EP0633236A1 - Revêtement énergétique pour propergols pour armes à feu - Google Patents

Revêtement énergétique pour propergols pour armes à feu Download PDF

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Publication number
EP0633236A1
EP0633236A1 EP94106584A EP94106584A EP0633236A1 EP 0633236 A1 EP0633236 A1 EP 0633236A1 EP 94106584 A EP94106584 A EP 94106584A EP 94106584 A EP94106584 A EP 94106584A EP 0633236 A1 EP0633236 A1 EP 0633236A1
Authority
EP
European Patent Office
Prior art keywords
propellant
gap
catalyst
parts
fabricating
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.)
Withdrawn
Application number
EP94106584A
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German (de)
English (en)
Inventor
James R. Northrup
Allen W. Olson
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.)
Northrop Grumman Innovation Systems LLC
Original Assignee
Alliant Techsystems Inc
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 Alliant Techsystems Inc filed Critical Alliant Techsystems Inc
Publication of EP0633236A1 publication Critical patent/EP0633236A1/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Withdrawn legal-status Critical Current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
    • 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
    • C—CHEMISTRY; METALLURGY
    • C06—EXPLOSIVES; MATCHES
    • C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
    • C06B21/00—Apparatus or methods for working-up explosives, e.g. forming, cutting, drying
    • C06B21/0083—Treatment of solid structures, e.g. for coating or impregnating with a modifier
    • 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
    • C06B45/02—Compositions or products which are defined by structure or arrangement of component of product comprising particles of diverse size or shape

Definitions

  • the present invention relates to the field of cased telescoped propellant and, in particular, an energetic gun propellant coating employing Glycidyl Azide Polymer (GAP) and a method of manufacturing an energetic gun propellant coating.
  • GAP Glycidyl Azide Polymer
  • Methods of the prior art disclose a gun propellant coated with polyvinyl acetate or polyvinyl nitrate (PVN) which is consolidated in a heated die.
  • a heated die is shown in Figure 1.
  • the die comprises top and bottom punches or rams 1 and 4, respectively, and spray nozzles 7 for spraying solvent 6 onto a propellant 5.
  • the die itself comprises a top member 2 and a bottom member 3 for containing and compressing the propellant 5 in cooperation with the punches 1, 4 which press inwardly against the propellant and solvent mixture under heat treatment.
  • the invention offers a method for coating a cased telescoped propellant which does not require the use of solvent.
  • the method of the present invention reduces processing time for labor intensive solvation, and compaction and drawing processing which may take up to eight days.
  • the GAP coated propellant of the present invention offers a new material for deterring propellants.
  • the method of the present invention inhibits water penetration into the propellent, offers insensitive ammunition advantages, and produces better ballistic performance.
  • the performance of GAP coated propellants is improved over, for example, the PVN coated propellants of the prior art.
  • the present invention provides a method for fabricating an energetic gun propellant coating.
  • the method includes the step of weighing a quantity of propellant.
  • the quantity of propellant is mixed with Glycidyl Azide Polymer (GAP).
  • GAP Glycidyl Azide Polymer
  • the present invention provides a method for fabricating a gun propellant coating by weighing a quantity of propellant and mixing it with glycidyl azide polymer (GAP).
  • GAP glycidyl azide polymer
  • a catalyst may also be added before consolidating the coated propellant.
  • a catalyst is added to the mixture of propellant with GAP.
  • the catalyst may consist of a material selected from the group including triphenyl bismouth, dibutyl tin laureate, stannous octalate, and methyl di-aniline.
  • Figure 1 shows a propellant mold of the prior art used for coating and compacting gun propellant.
  • Figure 2 illustrates a slow cure method in accordance with the method of the invention for curing a gun propellant without the need for solvation.
  • Figure 3 shows an alternative fast cure approach for curing a gun propellant without the need for a solvation step in accordance with the method of the present invention.
  • Glycidyl Azide Polymer is an energetic material available from 3M Corporation of St. Paul, Minnesota. By applying a 3% mixture of GAP to a propellant with a catalyst, the material forms a coating on the propellant.
  • the coated propellant, prior to cure, may be compacted to achieve a higher density propellant charge than may be accomplished through standard loading methods. Ballistic tests of the coated propellant show that the GAP coating acts as a surface deterrent. Its energetic nature, however, does not effect the underlying propellant ignition which is critical for rapid fire guns. Initial tests also show that GAP coated propellant produces superior ballistic performance.
  • the GAP coated propellant of the present invention also has other significant advantages.
  • the coating greatly reduces the hygroscopicity of the propellant. This is significant because lower hygroscopicity extends the life and improves handling characteristics of propellants as compared to the current state of art.
  • One gun propellant performance characteristic which may be improved over the prior art is moisture sensitivity.
  • the present invention provides a reduction in hygroscopicity which may allow more ammunition to be packed without requiring metallic cartridge cases.
  • the GAP coated propellant as provided by the present invention also has improved insensitive munition properties.
  • the coating does not substantially propagate burning at ambient pressure. Therefore, if a cartridge case is adequately designed to open under low pressures when outside of the gun chamber, the propellant is resistant to burning.
  • the fabrication process for the GAP propellant grains includes the steps of charge weighing at step 12, mixing the propellant with GAP and a catalyst at step 14, placing the propellant in a mold at step 16, consolidating the propellant at step 18, and loading, assembling and packing rounds at step 20.
  • Charge weighing at step 12 may be accomplished using a known method of weighing grains of propellant in accordance with weight specifications required by the cartridge being manufactured. For example, propellant grains may be weighed in quantities of 50 grams for some applications.
  • the propellant is mixed with GAP and a catalyst using any conventional mixing apparatus.
  • a propellant may be mixed in batches with GAP and stirred or, as another example, GAP may be sprayed onto a layer of propellant on a conveyor belt with a conventional catalyst.
  • each grain of propellant may receive a load of about 14,000 pounds or more for about 3 minutes, ⁇ .2 minutes, on a single compacting press. After consolidation, the propellant is prepared to be loaded, assembled and packed into rounds at step 20.
  • the alternative method 30 comprises charge weighing at step 12, mixing propellant with GAP at step 34, placing propellant in a mold at step 36, spraying catalyst through the propellant at step 38, consolidation of separate propellant at step 18 and loading, assembling and packing into rounds at step 20.
  • charge weighing at step 12 consolidation at step 18, and loading, assembling and packing rounds at step 20 are substantially the same as discussed hereinabove with reference to Figure 2.
  • the process differs after the charge weighing step wherein the propellant is mixed with GAP at step 34.
  • the catalyst is not yet introduced at this point in the fast cure method.
  • the propellant mixed with GAP is then placed in a mold at step 36.
  • a spraying apparatus is used to spray the catalyst throughout the propellant while the propellant is residing in the mold.
  • the mold may be any conventional mold as is known by those skilled in the art.
  • the spraying apparatus may be any conventional spraying apparatus and the catalyst may be sprayed in amounts in accordance with the desired set time. The spray is adjusted until the desired set time is achieved.
  • Possible catalysts for use in any of the methods described herein include triphenyl bismouth, dibutyl tin laureate, stannous octalate, and methyl di-aniline.
  • the triphenyl bismouth and dibutyl tin laureate may be used as recommended by the GAP manufacturer.
  • Stannous octalate may be used as a cure for curing in about 5-10 minutes when used in 2 parts stannous octalate to 100 parts polymer.
  • Methyl di-aniline may be used as a cure for curing in less than 5 minutes when used in 12 parts methyl di-aniline to 100 parts polymer.
  • Methyl di-aniline has been used in spray applicators as a pure solution and also diluted in methyl ethel ketone (MEK).
  • MEK methyl ethel ketone
  • the use of MEK as a diluent is not preferred because the MEK is a solvent which must be removed downstream in the process.
  • Use of methyl di-aniline may result in an almost immediate cure as the MEK is removed by vacuum, for example.
  • GAU-8 munitions are 30 mm rounds for use in a Gatling type gun employed on the A-10 Fairchild aircraft.
  • the results of the GAU-8 tests are shown in the summary table below.
  • GAP coated propellant was added, the ballistic performance decreased. The performance decrease is believed due to a mixture of 2.83% GAP coating (and 97.17% propellant by weight) replacing more energetic components in the 150 gram propellant charge load. More significantly, the GAP coating appears to deter the propellant burning process. The GAP coated propellant did not appear to inhibit ignition at 70°F. This is demonstrated by the consistent standard deviations and linear response to adding more GAP coated propellant.
  • N is defined as the number of rounds
  • S is the standard deviation
  • BS-1368 is a lot number designating a particular propellant manufactured by Hercules Corporation.
  • GUNS A software program called GUNS was also used to predict the response of GAP coated propellant, treating GAP for simulation purposes as if it acted as a common deterrent such as methyl centralite, or Hercote (Hercote is a trademark of Hercules Corporation).
  • GUNS is a software modeling program developed to model case telescoped ammunition.

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  • Chemical & Material Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Organic Chemistry (AREA)
  • Health & Medical Sciences (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Dispersion Chemistry (AREA)
  • Molecular Biology (AREA)
  • Application Of Or Painting With Fluid Materials (AREA)
  • Paints Or Removers (AREA)
EP94106584A 1993-06-30 1994-04-27 Revêtement énergétique pour propergols pour armes à feu Withdrawn EP0633236A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US8586793A 1993-06-30 1993-06-30
US85867 1993-06-30

Publications (1)

Publication Number Publication Date
EP0633236A1 true EP0633236A1 (fr) 1995-01-11

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EP94106584A Withdrawn EP0633236A1 (fr) 1993-06-30 1994-04-27 Revêtement énergétique pour propergols pour armes à feu

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EP (1) EP0633236A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5681904A (en) * 1996-04-01 1997-10-28 Minnesota Mining And Manufacturing Company Azido polymers having improved burn rate
CN114213200A (zh) * 2021-11-20 2022-03-22 中北大学 一种火炮膛内能量时序补偿固体发射药

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3655836A (en) * 1968-06-26 1972-04-11 Hercules Inc Process for preparation of molded propellant charges from smokeless powder and nonvolatile binders
US3682726A (en) * 1969-04-29 1972-08-08 Us Army Nitrocellulose grain having crosslinked polymeric deterrent coating and process of making
DE2449777A1 (de) * 1974-10-19 1976-04-22 Rockwell International Corp Treibladungspulver und insbesondere gekoernte inhibierte treibladungspulver fuer projektile sowie ein verfahren zu deren herstellung
EP0002968A1 (fr) * 1977-12-15 1979-07-11 Societe Nationale Des Poudres Et Explosifs Chargement unitaire fragmentable de poudre propulsive contenant un liant au nitrate de polyvinyle et son procédé de fabrication
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
EP0446085A1 (fr) * 1990-02-21 1991-09-11 Societe Nationale Des Poudres Et Explosifs Procédé de fabrication de chargements propulsifs fragmentables résistant à la température, poudres constitutives et chargements ainsi obtenus
US5164521A (en) * 1985-08-30 1992-11-17 Minnesota Mining And Manufacturing Company Primary hydroxyl-terminated polyglycidyl azide

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3655836A (en) * 1968-06-26 1972-04-11 Hercules Inc Process for preparation of molded propellant charges from smokeless powder and nonvolatile binders
US3682726A (en) * 1969-04-29 1972-08-08 Us Army Nitrocellulose grain having crosslinked polymeric deterrent coating and process of making
DE2449777A1 (de) * 1974-10-19 1976-04-22 Rockwell International Corp Treibladungspulver und insbesondere gekoernte inhibierte treibladungspulver fuer projektile sowie ein verfahren zu deren herstellung
EP0002968A1 (fr) * 1977-12-15 1979-07-11 Societe Nationale Des Poudres Et Explosifs Chargement unitaire fragmentable de poudre propulsive contenant un liant au nitrate de polyvinyle et son procédé de fabrication
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
US5164521A (en) * 1985-08-30 1992-11-17 Minnesota Mining And Manufacturing Company Primary hydroxyl-terminated polyglycidyl azide
EP0446085A1 (fr) * 1990-02-21 1991-09-11 Societe Nationale Des Poudres Et Explosifs Procédé de fabrication de chargements propulsifs fragmentables résistant à la température, poudres constitutives et chargements ainsi obtenus

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
M.B. FRANKEL ET AL.: "Historical Development of Glycidyl Azide Polymer", JOURNAL OF PROPULSION AND POWER, vol. 8, no. 3, May 1992 (1992-05-01), WASHINGTON, DC,US, pages 560 - 563, XP000268283 *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5681904A (en) * 1996-04-01 1997-10-28 Minnesota Mining And Manufacturing Company Azido polymers having improved burn rate
CN114213200A (zh) * 2021-11-20 2022-03-22 中北大学 一种火炮膛内能量时序补偿固体发射药

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