US3682727A - Igniter charge for propellant compositions and rocket propellant charges - Google Patents

Igniter charge for propellant compositions and rocket propellant charges Download PDF

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US3682727A
US3682727A US847701A US3682727DA US3682727A US 3682727 A US3682727 A US 3682727A US 847701 A US847701 A US 847701A US 3682727D A US3682727D A US 3682727DA US 3682727 A US3682727 A US 3682727A
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igniter
propellant
charge
charges
group
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Walter Heinzelmann
Karl-Egon Flach
Alfred Voss
Heinz Kroschel
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Dynamit Nobel AG
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    • 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
    • C—CHEMISTRY; METALLURGY
    • C06—EXPLOSIVES; MATCHES
    • C06C—DETONATING OR PRIMING DEVICES; FUSES; CHEMICAL LIGHTERS; PYROPHORIC COMPOSITIONS
    • C06C7/00—Non-electric detonators; Blasting caps; Primers
    • C—CHEMISTRY; METALLURGY
    • C06—EXPLOSIVES; MATCHES
    • C06C—DETONATING OR PRIMING DEVICES; FUSES; CHEMICAL LIGHTERS; PYROPHORIC COMPOSITIONS
    • C06C9/00—Chemical contact igniters; Chemical lighters

Definitions

  • an igniter charge for propellant powder charges and rocket propellant charges comprising a hot particle igniter mass containing a binder selected from the group consisting of polyepoxides, polyesters, polyurethanes, polybutadienes, polyolefins, silicones, cellulose derivatives, and rubber, an oxygen donor selected from the group consisting of ammonium and alkali metal nitrates and perchlorates and a hot particle donor selected from the group consisting of at least one metal or metal oxide of the elements of Groups I to VIII of the Periodic Table.
  • a binder selected from the group consisting of polyepoxides, polyesters, polyurethanes, polybutadienes, polyolefins, silicones, cellulose derivatives, and rubber
  • an oxygen donor selected from the group consisting of ammonium and alkali metal nitrates and perchlorates
  • a hot particle donor selected from the group consisting of at least one metal or metal oxide of the elements of Groups I to VIII of the Period
  • the present invention relates to igniter charges for propellant compositions and rocket propellant charges and more particularly to obviating disadvantages which substantially reduce the variations in activity and effectiveness of the igniter charge caused by the temperature dependency of the defiagrating properties of the igniter charge during the transmission of the ignition from said charge to the base propellant.
  • igniter boost
  • propellant powder charges for projectiles of all types, including rocket propellant charges.
  • the igniter charge is ignited, in the case of propellant powder charges, by propellant charge primers, and in the case of rockets, by primer pellets or special primer charges.
  • igniting means having a more complicated construction are employed.
  • the igniter charge usually consists of gunpowder and/ or single-base or double-base nitrocellulose powders.
  • no uniformly effective transmission of the ignition from the igniter charge to the base propellant is achieved, due to the temperature dependency of the defiagration properties of the igniter charge within the range of use required for the respective ammunition or rocket, for example, temperatures of about 40 to +50 C.
  • This fact also substantially increases the temperature-dependent variations of the muzzle velocity of the projectiles, or the starting acceleration of rockets, said variations being caused, on the one hand, by the temperature-dependencies of the defiagration properties of the base propellant and, on the other hand, by the mechanical properties of the cartridge material employed.
  • Typical types of Weapons include those of the conventional apelooka-type provided with a fixed-launching tube open on both ends.
  • the projectiles are thus driven forward by means of a propellant charge accommodated in the projectile end, the shock wave of 3,62,727 Patented Aug. 8, 1972 which is supported, with tamping, against the shock wave of a simultaneously ignited propellant charge accommodated in the rear section of the fixed-launching tube.
  • the two propellant charges in most cases, consist of a nitrocellulose double-base powder and are customarily disposed in a common cartridge case which in turn is ignited by an igniter charge.
  • An object of the present invention is to avoid the prior art disadvantages in the use of an igniter charge for propellant compositions and rocket propellant charges.
  • Another object of the present invention is to provide an improved igniter charge composition which counteracts the temperature-dependent disadvantages and substantially reduces the variations in activity and elfectiveness caused by the temperature-dependency of the defiagrating properties of the igniter charge during the transmission of the ignition from the igniter to the propellant charge to the base propellant (powder propellant charge, rocket propellant composition, etc.).
  • a further object of the present invention is to reduce the associated variations in the muzzle velocity of the projectiles, or the lift-off (starting) acceleration of rockets, and consequently to achieve a more satisfactory hit distribution characteristic.
  • a primer igniter (booster) charge for propellant powder charges and rocket propellant charges which comprises a hot-particle primer (igniter) mass containing, as a binder, a cold-curable or thermosetting polymer free of plasticizers, such as for example, polyepoxides, polyesters, polyurethanes, polybutadienes, polyolefins, silicones,
  • the preferred binders are polyurethanes comprising about 25 parts of a viscous, pre-polymerized diisocyanate of toluylene diisocyanate and 1,4-butanediol, said diisocyanate having an average molecular weight of about 2,000 and an average isocyanate content of about 4%.
  • These polyurethanes are known by the trade name Adeprene L 100, which is a Du Pont product. Used in conjunction with the polyurethanes are about 2.7 parts of methylenebis-o-chloroaniline as the curing agent therefor.
  • ammonium or alkali metal nitrates or perchlorates preferably potassium nitrate
  • ammonium or alkali metal nitrates or perchlorates preferably potassium nitrate
  • the methylene-bis-o-chloroaniline, mentioned above, is known under the trade name of Moca, which is also a Du Pont product.
  • the igniter charge can be made up exclusively from such a hot particle igniter mass, or it can also contain, in addition to the hot particle mass, 2. more or less large proportion of a conventional igniter powder, such as for example, gunpowder (black powder) and/or single or double-base nitrocellulose powders as well as mixtures thereof.
  • a conventional igniter powder such as for example, gunpowder (black powder) and/or single or double-base nitrocellulose powders as well as mixtures thereof.
  • the igniter charge of the present invention can be employed for the ignition of gunpowders, of single or double-base nitrocellulose powders, mixtures of these with gunpowders, for the initiation of propellant powder charges in cartridge ammunition for guns and cannons, as well as for the ignition of ammunition for recoilless weapons, particularly recoilless anti-tank firearms, and rocket propellant charges of polar powders, compound powders (composite powders) and gunpowders. Additionally, however, the igniter charge is also suitable for use as a detonating charge, particularly in the ignition of cartridge ammunition and rocket propellant charges.
  • the hot particle igniter mass When the hot particle igniter mass is employed as the sole component of the igniter charge, as well as when it is being used in conjunction with a more or less large proportion of a conventional igniter powder, the igniter mass can be produced and utilized, depending on the respective application, in a more or less compressed or granulated form.
  • the hot particle igniter mass can also contain natural cellulose, glue, starch, or gum arabic, and as the hot particle donor, the igniter mass can contain at least one metal and/r alloy or intermetallic phases of said materials.
  • the metals and oxides can be selected from the metals of Groups I to VIII of the Periodic Table and also the transition and rare earth elements.
  • Suitable metals and/ or metal oxides include, for example, magnesium, calcium, boron, aluminum, silicon, tin, lead, arsenic, antimony, bismuth, titanium, zirconium, vanadium, niobium, tantalum, chromium, molybdenum, tungsten, manganese, iron, cobalt, nickel, copper, zinc, cadmium, cerium, as Well as the readily reducible metallic oxides, such as for example, CuO, Cu O, PbO MnO and the like.
  • the igniter mass preferably contains elemental boron and/or mixtures or alloys or intermetallic phases of boron with titanium, zirconium, hafnium vanadium, niobium, tantalum, chromium, molybdenum, tungsten, cobalt, nickel, as well as other transition elements.
  • the hot particle igniter mass can further contain fluxes, such as, for example, calcium fluoride, magnesium oxide, as well as mold lubricants (parting compounds), such as for example, stearates or waxes.
  • compositions of a gunpowder suitable for ignitions, as well as a 'suitable hot particle igniter mass are set forth in the following examples:
  • An igniter charge for propellant powder charges and rocket propellant charge comprising a hot particle igniter mass containing about 6% by weight of a binder selected from the group consisting of polyepoxides, polyesters, polyurethane, polybutadienes, polyolefins, silicones, cellulose derivatives, and rubber, about 70% by weight of an oxygen donor selected from the group consisting of alkali metal nitrates and perchlorates and a hot particle donor of elemental boron, mixtures, alloys or intermetallic phases of boron with at least one member selected from the group consisting of titanium, zirconium, hafnium, vanadium, niobium, tantalum, chromium, molybdenum, tungsten, cobalt, nickel and the transition elements.
  • a binder selected from the group consisting of polyepoxides, polyesters, polyurethane, polybutadienes, polyolefins, silicones, cellulose derivatives, and rubber
  • the binder is a polyurethane comprising about 25 parts of a prepolymerized toluylene diisocyanate and 1,4-butanediol having an average molecular weight of about 2,000 and an average isocyanate content of about 4%.
  • the igniter charge of claim 1 further containing at least one member selected from the group consisting of nitrocellulose glue, starch and gum arabic.
  • igniter charge of claim 8 wherein the igniter powder is gunpower comprising about by weight potassium nitrate, about 10% by Weight sulfur and about 15 by weight charcoal.
  • the igniter charge of claim 1 comprising about 6% by weight of a binder consisting of about 90.13% by weight of a pre-polymerized diisocyanate of toluylene diisocyanate and 1,4-butanediol and 9.87% by weight of methylene-bis-o-chloroaniline, about 70% by weight of anhydrous potassium nitrate and about 24% by weight of amorphous boron.
  • An igniter charge for propellant powder charges and rocket propellant charges comprising a hot particle igniter mass containing a binder consisting essentially of about 25 parts of a viscous, pre-polymerized diisocyanate of toluylene diisocyanate and 1,4-butanediol having an average molecular weight of about 2,000 and an average isocyanate content of about 4%, about 2.7 parts of methylene-bis-o-chloroaniline as a curing agent, a hot particle donor consisting of amorphous boron and an oxygen donor selected from the group consisting of alkali metal nitrates and perchlorates.

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Abstract

THE PRESENT DISCLOSURE RELATES TO AN IGNITER CHARGE FOR PROPELLANT POWDER CHARGES AND ROCKET PROPELLANT CHARGES COMPRISING A HOT PARTICLE IGNITER MASS CONTAINING A BINDER SELECTED FROM THE GROUP CONSISTING OF POLYEPOXIDES, POLYESTERS, POLYURETHANES, POLYBUTANDIENES, POLYOLEFINS, SILICONES, CELLULOSE DERIVATIVES, AND RUBBER, AND OXYGEN DONOR SELECTED FROMTHE GROUP CONSISTING OF AMMONIUM AND ALKALI METAL NITRATES AND PERCHLORATES AND A HOT PARTICLE DONOR SLECTED FROM THE GROUP CONSISTING OF AT LEAST ONE METAL OR METAL OXIDE OF THE ELEMENTS GROUPS I TO VIII OF THE PERIODIC TABLE.

Description

3,682,727 IGNITER CHARGE FOR PROPELLANT COMPOSI- TIONS AND ROCKET PROPELLANT CHARGES Walter Heinzelmann, Sarninghauser, Karl-Egon Fiach, Cologne Dellbruch, Alfred Voss, Hagen, Westphalia, and Heinz Kroschel, Oberlar, Germany, assignors to Dynamit Nobel Aktiengesellschaft, Troisdorf, Germany No Drawing. Filed Aug. 5, 1969, Ser. No. 847,701 Claims priority, application Germany, Aug. 5, 1968, P 17 71 943.6 Int. Cl. C06c 9/00 U.S. Cl. 149-19 11 Claims ABSTRACT OF THE DISCLOSURE The present disclosure relates to an igniter charge for propellant powder charges and rocket propellant charges comprising a hot particle igniter mass containing a binder selected from the group consisting of polyepoxides, polyesters, polyurethanes, polybutadienes, polyolefins, silicones, cellulose derivatives, and rubber, an oxygen donor selected from the group consisting of ammonium and alkali metal nitrates and perchlorates and a hot particle donor selected from the group consisting of at least one metal or metal oxide of the elements of Groups I to VIII of the Periodic Table.
BACKGROUND OF THE INVENTION The present invention relates to igniter charges for propellant compositions and rocket propellant charges and more particularly to obviating disadvantages which substantially reduce the variations in activity and effectiveness of the igniter charge caused by the temperature dependency of the defiagrating properties of the igniter charge during the transmission of the ignition from said charge to the base propellant.
It is well known to use an igniter (booster) charge to ignite propellant powder charges for projectiles of all types, including rocket propellant charges. The igniter charge is ignited, in the case of propellant powder charges, by propellant charge primers, and in the case of rockets, by primer pellets or special primer charges. Optionally, igniting means having a more complicated construction are employed.
The igniter charge usually consists of gunpowder and/ or single-base or double-base nitrocellulose powders. However, when using such igniter charges, no uniformly effective transmission of the ignition from the igniter charge to the base propellant is achieved, due to the temperature dependency of the defiagration properties of the igniter charge within the range of use required for the respective ammunition or rocket, for example, temperatures of about 40 to +50 C. This fact also substantially increases the temperature-dependent variations of the muzzle velocity of the projectiles, or the starting acceleration of rockets, said variations being caused, on the one hand, by the temperature-dependencies of the defiagration properties of the base propellant and, on the other hand, by the mechanical properties of the cartridge material employed.
Thus, in many cases it is necessary to adjust the weapon in accordance with the respective ammunition temperature, which is cumbersome, not only in case of cartridge ammunition and rockets, but also in case of recoilless firing firarmes, for example, tank-destroying hollow-charge projectiles, with or without booster acceleration by a rocket propellant charge. Typical types of Weapons include those of the conventional bazooka-type provided with a fixed-launching tube open on both ends. The projectiles are thus driven forward by means of a propellant charge accommodated in the projectile end, the shock wave of 3,62,727 Patented Aug. 8, 1972 which is supported, with tamping, against the shock wave of a simultaneously ignited propellant charge accommodated in the rear section of the fixed-launching tube.
The two propellant charges in most cases, consist of a nitrocellulose double-base powder and are customarily disposed in a common cartridge case which in turn is ignited by an igniter charge.
SUMMARY OF THE INVENTION An object of the present invention is to avoid the prior art disadvantages in the use of an igniter charge for propellant compositions and rocket propellant charges.
Another object of the present invention is to provide an improved igniter charge composition which counteracts the temperature-dependent disadvantages and substantially reduces the variations in activity and elfectiveness caused by the temperature-dependency of the defiagrating properties of the igniter charge during the transmission of the ignition from the igniter to the propellant charge to the base propellant (powder propellant charge, rocket propellant composition, etc.).
A further object of the present invention is to reduce the associated variations in the muzzle velocity of the projectiles, or the lift-off (starting) acceleration of rockets, and consequently to achieve a more satisfactory hit distribution characteristic.
Other objects and further scope of applicability of the present invention will become apparent from the detailed description given hereinafter; it should be understood, however, that the detailed description and specific examples, while indicating preferred embodiments of the invention, are given by Way of illustration only, since various changes and modifications within the spirit and scope of the invention will become apparent to those skilled in the art from this detailed description.
Pursuant to the present invention, it has been found that the above-mentioned disadvantaes may be eliminated and a much improved propellant composition may be obtained by providing a primer igniter (booster) charge for propellant powder charges and rocket propellant charges which comprises a hot-particle primer (igniter) mass containing, as a binder, a cold-curable or thermosetting polymer free of plasticizers, such as for example, polyepoxides, polyesters, polyurethanes, polybutadienes, polyolefins, silicones,
cellulose derivatives, as well as various types of rubbers. The preferred binders are polyurethanes comprising about 25 parts of a viscous, pre-polymerized diisocyanate of toluylene diisocyanate and 1,4-butanediol, said diisocyanate having an average molecular weight of about 2,000 and an average isocyanate content of about 4%. These polyurethanes are known by the trade name Adeprene L 100, which is a Du Pont product. Used in conjunction with the polyurethanes are about 2.7 parts of methylenebis-o-chloroaniline as the curing agent therefor. As the oxygen donor, ammonium or alkali metal nitrates or perchlorates, preferably potassium nitrate, can be used. The methylene-bis-o-chloroaniline, mentioned above, is known under the trade name of Moca, which is also a Du Pont product.
In this connection, the igniter charge can be made up exclusively from such a hot particle igniter mass, or it can also contain, in addition to the hot particle mass, 2. more or less large proportion of a conventional igniter powder, such as for example, gunpowder (black powder) and/or single or double-base nitrocellulose powders as well as mixtures thereof.
The igniter charge of the present invention can be employed for the ignition of gunpowders, of single or double-base nitrocellulose powders, mixtures of these with gunpowders, for the initiation of propellant powder charges in cartridge ammunition for guns and cannons, as well as for the ignition of ammunition for recoilless weapons, particularly recoilless anti-tank firearms, and rocket propellant charges of polar powders, compound powders (composite powders) and gunpowders. Additionally, however, the igniter charge is also suitable for use as a detonating charge, particularly in the ignition of cartridge ammunition and rocket propellant charges.
When the hot particle igniter mass is employed as the sole component of the igniter charge, as well as when it is being used in conjunction with a more or less large proportion of a conventional igniter powder, the igniter mass can be produced and utilized, depending on the respective application, in a more or less compressed or granulated form.
Any higher gas pressures which may occur can be lessened by reducing the total weight of the igniter charge without adversely effecting its precise functioning.
As the binder portion, the hot particle igniter mass can also contain natural cellulose, glue, starch, or gum arabic, and as the hot particle donor, the igniter mass can contain at least one metal and/r alloy or intermetallic phases of said materials. Examples of said metals and oxides can be selected from the metals of Groups I to VIII of the Periodic Table and also the transition and rare earth elements. Suitable metals and/ or metal oxides include, for example, magnesium, calcium, boron, aluminum, silicon, tin, lead, arsenic, antimony, bismuth, titanium, zirconium, vanadium, niobium, tantalum, chromium, molybdenum, tungsten, manganese, iron, cobalt, nickel, copper, zinc, cadmium, cerium, as Well as the readily reducible metallic oxides, such as for example, CuO, Cu O, PbO MnO and the like. The igniter mass preferably contains elemental boron and/or mixtures or alloys or intermetallic phases of boron with titanium, zirconium, hafnium vanadium, niobium, tantalum, chromium, molybdenum, tungsten, cobalt, nickel, as well as other transition elements. Optionally, the hot particle igniter mass can further contain fluxes, such as, for example, calcium fluoride, magnesium oxide, as well as mold lubricants (parting compounds), such as for example, stearates or waxes.
DESCRIPTION OF THE PREFERRED EMBODIMENTS The following examples are given merely as illustrative of the present invention and accordingly are not to be considered as limiting.
Representative compositions of a gunpowder suitable for ignitions, as well as a 'suitable hot particle igniter mass are set forth in the following examples:
(a) Gunpowder for igniter charges Composition:
About 75% by weight of potassium nitrate About by weight of sulfur About by weight of charcoal (b) Hot particle igniter mass Composition:
About 24% by weight of amorphous boron About 70% by weight of anhydrous potassium nitrate About 6% by weight of a binder consisting of 90.13% by weight of Adiprene L 100 and 9.87% by weight of Moca.
The invention being thus described, it would be obvious that the same may be varied in many ways. Such variations are not to be reguarded as a departure from the spirit and scope of the invention, and all such modifications as would be apparent to one skilled in the art are intended to be included.
What is claimed is:
1. An igniter charge for propellant powder charges and rocket propellant charge comprising a hot particle igniter mass containing about 6% by weight of a binder selected from the group consisting of polyepoxides, polyesters, polyurethane, polybutadienes, polyolefins, silicones, cellulose derivatives, and rubber, about 70% by weight of an oxygen donor selected from the group consisting of alkali metal nitrates and perchlorates and a hot particle donor of elemental boron, mixtures, alloys or intermetallic phases of boron with at least one member selected from the group consisting of titanium, zirconium, hafnium, vanadium, niobium, tantalum, chromium, molybdenum, tungsten, cobalt, nickel and the transition elements.
2. The igniter charge of claim 1, wherein the binder is a polyurethane comprising about 25 parts of a prepolymerized toluylene diisocyanate and 1,4-butanediol having an average molecular weight of about 2,000 and an average isocyanate content of about 4%.
3. The igniter charge of claim 2, wherein the binder contains methylene-bis-o-chloroaniline as a curing agent.
4. The igniter charge of claim 3, wherein the oxygen donor is potassium nitrate.
5. The igniter charge of claim 1, further containing at least one member selected from the group consisting of nitrocellulose glue, starch and gum arabic.
6. The igniter charge of claim 1, further comprising at least one member selected from the group consisting of calcium fluoride, magnesium oxide, stearates and waxes.
7. The igniter charge of claim 1, further comprising an igniter powder.
8. The igniter charge of claim 7, wherein the igniter powder is gunpowder or nitrocellulose.
9. The igniter charge of claim 8, wherein the igniter powder is gunpower comprising about by weight potassium nitrate, about 10% by Weight sulfur and about 15 by weight charcoal.
10. The igniter charge of claim 1, comprising about 6% by weight of a binder consisting of about 90.13% by weight of a pre-polymerized diisocyanate of toluylene diisocyanate and 1,4-butanediol and 9.87% by weight of methylene-bis-o-chloroaniline, about 70% by weight of anhydrous potassium nitrate and about 24% by weight of amorphous boron.
11. An igniter charge for propellant powder charges and rocket propellant charges comprising a hot particle igniter mass containing a binder consisting essentially of about 25 parts of a viscous, pre-polymerized diisocyanate of toluylene diisocyanate and 1,4-butanediol having an average molecular weight of about 2,000 and an average isocyanate content of about 4%, about 2.7 parts of methylene-bis-o-chloroaniline as a curing agent, a hot particle donor consisting of amorphous boron and an oxygen donor selected from the group consisting of alkali metal nitrates and perchlorates.
References Cited UNITED STATES PATENTS 3,377,955 4/1968 Hodgson 149-19 3,126,305 3/1964 Armstrong 149-77 3,234,059 2/1966 Proell 149-19 3,245,849 4/1966 Klager et al. 149-19 3,257,801 l/1966 Martinez et al. 60-354- 3,350,245 10/1967 Dickinson 149-19 3,473,982 10/1969 Herzog 149-20 CARL D. QUARFORTH, Primary Examiner E. A. MILLER, Assistant Examiner US. Cl. X.R.
US847701A 1968-08-05 1969-08-05 Igniter charge for propellant compositions and rocket propellant charges Expired - Lifetime US3682727A (en)

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US3862865A (en) * 1971-05-24 1975-01-28 Kilgore Corp Sparkler composition
US3905846A (en) * 1973-05-23 1975-09-16 Us Navy Composite modified double base propellant with metal oxide stabilizer
US3986910A (en) * 1974-04-12 1976-10-19 The United States Of America As Represented By The Secretary Of The Navy Composite propellants containing critical pressure increasing additives
US4021514A (en) * 1974-06-21 1977-05-03 Werkzeugmaschinenfabrik Oerlikon-Buhrle Ag Method for the production of an inhibitor coating for a solid rocket propellent charge
US4034676A (en) * 1974-06-21 1977-07-12 Werkzeugmaschinenfabrik Oerlikon-Buhrle Ag Inhibitor coating for solid rocket propellent charge
US4167428A (en) * 1974-05-17 1979-09-11 The United States Of America As Represented By The Secretary Of The Army Conductance method for determining the mechanical properties of propellants
US4332631A (en) * 1982-03-04 1982-06-01 Hercules Incorporated Castable silicone based magnesium fueled propellant
US4412874A (en) * 1981-11-19 1983-11-01 The United States Of America As Represented By The Secretary Of The Army Silane ballistic modifier containing propellant
DE3243425A1 (en) * 1982-11-24 1984-05-24 Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V., 8000 München Igniter for propellant charges
US5368662A (en) * 1992-09-29 1994-11-29 Thiokol Corporation TPE binder containing crystalline modifiers and solid propellants based thereon
US6045726A (en) * 1998-07-02 2000-04-04 Atlantic Research Corporation Fire suppressant
US6086693A (en) * 1999-02-02 2000-07-11 Autoliv Asp, Inc. Low particulate igniter composition for a gas generant
US6170399B1 (en) 1997-08-30 2001-01-09 Cordant Technologies Inc. Flares having igniters formed from extrudable igniter compositions
US6224099B1 (en) * 1997-07-22 2001-05-01 Cordant Technologies Inc. Supplemental-restraint-system gas generating device with water-soluble polymeric binder
AU750304B2 (en) * 1997-09-04 2002-07-18 Alliant Techsystems Inc. Flares having igniters formed from extrudable igniter compositions
US6651563B2 (en) 1994-09-13 2003-11-25 Dynamit Nobel Artiengesellschaft Ignition elements and finely graduatable ignition components
KR100407715B1 (en) * 1994-09-13 2004-03-30 다이나미트 노벨 게엠베하 엑스플로시브슈토프-운트 지스템테히닉 Ignition elements and finely adjustable ignition components
US20070017612A1 (en) * 1996-04-26 2007-01-25 Rainer Hagel Ignition mixtures
US20070204941A1 (en) * 1999-12-03 2007-09-06 Klaus Kedecker Ignition means for propellant powders
US20090025841A1 (en) * 2007-07-06 2009-01-29 Paul Smith Surface-modified magnesium powders for use in pyrotechnic compositions
US20100300319A1 (en) * 2007-12-24 2010-12-02 Louise Guindon Low toxicity primer compositions for reduced energy ammunition

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DE3245907C2 (en) * 1982-12-11 1986-10-30 Diehl GmbH & Co, 8500 Nürnberg Process for the production of an incendiary mixture and its use in ammunition
FR2650586B1 (en) * 1989-08-01 1991-10-11 France Etat Armement IGNITION COMPOSITION FOR PYROTECHNIC DELAY
JP3543347B2 (en) * 1994-01-24 2004-07-14 日本油脂株式会社 Method for producing igniter granules
DE19548544A1 (en) * 1995-12-23 1997-06-26 Dynamit Nobel Ag Ignition mixture free of initial explosives
ES2170199T3 (en) * 1996-12-13 2002-08-01 Ruag Munition PIROTECHNICAL DELAY, PROCEDURE FOR MANUFACTURING AS WELL AS ITS USE.
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US3862865A (en) * 1971-05-24 1975-01-28 Kilgore Corp Sparkler composition
US3905846A (en) * 1973-05-23 1975-09-16 Us Navy Composite modified double base propellant with metal oxide stabilizer
US3986910A (en) * 1974-04-12 1976-10-19 The United States Of America As Represented By The Secretary Of The Navy Composite propellants containing critical pressure increasing additives
US4167428A (en) * 1974-05-17 1979-09-11 The United States Of America As Represented By The Secretary Of The Army Conductance method for determining the mechanical properties of propellants
US4021514A (en) * 1974-06-21 1977-05-03 Werkzeugmaschinenfabrik Oerlikon-Buhrle Ag Method for the production of an inhibitor coating for a solid rocket propellent charge
US4034676A (en) * 1974-06-21 1977-07-12 Werkzeugmaschinenfabrik Oerlikon-Buhrle Ag Inhibitor coating for solid rocket propellent charge
US4412874A (en) * 1981-11-19 1983-11-01 The United States Of America As Represented By The Secretary Of The Army Silane ballistic modifier containing propellant
US4332631A (en) * 1982-03-04 1982-06-01 Hercules Incorporated Castable silicone based magnesium fueled propellant
FR2523954A1 (en) * 1982-03-04 1983-09-30 Hercules Inc CASTABLE PROPERGOL COMPOSITION CONTAINING MAGNESIUM AS A FUEL
DE3243425A1 (en) * 1982-11-24 1984-05-24 Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V., 8000 München Igniter for propellant charges
US5368662A (en) * 1992-09-29 1994-11-29 Thiokol Corporation TPE binder containing crystalline modifiers and solid propellants based thereon
US6651563B2 (en) 1994-09-13 2003-11-25 Dynamit Nobel Artiengesellschaft Ignition elements and finely graduatable ignition components
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US20070017612A1 (en) * 1996-04-26 2007-01-25 Rainer Hagel Ignition mixtures
US20100180787A1 (en) * 1996-04-26 2010-07-22 Rainer Hagel Ignition mixtures
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US6224099B1 (en) * 1997-07-22 2001-05-01 Cordant Technologies Inc. Supplemental-restraint-system gas generating device with water-soluble polymeric binder
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US6045726A (en) * 1998-07-02 2000-04-04 Atlantic Research Corporation Fire suppressant
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US20070204941A1 (en) * 1999-12-03 2007-09-06 Klaus Kedecker Ignition means for propellant powders
US8147627B2 (en) * 1999-12-03 2012-04-03 Klaus Redecker Ignition means for propellant powders
US20090025841A1 (en) * 2007-07-06 2009-01-29 Paul Smith Surface-modified magnesium powders for use in pyrotechnic compositions
US7998293B2 (en) * 2007-07-06 2011-08-16 Paul Smith Surface-modified magnesium powders for use in pyrotechnic compositions
US20100300319A1 (en) * 2007-12-24 2010-12-02 Louise Guindon Low toxicity primer compositions for reduced energy ammunition

Also Published As

Publication number Publication date
NL6911485A (en) 1970-02-09
FR2015074A1 (en) 1970-04-24
BE737055A (en) 1970-01-16
DE1771943C2 (en) 1975-03-27
DE1771943B1 (en) 1972-05-31
GB1279680A (en) 1972-06-28

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