Oxidizer Compound for Rocket Propulsion

Abstract

A rocket propulsion oxidizer compound that is a mixture that is a homogenous and stable liquid at room temperature that includes nitrous oxide and nitrogen tetroxide.

Description

ORIGIN OF THE INVENTION[0001]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.BACKGROUND OF THE INVENTION[0002]1. Field of the Invention[0003]This invention relates to rocket propellants. More specifically, the invention is an oxidizer compound for use in a rocket propulsion system.[0004]2. Description of the Related Art[0005]The need for high performance propulsion systems for space access and satellites has existed for decades. Small and large propulsion systems are needed for a variety of tasks or systems including rocket boost, orbit insertion and maintenance, attitude control systems (ACS), reaction control systems (RCS), station keeping, orbital maneuvering systems (OMS), and auxiliary power units (APU). However, the drawbacks and consequences associated with s...

AI Technical Summary

Benefits of technology

[0010]Another object of the present invention is to provide a rocket propulsion oxidizer that is not toxic in its exhaust products, and has reduced toxicity in its stored state.

[0011]Still another object of the present invention is to provide a rocket propulsion oxidizer that is easily stored at ambient conditions.

[0012]Yet another object of the present invention is to provide a rocket propulsion oxidizer that provides good performance.

Problems solved by technology

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

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 materials such as fluorine, nitrogen tetroxide (N2O4), inhibited red fuming nitric acid, etc.

If the propellant requires cryogenic storage (e.g., propellants using liquid oxygen, nitrogen fluoride, etc.), other or additional operating complications include the storage of the materials in a way that prevents “boil off” prior to usage.

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.

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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