US3898934A - Multistrand powder charge - Google Patents

Multistrand powder charge Download PDF

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Publication number
US3898934A
US3898934A US358954A US35895473A US3898934A US 3898934 A US3898934 A US 3898934A US 358954 A US358954 A US 358954A US 35895473 A US35895473 A US 35895473A US 3898934 A US3898934 A US 3898934A
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United States
Prior art keywords
powder
strands
multistrand
charge
bracing means
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Expired - Lifetime
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US358954A
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English (en)
Inventor
Jacques Mercier
Bernard Lancon
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REPUBLIC OF FRANCE
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REPUBLIC OF FRANCE
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
    • F02K9/32—Constructional parts; Details not otherwise provided for
    • F02K9/36—Propellant charge supports
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
    • F02K9/10—Shape or structure of solid propellant charges
    • F02K9/14—Shape or structure of solid propellant charges made from sheet-like materials, e.g. of carpet-roll type, of layered structure

Definitions

  • ABSTRACT A multistrand powder charge consists of a bundle of powder strands fixed by one of their ends on a support.
  • the charge is characterized in that there is provision, in the very heart of the bundle and in at least one region between the support and the free end of the powder strands, of internal bracing means that extend crosswise with reference to the powder strands, designed to hold the said powder strands between them in such a way that each strand is separated from at least one adjacent strand, to allow a gaseous flow between the said powder strands during combustion of the charge.
  • the invention relates to multistrand powder charges, i,e., powder charges that comprise an elongated bundle of powder elements called powder strandsf fixed by one of their ends on a support.
  • the combustion of such charges can be effected without intervention of any other product (the powder then contain ing both the combustible material and the kindling material) or with intervention of another product in the fluid state (generally containing the kindling material, the powder then containing the combustible material).
  • the invention applies more especially, because this is the case in which its application appears to offer most interest, to powder charges whose combustion is effected without intervention of another product, the initiation of the reaction being provoked by an igniting device.
  • powder charges can be utilized especially for rocket propulsion.
  • the implanting of the powder strands in the support should be such that the holding of the strands of powder is ensured during the passive life of the charge as well as during its active life.
  • the powder strands In its passive life, the powder strands must present sufficient resistance in the course of the various manipulations of the charge (especially of the rocket equipped with a propulsion device that uses a powder charge of this kind). It is especially necessary that if there be shocks in the course of these manipulations, there will be no rupture of the powder strands constituting the charge.
  • the invention relates to a multistrand powder charge in which the strands of powder are mutually held, both during their passive life and during their active life, such that combustion in the heart of the charge is effected evenly, without bursting of the bundle of powder strands.
  • the multistrand powder charge of the invention comprises a bundle of powder strands fixed by one of their ends on a support. It is characterized in that there is provided in the very heart of the bundle, in at least one region located between the support and the free ends of the powder strands, means for internal bracing that extend crosswise with reference to the powder strands, arranged to hold the powder strands in such a way that each strand is separated from at least one adjacent strand, to allow gaseous flow between the said powder strands in combustion of the charge.
  • the invention comprises certain other dispositions that are preferably used at the same time, and that will be discussed more explicitly below.
  • FIG. 1 of these drawings is a schematic section of a rocket with a propulsion device designed on the basis of a powder charge in conformity with a first embodiment of the invention.
  • FIG. 2 is an enlarged section along IIII of FIG. 1.
  • FIG. 3 shows, by a section analogous to that of FIG. 2, a second embodiment of the invention.
  • FIG. 4 is a view in perspective, showing a third embodiment of the invention.
  • FIG. 5 is an end view of a powder charge designed according to a fourth embodiment of the invention.
  • FIG. 6 is a view in section of a powder charge designed according to a fifth embodiment of the invention.
  • FIG. 7 finally is a partial developed view of the powder charge of FIG. 6.
  • the rocket shown in FIG. I is equipped with a powder propulsion device designated in general by reference numeral 1.
  • This propulsion device is based in its design on a multistrand powder charge comprising a bundle of powder strands 2, disposed in parallel and fixed by one of their ends on a support 3 which has the form of a plate.
  • a multistrand powder charge is shown which comprises a bundle of powder strands disposed radially and fixed by one of their ends on the inner face 30 of a support 3, which is cylindrical.
  • internal bracing means 4 are provided in the very heart of the bundle of powder strands 2, in at least one region situated between support 3 and the free end of the said powder strands 2.
  • These bracing means 4 extend crosswise with reference to the powder strands 2, and are arranged to hold powder strands 2 between them in such a way that each strand is separated from at least one adjacent strand, to allow a gaseous flow between said powder strands 2 in combustion of the charge. It will be understood then that the powder strands are held with respect to each other, this arrangement imparting to the powder charge excellent resistance to shock and vibration.
  • the arrangement of the said bracing means 4 allows regular burning of the powder strands over the whole of their surfaces at the moment of ignition, the combustion being readily propagated across the said bracing means 4.
  • bracing means 4 are located in one or more regions near the free end of powder strands 2.
  • the bracing means 4 may be constituted by a plurality of closed concentric ties 5a, 5b, 5c, etc., which each surround a circular layer of powder strands 2.
  • bracing means 4 may also be constituted by a single tie 6 that successively surrounds the circular layers of powder strands 2, passing from one layer to the other between any two adjacent powder strands 2.
  • the outer circular layer of powder strands 2 may be held by the said single tie 6 or by an independent closed external tie 7.
  • bracing means 4 may have elastic properties, or on the contrary they may be practically inextensible.
  • the external circular layer of powder strands 2 may be held by a single tie 6 if the said tie has elastic properties.
  • the independent outer tie 7 if the single tie 6 is not elastic, said independent external tie 7 then itself being elastic.
  • one of its ends may be fixed on or about a powder strand 2 disposed at the center, and the other end may be fixed on or about a powder strand 2 that belongs to the outer layer.
  • bracing means 4 may be constituted by a grid 8 comprising, on the one hand, bearings for powder strands 2 and, on the other hand, apertures which may exist between the grid and the powder strands, or in the structure. of the grid itself.
  • the said grid 8 may be constituted by two networks of offset or staggered elements 80 and 8b, the two said networks being oriented crosswise with reference to each other and being joined at their intersecting points by braces 9, oriented parallel to powder strands 2.
  • the said powder strands 2 are then captured in the squares defined by the two said networks 80 and 8b. This shifted disposition of the two networks 8a and 8b promotes the passage of the gaseous flow between powder strands 2, while ensuring effective holding of the said powder strands 2.
  • bracing means 4 by several interconnected, offset networks, the interconnection being effected by axial braces.
  • the bracing means 4 may comprise two ties 10a and 10b situated in different planes, one of the said ties, tie 10a, separating and surrounding the lines of powder strands 2, whereas the other tie, tie 10b, separates and surrounds the columns of powder strands 2.
  • bracing means 4 are a grid type.
  • the said grid 8 is constituted by axially longitudinal elements and circular elements Sdjoined to each other at their points of intersection.
  • bracing means 4 As described above is concerned, various materials may be used, but it is advantageous to constitute the said bracing means of plastic or of an elastomer, because of the elastic properties that are found in these materials, and because of possibilities of molding, if bracing means of the grid type are to be used.
  • bracing means 4 is a consumable material (plastic, elastomer) which is destroyed in the course of moments after initiation of the combustion.
  • the powder strands 2 are nonetheless held between them during ignition and establishing of the gaseous flow, i.e. during the period in which the relative position and the holding of powder strands 2 have to be ensured to obtain satisfactory propagation of the ignition front and to avoid ruptures in powder strands 2.
  • bracing means 4 of a material capable of resisting combustion conditions, the powder strands 2 then remaining braced for a longer time.
  • Multistrand powder charge comprising a bundle of elongate rod-like individual powder strands fixed by one of their ends on a support so as to extendtherefrom to their oppositely located free ends; internal bracing means in the heart of the bundle and in at least one region between the support and the free end of the powder strands, extending crosswise relative to and between the powder strands, for separating and holding the said powder strands fixedly relative to each other and such that each strand is separated from at least one adjacent strand by said internal bracing means, to allow a gaseous flow between the said powder strands during the combustion of the charge and maintain the bundle as an integral unit, the separations between adjacent strands constituting open gas flow paths over at least the major part of the lengths of said strands.
  • Multistrand powder charge as in claim 6, wherein the grid comprises at least two offset networks of spaced elements, the two said networks being oriented crosswise with reference to each other and joined by crosspieces at their intersections.
  • Missile or rocket equipped with a powder propulsion device comprising a multistrand powder charge as claimed in claim 1.
  • Multistrand powder charge as claimed in claim 12 wherein said powder strands are arranged in generally concentric circular layers as viewed longitudinally, and wherein the internal bracing means comprise tie means surrounding adjacent circular layers so as to separate adjacent layers and maintain the bundle as an in-

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physical Or Chemical Processes And Apparatus (AREA)
US358954A 1972-05-12 1973-05-10 Multistrand powder charge Expired - Lifetime US3898934A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR727216943A FR2183591B1 (de) 1972-05-12 1972-05-12

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US3898934A true US3898934A (en) 1975-08-12

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US (1) US3898934A (de)
CH (1) CH567239A5 (de)
DE (1) DE2323966A1 (de)
FR (1) FR2183591B1 (de)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3967558A (en) * 1974-12-09 1976-07-06 The United States Of America As Represented By The Secretary Of The Army Propellant grain support apparatus
DE2757764A1 (de) * 1976-12-30 1978-07-20 Poudres & Explosifs Ste Nale Treibsatz, verfahren zu dessen herstellung und dessen anwendung
US4257330A (en) * 1978-01-18 1981-03-24 Forenade Fabriksverken Propelling charge for a recoilless weapon or a rocket and a method to produce the charge
US4311005A (en) * 1979-05-11 1982-01-19 Raytheon Company Rocket motor
US4382409A (en) * 1980-10-30 1983-05-10 The United States Of America As Represented By The Secretary Of The Army Longitudinal reinforcement of high explosive fill in projectiles
US5080017A (en) * 1991-01-18 1992-01-14 Pocal Industries, Inc. Ignition cartridge system
US20080047453A1 (en) * 2003-12-09 2008-02-28 Eurenco Bofors Ab Progressive Propellant Charge With High Charge Density
US11746728B1 (en) * 2022-03-31 2023-09-05 Raytheon Company Propulsion system with grooved inert rods for reactive wire

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0321444A3 (de) * 1987-12-16 1989-09-06 NORICUM MASCHINENBAU UND HANDEL GESELLSCHAFT m.b.H. Treibsatz für eine Einrichtung zur Verringerung des Bodensoges an Artilleriegeschossen

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3017743A (en) * 1956-01-20 1962-01-23 Phillips Petroleum Co Rocket and propellant charge therefor
US3021748A (en) * 1958-05-19 1962-02-20 Phillips Petroleum Co Method for bonding support rods in propellant grains
US3029736A (en) * 1957-12-26 1962-04-17 Phillips Petroleum Co Restricting material for solid rocket propellant
US3234878A (en) * 1962-10-05 1966-02-15 Soc Tech De Rech Ind Powder-fuelled rocket
US3613597A (en) * 1964-01-16 1971-10-19 North American Rockwell Solid propellant grain

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3017743A (en) * 1956-01-20 1962-01-23 Phillips Petroleum Co Rocket and propellant charge therefor
US3029736A (en) * 1957-12-26 1962-04-17 Phillips Petroleum Co Restricting material for solid rocket propellant
US3021748A (en) * 1958-05-19 1962-02-20 Phillips Petroleum Co Method for bonding support rods in propellant grains
US3234878A (en) * 1962-10-05 1966-02-15 Soc Tech De Rech Ind Powder-fuelled rocket
US3613597A (en) * 1964-01-16 1971-10-19 North American Rockwell Solid propellant grain

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3967558A (en) * 1974-12-09 1976-07-06 The United States Of America As Represented By The Secretary Of The Army Propellant grain support apparatus
DE2757764A1 (de) * 1976-12-30 1978-07-20 Poudres & Explosifs Ste Nale Treibsatz, verfahren zu dessen herstellung und dessen anwendung
US4275657A (en) * 1976-12-30 1981-06-30 Societe Nationale Des Poudres Et Explosifs Spirally wound pyrotechnic charge useful for the propulsion of an engine and the like
US4257330A (en) * 1978-01-18 1981-03-24 Forenade Fabriksverken Propelling charge for a recoilless weapon or a rocket and a method to produce the charge
US4311005A (en) * 1979-05-11 1982-01-19 Raytheon Company Rocket motor
US4382409A (en) * 1980-10-30 1983-05-10 The United States Of America As Represented By The Secretary Of The Army Longitudinal reinforcement of high explosive fill in projectiles
US5080017A (en) * 1991-01-18 1992-01-14 Pocal Industries, Inc. Ignition cartridge system
US20080047453A1 (en) * 2003-12-09 2008-02-28 Eurenco Bofors Ab Progressive Propellant Charge With High Charge Density
US7918163B2 (en) * 2003-12-09 2011-04-05 Eurenco Bofors Ab Progressive propellant charge with high charge density
US8544387B2 (en) 2003-12-09 2013-10-01 Eurenco Bofors Ab Progressive propellant charge with high charge density
US11746728B1 (en) * 2022-03-31 2023-09-05 Raytheon Company Propulsion system with grooved inert rods for reactive wire

Also Published As

Publication number Publication date
FR2183591A1 (de) 1973-12-21
FR2183591B1 (de) 1974-07-26
CH567239A5 (de) 1975-09-30
DE2323966A1 (de) 1973-11-22

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