Abstract
The paper presents influence of additives like aluminium, magnesium, AMD (aluminium-magnesium dust) and boron on selected properties of heterogeneous solid rocket propellants (HSRP) based on HTPB in which ammonium chlorate was partly replaced by sodium nitrate. The presence of sodium nitrate reduces the content of hydrogen chloride (HCl) in combustion products. Theoretical values of thermochemical and thermodynamical properties like isochoric heat of combustion (Q), specific impulse (Isp) and combustion products in motor chamber and nozzle were identified by ICT-Code program. A laboratory rocket motor (LRM) was used to examine ballistic properties for prepared samples of propellants. Their temperature of decomposition, heat of combustion and hardness were tested both with sensitivity to mechanical stimuli (impact, friction) and rheological properties at curing.
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