US2573471A - Reaction motor operable by liquid propellants and method of operating it - Google Patents

Reaction motor operable by liquid propellants and method of operating it Download PDF

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US2573471A
US2573471A US486236A US48623643A US2573471A US 2573471 A US2573471 A US 2573471A US 486236 A US486236 A US 486236A US 48623643 A US48623643 A US 48623643A US 2573471 A US2573471 A US 2573471A
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propellants
nitric acid
combustion
chamber
reaction
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US486236A
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Frank J Malina
John W Parsons
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Aerojet Rocketdyne Inc
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Aerojet Engineering Corp
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Priority to US486236A priority Critical patent/US2573471A/en
Priority to GB14873/44A priority patent/GB650444A/en
Priority to US182742A priority patent/US2693077A/en
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Publication of US2573471A publication Critical patent/US2573471A/en
Priority to US342564A priority patent/US2771739A/en
Priority to US412196A priority patent/US2774214A/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/425—Propellants
    • 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
    • Y10S149/122—Containing N, without B, P or S

Definitions

  • Our invention relates to jet propulsion and more particularly to propellants which are useful in connection therewith.
  • the present invention relates to fuels, and oxidizers and their combination as propellants and their method of injection into a jet motor.
  • the objects of our invention are: to provide more eificient and eiiective propellants for jet propulsion systems; to provide an oxidizing agent which is easily combustible with a suitable fuel and which has a large amount of oxygen available for burning a fuel; to provide propellants, that is, fuels and oxidizers, which are spontaneously combustible; to provide a method for utilizing such propellants to give smooth combustion and to eliminate danger of explosion; to obviate the difiiculties attendant upon the use of liquified gases; to eliminate the need of an auxiliary ignition system to ignite the propellants.
  • nitric acid As a result of a thorough investigation of the various oxidizing agents which may be used as propellants we prefer to employ nitric acid. Since water tends to retard combustion of the acid with any fuel, the nitric acid should be substantially free of water. Thus, white fuming nitric acid, which normally contai s less than (01. lac-35.6)
  • nitric acid should contain at least about 5% N02 but preferably at least about to N02.
  • red fuming nitric acid is known as red fuming nitric acid and almost all red fuming nitric acid which is commercially available in this country contains between about 5% and 20% nitrogen dioxide by weight and less than about 5% water by weight.
  • Specifications for nitric acid, obtainable commercially as red fuming nitric acid, are as follows:
  • HNOa 90.5% by weight minimum.
  • Water 2.5% by weight maximum.
  • N02 7.25% by weight maximum-6.50% by weight minimum.
  • Density 1.5 minimum1.55 maximum 70 F. Melting point, -50 F. maximum. Color, etc., orange to dark red-fume s vigorously when exposed to air.
  • nitric acid obtainable commercially as white fuming nitric acid, are as follows:
  • Nitric acid 97.5% by weight minimum. Water, 2.0% by weight maximum. N02 content, 0.5% by weight maximum.
  • liquid nitrogen dioxide is a very satis- Y factory oxidizer.
  • Group II.Highly unsaturated hydrocarbons iquidhy arbons of th ace yl ty e and containin a large fraction of unsaturated (double and triple) carbon bonds, or both, for example, divinyl acetylene, dipropargyl, and propargyl alcohol.
  • oxidizers and fuels may be used together as pairs of spontaneously combustible propellants at atmospheric temperature and pressure. However, if desired these oxidizers and fuels may be used with other fuels (such as gasoline) or other oxidizers (such as liquid oxygen) respectively.
  • the figure shows a jet motor system including tanks and conduits for supplying propellants to the motor.
  • the fuels and oxidizers hereinbefore dc.- scribed are advantageously .employed'in the pro-,- pulsionof an aircraft by providing the-fuel andoxidizer in separate containers H and I2 rein to the receptacles II and llandi 'provided with a gas under pressure, preferably a gas inert with respect to either propellant.
  • a gas under pressure preferably a gas inert with respect to either propellant.
  • the container for the fuel and the container for the oxidizer are connected toa source of pressure adapted to force the" contents ofsueh containers into. the jet or'combustion chamber-at controlled rates determined by the degree of opening of the valves in said pipes.
  • the practice of the method of our invention contemplates so relating the. rates of injection" of the oxidizer and of the fuel to the combustion or jet chamber to their inherent combustion properties and the size and temperature of the chamber that smooth non-explosive combustion occurs initially and throughout the entire operation While providing the desired quantity of propulsive power.
  • Our invention is particularly advantageous when the combustion chamber is initially at atmospheric temperature, or at the temperature of any other medium in which the motor is to operate, as We are able to achieve combustion initially without auxiliary ignition or preheating of the chamber or the propellants.
  • propellants are supplied at such initial rates, then, when the propellants are initially injected into the jet motor, the initially burned propellants soon fill the combustion chamber with high temperature gases and vapors which heat the incoming propel ants thereby vaporizing them and reducing the ignition time lag. Then the subsequently injected propellants burn spontaneously without any substantial accumulation of propellants in the liquid phase.
  • highly concentrated nitric acid and aniline operate very satisfactorily when they are injected into the combustion chamber initially and prior to combustion at the rates of 3.6 lbs. per second and 2.4 lbs. per second respectively.
  • Means for supplying propellants to a reaction motor including: two containers; a fuel in one of said containers, said fuel comprising a liquid organic compound of the group consisting of aniline, orthotoluidine, and methylamine; a liquid oxidizer consisting of red fuming nitric acid, white fuming nitric acid, and nitrogen dioxide in the other of said containers, said fuel and oxidizer being adapted for spontaneous combustion when mixed in such reaction motor at the temperature and pressure of the medium surrounding said reaction motor; and means for separately and simultaneous injecting said liquids into the motor.
  • Means for supplying propellants to a reaction motor including: two containers connected to such reaction motor; aniline in one of said containers; an oxidizer consisting of red fuming nitric acid, white fuming nitric acid, and nitrogen dioxide in the other of said containers, said aniline and oxidizer being adapted for combustion when mixed in such reaction motor; and means for separately and simultaneously injecting said aniline and oxidizer into said motor.
  • the method of propelling a device having a combustion chamber which includes the steps of supplying aniline to the combustion chamber, and simultaneously supplying to the combustion chamber nitric acid which is substantially free of water, and causing the products of the sponta- 6; neous reaction betweensaid aniline and said nitric acid to escape from said combustion chamber to produce a reaction thrust on said device.
  • the method of developing thrust which comprises impinging aniline andnitric acid from the group consisting of red fuming nitric acid and white fuming nitric acidagainst each other in a chamber whichis closed except for a constricted exhaust nozzle, and expelling the resultant reaction products through said nozzle to produce a reaction thrust on said chamber.
  • the method of developing thrust which comprises impinging orthotoluidine and nitric acid from the group consisting of red fuming nitric acid and white fuming nitric acid against each other in a chamber which is closed except for a constricted exhaust nozzle, and expelling the resultant reaction products through said nozzle to produce a reaction thrust on said chamber.
  • the method of developing thrust which comprises impinging methylamine and nitric acid from the group consisting of red fuming nitric acid and white fuming nitric acid against each other in a chamber which is closed except for a constricted exhaust nozzle, and expelling the resultant reaction products through said nozzle to produce a reaction thrust on said chamber.
  • the method of developing thrust which comprises ejecting from a reaction chamber the gaseous products produced by the spontaneous combustion in said reaction chamber of aniline and nitric acid from the group consisting of red fuming nitric acid and white fuming nitric acid.
  • the method of propelling a device having a combustion chamber which includes the steps of supplying aniline to the chamber and simultaneously supplying to the chamber nitric acid containing N02 and not more than about 2% water, and causing the products of the spontaneous reaction between the aniline and the acid to escape from the chamber to produce a reaction thrust on the device.
  • the method of developing thrust which comprises ejecting from a reaction chamber the gaseous products produced by the spontaneous combustion in said chamber of aniline and red fuming nitric acid.
  • the method of developing thrust comprises ejecting from a reaction chamber the gaseous products produced by the spontaneous combustion in said reaction chamber of a liquid organic compound of the group consisting of aniline, orthotoluidine and methyl amine with a liquid oxidizer selected from the class of compounds consisting of nitrogen dioxide and nitric acid containing N02 and not more than about 2% water.

Description

MALINA ETAL REACTION MOTOR OPERABLE BY LIQUID PROPELLANTS Oct. 30, 1951 F. J.
AND METHOD OF OPERATING IT Filed May 8, 1945 OX/D/ZER INERT 6A5 JOH/VWPARM/VS FRANK J MAL/NA PRESSURE REG ULA T0}? FUEL IN VEN TORS,
BY I
AGENT Patented Oct. 30, 1951 REACTION MOTOR OPERABLE BY LIQUID PROPELLANTS AND METHOD OF OPER- ATING IT Frank J. Malina and John W. Parsons, Pasadena,
Calif., assignors to Aerojet Engineering Corporation, A zusa, Calif.,
a corporation of Delaware Application May 8, 1943, Serial No. 486,236
Claims.
Our invention relates to jet propulsion and more particularly to propellants which are useful in connection therewith.
While our invention is capable of use in connection with the propulsion of a wide variety of different devices and vehicles, since it finds particular utility in the propulsion of aircraft, its advantages are described with relation to such use, it being understood that our invention is, however not limited to such use.
Prior to our invention special means were always required to ignite the propellants. For example, when liquid oxygen is used as an oxidizer and gasoline is used as a fuel, some auxiliary ignition means must always be provided to initiate combustion of the propellants. This is objectionable because it requires either a spark plug or other i-gnitor or means for heating the walls of the combustion chamber above the ignition point of the propellant mixture making this system complex and dependent upon the operation of such ignition system.
While spontaneous combustion is obtained with our preferred combinations of propellants which is especially effective when operating in accordance with our preferred method it will be understood that the propellants we have discovered offer advantages even when operating under other conditions.
The present invention relates to fuels, and oxidizers and their combination as propellants and their method of injection into a jet motor. Among the objects of our invention are: to provide more eificient and eiiective propellants for jet propulsion systems; to provide an oxidizing agent which is easily combustible with a suitable fuel and which has a large amount of oxygen available for burning a fuel; to provide propellants, that is, fuels and oxidizers, which are spontaneously combustible; to provide a method for utilizing such propellants to give smooth combustion and to eliminate danger of explosion; to obviate the difiiculties attendant upon the use of liquified gases; to eliminate the need of an auxiliary ignition system to ignite the propellants.
oxidizers As a result of a thorough investigation of the various oxidizing agents which may be used as propellants we prefer to employ nitric acid. Since water tends to retard combustion of the acid with any fuel, the nitric acid should be substantially free of water. Thus, white fuming nitric acid, which normally contai s less than (01. lac-35.6)
about 2% of water by weight, is to be preferred to weaker solutions of nitric acid. However, we
have found that more dilute solutions of nitric acid may be utilized provided that nitrogen di- 5 oxide is dissolved in the nitric acid; which is a way of increasing the concentration of an otherwise more dilute solution. Preferably the nitric acid should contain at least about 5% N02 but preferably at least about to N02. Such a solution of nitrogen dioxide is known as red fuming nitric acid and almost all red fuming nitric acid which is commercially available in this country contains between about 5% and 20% nitrogen dioxide by weight and less than about 5% water by weight. Specifications for nitric acid, obtainable commercially as red fuming nitric acid, are as follows:
Chemical composition:
HNOa, 90.5% by weight minimum. Water, 2.5% by weight maximum. N02, 7.25% by weight maximum-6.50% by weight minimum.
Physical properties:
Density, 1.5 minimum1.55 maximum 70 F. Melting point, -50 F. maximum. Color, etc., orange to dark red-fume s vigorously when exposed to air.
Specifications for nitric acid, obtainable commercially as white fuming nitric acid, are as follows:
Chemical composition:
Nitric acid, 97.5% by weight minimum. Water, 2.0% by weight maximum. N02 content, 0.5% by weight maximum.
Physical properties:
Density, 1.46 minimum1.52 maximum 68 F. Melting point F. Color, etc., straw yellow to water white;
fumes vigorously when exposed to air.
found that liquid nitrogen dioxide is a very satis- Y factory oxidizer.
agents hereinabove mentioned and which are satisfactory for jet propulsion provided that the propellants are supplied to I the combustion.
chamber under suitable operating conditions.
These operating conditions are discussed more in detail hereinbelow.
We have found that the four groupsof compounds listed below may be utilized as fuels.
These groups are listed in the order of their effectiveness. I
Grou I.Liquid organic compounds containing at least one amine radical, such as,
A. Aniline, orthotoluidine, and methylamine,
B. Liquid hydrocarbons, containing large percentages of such amine substituted. organic compounds.
Group II.Highly unsaturated hydrocarbons: iquidhy arbons of th ace yl ty e and containin a large fraction of unsaturated (double and triple) carbon bonds, or both, for example, divinyl acetylene, dipropargyl, and propargyl alcohol.
Group III'.Liquid substances containing the v elements having the properties of lithium (Li), berillium (Be), boron (LB), aluminum (Al) magnesium (Mg), phosphorus 1?), potassium (k),
and sodium (Na). With the exception of phosphorus all of the foregoingelements are particularly useful in fuels because they generate large amounts of heat during. combustion, and phosphorus is. particularly-useful because it has a low ignition. temperature. I
A. Liquid hydrides of those elements. I B. Liquid organo-metallic compounds containing one or more of such elements. C. Liquid fuels containing one ormore such elements. D. Liquid fuels containinsone: or more such elements in susp n i n- Group IV.Organic compounds having the p p rties-of pyrole pyridine pinene terpene pinole terpinol hydrazine ozonides V carbon disulphide containing phosphorus.
All the above identifiedsubstances are spontaneously combustible with the. oxidizers hereinbefore discussed. andare independently useful with other oxidizers where means for ignition is provided.
s e-s w Of all of these fuels we prefer to. employ the While during the initial combustion, and subsequent propellants.
inject propellants into the combustion chamber Method of operation The above mentioned oxidizers and fuels may be used together as pairs of spontaneously combustible propellants at atmospheric temperature and pressure. However, if desired these oxidizers and fuels may be used with other fuels (such as gasoline) or other oxidizers (such as liquid oxygen) respectively.
So far as we know we are the first to achieve spontaneous combustion in jet propulsion systems at the temperature and pressure of the medium surrounding the jet motor and while other fuels and oxidizers might be utilized to accomplishsuch spontaneous combustion we prefer to. use the fuels; and oxidizers hereinbefore mentioned. 7
j. Certain difficulties are encountered when utilizing. these propellants for propulsion. Unless the propellants are supplied to the jet motor under the proper conditions the motor is liable to fail completely, to pulsate in its ope'ration','-or to explode, even though the propellants ares'up-"f plied at uniform rates. e
These difficulties may be eliminated and certainty and smoothness of operation secured by} so relating the rates of injection of fuel and oxidizer to the-size of'the' jetchamber and the inherent ignition properties of the mixturethat explosion of the combustible mixture isavoided injection occurs at rates conducive to the'combustion of the continuously supplied propellants so as to avoid the accumulation in the jet chainber of any substantial amount of the unburned To achieve this result, we initially 9 at rates such that the amount of propellants in jected' prior to the initiation of combustionjisf less than about 20% of the volume of the combustion chamber.
After combustion has been'initiated', the pro-=- pellants may be injected at a greater'rate than they are injected initially inasmuch as. the time interval between their injection and combustion is reduced becauseof the higher temperatureand pressure ofthe mixture resulting from prior combustion and the; heating of the. walls-0f the. combustion chamber by; the products ofcombustion.
In. the drawing the figure shows a jet motor system including tanks and conduits for supplying propellants to the motor.
The fuels and oxidizers hereinbefore dc.- scribed are advantageously .employed'in the pro-,- pulsionof an aircraft by providing the-fuel andoxidizer in separate containers H and I2 rein to the receptacles II and llandi 'provided with a gas under pressure, preferably a gas inert with respect to either propellant. Preferably the container for the fuel and the container for the oxidizer are connected toa source of pressure adapted to force the" contents ofsueh containers into. the jet or'combustion chamber-at controlled rates determined by the degree of opening of the valves in said pipes.
The practice of the method of our invention contemplates so relating the. rates of injection" of the oxidizer and of the fuel to the combustion or jet chamber to their inherent combustion properties and the size and temperature of the chamber that smooth non-explosive combustion occurs initially and throughout the entire operation While providing the desired quantity of propulsive power. Our invention is particularly advantageous when the combustion chamber is initially at atmospheric temperature, or at the temperature of any other medium in which the motor is to operate, as We are able to achieve combustion initially without auxiliary ignition or preheating of the chamber or the propellants.
If the propellants are supplied at such initial rates, then, when the propellants are initially injected into the jet motor, the initially burned propellants soon fill the combustion chamber with high temperature gases and vapors which heat the incoming propel ants thereby vaporizing them and reducing the ignition time lag. Then the subsequently injected propellants burn spontaneously without any substantial accumulation of propellants in the liquid phase.
As an example, applied to a combustion chamber having a length of about inches and a cross sectional area of about 7 square inches, highly concentrated nitric acid and aniline operate very satisfactorily when they are injected into the combustion chamber initially and prior to combustion at the rates of 3.6 lbs. per second and 2.4 lbs. per second respectively.
While these propellants and method of use and the apparatus for their use in propelling aircraft or other devices, which are hereinbefore described, are fully capable of providing the advantages primarily stated, it will be recognized by those skilled in the art that various modifications and alterations may be made therein while still providing such advantages, and our invention is therefore to be understood as not limited to the specific embodiments hereinbefore described but as including all modifications and variations thereof coming within the scope of the claims which follow.
We claim as our invention:
1. Means for supplying propellants to a reaction motor, including: two containers; a fuel in one of said containers, said fuel comprising a liquid organic compound of the group consisting of aniline, orthotoluidine, and methylamine; a liquid oxidizer consisting of red fuming nitric acid, white fuming nitric acid, and nitrogen dioxide in the other of said containers, said fuel and oxidizer being adapted for spontaneous combustion when mixed in such reaction motor at the temperature and pressure of the medium surrounding said reaction motor; and means for separately and simultaneous injecting said liquids into the motor.
2. Means for supplying propellants to a reaction motor, including: two containers connected to such reaction motor; aniline in one of said containers; an oxidizer consisting of red fuming nitric acid, white fuming nitric acid, and nitrogen dioxide in the other of said containers, said aniline and oxidizer being adapted for combustion when mixed in such reaction motor; and means for separately and simultaneously injecting said aniline and oxidizer into said motor.
3. The method of propelling a device having a combustion chamber, which includes the steps of supplying aniline to the combustion chamber, and simultaneously supplying to the combustion chamber nitric acid which is substantially free of water, and causing the products of the sponta- 6; neous reaction betweensaid aniline and said nitric acid to escape from said combustion chamber to produce a reaction thrust on said device.
4. The method of developing thrust which comprises impinging aniline andnitric acid from the group consisting of red fuming nitric acid and white fuming nitric acidagainst each other in a chamber whichis closed except for a constricted exhaust nozzle, and expelling the resultant reaction products through said nozzle to produce a reaction thrust on said chamber.
5. The method of developing thrust which comprises impinging orthotoluidine and nitric acid from the group consisting of red fuming nitric acid and white fuming nitric acid against each other in a chamber which is closed except for a constricted exhaust nozzle, and expelling the resultant reaction products through said nozzle to produce a reaction thrust on said chamber.
6. The method of developing thrust which comprises impinging methylamine and nitric acid from the group consisting of red fuming nitric acid and white fuming nitric acid against each other in a chamber which is closed except for a constricted exhaust nozzle, and expelling the resultant reaction products through said nozzle to produce a reaction thrust on said chamber.
7. The method of developing thrust which comprises ejecting from a reaction chamber the gaseous products produced by the spontaneous combustion in said reaction chamber of aniline and nitric acid from the group consisting of red fuming nitric acid and white fuming nitric acid.
8. The method of propelling a device having a combustion chamber which includes the steps of supplying aniline to the chamber and simultaneously supplying to the chamber nitric acid containing N02 and not more than about 2% water, and causing the products of the spontaneous reaction between the aniline and the acid to escape from the chamber to produce a reaction thrust on the device.
9. The method of developing thrust which comprises ejecting from a reaction chamber the gaseous products produced by the spontaneous combustion in said chamber of aniline and red fuming nitric acid.
10. The method of developing thrust which comprises ejecting from a reaction chamber the gaseous products produced by the spontaneous combustion in said reaction chamber of a liquid organic compound of the group consisting of aniline, orthotoluidine and methyl amine with a liquid oxidizer selected from the class of compounds consisting of nitrogen dioxide and nitric acid containing N02 and not more than about 2% water.
FRANK J. MALINA. JOHN W. PARSONS.
REFERENCES CITED The following references are of record in the file of this patent:
UNITED STATES PATENTS Number Name Date 254,021 Johnston Feb. 21, 1882 914,624 Winand Mar. 9, 1909 1,305,340 Bostedo June 3, 1919 1,405,482 Bostedo Feb. '7, 1922 1,506,322 ONeill Aug. 26, 1924 1,506,323 O'Neill Aug. 26, 1924 1,532,930 ONeill Apr. 7, 1925 2,474,183 King June 21, 1949 (Other references on following page) Number FOREIGN PATEN'IS.
OTHER REFERENCES Bflstein, Handbuch der- Crganischefi cngni Countr- Date ieQ' Qth edition; v01. 1-, page454. itg- 17 1915 Organic Chemistry by Whitmore; D. V611? Great Britain Jan 1934 Nostrand, Inca, C., 1937, Reprint-I937-,P E- Great Britain "Dec. 3, 1937 5 7441 1 France Jan; -4 "The'lnteractronrofDimethylamlmeand-Nltr m- Switzerland 1, 93 Acid by H. Hodgson and Gerald 'Iurner in the Journal; of the Chemical Society, pfiblished 1942 by the' C1Iem1ca1' Society; London, pagea-
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US486236A US2573471A (en) 1943-05-08 1943-05-08 Reaction motor operable by liquid propellants and method of operating it
GB14873/44A GB650444A (en) 1943-05-08 1944-08-03 Improvements in or relating to a method of producing hot gases for the purpose of jet propulsion
US182742A US2693077A (en) 1943-05-08 1950-09-01 Reaction motor operable by liquid propellants and method of operating it
US342564A US2771739A (en) 1943-05-08 1953-02-03 Rocket propulsion method
US412196A US2774214A (en) 1943-05-08 1954-02-08 Rocket propulsion method

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US2959915A (en) * 1955-12-27 1960-11-15 Texaco Inc Fuel for and method of operating a jet engine
US2968917A (en) * 1954-05-06 1961-01-24 Ethyl Corp Method of operating a jet engine and fuel composition
US2978304A (en) * 1952-07-05 1961-04-04 Aerojet General Co Sodium, calcium, lithium alloy hydrofuel
US2978864A (en) * 1958-05-19 1961-04-11 Commercial Solvents Corp Ammonium nitrate explosives
US2981617A (en) * 1957-06-25 1961-04-25 Karl F Hager Inhibited fuming nitric acids
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US2983099A (en) * 1952-04-25 1961-05-09 Union Oil Co Method of operating a jet propulsion motor
US2986072A (en) * 1952-11-19 1961-05-30 Colin M Hudson Liquid fuel catapult
US2987547A (en) * 1957-01-31 1961-06-06 Phillips Petroleum Co Nu, nu, nu', nu', nu'', nu'' hexasubstituted-1, 2, 3-triamino-propanes
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US2993335A (en) * 1956-09-13 1961-07-25 Phillips Petroleum Co Reaction motor fuel
US2994190A (en) * 1954-06-07 1961-08-01 Phillips Petroleum Co Additives for nitric acid
US2994191A (en) * 1956-09-24 1961-08-01 Phillips Petroleum Co Operation of reaction motors
US3001361A (en) * 1952-01-29 1961-09-26 Standard Oil Co Boron triamide rocket fuel
US3010279A (en) * 1957-04-08 1961-11-28 Texaco Experiment Inc Method of operating propulsion devices
US3012868A (en) * 1957-12-16 1961-12-12 Dow Chemical Co Enhanced organic explosives
US3013382A (en) * 1957-08-14 1961-12-19 Phillips Petroleum Co Monopropellants
US3019145A (en) * 1958-05-05 1962-01-30 Dow Chemical Co High energy hydrocarbon fuel containing magnesium alloys
US3019687A (en) * 1952-09-11 1962-02-06 Aerojet General Co Method of forming a solid propellant
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
US3026671A (en) * 1958-01-29 1962-03-27 American Cyanamid Co Rocket propulsion method
US3046728A (en) * 1953-11-25 1962-07-31 Airtronics Inc Hydrogen gas generating propellant compositions
US3053710A (en) * 1957-12-12 1962-09-11 Dow Chemical Co Magnesium hydride explosive compositions
US3058301A (en) * 1958-12-24 1962-10-16 Phillips Petroleum Co Reaction motor fuels
US3066478A (en) * 1951-11-30 1962-12-04 Standard Oil Co Organic trithiophosphites as rocket propellants
US3069854A (en) * 1959-09-08 1962-12-25 Ohio Commw Eng Co Catalyzed fuel mixture and method of burning
US3075463A (en) * 1959-09-04 1963-01-29 Dow Chemical Co Well fracturing
US3082598A (en) * 1958-11-17 1963-03-26 Phillips Petroleum Co Rocket fuels
US3086354A (en) * 1958-10-02 1963-04-23 Avir Res Corp Utilization of promoters in effecting reactions
US3099132A (en) * 1952-06-20 1963-07-30 California Research Corp Propulsion method using organic thiophosphites with hydrogen peroxide
US3101589A (en) * 1958-11-10 1963-08-27 Thompson Ramo Wooldridge Inc Method of igniting rocket fuels
US3115005A (en) * 1957-02-28 1963-12-24 John D Clark Composition for the ignition of rocket monopropellants
US3144750A (en) * 1951-12-10 1964-08-18 Phillips Petroleum Co Polycyclic alcohols as hypergolic fuels
US3147592A (en) * 1960-08-01 1964-09-08 Thompson Ramo Wooldridge Inc Hydrazine gas generator
US3157989A (en) * 1958-02-10 1964-11-24 Callery Chemical Co High energy fuel and method of minimizing boron oxide deposits
US3172254A (en) * 1961-04-17 1965-03-09 Chandler Evans Corp Propellant control system for a rocket engine
US3183132A (en) * 1963-04-23 1965-05-11 Seymour M Kaye Method of delaying the ignition of white phosphorus incendiary compositions
US3196607A (en) * 1952-04-25 1965-07-27 Union Oil Co Rocket propulsion method using organic sulfur-containing fuels
US3203773A (en) * 1960-10-25 1965-08-31 Olin Mathieson Boron-containing fuel composition
US3212254A (en) * 1957-08-14 1965-10-19 Phillips Petroleum Co Two component amine nitrate monopropellants and method of propulsion
US3212866A (en) * 1962-12-26 1965-10-19 Texaco Inc Hydrazine-hydrocarbon dispersion composition
US3230700A (en) * 1958-10-27 1966-01-25 Phillips Petroleum Co Rocket propulsion method using hydrocarbon fuels containing aminoalkyl acrylate polymers
US3313208A (en) * 1953-03-25 1967-04-11 Jr Edward G Dorsey Liquid propellant for small caliber gun
US3668873A (en) * 1959-10-14 1972-06-13 Dow Chemical Co Bipropellant rocket process using nitridable fuel
US4316359A (en) * 1979-09-07 1982-02-23 The United States Of America As Represented By The Secretary Of The Army Method of imparting hypergolicity to non-hypergolic rocket propellants
US4899536A (en) * 1988-07-21 1990-02-13 Sundstrand Corporation Starting system for a turbine engine

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US2693077A (en) * 1943-05-08 1954-11-02 Aerojet General Co Reaction motor operable by liquid propellants and method of operating it
US2712497A (en) * 1949-10-28 1955-07-05 Phillips Petroleum Co Jet engine fuel
US2637161A (en) * 1949-11-10 1953-05-05 Us Army Process of ignition for rockets and the like
US2702984A (en) * 1950-07-25 1955-03-01 Phillips Petroleum Co Method and fuel for operating jet engines
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
US2771738A (en) * 1951-10-01 1956-11-27 Phillips Petroleum Co Morpholines as hypergolic fuels
US2750732A (en) * 1951-10-29 1956-06-19 California Research Corp Self-igniting fuel and a method of using same
US2874535A (en) * 1951-11-08 1959-02-24 Phillips Petroleum Co Substituted furans as hypergolic fuels
US3066478A (en) * 1951-11-30 1962-12-04 Standard Oil Co Organic trithiophosphites as rocket propellants
US3144750A (en) * 1951-12-10 1964-08-18 Phillips Petroleum Co Polycyclic alcohols as hypergolic fuels
US2778189A (en) * 1951-12-17 1957-01-22 Standard Oil Co Liquid hydrocarbon rocket fuel
US2778188A (en) * 1951-12-17 1957-01-22 Standard Oil Co Liquid hydrocarbon rocket propellant
US3001361A (en) * 1952-01-29 1961-09-26 Standard Oil Co Boron triamide rocket fuel
US2898732A (en) * 1952-01-29 1959-08-11 Standard Oil Co Rocket propulsion method using phosphorus triamide rocket fuel
US2731342A (en) * 1952-03-24 1956-01-17 Otto T Pfefferkorn Water reactive alloy
US2983099A (en) * 1952-04-25 1961-05-09 Union Oil Co Method of operating a jet propulsion motor
US3196607A (en) * 1952-04-25 1965-07-27 Union Oil Co Rocket propulsion method using organic sulfur-containing fuels
US2842936A (en) * 1952-05-09 1958-07-15 Phillips Petroleum Co Rocket propellants and their utilization
US2943439A (en) * 1952-05-19 1960-07-05 Phillips Petroleum Co Method of propelling rockets and rocket fuels
US2851094A (en) * 1952-06-10 1958-09-09 Donald N Griffin Means for hypergolic flame combat
US3099132A (en) * 1952-06-20 1963-07-30 California Research Corp Propulsion method using organic thiophosphites with hydrogen peroxide
US2763619A (en) * 1952-06-20 1956-09-18 California Research Corp Oxidizing agent
US2753683A (en) * 1952-06-24 1956-07-10 Standard Oil Co Liquid propellant
US2978304A (en) * 1952-07-05 1961-04-04 Aerojet General Co Sodium, calcium, lithium alloy hydrofuel
US2857736A (en) * 1952-07-12 1958-10-28 Standard Oil Co Reaction propulsion method
US3019687A (en) * 1952-09-11 1962-02-06 Aerojet General Co Method of forming a solid propellant
US3021238A (en) * 1952-11-12 1962-02-13 Phillips Petroleum Co Fast burning fuels
US2986072A (en) * 1952-11-19 1961-05-30 Colin M Hudson Liquid fuel catapult
US2749317A (en) * 1952-12-10 1956-06-05 California Research Corp Oxidizing agent
US2764866A (en) * 1953-01-02 1956-10-02 Exxon Research Engineering Co Use of phosphorus compounds in leaded gasoline
US2982637A (en) * 1953-02-13 1961-05-02 Howard W Kruse Motor fuel composition
US2892305A (en) * 1953-02-16 1959-06-30 Standard Oil Co Rocket propulsion method
US3313208A (en) * 1953-03-25 1967-04-11 Jr Edward G Dorsey Liquid propellant for small caliber gun
US2919541A (en) * 1953-07-06 1960-01-05 Phillips Petroleum Co Method for propelling rockets and rocket fuels
US2857737A (en) * 1953-07-28 1958-10-28 Standard Oil Co Method of rocket propulsion
US2810257A (en) * 1953-07-29 1957-10-22 Standard Oil Co Rocket propulsion method
US2898733A (en) * 1953-09-16 1959-08-11 Standard Oil Co Rocket propulsion method
US2898734A (en) * 1953-09-16 1959-08-11 Standard Oil Co Rocket propulsion method
US3046728A (en) * 1953-11-25 1962-07-31 Airtronics Inc Hydrogen gas generating propellant compositions
US2885277A (en) * 1953-11-25 1959-05-05 Airtronics Inc Hydrogen gas generating propellent compositions
US2857738A (en) * 1953-12-09 1958-10-28 Standard Oil Co Method of generating gas
US2893202A (en) * 1953-12-15 1959-07-07 Standard Oil Co Rocket propulsion method
US2893203A (en) * 1954-01-04 1959-07-07 Standard Oil Co Rocket propulsion method
US2968917A (en) * 1954-05-06 1961-01-24 Ethyl Corp Method of operating a jet engine and fuel composition
US2852916A (en) * 1954-05-25 1958-09-23 Napier & Son Ltd Gas producing apparatus especially for rocket type propulsion devices
US2994190A (en) * 1954-06-07 1961-08-01 Phillips Petroleum Co Additives for nitric acid
US2869320A (en) * 1954-07-06 1959-01-20 Phillips Petroleum Co Hypergolic fuel and its method of use in developing thrust
US2769304A (en) * 1954-07-06 1956-11-06 Phillips Petroleum Co Hypergolic fuel and the method of using it
US2909486A (en) * 1954-07-13 1959-10-20 Eugene L Colichman Inhibiting the polymerization of nuclear coolants
US2938330A (en) * 1954-07-21 1960-05-31 Exxon Research Engineering Co Rocket propellant and method for operating a rocket motor or the like
US2993334A (en) * 1954-08-02 1961-07-25 Phillips Petroleum Co Ignition delay reducing agents for hypergolic rocket fuels
US2898735A (en) * 1954-08-12 1959-08-11 Standard Oil Co Rocket propulsion method
US2859833A (en) * 1954-08-23 1958-11-11 Phillips Petroleum Co Recovery of acetylene from gases, and acetylene-n-substituted pyrrole compositions
US2890108A (en) * 1954-09-02 1959-06-09 Ohio Commw Eng Co Catalyzed metal fuel
US2927849A (en) * 1954-12-23 1960-03-08 Ethyl Corp Metal dispersions
US2926750A (en) * 1955-09-06 1960-03-01 Phillips Petroleum Co Unsymmetrical dimethyl hydrazine as a solvent for acetylene
US2959915A (en) * 1955-12-27 1960-11-15 Texaco Inc Fuel for and method of operating a jet engine
US2901886A (en) * 1956-03-21 1959-09-01 Dow Chemical Co Method of increasing engine thrust
US2813013A (en) * 1956-05-21 1957-11-12 Happel John Blends of acetylenic hydrocarbons
US2993335A (en) * 1956-09-13 1961-07-25 Phillips Petroleum Co Reaction motor fuel
US2994191A (en) * 1956-09-24 1961-08-01 Phillips Petroleum Co Operation of reaction motors
US2987547A (en) * 1957-01-31 1961-06-06 Phillips Petroleum Co Nu, nu, nu', nu', nu'', nu'' hexasubstituted-1, 2, 3-triamino-propanes
US3115005A (en) * 1957-02-28 1963-12-24 John D Clark Composition for the ignition of rocket monopropellants
US3010279A (en) * 1957-04-08 1961-11-28 Texaco Experiment Inc Method of operating propulsion devices
US2981617A (en) * 1957-06-25 1961-04-25 Karl F Hager Inhibited fuming nitric acids
US3212254A (en) * 1957-08-14 1965-10-19 Phillips Petroleum Co Two component amine nitrate monopropellants and method of propulsion
US3013382A (en) * 1957-08-14 1961-12-19 Phillips Petroleum Co Monopropellants
US3053710A (en) * 1957-12-12 1962-09-11 Dow Chemical Co Magnesium hydride explosive compositions
US3012868A (en) * 1957-12-16 1961-12-12 Dow Chemical Co Enhanced organic explosives
US3026671A (en) * 1958-01-29 1962-03-27 American Cyanamid Co Rocket propulsion method
US3157989A (en) * 1958-02-10 1964-11-24 Callery Chemical Co High energy fuel and method of minimizing boron oxide deposits
US3019145A (en) * 1958-05-05 1962-01-30 Dow Chemical Co High energy hydrocarbon fuel containing magnesium alloys
US2978864A (en) * 1958-05-19 1961-04-11 Commercial Solvents Corp Ammonium nitrate explosives
US2958182A (en) * 1958-05-19 1960-11-01 Commercial Solvents Corp Stable propellants
US3086354A (en) * 1958-10-02 1963-04-23 Avir Res Corp Utilization of promoters in effecting reactions
US3230700A (en) * 1958-10-27 1966-01-25 Phillips Petroleum Co Rocket propulsion method using hydrocarbon fuels containing aminoalkyl acrylate polymers
US3101589A (en) * 1958-11-10 1963-08-27 Thompson Ramo Wooldridge Inc Method of igniting rocket fuels
US3082598A (en) * 1958-11-17 1963-03-26 Phillips Petroleum Co Rocket fuels
US3058301A (en) * 1958-12-24 1962-10-16 Phillips Petroleum Co Reaction motor fuels
US3075463A (en) * 1959-09-04 1963-01-29 Dow Chemical Co Well fracturing
US3069854A (en) * 1959-09-08 1962-12-25 Ohio Commw Eng Co Catalyzed fuel mixture and method of burning
US3668873A (en) * 1959-10-14 1972-06-13 Dow Chemical Co Bipropellant rocket process using nitridable fuel
US3147592A (en) * 1960-08-01 1964-09-08 Thompson Ramo Wooldridge Inc Hydrazine gas generator
US3203773A (en) * 1960-10-25 1965-08-31 Olin Mathieson Boron-containing fuel composition
US3172254A (en) * 1961-04-17 1965-03-09 Chandler Evans Corp Propellant control system for a rocket engine
US3212866A (en) * 1962-12-26 1965-10-19 Texaco Inc Hydrazine-hydrocarbon dispersion composition
US3183132A (en) * 1963-04-23 1965-05-11 Seymour M Kaye Method of delaying the ignition of white phosphorus incendiary compositions
US4316359A (en) * 1979-09-07 1982-02-23 The United States Of America As Represented By The Secretary Of The Army Method of imparting hypergolicity to non-hypergolic rocket propellants
US4899536A (en) * 1988-07-21 1990-02-13 Sundstrand Corporation Starting system for a turbine engine

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