US3097479A - Rocket fuel - Google Patents
Rocket fuel Download PDFInfo
- Publication number
- US3097479A US3097479A US3097479DA US3097479A US 3097479 A US3097479 A US 3097479A US 3097479D A US3097479D A US 3097479DA US 3097479 A US3097479 A US 3097479A
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- US
- United States
- Prior art keywords
- nitric acid
- mixture
- fuel
- rocket
- weight
- 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
- 239000002760 rocket fuel Substances 0.000 title claims description 28
- GRYLNZFGIOXLOG-UHFFFAOYSA-N nitric acid Chemical compound O[N+]([O-])=O GRYLNZFGIOXLOG-UHFFFAOYSA-N 0.000 claims description 68
- 239000000203 mixture Substances 0.000 claims description 40
- 239000000446 fuel Substances 0.000 claims description 32
- 238000002485 combustion reaction Methods 0.000 claims description 24
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 claims description 12
- 229910052796 boron Inorganic materials 0.000 claims description 12
- 238000006243 chemical reaction Methods 0.000 claims description 10
- 150000004678 hydrides Chemical class 0.000 claims description 8
- 239000000463 material Substances 0.000 claims description 8
- JUJWROOIHBZHMG-UHFFFAOYSA-N pyridine Chemical compound C1=CC=NC=C1 JUJWROOIHBZHMG-UHFFFAOYSA-N 0.000 description 48
- 238000006396 nitration reaction Methods 0.000 description 24
- MVPPADPHJFYWMZ-UHFFFAOYSA-N Chlorobenzene Chemical compound ClC1=CC=CC=C1 MVPPADPHJFYWMZ-UHFFFAOYSA-N 0.000 description 22
- BFCFYVKQTRLZHA-UHFFFAOYSA-N 2-Nitrochlorobenzene Chemical compound [O-][N+](=O)C1=CC=CC=C1Cl BFCFYVKQTRLZHA-UHFFFAOYSA-N 0.000 description 20
- 150000001875 compounds Chemical class 0.000 description 16
- WDCYWAQPCXBPJA-UHFFFAOYSA-N 1,3-dinitrobenzene Chemical compound [O-][N+](=O)C1=CC=CC([N+]([O-])=O)=C1 WDCYWAQPCXBPJA-UHFFFAOYSA-N 0.000 description 12
- 229910052751 metal Inorganic materials 0.000 description 12
- 239000002184 metal Substances 0.000 description 12
- MYMOFIZGZYHOMD-UHFFFAOYSA-N oxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 12
- 229910052760 oxygen Inorganic materials 0.000 description 12
- 239000001301 oxygen Substances 0.000 description 12
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminum Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 10
- SRTHRWZAMDZJOS-UHFFFAOYSA-N Lithium hydride Chemical compound [H-].[Li+] SRTHRWZAMDZJOS-UHFFFAOYSA-N 0.000 description 8
- 239000002253 acid Substances 0.000 description 8
- 229910052782 aluminium Inorganic materials 0.000 description 8
- 230000002950 deficient Effects 0.000 description 8
- WHXSMMKQMYFTQS-UHFFFAOYSA-N lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 8
- 229910052744 lithium Inorganic materials 0.000 description 8
- 150000002739 metals Chemical class 0.000 description 8
- AMQHSUQKUZLJQL-UHFFFAOYSA-N [O].O[N+]([O-])=O Chemical compound [O].O[N+]([O-])=O AMQHSUQKUZLJQL-UHFFFAOYSA-N 0.000 description 6
- 150000001491 aromatic compounds Chemical class 0.000 description 6
- 229910052987 metal hydride Inorganic materials 0.000 description 6
- 150000004681 metal hydrides Chemical class 0.000 description 6
- 150000002894 organic compounds Chemical class 0.000 description 6
- 239000000126 substance Substances 0.000 description 6
- 125000003118 aryl group Chemical group 0.000 description 4
- 150000001555 benzenes Chemical class 0.000 description 4
- 238000009835 boiling Methods 0.000 description 4
- 238000001816 cooling Methods 0.000 description 4
- 238000005381 potential energy Methods 0.000 description 4
- 238000003756 stirring Methods 0.000 description 4
- QARVLSVVCXYDNA-UHFFFAOYSA-N Bromobenzene Chemical compound BrC1=CC=CC=C1 QARVLSVVCXYDNA-UHFFFAOYSA-N 0.000 description 2
- 229910010277 boron hydride Inorganic materials 0.000 description 2
- -1 bromobenzene Chemical class 0.000 description 2
- 230000005591 charge neutralization Effects 0.000 description 2
- 239000003795 chemical substances by application Substances 0.000 description 2
- 230000000052 comparative effect Effects 0.000 description 2
- 230000000875 corresponding Effects 0.000 description 2
- KLDBIFITUCWVCC-UHFFFAOYSA-N diborane(6) Chemical compound [H]B1([H])[H]B([H])([H])[H]1 KLDBIFITUCWVCC-UHFFFAOYSA-N 0.000 description 2
- 125000000623 heterocyclic group Chemical group 0.000 description 2
- 238000002156 mixing Methods 0.000 description 2
- 230000001264 neutralization Effects 0.000 description 2
- 238000006386 neutralization reaction Methods 0.000 description 2
- 230000000802 nitrating Effects 0.000 description 2
- 125000000449 nitro group Chemical group [O-][N+](*)=O 0.000 description 2
Classifications
-
- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B43/00—Compositions characterised by explosive or thermic constituents not provided for in groups C06B25/00 - C06B41/00
-
- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B47/00—Compositions in which the components are separately stored until the moment of burning or explosion, e.g. "Sprengel"-type explosives; Suspensions of solid component in a normally non-explosive liquid phase, including a thickened aqueous phase
- C06B47/02—Compositions in which the components are separately stored until the moment of burning or explosion, e.g. "Sprengel"-type explosives; Suspensions of solid component in a normally non-explosive liquid phase, including a thickened aqueous phase the components comprising a binary propellant
- C06B47/04—Compositions in which the components are separately stored until the moment of burning or explosion, e.g. "Sprengel"-type explosives; Suspensions of solid component in a normally non-explosive liquid phase, including a thickened aqueous phase the components comprising a binary propellant a component containing a nitrogen oxide or acid thereof
Definitions
- This invention relates to improved rocket fuels. More articularly, this invention relates to rocket fuels comrising nitric acid and an organic compound which is :ficient in oxygen, e.g. chloronitrobenzene, pyridine, or le like.
- a satisfactory rocket fuel must contain both a comustible substance and an oxygen supplier for the comustion of that substance.
- rocket fuels Generally such rocket fuels :quire great care in handling because of their tendency spontaneously ignite at room temperatures.
- Typical f the prior art rocket fuels are solutions of nitric acid nd aromatic polynitro compounds, for example, a soluon of nitric acid and meta-dinitrobenzene.
- the polyitro compound, in this case the meta-dinitrobenzene is he actual fuel, the ntiric acid serving to supply oxygen ontinuously thereto so as to ensure complete combustion f the dinitrobenzene.
- rocket Euels of unusually high energy contnt are provided by mixing nitric acid with an organic compound that is both clefinient in oxygen and also resistant to nitric acid.
- organic compound that is both clefinient in oxygen and also resistant to nitric acid.
- Such a compound should be resistant to nitric acid even when the acid is heated to its boiling point.
- organic compounds are preferably aromatic or heterocyclic.
- Suitable oxyen-deficient aromatic compounds that resist reaction with nitric acid include the halonitrobenzenes, e.g. chloronitrobenzene, and pyridine. If chloronitrobenzene is used, any of the ortho-, meta-, or para isomers is satisfactory, either alone or as mixed with one or both of the other two isomers.
- the mixture of the nitric acid with a suitable oxygendeficient aromatic compound should preferably contain about 60-80% by weight of concentrated nitric acid and correspondingly about -40% by weight of the oxygendeficient compound.
- one or more metals or metal hydrides are added to the nitric acid-oxygen-deficient compound solution.
- Suitable metals include aluminum, boron, and lithium.
- the corresponding hydrides of these metals are equally applicable.
- the addition of such metals to the nitric acid-oxygen-deficient compound mixture serves a dual purpose in that (1) the combustion temperature of the fuel is further increased, thereby resulting in greater power and efliciency and (2) the specific weight of thefuel is increased.
- the amount of metal or metal hydride added is preferably from 1 to 40 percent (by weight) of the weight of the nitric acid-oxygen-deficient compound solution.
- nitric acid-halonitrobenzene rocket fuels of this invention are readily prepared by simply reacting nitric acid with a suitable monohalogenated benzene.
- the resulting halonitrobenzene compound is resistant to further nitration from excess nitric acid, even when such aCld is at its boiling point.
- Typical of the monohalobenzenes to be reacted with nitric acid is monochlorobenzene.
- Example 1 Twenty-five parts of chlorobenzene were added with cooling and agitatin to parts of concentrated (98%) nitric acid. The heat of the reaction indicated a mononitration of the chlorobenzene had occurred. There resulted a mixture of three (ortho, meta, and para) chloronitrobenzene isomers along with excess nitric acid. No dinitration occurred. The chloronitrobenzene isomers were each resistant to further nitration, by the nitric acid so that the heat capable of being liberated by any further exothermic nitrations was maintained as potential energy of the rocket fuel. Upon proper ignition of this mixture in a rocket the heat of combustion, as determined by the thrust developed, was considerably greater than that developed by a similar fuel wherein m-dinitrobenzene was substituted for the chloronitrobenzene.
- Example 2 To parts of concentrated (98%) nitric acid were added, with cooling, 20 parts of pyridine. The amount of heat liberated was precisely the calculated theoretical amount that would be expected to be developed upon the neutralization of a base (pyridine) by an acid. No nitration of the pyridine occurred. The heat capable of being liberated by any subsequent exothermic nitration of the pyridine was maintained as potential energy of the rocket fuel. Upon proper ignition of the above mixture there was developed a very large heat of combustion-much greater than that developed by a similar fuel wherein m-dinitrobenzene was substituted for pyridine.
- Example 3 To the mixture of nitric acid and chloronitrobenzene produced in Example 1 were added with stirring 25 parts of powdered aluminum metal. There resulted a mixture that was eminently suitable as a rocket fuel in that it had a high combustion temperature, a high specific weight, and was capable of liberating a considerable heat of combustion.
- Example 4 To the solution of pyridine in nitric acid produced by Example 2 were added with stirring 35 parts of powdered lithium hydride. The resulting mixture was also an excellent rocket fuel by virtue of its high specific weight, high combustion temperature, and high heat of combustion.
- a method of producing thrust which comprises ejecting from a reaction chamber the gaseous products produced by the combustion of a fuel comprising a mixture of concentrated nitric acid and a halomononitrobenzen-e.
- said fuel contains from 1 to 40 weight percent, based on the amount of 5 said mixture, of a material selected from the group consisting of aluminum, boron, lithium, and their hydrides.
- a rocket fuel consisting essentially of (1) a mixture of from 60 to 80 weight percent concentrated nitric acid and from 20 to 40 weight percent pyridine and (2) from 1 to 40 Weight percent, based on the total amount of said mixture, of a material selected from the group consisting of aluminum, boron, lithium, and their hydrides.
- a rocket fuel comprising a mixture containing from about 60 to 80 parts by weight of concentrated nitric acid and correspondingly from about to 40 parts by weight of halomononitrobenzene, and containing from 1 to 40 parts by weight of a material selected from the group consisting of almuminum, boron, lithium, and their hy- 20 drides.
Landscapes
- Chemical & Material Sciences (AREA)
- Organic Chemistry (AREA)
- Organic Low-Molecular-Weight Compounds And Preparation Thereof (AREA)
- Pyridine Compounds (AREA)
Description
Jnited States Patent ration No Drawing. Filed Nov. 2, 1959, Ser. No. 850,067 5 Claims. (Cl. 60-35.4)
This invention relates to improved rocket fuels. More articularly, this invention relates to rocket fuels comrising nitric acid and an organic compound which is :ficient in oxygen, e.g. chloronitrobenzene, pyridine, or le like.
A satisfactory rocket fuel must contain both a comustible substance and an oxygen supplier for the comustion of that substance. Generally such rocket fuels :quire great care in handling because of their tendency spontaneously ignite at room temperatures. Typical f the prior art rocket fuels are solutions of nitric acid nd aromatic polynitro compounds, for example, a soluon of nitric acid and meta-dinitrobenzene. The polyitro compound, in this case the meta-dinitrobenzene, is he actual fuel, the ntiric acid serving to supply oxygen ontinuously thereto so as to ensure complete combustion f the dinitrobenzene.
As is well known, the nitration of aromatic compounds an exothermic reaction resulting in the liberation of a onsiderable amount of heat. Accordingly, when using a nitric acid solution of m-dinitrobenzene as a rocket fuel he exothermic heat of nitration is not available as energy :ontent in the rocket fuel, so that the heat of combustion if the fuel is considerably less than it would have been lad such exothermic energy of nitration been available. [his results in a less efficient and less powreful rocket fuel.
Accordingly, it is an object of this invention to provide mproved rocket fuels capable of burning with higher leats of combustion than previously thought possible.
Another objects to provide rocket fuels that are stable it ordinary temperatures and not prone to self ignition whereby they may be readily handled with comparative iafety yet without requiring undue precautions.
Additional objects will become apparent hereinafter.
In accordance with one aspect of this invention, rocket Euels of unusually high energy contnt are provided by mixing nitric acid with an organic compound that is both clefinient in oxygen and also resistant to nitric acid. Such a compound should be resistant to nitric acid even when the acid is heated to its boiling point. These organic compounds are preferably aromatic or heterocyclic.
Suitable oxyen-deficient aromatic compounds that resist reaction with nitric acid include the halonitrobenzenes, e.g. chloronitrobenzene, and pyridine. If chloronitrobenzene is used, any of the ortho-, meta-, or para isomers is satisfactory, either alone or as mixed with one or both of the other two isomers.
The mixture of the nitric acid with a suitable oxygendeficient aromatic compound should preferably contain about 60-80% by weight of concentrated nitric acid and correspondingly about -40% by weight of the oxygendeficient compound.
In accordance with a preferred aspect of my invention, one or more metals or metal hydrides are added to the nitric acid-oxygen-deficient compound solution. Suitable metals include aluminum, boron, and lithium. The corresponding hydrides of these metals are equally applicable. The addition of such metals to the nitric acid-oxygen-deficient compound mixture serves a dual purpose in that (1) the combustion temperature of the fuel is further increased, thereby resulting in greater power and efliciency and (2) the specific weight of thefuel is increased. The amount of metal or metal hydride added is preferably from 1 to 40 percent (by weight) of the weight of the nitric acid-oxygen-deficient compound solution.
The nitric acid-halonitrobenzene rocket fuels of this invention are readily prepared by simply reacting nitric acid with a suitable monohalogenated benzene. The resulting halonitrobenzene compound is resistant to further nitration from excess nitric acid, even when such aCld is at its boiling point. Typical of the monohalobenzenes to be reacted with nitric acid is monochlorobenzene. Upon nitration of chlorobenzene with nitric acid there results mononitrochlorobenzene. This is resistant to further attack by the nitric acid.
It will be noted that by a single nitration of chlorobenzene with excess nitric acid there is at once obtained a mixture which is an improved rocket fuela fuel of high energy content and proper oxygen balance which, upon ignitlon, burns with an unusually high heat of combustron. That is, this mixture comprises chloronitrobenzene (the combustible of the rocket fuel) and excess nitric acid. Upon ignition of the chloronitrobenzene combustible the nitric acid functions both as an oxygen supplier and also as a nitrating agent therefor, thereby introducing additional nitro groups into the combustible with the consequent liberation of considerable heat (since this nitration reaction is highly exothermic). Accordingly, the combustion temperature is greatly elevated.
The following examples will more fully illustrate this invention. All parts are by weight unless otherwise indicated.
Example 1 Twenty-five parts of chlorobenzene were added with cooling and agitatin to parts of concentrated (98%) nitric acid. The heat of the reaction indicated a mononitration of the chlorobenzene had occurred. There resulted a mixture of three (ortho, meta, and para) chloronitrobenzene isomers along with excess nitric acid. No dinitration occurred. The chloronitrobenzene isomers were each resistant to further nitration, by the nitric acid so that the heat capable of being liberated by any further exothermic nitrations was maintained as potential energy of the rocket fuel. Upon proper ignition of this mixture in a rocket the heat of combustion, as determined by the thrust developed, was considerably greater than that developed by a similar fuel wherein m-dinitrobenzene was substituted for the chloronitrobenzene.
Example 2 To parts of concentrated (98%) nitric acid were added, with cooling, 20 parts of pyridine. The amount of heat liberated was precisely the calculated theoretical amount that would be expected to be developed upon the neutralization of a base (pyridine) by an acid. No nitration of the pyridine occurred. The heat capable of being liberated by any subsequent exothermic nitration of the pyridine was maintained as potential energy of the rocket fuel. Upon proper ignition of the above mixture there was developed a very large heat of combustion-much greater than that developed by a similar fuel wherein m-dinitrobenzene was substituted for pyridine.
It will be noted that when a monohalobenzene is treated with nitric acid (Example 1) there is a mononitration resulting in a halonitrobenzene. This halonitrobenzene resists further attack by the nitric acid. However, when pyridine is treated with nitric acid (Example 2) not even mononitration occurs, for the pyridine merely dissolves in the acid. Of course, subsequent ignition of the product of Example 2 does cause exothermic nitration of the pyridine.
Example 3 To the mixture of nitric acid and chloronitrobenzene produced in Example 1 were added with stirring 25 parts of powdered aluminum metal. There resulted a mixture that was eminently suitable as a rocket fuel in that it had a high combustion temperature, a high specific weight, and was capable of liberating a considerable heat of combustion.
Example 4 To the solution of pyridine in nitric acid produced by Example 2 were added with stirring 35 parts of powdered lithium hydride. The resulting mixture was also an excellent rocket fuel by virtue of its high specific weight, high combustion temperature, and high heat of combustion.
It will of course be understood that the foregoing detailed description and examples are given merely by way of illustration, and that many variations can be made therein without departing from the spirit of the invention. For example, another halogenated benzene, e.g. bromobenzene, might be substituted for the chlorobenzene of Example 1, leading to a mixture of nitric acid and brornonitrobenzene, which mixture would also exemplify an improved rocket fuel of this invention. Similarly another metal or metal hydride, e.g. powdered boron or boron hydride, could be substituted for the aluminum of Example 3 or the lithium hydride of Example 4.
Having thus described my invention, what I desire to claim and secure by Letters Patent is:
1. A method of producing thrust which comprises ejecting from a reaction chamber the gaseous products produced by the combustion of a fuel comprising a mixture of concentrated nitric acid and a halomononitrobenzen-e.
2, The method of claim 1 wherein said mixture contains from 60 to 80 weight percent of nitric acid and from 20 to 40 weight percent of said halomononitrobenzene.
3. The method of claim 1 wherein said fuel contains from 1 to 40 weight percent, based on the amount of 5 said mixture, of a material selected from the group consisting of aluminum, boron, lithium, and their hydrides.
4. A rocket fuel consisting essentially of (1) a mixture of from 60 to 80 weight percent concentrated nitric acid and from 20 to 40 weight percent pyridine and (2) from 1 to 40 Weight percent, based on the total amount of said mixture, of a material selected from the group consisting of aluminum, boron, lithium, and their hydrides.
5. A rocket fuel comprising a mixture containing from about 60 to 80 parts by weight of concentrated nitric acid and correspondingly from about to 40 parts by weight of halomononitrobenzene, and containing from 1 to 40 parts by weight of a material selected from the group consisting of almuminum, boron, lithium, and their hy- 20 drides.
References Cited in the file of this patent UNITED STATES PATENTS 2,749,372 Dittmar June 5, 1956 2,774,214 Malina et al Dec. 18, 1956 2,810,000 Schenck 0a. 15, 1957 OTHER REFERENCES Journal of Chemical Education, Penner, January 1952, pages 37-39.
Ind. and Eng. Chem, vol. 48, No. 4, April 1956, pages 722-724.
C and En, June 23, 1958, pages 62 67. Spindler: Ann. Chem., vol. 224 (1884), pp. 283-313 (only pp. 299 to 301 relied on).
Claims (2)
1. A METHOD OF PRODUCING THRUS WHICH COMPRISES EJECTING FROM A REACTION CHAMBER THE GASEOUS PRODUCTS PRODUCED BY THE COMBUSTION OF A FUEL COMPRISING A MIXTURE OF CONCENTRATED NITRIC ACID AND A HALOMONONITROBENZE.
5. A ROCKET FUEL COMPRISING A MIXTURE CONTAINING FROM ABOUT 60 TO 80 PARTS BY WEIGHT OF CONCENTRATED NITRIC ACID AND CORRESPONDINGLY FROM ABOUT 20 TO 40 PARTS BY WEIGHT OF HALOMONONITROBENZENE, AND CONTAINING FROM 1 TO 40 PARTS BY WEIGHT OF A MATERIAL SELECTED FROM THE GROUP CONSISTING OF ALMUMINUM, BORON, TITHIUM, AND THEIR HYDRIDES.
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US3097479A true US3097479A (en) | 1963-07-16 |
Family
ID=3451641
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US3097479D Expired - Lifetime US3097479A (en) | Rocket fuel |
Country Status (1)
| Country | Link |
|---|---|
| US (1) | US3097479A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3921394A (en) * | 1964-04-22 | 1975-11-25 | Thiokol Corp | Heterogeneous monopropellant compositions and thrust producing method |
| US3925124A (en) * | 1964-04-22 | 1975-12-09 | Thiokol Corp | Heterogeneous monopropellant compositions |
| US6415596B1 (en) | 1998-07-28 | 2002-07-09 | Otkrytoe Aktsionernoe Obschestvo ″NPO Energomash imeni akademika V.P. | Method for increasing the specific impulse in a liquid-propellant rocket engine and rocket powder unit for realising the same |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2749372A (en) * | 1951-08-31 | 1956-06-05 | Ethyl Corp | Trichlorodinitrobenzenes |
| US2774214A (en) * | 1943-05-08 | 1956-12-18 | Aerojet General Co | Rocket propulsion method |
| US2810000A (en) * | 1955-12-13 | 1957-10-15 | Gen Aniline & Film Corp | Method for the mononitration of p-chlorotoluene |
-
0
- US US3097479D patent/US3097479A/en not_active Expired - Lifetime
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2774214A (en) * | 1943-05-08 | 1956-12-18 | Aerojet General Co | Rocket propulsion method |
| US2749372A (en) * | 1951-08-31 | 1956-06-05 | Ethyl Corp | Trichlorodinitrobenzenes |
| US2810000A (en) * | 1955-12-13 | 1957-10-15 | Gen Aniline & Film Corp | Method for the mononitration of p-chlorotoluene |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3921394A (en) * | 1964-04-22 | 1975-11-25 | Thiokol Corp | Heterogeneous monopropellant compositions and thrust producing method |
| US3925124A (en) * | 1964-04-22 | 1975-12-09 | Thiokol Corp | Heterogeneous monopropellant compositions |
| US6415596B1 (en) | 1998-07-28 | 2002-07-09 | Otkrytoe Aktsionernoe Obschestvo ″NPO Energomash imeni akademika V.P. | Method for increasing the specific impulse in a liquid-propellant rocket engine and rocket powder unit for realising the same |
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