On the Use of Fluorine‐Containing Nano‐Aluminum Composite Particles to Tailor Composite Solid Rocket Propellants

Abstract

The burning rate of solid propellants is an important factor for optimizing rocket motors and improving performance. The enhanced burning rate can increase thrust and reduce a propulsion system's overall size and weight. In this study, a novel nano-aluminum/THV composite additive was prepared and introduced into a solid ammonium perchlorate/polybutadiene composite solid rocket propellant to enhance its burning rate. The morphology of the composite particle additive and its effects on combustion were characterized. The use of small quantities (< 15 wt.%) of the additive resulted in a burning rate enhancement of up to 2.1 times that of the conventional coarse aluminized propellant with a specific impulse loss of only 3 seconds, and as much as 4.7 times enhancement with a predicted loss of 22 seconds in theoretical specific impulse. Some of this loss may be recovered by the improved combustion efficiency in smaller rocket motors because the additive was shown to significantly reduce the aluminum agglomeration at the propellant burning surface and reduce the size of reaction products which may reduce two-phase flow losses. The additive also provides wide burning rate tailorability, favorable for motor, grain, and thrust curve design. The burning rate enhancement mechanism is thought to be a physical cratering mechanism governed by the burning rate disparity between the binder/oxidizer system and the nano-aluminum/fluoropolymer additive and not a chemical catalytic effect.

Production of anhydrous hydrogen fluoride from fluorosilicic acid: a review

“…In aerospace, AHF is a component in the synthesis of propellants used in liquid rocket engines ( Feng et al, 2009 ). It helps produce high-energy compounds, such as oxidizers for rocket fuel ( Uhlenhake et al, 2022 ). Additionally, AHF-derived compounds serve as additives to improve the stability and performance of these propellants.…”

Reduction of agglomeration effect by aluminum trihydride in solid propellant combustion

“…Agglomerates formed during combustion generate condensed combustion products (CCPs) that have detrimental effects on the solid rocket motor system. These effects include specific impulse loss due to incomplete aluminum combustion and two-phase flow effect, slag deposition near the nozzle, ablation of the internal insulation layer caused by particle erosion, and motor operation instability [3][4][5][6]. To improve the motor performance, the suppression of aluminum agglomeration becomes a critical consideration in the design of propellant formulations.…”