GB1605458A - Double-base propellant - Google Patents
Double-base propellant Download PDFInfo
- Publication number
- GB1605458A GB1605458A GB2343575A GB2343575A GB1605458A GB 1605458 A GB1605458 A GB 1605458A GB 2343575 A GB2343575 A GB 2343575A GB 2343575 A GB2343575 A GB 2343575A GB 1605458 A GB1605458 A GB 1605458A
- Authority
- GB
- United Kingdom
- Prior art keywords
- propellant charge
- lead
- double
- nitrocellulose
- propellant
- 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.)
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Classifications
-
- C—CHEMISTRY; METALLURGY
- C06—EXPLOSIVES; MATCHES
- C06B—EXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
- C06B25/00—Compositions containing a nitrated organic compound
- C06B25/18—Compositions containing a nitrated organic compound the compound being nitrocellulose present as 10% or more by weight of the total composition
- C06B25/24—Compositions containing a nitrated organic compound the compound being nitrocellulose present as 10% or more by weight of the total composition with nitroglycerine
-
- 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
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- Chemical & Material Sciences (AREA)
- Organic Chemistry (AREA)
- Health & Medical Sciences (AREA)
- Emergency Medicine (AREA)
- Pharmaceuticals Containing Other Organic And Inorganic Compounds (AREA)
- Compositions Of Macromolecular Compounds (AREA)
Description
00 in
Tf
IT)
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*s©
PATENT SPECIFICATION
(21) (23) (44)
(51)
(52)
(22) Filed 29/05/1975
Application No. 23435/75 Complete Specification filed 15/03/1976 Complete Specification published: 17 December 2008 International Classification7 C06B: 21/00, 29/16, 29/20 Index at acceptance CI D: D6A2C, D6A2D. D6B4
(72) Inventor(s) GWYNN LEWIS & ROBERT RE1D STEVELY
(54) DOUBLE-BASE PROPELLANT
id 1 605 458
(71) We, IMPERIAL CHEMICAL INDUSTRIES LIMITED a British Company of Imperial Chemical House, Millbank, London, SW1P 3JF do hereby declare the invention, for which we pray that a patent may be granted to us, and the method by which it is to be performed, to be particularly described in and by the following statement:-
5
This invention relates to double-base propellants and more particularly to such propellants containing lead salts to modify their ballistic properties.
A double-base propellant is one containing nitrocellulose plasticised or gelatinised with a liquid nitric 10 ester, the usual ester being nitroglycerine, although others such as diethylene glycol dinitrate and metriol trinitrate may be employed. The ingredients may be mixed by a process involving mastication and shaped to the final charge by a process such as extrusion. Alternatively, in the case of cast double-base charges, the final charge is usually made by filling a single (based on nitrocellulose only) or double-base propellant casting powder into a casing, allowing a 'casting liquid' containing nitroglycerine and a liquid non-15 explosive plasticizer for nitrocellulose to displace all the air in the casing, and curing at about 40- 65°C for several days to allow the powder to swell to form a homogeneous rigid or rubbery mass. A cast double-base charge may also be made by filling a container with a preformed slurry of powder in casting liquid with subsequent curing by heat.
20 Conventional propellants have a burning rate at a fixed ignition temperature given by the expression r = kpn where r is the burning rate, p is the pressure and k and n are constants. Normally the exponent n has a value of 0.5 to 0.8 but compositions have been developed incorporating lead salts as ballistic modifiers which have the effect of reducing the exponent to zero or nearly so over a substantial range of useful working pressures. The graph of the log r against log p contains a flat portion or plateau and 25 these compositions are therefore termed 'platonised'. It is convenient to refer to the burning rate over the plateau range as the 'plateau burning rate'. These platonised propellants are particularly suited to gas producing and rocket charges where the desired characteristics are a plateau covering a wide pressure range and, especially for rocket boost charges, a high plateau burning rate. These two requirements are not easily satisfied simultaneously and the composition is usually designed to achieve a compromise of 30 burning rate and plateau characteristic at the desired working pressure. The lead salts currently favoured include the lead salts of salicylic, phthalic, IJ-resorcylic and stearic acids. The effect of such salts is described in the United States Patent Specification. No. 3,088,858 and their effect in conjunction with copper salts is described in the United States Patent Specification No. 3,138,499. A particularly suitable burning rate is achieved when the ballistic modifier consists of a mixture of lead salicylate and load 35 13-resorcylate. However, as described in our copending United Kingdom Patent Application No. 23434/75 when the moisture content of the casting powder is greater than 0.2.5% w,/w, cast double-base charges platonised with such mixtures normally show a downward drift in burning rate after storage, the drift being faster at elevated temperature. Under normal atmospheric conditions the equilibrium moisture content of such casting powders is of the order of 0.4 to 0.6% w/w.
1.605,458
It is an object of this invention to provide platonised double-base propellant charges of enhanced plateau burning rates, and a further object is to provide cast double-base propellant charges platonised with a mixture of lead salicylate and lead B-resorcylate having enhanced burning rates which are maintained when the charges are stored at elevated temperature.
5
We have now found that the addition of certain nitrocellulose crosslinking agents to platonised double-base propellants increases the plateau burning rate without markedly reducing the plateau pressure range although, in some cases, the plateau may occur at a slightly higher pressure level.
10 Thus, in accordance with this invention, a double-base propellant charge comprises at least one platonising lead salt and a nitrocellulose crosslinking compound having in its molecular structure two or more groups having the formula -N-CH, -OR wherein R is hydrogen or an alkyl group containing 1 to 8 carbon atoms.
15 Suitable crosslinking compounds include dimethylol and dialkoxymethyl derivatives of amides, urea and cyclic ureas, and methylol and alkoxymethyl derivatives of melamine. Preferred crosslinking compounds are N, N' -bi s (methoxymethyl) uron and hexamethoxymethyl melamine. To achieve a substantial increase in the propellant plateau burning rate the crosslinking agent should preferably be present in an amount in the range from 0.5 to 2.0% by weight of the composition. This amount of crosslinking agent 20 has no effect on the chemical stability or crack life of the propellant charge and generally improves the tensile strength.
Although the specified crosslinking agent has the effect of increasing the plateau burning rate of all double-base propellants containing platonising lead salts, the effect is especially beneficial in cast 25 double-base propellants containing platonising mixtures of lead salicylate and lead B-resorcylate (lead 2,4—dihydroxybenzoate). Such mixtures generally contain lead salicylate and lead B-resorcylate in the weight ratio of from 4:1 to 1:4. These platonised propellants have high plateau burning rates but, unless the casting powder is dried to an abnormally low moisture content, the burning rate decreases on storage at elevated temperature to a minimum value about 5 to 15% lower than the rate immediately after curing. 30 Using the specified crosslinking compounds, not only are the initial plateau burning rates increased but there is no subsequent downward drift in burning rate when the propellant is stored at 50°C.
In addition to the nitrocellulose, liquid nitric ester and ballistic modifier, the propellant charge may include plasticisers, stabilisers, glazing agents and the like as are conventional in such charges. Metal 35 powders such as aluminium may also be incorporated, if desired, to raise the heat of combustion (and consequently the specific impulse). Carbon black is also commonly added to increase the burning rate.
The preferred double-base propellant composition comprises as basic ingredients from about 35 to 55% by weight of nitrocellulose, from about 30 to 50% by weight of nitroglycerine or other liquid nitric ester, 40 from 0.5 to 2.0% by weight of the nitrocellulose crosslinking compound, from about 1 to 5% by weight of lead salt ballistic modifier and from about 1 to 3% by weight of a stabiliser such as, for example, 2-n. itrociphenyl-amine or N-methyl-p-nitro aniline. The composition preferably also comprises from about 5 to 12% by weight of a non-explosive plasticiser such as, for example, triacetin or dibutyl phthalate.
45 In the case of cast double-base propellant charges, the nitrocellulose crosslinking agent may be introduced in either the casting powder or casting liquid as an extra additive or to replace an equivalent weight of another non-explosive ingredient of a conventional propellant composition. An increased cure period may be required to complete the reaction of the crosslinking agent and obtain the maximum plateau burning rate. This may be conveniently achieved by exposing the propellant to a short period of storage at 50 elevated temperature after a relatively low temperature cure, or alternatively, by the use of a higher cure temperature.
t
3
1,605,458
3
The invention is further illustrated by the following Examples wherein all parts and percentages are by weight. Examples 1 and 6 do not contain the nitrocellulose crosslinking agent and are not in: accordance with the invention but are included for comparison. The Examples were cast double-base propellant charges having the composition and calculated heats of explosion as shown in Table 1 and prepared by the 5 following procedure.
In the preparation of the casting powder all the ingredients of the casting powder shown in Table 1, together w ith a sufficient quantity of solvent for the nitrocellulose, were mixed in an incorporator mixer to form a homogeneous rubbery dough. The dough was extruded into cords and the cords cut on a rotary 10 cutting machine to produce granules. The solvent was removed from the resulting powder granules by hot stoving and the finished powder was glazed by tumbling with graphite in a rotating pan glazer.
The casting powder was filled into a cellulose acetate beaker in a casing and a casting liquid as shown in Table 1. which had been evacuated under high vacuum for about 2 hours to remove water and volatile 15 impurities, was added to displace the air in the beaker. The charge was cured at 43°C under nitrogen at a pressure of 25 psi for 4 days to allow the powder to swell to form a homogeneous rigid or rubbery mass. Those Examples containing nitrocellulose crosslinking agent were given an additional cure at 50°C in air at atmospheric pressure for 1 to 2 weeks until the maximum burning rate was achieved. The final propellant compositions shown in Table 1 were calculated from the measured powder to liquid (weight to 20 weight) ratios of the cast propellant charges.
The heats of explosion (expressed in Table 1 as Kilojoules/Kilogram) were calculated in the conventional manner. The ballistic data quoted in the Examples and illustrated in the accompanying graphs was obtained by burning a 122 mm x 61 mm x 20 mm slab of propellant in a motor at an ignition temperature 25 of 20°C and obtaining the pressure v time curve. This method of ballistic proof is well known in the art.
Example 1
The cast double-base propellant charge of this Example contained lead salicylate (anhydrous normal 30 salt) and lead B-resorcylate (normal salt monohydrate) and was prepared from a casting powder having equilibrium water content of 0.53%. The charge had the following burning rates when fresh and after storage at 50°C. It will be noted that there was a significant downward drift in the plateau burning rate after storage.
Pressure (bar)
80
100
120
140
160
180
Burning Rate mm/sec
Fresh (after cure)
21.42
23.02
23.08
22.95
22.51
22.12
After storage at 50°c
2 weeks
18.24
1973
20.47
21.10
21.52
21.28
5 weeks
16.76
18.08
19.31
19.88
20.02
20.11
24 weeks
16.72
18.12
19.28
19.75
20.05
20.06
4
1,605,458
4
The rate of burning v pressure curves at 20°C are also shown graphically in Fig. 1 of the accompanying drawings. The plateau burning rate reached a minimum value after 2 to 5 weeks and showed no significant change on further storage at 50°C.
5 Example 2
This Example had the same composition as Example 1 except that the casting powder contained additionally 1.5 parts by weight of N, N'-bis (methoxymethyl)uron. The equilibrium moisture content of the casting powder was 0.52%.
10
The charge had the following burning rates which are shown graphically in Fig. 2.
15
20
It will be seen that the plateau burning rate was significantly higher than that of Example 1 and the rate did not diminish on storage at 50°C but the plateau occurred at a somewhat higher pressure level. The 25 heat of explosion did not differ significantly from that of Example 1.
Example 3
The composition of the cast double-base propellant charge of this Example was the same as Example 1, except that the casting liquid contained 3.0 parts of N,N'-bis(methoxymethyl) uron instead of the same weight of the triacetin. The equilibrium water content of the casting powder was 0.53%. The propellant had an increased plateau burning rate compared with Example 1 and showed essentially stable ballistic properties when stored at 50°C. The burning rates are given below and are shown graphically in Fig. 2.
35
40
Pressure (bar)
100
120
140
160
180
200
Burning Rate mm/sec
Fresh (after cure)
25.47
26.91
27.42
27.28
27.15
27.65
After storage at 50°c
12 weeks
25.32
26.85
27.40
27.32
27.10
27.68
Pressure (bar)
120
140
160
180
200
220
Burnine Rate mm/sec
Fresh (after cure)
27.31
28.23
28.62
28.51
28.49
29.14
After storage at 50°c
12 weeks
27.20
28.19
28.60
28.45
28.47
29.16
45
The plateau burning rate was similar to that of Example 2 and there was no reduction of the burning rate after storage at 50°C
5
1,605,458
5
Example 4
The compositian of the cast double-base propellant of this Example was the same as Example 2 except that the casting powder contained only 2.0 parts of lead 6-resorcylate. The equilibrium water content of 5 the casting powder was o.51%. The propellant had similar plateau characteristics to Example 1 (fresh after cure): but there was no reduction in the burning rate after storage at 50°C. The burning rates are given below and are shown graphically in Fig. 2.
10
15
Example5
20
The composition of the cast double-base propellant of this Example was the same as Example 1 except that the casting liquid contained 3 parts of hexamethoxymethyl melamine instead of 3parts of triacetin. The equilibrium water content of the casting powder was 0.56%. The propellant had a plateau burning rate markedly higher than that of Example 1 and slightly higher than those of Examples 2 and 3, the 25 plateau occurring at a higher pressure level. The burning rate did not reduce on storage at 50°C. The burning rates are given below and shown graphically in Fig. 2.
30
35
Example 6
40 The cast double-base propellant of this Example was prepared with a lower energy casting powder containing as ballistic modifier lead stearate, (anhydrous, normal salt) in addition to lead. B-resorcylate and lead salicylate, and no aluminium. The equilibrium water content of the casting powder was 0.48% The following burning rates, which are graphically shown in Fig. 3 were observed. There was no 45 significant reduction in burning rate on storage at 50°C.
Pressure (bar)
60
80
100
120
140
160
Burning Rate mm/sec
Fresh (after cure)
12.81
13.75
13.68
13.46
15.20
17.04
After storage at 50°c
12 weeks
12.78
13.68
13.65
13.43
15.09
16.98
Pressure (bar)
80
100
120
140
160
180
Burning Rate mm/sec
Fresh (after cure)
21.35
22.94
23.59
23.75
23.03
21.94
After storage at 50°c
12 weeks
21.31
22.87
23.55
23.79
23.05
21.90
Pressure (bar)
120
140
160
180
200
220
Burning Rate mm/sec
Fresh (after cure)
29.16
30.55
31.48
31.66
31.49
31.43
After storage at 50°c
12 weeks
29.15
30.52
31.45
31.61
31.52
31.48
6
1,605,458
6
Example 7
The propellant of this Example had the same composition as Example 6 except that the casting liquid contained 3 parts of N,N'-bis(methoxymethyl)uron to replace 3 parts triacetin. The equilibrium water 5 content of the casting powder was 0.49%
The following burning rates, which are shown graphically in Fig. 3, were observed.
10
15
Pressure (bar)
60
80
100
120
140
160
Burning Rate mm/sec
Fresh (after cure)
14.16
16.21
16.85
16.79
15.87
17.40
After storage at 50°c
12 weeks
14.09
16.20
16.81
16.76
15.83
17.40
20
Example 7 had a significantly higher plateau burning rate than Example 6 which also was not. reduced by storage at 50°C.
Table 1 - Cdttoosirion3
Casting; Powder {Parts
N /
Componsnt
Example 1 1 |
Example 2
Eivair.pla
3
Example k
Exarcole
5"
*
Bzarupl e i 6 |
Example .
7
Jltrocolluic^o (12.6^ vf) ! "LkroftWce.r-.inf)
Ir*.«11 iy 1 -p-ru tr- o 6.y«iiI ne A lu:t i r,U;ai powder Carbon blue I:
Lead salicylate Lead 3-i*esorcylafca.
Lead gtearate
X, L1 -bl s {r,etho?:ynBthy 1)uron Graph!to g'laso Equilibrium wnter content
60.0 33.0 1 ,0
n £ 1 * Z>
0.3 3-0
5.o o.os 0.53'
60.0 33-0
1 .0 ■7 £
1 »7 0. }
3.0 i|..0 .
1.5 0.05
; 0.>?
;
60,0 33.0 ) .0
7.5 0.3 3-0 ij.,0
0.05
0.53
60.0 33-0 1 .0
7.5
0.3 3.0
2.0
1 -5 0.05
; 0/51
l
60.0
33-0
1.0 7.5 0.3 3-0 5.0
0.0?
0.56
80.0 13-5 - 1 .£
0.2 2.5 1 .0
1.5
0.05 [ O.itfi'
80.0 ! 13.5
1 .5 0.2
2.5 . 1 .0 1.5
0.05
o.i^
Casting Liquid (Percent)
■ ITitro glycerine ir'j.acBUi n
2~>":iti,»c diphonylfcL.i2ir.e il1 ~bi (xs thurcothy 1 )u;-on Lcxftr.e-choxyncwiiyl raelajaiike
76,0 23-0 1 ,0
76.0 23.0 1 .0
76. c
20.0 1 .0
3.0
76.0 23.0 i .0
76.0
20.0 1 .0
3.0
76.0 23.0 1 .0
76.0 20.0
1 1.0
i 3-0 j
oo
Table 1 (Continued)
Cast
Propellan t (Percent}
Component
Exasiple 1
Er-ir^ple
2
E;caFit>l6
3
Sx.irtrDle
I 4'
Example
5
Examole 6
Errir.ipl.C; 7
"iLr'C<.;«illulo3£- (12.63? ST) Xitro^Iyeerine " - no te 1 ly 1 - p - r. i t r o anil i ne Aiuminium powder'
Cr.rnc»n h'laok ^oocl sal inylafce Lc.'irl p-resorcylafce Loctfi ctor.rutc Triuinst*' n
2-n11 p o dj>honylonine 11, I."'-bis (s;cthoxyraethy 1)uron Renamecho;tytnafchyl melaraino Graphite p-lase
Powder/liquid ratio (w/w)
37.10
" 45.25
0.61 '4 • 64 0.19 1 .86 2.14?
7-52 0.33
0.03
&7 ■ 3/ 32,7
36.76 l.>lt. S3 6.62 4.60 0,16 • 1.P4 2.IS
7-4? 0.3? 0.92
0.03 67.6/ 32,4
37.20
45.17 0.61 4-65 0*19 1 .86 2.48
6.50
0.33 0,98
0.03 67,5/
32.5
37.44 45 >21
0.62 4 - 68
0.19 1.8?
1 >25
7 J;5 0.33 C.93
0.03 67.6/ 32.ii
37,01).
45.31 0.6*
lj. 6 li
0.^9
1 .05 2.U7
6.56 0.33
0.98 0.03 67.2/ 32.6
54-27
33.47
1 .02
0,1?; 1 .69 0,68 1 .02 7.36 0.32
0.03 68.0/ 32.0
54.09 33.60 1 . 0?
0.1 i|.
1,69 0.6.3
1 .02
6.L4
0.32 0.97
0. C 3 67.6/ 32.2 :
Heat of Explosion (KJ/E<
3)
j
Calculated heat of explosion
4560
44S8
4>8S
4585
4551
1
! I
4057 ' q0?d j
! I
OO
Claims (1)
- 91,605,4589WHAT WE CLAIM IS:1. A double-base propellant charge comprising at least one platonising lead salt and a nitrocellulose crosslinking compound having in its molecular structure two or more groups hav ing the formula -N-CH,-5 OR wherein R is hydrogen or an alkyl group containing 1 to 8 carbon atoms.2. A propellant charge as claimed in Claim 1 wherein the propellant composition comprises as basic ingredients from 35 to 55% w/w nitrocellulose, from 30 to 50% w/w of liquid nitric ester, from 0.5 to 2.0% w/w of the nitrocellulose crosslinking compounds specified in Claim I, from 1 to 5% w/w of lead10 salt ballistic modifier and from 1 to 3% w/w of stabiliser.3. A propellant charge as claimed in Claim 2 wherein the composition also comprises from 5 to 12% by weight of a nonexplosive plasticiser.15 4. A propellant charge as claimed in Claim 3 wherein the plasticiser comprises triacetin or dibutyl phthalate.5. A propellant charge as claimed in any one of Claims 2 to 4 wherein the stabiliser comprises 2-nitrodiphenylamine or N-methyl-p-nitro aniline.206. A propellant charge as claimed in any one of Claims lto 5 wherein the nitrocellulose crosslinking compound comprises a dimethylol or a dialkoxymethyl derivative of an amide, urea or cyclic urea or a methylol or an alkoxysnethyl derivative of melamine.25 7. A propellant charge as claimed in any one of Claims lto 6 wherein the crosslinking agent is present in an amount in the range from 0.5 to 2.0% w/w of the composition.8. A cast double-base propellant charge in accordance with any one of Claims 1 to 7 containing a platonising mixture of lead salicylate and lead B-resorcylate.309. A propellant charge as claimed in Claim 8 wherein the platonising mixture comprises lead salicylate and lead B-resorcylate in the weight ratio of from 4:1 to 1:4.10. A double-base propellant charge substantially as herein described with particular reference to any one 35 of Examples 2 to 5 inclusive and Example 7.BAE Systems pic Group, IP Department, Lancaster House, PO Box 87, Famborough Aerospace Centre, Famborough, Hampshire, GUM 6YU
Priority Applications (4)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB2343575A GB1605458A (en) | 1975-05-29 | 1975-05-29 | Double-base propellant |
| AU13950/76A AU785509B1 (en) | 1975-05-29 | 1976-05-14 | Double-base propellant |
| DE19762623991 DE2623991B3 (en) | 1975-05-29 | 1976-05-28 | Double base propellant charge |
| FR7616154A FR2904625A1 (en) | 1975-05-29 | 1976-05-28 | Double base propellant filler, useful to produce gas and charge of rockets and rocket reactors, comprises lead salt to obtain plane/plateau in the logarithmic curve of combustion speed according to log pressure and nitrocellulose |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB2343575A GB1605458A (en) | 1975-05-29 | 1975-05-29 | Double-base propellant |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB1605458A true GB1605458A (en) | 2008-12-17 |
Family
ID=38922389
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB2343575A Active GB1605458A (en) | 1975-05-29 | 1975-05-29 | Double-base propellant |
Country Status (4)
| Country | Link |
|---|---|
| AU (1) | AU785509B1 (en) |
| DE (1) | DE2623991B3 (en) |
| FR (1) | FR2904625A1 (en) |
| GB (1) | GB1605458A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2016525992A (en) * | 2013-04-25 | 2016-09-01 | フィッシャーヴェルケ ゲゼルシャフト ミット ベシュレンクテル ハフツング ウント コンパニー コマンディートゲゼルシャフトｆｉｓｃｈｅｒｗｅｒｋｅ ＧｍｂＨ ＆ Ｃｏ． ＫＧ | Electrically ignitable caseless propellant, its manufacturing method and use |
-
1975
- 1975-05-29 GB GB2343575A patent/GB1605458A/en active Active
-
1976
- 1976-05-14 AU AU13950/76A patent/AU785509B1/en not_active Expired - Fee Related
- 1976-05-28 FR FR7616154A patent/FR2904625A1/en active Pending
- 1976-05-28 DE DE19762623991 patent/DE2623991B3/en not_active Expired - Lifetime
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2016525992A (en) * | 2013-04-25 | 2016-09-01 | フィッシャーヴェルケ ゲゼルシャフト ミット ベシュレンクテル ハフツング ウント コンパニー コマンディートゲゼルシャフトｆｉｓｃｈｅｒｗｅｒｋｅ ＧｍｂＨ ＆ Ｃｏ． ＫＧ | Electrically ignitable caseless propellant, its manufacturing method and use |
Also Published As
| Publication number | Publication date |
|---|---|
| FR2904625A1 (en) | 2008-02-08 |
| AU785509B1 (en) | 2010-04-29 |
| DE2623991B3 (en) | 2008-02-14 |
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