Oxidizer compound for rocket propulsion

Abstract

The present disclosure generally pertains to a rocket propulsion oxidizer compound that is a solution, is a homogenous and stable liquid at room temperature and includes nitrous oxide and nitrogen tetroxide. In addition, an apparatus is provided for burning a fuel and nitrous oxide / nitrogen tetroxide. The apparatus has a combustor, a catalyst, a nitrous oxide / nitrogen tetroxide supply passage for directing the nitrous oxide / nitrogen tetroxide to a contact position with the catalyst, and a fuel supply passage for supplying the fuel to the combustor. The catalyst acts to facilitate decomposition of the nitrous oxide / nitrogen tetroxide, while the combustor burns the fuel, the decomposed nitrous oxide / nitrogen tetroxide and / or nitrous oxide / nitrogen tetroxide decomposed in the reaction.

Description

CROSS REFERENCE TO RELATED APPLICATION[0001]This application is a continuation-in-part of U.S. patent application Ser. No. 11,619,674, entitled “Oxidizer Compound for Rocket Propulsion,” and filed Jan. 4, 2007, which is incorporated herein by reference. This application is related to U.S. Pat. No. 6,779,335, entitled “Burning Nitrous Oxide and a Fuel,” and filed Dec. 7, 2001, which is incorporated herein by reference.GOVERNMENT INTEREST[0002]The invention described herein was made in part by an employee of the United States Government and may be manufactured and used by or for the Government of the United States of America for governmental purposes without the payment of any royalties thereon or therefore.FIELD OF THE INVENTION[0003]This invention relates to rocket propellants. More specifically, the invention is an approach to catalyze an oxidizer solution to combust with a fuel, catalyze a fuel to combust with an oxidizer solution, or combine catalyzed oxidizer and fuel solutions ...

AI Technical Summary

Benefits of technology

[0011]Still another object of the present invention is to provide the use of a catalyst bed to heat the fuel to temperatures such that it promotes spontaneous ignition with the oxidizer.

Problems solved by technology

The drawbacks and consequences associated with systems utilizing current propellants are daunting, while research and development efforts over the years have not greatly improved the technology during this period.

Present systems are either liquid propellants that use hypergolic or cryogenic oxidizers, or solid propellants that are single use only, cannot be throttled, and can be highly toxic and / or can detonate.

The current challenge is to attain the high energy and density goals for these propulsion systems while maintaining acceptable physical properties for the propellants.

While the problem is well understood, practical solutions which meet the objectives have been elusive and research has not been very fruitful to date.

For example, high operating costs result from occupational safety requirements associated with the handling of toxic, hypergolic propellants using inherently dangerous oxidizing materials such as fluorine, pure nitrogen tetroxide (N2O4), inhibited red fuming nitric acid, etc.

While less toxic and easily stored propellant oxidizers are known (e.g., nitrous oxide (N2O)), their energy (i.e., heat of formation or ΔHf) is generally too low to provide the required performance.

While less toxic and easily stored propellant fuels are known (e.g. RP-1, a derivative of kerosene, or propane (C3H8)), they lack the capability to be hypergolic when combined with the oxidizer, thus requiring a more complex system and requiring an external ignition source.

Other drawbacks and limitations of current technologies include the added weight and complexity of pressurants and feed systems for the propellants, state change of the propellants during prolonged storage, and the general problems of hot gas impingement and contamination to cold receiving surfaces from undesirable exhaust gas constituents.

Unfortunately, current solutions available to address the storage and handling issues severely impact performance.

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