Gas-generating liquid compositions (OXSOL 3)

BACKGROUND OF THE INVENTION

1. Field of the Invention

The present invention relates to energetic and gas-generating compositions, and in particular to oxidizing compositions.

2. Description of the Related Art

There are numerous applications for gas-generating compositions. Energetic gas-generating compositions are commonly used, for example, in rocket propulsion systems as well as torpedos, safety air bags, etc. Oxygen-generating compositions also have utility in breathable air generators and underwater welding.

Of particular interest among these compositions are those which are liquids, in particular liquids which are oxidizers. Liquids are necessary for many propulsion systems since they can be pumped, and liquids are in general easier to handle and store than solids. The most commonly used liquid oxidizers for rocket propulsion have generally been liquid oxygen (LOX), inhibited red fuming nitric acid (IRFNA), hydrogen peroxide (H

2

O

2

), aqueous hydroxylammonium perchlorate (HAP) and nitrogen tetroxide (NTO). Each of these liquid oxidizers has problems associated with use. For example, LOX requires cryogenic storage and is dangerous when spilled. IRFNA, NTO and H

2

O

2

also have handling and toxicity problems. HAP offers some advantages, but suffers from the presence of hydrochloric acid in the generated gas. Most of the liquid oxidizers in current use present a vapor toxicity or contact hazard, and are hypergolic, that is, spontaneously combusting, in the presence of fuels.

Thus, there are in fact a limited number of available choices of liquid oxidizers. That there is a need to fill the technology “gap” in liquid oxidizers of the contemporary art is seen, for example, in the following articles. In Mul, et al.,

Search For New Storable High Performance Propellants

, (AIAA-88-3354, AIAA/ASME/SAE/ASEE 24

th

Joint Propulsion Conference, Boston, July 1988), the authors discuss the need for storable, non-cryogenic propellants with better performance properties. They discuss nitric acid, NTO and hydrazinium perchlorate as storable oxidizers.

Another problem with the available liquid oxidizers is that they are mostly limited to a single composition, and thus a single set of performance and physical properties. That is, they are not formulated to achieve different values of performance and physical parameters. Thus, variation of performance properties of propellant systems using these oxidizers can only be achieved by varying the composition of the fuel, thus limiting design options.

Anderson, W., et al.,

Low Cost Propulsion Using A High-Density, Storable, and Clean Propellant Combination

, discuss the need for nontoxic, storable, restartable, throttleable and high density impulse systems for rocket motors. They suggest the use of high concentration hydrogen peroxide as a propellant. Although the authors describe hydrogen peroxide as nontoxic, direct human contact with hydrogen peroxide is extremely dangerous.

Rusek, J.,

New Decomposition Catalysts And Characterization Techniques For Rocket-Grade Hydrogen Peroxide, J. of Propulsion and Power

, 1996, 12, 574-579, discusses the use of hydrogen peroxide as a rocket propellant, both as a monopropellant and as an oxidizer with hydrazine hydrate/methyl alcohol fuel.

Gas-generating systems in other applications also have problems associated with them. For example, chlorate-based “chlorate candle” oxygen generators are used for emergency breathable oxygen in some airplanes and in welding applications. Because of the solid nature of the sodium chlorate, many of these devices cannot be turned off once triggered, and the heat production from such a device can prove to be a fire hazard. A liquid-based oxygen generator might overcome this problem. Moreover, chlorate-based devices typically produce some by-product chlorine, which is toxic, in the breathable gas, and do not produce any diluent for the generated oxygen.

Examples of liquid gas-generating and explosive compositions of the contemporary art are seen in the following U.S. Patents. U.S. Pat. No. 3,561,533, to McKinnell, entitled Controlled Chemical Heating Of A Well Using Aqueous Gas-In-Liquid Foams, describes a two-component hypergolic reaction system in which an aqueous foam of hydrazine or dimethylhydrazine and an aqueous foam of hydrogen peroxide are mixed. The system is used to heat oil wells.

U.S. Pat. No. 3,790,415, to Tomic, entitled Chemical Foaming And Sensitizing of Water-Bearing Explosives With Hydrogen Peroxide, describes addition of hydrogen peroxide as a foaming agent/sensitizer to water-bearing explosives having ammonium nitrate and fuel. Here, the hydrogen peroxide is added to the thickened or emulsified explosive mixture, and decomposes in the formulation to provide oxygen bubbles for foaming before the mixture is detonated.

U.S. Pat. No. 4,047,988, to Weill et al., entitled Liquid Monopropellant Compositions, describes a monopropellant which is an aqueous solution of a secondary or tertiary amine, and an oxidizer such as perchloric or nitric acid. Hydrogen peroxide is also mentioned as a possible oxidizer. Here, the amine apparently serves as the fuel in the monopropellant. Properties of the compositions including low freezing temperature, and use as a torpedo propellant, are described.

U.S. Pat. No. 5,607,181, to Richardson et al., entitled Liquid-Fueled Inflator With A Porous Containment Device, describes an automotive airbag inflator using a liquid monopropellant composed of a hydroxylamine nitrate (HAN)/triethanolamine nitrate (TEAN)/water system. A system with hydrazine and hydrogen peroxide as liquid fuel components is also mentioned. HAN is a relatively expensive component, however. Moreover, TEAN serves as a fuel in this mixture, so the mixture probably cannot serve as a general oxidant for other fuels.

In addition to the above patents, U.S. Statutory Invention Registration No. H1,768, to Mueller et al., entitled Oxidizing Agent, describes liquid oxidizers comprising water, hydroxylammonium nitrate, and ammonium nitrate or hydrazine mononitrate. Two oxidizing agents designated OXSOL 1 and OXSOL 2 are described. Discussed applications include use in gas generators for air bags, rocket propellants and torpedo propellants.

A document entitled Advanced Chemical Propulsion Systems discusses the need to replace hydrazine as a fuel, and suggests use of HAN/TEAN in a catalytic thruster. As noted above, HAN is relatively expensive, and HAN/TEAN system probably cannot be used as a general oxidant with other fuels.

An additional examples of a possible utility of a gas-generating system is seen in Berezovsky,

Pyrogen Fire Suppression System-Marine & Vehicle Applications

, dated August 22 1997, which describes a fire extinguishing system (PyroGen) which is pyrotechnic-driven. The system produces an aerosol, and the composition of the system is not disclosed.

Based on my reading of the contemporary art, I have decided that what is needed is a gas-generating liquid composition which can be used as an oxidizer, and which has low cost, low toxicity and excellent handling properties.

SUMMARY OF THE INVENTION

It is therefore an object of the present invention to provide improved gas-generating liquid compositions.

It is also an object of the invention to provide improved liquid oxidizers for use in monopropellant and bipropellant systems.

It is another object of the invention to provide improved liquid compositions for generation of breathable air.

It is yet another object of the invention to provide gas-generating liquid compositions which have low cost.

It is still another object to provide gas-generating liquid compositions from readily available components.

It is a filer object to provide gas-generating liquid compositions which have low vapor and skin toxicity.

It is a yet further object to provide gas-generating liquid compositions which have a low explosion hazard.

It is a yet still further object to provide compositions having excellent handling and storage characteristics, such as low corrosivity.

It is an additional object to provide gas-generating liquid compositions which are easy to prepare.

It is a yet additional object to provide gas-generating liquid compositions allowing ready production of customized formulations.

It is a still additional object of the invention to provide a gas-generating liquid having a low freezing point.

It is yet another object of the invention to provide a gas-generating liquid which has high density and high energy density.

It is yet another object of the invention to provide a gas-generating liquid which is “green”, that is, disposable without damage to the environment.

It is still another object of the invention to provide a gas-generating liquid which allows water-based cleanup of spills.

These objects are achieved in the present invention which provides a family of water-based based gas-generating liquid compositions which may be used in rocket propulsion, torpedo propellants, air bags, and other applications. Applications also include use in oxygen generators and in fuel cells.

The general composition of the water-based gas-generating liquid of the present invention includes: a first compound which may be hydrazinium mononitrate or methylhydrazinium mononitrate; ammonium nitrate (AN); and water. Generally, the water concentration (that is, content) in the gas-generating liquid will be in the range of approximately 15 to 50 percent by weight (w/w-%), and the water concentration may be in the range of 20 to 35 w/w-%. Generally, the ammonium nitrate concentration will be in the range of approximately 10 to 60 w/w-%, and may be in the range of approximately 20 to 40 w/w-%. When the first compound is hydrazinium mononitrate (HN), the concentration of hydrazinium mononitrate will generally be in the range of approximately 10 to 60 w/w-% and may be in the range of approximately 20 to 40 w/w-%. When the first compound is methylhydrazinium mononitrate, the concentration of methylhydrazinium mononitrate will generally be in the range of approximately 10 to 40 w/w-% and may be in the range of approximately 10 to 25 w/w-%. The gas-generating liquid composition of the present invention may have additional components, such as a colorant, an odorant, a gelant, a thixotropic agent, a surfactant, or a burning rate modifier.

In one embodiment, the gas-generating liquid compositions of the present invention may be added to a fuel to form a monopropellant. In another embodiment of the present invention, the gas-generating liquid composition may consist essentially of the first compound which may be hydrazinium mononitrate or methylhydrazinium mononitrate; ammonium nitrate; and water. Here, “consists essentially of' means that this composition has no added fuel, nor other component substantially affecting the energy content, freezing point, or density of the composition. Such a composition may have minor additional components, such as a colorant, a gelant, an odorant, a thixotropic agent, a surfactant, or a burning rate modifier, which do not substantially affect these parameters.

In addition to the compositions of the present invention, the invention also includes methods of use of the compositions. Specifically, the compositions of the present invention can be used for generating gas by passing the compositions through a solid catalyst bed, heating the compositions, or adding catalyst to the compositions. The compositions can also be mixed with a fuel to form monopropellants or can be used in bipropellant and hybrid rocket systems.

BRIEF DESCRIPTION OF THE DRAWINGS

A more complete appreciation of the invention, and many of the attendant advantages, thereof, will be readily apparent as the same becomes better understood by reference to the following detailed description when considered in conjunction with the accompanying drawings in which like reference symbols indicate the same or similar components, wherein:

FIG. 1

is a response surface diagram illustrating freezing points of compositions of the present invention; and

FIG. 2

is a response surface diagram illustrating densities of compositions of the present invention.

DETAILED DESCRIPTION OF THE INVENTION

The gas-generating liquid compositions of the present invention are a family of compositions which the inventor refers to as OXSOL 3. The general composition of the water-based gas-generating liquid of the present invention includes: a first compound which may be hydrazinium mononitrate or methylhydrazinium mononitrate; ammonium nitrate; and water. The invention may also comprise any of a number of additives, and may comprise a fuel.

The present invention includes a family of compositions with varying amounts of the first compound, ammonium nitrate and water. Preparation of the compositions of the present invention can generally be achieved simply by mixing the ingredients of the invention. Generally, the water concentration (that is, content) in the gas-generating liquid will be in the range of approximately 15 to 50 percent by weight (w/w-%), and the water concentration may be in the range of 20 to 35 w/w-%. Generally, the ammonium nitrate concentration will be in the range of approximately 10 to 60 w/w-%, and may be in the range of approximately 20 to 40 w/w-%. When the first compound is hydrazinium mononitrate, the concentration of hydrazinium mononitrale will generally be in the range of approximately 10 to 60 w/w-% and may be in the range of approximately 20 to 40 w/w-%. When the first compound is methylhydrazinium mononitrate, the concentration of methylhydrazinium mononitrate will generally be in the range of approximately 10 to 40 w/w-% and may be in the range of approximately I0 to 25 w/w-%. Different compositions will have different values of parameters relevant to the use of the invention, and thus customized compositions of the present invention may be prepared.

Among the advantages of the present invention are the low freezing point achievable in some compositions. An important parameter of liquid gas-generating compositions is the freezing point. At temperatures below the freezing point, solids appear in the liquid, affecting many aspects of handling the liquid, for example, the ability to pump the liquid. In the present patent application, the term “freezing point” is taken to be the temperature below which any precipitation occurs in a gas-generating liquid composition. If, repeatedly, cooling the liquid below the freezing point leads to precipitation and heating to a temperature above the freezing point allows redissolution, then the freezing point can be considered to be reasonably well defined. Generally, it is desirable that a gas-generating liquid composition be selected to have a freezing point below the ambient temperature at which the composition will be used and stored.

In order to determine the freezing point of a composition of the present invention, the following method is used. This method may be easily performed by one skilled in the art. A sample of the liquid composition of interest is placed in a 16-mm test tube along with the bulb of a glass thermometer of appropriate temperature range. Generally, enough liquid to give a height of ¾″ is used. The bottom portion of the test tube is then placed in a dry ice-ethanol bath in a Dewar flask. The sample is cooled until crystals appear visually in the liquid sample. The test tube is then removed from the bath and is warmed as necessary with stirring by the thermometer, until the crystals redissolve, noting the temperature at which redissolution occurs. The test tube is then cooled again in the bath to the noted temperature. While stirring, the test tube is cooled until crystals appear, and then removed to allow warming and dissolution. This is performed repeatedly until the temperature where a slight cooling causes crystal formation and slight warming allows dissolution is found, and this temperature is recorded as the freezing point.

Another advantage of the present invention is the high density achievable in some of the inventive compositions. Density is an important contribution to the energy content of a given composition, as more mass per unit volume allows more chemical energy per unit volume. Greater density thus allows for a smaller storage volume and correspondingly smaller storage tanks on the propelled vehicle resulting in reduced weight. Likewise, greater density also allows for a greater amount of gas generated per unit volume of liquid. In the present invention, density is presented as specific gravity, that is, a unitless value relative to the density of water at 4° C. Here, densities of the liquid compositions are measured at room temperature, about 20° C., using a commercial hydrometer, by method well known in the art.

In Table I, freezing-point data and density data for selected compositions of ammonium nitrate, hydrazinium mononitrate and water. The table includes some data for compositions with ammonium nitrate for comparison to compositions of the present invention.

TABLE I

Observed Freezing Point (° C.) and Density (g/cc)

Data For Some Compositions of Ammonium Nitrate,

Hydrazinium Mononitrate and Water

Ammonium

Hydrazinium

Freezing

Nitrate

Mononitrate

Water

Point

Density

.000

.733

.267

19

1.397

.000

.724

.277

19

1.390

.016

.721

.262

20

1.396

.032

.710

.258

20.5

1.397

.048

.698

.254

20.5

1.397

.063

.688

.250

20.5

1.398

.077

.677

.246

20.5

1.4005

.091

.667

.242

20

1.4014

.104

.648

.248

20

1.402

.118

.647

.235

19

1.403

.130

.638

.232

19.5

1.405

.143

.629

.229

19.5

1.407

.167

.611

.222

19

1.410

.191

.593

.216

19

1.414

.211

.579

.210

18

1.416

.231

.557

.213

18

1.418

.250

.550

.200

17

1.422

.272

.534

.194

17

1.424

.236

.524

.190

16

1.426

.310

.506

.184

16

1.429

.333

.489

.178

14

1.432

.362

.468

.170

14

1.436

.388

.443

.169

16

1.439

.412

.431

.157

19

1.441

.434

.415

.151

24

1.442

.414

.396

.139

13

1.420

.397

.379

.224

7

1.400

.330

.364

.256

−2

1.381

.365

.349

.286

−5

1.364

.351

.336

.313

−5

1.3475

.338

.323

.338

−7

1.3325

.000

.611

.389

8

1.319

.063

.573

.365

7

1.326

.118

.539

.343

7

1.3375

.167

.509

.324

6

1.3475

.211

.483

.307

5

1.355

.250

.458

.292

4

1.363

.291

.433

.307

3

1.370

.318

.417

.292

2

1.373

.348

.399

.254

1

1.378

.375

.382

.243

2

1.384

.400

.367

.233

5

1.388

.423

.353

.224

9

1.394

.444

.340

.216

14

1.396

.464

.327

.208

18

1.398

.000

.408

.592

−6

1.205

.091

.371

.538

−8

1.228

.167

.340

.494

−12

1.249

.231

.314

.456

−16

1.269

.236

.291

.423

−13

1.281

.333

.272

.395

−13

1.297

.378

.254

.368

−13

1.3115

.412

.240

.348

−7

1.321

.444

.227

.329

−2

1.3315

.474

.215

.312

5

1.3415

.500

.204

.296

10

1.348

.476

.194

.330

4

1.330

.455

.185

.360

−2

1.313

.435

.177

.388

−7

1.297

.417

.170

.413

−10

1.283

.000

.650

.350

11

1.340

.000

.500

.500

0

1.255

.000

.400

.600

−7

1.18

.000

.247

.753

−7

1.12

The freezing point data of Table I were statistically analyzed and fitted to a quadratic model, using the commercially available computer program STATGRAPHICS. Statistical analysis and response surface modeling of this sort is well known in the art. A ternary composition response surface diagram of freezing points the compositions of the present invention is presented as FIG.

1

. It is evident from the data presented that the freezing points of compositions of the present invention are not readily predictable from only a few data of widely spaced points on the ternary response diagram. The freezing point properties of these compositions could not have been predicted without experimentation using current methods of the art. However, by obtaining sufficient data on a variety of compositions, one skilled in the art should be able to identify compositions of the present invention having freezing points below +5° C. or alternatively below −15° C., as desired. For example, a freezing point of +5° C. might suitable for space flight applications, but a freezing point of −15° C. might be desirable for military applications in harsh environments.

The density data of Table I were likewise analyzed and fitted to a special cubic model. A ternary composition response surface diagram of densities the compositions of the present invention is presented as FIG.

2

. By suitable experimentation, one skilled in the art should be able to identify compositions of the present invention with densities above 1.3, or alternatively above 1.4. The density of an energetic composition is an important parameter in the performance of the composition in propellants, with greater density generally allowing greater energy content per unit volume.

Another advantage of the present invention is the customizability of the formulation. In particular, by adjusting the water content of the final formulation, the combustion temperature can be adjusted to give a desired flame temperature or to achieve specific physical/chemical/safety properties. For example, this can reduce the vulnerability characteristics and the corrosivity/erosion problems associated with the exhaust gases.

Another advantage of the present invention is cost. Ammonium nitrate, in particular, is very inexpensive.

In addition to the hydrazinium mononitrate or methylhydrazinium mononitrate; ammonium nitrate; and water, compositions of the present invention may also contain additives to modify other properties of the gas-generating liquids. These additives usually total less than 1 percent by weight of the composition. For example, the composition may contain a colorant. This is a dye which allows the gas-generating liquid to be more easily seen. This is particularly useful, for example, in locating spills.

Another additive which may be used is an odorant. This is a compound with an odor readily detected by the human nose, and is generally used for detecting and locating spills.

Another additive which may be used is a stabilizer. This will usually be an oxygen scavenger, such as ammonium thiosulfate, which serves to slow chemical degradation of the gas-generating generating liquid.

Another additive which may be used is a chelating agent, such as ethylenediamine tetraacetic acid (EDTA) or cyclohexanediaminetetraacetic acid (CDTA) or sodium salts of these compounds. Chelating agents serve to bind impurity metal ions in the liquid, and can serve to slow degradation of the gas-generating liquid.

Another additive which may be used is a gelant, or gelling agent. Having the gas-generating generating liquid in gel form may be useful in certain applications.

Another additive which may be used is a thixotropic agent. Such an agent can improve the general handling properties of the liquid, such as pumping or pouring.

Another additive which may be used is a burning rate modifier. Such an additive affects the kinetics, or rate of burn of compositions.

Another additive which may be used is a surfactant. Surfactants can serve to allow miscibility of the gas-generating liquid with certain fuels. Also, a surfactant can serve to modify the droplet size of the gas-generating liquid when it is sprayed, for example into a rocket combustion chamber.

The compositions of the present invention may be used as liquid oxidizes for a variety of propellant systems. In general, propellant systems are monopropellant or bipropellant systems.

In theory, a liquid monopropellant is the ideal energy source for various liquid gas generator applications such as gun propellants, air bag inflators, torpedo propulsion and rocket motors. The monopropellant's main advantage is simplicity when compared to liquid bipropellant systems: a monopropellant requires only half the number of pumps, valves, storage tanks and pipes. An example of a monopropellant is the nitrate ester-based Otto fuel used in torpedoes.

When used as a monopropellant, a composition of the present invention would generally be preblended with a fuel. Such a fuel could be a water-soluble fuel, in which case the fuel would generally dissolve in the liquid oxidizer. Non-water soluble fuels, such as hydrocarbons, may also be used. Monopropellants using hydrocarbons and the liquid oxidizers of the present invention would generally be emulsified mixtures. In some cases, surfactants may be added to allow for better emulsification. Among the fuels that may be used with the invention are alkylammonium nitrates and alkanolammonium nitrates having one, two or three carbon atoms.

Monopropellants made using the liquid oxidizer of the present invention may be used for other purposes. If the oxidizer containing hydrazinium nitrate, ammonium nitrate and water is mixed in appropriate ratio with a fuel, for example urea, an alkylammonium nitrate or hydrocarbon, the decomposition reaction can in theory yield nitrogen, carbon dioxide, carbon monoxide and water. Such a decomposition mixture would not support combustion, and might be usable in air-bag inflation, fire suppressant or related uses.

In practice, most liquid propellant systems use bipropellants. One problem with some liquid monopropellants is the low energy content of the monopropellant, in order to meet physical, chemical and safety requirements. If the oxidizer and fuel are separated, the sensitivity to shock, friction and static discharge are reduced. The homogeneous mixture of the two components of a liquid propellant has a sensitivity which is greater than that of either component.

Bipropellant systems are commonly used in rocket motors. In a bipropellant system, the liquid oxidizer contacts the fuel at the time of combustion. Rocket motors may use liquid fuel, or in the case of hybrid rocket motors, the fuel may be solid. The compositions of the present invention may be usable as liquid oxidizers for both kinds of rocket motors. Metallic additives may be added to these fuels to improve the propellants' energy outputs.

In general, catalytic or thermal combustion of an oxidizer composition of the present invention with a low-carbon content fuel should generate an exhaust gas containing N

2

, H

2

O, and some CO

2

. If no fuel is present, they will generate N

2

, H

2

O and O

2

. Catalytic or thermal combustion of an oxidizer composition of the present invention should generate an exhaust gas containing N

2

, H

2

O, CO

2

, CO, CH

4

and other gases. However, no HCN is expected in the exhaust gas, unlike exhaust gases resulting from nitrate ester fuels.

In Table II, below, are tabulated theoretical performance data for bipropellant systems with an oxidizer composition of the present invention, mixed with JP-10 fuel in the indicated oxidizer to fuel ratio. Three compositions of the present invention are listed in the first three rows of data. Also included in this table for comparison are data for an oxidizer composition of HN and H

2

O and for a composition of AN and H

2

O, with JP-10 fuel. In the case of the HN/H

2

O and AN/H

2

O oxidizers, no performance data are given because these formulations contain too much water to sustain combustion at 5000 psi chamber pressure. Based on these data, it should be possible to obtain a formulation of the present invention with a 12% greater energy density than Otto Fuel 2.

TABLE II

Theoretical Performance Data for Selected Bi-Propellant Hydrazinium

mononitrate-Ammonium Nitrate-Water (“OXSOL 3”)/JP-10 Systems

Oxidizer Formulation

Oxidizer

Chamber

%

%

%

To

Temp.

Impulse

AN

HN

H

2

O

Fuel Ratio

Tc, F.

Isp

Rho Isp

C*

25.0

55.0

20.0

34.2

2283

203

289

3845

41.2

43.1

32.7

27.7

2184

197

284

3743

46.4

32.7

20.8

27.4

1717

178

249

3397

0

72

28

54.2

66

0

34

25.0

The compositions of the present invention may also be decomposed to yield gases and energy. This decomposition may be achieved by catalysis. For example, placing the composition of the present invention in contact with a fixed bed catalyst, such as Pt, Pd, or MnO

2

, may yield decomposition. Such a reaction is well known in the art for other liquids, for example, hydrogen peroxide decomposing to water and oxygen. Alternatively, the composition of the present invention might by decomposed by adding a catalyst to the composition to dissolve or suspend the catalyst. This may be done in a catalyst stream flow process. For example, the composition of the present invention and a catalyst could be delivered from a bladder and mixed upon delivery, by methods known in the art.

Alternatively, decomposition of a composition of the present invention may be achievable by heating the composition. If, for example, the composition is injected into a hot reaction chamber, the heat of decomposition may be sufficient to self-sustain the decomposition reaction, and a continuous decomposition of a stream of the composition may be possible.

One possible application of decomposition of compositions of the present invention is in breathable air generators. Ammonium nitrate and hydrazinium nitrate may be theoretically decomposed to oxygen, nitrogen and water according to the following stoichiometries:

NH

4

NO

3

→0.5 O

2

+N

2

+2 H

2

O (1)

N

2

H

5

NO

3

→0.25 O

2

+1.5 N

2

+2.5 H

2

O (2)

Therefore, compositions of the present invention containing ammonium nitrate, hydrazinium nitrate and water can theoretically be decomposed into oxygen, nitrogen and water. Such a decomposition could be used to create a gas mixture which could be used for breathable air. Unlike chlorate-based systerns, the present invention would provide a mixture of oxygen and nitrogen, which may be better for use as breathable air at atmospheric pressure than pure oxygen. Moreover, the present invention would yield no chlorine, which is a byproduct of chlorate candle systems.

In Table III, below, theoretical performance data of the oxidizer compositions of Table II as oxygen generators are tabulated. As can be seen, the three compositions of the present invention in the first three data rows are expected to effectively burn to give water, nitrogen and oxygen. However, in the case of the HN/H

2

O and AN/H

2

O oxidizers of the fourth and fifth rows, no performance data are given because these formulations contain too much water to sustain combustion at 5000 psi chamber pressure. Additionally, in the case of the three compositions of the present invention, in the first three rows of data, it is calculated that the thermal stability as given by differential scanning calorimetry should be greater than 200° C.

TABLE III

Oxygen Gas Generator Theoretical Performance Data for Selected Hydrazinium

mononitrate-Ammonium nitrate-Water (“OXSOL 3”) Compositions

Oxidizer

Exhaust Gas

Formulation

Chamber

Composition,

%

%

%

Temp.

Impulse

Rho

moles/100 g

Freezing

Density

AN

HN

H

2

O

Tc, F.

Isp

Isp

C*

H

2

O

N

2

O

2

NO

x

Point, ° C.

g/cc

25.0

55.0

20.0

2283

203

289

3845

3.18

1.18

0.30

0

17

1.422

41.2

43.1

32.7

2184

197

284

3743

3.03

1.19

0.37

0

19

1.441

46.4

32.7

20.8

1717

178

249

3397

3.18

1.10

0.38

0

18

1.398

0

72

28

20

1.39

66

0

34

20

1.314

In addition to the described functional properties, the compositions of the present invention also have excellent handling and safety characteristics. Because they are non-cryogenic, the problems associated with cryogenic materials are avoided. Corrosivity is also expected to be relatively low, simplifying storage and handling. Due to the water content and the use of protonated salts, the vapor pressure of toxic chemicals is extremely low in the compositions, and skin toxicity is also expected to be relatively low.

The preparation of the compositions from the constituent ingredients is relatively simple and safe, as the dissolution of the ingredients is generally an endothermic process. And, due to the water solubility of the components, water can be used in the cleanup of spills. The compositions of the invention should be readily chemically degradable or biodegradable, simplifying disposal of the compositions. The compositions of the present invention may be considered to be “green”, that is, not a hazard to the environment.

As will be evident to those skilled in the art, various combinations and modifications can be made in light of the foregoing disclosure without departing from the spirit or scope of the disclosure. It is therefore to be understood that within the scope of the appended claims the invention may be practiced otherwise than as specifically described.

Number	Name	Date
3419444	Maes	Dec 1968
3658609	Lum et al.	Apr 1972
3768410	Maes et al.	Oct 1973
3861138	Bridgeforth, Jr. et al.	Jan 1975
3888159	Elmore et al.	Jun 1975
3916792	Elmore et al.	Nov 1975
3923565	Sakai et al.	Dec 1975
4042431	Friant et al.	Aug 1977
4090895	Outten	May 1978
4161104	Ladacki	Jul 1979
4620415	Schmidt	Nov 1986
5734124	Bruenner et al.	Mar 1998
5837931	Bruenner	Nov 1998
5847315	Katzakian, Jr. et al.	Dec 1998
6001197	Wagaman	Dec 1999

	Number	Date	Country
Parent	09/447274	Nov 1999	US
Child	09/664703		US

Gas-generating liquid compositions (OXSOL 3)

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