Propellant material with oxidizer reduction to lead oxide

Abstract

A solid propellant acts in a chamber to propel a member such as a rocket, the chamber being closed to the atmosphere. The propellant provides high density-impulses and, when combusted, produces end products which do not have any deleterious effects. The propellant preferably includes a binder having hydrocarbon linkages and a lead compound oxidizer formed from an inorganic lead oxidizer salt. This oxidizer has dense characteristics and stable properties at ambient temperatures and through a particular range of temperatures above ambient. The propellant also includes a fuel additive, preferably a metal such as aluminum, having properties of being oxidized by the oxidizer and of reducing the lead. The fuel additive has a percentage by weight relative to the lead compound oxidizer to reduce the lead to lead oxide. The fuel additive is preferably included in the propellant in the range to approximately twenty percent (20%) by weight and is preferably in a fragmentary form. The binder is preferably included in the range of approximately eight percent (8%) to ten percent (10%) by weight. A second oxidizer such as potassium perchlorate may also be included in the propellant. The oxidizers are preferably included in the propellant in the range of approximately seventy-two percent (72%) to ninety-two percent (92%) by weight. An additional binder such as carbon can also be included in the propellant.