USA As Represented by Secretary of the Navy

Douglas J Elstrodt

Kerry L Wagaman

Jan Puszynski

Joel P Fields

James E Rose

Kenneth K Kuo

Christopher J Fawls

Timothy J Dunn

Michael L Hudson

A gas generating process, which is for the continuous production of energy and hydrogen for rocket and other propulsion and is also for the continuous production of hydrogen, utilizes the reaction of metallic materials, particularly aluminum, with organic materials, particularly hydrocarbons provided as jet fuel, and with water or an oxidizer which is predominantly water. In comparison with related reactions, the reaction produces hot gases containing more hydrogen and the products have a lower temperature for the same specific impulse. The process incorporates organic liquids with metallic powders to produce desirable, lower molecular weight exhaust gas products; and the increased hydrogen is desirable for use with a fuel cell and in connection with propulsion of a super-cavitating underwater device. The process is advantageous in that a metal, in powdered form, and a hydrocarbon liquid may be provided together as a slurry or gel for effective metering. The metallic material may also be provided with the organic material in the form of a binder as used in solid propellants, and the organic material and water may be provided together in the form of a water containing liquid monopropellant. The hydrogen containing product gases from the reaction may be further reacted with suitable oxidizers for production of additional energy or steam. The reaction is particularly useful for underwater vehicles where ambient water is available and the reaction products may be used for propulsion.

Gas generating process for propulsion and hydrogen production

The present invention is a lead-free pyrotechnic composition comprising from about 60 percent by weight to about 80 percent by weight iodine pentoxide and from about 15 percent by weight to about 35 percent by weight of a solid-powder fuel. The solid-powder fuel may normally be selected from aluminum, magnesium, or a combination thereof. Depending upon the potential use for the lead-free pyrotechnic composition of the present invention, the composition may also include from about 4 to 10 percent by weight of a stabilizer that neutralizes any iodic acid formed by the iodine pentoxide, from about 3 to 5 percent by weight of a binder, or from about 5 to 15 percent by weight of a coloring agent. In a preferred embodiment of the invention, the aluminum will comprise aluminum flake having a size ranging from about nanometers to about 100 nanometers.

Lead-free pyrotechnic composition

The present invention is a propellant composition comprising from about 2 percent to about 46 percent, by weight, boron particles having a diameter of less than about 500 nanometers. Liquid or gel embodiments of the invention may also include adding the boron particles to a liquid fuel in order to form a liquid fuel system. Examples of such liquid fuels include ethyl ammonium nitrate (EAN), triethyl amine nitrate (TEAN), Cyclotetramethylenetetranitramine (HMX), trinitrotoluene (TNT), jet fuel formula (JP-10), kerosene, RJ-4, or other hydrocarbon based fuels. These liquid fuel systems can be part of bipropellants wherein the liquid fuel system is stored separately from an oxidizing agent and the two are mixed during operation. Examples of oxidizing agents may include nitrogen tetroxide, oxygen, hydrogen peroxide, hydroxyl ammonium perchlorate (HAP), hydoxyl ammonium nitrate (HAN), ammonium perchlorate, ammonium nitrate, ammonium dinitramide (ADN), or a combination of said chemicals. One specific preferred embodiment of the invention comprises a fuel comprising approximately 61.60 percent by weight EAN, approximately 23 percent by weight boron particles having a diameter of less than about 500 nanometers, approximately 3.85 percent by weight ammonium nitrate, and approximately 11.55 percent by weight water coupled with an oxidizing agent comprising approximately 38 percent by weight hydrogen peroxide, approximately 46 percent by weight ammonium nitrate, and approximately 16 percent by weight water. The present invention also comprises a monopropellant formed by adding the nano-sized boron particles to a fuel containing oxygen. Another embodiment of the invention is a solid propellant wherein the nano-sized boron particles are used as a metal fuel component or as a portion of a metal fuel component and are mixed with an oxidizing agent and bound with a binder.

Propellant composition comprising nano-sized boron particles

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Waldorf, MD, United States of America

Douglas J Elstrodt