US2901886A - Method of increasing engine thrust - Google Patents
Method of increasing engine thrust Download PDFInfo
- Publication number
- US2901886A US2901886A US572805A US57280556A US2901886A US 2901886 A US2901886 A US 2901886A US 572805 A US572805 A US 572805A US 57280556 A US57280556 A US 57280556A US 2901886 A US2901886 A US 2901886A
- Authority
- US
- United States
- Prior art keywords
- propynyl
- hydrazine
- combustion
- fuel
- engine
- 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
- 238000000034 method Methods 0.000 title claims description 10
- 239000000446 fuel Substances 0.000 claims description 29
- 238000002485 combustion reaction Methods 0.000 claims description 26
- -1 1-ETHYL-I-(-PROPYNYL) HYDRAZINE Chemical compound 0.000 claims description 13
- 150000001412 amines Chemical class 0.000 claims description 8
- 239000007800 oxidant agent Substances 0.000 claims description 8
- CYCYZHMUOSKYBG-UHFFFAOYSA-N prop-2-ynylhydrazine Chemical compound NNCC#C CYCYZHMUOSKYBG-UHFFFAOYSA-N 0.000 claims description 2
- 230000002269 spontaneous effect Effects 0.000 claims description 2
- 230000000694 effects Effects 0.000 claims 2
- FLCVMSCBIOSEIV-UHFFFAOYSA-N 1,1-bis(prop-2-ynyl)hydrazine Chemical compound C#CCN(N)CC#C FLCVMSCBIOSEIV-UHFFFAOYSA-N 0.000 claims 1
- PJDXKHMHDLLSDJ-UHFFFAOYSA-N 1-methyl-1-prop-2-ynylhydrazine Chemical compound CN(N)CC#C PJDXKHMHDLLSDJ-UHFFFAOYSA-N 0.000 claims 1
- OTMSDBZUPAUEDD-UHFFFAOYSA-N Ethane Chemical compound CC OTMSDBZUPAUEDD-UHFFFAOYSA-N 0.000 claims 1
- WCYWZMWISLQXQU-UHFFFAOYSA-N methyl Chemical class [CH3] WCYWZMWISLQXQU-UHFFFAOYSA-N 0.000 claims 1
- OAKJQQAXSVQMHS-UHFFFAOYSA-N Hydrazine Chemical compound NN OAKJQQAXSVQMHS-UHFFFAOYSA-N 0.000 description 34
- WFPZPJSADLPSON-UHFFFAOYSA-N dinitrogen tetraoxide Chemical compound [O-][N+](=O)[N+]([O-])=O WFPZPJSADLPSON-UHFFFAOYSA-N 0.000 description 6
- 150000001875 compounds Chemical class 0.000 description 5
- 125000001494 2-propynyl group Chemical group [H]C#CC([H])([H])* 0.000 description 4
- PAYRUJLWNCNPSJ-UHFFFAOYSA-N Aniline Chemical compound NC1=CC=CC=C1 PAYRUJLWNCNPSJ-UHFFFAOYSA-N 0.000 description 4
- MHAJPDPJQMAIIY-UHFFFAOYSA-N Hydrogen peroxide Chemical compound OO MHAJPDPJQMAIIY-UHFFFAOYSA-N 0.000 description 4
- 125000003903 2-propenyl group Chemical group [H]C([*])([H])C([H])=C([H])[H] 0.000 description 3
- RTZKZFJDLAIYFH-UHFFFAOYSA-N Diethyl ether Chemical compound CCOCC RTZKZFJDLAIYFH-UHFFFAOYSA-N 0.000 description 3
- GRYLNZFGIOXLOG-UHFFFAOYSA-N Nitric acid Chemical compound O[N+]([O-])=O GRYLNZFGIOXLOG-UHFFFAOYSA-N 0.000 description 3
- 238000006243 chemical reaction Methods 0.000 description 3
- 229910017604 nitric acid Inorganic materials 0.000 description 3
- GBQUSOVLEXMGII-UHFFFAOYSA-N prop-1-ynylhydrazine Chemical class CC#CNN GBQUSOVLEXMGII-UHFFFAOYSA-N 0.000 description 3
- VVJKKWFAADXIJK-UHFFFAOYSA-N Allylamine Chemical compound NCC=C VVJKKWFAADXIJK-UHFFFAOYSA-N 0.000 description 2
- BAVYZALUXZFZLV-UHFFFAOYSA-N Methylamine Chemical compound NC BAVYZALUXZFZLV-UHFFFAOYSA-N 0.000 description 2
- 150000001338 aliphatic hydrocarbons Chemical class 0.000 description 2
- 239000003153 chemical reaction reagent Substances 0.000 description 2
- 125000000118 dimethyl group Chemical group [H]C([H])([H])* 0.000 description 2
- RTWCHRMHGXBETA-UHFFFAOYSA-N prop-1-yn-1-amine Chemical compound CC#CN RTWCHRMHGXBETA-UHFFFAOYSA-N 0.000 description 2
- 125000002568 propynyl group Chemical group [*]C#CC([H])([H])[H] 0.000 description 2
- NWZSZGALRFJKBT-KNIFDHDWSA-N (2s)-2,6-diaminohexanoic acid;(2s)-2-hydroxybutanedioic acid Chemical compound OC(=O)[C@@H](O)CC(O)=O.NCCCC[C@H](N)C(O)=O NWZSZGALRFJKBT-KNIFDHDWSA-N 0.000 description 1
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 description 1
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- 240000007049 Juglans regia Species 0.000 description 1
- 235000009496 Juglans regia Nutrition 0.000 description 1
- 239000000654 additive Substances 0.000 description 1
- 150000001448 anilines Chemical class 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 125000001495 ethyl group Chemical group [H]C([H])([H])C([H])([H])* 0.000 description 1
- WHRIKZCFRVTHJH-UHFFFAOYSA-N ethylhydrazine Chemical compound CCNN WHRIKZCFRVTHJH-UHFFFAOYSA-N 0.000 description 1
- 238000004508 fractional distillation Methods 0.000 description 1
- 230000008014 freezing Effects 0.000 description 1
- 238000007710 freezing Methods 0.000 description 1
- IKDUDTNKRLTJSI-UHFFFAOYSA-N hydrazine monohydrate Substances O.NN IKDUDTNKRLTJSI-UHFFFAOYSA-N 0.000 description 1
- 239000001257 hydrogen Substances 0.000 description 1
- 229910052739 hydrogen Inorganic materials 0.000 description 1
- 125000004435 hydrogen atom Chemical group [H]* 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 125000002496 methyl group Chemical group [H]C([H])([H])* 0.000 description 1
- HDZGCSFEDULWCS-UHFFFAOYSA-N monomethylhydrazine Chemical compound CNN HDZGCSFEDULWCS-UHFFFAOYSA-N 0.000 description 1
- SQRXWXCCRCQPKC-UHFFFAOYSA-N n-methyl-n-prop-2-ynylprop-2-yn-1-amine Chemical compound C#CCN(C)CC#C SQRXWXCCRCQPKC-UHFFFAOYSA-N 0.000 description 1
- 239000003960 organic solvent Substances 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 235000015927 pasta Nutrition 0.000 description 1
- YORCIIVHUBAYBQ-UHFFFAOYSA-N propargyl bromide Chemical compound BrCC#C YORCIIVHUBAYBQ-UHFFFAOYSA-N 0.000 description 1
- LJZPPWWHKPGCHS-UHFFFAOYSA-N propargyl chloride Chemical compound ClCC#C LJZPPWWHKPGCHS-UHFFFAOYSA-N 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 235000020234 walnut Nutrition 0.000 description 1
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
- C06B47/08—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 hydrazine or a hydrazine derivative
-
- 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
Definitions
- high energy fuel refers to fuels which spontaneously ignite and violently burn when mixed with an oxidizing agent such as hydrogen peroxide, nitric acid or nitrogen tetroxide to produce thrust in a rocket, jet or turbo-jet engine.
- oxidizing agent such as hydrogen peroxide, nitric acid or nitrogen tetroxide
- High energy fuels frequently used in such engines include hydrazine, hydrazine hydrate, aniline and aliphatic hydrocarbons.
- a particular disadvantage of such fuels has been their liquidus properties whereby they freeze at temperatures commonly encountered in missile and jet plane flight.
- Another disadvantage of many such fuels has been their inability to produce high thrusts due to their unfavorable heats of combustion or undesirable ignition characteristics.
- a fuel which would be charao terized by a high heat of combustion, low freezing point, short ignition delay and high specific impulse would be of outstanding value in the development of rockets and missiles. It is thus clearly evident that fuels having improved ignition, combustion and liquidus properties would be a distinct advantage to the development of the rocket and jet engine industry.
- One object of this invention is to provide a novel method of obtaining thrust from an engine capable of burning a high energy fuel. Another object is to provide an improved method of increasing the thrust of an engine which burns a high energy fuel by supplying to the combustion zone of such an engine a fuel having very desirable liquidus, ignition and combustion properties.
- thrust may be obtained from an engine capable of burning a high energy fuel by supplying to the combustion zone of such an engine a propynyl compound having the general formula:
- HCEC-CHr-IiF-R where R is hydrogen, methyl, ethyl or Z-propynyl and R is amino, methyl or allyl, along with an oxidizer such as nitric acid, nitrogen tetroxide, hydrogen peroxide or oxygen.
- oxidizer such as nitric acid, nitrogen tetroxide, hydrogen peroxide or oxygen.
- propynyl compounds have very desirable overall characteristics such as high heat of combustion, high specific impulse, wide liquidus range and 2 a short ignition delay whereby theyare particularly adapted to be employed as high energy fuels.
- the oxidizing agent be introduced into the combustion chamber at a rate and in an amount suificient to efiect substantially complete combustion of the propynyl fuel compound.
- the rate at which thrust is developed in the engine varies directly with the rate at which the propynyl compound and oxidizing agent are metered into the combustion chamber.
- the propynyl compound may be supplied to the combustion zone along with other additives such as aniline, substituted anilines or aliphatic hydrocarbons.
- the thrust developed from the combustion of the fuel is found to be considerably greater when one or more of the propynyl hydrazines or propynyl amines is used as the fuel than when hydrazine is used.
- the propynyl hydrazine and propynyl amine compounds used as fuels in the method of the present invention to increase engine thrust may be prepared by reacting propargyl bromide or propargyl chloride with hydrazine, methyl hydrazine, ethyl hydrazine, methylamine or allylamine.
- the reaction is carried out in an inert organic solvent such as a lower alcohol or diethyl ether.
- the reaction is exothermic and takes place smoothly at l0 to C. with the production of the desired product and the hydrohalide of the hydrazine or amine reagent.
- WhatI claim is: 1.
- com-bustionzonev is. di.u1ethyl )(2- propynyl) amine.
- a method of increiiinglizthe thrust of an engine capab1e,. of ,burning afihigh energy ,fuel which comprises sutlicirelwto. effecu-substantiaily completes; combustion of the fuel, the high energy fuel bei'ngseleeted' from the group consisting of,.(2- rppynyl),;hydrazine,; 1,lbis (2- propynyl) hydrazinemthifl vlq z-pubiiynyl) hydrazine, l-ethyl-l-(Z-propynyl) hydrazine, methyl di(2-propynyl) amine, dimethy1 (2-propynyl) aniine -and allyl di(2-propynyl) amine, and the oxidizer being selected from the group consisting of nitric acid, nitrogen tetroxide, hydrogem-peroxide and oxygenk a ReferencesaGitedi
Landscapes
- Chemical & Material Sciences (AREA)
- Organic Chemistry (AREA)
- Organic Low-Molecular-Weight Compounds And Preparation Thereof (AREA)
Description
United States Patent 2,901,886 METHOD or INCREASING ENGINE THRUST Mona Phyllis Doemer, Walnut Creek, Calif., assignor to The Dow Chemical Company, Midland, Mich., a corporation of Delaware,
No Drawing. Application-March 21, 1956 Serial'No. 572,805
an engine an improved high energy fuel.
.Several materials have been usedin the pastas high energy fuels for rocket and jet engines. The term high energy fuel refers to fuels which spontaneously ignite and violently burn when mixed with an oxidizing agent such as hydrogen peroxide, nitric acid or nitrogen tetroxide to produce thrust in a rocket, jet or turbo-jet engine. High energy fuels frequently used in such engines include hydrazine, hydrazine hydrate, aniline and aliphatic hydrocarbons. A particular disadvantage of such fuels has been their liquidus properties whereby they freeze at temperatures commonly encountered in missile and jet plane flight. Another disadvantage of many such fuels has been their inability to produce high thrusts due to their unfavorable heats of combustion or undesirable ignition characteristics. A fuel which would be charao terized by a high heat of combustion, low freezing point, short ignition delay and high specific impulse would be of outstanding value in the development of rockets and missiles. It is thus clearly evident that fuels having improved ignition, combustion and liquidus properties would be a distinct advantage to the development of the rocket and jet engine industry.
One object of this invention is to provide a novel method of obtaining thrust from an engine capable of burning a high energy fuel. Another object is to provide an improved method of increasing the thrust of an engine which burns a high energy fuel by supplying to the combustion zone of such an engine a fuel having very desirable liquidus, ignition and combustion properties. Other objects will appear throughout the following description and appended claims.
This new and improved method of providing thrust to an engine which will burn a high energy fuel will be more fully described hereinafter and the novelty thereof will be particularly pointed out and distinctly claimed.
In accordance with the present invention, it has been discovered that thrust may be obtained from an engine capable of burning a high energy fuel by supplying to the combustion zone of such an engine a propynyl compound having the general formula:
HCEC-CHr-IiF-R where R is hydrogen, methyl, ethyl or Z-propynyl and R is amino, methyl or allyl, along with an oxidizer such as nitric acid, nitrogen tetroxide, hydrogen peroxide or oxygen. These propynyl compounds have very desirable overall characteristics such as high heat of combustion, high specific impulse, wide liquidus range and 2 a short ignition delay whereby theyare particularly adapted to be employed as high energy fuels. The compounds are stable liquids in air at normal temperatures and pressures. (2-propynyl) hydrazine andl,1-bis (2-propynyl=)' hydrazine freeze at approximately 60 C. and '-4S C;
and boil at 63 66 C. at 17 millimeters pressure and 6l63 C. at 4 millimeters pressure, respectively. Dimethyl (Z-propynyl) amine and allyl di(Z-propyhyl) amine freeze at approximately .44 C. and -60 C. respectively. The compounds also possess much higher heats of combustion than hydrazine as shown in the table below in which the heat of combustion is expressed in kilocalories per pound:
Heat of Compound: combustion Hydrazine v V 1930 (Z-propynyl) hydrazine 3540 1,1-bis (Z-propynyl) hydrazine 4020 l-methyl-l-(Z-propynyl) hydrazine 3780 1-ethyl-l-(2-propynyl) hydrazine; 3930 Methyl di(2-propynyl)- amine 4440 Dimethyl (Z-propynyl) amine 4330 Allyl di(Z-propynyl) amine 4480 When operating in accordance with the present invention, the propynyl compound and the oxidizing agent are separately metered into the combustion chamber of the engine where combustion and violent burning take place spontaneously. In such operations, it is desirable that the oxidizing agent be introduced into the combustion chamber at a rate and in an amount suificient to efiect substantially complete combustion of the propynyl fuel compound. The rate at which thrust is developed in the engine varies directly with the rate at which the propynyl compound and oxidizing agent are metered into the combustion chamber. The propynyl compound may be supplied to the combustion zone along with other additives such as aniline, substituted anilines or aliphatic hydrocarbons. The thrust developed from the combustion of the fuel is found to be considerably greater when one or more of the propynyl hydrazines or propynyl amines is used as the fuel than when hydrazine is used. Since the thrust developed in an engine is directly proportional to the heat of combustion of the fuel employed, it is evident that an engine burning a propynyl hydrazine or propynyl amine can propel a missile proportionately further or can propel a proportionately greater load than an engine burning a conventional fuel.
The propynyl hydrazine and propynyl amine compounds used as fuels in the method of the present invention to increase engine thrust may be prepared by reacting propargyl bromide or propargyl chloride with hydrazine, methyl hydrazine, ethyl hydrazine, methylamine or allylamine. The reaction is carried out in an inert organic solvent such as a lower alcohol or diethyl ether. The reaction is exothermic and takes place smoothly at l0 to C. with the production of the desired product and the hydrohalide of the hydrazine or amine reagent. Good results are obtained when employing one molecular proportion of propargyl halide with at least two molecular proportions of the hydrazine or amine reagent. Upon completion of the reaction, the desired product may be separated by fractional distillation under reduced pressure.
In accordance with the patent statutes, this invention has been fully and completely described including what is now considered to be one of its best embodiments. However, it will be apparent to those skilled in the art that other variations are possible. Thus, it should be understood that within the scope of the appended claims this invention may be practiced otherwise than as specifically described.
WhatI claim is: 1. In a method of obtaining thrust from an engine adapted for producing thrustupon combustion therein of; a high; energy, fuehwith; an, ;-oxidizer-. which-- -will-: efiecta" hypengolieand spontaneous; cQmbIQSt -OII with th fu l, and;Wl1erein-the;fueL and an amount Ofgllhe oxidizer suflii-xcienL toflefifect substantially: complete combustion ,thereof,
are simultaneously supplied, to:- the com ustion: zone of said; engine thesimprovement which comprisesemployingz as'the highsenergy fueLa-membenofigthe group-iconsisting of; (2 -prOPY-. lYL) hydrazine, 1';1-bis(2-pr opyny1) hydrazine, 1 -methy1-1I-( 2 propyny1): hydrazine,- 1-ethyl-1-(;2-:
4 pound suppliedrtothe. com-bustionzonev is. di.u1ethyl )(2- propynyl) amine.
6. A method according to -claim 1 in which the compound supplied to the combustion zone is allyl di(2- propynyl) amine.
7. A method of increiiinglizthe thrust of an engine capab1e,. of ,burning afihigh energy ,fuel which comprises sutlicirelwto. effecu-substantiaily completes; combustion of the fuel, the high energy fuel bei'ngseleeted' from the group consisting of,.(2- rppynyl),;hydrazine,; 1,lbis (2- propynyl) hydrazinemthifl vlq z-pubiiynyl) hydrazine, l-ethyl-l-(Z-propynyl) hydrazine, methyl di(2-propynyl) amine, dimethy1 (2-propynyl) aniine -and allyl di(2-propynyl) amine, and the oxidizer being selected from the group consisting of nitric acid, nitrogen tetroxide, hydrogem-peroxide and oxygenk a ReferencesaGitediinl theifile" of. this patent: NIIEDLPSTATBs PATENTS"
Claims (1)
1. IN A METHOD OF OBTAINING THRUST FROM AN ENGINE ADAPTED FOR PRODUCING THRUST UPON COMBUSTION THEREIN OF A HIGH ENERGYH FUEL WITH AN OXIDEZER WHICH WILL EFFECT A HYPERGOLIC AND SPONTANEOUS COMBUSTION WITH THE FUEL, AND WHEREIN THE FUEL AND AN AMOUNT OF THE OXIDIZER SUFFICIENT OT EFFECT SUBSTANTIALLY COMPLETE COMBUSTION THEREOF ARE SIMULTANEOUSLY SUPPLIED TO THE COMBUSTION ZONE OF SAID ENGINE, THE IMPORVEMENT WHICH COMPRISES EMPLOYING AS THE HIGH ENERGY FUEL A MEMBER OF THE GROUP CONSISTING OF (2-PROPYNYL) HYDRAZINE, 1,1-BIS(2-PROPYNYL) HYDRAZINE, 1-METHYL-I-(2-PROPYNYL) HYDRAZINE, 1-ETHYL-I-(-PROPYNYL) HYDRAZINE, METHYL DI(2-PROPYNLY)AMINE, DIMETHYL(2-PROPYNL)AMINE AND ALLYL DI(2-PROPYNYL)AMINE.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US572805A US2901886A (en) | 1956-03-21 | 1956-03-21 | Method of increasing engine thrust |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US572805A US2901886A (en) | 1956-03-21 | 1956-03-21 | Method of increasing engine thrust |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US2901886A true US2901886A (en) | 1959-09-01 |
Family
ID=24289423
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US572805A Expired - Lifetime US2901886A (en) | 1956-03-21 | 1956-03-21 | Method of increasing engine thrust |
Country Status (1)
| Country | Link |
|---|---|
| US (1) | US2901886A (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3086356A (en) * | 1959-05-18 | 1963-04-23 | Air Reduction | Hypergolic fuel-oxidizer system |
| US3172912A (en) * | 1965-03-09 | Haloacetylenic amines | ||
| US3211720A (en) * | 1958-08-08 | 1965-10-12 | Bell Aerospace Corp | Hydrazine based solid propellant |
| US3221494A (en) * | 1961-02-13 | 1965-12-07 | North American Aviation Inc | Compositions, processes, and apparatus for the improvement of bi-propellant fuels |
| US3257249A (en) * | 1963-06-06 | 1966-06-21 | Thiokol Chemical Corp | Method of making acetylenic epoxy amino compounds |
| US3257250A (en) * | 1963-06-06 | 1966-06-21 | Thiokol Chemical Corp | Acetylenic epoxy amino compounds and method of making the same |
| US3265730A (en) * | 1959-08-24 | 1966-08-09 | Bell Aerospace Corp | High energy polymeric salts obtained by reacting urea-formaldehyde polymers with a strong inorganic acid |
| US3497343A (en) * | 1964-12-22 | 1970-02-24 | Basf Ag | Method of stunting plant growth with substituted hydrazonium salts |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2573471A (en) * | 1943-05-08 | 1951-10-30 | Aerojet Engineering Corp | Reaction motor operable by liquid propellants and method of operating it |
| US2712496A (en) * | 1948-11-19 | 1955-07-05 | Skolnik Sol | Jet fuel |
-
1956
- 1956-03-21 US US572805A patent/US2901886A/en not_active Expired - Lifetime
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2573471A (en) * | 1943-05-08 | 1951-10-30 | Aerojet Engineering Corp | Reaction motor operable by liquid propellants and method of operating it |
| US2712496A (en) * | 1948-11-19 | 1955-07-05 | Skolnik Sol | Jet fuel |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3172912A (en) * | 1965-03-09 | Haloacetylenic amines | ||
| US3211720A (en) * | 1958-08-08 | 1965-10-12 | Bell Aerospace Corp | Hydrazine based solid propellant |
| US3086356A (en) * | 1959-05-18 | 1963-04-23 | Air Reduction | Hypergolic fuel-oxidizer system |
| US3265730A (en) * | 1959-08-24 | 1966-08-09 | Bell Aerospace Corp | High energy polymeric salts obtained by reacting urea-formaldehyde polymers with a strong inorganic acid |
| US3221494A (en) * | 1961-02-13 | 1965-12-07 | North American Aviation Inc | Compositions, processes, and apparatus for the improvement of bi-propellant fuels |
| US3257249A (en) * | 1963-06-06 | 1966-06-21 | Thiokol Chemical Corp | Method of making acetylenic epoxy amino compounds |
| US3257250A (en) * | 1963-06-06 | 1966-06-21 | Thiokol Chemical Corp | Acetylenic epoxy amino compounds and method of making the same |
| US3497343A (en) * | 1964-12-22 | 1970-02-24 | Basf Ag | Method of stunting plant growth with substituted hydrazonium salts |
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