Oxidizer Compound for Rocket Propulsion

a rocket propulsion and compound technology, applied in the field of rocket propulsion systems, can solve the problems of difficult to meet the objectives, difficult to improve the technology, and the system utilizing current propellants is still daunting, and achieves the effects of reducing toxicity in the stored state, easy storage at ambient conditions, and good performan

Inactive Publication Date: 2012-06-14
SACKHEIM ROBERT L
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  • Abstract
  • Description
  • Claims
  • Application Information

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 i

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

Method used

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  • Oxidizer Compound for Rocket Propulsion
  • Oxidizer Compound for Rocket Propulsion

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Embodiment Construction

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[0018]The novel oxidizer compound of the present invention can be used in a variety of rocket propulsion systems to include, for example, those used in launch vehicle propulsion systems, multi-mode spacecraft propulsion systems, upper stage spacecraft propulsion systems, and missile propulsion systems. Furthermore, the oxidizer compound of the present invention can be matched with a variety of propellant fuels in these propulsion systems. Accordingly, it is to be understood that the type of propulsion system and / or propellant fuel used therein are not limitations of the present invention.

[0019]In general, the oxidizer compound of the present invention is a mixture of nitrous oxide and nitrogen tetroxide that is homogenous and a stable liquid (i.e., will not boil off) at room temperature. As used herein, the term “room temperature” is defined as temperatures that are generally close to approximately 20° C. or 72° F. as would be well understood in the art.

[0020]The new oxidizer compo...

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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...

Claims

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Application Information

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IPC IPC(8): F02K9/00C06B47/00
CPCF02K9/425C06B47/04C06B33/08C06B43/00F02C7/22
Inventor SACKHEIM, ROBERT L.HERDY, JR., JOSEPH R.
Owner SACKHEIM ROBERT L
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