CA1265344A - Propellant charge for tubular weapons and a process for the production thereof - Google Patents
Propellant charge for tubular weapons and a process for the production thereofInfo
- Publication number
- CA1265344A CA1265344A CA000470528A CA470528A CA1265344A CA 1265344 A CA1265344 A CA 1265344A CA 000470528 A CA000470528 A CA 000470528A CA 470528 A CA470528 A CA 470528A CA 1265344 A CA1265344 A CA 1265344A
- Authority
- CA
- Canada
- Prior art keywords
- propellant charge
- powder
- firing temperature
- powders
- homogeneous
- 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.)
- Expired - Fee Related
Links
Classifications
-
- 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
Landscapes
- Chemical & Material Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Organic Chemistry (AREA)
- Manufacture Of Metal Powder And Suspensions Thereof (AREA)
- Cosmetics (AREA)
- Organic Low-Molecular-Weight Compounds And Preparation Thereof (AREA)
- Medicinal Preparation (AREA)
- Ceramic Products (AREA)
Abstract
ABSTRACT
A propellant charge for tubular weapons with almost constant burning behavior in a rated reference temperature range is produced from a mixture of at least one mono- or polybasic homogeneous propellant charge powder, of which the particles are of homogeneous material, with at least one heterogeneous propellant charge powder of which the particles consist of a mono- or polybasic base powder with mono- or polybasic powder granulates embedded therein and which, by virtue of its heterogeneous composition, has a pressure characteristic with a negative firing temperature coefficient. The powders have similar heat of explosion, force and particle size, and are mixed in proportions such as to provide the desired constant burning behavior.
A propellant charge for tubular weapons with almost constant burning behavior in a rated reference temperature range is produced from a mixture of at least one mono- or polybasic homogeneous propellant charge powder, of which the particles are of homogeneous material, with at least one heterogeneous propellant charge powder of which the particles consist of a mono- or polybasic base powder with mono- or polybasic powder granulates embedded therein and which, by virtue of its heterogeneous composition, has a pressure characteristic with a negative firing temperature coefficient. The powders have similar heat of explosion, force and particle size, and are mixed in proportions such as to provide the desired constant burning behavior.
Description
~53~L~
A propellant charge for tubular weapons and a process for the production thereof BACKGROUND OF THE INVENTION
. .
FIELD OF THE INVENTION
-This invention relates to propellant charges consisting of propellant charge powders, the energy carriers of which consist of nitrocelluloses or nitrocelluloses and nitroglycerols or nitrocelluloses, nitroglycerols, nitroguanidine and/or hexogen or octogen, that is of propellant charge powders which are designated as mono-, di- or tri basic propellant eharge powders.
D SCRIPTION OF THE PRIOR ART
Propellant cnarge powders with the above compositions can be prepared as solid- porous- or tubular-type powders. Mono-basic propellant charge powders have to be prepared with suitable solvents, such as ether, alcohol and acetone to gelatinate the nitrocelluloses~
Di- and tri-basic propellant charge powders having a suitable composition can be prepared without solvents.
They are known as PoL powders.
It is generally held that, all components are most auitab1y mixed toyether in the production of mono-, di~
or tri-basic propellant charge powders, so that the base compos~ition uf the finished powder has a homogeneous composition.
~k -, ~ :
. .:: , The surface treatment optionally carried out on bulk powders can be left out of consideration in this case.
These conventional propellant charge powders generally used in tubular weapons are designated as "homogeneous powders" within the context of the present application.
A characteristic of "homogeneous powders" is that their rate of combustion increases as the firi~g or surrounding temperature rises. This means that, when the weapon is fired, the projectile speed is substantially slower at a firing temperature of, for example, -40 C
than at a iring temperature of, for example, ~60 C
when propellant charges of "homogeneous powders" are used. The temperature-dependent performance of the propellant charges causes substantial problems for guns for armoured vehicles, for example with regard to reliable first strike capability and to the projectile performance which is restricted by the weapon pressure produced at high temperatures, such as +60 C.
Propellant charge powders which do not experience ~ the increase in the rate of combustion as the : temperature rises, oharacterlstic ~of "homogeneous powders", are described in DE-PS 17 71 087, DE-PS
A propellant charge for tubular weapons and a process for the production thereof BACKGROUND OF THE INVENTION
. .
FIELD OF THE INVENTION
-This invention relates to propellant charges consisting of propellant charge powders, the energy carriers of which consist of nitrocelluloses or nitrocelluloses and nitroglycerols or nitrocelluloses, nitroglycerols, nitroguanidine and/or hexogen or octogen, that is of propellant charge powders which are designated as mono-, di- or tri basic propellant eharge powders.
D SCRIPTION OF THE PRIOR ART
Propellant cnarge powders with the above compositions can be prepared as solid- porous- or tubular-type powders. Mono-basic propellant charge powders have to be prepared with suitable solvents, such as ether, alcohol and acetone to gelatinate the nitrocelluloses~
Di- and tri-basic propellant charge powders having a suitable composition can be prepared without solvents.
They are known as PoL powders.
It is generally held that, all components are most auitab1y mixed toyether in the production of mono-, di~
or tri-basic propellant charge powders, so that the base compos~ition uf the finished powder has a homogeneous composition.
~k -, ~ :
. .:: , The surface treatment optionally carried out on bulk powders can be left out of consideration in this case.
These conventional propellant charge powders generally used in tubular weapons are designated as "homogeneous powders" within the context of the present application.
A characteristic of "homogeneous powders" is that their rate of combustion increases as the firi~g or surrounding temperature rises. This means that, when the weapon is fired, the projectile speed is substantially slower at a firing temperature of, for example, -40 C
than at a iring temperature of, for example, ~60 C
when propellant charges of "homogeneous powders" are used. The temperature-dependent performance of the propellant charges causes substantial problems for guns for armoured vehicles, for example with regard to reliable first strike capability and to the projectile performance which is restricted by the weapon pressure produced at high temperatures, such as +60 C.
Propellant charge powders which do not experience ~ the increase in the rate of combustion as the : temperature rises, oharacterlstic ~of "homogeneous powders", are described in DE-PS 17 71 087, DE-PS
2~ 42 457 and DE-OS 30 08 196.
The energy carriers of these propellant charge . -: .
pWders are the same as those used in conventional"homogeneous powders". The fundamental difference is in the material structure of the powder composition.
The production of the powder composition S illustrates this point. Mono-, di- or tri-basic bulk powders, termed granulate, of suitable dimensions are incorporated into the kneading composition, termed base composition, of a monobasic propellant charge powder.
The degree of nitration of the nitrocelluloses used for the production of granulate and base composition are selected, such that the granulate remains as granulate during production of the powders.
These types of powder are known as "HET powdersl ~
owing to the heterogeneous structure of the grain of the powder which becomes a powder base composition by the incorporation of a granulate.
"HET-powders" have a funda~entally different temperature-dependence from "homogeneous powders'l.
As the firing temperature rises, their rate of combustion descreases.
The "negatlve" temperature-dependence of the rate of combustion of HET powders can be explained by the fact that the connection between t:he base composition and the granulate is temperature-dependent. If, for example, the base compositlon ismonobasic and the granulate is dibasic~ the connection ;
j ~, ,.
~; , ,: ., . :
'- ~
. ~ 2Ç~3~
becomes stronger as the temperature rises, through the expansion of the thermoplastic granulate into the comparatively rigid base composition. Consequently the combustion surface forming in the grain of the powder becomes smaller. Larger combustion surfaces are formed in the grain of the powder at sub-freezing temperatur~ due to the greater contraction of the granulate~ The given fall in the rate of combustion as the temperature drops is over-compensated into a rise, at least down to a specific low firing temperature of, for example, -15 C,as a result of the increase in the combustion surfaces at sub-freezing temperatures and the reduction in the combustion surfaces as the temperature rises.
The composition of the base mass and the granulates, the proportion of granulate and the size of the granules are factors by which the temperature behaviour of an "HET powder" may be controlled, that is to what extent the rate of combustion falls as the temperature rises and rises as the temperature falls.
/ Burning "HET-powders n should advantageously be completely temperature-neutral. However, this is imposs1ble with known types of powder, within a relati~ely large firing temperature range of several tens of C,~with predetermined heat of explosion, force and propellant charge powder dimensions.
~;
.: .,, . .:
,, .~.. , .;. . ....
:
: ,. :::
.:
:, :. :
. , ~53~
BRIEF SUMMARY OF THE INVENTION
Propellant charges with burning behavior which is temperature-neutral within a large firing temperature range can be obtained in a surprisingly straightforward manner according to the present invention. According to the invention, there is provided a propellant charge for tubular weapons, consisting of a mixture of at least one mono- or polyhasic homogeneous propellant charge powder, of which the particles are of homogeneous material, with at least one heterogeneous propellant charge powder of which the particles consist of a mono- or polybasic base powder with mono- or polybasic powder granulates embedded therein and which, by virtue of its heterogeneous composition, has a pressure characteristic with a negative firing temperature coefficient; wherein the propellant charge powders are adjusted to the same or comparable characteristic values in regard to heat of explosion, force and dimensions; and wherein the mixing ratio between the propellant charge powders is selected so that, in a desired, predetermined nominal firing temperature range, the positive firing temperature coefficient of the homogeneous propellant charge powder is compensated by the negative firing temperature coefficient of the heterogeneous propellant charge powder to give substantially constant burning behavior of the propellant charge.
Outside of the nominal firing temperature range, a drop in weapon pressure is occasionally consciously sought at extremely low firing temperatures in order to guarantee against an accidental rise in weapon pxessure owing to the powder becoming brittle at such temperatures. Likewise, a drop in weapon pressure at unusually high, and thus infrequent, firing temperature is acceptable. Such burning behavior of the finished propellant charge can be obtained by suitable selection of the types of powder to be mixed and the....
., j , ~.,"ri ' . " ' ;~" '' `' ' ' ; '', "' '.
mixing ratio, such that the burning characteristics, such as weapon pressure ~nd projectile speed are almost constant within a relatively large firing temperature rated range, and at least do not increase outside the rated range.
DETAILED DESCRIPTION OF THE INV~NTION
Advantageous embodimen~ of the present invention are disclosed in the various sub-claims appended to this description.
The present invention will be explained in more detail in the following two Examples with reference to Figures 1 and 2.
Figures l and 2 show the measured values of weapon pressure and projectile speed ln the firing temperature range of from -40 C to +60 C for a 2 cm automatic weapon. Part A shows the projectile speeds measured at 16 m from the weapon, and part B shows the weapon pressuresmeasured.
Example 1 An adapted "HET powder" is developed into a "homvgeneous powder" which ls used in one type of ammunition for structuring the propel~lantcharge. This means that the heat of explosion, force and the dimensions of the "HET powder" are set at the same values as, or at comparable values to, the "homogeneous powder", by .
,. `'" ~ , ~
.. ,.. ,. , ~ . ; :
.
.' ', :: . ` -.,,. ~ ,~. ..
.
~%~
a suitable selection of the composition of the base mass and granulate~ and the quantity of granulate. The "HET
powder" is adjusted to the "homogeneous powder" such that, when the weapon is fired, at a reference firing temperature of, for example, from -5 to ~10 C the same projectile speed is produced, at the same or comparable pressure pattern,as in the case of propellant charges consisting of "homogeneou~" or "HET powders".
If these conditions are fulfilled, the pressure and speed curves of the "homogeneous" and "HET powders" are mirror-inverted with respect to rising and falling firing temperatures.
If the propellant charge consists of a mixture, of the same proportion by weight, of "homogeneous powder" and "HET powder" which has been adjusted thereto as explained above, the weapon pressure and the projectile speed are almost constant in the firing temperature ra~ge of:from -40 C to +60 C.
In Figure 1~ the curves designated by reference numeral 1 show the values for weapon pressure and projectlle speed, obtained with the "homogeneous : propellant charge powder" used for this ammunition.
The curves designated by reference numeral 2 show the values obtained with the adjusted "HET powder".
The curves designated ~y reference numeral 3 show the ;
values obtalned with a mixture~ of the same proportions by welght, of both powders.
:, ,., :. .
: , . . .
~: .
.: .. : :. : : , -, :
The energy carriers of these propellant charge . -: .
pWders are the same as those used in conventional"homogeneous powders". The fundamental difference is in the material structure of the powder composition.
The production of the powder composition S illustrates this point. Mono-, di- or tri-basic bulk powders, termed granulate, of suitable dimensions are incorporated into the kneading composition, termed base composition, of a monobasic propellant charge powder.
The degree of nitration of the nitrocelluloses used for the production of granulate and base composition are selected, such that the granulate remains as granulate during production of the powders.
These types of powder are known as "HET powdersl ~
owing to the heterogeneous structure of the grain of the powder which becomes a powder base composition by the incorporation of a granulate.
"HET-powders" have a funda~entally different temperature-dependence from "homogeneous powders'l.
As the firing temperature rises, their rate of combustion descreases.
The "negatlve" temperature-dependence of the rate of combustion of HET powders can be explained by the fact that the connection between t:he base composition and the granulate is temperature-dependent. If, for example, the base compositlon ismonobasic and the granulate is dibasic~ the connection ;
j ~, ,.
~; , ,: ., . :
'- ~
. ~ 2Ç~3~
becomes stronger as the temperature rises, through the expansion of the thermoplastic granulate into the comparatively rigid base composition. Consequently the combustion surface forming in the grain of the powder becomes smaller. Larger combustion surfaces are formed in the grain of the powder at sub-freezing temperatur~ due to the greater contraction of the granulate~ The given fall in the rate of combustion as the temperature drops is over-compensated into a rise, at least down to a specific low firing temperature of, for example, -15 C,as a result of the increase in the combustion surfaces at sub-freezing temperatures and the reduction in the combustion surfaces as the temperature rises.
The composition of the base mass and the granulates, the proportion of granulate and the size of the granules are factors by which the temperature behaviour of an "HET powder" may be controlled, that is to what extent the rate of combustion falls as the temperature rises and rises as the temperature falls.
/ Burning "HET-powders n should advantageously be completely temperature-neutral. However, this is imposs1ble with known types of powder, within a relati~ely large firing temperature range of several tens of C,~with predetermined heat of explosion, force and propellant charge powder dimensions.
~;
.: .,, . .:
,, .~.. , .;. . ....
:
: ,. :::
.:
:, :. :
. , ~53~
BRIEF SUMMARY OF THE INVENTION
Propellant charges with burning behavior which is temperature-neutral within a large firing temperature range can be obtained in a surprisingly straightforward manner according to the present invention. According to the invention, there is provided a propellant charge for tubular weapons, consisting of a mixture of at least one mono- or polyhasic homogeneous propellant charge powder, of which the particles are of homogeneous material, with at least one heterogeneous propellant charge powder of which the particles consist of a mono- or polybasic base powder with mono- or polybasic powder granulates embedded therein and which, by virtue of its heterogeneous composition, has a pressure characteristic with a negative firing temperature coefficient; wherein the propellant charge powders are adjusted to the same or comparable characteristic values in regard to heat of explosion, force and dimensions; and wherein the mixing ratio between the propellant charge powders is selected so that, in a desired, predetermined nominal firing temperature range, the positive firing temperature coefficient of the homogeneous propellant charge powder is compensated by the negative firing temperature coefficient of the heterogeneous propellant charge powder to give substantially constant burning behavior of the propellant charge.
Outside of the nominal firing temperature range, a drop in weapon pressure is occasionally consciously sought at extremely low firing temperatures in order to guarantee against an accidental rise in weapon pxessure owing to the powder becoming brittle at such temperatures. Likewise, a drop in weapon pressure at unusually high, and thus infrequent, firing temperature is acceptable. Such burning behavior of the finished propellant charge can be obtained by suitable selection of the types of powder to be mixed and the....
., j , ~.,"ri ' . " ' ;~" '' `' ' ' ; '', "' '.
mixing ratio, such that the burning characteristics, such as weapon pressure ~nd projectile speed are almost constant within a relatively large firing temperature rated range, and at least do not increase outside the rated range.
DETAILED DESCRIPTION OF THE INV~NTION
Advantageous embodimen~ of the present invention are disclosed in the various sub-claims appended to this description.
The present invention will be explained in more detail in the following two Examples with reference to Figures 1 and 2.
Figures l and 2 show the measured values of weapon pressure and projectile speed ln the firing temperature range of from -40 C to +60 C for a 2 cm automatic weapon. Part A shows the projectile speeds measured at 16 m from the weapon, and part B shows the weapon pressuresmeasured.
Example 1 An adapted "HET powder" is developed into a "homvgeneous powder" which ls used in one type of ammunition for structuring the propel~lantcharge. This means that the heat of explosion, force and the dimensions of the "HET powder" are set at the same values as, or at comparable values to, the "homogeneous powder", by .
,. `'" ~ , ~
.. ,.. ,. , ~ . ; :
.
.' ', :: . ` -.,,. ~ ,~. ..
.
~%~
a suitable selection of the composition of the base mass and granulate~ and the quantity of granulate. The "HET
powder" is adjusted to the "homogeneous powder" such that, when the weapon is fired, at a reference firing temperature of, for example, from -5 to ~10 C the same projectile speed is produced, at the same or comparable pressure pattern,as in the case of propellant charges consisting of "homogeneou~" or "HET powders".
If these conditions are fulfilled, the pressure and speed curves of the "homogeneous" and "HET powders" are mirror-inverted with respect to rising and falling firing temperatures.
If the propellant charge consists of a mixture, of the same proportion by weight, of "homogeneous powder" and "HET powder" which has been adjusted thereto as explained above, the weapon pressure and the projectile speed are almost constant in the firing temperature ra~ge of:from -40 C to +60 C.
In Figure 1~ the curves designated by reference numeral 1 show the values for weapon pressure and projectlle speed, obtained with the "homogeneous : propellant charge powder" used for this ammunition.
The curves designated by reference numeral 2 show the values obtained with the adjusted "HET powder".
The curves designated ~y reference numeral 3 show the ;
values obtalned with a mixture~ of the same proportions by welght, of both powders.
:, ,., :. .
: , . . .
~: .
.: .. : :. : : , -, :
3~g~
-- 8~ --Example 2 Example 2 differs from Example 1 in that the "~ET powder" used is structured, such that from the reference firing temperature of 0 C, thle weapon pressure drops as the temperature rises and falls.
In Figure 2, the curves designated by reference numeral 1 show the values of the "homogeneous powder", the curves designated by reference numeral 2 show the 10 values of the "HET powder" and the curves deslgnated by reference numeral 3 give the values with a mixture, of equal proportions by weight, of both powders.
~' ~
, ~ 25 :
.
' ,:
:~
-: ~ , :. . .
. ,~ .. ,. : , ~ ,
-- 8~ --Example 2 Example 2 differs from Example 1 in that the "~ET powder" used is structured, such that from the reference firing temperature of 0 C, thle weapon pressure drops as the temperature rises and falls.
In Figure 2, the curves designated by reference numeral 1 show the values of the "homogeneous powder", the curves designated by reference numeral 2 show the 10 values of the "HET powder" and the curves deslgnated by reference numeral 3 give the values with a mixture, of equal proportions by weight, of both powders.
~' ~
, ~ 25 :
.
' ,:
:~
-: ~ , :. . .
. ,~ .. ,. : , ~ ,
Claims (4)
PROPERTY OR PRIVILEGE IS CLAIMED ARE DEFINED AS FOLLOWS :
1. A propellant charge for tubular weapons, consisting of a mixture of at least one mono- or polybasic homogeneous propellant charge powder, of which the particles are of homogeneous material, with at least one heterogeneous propellant charge powder of which the particles consist of a mono- or polybasic base powder with mono- or polybasic powder granulates embedded therein and which, by virtue of its heterogeneous composition, has a pressure characteristic with a negative firing temperature coefficient; wherein the propellant charge powders are adjusted to the same or comparable characteristic values in regard to heat of explosion, force and dimensions; and wherein the mixing ratio between the propellant charge powders is selected so that, in a desired, predetermined nominal firing temperature range, the positive firing temperature coefficient of the homogeneous propellant charge powder is compensated by the negative firing temperature coefficient of the heterogeneous propellant charge powder to give substantially constant burning behavior of the propellant charge.
2. A propellant charge as claimed in claim 1, wherein the propellant charge powders of the mixture all produce the same ballistic performance for the same weapon pressure at a predetermined reference value of the firing temperature.
3. A propellant charge as claimed in claim 2, wherein the predetermined reference value of the firing temperature is 21°C.
4. A propellant charge as claimed in claim 1 or 2, wherein the proportion of homogeneous propellant charge powder in the propellant charge is approximately 20 to 40 parts by weight.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DEP3346287.9 | 1983-12-21 | ||
| DE19833346287 DE3346287A1 (en) | 1983-12-21 | 1983-12-21 | DRIVING CHARGE FOR TUBE ARMS AND METHOD FOR THEIR PRODUCTION |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1265344A true CA1265344A (en) | 1990-02-06 |
Family
ID=6217613
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA000470528A Expired - Fee Related CA1265344A (en) | 1983-12-21 | 1984-12-19 | Propellant charge for tubular weapons and a process for the production thereof |
Country Status (6)
| Country | Link |
|---|---|
| EP (1) | EP0150431B1 (en) |
| CA (1) | CA1265344A (en) |
| DE (2) | DE3346287A1 (en) |
| ES (1) | ES8800120A1 (en) |
| IL (1) | IL73741A (en) |
| PT (1) | PT79719B (en) |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0767155B1 (en) * | 1995-10-06 | 2000-08-16 | Autoliv Asp, Inc. | Heterogeneous gas generant charges |
| DE19635795C2 (en) * | 1996-09-04 | 2002-09-26 | Rheinmetall W & M Gmbh | Propellant charge for barrel weapons |
| DE19907809C2 (en) | 1999-02-24 | 2002-10-10 | Nitrochemie Gmbh | Process for the production of one-, two- or three-base propellant charge powders for gun ammunition |
| DE102011118547B4 (en) * | 2011-11-16 | 2013-06-27 | Diehl Bgt Defence Gmbh & Co. Kg | Method for predicting the burn-up behavior of a propellant charge powder |
| EP3495338A1 (en) | 2017-12-08 | 2019-06-12 | Nederlandse Organisatie voor toegepast- natuurwetenschappelijk onderzoek TNO | Propellant charge |
| CN113149796A (en) * | 2021-05-10 | 2021-07-23 | 雷存炬 | Integrated nail propellant and preparation method thereof |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3718094A (en) * | 1962-07-30 | 1973-02-27 | North American Aviation Inc | Gas generator charge with decreased temperature sensitivity |
| DE2042457C3 (en) * | 1968-04-01 | 1975-06-19 | Wilhelm Dipl.-Chem Dr. 5400 Koblenz Oversohl | Process for the production of a single- or multi-base propellant charge powder |
| DE1771087C3 (en) * | 1968-04-01 | 1973-09-27 | Wilhelm Dipl.-Chem Dr. 5400 Koblenz Oversohl | Monobasic or polybasic propellant charge powder and process for its manufacture |
| FR2234246B1 (en) * | 1973-06-19 | 1976-09-17 | Poudres & Explosifs Ste Nale | |
| DE3008196A1 (en) * | 1980-03-04 | 1981-09-17 | Wilhelm Dipl.-Chem. Dr. 5400 Koblenz Oversohl | Explosive charge contains powder and granulate - of similar or different composition and combustion rate |
-
1983
- 1983-12-21 DE DE19833346287 patent/DE3346287A1/en not_active Withdrawn
-
1984
- 1984-12-05 IL IL73741A patent/IL73741A/en not_active IP Right Cessation
- 1984-12-18 DE DE8484115678T patent/DE3480649D1/en not_active Expired - Fee Related
- 1984-12-18 ES ES538754A patent/ES8800120A1/en not_active Expired
- 1984-12-18 EP EP84115678A patent/EP0150431B1/en not_active Expired
- 1984-12-19 CA CA000470528A patent/CA1265344A/en not_active Expired - Fee Related
- 1984-12-20 PT PT79719A patent/PT79719B/en not_active IP Right Cessation
Also Published As
| Publication number | Publication date |
|---|---|
| DE3480649D1 (en) | 1990-01-11 |
| EP0150431B1 (en) | 1989-12-06 |
| PT79719B (en) | 1987-07-13 |
| IL73741A0 (en) | 1985-03-31 |
| IL73741A (en) | 1989-12-15 |
| DE3346287A1 (en) | 1985-07-04 |
| EP0150431A1 (en) | 1985-08-07 |
| PT79719A (en) | 1985-01-01 |
| ES538754A0 (en) | 1987-11-01 |
| ES8800120A1 (en) | 1987-11-01 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US9199887B2 (en) | Propellant compositions including stabilized red phosphorus and methods of forming same | |
| US5567912A (en) | Insensitive energetic compositions, and related articles and systems and processes | |
| US3682727A (en) | Igniter charge for propellant compositions and rocket propellant charges | |
| US4131498A (en) | Metallic sponge incendiary compositions | |
| US3309249A (en) | Thermite-resin binder solid fuel composition | |
| US3730094A (en) | Energetic protective coating for caseless ammunition | |
| CA1265344A (en) | Propellant charge for tubular weapons and a process for the production thereof | |
| US4519855A (en) | Mixed charges for ammunitions with a casing constituted by agglomerated propellant powder and propellant powder in grain form | |
| US2929697A (en) | Propellants for rockets and process of making | |
| GB2092274A (en) | Projectiles | |
| US5035756A (en) | Bonding agents for thermite compositions | |
| US3732132A (en) | Extrudable fluorocarbon propellants | |
| US3841929A (en) | Solid propellant containing strontium carbonate-calcium citrate burning rate depressant | |
| US5468312A (en) | Ignition-sensitive low-vulnerability propellent powder | |
| US2425854A (en) | Propellent powder | |
| US3386868A (en) | Heat resistant propellants containing organic oxidizers | |
| US4508580A (en) | Incendiary mixture constituted of metals | |
| CA1090582A (en) | Unit charges of propellant powder | |
| US3718094A (en) | Gas generator charge with decreased temperature sensitivity | |
| US3017300A (en) | Pelleted igniter composition and method of manufacturing same | |
| US11112222B2 (en) | Propellant with pattern-controlled burn rate | |
| US5320692A (en) | Solid fuel ramjet composition | |
| US4952341A (en) | Mechanical enhancement of the burning rate of solid propellants by means of shrink tubes or spheres | |
| US3738878A (en) | High burning rate solid propellant having a silicon-carboranyl copolymer fuel binder | |
| US4239073A (en) | Propellants in caseless ammunition |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| MKLA | Lapsed |