US2489051A - Rocket propulsion utilizing hydrocarbon, sulfate turpentine, nitric acid, and sulfuric acid or oleum - Google Patents
Rocket propulsion utilizing hydrocarbon, sulfate turpentine, nitric acid, and sulfuric acid or oleum Download PDFInfo
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- US2489051A US2489051A US498892A US49889243A US2489051A US 2489051 A US2489051 A US 2489051A US 498892 A US498892 A US 498892A US 49889243 A US49889243 A US 49889243A US 2489051 A US2489051 A US 2489051A
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- Prior art keywords
- nitric acid
- oleum
- turpentine
- sulfuric acid
- oxidant
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- GRYLNZFGIOXLOG-UHFFFAOYSA-N Nitric acid Chemical compound O[N+]([O-])=O GRYLNZFGIOXLOG-UHFFFAOYSA-N 0.000 title description 24
- 229910017604 nitric acid Inorganic materials 0.000 title description 23
- QAOWNCQODCNURD-UHFFFAOYSA-N Sulfuric acid Chemical compound OS(O)(=O)=O QAOWNCQODCNURD-UHFFFAOYSA-N 0.000 title description 22
- 241000779819 Syncarpia glomulifera Species 0.000 title description 18
- 239000001739 pinus spp. Substances 0.000 title description 17
- 229940036248 turpentine Drugs 0.000 title description 17
- QAOWNCQODCNURD-UHFFFAOYSA-L Sulfate Chemical compound [O-]S([O-])(=O)=O QAOWNCQODCNURD-UHFFFAOYSA-L 0.000 title description 10
- 229930195733 hydrocarbon Natural products 0.000 title description 8
- 239000004215 Carbon black (E152) Substances 0.000 title description 6
- 150000002430 hydrocarbons Chemical class 0.000 title description 4
- 239000007800 oxidant agent Substances 0.000 description 21
- 235000007586 terpenes Nutrition 0.000 description 21
- 239000000446 fuel Substances 0.000 description 20
- 230000001590 oxidative effect Effects 0.000 description 16
- 150000003505 terpenes Chemical class 0.000 description 16
- 239000000203 mixture Substances 0.000 description 11
- 239000003502 gasoline Substances 0.000 description 8
- 238000002485 combustion reaction Methods 0.000 description 7
- 238000000034 method Methods 0.000 description 7
- -1 monocyclic terpene alcohols Chemical class 0.000 description 7
- 150000001338 aliphatic hydrocarbons Chemical class 0.000 description 5
- 239000003795 chemical substances by application Substances 0.000 description 5
- 239000002283 diesel fuel Substances 0.000 description 5
- XMGQYMWWDOXHJM-UHFFFAOYSA-N limonene Chemical compound CC(=C)C1CCC(C)=CC1 XMGQYMWWDOXHJM-UHFFFAOYSA-N 0.000 description 4
- 230000001141 propulsive effect Effects 0.000 description 4
- UHOVQNZJYSORNB-UHFFFAOYSA-N Benzene Chemical compound C1=CC=CC=C1 UHOVQNZJYSORNB-UHFFFAOYSA-N 0.000 description 3
- YXFVVABEGXRONW-UHFFFAOYSA-N Toluene Chemical compound CC1=CC=CC=C1 YXFVVABEGXRONW-UHFFFAOYSA-N 0.000 description 3
- 238000006243 chemical reaction Methods 0.000 description 3
- MOYAFQVGZZPNRA-UHFFFAOYSA-N Terpinolene Chemical compound CC(C)=C1CCC(C)=CC1 MOYAFQVGZZPNRA-UHFFFAOYSA-N 0.000 description 2
- 150000001875 compounds Chemical class 0.000 description 2
- HIFJUMGIHIZEPX-UHFFFAOYSA-N sulfuric acid;sulfur trioxide Chemical compound O=S(=O)=O.OS(O)(=O)=O HIFJUMGIHIZEPX-UHFFFAOYSA-N 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- GRWFGVWFFZKLTI-UHFFFAOYSA-N α-pinene Chemical compound CC1=CCC2C(C)(C)C1C2 GRWFGVWFFZKLTI-UHFFFAOYSA-N 0.000 description 2
- WUOACPNHFRMFPN-SECBINFHSA-N (S)-(-)-alpha-terpineol Chemical compound CC1=CC[C@@H](C(C)(C)O)CC1 WUOACPNHFRMFPN-SECBINFHSA-N 0.000 description 1
- RUJPNZNXGCHGID-UHFFFAOYSA-N (Z)-beta-Terpineol Natural products CC(=C)C1CCC(C)(O)CC1 RUJPNZNXGCHGID-UHFFFAOYSA-N 0.000 description 1
- GRWFGVWFFZKLTI-IUCAKERBSA-N 1S,5S-(-)-alpha-Pinene Natural products CC1=CC[C@@H]2C(C)(C)[C@H]1C2 GRWFGVWFFZKLTI-IUCAKERBSA-N 0.000 description 1
- QBYYXIDJOFZORM-LBPAWUGGSA-N 4-amino-5-chloro-n-[(3s,4r)-1-[3-(4-fluorophenoxy)propyl]-3-methoxypiperidin-4-yl]-2-methoxybenzamide;hydrate Chemical compound O.C([C@@H]([C@@H](CC1)NC(=O)C=2C(=CC(N)=C(Cl)C=2)OC)OC)N1CCCOC1=CC=C(F)C=C1 QBYYXIDJOFZORM-LBPAWUGGSA-N 0.000 description 1
- XZMCDFZZKTWFGF-UHFFFAOYSA-N Cyanamide Chemical compound NC#N XZMCDFZZKTWFGF-UHFFFAOYSA-N 0.000 description 1
- 239000001293 FEMA 3089 Substances 0.000 description 1
- 101100400378 Mus musculus Marveld2 gene Proteins 0.000 description 1
- 150000001298 alcohols Chemical class 0.000 description 1
- OVKDFILSBMEKLT-UHFFFAOYSA-N alpha-Terpineol Natural products CC(=C)C1(O)CCC(C)=CC1 OVKDFILSBMEKLT-UHFFFAOYSA-N 0.000 description 1
- MVNCAPSFBDBCGF-UHFFFAOYSA-N alpha-pinene Natural products CC1=CCC23C1CC2C3(C)C MVNCAPSFBDBCGF-UHFFFAOYSA-N 0.000 description 1
- 238000013329 compounding Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000001704 evaporation Methods 0.000 description 1
- 230000008014 freezing Effects 0.000 description 1
- 238000007710 freezing Methods 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 150000002576 ketones Chemical class 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- KWKAKUADMBZCLK-UHFFFAOYSA-N methyl heptene Natural products CCCCCCC=C KWKAKUADMBZCLK-UHFFFAOYSA-N 0.000 description 1
- TVMXDCGIABBOFY-UHFFFAOYSA-N n-Octanol Natural products CCCCCCCC TVMXDCGIABBOFY-UHFFFAOYSA-N 0.000 description 1
- JTJMJGYZQZDUJJ-UHFFFAOYSA-N phencyclidine Chemical compound C1CCCCN1C1(C=2C=CC=CC=2)CCCCC1 JTJMJGYZQZDUJJ-UHFFFAOYSA-N 0.000 description 1
- 239000002760 rocket fuel Substances 0.000 description 1
- 230000002269 spontaneous effect Effects 0.000 description 1
- QJVXKWHHAMZTBY-GCPOEHJPSA-N syringin Chemical compound COC1=CC(\C=C\CO)=CC(OC)=C1O[C@H]1[C@H](O)[C@@H](O)[C@H](O)[C@@H](CO)O1 QJVXKWHHAMZTBY-GCPOEHJPSA-N 0.000 description 1
- 229930006978 terpinene Natural products 0.000 description 1
- 150000003507 terpinene derivatives Chemical class 0.000 description 1
- 239000000341 volatile oil Substances 0.000 description 1
- 239000002023 wood Substances 0.000 description 1
Images
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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10S149/00—Explosive and thermic compositions or charges
- Y10S149/12—High energy fuel compounds
- Y10S149/121—Containing B, P or S
Definitions
- This invention relates to a reaction propulsion method, and more particularly to a method for generating power by ejecting a stream of combustion products at high velocities.
- Rocket propulsion of the type used for propelling airplanes is the most important eld in which this method of propulsion is employed at the present time, although the invention in its broader aspects is not limited to this eld.
- Modern rocket motors of the type now in use to give an accelerated take-on or accelerated speeds in airplanes consist of a suitable housing provided with pairs of jets adapted to inject a fuel and an oxidant, respectively.
- the combustion of these two materials creates a mass of hot, burning gases which are ejected at high velocity through a suitable orifice, the reaction from this ejection providing the propulsive force.
- Such motors are of great potential value in assisting the take-nii' of seaplanes, since additional power is needed to overcome the skin friction of the Water against the hulls of such planes.
- the terpenes as a class are particularly well suited for use as fuels for use in rocket motors, either when used alone or in admixture with other fuels.
- the terpenes are hydroaromatic compounds containing atleast one double bond and they are capable of igniting spontaneously upon admixture with strong nitric acid in the proper ratios. They are compounds of low freezing point that are soluble in gasoline, fuel oil and mixtures thereof, and they can therefore be used as igniting agents in cheaper fuels such as gasoline and other aliphatic hydrocarbons if desired.
- the hydroaromatic alcohols such as alpha and beta terpineol and similar Application August 16, 1943, Serial No. 498,892
- terpene hydrocarbons such as the pinenes, terpinolene, terpinene, dipentene, and mixtures such as ordinary turpentine oil, sulfate turpentine and the like.
- Our invention in its broader aspects therefore includes the generation of rocket power by igniting a terpene with an oxidant such as strong nitric acid or nitric acid-containing mixtures, while the terpene hydrocarbons and mixtures such as turpentines constitute preferred fuels.
- Sulfate turpentine is particularly useful because oi' its low cost and ready availability.
- any suitable oxidant may be employed in conjunction with the terpenes for the development of rocket power, the most reliable results are obtained with oxidants containing strong nitric acid, and particularly with mixtures of strong nitric acid and sulfuric acid or oleum. Bleached nitric acid having a strength of about HNOs will function as an oxidant for terpenes and terpene mixtures, but much better results are obtained with nitric acid oi about .9S-99.5% HNOS or with fuming nitric acid containing not more than 8-10% of water. Still better results are obtained when 2030% of suifuric acid monohydrate (H2804) or about 1-30% of oleum are dissolved in strong nitric acid and the resulting solution' is used as the oxidant.
- H2804 suifuric acid monohydrate
- the eicacy of the terpenes as igniting agents and fuels in the generation of rocket propulsion can be demonstrated by a cup test in which suitable quantities of the oxidant are poured into a i-inch evaporating dish containing the igniting agent. Upon adding quantities of 10-14 parts by volume of strong nitric acid to 7 parts of the terpenes an immediate bright iiash is obtained with a time lag of about 0.25 second, accompanied by violent combustion with evolution of an intense bright flame.
- Cup tests with ordinary wood turpentine, with sulfate tinepentine consisting principally of alpha pinene and with dipentene and other representative terpenes have shown that in all cases a spontaneous ignition followed by violent combustion is obtained upon addition of 95% or stronger nitric acid or of mixtures thereof with sulfuric acid or oleum.
- terpenes may be employed as such as self-igniting fuels in the generation of rocket power, they may alsoabe employed in the form of solutions in gasoline, Diesel oil, benzene, toluene and the like with a considerable saving in the fuel cost.
- Fig. l is a graph showing the results of cup tests per- 3 formed on solutions of sulfate turpentine in ⁇ 9 1 octane gasoline
- Fig. 2 is a similar graph showing the results of tests with sulfate turpentine dissolved in Diesel oil.
- a prompt ignition with a time lag of less than 2 seconds is obtained when as little as about 15% of turpentine is added to gasoline, provided an oxidant containing both 95% or stronger nitric acid and sulfuric acid or 20% oleum is employed.
- an oxidant containing both 95% or stronger nitric acid and sulfuric acid or 20% oleum is employed.
- about the same results are obtained with either sulfuric acid or oleum and with either 95% nitric acid or with 99.5% nitric acid, but in all cases the time lag before ignition is further reduced by increasinglthe quantity of turpentine in the gasoline to 20-40%.
- 95% nitric acid is used alone it is necessary to employ about 45- 50% of turpentine in the gasoline to obtain prompt and reliable ignition.
- the process of our present invention consists in' generating an ignited propulsive charge by commingling a fuel comprising a terpene, and preferably a terpene hydrocarbon or hydrocarbon mixture such as sulfate turpentine with an oxidant capable of igniting and burning the fuel.
- the oxidant preferably comprises strong nitric acid, and the best results are obtained when sulfuric acid or oleum in amounts of about 10% up to about 15-30% of the weight of the oxidant are added to strong nitric acid.
- the terpenes as a class will ignite rapidly and spontaneously-upon admixture with these oxidants in the proper ratio, and a strong ,propulsive force is obtained by ejection of the burning charge at high velocity,
- the ratio of oxidant to fuel will depend upon the type and strength of the oxidant used and also on the type of fuel.
- the terpenes may be used as fuel or they may be dissolved in an aliphatic hydrocarbon fuel to function as an igniting agent therefore, but in the latter case at least -25% of the terpenes should be used with the strongest oxidants and more than 50% should be present when weaker oxidants such as nitric acid are used.
- the motor may be started by the use of a straight terpene or a rich mixture thereof with other fuels and then operated with an aliphatic hydrocarbon fuel or with a similar fuel containing considerably smaller quantities of the terpenes as igniting agents.
- a rocket propulsion method which comprises injecting into a combustion chamber a fuel comprising a volatile aliphatic hydrocarbon having at least 15-25% of a terpene hydrocarbon dissolved therein together with an oxidant comprising nl tric ⁇ acid containing about l0-30% of a member of the group consisting of sulfuric acid and oleum, whereby an ignited propulsion charget is formed, and electing the burning charge at high velocity.
- a rocket propulsion method which comprises injecting into a combustion chamber a fuel comprising a volatile aliphatic hydrocarbon having at least l5-25% of sulfate turpentine dis-5 solved therein together with an oxidant comprising nitric acid containing about 10-30% of a member of the group consistingk of sulfuric acid and oleum whereby an ignited propulsive charge is formed, and ejecting the burning charge at high velocity.
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- Chemical & Material Sciences (AREA)
- Organic Chemistry (AREA)
- Solid Fuels And Fuel-Associated Substances (AREA)
Description
N0 22 1949 J. M. sAYwARD ErAL 2,489,051
I ROCKET PROPULSION UTILIZING HYDROCARBON,
SULFATE TURPENTINE, NITRIC ACID, AND SULFURIC ACID 0R OLEUM Filed Aug. 16, 1945 BY awww ATTORNEY Patented Nov. 22, 1949 ROCKET PROPULSIN UTILIZING HYDRO- CARBON, SULFATE TURPENTINE, NITRIC ACID, AND SULFURIC ACID R OLEUM John M. Sayward and Daniel E. Nagy, Stamford,
Conn., assignors to American Cyanamid Company, New York, N. Y., a corporation of Maine 2 claims. 1
This invention relates to a reaction propulsion method, and more particularly to a method for generating power by ejecting a stream of combustion products at high velocities. Rocket propulsion of the type used for propelling airplanes is the most important eld in which this method of propulsion is employed at the present time, although the invention in its broader aspects is not limited to this eld.
Modern rocket motors of the type now in use to give an accelerated take-on or accelerated speeds in airplanes consist of a suitable housing provided with pairs of jets adapted to inject a fuel and an oxidant, respectively. The combustion of these two materials creates a mass of hot, burning gases which are ejected at high velocity through a suitable orifice, the reaction from this ejection providing the propulsive force. Such motors are of great potential value in assisting the take-nii' of seaplanes, since additional power is needed to overcome the skin friction of the Water against the hulls of such planes. They are also of great value in assisting the take-olf of heavily loaded land planes, since it is Well-known that only a fraction of the power in a modern airplane is used in flight, as compared with that necessary to lift the plane from the ground under ordinary take-oir conditions.
In order to assist the take-olf of airplanes it is of utmost importance to have a rocket fuel which will ignite immediately and with certainty, as the plane would be almost certain to crash if the rocket motor failed to re. For this reason a self-igniting fuel mixture is greatly preferred to one which must be ignited by a spark or by compression, as in ordinary internal combustion engines. It is a principal object of the present invention to provide a reaction propulsion method which is both instantaneous in action and certain in character, so that power failure is reduced to a minimum.
We have found that the terpenes as a class are particularly well suited for use as fuels for use in rocket motors, either when used alone or in admixture with other fuels. The terpenes are hydroaromatic compounds containing atleast one double bond and they are capable of igniting spontaneously upon admixture with strong nitric acid in the proper ratios. They are compounds of low freezing point that are soluble in gasoline, fuel oil and mixtures thereof, and they can therefore be used as igniting agents in cheaper fuels such as gasoline and other aliphatic hydrocarbons if desired. Although the hydroaromatic alcohols such as alpha and beta terpineol and similar Application August 16, 1943, Serial No. 498,892
monocyclic terpene alcohols and ketones may be employed, We prefer to use the terpene hydrocarbons such as the pinenes, terpinolene, terpinene, dipentene, and mixtures such as ordinary turpentine oil, sulfate turpentine and the like. Our invention in its broader aspects therefore includes the generation of rocket power by igniting a terpene with an oxidant such as strong nitric acid or nitric acid-containing mixtures, while the terpene hydrocarbons and mixtures such as turpentines constitute preferred fuels. Sulfate turpentine is particularly useful because oi' its low cost and ready availability.
Although any suitable oxidant may be employed in conjunction with the terpenes for the development of rocket power, the most reliable results are obtained with oxidants containing strong nitric acid, and particularly with mixtures of strong nitric acid and sulfuric acid or oleum. Bleached nitric acid having a strength of about HNOs will function as an oxidant for terpenes and terpene mixtures, but much better results are obtained with nitric acid oi about .9S-99.5% HNOS or with fuming nitric acid containing not more than 8-10% of water. Still better results are obtained when 2030% of suifuric acid monohydrate (H2804) or about 1-30% of oleum are dissolved in strong nitric acid and the resulting solution' is used as the oxidant.
The eicacy of the terpenes as igniting agents and fuels in the generation of rocket propulsion can be demonstrated by a cup test in which suitable quantities of the oxidant are poured into a i-inch evaporating dish containing the igniting agent. Upon adding quantities of 10-14 parts by volume of strong nitric acid to 7 parts of the terpenes an immediate bright iiash is obtained with a time lag of about 0.25 second, accompanied by violent combustion with evolution of an intense bright flame. Cup tests with ordinary wood turpentine, with sulfate tinepentine consisting principally of alpha pinene and with dipentene and other representative terpenes have shown that in all cases a spontaneous ignition followed by violent combustion is obtained upon addition of 95% or stronger nitric acid or of mixtures thereof with sulfuric acid or oleum.
Although the terpenes may be employed as such as self-igniting fuels in the generation of rocket power, they may alsoabe employed in the form of solutions in gasoline, Diesel oil, benzene, toluene and the like with a considerable saving in the fuel cost. The effectiveness of such solutions is shown on the attached drawing, wherein Fig. l is a graph showing the results of cup tests per- 3 formed on solutions of sulfate turpentine in `9 1 octane gasoline and Fig. 2 is a similar graph showing the results of tests with sulfate turpentine dissolved in Diesel oil.
Referring to Fig. 1 it will be seen that a prompt ignition with a time lag of less than 2 seconds is obtained when as little as about 15% of turpentine is added to gasoline, provided an oxidant containing both 95% or stronger nitric acid and sulfuric acid or 20% oleum is employed. About the same results are obtained with either sulfuric acid or oleum and with either 95% nitric acid or with 99.5% nitric acid, but in all cases the time lag before ignition is further reduced by increasinglthe quantity of turpentine in the gasoline to 20-40%. When 95% nitric acid is used alone it is necessary to employ about 45- 50% of turpentine in the gasoline to obtain prompt and reliable ignition.
The behavior of turpentine in Diesel oil is somewhat similar to its behavior in gasoline, but a wider variation in behavior towards different oxidants is found. Referring to Fig. 2, it will be seen that prompt ignition with a time lag of 1.5 seconds or less is obtained when slightly more than 20% of turpentine is added, providing a mixture containing very strong nitric acid and 15% of oleum is used as the oxidant. When a similar oxidant is prepared from 95% nitric acid it is necessary to add about 35% or more of turpentine to the Diesel oil and approximately the same result is found' when sulfuric acid is substituted for the 01eum. when straight 95% HNO: is used the Diesel oil should contain more than 50% of turpentine to obtain reliable ignition.
From the foregoing it will be seen that the process of our present invention'consists in' generating an ignited propulsive charge by commingling a fuel comprising a terpene, and preferably a terpene hydrocarbon or hydrocarbon mixture such as sulfate turpentine with an oxidant capable of igniting and burning the fuel. For use in rocket motors the oxidant preferably comprises strong nitric acid, and the best results are obtained when sulfuric acid or oleum in amounts of about 10% up to about 15-30% of the weight of the oxidant are added to strong nitric acid. The terpenes as a class will ignite rapidly and spontaneously-upon admixture with these oxidants in the proper ratio, and a strong ,propulsive force is obtained by ejection of the burning charge at high velocity, The ratio of oxidant to fuel will depend upon the type and strength of the oxidant used and also on the type of fuel. The terpenes may be used as fuel or they may be dissolved in an aliphatic hydrocarbon fuel to function as an igniting agent therefore, but in the latter case at least -25% of the terpenes should be used with the strongest oxidants and more than 50% should be present when weaker oxidants such as nitric acid are used. Alternatively, the motor may be started by the use of a straight terpene or a rich mixture thereof with other fuels and then operated with an aliphatic hydrocarbon fuel or with a similar fuel containing considerably smaller quantities of the terpenes as igniting agents.
What we claim is:
1. A rocket propulsion method which comprises injecting into a combustion chamber a fuel comprising a volatile aliphatic hydrocarbon having at least 15-25% of a terpene hydrocarbon dissolved therein together with an oxidant comprising nl tric `acid containing about l0-30% of a member of the group consisting of sulfuric acid and oleum, whereby an ignited propulsion charget is formed, and electing the burning charge at high velocity.
2. A rocket propulsion method which comprises injecting into a combustion chamber a fuel comprising a volatile aliphatic hydrocarbon having at least l5-25% of sulfate turpentine dis-5 solved therein together with an oxidant comprising nitric acid containing about 10-30% of a member of the group consistingk of sulfuric acid and oleum whereby an ignited propulsive charge is formed, and ejecting the burning charge at high velocity.
, JOHN M. SAYWARD.
DANIEL E. NAGYl REFERENCES CITED The following references are of record in the ille of this patent:
UNITED STATES PATENTS Number Name Date 914,624 Winand Mar. 9, 1909 1,571,862 Midgley Feb. 2, 1926 1,770,315 Laurent July 8, 1930 2,217,649 Goddard Oct. 8, 1940 2,398,201 Young et al. Apr. 9, 1946 FOREIGN PATENTS Number Country Date 17,696 Great Britain Dec. 17, 1915 405,645 Great Britain Jan. 29, 1934 157,231 Switzerland Dec. 1, 1932 OTHER REFERENCES Astronautica No. 29, Sept. 1934, page 6. 'I'he Essential Oils,`by Fennemore (1926), pp. 74-77.
Pharmaceutical and Medical Chemistry, by Sadtler, Coblentz and Hostmann, 6th ed., 1927, Lippincott & Co., Phila., and London, page 660.
"The Art of Compounding, by Scoville, 5th ed., 1927, Blakestons Son & Co., Phila., p. 437.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US498892A US2489051A (en) | 1943-08-16 | 1943-08-16 | Rocket propulsion utilizing hydrocarbon, sulfate turpentine, nitric acid, and sulfuric acid or oleum |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US498892A US2489051A (en) | 1943-08-16 | 1943-08-16 | Rocket propulsion utilizing hydrocarbon, sulfate turpentine, nitric acid, and sulfuric acid or oleum |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US2489051A true US2489051A (en) | 1949-11-22 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US498892A Expired - Lifetime US2489051A (en) | 1943-08-16 | 1943-08-16 | Rocket propulsion utilizing hydrocarbon, sulfate turpentine, nitric acid, and sulfuric acid or oleum |
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Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2647364A (en) * | 1948-09-10 | 1953-08-04 | Kellogg M W Co | Pulse jet engine with spontaneously ignitable fuel and oxidizer |
| US2749317A (en) * | 1952-12-10 | 1956-06-05 | California Research Corp | Oxidizing agent |
| US2750732A (en) * | 1951-10-29 | 1956-06-19 | California Research Corp | Self-igniting fuel and a method of using same |
| US2851094A (en) * | 1952-06-10 | 1958-09-09 | Donald N Griffin | Means for hypergolic flame combat |
| US2859587A (en) * | 1953-06-08 | 1958-11-11 | Phillips Petroleum Co | Hypergolic fuel and method of propelling rockets |
| US2864233A (en) * | 1950-12-15 | 1958-12-16 | Johann G Tschinkel | Self vaporization of liquid fuels by partial oxidation |
| US2865727A (en) * | 1950-12-04 | 1958-12-23 | North American Aviation Inc | Rocket motor liquid propellant combination |
| US2932941A (en) * | 1951-11-08 | 1960-04-19 | Phillips Petroleum Co | Sulfenamides and thiosulfenamides as hypergolic fuels |
| US2938330A (en) * | 1954-07-21 | 1960-05-31 | Exxon Research Engineering Co | Rocket propellant and method for operating a rocket motor or the like |
| US2998699A (en) * | 1952-02-25 | 1961-09-05 | Standard Oil Co | Aliphatic orthothioesters as rocket fuels |
| US3021238A (en) * | 1952-11-12 | 1962-02-13 | Phillips Petroleum Co | Fast burning fuels |
| US3020708A (en) * | 1951-01-02 | 1962-02-13 | Phillips Petroleum Co | Rocket propellants and their utilization |
| US3113836A (en) * | 1959-08-12 | 1963-12-10 | Phillips Petroleum Co | Stabilized nitric acid |
| US3132977A (en) * | 1948-10-04 | 1964-05-12 | Aerojet General Co | Hydrazine base fuel |
| US5100642A (en) * | 1989-07-11 | 1992-03-31 | Baycura Orestes M | Method of generating a fuel from water and a compound containing free radicals |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US914624A (en) * | 1906-10-31 | 1909-03-09 | Paul Winand | Explosive mixture for combustion-engines. |
| GB191517696A (en) * | 1915-12-17 | 1919-03-27 | Percy Harold Lawrence | Improvements relating to Means for Ejecting Burning Liquid, Discharging Gases and Producing Flame. |
| US1571862A (en) * | 1923-09-18 | 1926-02-02 | Gen Motors Corp | Prevention of fuel knock |
| US1770315A (en) * | 1925-11-21 | 1930-07-08 | Laurent Andre | Liquid fuel |
| CH157231A (en) * | 1930-04-30 | 1932-09-15 | Leemann Theodor | Method and device for moving vehicles by means of the recoil of expanding gases. |
| GB405645A (en) * | 1932-07-29 | 1934-01-29 | David Hodge | Improvements in and relating to cartridges for blasting, also applicable to the discharge of projectiles from guns |
| US2217649A (en) * | 1939-06-05 | 1940-10-08 | Robert H Goddard | Combustion chamber for rocket apparatus |
| US2398201A (en) * | 1943-05-06 | 1946-04-09 | Aerojet Engineering Corp | Motor |
-
1943
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US914624A (en) * | 1906-10-31 | 1909-03-09 | Paul Winand | Explosive mixture for combustion-engines. |
| GB191517696A (en) * | 1915-12-17 | 1919-03-27 | Percy Harold Lawrence | Improvements relating to Means for Ejecting Burning Liquid, Discharging Gases and Producing Flame. |
| US1571862A (en) * | 1923-09-18 | 1926-02-02 | Gen Motors Corp | Prevention of fuel knock |
| US1770315A (en) * | 1925-11-21 | 1930-07-08 | Laurent Andre | Liquid fuel |
| CH157231A (en) * | 1930-04-30 | 1932-09-15 | Leemann Theodor | Method and device for moving vehicles by means of the recoil of expanding gases. |
| GB405645A (en) * | 1932-07-29 | 1934-01-29 | David Hodge | Improvements in and relating to cartridges for blasting, also applicable to the discharge of projectiles from guns |
| US2217649A (en) * | 1939-06-05 | 1940-10-08 | Robert H Goddard | Combustion chamber for rocket apparatus |
| US2398201A (en) * | 1943-05-06 | 1946-04-09 | Aerojet Engineering Corp | Motor |
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2647364A (en) * | 1948-09-10 | 1953-08-04 | Kellogg M W Co | Pulse jet engine with spontaneously ignitable fuel and oxidizer |
| US3132977A (en) * | 1948-10-04 | 1964-05-12 | Aerojet General Co | Hydrazine base fuel |
| US2865727A (en) * | 1950-12-04 | 1958-12-23 | North American Aviation Inc | Rocket motor liquid propellant combination |
| US2864233A (en) * | 1950-12-15 | 1958-12-16 | Johann G Tschinkel | Self vaporization of liquid fuels by partial oxidation |
| US3020708A (en) * | 1951-01-02 | 1962-02-13 | Phillips Petroleum Co | Rocket propellants and their utilization |
| US2750732A (en) * | 1951-10-29 | 1956-06-19 | California Research Corp | Self-igniting fuel and a method of using same |
| US2932941A (en) * | 1951-11-08 | 1960-04-19 | Phillips Petroleum Co | Sulfenamides and thiosulfenamides as hypergolic fuels |
| US2998699A (en) * | 1952-02-25 | 1961-09-05 | Standard Oil Co | Aliphatic orthothioesters as rocket fuels |
| US2851094A (en) * | 1952-06-10 | 1958-09-09 | Donald N Griffin | Means for hypergolic flame combat |
| US3021238A (en) * | 1952-11-12 | 1962-02-13 | Phillips Petroleum Co | Fast burning fuels |
| US2749317A (en) * | 1952-12-10 | 1956-06-05 | California Research Corp | Oxidizing agent |
| US2859587A (en) * | 1953-06-08 | 1958-11-11 | Phillips Petroleum Co | Hypergolic fuel and method of propelling rockets |
| US2938330A (en) * | 1954-07-21 | 1960-05-31 | Exxon Research Engineering Co | Rocket propellant and method for operating a rocket motor or the like |
| US3113836A (en) * | 1959-08-12 | 1963-12-10 | Phillips Petroleum Co | Stabilized nitric acid |
| US5100642A (en) * | 1989-07-11 | 1992-03-31 | Baycura Orestes M | Method of generating a fuel from water and a compound containing free radicals |
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