US3706608A - Combustion tailoring of solid propellants by oxidizer encasement - Google Patents
Combustion tailoring of solid propellants by oxidizer encasement Download PDFInfo
- Publication number
- US3706608A US3706608A US24894A US3706608DA US3706608A US 3706608 A US3706608 A US 3706608A US 24894 A US24894 A US 24894A US 3706608D A US3706608D A US 3706608DA US 3706608 A US3706608 A US 3706608A
- Authority
- US
- United States
- Prior art keywords
- oxidizer
- fuel particles
- combustion
- binder
- particles
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
Links
Images
Classifications
-
- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B21/00—Apparatus or methods for working-up explosives, e.g. forming, cutting, drying
- C06B21/0083—Treatment of solid structures, e.g. for coating or impregnating with a modifier
-
- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B33/00—Compositions containing particulate metal, alloy, boron, silicon, selenium or tellurium with at least one oxygen supplying material which is either a metal oxide or a salt, organic or inorganic, capable of yielding a metal oxide
- C06B33/12—Compositions containing particulate metal, alloy, boron, silicon, selenium or tellurium with at least one oxygen supplying material which is either a metal oxide or a salt, organic or inorganic, capable of yielding a metal oxide the material being two or more oxygen-yielding compounds
- C06B33/14—Compositions containing particulate metal, alloy, boron, silicon, selenium or tellurium with at least one oxygen supplying material which is either a metal oxide or a salt, organic or inorganic, capable of yielding a metal oxide the material being two or more oxygen-yielding compounds at least one being an inorganic nitrogen-oxygen salt
-
- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B45/00—Compositions or products which are defined by structure or arrangement of component of product
- C06B45/04—Compositions or products which are defined by structure or arrangement of component of product comprising solid particles dispersed in solid solution or matrix not used for explosives where the matrix consists essentially of nitrated carbohydrates or a low molecular organic explosive
- C06B45/06—Compositions or products which are defined by structure or arrangement of component of product comprising solid particles dispersed in solid solution or matrix not used for explosives where the matrix consists essentially of nitrated carbohydrates or a low molecular organic explosive the solid solution or matrix containing an organic component
- C06B45/10—Compositions or products which are defined by structure or arrangement of component of product comprising solid particles dispersed in solid solution or matrix not used for explosives where the matrix consists essentially of nitrated carbohydrates or a low molecular organic explosive the solid solution or matrix containing an organic component the organic component containing a resin
-
- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B45/00—Compositions or products which are defined by structure or arrangement of component of product
- C06B45/18—Compositions or products which are defined by structure or arrangement of component of product comprising a coated component
-
- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B45/00—Compositions or products which are defined by structure or arrangement of component of product
- C06B45/18—Compositions or products which are defined by structure or arrangement of component of product comprising a coated component
- C06B45/30—Compositions or products which are defined by structure or arrangement of component of product comprising a coated component the component base containing an inorganic explosive or an inorganic thermic component
Definitions
- oxidizer and fuel particles have been mixed into and contained by the binder matrix as discrete entities. Studies have shown that this results in propellant grains made up of relatively large oxidizer particles surrounded by pockets of smaller fuel particles within the binder matrix. Upon combustion, pockets of fuel particles exposed at the burning surface become rapidly heated, melt together, and exude as molten droplets onto the surface of the propellant. The molten droplets then roll around on the surface until several of them came together and form an agglomerate. Agglomerates thus formed are generally to 100 times larger than the original fuel particles found in the pockets of unburned propellant grains. After formation, the agglomerates are transported into the combustion chamber by high velocity gaseous decomposition products formed by reaction between oxidizer and binder.
- the fuel particles act as reducing agents and become oxidized as a result of reaction with oxidizer particles.
- the agglomerate formation process has been found to hamper the efficiency of the oxidation-reduction process. Further, the melting action prior to the formation of agglomerates leaves pits in the burning surface of the propellant grain which interfere with the smooth, layer-by-layer combustion necessary to obtain the highest combustion efficiency.
- FIG. 1 shows a cross section of a typical prior art propellant grain during combustion
- FIG. 2 shows a cross section of a propellant grain contemplated by the present invention during combustion.
- FIG. 1 of the drawing is a cross section of a typical prior art propellant grain during the process of combustion.
- 0 idizer particles 1 and fuel particles 2 are shown as discrete particles within a binder matrix 3.
- pockets of discrete fuel particles melt together to form larger single particles 4.
- varying numbers of larger, melted together particles 4 roll around on the grain surface and form into agglomerates 5.
- High velocity gases created by reaction between the oxidizer and the binder carry the agglomerates away from the surface of the propellant grain into the combustion chamber proper where they are oxidized and blown out through the rocket nozzle.
- the agglomeration process lowers the efficiency of oxidation by lowering the surface area of fuel material exposed to the heat of the combustion chamber and in contact with oxidizer.
- smooth layer-by-layer burning of the propellant is hampered when pockets of discrete fuel particles 2 melt together to form the larger single particles 4 leaving pits in the propellant grain surface.
- FIG. 2 shows a propellant grain of this invention wherein, prior to being incorporated into the binder 3, the fuel particles 1 have been provided with a coat of oxidizer 2 by crystallizing oxidizer material on them. Coating of the fuel particles with ox idizer increases the efficiency of combustion of the fuel particles by insuring that the oxidation-reduction reaction between oxidizer and fuel takes place while the fuel particle is in its small, original size. For a given weight of fuel particles in a propellant grain, a greater amount of surface area is exposed for purposes of reaction by keeping the fuel particles discrete from one another with oxidizer coats than is accomplished by the prior art method described above.
- coating fuel particles with oxidizer prevents the formation of pockets caused by the melting together of pockets of particles prior to agglomerate formation.
- Efficiency gains of from 2 to 10 percent may be obtained by coating the fuel particles as shown by FIG. 2 because the fuel is oxidized prior to its entry into the combustion chamber proper rather than being allowed to agglomerate.
- Burn rate catalysts may also be coated with oxidizer to assist in the tailoring of combustion.
- Either burn rate accelerators such as iron oxide, iron blue, and copper chromate or burn rate decelerators such as oxamides, barbiturates, and guanadine derivatives may be coated with oxidizer and utilized to tailor the combustion rate as desired. Since coating places the accelerators or decelerators, whichever the case may be, in more intimate contact with the oxidizer, their action is made more effective at a given concentration level.
- Examples of fuel particles and oxidizers which may be utilized in conjunction with one another according to this invention include such fuels as aluminum, beryllium, magnesium, and boron particles and such oxidizers as ammonium perchlorate, ammonium nitrate, cyclotetramethylenetetranitramine (I-IMX), cyclotrimethylenetrinitramine (RDX), and metal perchlorates such as alkali metal perchlorates.
- oxidizers as ammonium perchlorate, ammonium nitrate, cyclotetramethylenetetranitramine (I-IMX), cyclotrimethylenetrinitramine (RDX), and metal perchlorates such as alkali metal perchlorates.
- EXAMPLE 1 Aluminum powder is placed in a saturated solution of ammonium perchlorate in water. The ammonium perchlorate is then shocked out of solution by rapidly lowering the temperature until a precipitate appears. The precipitate is a plurality of aluminum particle nuclei coated with ammonium perchlorate.
- EXAMPLE ll EXAMPLE Ill Ammonium perchlorate coated fuel particles are obtained bydripping a nonsolvent, ethyl ether, into saturated solutions of ammonium perchlorate in the solvents of Examples I and II containing suspended fuel particles. The coated particles are then centrifuged and the liquid decanted.
- EXAMPLE V Surface treatment of aluminum powder may be used to enhance the process of Example I.
- aluminum powder is treated with perchloric acid to form a thin surface layer of the perchlorate derivative on aluminum.
- the resulting coated aluminum is then substituted for the nontreated aluminum powder of Example I and the method of Example I used to coat the treated aluminum.
- Separation of oxidizer coated fuel particles from the saturated solutions of oxidizer may be accomplished either by centrifugal or sedimentation methods taking advantage of differences in specific gravity.
- the coated particles may be incorporated into abinder by standard propellant processing techniques.
- the binder, coated particles (either fuel, catalyst, or both), and any other additives may be charged into a standard horizontal or vertical propellant mixer and mixed at temperatures of from about F to about F.
- the propellant is cast into molds or rocket motor cases with suitable mandrels and cured.
- Typical compositions which may be prepared are:
- the propellant may be plasticized with liquid hydrocarbon to improve processibility and mechanical properties. Either all or only part of the fuel may be oxidizer coated. Curatives may be added to the binder to achieve an infinite polymer network as is usual in the art.
- binder is selected from the group consisting of carboxy terminated polybutadiene, hydroxy terminated polybutadiene, a copolymer of butadiene and acrylic acid, a copolymer of butadiene and acrylonitrile, and a terpolymer of butadiene with acrylic acid and acrylonitrile.
Landscapes
- Chemical & Material Sciences (AREA)
- Organic Chemistry (AREA)
- Crystallography & Structural Chemistry (AREA)
- Inorganic Chemistry (AREA)
- Health & Medical Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Dispersion Chemistry (AREA)
- Molecular Biology (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Solid Fuels And Fuel-Associated Substances (AREA)
Abstract
Solid rocket fuel particles such as aluminum, beryllium, magnesium, or boron are encased in an oxidizer by crystallizing the oxidizer onto the fuel particles. Encasement of the fuel particles before binding with a binder matrix enhances the combustion efficiency of the propellant.
Description
United States Patent 1 1 3,706,608
Geisler 1 1 Dec. 19, 1972 [S4] COMBUSTION TAILORING OF SOLID [56] References Cited PROPELLANTS BY OXIDIZER ENCASEMENT UNITED STATES PATENTS [72] Inventor: Robert L. Geisler Lancaster Calif 2,982,640 5/196] Blake ..l49/8 3,l20,459 2/1964 Coates et al ..l49/5 [73] Assignee: The United States of America as i represented by the secretary of the Primary ExamznerCarl D. Quarforth Fol-ce Assistant ExaminerStephen J. Lechert, .lr.
AttorneyHarry A. Herbert, Jr. and Cedric H. Kuhn [22] Filed: March 24, 1970 21] Appl. No.: 24,894 [571' ABSTRACT Solid rocket fuel particles such as aluminum, berylli- 1521 vs. c1. ..l49/6, 149/5, 149/19, magnesium are encased in Miler 149/20, 149/22, 149/42, 149/43, 149/44 by crystallizing the oxidizer onto the fuel particles. En- 49/ 0 149/ 1 149/7 149/35 2 4 3 C casement of the fuel particles before binding with a 1511 Int. Cl. ..C06b 19/02 binder matrix enhances the Combustion efficiency of Field of Search ..149/5, 8, 6, 19, 20, 22, 42, the p p 3 Claims, 2 Drawing Figures COMBUSTION TAILORING OF SOLID PROPELLANTS BY OXIDIZER ENCASEMENT BACKGROUND OF THE INVENTION 1. Field of the Invention This invention is in the field of solid rocket propellants.
2. Description of the Prior Art The mixing and casting of solid oxidizer particles and solid fuel particles in hydrocarbon binders to form a 1 solid propellant grain is well known. It is also well known that, in order to burn efficiently, a solid propellant grain should combust in a smooth, layer-by-layer manner with combustion beginning at the surface of an opening running through its center and proceeding smoothly outwardly toward the case of the rocket motor.
In the prior art, oxidizer and fuel particles have been mixed into and contained by the binder matrix as discrete entities. Studies have shown that this results in propellant grains made up of relatively large oxidizer particles surrounded by pockets of smaller fuel particles within the binder matrix. Upon combustion, pockets of fuel particles exposed at the burning surface become rapidly heated, melt together, and exude as molten droplets onto the surface of the propellant. The molten droplets then roll around on the surface until several of them came together and form an agglomerate. Agglomerates thus formed are generally to 100 times larger than the original fuel particles found in the pockets of unburned propellant grains. After formation, the agglomerates are transported into the combustion chamber by high velocity gaseous decomposition products formed by reaction between oxidizer and binder. During the process of agglomerate formation and transportation into the combustion chamber, from which they exit through the rocket nozzle, the fuel particles act as reducing agents and become oxidized as a result of reaction with oxidizer particles. The agglomerate formation process has been found to hamper the efficiency of the oxidation-reduction process. Further, the melting action prior to the formation of agglomerates leaves pits in the burning surface of the propellant grain which interfere with the smooth, layer-by-layer combustion necessary to obtain the highest combustion efficiency.
SUMMARY OF THE INVENTION It has now been found that combustion efficiency of BRIEF DESCRIPTION OF THE DRAWING FIG. 1 shows a cross section of a typical prior art propellant grain during combustion; and
FIG. 2 shows a cross section of a propellant grain contemplated by the present invention during combustion.
DESCRIPTION OF THE PREFERRED EMBODIMENTS This invention may be conveniently understood by viewing a cross section of a typical prior art solid propellant grain in conjunction with a cross section of a propellant grain of the type contemplated herein. FIG. 1 of the drawing is a cross section of a typical prior art propellant grain during the process of combustion. Ox-
0 idizer particles 1 and fuel particles 2 are shown as discrete particles within a binder matrix 3. During combustion, pockets of discrete fuel particles melt together to form larger single particles 4. Then, varying numbers of larger, melted together particles 4 roll around on the grain surface and form into agglomerates 5. High velocity gases created by reaction between the oxidizer and the binder carry the agglomerates away from the surface of the propellant grain into the combustion chamber proper where they are oxidized and blown out through the rocket nozzle. The agglomeration process lowers the efficiency of oxidation by lowering the surface area of fuel material exposed to the heat of the combustion chamber and in contact with oxidizer. Also, smooth layer-by-layer burning of the propellant is hampered when pockets of discrete fuel particles 2 melt together to form the larger single particles 4 leaving pits in the propellant grain surface.
In contrast to FIG. 1, FIG. 2 shows a propellant grain of this invention wherein, prior to being incorporated into the binder 3, the fuel particles 1 have been provided with a coat of oxidizer 2 by crystallizing oxidizer material on them. Coating of the fuel particles with ox idizer increases the efficiency of combustion of the fuel particles by insuring that the oxidation-reduction reaction between oxidizer and fuel takes place while the fuel particle is in its small, original size. For a given weight of fuel particles in a propellant grain, a greater amount of surface area is exposed for purposes of reaction by keeping the fuel particles discrete from one another with oxidizer coats than is accomplished by the prior art method described above. Further, coating fuel particles with oxidizer prevents the formation of pockets caused by the melting together of pockets of particles prior to agglomerate formation. Thus, more smooth, layer-by-layer burning is accomplished. Efficiency gains of from 2 to 10 percent may be obtained by coating the fuel particles as shown by FIG. 2 because the fuel is oxidized prior to its entry into the combustion chamber proper rather than being allowed to agglomerate.
Burn rate catalysts may also be coated with oxidizer to assist in the tailoring of combustion. Either burn rate accelerators such as iron oxide, iron blue, and copper chromate or burn rate decelerators such as oxamides, barbiturates, and guanadine derivatives may be coated with oxidizer and utilized to tailor the combustion rate as desired. Since coating places the accelerators or decelerators, whichever the case may be, in more intimate contact with the oxidizer, their action is made more effective at a given concentration level.
Examples of fuel particles and oxidizers which may be utilized in conjunction with one another according to this invention include such fuels as aluminum, beryllium, magnesium, and boron particles and such oxidizers as ammonium perchlorate, ammonium nitrate, cyclotetramethylenetetranitramine (I-IMX), cyclotrimethylenetrinitramine (RDX), and metal perchlorates such as alkali metal perchlorates. Several methods are available for the crystallization of a solute onto a seed particle suspended in solution.
EXAMPLE 1 Aluminum powder is placed in a saturated solution of ammonium perchlorate in water. The ammonium perchlorate is then shocked out of solution by rapidly lowering the temperature until a precipitate appears. The precipitate is a plurality of aluminum particle nuclei coated with ammonium perchlorate.
EXAMPLE ll EXAMPLE Ill Ammonium perchlorate coated fuel particles are obtained bydripping a nonsolvent, ethyl ether, into saturated solutions of ammonium perchlorate in the solvents of Examples I and II containing suspended fuel particles. The coated particles are then centrifuged and the liquid decanted.
EXAMPLE IV Saturated solutions of ammonium nitrate, various alkali metal perchlorates such as sodium perchlorate or potassium perchlorate, HMX, and RDX are used in lieu of the ammonium perchlorate solutions of the previous examples and the methods of the previous examples utilized with similar results.
EXAMPLE V Surface treatment of aluminum powder may be used to enhance the process of Example I. In this embodiment, aluminum powder is treated with perchloric acid to form a thin surface layer of the perchlorate derivative on aluminum. The resulting coated aluminum is then substituted for the nontreated aluminum powder of Example I and the method of Example I used to coat the treated aluminum.
Separation of oxidizer coated fuel particles from the saturated solutions of oxidizer may be accomplished either by centrifugal or sedimentation methods taking advantage of differences in specific gravity.
After preparing the oxidizer coated fuel particles of oxidizer coated burn rate catalysts, the coated particles may be incorporated into abinder by standard propellant processing techniques. The binder, coated particles (either fuel, catalyst, or both), and any other additives may be charged into a standard horizontal or vertical propellant mixer and mixed at temperatures of from about F to about F. After mixing, the propellant is cast into molds or rocket motor cases with suitable mandrels and cured. Typical compositions which may be prepared are:
Binder-l2 to 20% by weight oxidizer-60 to 75% by weight Metal Fuel-0 020%b we t wherein the bintler may lie lig'liroxy or carboxy terminated polybutadiene, a copolymer of butadiene with acrylic acid and/or acrylonitrile. The propellant may be plasticized with liquid hydrocarbon to improve processibility and mechanical properties. Either all or only part of the fuel may be oxidizer coated. Curatives may be added to the binder to achieve an infinite polymer network as is usual in the art.
I claim:
1. The method of tailoring solid rocket propellants comprising the steps of:
a. coating solid metal fuel particles with a crystallized coat of oxidizer selected from the group consisting of ammonium perchlorate, ammonium nitrate, metal perchlorates, cyclotetramethylenetetranitramine and cyclotrimethylenetrinitramine;
b. mixing the oxidizer coated fuel particles witha binder material; and
c. curing the binder.
2. The method of tailoring solid rocket propellants comprising the steps of:
a. coating solid fuel particles selected from the group consisting of aluminum, beryllium, magnesium and boron with a crystallized coat of oxidizer selected from the group consisting of ammonium perchlorate, ammonium nitrate, metal perchlorates, cyclotetramethylenetetranitramine and cyclotrimethylentrinitramine;
b. mixing the oxidizer coated fuel particles with a binder material; and
c. curing the binder.
3. The method according to claim 2 wherein the binder is selected from the group consisting of carboxy terminated polybutadiene, hydroxy terminated polybutadiene, a copolymer of butadiene and acrylic acid, a copolymer of butadiene and acrylonitrile, and a terpolymer of butadiene with acrylic acid and acrylonitrile.
Claims (2)
- 2. The method of tailoring solid rocket propellants comprising the steps of: a. coating solid fuel particles selected from the group consisting of aluminum, beryllium, magnesium and boron with a crystallized coat of oxidizer selected from the group consisting of ammonium perchlorate, ammonium nitrate, metal perchlorates, cyclotetramethylenetetranitramine and cyclotrimethylentrinitramine; b. mixing the oxidizer coated fuel particles with a binder material; and c. curing the binder.
- 3. The method according to claim 2 wherein the binder is selected from the group consisting of carboxy terminated polybutadiene, hydroxy terminated polybutadiene, a copolymer of butadiene and acrylic acid, a copolymer of butadiene and acrylonitrile, and a terpolymer of butadiene with acrylic acid and acrylonitrile.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US2489470A | 1970-03-24 | 1970-03-24 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US3706608A true US3706608A (en) | 1972-12-19 |
Family
ID=21822911
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US24894A Expired - Lifetime US3706608A (en) | 1970-03-24 | 1970-03-24 | Combustion tailoring of solid propellants by oxidizer encasement |
Country Status (1)
| Country | Link |
|---|---|
| US (1) | US3706608A (en) |
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3830673A (en) * | 1973-02-02 | 1974-08-20 | G Simmons | Preparing oxidizer coated metal fuel particles |
| US3976521A (en) * | 1974-11-20 | 1976-08-24 | The United States Of America As Represented By The Secretary Of The Air Force | Method of coating boron particles with ammonium perchlorate |
| US4086110A (en) * | 1976-11-22 | 1978-04-25 | Thiokol Corporation | Propellant made with cocrystals of cyclotetramethylenetetranitramine and ammonium perchlorate |
| US4135956A (en) * | 1975-06-06 | 1979-01-23 | Teledyne Mccormick Selph | Coprecipitated pyrotechnic composition processes and resultant products |
| US5030301A (en) * | 1990-09-28 | 1991-07-09 | Honeywell, Inc. | Oxidizer coated metal fuels with means to prevent auto-ignition |
| US5554820A (en) * | 1995-03-20 | 1996-09-10 | Thiokol Corporation | High solids rocket motor propellants using diepoxy curing agents |
| US6132536A (en) * | 1997-08-20 | 2000-10-17 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Automated propellant blending |
| US6143101A (en) * | 1999-07-23 | 2000-11-07 | Atlantic Research Corporation | Chlorate-free autoignition compositions and methods |
| WO2001038264A1 (en) * | 1999-11-23 | 2001-05-31 | Technanogy, Llc | Composition and method for preparing oxidizer matrix containing dispersed metal particles |
| US6430920B1 (en) | 1999-11-23 | 2002-08-13 | Technanogy, Llc | Nozzleless rocket motor |
| US6503350B2 (en) | 1999-11-23 | 2003-01-07 | Technanogy, Llc | Variable burn-rate propellant |
| US6679960B2 (en) | 2001-04-25 | 2004-01-20 | Lockheed Martin Corporation | Energy dense explosives |
| US20040060626A1 (en) * | 2000-06-02 | 2004-04-01 | The Regents Of The University Of California | Metal-oxide-based energetic materials and synthesis thereof |
| US6748868B2 (en) | 2002-05-15 | 2004-06-15 | Atlantic Research Corp. | Destroying airborne biological and/or chemical agents with solid propellants |
| US20150175495A1 (en) * | 2011-10-17 | 2015-06-25 | David A. Reese | Crystal encapsulated nanoparticles methods and compositions |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2982640A (en) * | 1955-01-17 | 1961-05-02 | Olin Mathieson | Explosive |
| US3120459A (en) * | 1959-11-20 | 1964-02-04 | Arthur D Coates | Composite incendiary powder containing metal coated oxidizing salts |
-
1970
- 1970-03-24 US US24894A patent/US3706608A/en not_active Expired - Lifetime
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2982640A (en) * | 1955-01-17 | 1961-05-02 | Olin Mathieson | Explosive |
| US3120459A (en) * | 1959-11-20 | 1964-02-04 | Arthur D Coates | Composite incendiary powder containing metal coated oxidizing salts |
Cited By (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3830673A (en) * | 1973-02-02 | 1974-08-20 | G Simmons | Preparing oxidizer coated metal fuel particles |
| US3976521A (en) * | 1974-11-20 | 1976-08-24 | The United States Of America As Represented By The Secretary Of The Air Force | Method of coating boron particles with ammonium perchlorate |
| US4135956A (en) * | 1975-06-06 | 1979-01-23 | Teledyne Mccormick Selph | Coprecipitated pyrotechnic composition processes and resultant products |
| US4086110A (en) * | 1976-11-22 | 1978-04-25 | Thiokol Corporation | Propellant made with cocrystals of cyclotetramethylenetetranitramine and ammonium perchlorate |
| US5030301A (en) * | 1990-09-28 | 1991-07-09 | Honeywell, Inc. | Oxidizer coated metal fuels with means to prevent auto-ignition |
| US5554820A (en) * | 1995-03-20 | 1996-09-10 | Thiokol Corporation | High solids rocket motor propellants using diepoxy curing agents |
| US6132536A (en) * | 1997-08-20 | 2000-10-17 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Automated propellant blending |
| US6143101A (en) * | 1999-07-23 | 2000-11-07 | Atlantic Research Corporation | Chlorate-free autoignition compositions and methods |
| US6454886B1 (en) | 1999-11-23 | 2002-09-24 | Technanogy, Llc | Composition and method for preparing oxidizer matrix containing dispersed metal particles |
| US6430920B1 (en) | 1999-11-23 | 2002-08-13 | Technanogy, Llc | Nozzleless rocket motor |
| WO2001038264A1 (en) * | 1999-11-23 | 2001-05-31 | Technanogy, Llc | Composition and method for preparing oxidizer matrix containing dispersed metal particles |
| US6503350B2 (en) | 1999-11-23 | 2003-01-07 | Technanogy, Llc | Variable burn-rate propellant |
| US20040060626A1 (en) * | 2000-06-02 | 2004-04-01 | The Regents Of The University Of California | Metal-oxide-based energetic materials and synthesis thereof |
| US6986819B2 (en) * | 2000-06-02 | 2006-01-17 | The Regents Of The University Of California | Metal-oxide-based energetic materials and synthesis thereof |
| US6679960B2 (en) | 2001-04-25 | 2004-01-20 | Lockheed Martin Corporation | Energy dense explosives |
| US6748868B2 (en) | 2002-05-15 | 2004-06-15 | Atlantic Research Corp. | Destroying airborne biological and/or chemical agents with solid propellants |
| US6782827B2 (en) | 2002-05-15 | 2004-08-31 | Aerojet-General Corporation | Solid propellant formulations and methods and devices employing the same for the destruction of airborne biological and/or chemical agents |
| US6808572B2 (en) | 2002-05-15 | 2004-10-26 | Aerojet-General Corporation | Solid propellant formulations and methods and devices employing the same for the destruction of airborne biological and/or chemical agents |
| US20150175495A1 (en) * | 2011-10-17 | 2015-06-25 | David A. Reese | Crystal encapsulated nanoparticles methods and compositions |
| US9517361B2 (en) * | 2011-10-17 | 2016-12-13 | Purdue Research Foundation | Crystal encapsulated nanoparticles methods and compositions |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US3706608A (en) | Combustion tailoring of solid propellants by oxidizer encasement | |
| US3191535A (en) | Solid cellular metallic propellants | |
| US3309249A (en) | Thermite-resin binder solid fuel composition | |
| US3325316A (en) | Pyrotechnic compositions of metal matrix with oxide dispersed therein | |
| US3986909A (en) | Boron-fuel-rich propellant compositions | |
| GB2412116A (en) | Reactive compositions including metal and methods of forming same | |
| US3639183A (en) | Gas generator compositions | |
| US10415938B2 (en) | Propellant | |
| ES8202324A1 (en) | A process for the preparation of aluminium-containing high-energy explosive compositions. | |
| US2988438A (en) | Combustible compositions | |
| US4747892A (en) | Melt-castable explosive composition | |
| US3956038A (en) | Process for obtaining coated pyrotechnic compositions | |
| US3925122A (en) | Molded explosive bodies having variable detonation speeds | |
| US4445948A (en) | Polymer modified TNT containing explosives | |
| US3830673A (en) | Preparing oxidizer coated metal fuel particles | |
| EP0217770B1 (en) | A method of phlegmatization of crystalline explosives and other explosive crystalline substances, as well as a method of producing plastic bound explosives and substances produced according to the method | |
| US2817581A (en) | Cast ammonium nitrate and urea explosive | |
| US3740278A (en) | Halogenated polyethylene coated crystalline explosive mixed with second explosive | |
| US3044911A (en) | Propellant system | |
| US3379588A (en) | Manufacture of plastic high-power blasting explosive compositions and charges | |
| US3476623A (en) | Metal azide electrically conductive priming composition and manufacture thereof | |
| US6641683B1 (en) | Plasticized, wax-based binder system for melt castable explosives | |
| US3180770A (en) | Propellant fuel containing magnesium aluminum alloy | |
| US3837938A (en) | Solid propellant containing fuel-oxidizer component prepared from fused oxidizers | |
| US3784419A (en) | Propellant composition containing a nickle-silver composite |