction research.

 

Key words: composite rocket propellant, ammonium perchlorate, hydroxyterminated polybutidiene, aluminium, magnesium, ballistic characteristics, mechanical characteristics, comparison results.