US 5,334,270 A · Controlled burn rate, reduced smoke, solid propellant formulations

Abstract

Solid rocket motor propellant formulations are provided which are capable of burning at at least two selected burn rates. The burn rate is controlled by controlling the pressure at which the propellant burns. For example, it is possible to mechanically modify the container, such as a rocket motor casing, in which the propellant is held in order to modify the pressure under which the propellant burns. Alternatively, the propellant may be configured or molded such that the pressure changes at a chosen time due to the process of burning the propellant. The propellant is capable of burning at a relatively constant burn rate at a chosen pressure. Once the pressure changes within chosen limits, the burn rate of the propellant is rapidly modified to another relatively constant burn rate. The solid rocket motor propellant is formulated with the addition of from about 0.5% to about 4.0% TiO.sub.2. The specific operating pressures and burn rates can be selected by modifying the amount of TiO.sub.2 added, the modifying particle size of the various ingredients, and modifying the specific ingredients used.

Claims18

Dependent claims

A solid rocket motor propellant comprising:

from about 6% to about 10% binder, said binder consisting essentially of hydroxy-terminated polybutadiene binder;
from about 65% to about 90% ammonium perchlorate;
and
from about 0.3% to about 5.0% refractory oxide selected from the group consisting of TiO.sub.2, and SiO.sub.2 ;
said propellant formulated such that it burns at at least two stable burn rates over at least two corresponding pressure ranges such that the propellant provides boost-sustain operation when burned in a solid rocket motor.

2 more elements

Dependencies are inferred from the claim text.

Controlled burn rate, reduced smoke, solid propellant formulations

Life of this patent

Controlled burn rate, reduced smoke, solid propellant formulations

Life of this patent

Abstract

Claims18