EP0365809A2 - Propergols solides pour missiles - Google Patents

Propergols solides pour missiles Download PDF

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Publication number
EP0365809A2
EP0365809A2 EP89116826A EP89116826A EP0365809A2 EP 0365809 A2 EP0365809 A2 EP 0365809A2 EP 89116826 A EP89116826 A EP 89116826A EP 89116826 A EP89116826 A EP 89116826A EP 0365809 A2 EP0365809 A2 EP 0365809A2
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EP
European Patent Office
Prior art keywords
weight
polymers
rocket
plasticizers
compounds
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.)
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Application number
EP89116826A
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German (de)
English (en)
Other versions
EP0365809A3 (fr
Inventor
Siegfried Chemie-Ing. Eisele (Grad)
Klaus Dr. Dipl.-Chem. Menke
Hiltmar Dr.-Dipl.-Chem. Schubert
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Fraunhofer Gesellschaft zur Foerderung der Angewandten Forschung eV
Original Assignee
Fraunhofer Gesellschaft zur Foerderung der Angewandten Forschung eV
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Fraunhofer Gesellschaft zur Foerderung der Angewandten Forschung eV filed Critical Fraunhofer Gesellschaft zur Foerderung der Angewandten Forschung eV
Publication of EP0365809A2 publication Critical patent/EP0365809A2/fr
Publication of EP0365809A3 publication Critical patent/EP0365809A3/fr
Withdrawn legal-status Critical Current

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    • C—CHEMISTRY; METALLURGY
    • C06—EXPLOSIVES; MATCHES
    • C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
    • C06B25/00—Compositions containing a nitrated organic compound
    • C06B25/34—Compositions containing a nitrated organic compound the compound being a nitrated acyclic, alicyclic or heterocyclic amine
    • C—CHEMISTRY; METALLURGY
    • C06—EXPLOSIVES; MATCHES
    • C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
    • C06B45/00—Compositions or products which are defined by structure or arrangement of component of product
    • C06B45/04—Compositions or products which are defined by structure or arrangement of component of product comprising solid particles dispersed in solid solution or matrix not used for explosives where the matrix consists essentially of nitrated carbohydrates or a low molecular organic explosive
    • C06B45/06—Compositions or products which are defined by structure or arrangement of component of product comprising solid particles dispersed in solid solution or matrix not used for explosives where the matrix consists essentially of nitrated carbohydrates or a low molecular organic explosive the solid solution or matrix containing an organic component
    • C06B45/10—Compositions or products which are defined by structure or arrangement of component of product comprising solid particles dispersed in solid solution or matrix not used for explosives where the matrix consists essentially of nitrated carbohydrates or a low molecular organic explosive the solid solution or matrix containing an organic component the organic component containing a resin
    • C06B45/105—The resin being a polymer bearing energetic groups or containing a soluble organic explosive

Definitions

  • the composite fuels based on ammonium perchlorate (AP) / aluminum (Al) used today as solid propellants for rockets have high performance, good processability, good mechanical properties and, in practice, a flexible combustion behavior.
  • the above types of fuel have a strong primary or secondary signature due to Al2O3 or HC1 in the exhaust gas.
  • the signature is a serious disadvantage for practical use on carrier- and field-bound weapon systems, since launch ramps and launch sites can be easily located using a smoke trail that is visible from afar.
  • Another disadvantage is the corrosive effect of the exhaust gases.
  • DB fuels are relatively low in signatures, but have only low performance and unsatisfactory mechanical properties (thermoplastics).
  • Energetic plasticizers e.g. nitroclycerin (NG), butanetriol trinitrate (BTTN), trimethylolethane trinitrate (TMETN), diethylene glycol dinitrate (DEGDN), bis-dinitropropyl formal / acetal (BDNPF / A) and others
  • Inert binder systems eg polyester polyurethane elastomers, polyether polyurethane elastomers, polybutadiene polyurethane elastomers and others
  • a reduction in the pressure exponent was found for DB fuels with nitramine contents below 50% and inert polyurethane binders as well as with the addition of heavy metal salts and soot.
  • the burning rate remains at low values.
  • the spectrum of properties is so unfavorable overall that these fuels have not found any practical use.
  • Burn-moderating additives showed no significant influence on the pressure exponent when using inert binder systems.
  • binder systems containing azide groups instead of inert binder systems (for example polyester polyurethanes) which lead to an increase in performance.
  • These binders have a polyether or polyester-like chain structure that contain high-energy azide groups in the side chain.
  • a glycidyl azidodiol with the following structural unit can be mentioned as an example of a binder containing azide groups: which can be cured with di- or triisocyanates (e.g. hexamethylene diisocyanate) to form elastomers (GAP).
  • di- or triisocyanates e.g. hexamethylene diisocyanate
  • the object of the present invention is to propose high-performance solid fuels with positive combustion behavior.
  • a fuel consisting of high-energy nitramine compounds in proportions of 50-90% by weight, an energetic binder system containing azide groups consisting of polymers and plasticizers in proportions of 8-50% by weight and heavy metal catalysts in the form of lead and tin - or copper compounds in concentrations of 0.5-10% by weight.
  • the fuels according to the invention preferably consist of 60-85% by weight of solid high-energy nitramine compounds which do not have any corrosive effects on decomposition Form gases and cause smokeless or low-smoke combustion in the fuel, i.e. show no or only minimal signature.
  • binders containing azide groups and preferably 1 to 5% by weight of heavy metal catalysts there is a significant reduction in the pressure exponent (n ⁇ 0.6).
  • High energy nitramine compounds such as octogen, hexogen, nitroguanidine, tetryl and others are preferably used. used.
  • the binders containing azide groups used in the fuel system according to the invention can vary in the range of 8% by weight, preferably 15-40% by weight, the binder itself being 0 - max. Contains 80% by weight, preferably 30-70% by weight, of plasticizers.
  • plasticizers In connection with azido polymers, all organic nitric acid esters or nitro compounds conventionally used in fuels can be used as energetic plasticizers. Nitroglycerin, butanetriol trinitrate, trimethylolethane trinitrate, diethylene glycol dinitrate or bis-dinitropropyl formal / acetal are preferably used as less sensitive plasticizers.
  • inert plasticizers such as alkyl acetates, preferably triacetin and / or phosphoric acid, phthalic, adipic or citric acid esters, preferably dibutyl, di-2-ethyhexyl and dioctyl phthalate, dimethyl and dibutyl glycol phthalate, can additionally be used -2-ethylhexyl and diisooctyl adipate can be used.
  • Curing to an azido polymer with high elasticity and extensibility is preferably carried out using trimeric isocyanates such as, for example, biuret trihexan diisocyanate or a combination of dimeric and trimeric isocyanates, hexamethylene diisocyanate and 2,4-toluene diisocyanate and isophorone diisocyanate are preferably used as dimeric isocyanates.
  • trimeric isocyanates such as, for example, biuret trihexan diisocyanate or a combination of dimeric and trimeric isocyanates, hexamethylene diisocyanate and 2,4-toluene diisocyanate and isophorone diisocyanate are preferably used as dimeric isocyanates.
  • the equivalent ratios can be varied between 0.4 and 1.2 NCO / OH proportions depending on the solids content.
  • Pb, Sn or Cu compounds used as catalysts are preferably used in the form of oxides, organic salts (salicylates, stearates, citrates, resorcylates etc.) or inorganic salts, but complex compounds are also suitable.
  • a further reduction in the pressure exponent can be achieved by adding small amounts of carbon or substances which supply carbon during combustion.
  • Carbon black, activated carbon, carbon fibers or graphite are preferably used, the proportion of which is between 0.2 and 3% by weight, preferably between 0.5 and 1% by weight.
  • the rocket solid propellants formulated in accordance with the invention can be used in all civil and military, rocket-based systems. They are particularly important in the case of military battlefield systems such as artillery, tank, and aircraft anti-aircraft or anti-ship missiles. Since, in contrast to AP composite fuels, no corrosive gases are generated, operating personnel and the launching system are not exposed to any stress.
  • the fuels formulated according to the invention show a property profile that is not achieved by any previous solid fuel type: - Higher performance than double base fuels - Pressure exponent n ⁇ 0.6 - Burning rate at 100 bar r100> 9 mm / s - better chemical stability than double base fuels - viscoelastic mechanical properties - Significantly reduced primary and secondary signature with almost smokeless burning, without the addition of metallic fuels, - no corrosive exhaust gases
  • column 1 shows a conventional solid propellant and compound according to the invention in columns 2 and 3 with their properties which are relevant for the use.
  • the high burning rate and the very low pressure exponent of the fuels according to the invention are striking.

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  • Chemical & Material Sciences (AREA)
  • Organic Chemistry (AREA)
  • Health & Medical Sciences (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Dispersion Chemistry (AREA)
  • Molecular Biology (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Solid Fuels And Fuel-Associated Substances (AREA)
  • Compositions Of Macromolecular Compounds (AREA)
  • Medicinal Preparation (AREA)
  • Cosmetics (AREA)
EP89116826A 1988-10-21 1989-09-12 Propergols solides pour missiles Withdrawn EP0365809A3 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3835854A DE3835854A1 (de) 1988-10-21 1988-10-21 Raketenfesttreibstoffe
DE3835854 1988-10-21

Publications (2)

Publication Number Publication Date
EP0365809A2 true EP0365809A2 (fr) 1990-05-02
EP0365809A3 EP0365809A3 (fr) 1990-05-16

Family

ID=6365605

Family Applications (1)

Application Number Title Priority Date Filing Date
EP89116826A Withdrawn EP0365809A3 (fr) 1988-10-21 1989-09-12 Propergols solides pour missiles

Country Status (5)

Country Link
US (1) US4938813A (fr)
EP (1) EP0365809A3 (fr)
JP (1) JPH02157177A (fr)
DE (1) DE3835854A1 (fr)
NO (1) NO894163L (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0679618A1 (fr) * 1994-04-30 1995-11-02 Fraunhofer-Gesellschaft Zur Förderung Der Angewandten Forschung E.V. Charge pyrotechnique pour la libération d'un gaz stocké dans un réservoir sous pression
EP0968983A4 (fr) * 1997-11-26 2000-09-27 Asahi Chemical Ind Composition d' hexanitrohexaazaisowurtzitane et composition explosive la contenant
WO2012028288A3 (fr) * 2010-09-03 2012-06-07 Rheinmetall Waffe Munition Gmbh Formulation d'explosif à liant plastique

Families Citing this family (28)

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Publication number Priority date Publication date Assignee Title
CA2053832C (fr) * 1990-12-11 1999-09-07 Edward H. Zeigler Plastifiants stables pour compositions de type nitrocellulose/nitroguanidine
US5154782A (en) * 1991-08-15 1992-10-13 Thiokol Corporation Obscuring and nontoxic smoke compositions
FR2688498B1 (fr) * 1992-03-11 1994-05-06 Poudres Explosifs Ste Nale Poudre propulsive a faible vulnerabilite sensible a l'allumage.
US5316600A (en) * 1992-09-18 1994-05-31 The United States Of America As Represented By The Secretary Of The Navy Energetic binder explosive
US5942720A (en) * 1993-04-29 1999-08-24 Cordant Technologies Inc. Processing and curing aid for composite propellants
US5695216A (en) * 1993-09-28 1997-12-09 Bofors Explosives Ab Airbag device and propellant for airbags
US5470408A (en) * 1993-10-22 1995-11-28 Thiokol Corporation Use of carbon fibrils to enhance burn rate of pyrotechnics and gas generants
US6364975B1 (en) 1994-01-19 2002-04-02 Universal Propulsion Co., Inc. Ammonium nitrate propellants
US5583315A (en) * 1994-01-19 1996-12-10 Universal Propulsion Company, Inc. Ammonium nitrate propellants
US5602361A (en) * 1994-03-18 1997-02-11 Oea, Inc. Hybrid inflator
DE69523499T2 (de) * 1994-03-18 2002-09-12 Autoliv Asp, Ogden Hybride Aufblasvorrichtung mit auf schneller Druckbeaufschlagung gegründeter Strömungseinleitungsvorrichtung
US5538567A (en) * 1994-03-18 1996-07-23 Olin Corporation Gas generating propellant
US5788275A (en) 1994-03-18 1998-08-04 Oea, Inc. Hybrid inflator
US5553889A (en) * 1994-03-18 1996-09-10 Oea, Inc. Hybrid inflator with rapid pressurization-based flow initiation assembly
US5711546A (en) * 1994-03-18 1998-01-27 Oea, Inc. Hybrid inflator with coaxial chamber
US5821448A (en) * 1994-03-18 1998-10-13 Oea, Inc. Compact hybrid inflator
US5616883A (en) * 1994-03-18 1997-04-01 Oea, Inc. Hybrid inflator and related propellants
US5630618A (en) * 1994-03-18 1997-05-20 Oea, Inc. Hybrid inflator with a valve
IL115567A0 (en) * 1994-10-25 1996-01-19 Oea Inc Compact hybrid inflator
CN100441550C (zh) * 1996-07-22 2008-12-10 大赛璐化学工业株式会社 用于气囊的产气剂
DE19821010C1 (de) * 1998-05-11 1999-10-28 Bayern Chemie Gmbh Flugchemie Gasgenerator-Festtreibstoff und dessen Verwendung
US6066213A (en) * 1998-09-18 2000-05-23 Atlantic Research Corporation Minimum smoke propellant composition
US6126763A (en) * 1998-12-01 2000-10-03 Atlantic Research Corporation Minimum smoke propellant composition
US6156137A (en) * 1999-11-05 2000-12-05 Atlantic Research Corporation Gas generative compositions
JP5987446B2 (ja) * 2012-04-23 2016-09-07 日油株式会社 トリプルベース発射薬組成物
FR3027598B1 (fr) 2014-10-28 2018-05-04 Arianegroup Sas Produit pyrotechnique composite avec charges d'adn et de rdx dans un liant de type pag et sa preparation
CN112500253B (zh) * 2020-12-02 2022-04-12 湖北航天化学技术研究所 一种温敏时变高能固体推进剂
JP7658141B2 (ja) * 2021-03-31 2025-04-08 日油株式会社 トリプルベース発射薬組成物

Family Cites Families (14)

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Publication number Priority date Publication date Assignee Title
US3870578A (en) * 1962-07-24 1975-03-11 Us Army Polyurethane propellant
US3844855A (en) * 1966-10-19 1974-10-29 Dow Chemical Co Solid composite propellant with autocondensation product of triaminoguanidinium azide as binder
US3883374A (en) * 1969-08-20 1975-05-13 Us Navy Double-base propellant containing organic azide
US4263071A (en) * 1974-07-19 1981-04-21 United Technologies Corporation Additive for reducing combustion instability in composite solid propellants
US4288262A (en) * 1978-03-30 1981-09-08 Rockwell International Corporation Gun propellants containing polyglycidyl azide polymer
US4655859A (en) * 1980-05-21 1987-04-07 The United States Of America As Represented By The Secretary Of The Army Azido-based propellants
DE3033519A1 (de) * 1980-09-05 1982-04-29 Hercules Inc., 19899 Wilmington, Del. Rauchloses, vernetztes zweikomponenten-treibmittel und verfahren zu seiner herstellung
US4405762A (en) * 1981-12-07 1983-09-20 Hercules Incorporated Preparation of hydroxy-terminated poly(3,3-bisazidomethyloxetanes)
US4379903A (en) * 1982-03-01 1983-04-12 The United States Of America As Represented By The Secretary Of The Navy Propellant binders cure catalyst
US4450110A (en) * 1983-03-24 1984-05-22 Hercules Incorporated Azido nitramine
US4689097A (en) * 1983-08-22 1987-08-25 Hercules Incorporated Co-oxidizers in solid crosslinked double base propellants (U)
US4601344A (en) * 1983-09-29 1986-07-22 The United States Of America As Represented By The Secretary Of The Navy Pyrotechnic fire extinguishing method
US4707199A (en) * 1983-10-17 1987-11-17 The United States Of America As Represented By The Secretary Of The Army Non nitroglycerin-containing composite-modified double-base propellant
US4726919A (en) * 1985-05-06 1988-02-23 Morton Thiokol, Inc. Method of preparing a non-feathering nitramine propellant

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0679618A1 (fr) * 1994-04-30 1995-11-02 Fraunhofer-Gesellschaft Zur Förderung Der Angewandten Forschung E.V. Charge pyrotechnique pour la libération d'un gaz stocké dans un réservoir sous pression
US5623121A (en) * 1994-04-30 1997-04-22 Fraunhofer-Gesellschaft Zur Forderung Der Angewandten Forschung E.V. Pyrotechnic charge for releasing enclosed pressurized gas
EP0968983A4 (fr) * 1997-11-26 2000-09-27 Asahi Chemical Ind Composition d' hexanitrohexaazaisowurtzitane et composition explosive la contenant
WO2012028288A3 (fr) * 2010-09-03 2012-06-07 Rheinmetall Waffe Munition Gmbh Formulation d'explosif à liant plastique

Also Published As

Publication number Publication date
NO894163L (no) 1990-04-23
JPH02157177A (ja) 1990-06-15
US4938813A (en) 1990-07-03
NO894163D0 (no) 1989-10-19
DE3835854A1 (de) 1990-05-23
DE3835854C2 (fr) 1990-11-08
EP0365809A3 (fr) 1990-05-16

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