US3183133A - Solid propellant compositions containing iron catalyst - Google Patents

Solid propellant compositions containing iron catalyst Download PDF

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Publication number
US3183133A
US3183133A US64220A US6422060A US3183133A US 3183133 A US3183133 A US 3183133A US 64220 A US64220 A US 64220A US 6422060 A US6422060 A US 6422060A US 3183133 A US3183133 A US 3183133A
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United States
Prior art keywords
finely divided
propellant
iron
percent
pyrotechnic composition
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
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US64220A
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English (en)
Inventor
Albert E Lemke
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Aerojet Rocketdyne Inc
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Aerojet General Corp
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Filing date
Publication date
Application filed by Aerojet General Corp filed Critical Aerojet General Corp
Priority to US64220A priority Critical patent/US3183133A/en
Priority to DEA38558A priority patent/DE1158884B/de
Priority to GB34536/61A priority patent/GB1002446A/en
Priority to LU40720D priority patent/LU40720A1/xx
Priority to FR876562A priority patent/FR1305700A/fr
Application granted granted Critical
Publication of US3183133A publication Critical patent/US3183133A/en
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    • C—CHEMISTRY; METALLURGY
    • C06—EXPLOSIVES; MATCHES
    • C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
    • C06B33/00—Compositions containing particulate metal, alloy, boron, silicon, selenium or tellurium with at least one oxygen supplying material which is either a metal oxide or a salt, organic or inorganic, capable of yielding a metal oxide
    • C06B33/06—Compositions containing particulate metal, alloy, boron, silicon, selenium or tellurium with at least one oxygen supplying material which is either a metal oxide or a salt, organic or inorganic, capable of yielding a metal oxide the material being an inorganic oxygen-halogen salt
    • C—CHEMISTRY; METALLURGY
    • C06—EXPLOSIVES; MATCHES
    • C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
    • C06B23/00—Compositions characterised by non-explosive or non-thermic constituents
    • C06B23/007—Ballistic modifiers, burning rate catalysts, burning rate depressing agents, e.g. for gas generating
    • 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

Definitions

  • This invention relates to solid propellants and has for its object to improve the burning rates and properties of such propellants.
  • solid propellant compositions useful for underwater propulsion and ignition devices are particularly preferred.
  • Propellant compositions heretofore employed for propelling underwater projectiles have been intimate mixtures of finely divided inorganic oxidizing salts such as the chlorate, perchlorate, chromate, or dichromate salts of a metal dispersed in a finely divided, readily oxidizable metal capable of liberating large quantities of heat during oxidation, such as beryllium, aluminum, or mag nesium.
  • These propellant compositions are particularly adapted for underwater military use since they do not produce noncondensable gases upon combustion. Such gases create a highly undesirable visible wake. Due to their compactness and nongassing properties, such propellants also find valuable use in burning and cutting metal such as pipe in oil wells. Unfortunately, however, the combustion of such propellants becomes unstable at high pressures and this feature seriously limits the conditions under which these propellants may be used either for underwater propulsion or cutting purposes.
  • the iron additive is incorporated into the propellant merely by mechanically mixing it with the other ingredients, all being in finely divided form, until an intimate and uniform mixture is obtained. Optimum results are achieved when the iron is employed in amounts of from about 1 percent to about 30 percent by weight of the propellant and the readily oxidizable metal and inorganic oxidizing salts are in approximately stoichiometirc proportions.
  • the readily oxidizable metals commonly employed in the propellant composition release large quantities of heat during oxidation, have a high positive electrode potential, and are stable in the presence of air under ordinary conditions.
  • Metals such as beryllium, aluminum, and magnesium which exhibit electrode potentials in excess of +1.6 volts at 25 C. and which liberate at least 2.4 kcaL/gram when reacted with perchlorates are preferred.
  • the oxidizing salt usually employed is a chlo- Patented May 11, 1965 rate, perchlorate, chromate, or dichromate salt of a metal, or mixturesof such salts.
  • the alkali and alkaline earth metal salts are preferred.
  • the perchlorate salts are preferred due to their light weight, stability, and high oxygen content.
  • the basic solid propellants into which iron is incoraporated to effect an improvement according to this invention are prepared by mixing the finely divided metal and finely divided inorganic oxidizing salt until an intimate, uniform mixture is obtained. The mixture is then compressed under high pressure to obtain the solid grain.
  • the preferred formulations of the propellant compositions which have been found to be particularly useful for underwater jet propulsion are shown in Table I.
  • FIGURE 1 curves indicate that throughout almost the entire range of pressures tested the burning rate of the iron-containing prw pellant of this invention was greater than that of the control and that at lower'pressures it was substantially greater. For example, at a chamber pressure of p.s.i.a. the burning rate of my novel propellant was almost four times greater than that of the control.
  • the FIGURE 1 curves indicate that the control propellant was unstable at chamber pressures greater than 100 p.s.i.a. whereas the iron-containing propellant was stable at all pressures under which it was tested.
  • stability as the term is employed in the propellant art, is meant the ability of the propellant to burn without wide pressure fluctuations.
  • r is the burning rate
  • p is absolute pressure (p.s.i.a.)
  • C and n are constants.
  • the burn- Table II Chamber Additive Pressure Stability Range Factor (n) (p.s.l.a.)
  • the primary advantage to the use of iron as an additive in the propellants of this invention is the fact that such use results in substantially higher burning rates, which means that more fuel will burn in a given period of time with a resulting increase in thrust.
  • the use of iron provides a substantial improvement in pressure stability permitting a broader range of operating conditions to be attained.
  • compositions of this invention have been referred to throughout this application as solid propellants, they have utility for many other purposes besides that of propelling underwater projectiles.
  • the novel compositions of this invention can be employed as a pyrotechnic charge for many applications such as, for example, as a charge for pyrotechnic flares.
  • ignitcr charges for use in the ignition systems of rocket motors. Since the material produces an extremely highflame temperature upon burning it liberates sufficient heat to vaporize all of the combustion product and deliver the required ignition pressures.
  • compositions of this invention have particular utility as a charge for igniters of the type which do not require nozzle closure members such as that more fully described in assignees copending US. patent application Serial No. 306,- 030, filed August 23, 1952, now US. Patent No. 3,000,- 312, issued September 19, 1961.
  • igniter utility is concerned- It is apparent from the above discussion that by incorporating finely divided iron into propellant compositions containing finely divided metals such as beryllium, magnesium, or aluminum and inorganic oxidizing salts, propellants which provide greater thrust when used for underwater propulsion are obtained.
  • propellants may be used under a wide range of pressures, thus greatly increasing their usefulness both for underwater propulsion and for burning and cutting operations in oil wells.
  • the improved propellants of this invention are particularly suited for use in underwater propulsion plants of the type disclosed in assignees copending US. application Serial No. 428,698, filed May 10, 1954, now abandoned. It it within the scope of my invention to employ iron as an additive for propellants of the type disclosed herein in conjunction with other additives such as, for example, lead if desired. It is also within the scope of the invention to employ mixtures of suitable metals such as beryllium, aluminum, and magnesium as well as mixtures of oxidizing salts in my novel propellants or, as they are more properly called, pyrotechnic compositions.
  • a pyrotechnic composition consisting essentially of an intimate mixture of readily oxidizable metal selected from the group consisting of beryllium, aluminum, and magnesium and an inorganic oxidizing material selected from the group consisting of the alkali and alkaline earth metal chlorates, perchlorates, chromates, dichromates, and mixtures thereof; the improvement which comprises the intimate dispersion of finely divided iron therein as a burning rate acceleration additive, said finely divided iron being present in an amount of from about 1 percent to about 30 percent of the total pyrotechnic composition.
  • a pyrotechnic composition consisting essentially ot readily oxidizable metal selected from the group consisting of beryllium, aluminum, magnesium, and mixtures thereof in substantially stoichiometric proportion with an inorganic oxidizing material selected from the group consisting of the alkali and alkaline earth metal chlorates, perchlorates, chromates, dichromates, and mixtures thereof and, as a burning rate acceleration additive, finely divided iron in an amount of from about 1 percent to about 30 percent by weight of the total pyrotechnic composition.
  • a pyrotechnic composition consisting essentially of an intimate mixture of finely divided aluminum, an alkali metal perchlorate, and finely divided iron, the iron being present in an amount of from about 1 percent to about 30 percent by weight of the total pyrotechnic composition.
  • a pyrotechnic composition consisting essentially of an intimate mixture of a finely divided aluminum and an alkali metal perchlorate in substantially stoichiometric proportions and finely divided iron in an amount of from about 1 percent to about 30 percent of the total pyrotechnic composition.
  • a pyrotechnic composition consisting essentially of an intimate mixture of finely divided aluminum and potassium perchlorate in substantially stoichiometric proportions and finely divided iron in an amount from about 1 percent to about 30 percent by weight of the total pyrotechnic composition.
  • a solid pyrotechnic composition consisting essentially of an intimate mixture of a metal having an electrode potential above +1.6 volts at 25 C. and which will liberate at least 2.4 kcal./gram when reacted with perchlorates, and an inorganic oxidizing material selected from the group consisting of the alkali and alkaline earth metal chlorates, perchlorates, chromates, dichromates, and mixtures thereof; the improvement which comprises incorporating therein as a burning rate acceleration additive, finely divided iron in an amount of from about 1 percent to about 30 percent by weight of the total pyrotechnic composition.
  • a solid pyrotechnic composition consisting essentially of an intimate, uniform, highly compressed mixture of a metal having an electrode potential above +1.6 volts at 25 C. and which will liberate at least 2.4 kcal./ gram when reacted with perchlorates, and an inorganic oxidizing material selected from the group consisting of the alkali and alkaline earth metal chlorates, perchlorates, chromates, dichromates, and mixtures thereof; the improvement which comprises incorporating therein as a burning rate acceleration additive, finely divided iron in an amount of from about 1 percent to about 30 percent by weight of the total pyrotechnic composition.
  • a solid pyrotechnic composition consisting of an intimate mixture of a metal having an electrode potential above +1.6 volts at 25 C. and which will liberate at least 2.5 kcal./gram when reacted with perchlorates, and an inorganic oxidizing material selected from the group consisting of the alkali and alkaline earth metal chlorates, perchlorates, chromates, dichromates, and mixtures thereof, and as a burning rate acceleration additive, finely divided iron in an amount of from about 1 percent to about 30 percent by weight of the total pyrotechnic composition.
  • a solid pyrotechnic composition consisting of an intimate uniform highly compressed mixture of a metal having an electrode potential above +1.6 volts at 25 C. and which will liberate at least 2.5 kcaL/grarn when reacted with perchlorates, an inorganic oxidizing material selected from the group consisting of the alkali and alkaline earth metal chlorates, perchlorates, ohrcmates, dichromates, and mixtures thereof, and containing uniform- 1y dispersed throughout said composition as a burning rate acceleration additive, finely divided iron -in an amount of from about 1 percent to about 30 percent by weight of the total pyrotechnic composition.

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  • Chemical & Material Sciences (AREA)
  • Organic Chemistry (AREA)
  • Inorganic Chemistry (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Air Bags (AREA)
  • Solid Fuels And Fuel-Associated Substances (AREA)
  • Liquid Carbonaceous Fuels (AREA)
US64220A 1960-10-21 1960-10-21 Solid propellant compositions containing iron catalyst Expired - Lifetime US3183133A (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US64220A US3183133A (en) 1960-10-21 1960-10-21 Solid propellant compositions containing iron catalyst
DEA38558A DE1158884B (de) 1960-10-21 1961-01-14 Exotherm reagierendes Gemisch
GB34536/61A GB1002446A (en) 1960-10-21 1961-09-26 Pyrotechnic compositions
LU40720D LU40720A1 (xx) 1960-10-21 1961-10-16
FR876562A FR1305700A (fr) 1960-10-21 1961-10-20 Perfectionnements aux compositions pyrotechniques, notamment aux mélanges propulseurs à base de chlorates et d'aluminium

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US64220A US3183133A (en) 1960-10-21 1960-10-21 Solid propellant compositions containing iron catalyst

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US3183133A true US3183133A (en) 1965-05-11

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US (1) US3183133A (xx)
DE (1) DE1158884B (xx)
FR (1) FR1305700A (xx)
GB (1) GB1002446A (xx)
LU (1) LU40720A1 (xx)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4286498A (en) * 1965-12-21 1981-09-01 General Dynamics, Pomona Division Decoy rounds and their method of fabrication

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB189311073A (en) * 1893-06-06 1893-07-08 Gustav Gillischewski Improvements in Pyrotechnical Compositions or Fireworks.
US763665A (en) * 1903-08-22 1904-06-28 Charles M Hall Explosive compound.
US1244940A (en) * 1916-12-09 1917-10-30 Walter Arthur Smoke-producing compound.
GB127031A (en) * 1916-11-24 1919-05-29 Ernest Edouard Frederic Berger Improvements in the Obtainment of Fumes, or Vapours, by the Combustion of Mixtures of Chemical Substances.
US2450892A (en) * 1944-05-05 1948-10-12 George C Hale Delay powder
US2967097A (en) * 1955-02-18 1961-01-03 Aerojet General Co Solid propellant compositions
US3019687A (en) * 1952-09-11 1962-02-06 Aerojet General Co Method of forming a solid propellant
US3034874A (en) * 1955-03-07 1962-05-15 Reynolds Metals Co Blow torch fuel and method of burning same

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB189311073A (en) * 1893-06-06 1893-07-08 Gustav Gillischewski Improvements in Pyrotechnical Compositions or Fireworks.
US763665A (en) * 1903-08-22 1904-06-28 Charles M Hall Explosive compound.
GB127031A (en) * 1916-11-24 1919-05-29 Ernest Edouard Frederic Berger Improvements in the Obtainment of Fumes, or Vapours, by the Combustion of Mixtures of Chemical Substances.
US1244940A (en) * 1916-12-09 1917-10-30 Walter Arthur Smoke-producing compound.
US2450892A (en) * 1944-05-05 1948-10-12 George C Hale Delay powder
US3019687A (en) * 1952-09-11 1962-02-06 Aerojet General Co Method of forming a solid propellant
US2967097A (en) * 1955-02-18 1961-01-03 Aerojet General Co Solid propellant compositions
US3034874A (en) * 1955-03-07 1962-05-15 Reynolds Metals Co Blow torch fuel and method of burning same

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4286498A (en) * 1965-12-21 1981-09-01 General Dynamics, Pomona Division Decoy rounds and their method of fabrication

Also Published As

Publication number Publication date
DE1158884B (de) 1963-12-05
GB1002446A (en) 1965-08-25
LU40720A1 (xx) 1961-12-16
FR1305700A (fr) 1962-10-05

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