High burning rate tactical solid rocket propellant, and related method
AssigneeThe United States of America as represented by the Secretary of the Navy
InventorsJohn M. Kelley, Robert C. Gill
Life of this patent
Estimating the term…
Abstract
The invention is a composition for a high burning-rate solid rocket propellant, where the composition includes a binder compounded with a soluble energetic additive; a metallic fuel; and an oxidative fuel. The resulting composition has a tactical Class 1.3 hazard rating, and a linear regression rate that is substantially equivalent to a tactical Class 1.1 hazard rating obtainable using solid rocket propellants. The composition may include a heat-conducting element, a plasticizer, a curing component, a combustion catalyst, and curing catalyst.
Claims14
A composition for a high burning-rate solid rocket propellant, consisting essentially of:
- a plasticizer;
- a soluble energetic additive being dissolved in a plasticizer;
- a binder being dissolved with the soluble energetic additive in solution;
- a metallic fuel;
- and
- an oxidative fuel,
- wherein said composition includes a tactical Class 1.3 hazard rating, and a linear regression rate substantially equivalent to a tactical Class 1.1 hazard rating of a solid rocket propellant;
- a cure catalyst;
- a combustion catalyst for facilitating burning;
- a curing agent;
- an antioxidant;
- a bonding agent;
- a processing agent;
- and
- a heat-conducting element,
- wherein said plasticizer is an inert liquid plasticizer,
- wherein said inert liquid plasticizer is a non-nitroplasticizer selected from at least one of TA (triacetin), DOP (dioctyl phthalate), DOA (dioctyladipate), DOM (dioctylmaleate), DBP (dibutylphthalate), and adiponitrile,
- wherein said heat conducting element is selected from at least one of whiskers, wires, staples, spheres, flakes, and nano-phase particles, and
- wherein the combustion catalyst is selected from one of copper chromite, nano-Fe2O3, nano-AL ferrocenes, and carboranes.
A composition for a high burning-rate solid rocket propellant, consisting of:
- a plasticizer;
- a soluble energetic additive being dissolved in a plasticizer;
- a binder being dissolved with the soluble energetic additive in solution;
- a heat-conducting element;
- a metallic fuel;
- an oxidative fuel;
- a cure catalyst;
- a curing agent;
- an antioxidant;
- a bonding agent;
- a processing agent;
- an opacifier;
- a colorant for visually illustrating homogeneity;
- and
- a combustion catalyst for facilitating burning,
- wherein said plasticizer is an inert liquid plasticizer,
- wherein said composition includes a predetermined thermochemical energy density and a predetermined chemical kinetic rate of regression,
- wherein said inert liquid plasticizer is a non-nitroplasticizer selected from at least one of TA (triacetin), DOP (dioctyl phthalate), DOA (dioctyladipate), DOM (dioctylmaleate), DBP (dibutylphthalate), and adiponitrile,
- wherein said heat conducting element is selected from at least one of whiskers, wires, staples, spheres, flakes, and nano-phase particles, and
- wherein the combustion catalyst is selected from one of copper chromite, nano-Fe2O3, nano-AL ferrocenes, and carboranes.
Dependencies are inferred from the claim text.