Abstract

In this chapter, experimental results of an aluminized fuel-rich propellant having energetics similar to boron based fuel-rich propellant and also having no residue after combustion are discussed. This work focuses on the development of aluminum based fuel-rich propellants, which have zero residue, high density and burn rates of around 5–7 mm/s. Combustion studies using thermogravimetric analysis, differential scanning calorimetry, scanning electron microscope analysis of the quenched propellant and X-ray diffraction analysis of residue showed the role of binder melt in the burning of these propellants. However, in the propellants developed with higher binder content, the residue could not be reduced below the value of 10–13% by weight. Fuel-rich propellants made with higher loading of aluminum (30% by weight) resulted in zero residue.

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