US3663322A - Hypergolic solid fuels of high storage stability for hybrid rocket engines and process for making the same - Google Patents

Hypergolic solid fuels of high storage stability for hybrid rocket engines and process for making the same Download PDF

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US3663322A
US3663322A US791803*A US3663322DA US3663322A US 3663322 A US3663322 A US 3663322A US 3663322D A US3663322D A US 3663322DA US 3663322 A US3663322 A US 3663322A
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parts
weight
triazole
triaminoguanidine
binder
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US791803*A
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Paula Sarten
Winfried Mair
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Airbus Defence and Space GmbH
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Messerschmitt Bolkow Blohm AG
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    • 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
    • C06B27/00—Compositions containing a metal, boron, silicon, selenium or tellurium or mixtures, intercompounds or hydrides thereof, and hydrocarbons or halogenated hydrocarbons
    • C—CHEMISTRY; METALLURGY
    • C06—EXPLOSIVES; MATCHES
    • C06D—MEANS FOR GENERATING SMOKE OR MIST; GAS-ATTACK COMPOSITIONS; GENERATION OF GAS FOR BLASTING OR PROPULSION (CHEMICAL PART)
    • C06D5/00—Generation of pressure gas, e.g. for blasting cartridges, starting cartridges, rockets
    • C06D5/10—Generation of pressure gas, e.g. for blasting cartridges, starting cartridges, rockets by reaction of solids with liquids

Definitions

  • the present invention relates to hypergolic solid fuels of high storage stability for hybrid rocket engines and to a process of producing the fuels.
  • Hypergolic denotes the capacity of self-ignition upon contact with another chemical
  • the known, presently used solid fuels for hybrid engines consist of polyethylene, polyester, polyurethanes, polyamides and others, which are rendered hypergolic by the addition of metals, hydrides, ferrocene and the like, when contacted with gaseous or liquid oxidizers.
  • gaseous or liquid oxidizer Upon reaction with the second component, the gaseous or liquid oxidizer, the combustion process leads to an undesirable deposition of carbon in the form of soot and/or solid oxidation products and causes surface incrustations, thus leading to a poor performance of the fuel.
  • a desired re-ignition is thus made more difficult, if not impossible, since due to carbonization or incrustation of the binder, a surface layer will result which prevents reignition or will at least make re-ignition unreliable. Moreover, due to the incomplete combustion, part of the combustible substance is entrained unburned by the effluent and deposited together with the soot, whereby the specific efficiency is decreased.
  • lt is also an object to provide a process for producing the solid rocket fuels above mentioned.
  • the solid fuels according to the invention comprise a combination of components which upon reaction with oxygen is capable of releasing an extremely high percentage of hydrogen and a high percentage of high energy nitrogen, both calculated on the carbon present, the nitrogen being present in the form of hydrazine of cyano groups.
  • Solid fuels according to the invention may have the following compositions:
  • binder mostly free of oxygen, basically consisting of hydrocarbon polymers, if de-sired combined with terpene resins and, in some cases, up to 3. 50 parts of additives of the type of powdered metals, e.g. Be, Mg, Al, B, Zr, etc. or hydrides of Li, Na, Be, K, etc. or alanates and boranates of Li, Na, K, Be, etc. or alkyls of Li, Na, K, Be, Al, Mg, Zn, etc. or colloids of Li, Na, K, etc. or a cyano derivative or substances of the type of ferrocenes, nickelo or cobaltocenes, etc., and
  • additives of the type of powdered metals e.g. Be, Mg, Al, B, Zr, etc. or hydrides of Li, Na, Be, K, etc. or alanates and boranates of Li, Na, K, Be, etc. or alkyls of Li, Na
  • Another embodiment of the invention comprises solid fuels of the following compositions:
  • binder based on polybutadiene or epoxy resins modified with, natural resins based on terpenes, if desired also up to 3. 50 parts of additives of the type of powdered metals, e. g. Be, Mg, Al, B, Zr, etc. or hydrides of Li, Na, Be, K, etc. or alanates and boranates of Li, Na, K, Be,etc. or alkyls of Li, Na, K, Be, Al, Mg, Zn, etc. or colloids of Li, Na, K, etc. or ferrocenes, nickeloor cobaltocenes or a cyano derivative of the type of dihydrazinodicyanodimine; finally, if desired,
  • the binder is present in comparatively small amounts.
  • Either the oxygen-free binder of the type indicated above is mixed at normal temperature with the triaminoguanidine and/or a derivative thereof, or the 4-aminodihydrazino-1,2,4- triazole and/or a derivative thereof, and the additives are admixed last; or,
  • triaminoguanidine and its derivatives or 4- aminodihydrazino-l,2,4-triazole and its derivatives are first mixed with the additives and the binder is added last; or,
  • the binder may first be mixed with the additives, and the triaminoguanidine or its salts, or the 4-aminodihydrazino- 1,2,4-triazole or its salts are added last.
  • EXAMPLE 2 About 67.5 parts of triaminoguanidine cyanide About 20 parts of Mg powder About 7.5 parts of binder About 1-2 parts of various additives (in the nature plasticizers, catalysts, hardeners).
  • EXAMPLE 3 About 10 parts of 4-aminodihydrazino-l ,2,4-triazole About 50 parts of triaminoguanidine cyanide About 20 parts of dihydrazinodicyanodiimine About 10 parts of binder About 1-2 parts of various additives (in the nature plasticizers, catalysts, hardeners).
  • EXAMPLE 4 About 70 parts of 4-aminodihydrazino-l ,2,4-triazole About 20 parts of Na colloid About 10 parts of binder About l-2 parts of various additives (in the nature plasticizers, catalysts, hardeners). EXAMPLE About 70 parts of 4-aminodihydrazino-l,2,4-triazole thiocyanate About 25 parts of NaAll-I,
  • EXAMPLE 7 About 40 parts of 4-aminodihydrazino-l,2,4-triazole About 50 parts of triaminoguanidine cyanide About 20 parts of dihydrazinodicyanodiimine About 20 parts of NaAll-l,
  • binder About 15 parts of binder about 1-2 parts of various additives (in the nature of plasticizers, catalysts, hardeners).
  • oxidizers we may use gaseous or liquid substances of the type of fluorine derivatives, such as ClF ClF and others, liquid oxygen, etc., H N 0 preferably however HNO WFNA (white fuming nitric acid), RFNA (red fuming nitric acid plus 1 percent HF) or perchloric acid which will react hypergolically with the mentioned fuels and make re-ignition possible.
  • HNO WFNA white fuming nitric acid
  • RFNA red fuming nitric acid plus 1 percent HF
  • perchloric acid which will react hypergolically with the mentioned fuels and make re-ignition possible.
  • the solid fuels according to the invention burn with a flame which becomes extinguished when the engine is cut off, without causing incrustations or soot deposition and without the risk of explosion.
  • a flame which becomes extinguished when the engine is cut off, without causing incrustations or soot deposition and without the risk of explosion.
  • the fuels according to the invention are distinguished by an extremely high amount of hydrogen and a high amount of nitrogen in the form of hydrazineor cyano groups, calculated on carbon.
  • the mentioned substances generate a high combustion temperature and due to their high energy cause a considerably increased rate of reaction and therewith increased rate of propulsion.
  • a hypergolic solid propellant charge of high storage stability for hybrid rocket engines comprising about 8-l5 percent of substantially oxygen free binder comprising polyhydrocarbons and a major amount of a compound selected from the group consisting of 4-aminodihydrazinel ,2,4-triazole 4-aminodihydrazinol ,2,4-triazole acid carbonate 4-aminodihydrazinol ,2,4triazole carbonate 4-aminodihydrazino 1,2,4-tiazole thiocyanate 4-aminodihydrazino-l ,2,4-tiazole cyanide triaminoguanidine triaminoguanidine acid carbonate triaminoguanidine carbonate triaminoguanidine thiocyanate triaminoguanidine cyanide.
  • the propellant charge according to claim 1 further comprising dihydrazinodicyanodiimine.
  • Solid fuel according to claim 1 comprising About 25 parts by weight of 4-aminodihydrazino-l ,2,4-
  • triazole about 40 parts by weight of triaminoguanidine thiocyanate about 25 parts by weight of NaAlI-l, and about 8 parts by weight of said binder.
  • Solid fuel according to claim 1 comprising about 67.5 parts by weight of triaminoguanidine cyanide about parts by weight of Mg powder and about 7.5 parts by weight of said binder.
  • Solid fuel according to claim 1 comprising about 10 parts by weight of 4-aminodihydrazinol ,2,4 triazole about 50 parts by weight of triaminoguanidine cyanide about 20 parts by weight of dihydrazinodicyanodiimine and about 10 parts by weight of said binder.
  • Solid fuel according to claim 1 comprising about 70 parts by weight of 4-aminodihydrazino-l ,2,4-triazole thiocyanate about 20 parts by weight of Na colloid and about 10 parts by weight of said binder.
  • Solid fuel according to claim 1 comprising about 70 parts by weight of 4-aminodihydrazinol ,2,4-
  • Solid fuel according to claim 1 comprising about parts by weight of 4-aminodihydrazinol ,2,4-
  • triazole about 30 parts by weight of triaminoguanidine cyanide about 20 parts by weight of dihydrazinodicyanodiimine about 20 parts by weight of NaAll-l and about 8 parts by weight of said binder.
  • Solid fuel according to claim 1 comprising about parts by weight of 4-aminodihydrazinol ,2,4-
  • triazole about parts by weight of triaminoguanidine cyanide about 20 parts by weight of dihydrazinodicyanodiimine about 20 parts by weight of NaAlI-l, and about 15 parts by weight of said binder.
  • a process for producing a hypergolic propellant charge for hybrid rocket engines which comprises the steps of incorporating at normal temperature into a viscous prepolymer of a substantially oxygenfree binder comprising polyhydrocarbon a compound selected from the group consisting of 4-aminodihydrazine-l ,2 ,4-triazole 4-aminodihydrazinol ,2,4-triazole acid carbonate 4-aminodihydrazino-1,2,4-triazole carbonate 4-aminodihydrazino-l ,2,4-triazole thiocyanate 4-aminodihydrazini-1,2,4-triazole cyanide triaminoguanidine triaminoguanidine acid carbonate triaminoguanidine acid carbonate triaminoguanidine thiocyanate triaminoguanidine cyanide mixing the said binder and said compound, while excluding oxygen, adding further high energy releasing compounds, and further admixing additives of the nature of

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  • Chemical & Material Sciences (AREA)
  • Organic Chemistry (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Engineering & Computer Science (AREA)
  • Combustion & Propulsion (AREA)
  • Liquid Carbonaceous Fuels (AREA)
  • Solid Fuels And Fuel-Associated Substances (AREA)

Abstract

A hypergolic solid fuel of high storage stability for hybrid rocket engines, comprising incorporated in a small amount of a binder a combination of compounds extremely rich in hydrogen and rich in nitrogen as compared to the contents in carbon, said nitrogen being in the form of cyano- or hydrazine groups and capable of releasing high energy upon contact with an oxidizer. The invention also relates to a process for making the fuels.

Description

States atem Sarten et a1.
[451 May 16, 1972 HYPERGOLIC SOLID FUELS OF HIGH STORAGE STABILITY F OR HYBRID ROCKET ENGINES AND PROCESS FOR MAKING THE SAME Inventors: Paula Sarten, Munich; Winfried Mair,
Riemerling, both of Germany Assignee: Messerschmitt-Bolkow, Gesellschaft mit beschrankter Haftung, Ottobrunn near- Munich Germany Filed: Jan. 16, 1969 Appl No.: 791,803
Foreign Application Priority Data Jan. 20, 1968 Germany ..P 16 46 310.8
U.S. Cl ..149/19, 149/36, 149/87, 149/20, 260/308 R, 60/219 Int. Cl. ..C06d 5/10 Field of Search ..l49/36, 87, 19, 20; 260/308 R; 60/219 [56] References Cited UNITED STATES PATENTS 3,338,762 8/1967 Oja ..l49/l9 3,398,215 8/1968 Spenadel et a1. 3,403,062 9/1968 Ponnell et a1. 3,499,289 3/1970 Olsen ..60/218 Primary ExaminerCarl D. Quarforth Assistant Examiner-E. A. Miller AttorneyMcGlew and Toren 57 ABSTRACT 11 Claims, No Drawings I'IYPERGOLIC SOLID FUELS OF HIGH STORAGE STABILITY FOR HYBRID ROCKET ENGINES AND PROCESS FOR MAKING THE SAME SUMMARY OF THE INVENTION The present invention relates to hypergolic solid fuels of high storage stability for hybrid rocket engines and to a process of producing the fuels.
Hypergolic denotes the capacity of self-ignition upon contact with another chemical,
The known, presently used solid fuels for hybrid engines consist of polyethylene, polyester, polyurethanes, polyamides and others, which are rendered hypergolic by the addition of metals, hydrides, ferrocene and the like, when contacted with gaseous or liquid oxidizers. Upon reaction with the second component, the gaseous or liquid oxidizer, the combustion process leads to an undesirable deposition of carbon in the form of soot and/or solid oxidation products and causes surface incrustations, thus leading to a poor performance of the fuel. Moreover, a desired re-ignition is thus made more difficult, if not impossible, since due to carbonization or incrustation of the binder, a surface layer will result which prevents reignition or will at least make re-ignition unreliable. Moreover, due to the incomplete combustion, part of the combustible substance is entrained unburned by the effluent and deposited together with the soot, whereby the specific efficiency is decreased.
Attempts have been made to overcome these difficulties by addition of moderate amounts of oxidizers or by incorporation to nitro groups into the fuel, thereby enhancing combustion and, sometimes, facilitating reignition. However, by these additions and by the introduction of nitro groups, the stability of such solid fuels during storage is considerably impaired; furthermore, by incorporation of high energy substances, the chemical stability of the fuel may be endangered.
It is the object of the present invention to overcome the existing shortcomings of known solid rocket fuels for hybrid rocket engines.
It is another object of the invention to provide solid rocket fuels for hybrid engines which will ensure re-ignition of the fuels after each combustion and which, moreover, are of higher energy that will be utilized to the highest degree.
It is yet another object to provide solid rocket fuels which will be very stable during storage and handling.
lt is also an object to provide a process for producing the solid rocket fuels above mentioned.
Other objects and advantages of the invention will become apparent from the detailed description hereinbelow.
The solid fuels according to the invention comprise a combination of components which upon reaction with oxygen is capable of releasing an extremely high percentage of hydrogen and a high percentage of high energy nitrogen, both calculated on the carbon present, the nitrogen being present in the form of hydrazine of cyano groups.
Solid fuels according to the invention may have the following compositions:
All parts are by weight.
1. 20-90 parts of 4-aminodihydrazino-l ,2,4-triazole, as well as the acid, neutral and basic carbonate of 4- aminodihydrazino-l,2,4-triazole, also the neutral and basic thiocyanate of 4-aminodihydrazino-l ,2,4-triazole, primarily the neutral and basic cyanide of 4-amino-dihydrazino-l,2,4- triazole;
moreover:
2. 5 parts of binder, mostly free of oxygen, basically consisting of hydrocarbon polymers, if de-sired combined with terpene resins and, in some cases, up to 3. 50 parts of additives of the type of powdered metals, e.g. Be, Mg, Al, B, Zr, etc. or hydrides of Li, Na, Be, K, etc. or alanates and boranates of Li, Na, K, Be, etc. or alkyls of Li, Na, K, Be, Al, Mg, Zn, etc. or colloids of Li, Na, K, etc. or a cyano derivative or substances of the type of ferrocenes, nickelo or cobaltocenes, etc., and
min
4. 0. l 10 parts of other additives of the type of plasticizers, catalysts and/ or surfactants. Another embodiment of the invention comprises solid fuels of the following compositions:
1. l0 parts of triaminoguanidine, as well as the acid, neutral and basic carbonate of triaminoguanidine, also the neutral and basic thiocyanate of triaminoguanidine, primarily the neutral and basic cyanide of triaminoguanidine, furthermore:
2. 5 20 parts of binder, based on polybutadiene or epoxy resins modified with, natural resins based on terpenes, if desired also up to 3. 50 parts of additives of the type of powdered metals, e. g. Be, Mg, Al, B, Zr, etc. or hydrides of Li, Na, Be, K, etc. or alanates and boranates of Li, Na, K, Be,etc. or alkyls of Li, Na, K, Be, Al, Mg, Zn, etc. or colloids of Li, Na, K, etc. or ferrocenes, nickeloor cobaltocenes or a cyano derivative of the type of dihydrazinodicyanodiimine; finally, if desired,
4. 0.1 10 parts of other additives of the type of a plasticizer, catalyst and/or surfactant.
It should be noted that the binder is present in comparatively small amounts.
In the preparation of the solid fuels according to the invention, we may proceed in different ways.
Either the oxygen-free binder of the type indicated above is mixed at normal temperature with the triaminoguanidine and/or a derivative thereof, or the 4-aminodihydrazino-1,2,4- triazole and/or a derivative thereof, and the additives are admixed last; or,
triaminoguanidine and its derivatives or 4- aminodihydrazino-l,2,4-triazole and its derivatives are first mixed with the additives and the binder is added last; or,
the binder may first be mixed with the additives, and the triaminoguanidine or its salts, or the 4-aminodihydrazino- 1,2,4-triazole or its salts are added last.
Other additives of the type of copper chromite, plasticizer and surfactant are finally added.
In the following, the invention will be more fully described by a number of examples which are given by way of illustration, but not of limitation. Parts are by weight.
EXAMPLE 1 About 25 parts of 4-aminodihydrazino-l ,2,4-triazo1e about 40 parts of triaminoguanidine or triaminoguanidine thiocyanate About 25 parts of NaAlH,
About 8 parts of binder About 1-2 parts of various additives (in the nature plasticizers, catalysts, hardeners). EXAMPLE 2 About 67.5 parts of triaminoguanidine cyanide About 20 parts of Mg powder About 7.5 parts of binder About 1-2 parts of various additives (in the nature plasticizers, catalysts, hardeners). EXAMPLE 3 About 10 parts of 4-aminodihydrazino-l ,2,4-triazole About 50 parts of triaminoguanidine cyanide About 20 parts of dihydrazinodicyanodiimine About 10 parts of binder About 1-2 parts of various additives (in the nature plasticizers, catalysts, hardeners). EXAMPLE 4 About 70 parts of 4-aminodihydrazino-l ,2,4-triazole About 20 parts of Na colloid About 10 parts of binder About l-2 parts of various additives (in the nature plasticizers, catalysts, hardeners). EXAMPLE About 70 parts of 4-aminodihydrazino-l,2,4-triazole thiocyanate About 25 parts of NaAll-I,
About 8 parts of binder About l2 parts of various additives (in the nature of plasticizers, catalysts, hardeners). EXAMPLE 6 About 30 parts of 4-aminodihydrazino-l,2,4-triazole cyanide About 30 parts of triaminoguanidine cyanide About 20 parts of dihydrazinodicyanidediimine About 20 parts of NaAlH About 8 parts of binder About l-2 parts of various additives (in the nature of plasticizers, catalysts, hardeners). EXAMPLE 7 About 40 parts of 4-aminodihydrazino-l,2,4-triazole About 50 parts of triaminoguanidine cyanide About 20 parts of dihydrazinodicyanodiimine About 20 parts of NaAll-l,
About 15 parts of binder About 1-2 parts of various additives (in the nature of plasticizers, catalysts, hardeners).
As oxidizers we may use gaseous or liquid substances of the type of fluorine derivatives, such as ClF ClF and others, liquid oxygen, etc., H N 0 preferably however HNO WFNA (white fuming nitric acid), RFNA (red fuming nitric acid plus 1 percent HF) or perchloric acid which will react hypergolically with the mentioned fuels and make re-ignition possible.
The solid fuels according to the invention burn with a flame which becomes extinguished when the engine is cut off, without causing incrustations or soot deposition and without the risk of explosion. Thus, upon restarting the engine, i.e. upon renewed addition of the oxidizer, dependable re-ignition is guaranteed.
As compared to known rocket fuels, the fuels according to the invention are distinguished by an extremely high amount of hydrogen and a high amount of nitrogen in the form of hydrazineor cyano groups, calculated on carbon. The mentioned substances generate a high combustion temperature and due to their high energy cause a considerably increased rate of reaction and therewith increased rate of propulsion.
What is claimed is:
1. A hypergolic solid propellant charge of high storage stability for hybrid rocket engines, comprising about 8-l5 percent of substantially oxygen free binder comprising polyhydrocarbons and a major amount of a compound selected from the group consisting of 4-aminodihydrazinel ,2,4-triazole 4-aminodihydrazinol ,2,4-triazole acid carbonate 4-aminodihydrazinol ,2,4triazole carbonate 4-aminodihydrazino 1,2,4-tiazole thiocyanate 4-aminodihydrazino-l ,2,4-tiazole cyanide triaminoguanidine triaminoguanidine acid carbonate triaminoguanidine carbonate triaminoguanidine thiocyanate triaminoguanidine cyanide.
2. The propellant charge according to claim 1 further comprising dihydrazinodicyanodiimine.
3. The propellant charge according to claim 1, wherein the binder is admixed with natural resins based on terpenes.
4. Solid fuel according to claim 1, comprising About 25 parts by weight of 4-aminodihydrazino-l ,2,4-
mun
triazole about 40 parts by weight of triaminoguanidine thiocyanate about 25 parts by weight of NaAlI-l, and about 8 parts by weight of said binder. 5. Solid fuel according to claim 1, comprising about 67.5 parts by weight of triaminoguanidine cyanide about parts by weight of Mg powder and about 7.5 parts by weight of said binder. 6. Solid fuel according to claim 1, comprising about 10 parts by weight of 4-aminodihydrazinol ,2,4 triazole about 50 parts by weight of triaminoguanidine cyanide about 20 parts by weight of dihydrazinodicyanodiimine and about 10 parts by weight of said binder. 7. Solid fuel according to claim 1, comprising about 70 parts by weight of 4-aminodihydrazino-l ,2,4-triazole thiocyanate about 20 parts by weight of Na colloid and about 10 parts by weight of said binder.
8. Solid fuel according to claim 1, comprising about 70 parts by weight of 4-aminodihydrazinol ,2,4-
triazole cyanide about parts by weight of NaAlH, and
about 8 parts by weight of said binder.
9. Solid fuel according to claim 1, comprising about parts by weight of 4-aminodihydrazinol ,2,4-
triazole about 30 parts by weight of triaminoguanidine cyanide about 20 parts by weight of dihydrazinodicyanodiimine about 20 parts by weight of NaAll-l and about 8 parts by weight of said binder.
10 Solid fuel according to claim 1, comprising about parts by weight of 4-aminodihydrazinol ,2,4-
triazole about parts by weight of triaminoguanidine cyanide about 20 parts by weight of dihydrazinodicyanodiimine about 20 parts by weight of NaAlI-l, and about 15 parts by weight of said binder.
11. A process for producing a hypergolic propellant charge for hybrid rocket engines, which comprises the steps of incorporating at normal temperature into a viscous prepolymer of a substantially oxygenfree binder comprising polyhydrocarbon a compound selected from the group consisting of 4-aminodihydrazine-l ,2 ,4-triazole 4-aminodihydrazinol ,2,4-triazole acid carbonate 4-aminodihydrazino-1,2,4-triazole carbonate 4-aminodihydrazino-l ,2,4-triazole thiocyanate 4-aminodihydrazini-1,2,4-triazole cyanide triaminoguanidine triaminoguanidine acid carbonate triaminoguanidine acid carbonate triaminoguanidine thiocyanate triaminoguanidine cyanide mixing the said binder and said compound, while excluding oxygen, adding further high energy releasing compounds, and further admixing additives of the nature of a catalyst and a plasticizer, completely mixing the entire mixture, and finally causing hardening of the so prepared propellant.

Claims (9)

  1. 2. The propellant charge according to claim 1 further comprising dihydrazinodicyanodiimine.
  2. 3. The propellant charge according to claim 1, wherein the binder is admixed with natural resins based on terpenes.
  3. 4. Solid fuel according to claim 1, comprising About 25 parts by weight of 4-aminodihydrazino-1,2,4-triazole about 40 parts by weight of triaminoguanidine thiocyanate about 25 parts by weiGht of NaAlH4 and about 8 parts by weight of said binder.
  4. 5. Solid fuel according to claim 1, comprising about 67.5 parts by weight of triaminoguanidine cyanide about 20 parts by weight of Mg powder and about 7.5 parts by weight of said binder.
  5. 6. Solid fuel according to claim 1, comprising about 10 parts by weight of 4-aminodihydrazino-1,2,4-triazole about 50 parts by weight of triaminoguanidine cyanide about 20 parts by weight of dihydrazinodicyanodiimine and about 10 parts by weight of said binder.
  6. 7. Solid fuel according to claim 1, comprising about 70 parts by weight of 4-aminodihydrazino-1,2,4-triazole thiocyanate about 20 parts by weight of Na colloid and about 10 parts by weight of said binder.
  7. 8. Solid fuel according to claim 1, comprising about 70 parts by weight of 4-aminodihydrazino-1,2,4-triazole cyanide about 25 parts by weight of NaAlH4 and about 8 parts by weight of said binder.
  8. 9. Solid fuel according to claim 1, comprising about 30 parts by weight of 4-aminodihydrazino-1,2,4-triazole about 30 parts by weight of triaminoguanidine cyanide about 20 parts by weight of dihydrazinodicyanodiimine about 20 parts by weight of NaAlH4 and about 8 parts by weight of said binder. 10 Solid fuel according to claim 1, comprising about 40 parts by weight of 4-aminodihydrazino-1,2,4-triazole about 50 parts by weight of triaminoguanidine cyanide about 20 parts by weight of dihydrazinodicyanodiimine about 20 parts by weight of NaAlH4 and about 15 parts by weight of said binder.
  9. 11. A process for producing a hypergolic propellant charge for hybrid rocket engines, which comprises the steps of incorporating at normal temperature into a viscous prepolymer of a substantially oxygenfree binder comprising polyhydrocarbon a compound selected from the group consisting of 4-aminodihydrazine-1,2,4-triazole 4-aminodihydrazino-1,2,4-triazole acid carbonate 4-aminodihydrazino-1,2,4-triazole carbonate 4-aminodihydrazino-1,2,4-triazole thiocyanate 4-aminodihydrazini-1,2,4-triazole cyanide triaminoguanidine triaminoguanidine acid carbonate triaminoguanidine acid carbonate triaminoguanidine thiocyanate triaminoguanidine cyanide mixing the said binder and said compound, while excluding oxygen, adding further high energy releasing compounds, and further admixing additives of the nature of a catalyst and a plasticizer, completely mixing the entire mixture, and finally causing hardening of the so prepared propellant.
US791803*A 1968-01-20 1969-01-16 Hypergolic solid fuels of high storage stability for hybrid rocket engines and process for making the same Expired - Lifetime US3663322A (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4065332A (en) * 1972-12-19 1977-12-27 Societe Nationale Des Poudres Et Explosifs Hybrid propellant compositions

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US3398215A (en) * 1961-04-19 1968-08-20 Exxon Research Engineering Co Method for making rocket propellant
US3403062A (en) * 1965-11-30 1968-09-24 Dow Chemical Co Plastisol binder composition for rocket propellants containing azide and hydrazine compounds
US3499289A (en) * 1961-05-02 1970-03-10 Exxon Research Engineering Co Monopropellant in binder matrix

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US3398215A (en) * 1961-04-19 1968-08-20 Exxon Research Engineering Co Method for making rocket propellant
US3499289A (en) * 1961-05-02 1970-03-10 Exxon Research Engineering Co Monopropellant in binder matrix
US3338762A (en) * 1962-01-24 1967-08-29 Dow Chemical Co Solid propellant composition with boron containing fuel and nitrogen containing oxidizers
US3403062A (en) * 1965-11-30 1968-09-24 Dow Chemical Co Plastisol binder composition for rocket propellants containing azide and hydrazine compounds

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4065332A (en) * 1972-12-19 1977-12-27 Societe Nationale Des Poudres Et Explosifs Hybrid propellant compositions

Also Published As

Publication number Publication date
GB1259824A (en) 1972-01-12
FR2000499A1 (en) 1969-09-05

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