U.S. patent number 3,779,819 [Application Number 05/210,752] was granted by the patent office on 1973-12-18 for propellant powder charge having finned internal configuration.
This patent grant is currently assigned to Societe Nationale des Poudres et Explosifs. Invention is credited to Jean Ramond, Jean-Pierre Thomas.
United States Patent |
3,779,819 |
Thomas , et al. |
December 18, 1973 |
PROPELLANT POWDER CHARGE HAVING FINNED INTERNAL CONFIGURATION
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.
Inventors: |
Thomas; Jean-Pierre
(Saint-Medard-en-Jalles, FR), Ramond; Jean
(Saint-Medard-en-Jalles, FR) |
Assignee: |
Societe Nationale des Poudres et
Explosifs (Paris, FR)
|
Family
ID: |
9066159 |
Appl.
No.: |
05/210,752 |
Filed: |
December 22, 1971 |
Foreign Application Priority Data
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Dec 22, 1970 [FR] |
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7046134 |
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Current U.S.
Class: |
149/2; 149/76;
149/97; 102/288; 149/42; 149/95; 264/3.1 |
Current CPC
Class: |
F02K
9/10 (20130101) |
Current International
Class: |
F02K
9/10 (20060101); F02K 9/00 (20060101); C06b
003/02 () |
Field of
Search: |
;264/3R
;149/2,42,76,95,97 ;102/100,99,101-104 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Lechert, Jr.; Stephen J.
Claims
What we claim is:
1. 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,
c. 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.
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 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.
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.
Description
This invention relates to a method of making a finned, one piece
propellant powder charge.
Previously, propellant powder charges with quick burning times
(<0.10 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 machined on 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. 1 to 6 are perspective views of a finned one-piece 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 one-piece 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 combustible 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 I, are given below in Table
II.
The composition of the propellant powder used was as follows:
% by weight cake (60 parts nitrocellulose, 40 parts nitroglycerine)
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 140 mm Internal diameter 136 mm
External diameter after coating 144 mm Length 288 mm Powder
cross-section: fins 5928 mm.sup.2 rim 867 mm.sup.2 Burning
thickness: fins 3.8 mm rim 1.9 to 2 mm Powder density 1.63 Velocity
at 20.degree.C and 300 bars 32 mm/s Initial pressure 410 Weight 3.2
kg Periphery 3000 mm Base area (6795 .times. 2) mm.sup.2 Area (3000
.times. 288) mm.sup.2 Total area 877,600 mm.sup.2 Nozzle area (K
410) 2140 mm.sup.2 Nozzle diameter 52.2 mm.sup.2
TABLE II
Time 0.06 s Weight burnt 3.2 kg Effective pressure 300 bars Thrust
110,000 N
in the embodiment illustrated in FIG. 7 of the drawings, the finned
one-piece charge has fins of different, alternating thicknesses 4a,
4b, 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.
* * * * *