US2811431A - Operation of thrust motors with high impulse and fuel for same - Google Patents
Operation of thrust motors with high impulse and fuel for same Download PDFInfo
- Publication number
- US2811431A US2811431A US546686A US54668644A US2811431A US 2811431 A US2811431 A US 2811431A US 546686 A US546686 A US 546686A US 54668644 A US54668644 A US 54668644A US 2811431 A US2811431 A US 2811431A
- Authority
- US
- United States
- Prior art keywords
- hydrogen
- compounds
- fuel
- oxygen
- acetylene
- 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
- 239000000446 fuel Substances 0.000 title description 26
- 239000000203 mixture Substances 0.000 claims description 30
- 239000001301 oxygen Substances 0.000 claims description 26
- MYMOFIZGZYHOMD-UHFFFAOYSA-N oxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 claims description 26
- 229910052760 oxygen Inorganic materials 0.000 claims description 26
- 150000001875 compounds Chemical class 0.000 claims description 22
- 239000007800 oxidant agent Substances 0.000 claims description 22
- 239000003380 propellant Substances 0.000 claims description 22
- 229910052739 hydrogen Inorganic materials 0.000 claims description 18
- 239000001257 hydrogen Substances 0.000 claims description 16
- 229910052736 halogen Inorganic materials 0.000 claims description 12
- 150000002367 halogens Chemical class 0.000 claims description 12
- 150000002430 hydrocarbons Chemical class 0.000 claims description 12
- IJGRMHOSHXDMSA-UHFFFAOYSA-N nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 12
- 239000004215 Carbon black (E152) Substances 0.000 claims description 10
- OKTJSMMVPCPJKN-UHFFFAOYSA-N carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 8
- 229910052799 carbon Inorganic materials 0.000 claims description 8
- 150000002483 hydrogen compounds Chemical class 0.000 claims description 8
- 229910052757 nitrogen Inorganic materials 0.000 claims description 8
- 150000002830 nitrogen compounds Chemical class 0.000 claims description 8
- 239000012530 fluid Substances 0.000 claims description 6
- 150000002366 halogen compounds Chemical class 0.000 claims description 6
- 150000002894 organic compounds Chemical class 0.000 claims description 4
- 150000002431 hydrogen Chemical class 0.000 claims 4
- 238000002485 combustion reaction Methods 0.000 description 36
- 125000002534 ethynyl group Chemical group [H]C#C* 0.000 description 30
- QGZKDVFQNNGYKY-UHFFFAOYSA-N ammonia Chemical compound N QGZKDVFQNNGYKY-UHFFFAOYSA-N 0.000 description 22
- 238000010494 dissociation reaction Methods 0.000 description 20
- 230000005593 dissociations Effects 0.000 description 20
- 239000007789 gas Substances 0.000 description 12
- UFHFLCQGNIYNRP-UHFFFAOYSA-N hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 12
- 125000004432 carbon atoms Chemical group C* 0.000 description 6
- 239000007788 liquid Substances 0.000 description 6
- 150000001412 amines Chemical class 0.000 description 4
- 125000003277 amino group Chemical group 0.000 description 4
- 125000003118 aryl group Chemical group 0.000 description 4
- KAKZBPTYRLMSJV-UHFFFAOYSA-N butadiene Chemical compound C=CC=C KAKZBPTYRLMSJV-UHFFFAOYSA-N 0.000 description 4
- 238000006243 chemical reaction Methods 0.000 description 4
- OAKJQQAXSVQMHS-UHFFFAOYSA-N hydrazine Chemical compound NN OAKJQQAXSVQMHS-UHFFFAOYSA-N 0.000 description 4
- KDKYADYSIPSCCQ-UHFFFAOYSA-N 1-Butyne Chemical group CCC#C KDKYADYSIPSCCQ-UHFFFAOYSA-N 0.000 description 2
- 235000010005 Catalpa ovata Nutrition 0.000 description 2
- 240000004528 Catalpa ovata Species 0.000 description 2
- LLCSWKVOHICRDD-UHFFFAOYSA-N Diacetylene Chemical group C#CC#C LLCSWKVOHICRDD-UHFFFAOYSA-N 0.000 description 2
- ZBCBWPMODOFKDW-UHFFFAOYSA-N Diethanolamine Chemical compound OCCNCCO ZBCBWPMODOFKDW-UHFFFAOYSA-N 0.000 description 2
- MWWATHDPGQKSAR-UHFFFAOYSA-N Propyne Chemical group CC#C MWWATHDPGQKSAR-UHFFFAOYSA-N 0.000 description 2
- WFYPICNXBKQZGB-UHFFFAOYSA-N Vinylacetylene Chemical group C=CC#C WFYPICNXBKQZGB-UHFFFAOYSA-N 0.000 description 2
- HSFWRNGVRCDJHI-UHFFFAOYSA-N acetylene Chemical compound C#C HSFWRNGVRCDJHI-UHFFFAOYSA-N 0.000 description 2
- 239000000567 combustion gas Substances 0.000 description 2
- 230000000875 corresponding Effects 0.000 description 2
- 238000000354 decomposition reaction Methods 0.000 description 2
- 238000003379 elimination reaction Methods 0.000 description 2
- 239000002360 explosive Substances 0.000 description 2
- 239000011261 inert gas Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- -1 nitrogen hydrogen compound Chemical class 0.000 description 2
- 230000001590 oxidative Effects 0.000 description 2
- 229920001197 polyacetylene Polymers 0.000 description 2
- 238000005215 recombination Methods 0.000 description 2
- 230000002269 spontaneous Effects 0.000 description 2
Images
Classifications
-
- 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
- C06B47/12—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 being a liquefied normally gaseous fuel
Description
Oct. 29, 1957 F. ZWlCKY ETAL Y 2,811,431
OPERATION OF THRUST MOTORS WITH HIGH IMPULSE, AND FUEL FOR SAME Filed July 26, 1944 a T may Beast/RE FUEL 7:4 Mk V ox/a/zaq TANK ACETYLENE 0 AMMONIA I ATH/GH RfssI/R I an ELECTED MAGNET/C VAL V5 Fkl TZ Z WIC I K K ATTORNEYS Unite i.
OPERATION OF THRUST MOTORS WITH HIGH IMPULSE AND FUEL FOR SAME Fritz Zwicky, Pasadena, James M. Carter, Highway Highlands, and Frederick J. Ewing, Altadena, Calif., assignors, by mesne assignments, to Aerojet-General Cor poration, Azusa, Califi, a corporation of Ohio Application July 26, 1944, Serial No. 546,686 8 Claims. (Cl. 52.5)
1b. sec.
Many fuels capable of producing such impulses have been impractical due to the fact that their combustion temperatures and pressures have not been within reasonably workable limits. In accordance with our invention we provide a propellant fuel which develops the desired high specific impulse at temperatures and pressures well below 2600 K. and 300 lbs. per square inch respectively. An attendant advantage of our invention is the elimination of the dissociation of the combustion gases and other unfavorable gas characteristics which would be encountered at temperatures above 4000 K.
One of the most effective means of reducing the combustion temperature is the introduction of H2 gas into the combustion chamber. Practically it is difficult to supply sufiicient gaseous Hz, and the use of liquid H2 is not expedient due to its low liquid density and temperature.
According to our invention endothermic high energy fuels having at least 5% hydrogen by weight are dissolved in compounds containing nitrogen and hydrogen which decompose readily to release hydrogen. The preferred endothermic compound is acetylene and the preferred nitrogen hydrogen compound is liquid ammonia. Ammonia decomposes easily (requiring 16 K. cal/mole) at about 800 C. or less. The low temperature of combustion of this mixture prevents dissociation of the gases thereby increasing the available energy supplied to the jet motors.
Endothermic compounds other than acetylene itself which might be used are the higher members of the acetylene series, these all being referred to herein as acetylenes. Thus, for the purpose of our invention, polyacetylenes, methyl acetylene, and ethyl acetylene may be used in place of acetylene itself. Endothermic olefinic hydrocarbons having two or more double or triple bonds or a combination of double and triple bonds in the molecule such as butadiene, diacetylene, or vinyl acetylene may be substituted for acetylene. Likewise, C, H, N, compounds having at least 6% hydrogen by weight and amines with at least one amine group for every two carbon atoms, hydrazine, or mixtures of any of these with ammonia can be substituted for ammonia.
The carburetant may be oxygen, a halogen or mix- States Patent 0 ice tures of these elements, or an oxygen bearing halogen compound volatile at room temperature. Such carburetants must be used rather than atmospheric oxygen as the oxygen content of the atmosphere is too low to produce the required specific impulse. The reaction requires that an oxidizing atmosphere containing at least 60% by volume of oxygen be used before impulses above 235 lbs. sec.
Oz. The reaction which occurs is substantially as follows:
0,112 2NH3 200 E20 3H, N2
The available specific impulse from such a mixture decomposing in the manner indicated by Equation 1 is 260 lbs. sec.
at a combustion pressure of 300 lbs. per square inch and is obtained at a combustion temperature of only 2600 K. This compares favorably with ordinary hydrocarbon type of fuels such as gasoline because the maximum specific impulses available from the gasoline type of hydrocarbon fuel when burned with oxygen is less than 225 lbs. sec.
at a combustion pressure of 300 lbs. per square inch, even when the combustion temperature approaches 3000 K. and usually the order of magnitude is only between and 200 lbs. sec.
Another advantage of our invention will become apparent when considering the combustion of acetylene and oxygen alone. In absence of dissociation this would proceed according to Equation 2.
and would theoretically give combustion temperatures above 5300 C. Due to dissociation of products of combustion and other unfavorable gas characteristics, however, the actual temperature obtained is much less than 5300 C. being only in a little excess of 3000 C.
Dissociation of the products of combustion is unfavorable except in some very special cases because the energy of dissociation is of the order of magnitude of the energy of combustion. The energy absorbed by the dissociation must be recovered during the expansion process, or it will be lost. Since the time available for recombination is extremely short, being in the order of a microsecond, very little of this absorbed energy is actually recovered.
Our invention eliminates dissociation of the products of combustion and thereby achieves higher efficiency in producing a given exhaust velocity, by expanding gases from a fixed temperature and pressure, than can in general be obtained when dissociation occurs.
An advantage of our invention is demonstrated by the 3 7 addition of NHstO acetylene. The NH3 lowers the theoretical temperature of combustion when oxygen is used in proportions indicated by Equation 1 from 5300 C. to about 2300 C. Because dissociation of the gases of combustion becomes'negligible below 2400 C. there is no corresponding loss of available energy of the propellant. This is indicated by the fact that the actual tem-' perature of combustion is of the same degree of magnitude as the calculated value.
An added feature of our invention is that endothermic compounds such as acetylene can be liquefied and kept under pressure when in solution with NHa and do not undergo spontaneous decomposition as is the case when relatively pure compounds of the class of acetylene are subjected to pressure.
The drawing shows a schematic assembly partly in cross section of a system comprising a motor with fuel, oxygen and inert gas-containers, arranged to operate in accordance with this invention.
Fuel in container 1 isplaced under pressure by the inert gas in container 3 or other suitable pressurizing means,- such as a fuel pump. Constant pressure is maintained by-the pressure regulator 15 placed in the line connecting tanks-3 and 1. Oxidizer under pressure is stored in oxidizer container 2. This tank supplies oxidizer through conduit 4 and constant pressure is maintained at the valve by pressure regulator 5. Electromagnetic valves 7 and 3 permit theoperator to control the flow of fuel and oxidizer into conduits 9 and 10 which connect to jets Hand 12. A spark plug 14 or other suitable ignition means ignites the-explosive mixture near the point of intersection of the oxidizer and fuelin combustion chamber 13 of the motor.
We claim:
1. A propellant charge consisting of a mixture of a non-aromatic, fluid, endothermic, unsaturated hydrocarbon containing at least hydrogen by weight; a compound selected from the group consisting of nitrogen and hydrogen compounds containing at least one NHz group, and organic compounds of hydrogen and nitrogen, containing no additional element .other than carbon, said carbon-containing hydrogen and nitrogen compounds having at least one NHz group for every two carbon atoms; and a volatile oxidizing agent selected from the group consisting of oxygen, a halogen, mixture of halogens, and
oxygen-bearing halogen compounds, volatile at room temperature.
2. A propellant charge according to claim 1 in which the endothermic compound is a compound of the acetylene series.
3. A propellant charge consisting of a mixture in the proportions of one mole of a non-aromatic fluid, endothermic, unsaturated hydrocarbon having at leasttwo double bonds in the molecule, two moles of ammonia and one and one-half moles of a volatile oxidizing agent.
4. A propellant charge consisting of a mixture in the proportions of one mole .of a compound of the acetylene series, two moles of ammonia and one and one-half moles of a volatile oxidizing agent.
5. A propellant charge consisting of a mixture'in the proportions of one mole of acetylene, two moles of an aliphatic amine, said amine having at least one amino group to every two carbon atoms and one and one-half moles of a volatile oxidizing agent.
6. A propellant charge consisting of a mixture in the proportion of one mole of acetylene, two moles of ammonia and one and one-half moles of an oxidizing agent.
7. A propellant'charge consisting of a mixture in the proportion of one mole of butadiene, two moles of ammonia, and one and one-half moles of oxygen.
8. A propellant charge consisting of a mixture in the proportion of one mole acetylene, two moles of ammonia, and one and one-half moles of a volatile halogen.
References Cited in the file of this patent UNITED STATES PATENTS 1,408,056 Wohl Feb. 28, 1922 1,488,009 Kirby Mar. 25, 1924 1,551,650 Eglofi Sept. 1, 1925 1,856,552 Hadamik et a1 May 3, 1932 2,183,313- Goddard Dec. 12, 1939 2,217,649 Goddard Oct. 8, 1940 2,357,184- Frejacques Aug. 29, 1944 2,474,183 King June 21, 1949 FOREIGN PATENTS 15,852 Great Britain Mar. 15, 1906 of 1905
Claims (1)
1. A PROPELLANT CHARGE CONSISTING OF A MIXTURE OF A NON-AROMATIC, FLUID, ENDOTHERMIC, UNSATURATED HYDROCARBON CONTAINING AT LEAST 5% HYDROGEN BY WEIGHT; A COMPOUND SELECTED FROM THE GROUP CONSISTING OF NITROGEN AND HYDROGEN COMPOUNDS CONTAINING AT LEAST NH2 GROUP, AND ORGANIC COMPOUNDS OF HYDROGEN AND NITROGEN, CONTAINING NO ADDITIONAL ELEMENT OTHER THAN CARBON, SAID CAR BON-CONTAINING HYDROGEN AND NITROGEN COMPOUNDS HAVING AT LEAST ONE NH2 GROUP FOR EVERY TWO CARBON ATOMS; AND A VOLATILE OXIDIZING AGENT SELECTED FROM THE GOUP CONSISTING OF OXYGEN, A HALOGEN, MIXTURE OF HALOGENS, AND OXYGEN-BEARING HALOGEN COMPOUNDS, VALATILE AT ROOM TEMPERATURE.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US546686A US2811431A (en) | 1944-07-26 | 1944-07-26 | Operation of thrust motors with high impulse and fuel for same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US546686A US2811431A (en) | 1944-07-26 | 1944-07-26 | Operation of thrust motors with high impulse and fuel for same |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US2811431A true US2811431A (en) | 1957-10-29 |
Family
ID=24181550
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US546686A Expired - Lifetime US2811431A (en) | 1944-07-26 | 1944-07-26 | Operation of thrust motors with high impulse and fuel for same |
Country Status (1)
| Country | Link |
|---|---|
| US (1) | US2811431A (en) |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2926750A (en) * | 1955-09-06 | 1960-03-01 | Phillips Petroleum Co | Unsymmetrical dimethyl hydrazine as a solvent for acetylene |
| US2944385A (en) * | 1958-05-19 | 1960-07-12 | Commercial Solvents Corp | Stable monopropellants |
| US3108431A (en) * | 1956-11-16 | 1963-10-29 | Aerojet General Co | Method of producing thrust for propulsion by combustion a reaction product of libh4 and nh3 with an oxidizer |
| US3112608A (en) * | 1960-11-03 | 1963-12-03 | Rocket Research Corp | Triplex propulsion system and method |
| US3112609A (en) * | 1960-12-12 | 1963-12-03 | Rocket Research Corp | Triplex propulsion system and method having thermal radiation suppression aspects |
| US3170281A (en) * | 1959-08-03 | 1965-02-23 | Air Reduction | Method of producing thrust by hydrogenation of an acetylenic hydrocarbon |
| US3219498A (en) * | 1960-02-17 | 1965-11-23 | Nitrochemie Gmbh | Organic acetylenic polymers, their preparation and use as explosives and rocket propellants |
| US3322228A (en) * | 1964-05-08 | 1967-05-30 | Sinclair Research Inc | Method of improving the impulse characteristics of seismic gas exploders |
| US4631096A (en) * | 1984-10-01 | 1986-12-23 | Deutsche Forschungs-Und Versuchsanstalt Fur Luft-Und Raumfahrt E.V. | High energy materials containing metastable helium, a process for producing same and applications thereof |
| US4873928A (en) * | 1987-06-15 | 1989-10-17 | Apti, Inc. | Nuclear-sized explosions without radiation |
| US20130305597A1 (en) * | 2012-05-21 | 2013-11-21 | CM Global Systems, LLC | Hydrocarbon-containing mixture and method and system for making the same |
| RU172588U1 (en) * | 2016-06-20 | 2017-07-13 | Общество с ограниченной ответственностью "Лин Индастриал" | Three-component liquid rocket launcher on cryogenic environmentally friendly components |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB190615852A (en) * | 1906-07-13 | 1907-01-03 | Fred Lobnitz | Improvements in the Cutters of Rock Cutting Apparatus. |
| US1408056A (en) * | 1920-06-04 | 1922-02-28 | Wohl Alfred | Explosive |
| US1488009A (en) * | 1921-03-30 | 1924-03-25 | Gen Oil Company Of New Jersey | Substitute fuel oil |
| US1551650A (en) * | 1921-08-26 | 1925-09-01 | Universal Oil Prod Co | Explosive and process of making same |
| US1856552A (en) * | 1931-06-26 | 1932-05-03 | Hadamik Frank | Carbide rocket |
| US2183313A (en) * | 1938-07-07 | 1939-12-12 | Robert H Goddard | Combustion chamber for aircraft |
| US2217649A (en) * | 1939-06-05 | 1940-10-08 | Robert H Goddard | Combustion chamber for rocket apparatus |
| US2357184A (en) * | 1940-10-21 | 1944-08-29 | Frejacques Jean Leon Maurice | Fuel for motor vehicles |
| US2474183A (en) * | 1949-06-21 | Rocket propulsion by reacting |
-
1944
- 1944-07-26 US US546686A patent/US2811431A/en not_active Expired - Lifetime
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2474183A (en) * | 1949-06-21 | Rocket propulsion by reacting | ||
| GB190615852A (en) * | 1906-07-13 | 1907-01-03 | Fred Lobnitz | Improvements in the Cutters of Rock Cutting Apparatus. |
| US1408056A (en) * | 1920-06-04 | 1922-02-28 | Wohl Alfred | Explosive |
| US1488009A (en) * | 1921-03-30 | 1924-03-25 | Gen Oil Company Of New Jersey | Substitute fuel oil |
| US1551650A (en) * | 1921-08-26 | 1925-09-01 | Universal Oil Prod Co | Explosive and process of making same |
| US1856552A (en) * | 1931-06-26 | 1932-05-03 | Hadamik Frank | Carbide rocket |
| US2183313A (en) * | 1938-07-07 | 1939-12-12 | Robert H Goddard | Combustion chamber for aircraft |
| US2217649A (en) * | 1939-06-05 | 1940-10-08 | Robert H Goddard | Combustion chamber for rocket apparatus |
| US2357184A (en) * | 1940-10-21 | 1944-08-29 | Frejacques Jean Leon Maurice | Fuel for motor vehicles |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2926750A (en) * | 1955-09-06 | 1960-03-01 | Phillips Petroleum Co | Unsymmetrical dimethyl hydrazine as a solvent for acetylene |
| US3108431A (en) * | 1956-11-16 | 1963-10-29 | Aerojet General Co | Method of producing thrust for propulsion by combustion a reaction product of libh4 and nh3 with an oxidizer |
| US2944385A (en) * | 1958-05-19 | 1960-07-12 | Commercial Solvents Corp | Stable monopropellants |
| US3170281A (en) * | 1959-08-03 | 1965-02-23 | Air Reduction | Method of producing thrust by hydrogenation of an acetylenic hydrocarbon |
| US3219498A (en) * | 1960-02-17 | 1965-11-23 | Nitrochemie Gmbh | Organic acetylenic polymers, their preparation and use as explosives and rocket propellants |
| US3112608A (en) * | 1960-11-03 | 1963-12-03 | Rocket Research Corp | Triplex propulsion system and method |
| US3112609A (en) * | 1960-12-12 | 1963-12-03 | Rocket Research Corp | Triplex propulsion system and method having thermal radiation suppression aspects |
| US3322228A (en) * | 1964-05-08 | 1967-05-30 | Sinclair Research Inc | Method of improving the impulse characteristics of seismic gas exploders |
| US4631096A (en) * | 1984-10-01 | 1986-12-23 | Deutsche Forschungs-Und Versuchsanstalt Fur Luft-Und Raumfahrt E.V. | High energy materials containing metastable helium, a process for producing same and applications thereof |
| US4873928A (en) * | 1987-06-15 | 1989-10-17 | Apti, Inc. | Nuclear-sized explosions without radiation |
| US20130305597A1 (en) * | 2012-05-21 | 2013-11-21 | CM Global Systems, LLC | Hydrocarbon-containing mixture and method and system for making the same |
| US8742194B2 (en) * | 2012-05-21 | 2014-06-03 | CM Global Systems, LLC | Hydrocarbon-containing mixture and method and system for making the same |
| RU172588U1 (en) * | 2016-06-20 | 2017-07-13 | Общество с ограниченной ответственностью "Лин Индастриал" | Three-component liquid rocket launcher on cryogenic environmentally friendly components |
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