US3779819A - Propellant powder charge having finned internal configuration - Google Patents

Propellant powder charge having finned internal configuration Download PDF

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US3779819A
US3779819A US00210752A US3779819DA US3779819A US 3779819 A US3779819 A US 3779819A US 00210752 A US00210752 A US 00210752A US 3779819D A US3779819D A US 3779819DA US 3779819 A US3779819 A US 3779819A
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propellant powder
block
finned
fins
sector
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J Thomas
J Ramond
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Societe Nationale des Poudres et Explosifs
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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
    • F02K9/10—Shape or structure of solid propellant charges

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  • ABSTRACT A method of manufacturing a finned, one-piece propellant powder charge in which an extruded or moulded cylindrical block of propellant powder is split into two or more cylindrical sectors along one or more planes containing the longitudinal axis of the block. Each sector is machined to form longitudinal grooves parallel to a plane of symmetry of each sector so as to divide each sector into parallel longitudinal fins integrally connected at their bases to the rim of the respective sector. The machined sectors are then joined to reconstitute the cylindrical block and the sides of the reconstituted block is then coated with a combustion inhibitor.
  • the present invention is concerned with an improved method of manufacturing such powder charges.
  • a method of manufacturing a finned, one-piece propellant powder charge which comprises a. splitting an extruded or moulded cylindrical block of propellant powder into two or more sectors of the cylinder along one or more planes containing the longitudinal axis of the block;
  • each sector machining each sector to form longitudinal grooves parallel to a plane of symmetry of each sector so as to divide each sector with parallel longitudinal fins integrally connected at their bases to the rim of the respective sector;
  • the propellant powder may be either a homogeneous powder, for example a double-base explosive (nitroglycerine, nitrocellulose) which may be extruded, calendered or moulded, or a compound powder formed of an oxidizing agent such as ammonium perchlorate, a reducing agent such as aluminium powder, and a rubbery binder such as polybutadiene.
  • a double-base explosive nitroglycerine, nitrocellulose
  • an oxidizing agent such as ammonium perchlorate
  • a reducing agent such as aluminium powder
  • a rubbery binder such as polybutadiene
  • the cylindrical block of powder is split into two half-blocks along a plane passing through the longitudinal axis of the block.
  • the flat surface of each half-block is machined to form each half of a central bore for the reconstituted block, the parallel longitudinal fins are then machinedon each half block to the desired thickness, spacing and shape, the two machined half-blocks are bonded together, optionally by. means of adhesive, to reconstitute the original cylindrical block, and then the sides of the reconstituted block are coated with a combustion inhibiting layer, for example a lacquer.
  • a combustion inhibiting layer for example a lacquer.
  • the sectors of the block are machined to provide fins of different thicknesses.
  • fins of two different thicknesses are provided alternately in each sector. In this manner, a plurality of thrust performances can be obtained by means of a single block.
  • FIGS. I to 6 are perspective views of a finned onepiece charge at various stages during production in the method according to the invention.
  • FIGS. 7 and 8 represent cross-sections through alternative one-piece charges which may be made according to the invention.
  • an extruded or moulded cylindrical block 1 (FIG. 1) of propellant powder of a given composition is split along its entire length into two half-blocks 2 (FIG. 2).
  • a desired shape is imparted to the flat portion 3 of each half-block (FIG. 3) by milling.
  • Thin sheets or fins 4 are then formed in each half-block by machining; the thickness, spacing and shape of the fins having been determined by means of calculation.
  • the fins in each sector are joined together at their bases through the annular periphery or rim 5 of the block.
  • the two half-blocks are then joined (FIG. 5) by means of adhesive 6 or a solvent (for example, nitromethane) which dissolves the propellant.
  • adhesive 6 for example, nitromethane
  • the reconstituted block is rolled to the desired diameter and its sides are coated with a combustion inhibitor 7 (FIG. 6).
  • the resulting finned onepiece charge has many advantages: satisfactory behaviour of the assembly, which forms a single unit since the fins are attached to the remainder of the block at their bases; highly reproducible performances since the block is wholly machined; a satisfactory filling coefficient; ease of adjustment of the performances obtained; and also the fact that the desired spacing of the two series of fins 4 can be maintained by means of combusti ble nitrocellulose felt, which is placed in the central bore before applying the coating of inhibitor.
  • composition of the propellant powder used was as follows:
  • the inhibitor lacquer was a polyester lacquer with a methyl-ethyl ketone peroxide catalyst and a cobalt naphthenate accelerator.
  • the finned one-piece charge has fins of different, alternating thicknesses 4a, 412, so that two different thrust performances (one for take-off and one for acceleration) can be obtained from a single block.
  • the finned one-piece charge is formed of four quarters 2a to 2d of a cylinder, machined to form fins 4, joined by means of adhesive 6 to reconstitute the cylindrical block, and whose sides 7 are coated with inhibitor.
  • a method of manufacturing a finned, one-piece propellant powder charge which comprises a. splitting an extruded or moulded cylindrical block of propellant powder into two or more sectors of the cylinder along one or more planes containing the longitudinal axis of the block,
  • each sector machining the interior of each sector to form longitudinal grooves parallel to a plane of symmetry of each sector so as to divide each sector with parallel longitudinal fins integrally connected at their bases to the rim of the respective sector,
  • the block of propellant powder is in the form of a right circular cylinder which is split into two semi-circular sectors for machining the fins thereon.
  • the block of propellant powder comprises a double-base or compound explosive, said compound explosive being formed of an oxidizing agent, a reducing agent and a rubbery binder.
  • a method according to claim 5 comprising a compound explosive, wherein said oxidizing agent is ammonium perchlorate, said reducing agent is aluminum powder and said rubbery binder is polybutadiene.
  • a finned, one-piece, propellant powder charge comprising a cylindrical block of propellant powder exteriorlycoated with a layer of a combustion inhibitor, said cylindrical block being composed of a plurality of substantially contiguous sectors along at least one plane containing the longitudinal axis of said block, wherein the interior of each sector contains a plurality of spaced parallel longitudinal fins of said propellant powder integrally connected at their bases to the rim of the sector thereby defining a void between a portion of said fins.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
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Abstract

A method of manufacturing a finned, one-piece propellant powder charge in which an extruded or moulded cylindrical block of propellant powder is split into two or more cylindrical sectors along one or more planes containing the longitudinal axis of the block. Each sector is machined to form longitudinal grooves parallel to a plane of symmetry of each sector so as to divide each sector into parallel longitudinal fins integrally connected at their bases to the rim of the respective sector. The machined sectors are then joined to reconstitute the cylindrical block and the sides of the reconstituted block is then coated with a combustion inhibitor.

Description

Uite States Patent 1 Thomas et all.
[ Dec. 18, 1973 PROPELLANT POWDER CHARGE HAVING FINNED INTERNAL CONFIGURATION [75] Inventors: Jean-Pierre Thomas; Jean Ramond,
both of Saint-Medard-en-Jalles,
France (73] Assignee: Societe Nationale des Poudres et Explosifs, Paris, France 22 Filed: Dec. 22, 1971 21 Appl. No.: 210,752
[30] Foreign Application Priority Data Dec. 22, 1970 France 7046134 [52] US. Cl 149/2, 149/42, 149/76, 149/95, 149/97, 102/100, 102/103, 264/3 R [51 Int. Cl C0611 3/02 [58] Field of Search 264/3 R; 149/2, 42,
[56] References Cited UNITED STATES PATENTS Shope 102/100 l/l969 Thibodaux 264/3 R 2/1970 McCullough 264/3 R Primary Examiner-Stephen J. Lechert, Jr. Attorney-James E. Armstrong et a1.
[5 7] ABSTRACT A method of manufacturing a finned, one-piece propellant powder charge in which an extruded or moulded cylindrical block of propellant powder is split into two or more cylindrical sectors along one or more planes containing the longitudinal axis of the block. Each sector is machined to form longitudinal grooves parallel to a plane of symmetry of each sector so as to divide each sector into parallel longitudinal fins integrally connected at their bases to the rim of the respective sector. The machined sectors are then joined to reconstitute the cylindrical block and the sides of the reconstituted block is then coated with a combustion inhibitor.
13 Claims, 8 Drawing Figures PATENTED M 81975 3.77913 1 9 sum 2 BF 2 PROPEILLANT POWDER CHARGE HAVING FINNEI) INTERNAL CONFIGURATION This invention relates to a method of making a finned, one piece propellant powder charge.
Previously, propellant powder charges with quick burning times O.IO s) and very strong thrust surges have been obtained by using charges formed of thin sheets of powder whose composition, thickness and length have varied with the ballistic performance required, the sheets being bonded together by a combustion inhibitor often in the form of a lacquer surrounding the periphery of the sheets.
The production of a charge of this type is, however, time-consuming, expensive and subject to many uncertainties. In particular, it is very difficult to bond the sheets with the lacquer. Furthermore, when the sheets are long and very thin, they are liable to deformation and this renders their behaviour highly unsatisfactory.
The present invention is concerned with an improved method of manufacturing such powder charges.
Accordng to the present invention, there is provided a method of manufacturing a finned, one-piece propellant powder charge which comprises a. splitting an extruded or moulded cylindrical block of propellant powder into two or more sectors of the cylinder along one or more planes containing the longitudinal axis of the block;
b. machining each sector to form longitudinal grooves parallel to a plane of symmetry of each sector so as to divide each sector with parallel longitudinal fins integrally connected at their bases to the rim of the respective sector;
c. joining the machined sectors to reconstitute the cylinder block, and
d. coating the sides of the reconstituted block with a layer of a combustion inhibitor.
The propellant powder may be either a homogeneous powder, for example a double-base explosive (nitroglycerine, nitrocellulose) which may be extruded, calendered or moulded, or a compound powder formed of an oxidizing agent such as ammonium perchlorate, a reducing agent such as aluminium powder, and a rubbery binder such as polybutadiene.
Preferably, the cylindrical block of powder is split into two half-blocks along a plane passing through the longitudinal axis of the block. The flat surface of each half-block is machined to form each half of a central bore for the reconstituted block, the parallel longitudinal fins are then machinedon each half block to the desired thickness, spacing and shape, the two machined half-blocks are bonded together, optionally by. means of adhesive, to reconstitute the original cylindrical block, and then the sides of the reconstituted block are coated with a combustion inhibiting layer, for example a lacquer.
In one embodiment of the invention, the sectors of the block are machined to provide fins of different thicknesses. Preferably, fins of two different thicknesses are provided alternately in each sector. In this manner, a plurality of thrust performances can be obtained by means of a single block.
The invention will be illustrated, by way of example, by means of the following description, referring to the accompanying drawings in which:
FIGS. I to 6 are perspective views of a finned onepiece charge at various stages during production in the method according to the invention;
FIGS. 7 and 8 represent cross-sections through alternative one-piece charges which may be made according to the invention.
Referring to FIGS. 1 to 6, an extruded or moulded cylindrical block 1 (FIG. 1) of propellant powder of a given composition is split along its entire length into two half-blocks 2 (FIG. 2). In order to adjust the specific flow rate per unit of the gas passage cross-section and to restrict or, conversely, promote erosive combustion, a desired shape is imparted to the flat portion 3 of each half-block (FIG. 3) by milling.
Thin sheets or fins 4 (FIG. 4) are then formed in each half-block by machining; the thickness, spacing and shape of the fins having been determined by means of calculation. The fins in each sector are joined together at their bases through the annular periphery or rim 5 of the block.
The two half-blocks are then joined (FIG. 5) by means of adhesive 6 or a solvent (for example, nitromethane) which dissolves the propellant.
The reconstituted block is rolled to the desired diameter and its sides are coated with a combustion inhibitor 7 (FIG. 6).
Since the fins can be machined to the desired lengths, shapes and thicknesses, the resulting finned onepiece charge has many advantages: satisfactory behaviour of the assembly, which forms a single unit since the fins are attached to the remainder of the block at their bases; highly reproducible performances since the block is wholly machined; a satisfactory filling coefficient; ease of adjustment of the performances obtained; and also the fact that the desired spacing of the two series of fins 4 can be maintained by means of combusti ble nitrocellulose felt, which is placed in the central bore before applying the coating of inhibitor.
By way of example, performances obtained with a finned one-piece charge prepared according to the invention, with the dimensional characteristics listed below in Table l, are given below in Table II.
The composition of the propellant powder used was as follows:
71 by weight cake (60 parts nitrocellulose, 40 parts nitroglycen'ne) 93 Centralite" 2 combustion catalyst 4 acetylene black (combustion accelerator) 1 The inhibitor lacquer was a polyester lacquer with a methyl-ethyl ketone peroxide catalyst and a cobalt naphthenate accelerator.
TABLE I External diameter before coating I40 mm Internal diameter 136 mm External diameter after coating 144 mm Length 288 mm Powder cross-section: fins 5928 mm rim 867 mm Burning thickness: fins 3.8 mm
rim 1.9 to 2 mm Powder density 1.63 Velocity at 20C and 300 bars 32 mm/s Initial pressure 410 Weight 3.2 kg Periphery 3000 mm Base area (6795 X 2) mm Area (3000 X 288) mm Total area 877,600 r'nrn Nozzle area (K 410) Nozzle diameter 2140 mm 52.2 mm
TABLE II In the embodiment illustrated in FIG. 7 of the drawings, the finned one-piece charge has fins of different, alternating thicknesses 4a, 412, so that two different thrust performances (one for take-off and one for acceleration) can be obtained from a single block.
In the embodiment shown in FIG. 8 of the drawings, the finned one-piece charge is formed of four quarters 2a to 2d of a cylinder, machined to form fins 4, joined by means of adhesive 6 to reconstitute the cylindrical block, and whose sides 7 are coated with inhibitor.
What we claim is:
l. A method of manufacturing a finned, one-piece propellant powder charge which comprises a. splitting an extruded or moulded cylindrical block of propellant powder into two or more sectors of the cylinder along one or more planes containing the longitudinal axis of the block,
b. machining the interior of each sector to form longitudinal grooves parallel to a plane of symmetry of each sector so as to divide each sector with parallel longitudinal fins integrally connected at their bases to the rim of the respective sector,
0. adhering the machined sectors to reconstitute the cylinder block, and
d. coating the exterior of the reconstituted block with a layer of a combustion inhibitor.
2. A method according to claim 1 in which the block of propellant powder is in the form of a right circular cylinder which is split into two semi-circular sectors for machining the fins thereon.
3. A method according to claim 1 in which fins of a plurality of thicknesses are machined on each sector.
4. A method according to claim 3 in which fins of two different thicknesses are machined alternately on each sector.
5. A method according to claim 1 in which the block of propellant powder comprises a double-base or compound explosive, said compound explosive being formed of an oxidizing agent, a reducing agent and a rubbery binder. I
6. A method according to claim 5 comprising a compound explosive, wherein said oxidizing agent is ammonium perchlorate, said reducing agent is aluminum powder and said rubbery binder is polybutadiene.
7. A finned, one-piece, propellant powder charge comprising a cylindrical block of propellant powder exteriorlycoated with a layer of a combustion inhibitor, said cylindrical block being composed of a plurality of substantially contiguous sectors along at least one plane containing the longitudinal axis of said block, wherein the interior of each sector contains a plurality of spaced parallel longitudinal fins of said propellant powder integrally connected at their bases to the rim of the sector thereby defining a void between a portion of said fins.
8. A finned, one-piece propellant powder charge of claim 7, wherein said cylindrical block contains two sectors.
9. A finned, one-piece propellant powder charge of claim 7, wherein said fins are of varying thicknesses.
10. A finned, one-piece propellant powder charge of claim 7, wherein said fins are of alternating thicknesses.
11. A finned, one-piece propellant powder charge of claim 7, wherein said clyindrical block comprises a double-base explosive.
12. A finned, one-piece propellant powder charge of claim 7, wherein said cylindrical block comprises a compound explosive formed of an oxidizing agent, a reducing agent and a rubbery binder.
13. A finned, one-piece propellant powder charge of claim 12, wherein said oxidizing agent is ammonium perchlorate, said reducing agent is aluminum powder and said rubbery binder is polybutadiene.

Claims (12)

  1. 2. A method according to claim 1 in which the block of propellant powder is in the form of a right circular cylinder which is split into two semi-circular sectors for machining the fins thereon.
  2. 3. A method according to claim 1 in which fins of a plurality of thicknesses are machined on each sector.
  3. 4. A method according to claim 3 in which fins of two different thicknesses are machined alternately on each sector.
  4. 5. A method according to claim 1 in which the block of propellant powder comprises a double-base or compound explosive, said compound explosive being formed of an oxidizing agent, a reducing agent and a rubbery binder.
  5. 6. A method according to claim 5 comprising a compound explosive, wherein said oxidizing agent is ammonium perchlorate, said reducing agent is aluminum powder and said rubbery binder is polybutadiene.
  6. 7. A finned, one-piece, propellant powder charge comprising a cylindrical block of propellant powder exteriorly coated with a layer of a combustion inhibitor, said cylindrical block being composed of a plurality of substantially contiguous sectors along at least one plane containing the longitudinal axis of said block, wherein the interior of each sector contains a plurality of spaced parallel longitudinal fins of said propellant powder integrally connected at their bases to the rim of the sector thereby defining a void between a portion of said fins.
  7. 8. A finned, one-piece propellant powder charge of claim 7, wherein said cylindrical block contains two sectors.
  8. 9. A finned, one-piece propellant powder charge of claim 7, wherein said fins are of varying thicknesses.
  9. 10. A finned, one-piece propellant powder charge of claim 7, wherein said fins are of alternating thicknesses.
  10. 11. A finned, one-piece propellant powder charge of claim 7, wherein said clyindrical block comprises a double-base explosive.
  11. 12. A finned, one-piece propellant powder charge of claim 7, wherein said cylindrical block comprises a compound explosive formed of an oxidizing agent, a reducing agent and a rubbery binder.
  12. 13. A finned, one-piece propellant powder charge of claim 12, wherein said oxidizing agent is ammonium perchlorate, said reducing agent is aluminum powder and said rubbery binder is polybutadiene.
US00210752A 1970-12-22 1971-12-22 Propellant powder charge having finned internal configuration Expired - Lifetime US3779819A (en)

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CA (1) CA957537A (en)
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DE (1) DE2164028C3 (en)
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IT (1) IT943322B (en)
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Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4551287A (en) * 1978-03-30 1985-11-05 Rheinmetall Gmbh Method of making a hollow-charge inserts for armor-piercing projectiles
WO1986001280A1 (en) * 1984-08-08 1986-02-27 The Commonwealth Of Australia Care Of The Secretar Macrogranular gun propellant charge
US4758287A (en) * 1987-06-15 1988-07-19 Talley Industries, Inc. Porous propellant grain and method of making same
US5623115A (en) * 1995-05-30 1997-04-22 Morton International, Inc. Inflator for a vehicle airbag system and a pyrogen igniter used therein
US5959237A (en) * 1995-08-31 1999-09-28 The Ensign-Bickford Company Explosive charge with assembled segments and method of manufacturing same
US9051223B2 (en) * 2013-03-15 2015-06-09 Autoliv Asp, Inc. Generant grain assembly formed of multiple symmetric pieces
US20180112627A1 (en) * 2015-08-07 2018-04-26 Aerojet Rocketdyne, Inc. Solid rocket motor with vortex inducing feature

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4202129B4 (en) * 1992-01-27 2005-06-23 Rheinmetall W & M Gmbh Compact charge body

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3048112A (en) * 1959-02-06 1962-08-07 Phillips Petroleum Co Gas generator
US3421325A (en) * 1961-11-08 1969-01-14 Joseph G Thibodaux Jr Solid propellant rocket motor
US3492815A (en) * 1967-03-10 1970-02-03 Thiokol Chemical Corp Means for forming radial slots in solid propellant grains

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3048112A (en) * 1959-02-06 1962-08-07 Phillips Petroleum Co Gas generator
US3421325A (en) * 1961-11-08 1969-01-14 Joseph G Thibodaux Jr Solid propellant rocket motor
US3492815A (en) * 1967-03-10 1970-02-03 Thiokol Chemical Corp Means for forming radial slots in solid propellant grains

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4551287A (en) * 1978-03-30 1985-11-05 Rheinmetall Gmbh Method of making a hollow-charge inserts for armor-piercing projectiles
WO1986001280A1 (en) * 1984-08-08 1986-02-27 The Commonwealth Of Australia Care Of The Secretar Macrogranular gun propellant charge
US4758287A (en) * 1987-06-15 1988-07-19 Talley Industries, Inc. Porous propellant grain and method of making same
US5623115A (en) * 1995-05-30 1997-04-22 Morton International, Inc. Inflator for a vehicle airbag system and a pyrogen igniter used therein
US5959237A (en) * 1995-08-31 1999-09-28 The Ensign-Bickford Company Explosive charge with assembled segments and method of manufacturing same
US6739265B1 (en) 1995-08-31 2004-05-25 The Ensign-Bickford Company Explosive device with assembled segments and related methods
US9051223B2 (en) * 2013-03-15 2015-06-09 Autoliv Asp, Inc. Generant grain assembly formed of multiple symmetric pieces
US20180112627A1 (en) * 2015-08-07 2018-04-26 Aerojet Rocketdyne, Inc. Solid rocket motor with vortex inducing feature
US10883448B2 (en) * 2015-08-07 2021-01-05 Aerojet Rocketdyne Inc. Solid rocket motor with vortex inducing feature

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DE2164028B2 (en) 1974-02-07
NL7117582A (en) 1972-06-26
DE2164028C3 (en) 1974-09-12
IT943322B (en) 1973-04-02
NL158290B (en) 1978-10-16
CA957537A (en) 1974-11-12
BE776933A (en) 1972-04-17
GB1315644A (en) 1973-05-02
CH549778A (en) 1974-05-31
SE431745B (en) 1984-02-27
FR2119128A5 (en) 1972-08-04
DE2164028A1 (en) 1972-08-03
JPS5128682B1 (en) 1976-08-20
LU64486A1 (en) 1972-06-20

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