Reactive Nanocomposites as Versatile Additives for Composite Propellants

Abstract

A new approach to improve the performance of composite propellants was developed in which reactive nanocomposites (RNCs) are used as replacements for aluminum powders in composite solid rocket propellants. The new materials are mechanically activated nanothermites comprising of nano-powders of aluminum as the fuel as well as oxides of copper, iron, molybdenum, or nickel as the oxidizer. The obtained RNCs were characterized using X-ray diffraction, scanning electron microscopy, and laser diffraction particle size analyzer. The obtained RNCs were used for preparation of modified composite solid * Prof. Dr. T. M. Klapötke 1222 rocket propellants (CSRPs). Burning rate, thermal decomposition behavior, heat of combustion, sensitivity, and mechanical properties of CSRPs were determined. The results showed increases in the combustion energy and the burning rate of the modified propellants were achieved, and that RNCs can be considered to be promising multifunction additives for composite solid rocket propellants. In addition, the mechanical properties and sensitivities of the modified propellants are within the desired range.

Influence of different crosslinking mixtures on the mechanical properties of composite solid rocket propellants based on HTPB

“…14,15 HTPB-based propellants have distinct advantages such as very high reliability, good processing, and unequaled mechanical performance. 16,17 Hocaoğlu et al 18 discussed the alteration in the mechanical behavior of the solid propellants based on HTPB and ammonium perchlorate (AP) during the curing process in relation to variation in the crosslink density (CLD) which was mainly calculated via the curing ratio ( R value), defined as the equivalent ratio of diisocyanate to total hydroxyl value, besides the corresponding ratio of triol to diol (triol/diol).…”

Burning rate measurement of composite propellant using acoustic wave emission in comparison with other techniques

“…The burning rate is a mainly characteristic parameter controlling the ballistic behavior of the solid rocket propellants and it is an operative factor for assessment the efficiency of the overall rocket motor design [1][2][3] . The burning rate of rocket propellants is subject to an exponential relation so it must be controlled throughout the burning period to avoid catastrophic rise in chamber pressure or abnormal, interrupted, unstable burning or chuffing phenomenon [4] .…”

Improving the Mechanical Properties of Glycidyl Azide Polymeric Matrix Used in Composite Solid Rocket Propellant by Adding Advanced Cross‐Linker

“…For several years, composite solid rocket propellants (CSRP) based on hydroxyl terminated polybutadiene (HTPB) binder system are considered the most usable rocket propellants . The mechanical properties, performance and thermal decomposition kinetics of HTPB based propellants are superior compared with other propellants . Glycidyl azide polymer (GAP) is an energetic binder used to produce propellants with performance higher than HTPB based traditional CSRP .…”