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

• a solid propellant charge for combined rocket-ram-jet engines contains a combination of compounds capable of yielding upon combustion an extremely high percentage of hydrogen and a high percentage of nitrogen, both calculated on the carbon present, said nitrogen-containing compound having cyanoor hydrazine groups capable of releasing high energy, said combination also including an oxidizer in an amount insutficient for complete combustion.
• the propellant charge has not only an unusually high efiectiveness, but exhibits among others the advantage that during the rocket phase no carbon will be deposited as soot, including other combustible residues.
• the invention also discloses a process for producing the propellant charge.
• the invention relates to solid propellants for combined rocket-ram-jet engines and a process for making the same.
• Such propellants have to satisfy stringent and extreme requirements. This is so because the incomplete combustion of the propellant during the rocket phase should result in the formation of gases that are rich in hydrogen or readily combustible low molecular saturated hydrocarbons and/or nitrogen compounds so that during the subsequent ram-jet operation reactive gases can be generated with the oxygen of the air which insure and yield high effectiveness and large specific output.
• the combustible gases have such a high temperature that combustion will proceed and be maintained smoothly and effectively.
• no carbon or soot should be deposited which could include combustible residues. These would, on the one hand, lower the temperature of the thrust flow during the rocket phase and, on the other hand, they would be incapable of reacting with air oxygen during the ram jet operation.
• a solid propellant charge of the type here contemplated should therefore yield combustible substances, primarily hydrogen, upon combustion or decomposition with the oxygen of the air.
• the solid propellant charges used up to now which are based on polybutadiene, or epoxy resins modified with natural resins based on terpenes, and the like, do not meet the requirements, or only meet them insufiiciently, even when various additives are used, such as ferrocene.
• solid propellant charges of the type described will yield to the energy released during the rocket phase a propellant gas of high effectiveness having the above-mentioned desirable properties, the gas being then completely burned by the oxygen of the air during the ram jet operation and generating a maximum thrust action.
• Ferrocenes nickeloor cobaltocenes, etc., and other plasticizers and catalysts and/or surfactants.
• EXAMPLE 1 About 72 parts of 4-aminodihydrazino-1,2,4-triazolrhodanide About 20 parts of Mg powder About 8 parts of binder About 650 parts of NH ClO About l-5 parts of various additives.
• EXAMPLE 3 About 62 parts of 4-aminodihydrazino -1,2,4-triazolcyanide About 20 parts of Mg powder About '8 parts of binder About 600 parts of NH ClO About 1-'5 parts of various additives.
• EXAMPLE 4 About 75 parts of triaminoguanidinecyanide About 20 parts of dihydrazinodicyanodiimine About 15 parts of binder About 650 parts of NH ClO About 1-5 parts of various additives.
• EXAMPLE 5 About 75 parts of triaminoguanidinecyanide About -25 parts of NaAlH About 8 parts of binder About 650 parts of NH ClO About 1-5 parts of various additives.
• the various additives mentioned in the examples may be known plasticizers, catalysts and hardening agents.
• binders polymers used heretofore in compounding the charges, are satisfactory.
• polybutadienes, epoxy resins, and similar polymers may be used while they are in the viscous or liquid state of prepolymerization.
• the use of the binders is explained more fully in the following example relating to the process of making the propellant charges according to the invention.
• EXAMPLE 6 In preparing the solid propellant charge, the indicated amount of one of the combustible compounds of Examples 1-5 is mixed with the binder which is in a viscous state of prepolymerization. The compound is thoroughly agitated in the binder until a completely homogeneous mixture is obtained. We then add the oxidizer, NH ClO and continue homogenization of the mass. Subsequently, some of the additives of metallic nature or a plasticizer or catalyst may be introduced under nitrogen gas and kneaded into the mass until complete homogenization has occurred.
• the composition is then stored, With or without addition of a hardening agent, at room temperature or slightly elevated temperature for hours.
• a solid propellant charge for combined rocket-ramjet engines comprising, in a small amount of a polymeric binder matrix, a compound selected from the group consisting of 4-aminodihydrazine-1,2,4-triazo1 4-aminodihydrazino-1,2,4-triazolehydrocarbonate 4-aminodihydrazino-1,2,4-triazolecarbonate 4-aminodihydrazino-1,2,4-triazolethiocyanate 4-aminodihydrazino-1,2,4-triazolecyanide triaminoguanidine triaminoguanidinehydrocarbonate triaminoguanidinecarbonate triaminoguanidinehydrorhodanide triaminoguanidinerhodanide triaminoguanidinecyanide and an inorganic oxidizer salt in an amount insufficient for complete combustion.
• triazol or 4-aminodihydrazino-1,2,4-triazolrhodanide about 20 parts by weight of Mg powder about 8 parts by weight of binder about 650 parts by weight of NH ClO and about 1 to 5 parts by weight of various additives such as a copperchromite as catalyst, an amine as hardener and a modified terpene resin as plasticizer.
• triazolcyanide about 25 parts by weight of NaAlH about 7.5 parts by weight of binder about 600 parts by weight of 'NH CIO and about 1 to 5 parts by weight of various additives such as a copperchromite as catalyst, an amine as hardener and a modified terpene resin as plasticizer.
• triazolcyanide about 20 parts by weight of Mg powder about 8 parts by Weight of binder about 600 parts by weight of NH CIO and about 1 to 5 parts by weight of various additives such as a copperchromite as catalyst, an amine as hardener and a modified terpene resin as plasticizer.
• a process for producing a solid propellant charge for combined rocket-ram-jet engines which comprises the steps of incorporating at normal temperature into a viscous prepolymer of a polymeric binder a compound selected from the group consisting of:

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• Chemical & Material Sciences (AREA)
• Organic Chemistry (AREA)
• Catalysts (AREA)
• Organic Low-Molecular-Weight Compounds And Preparation Thereof (AREA)

Applications Claiming Priority (1)

Publications (1)

Family

ID=5684575

Family Applications (1)

Country Status (4)

Cited By (4)

Families Citing this family (4)

• 1968
  • 1968-01-20 DE DE19681646311 patent/DE1646311A1/de active Granted
• 1969
  • 1969-01-16 US US791802*A patent/US3697339A/en not_active Expired - Lifetime
  • 1969-01-20 FR FR6900969A patent/FR2000500A1/fr not_active Withdrawn
  • 1969-01-20 GB GB1252497D patent/GB1252497A/en not_active Expired

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