CA1326597C - Combustion inhibitors - Google Patents
Combustion inhibitorsInfo
- Publication number
- CA1326597C CA1326597C CA000198626A CA198626A CA1326597C CA 1326597 C CA1326597 C CA 1326597C CA 000198626 A CA000198626 A CA 000198626A CA 198626 A CA198626 A CA 198626A CA 1326597 C CA1326597 C CA 1326597C
- Authority
- CA
- Canada
- Prior art keywords
- carbon
- filler
- composition according
- copolymer
- composition
- 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
- C06B45/12—Compositions or products which are defined by structure or arrangement of component of product having contiguous layers or zones
Landscapes
- Chemical & Material Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Organic Chemistry (AREA)
- Compositions Of Macromolecular Compounds (AREA)
- Liquid Carbonaceous Fuels (AREA)
- Agricultural Chemicals And Associated Chemicals (AREA)
Abstract
A B S T R A C T
An inhibitor for a solid propellant charge including a copolymer of ethylene or other suitable hydrocarbon with one or more components selected from the group methyl methacrylate, methacrylic acid, acrylic acid, methyl acrylate and hydroxy ethyl methacrylate. Fillers and other additions may be included.
An inhibitor for a solid propellant charge including a copolymer of ethylene or other suitable hydrocarbon with one or more components selected from the group methyl methacrylate, methacrylic acid, acrylic acid, methyl acrylate and hydroxy ethyl methacrylate. Fillers and other additions may be included.
Description
This invention re]ates to inhibitors for solid propellants, and has particular but not e~clusive reference to low smoke ~eneIating inhibitors.
; The invention al90 provides a composition which9 as well as being capable of use as a combustion inhibitor, also has other applications in a rocket motor combustion chamber.
Solid propellant rocket motors include a charge of propellant, an inhibitor on certain parts o~ the charge to control the area of burning surface, and an outer case. The inhibitor is used to control locally the ! burning area of the propellant so that the charge burns in the desired `, 10 geometricel manner. The inhibitor needs to be chemically and physically compatible with the charge. The inhlbitor may be completely or partially consumed during the firing of the rocket motor.
If a rocket motor ernits smoke, the trail can betray the firing point of the missile, and its trajectory. E~haust smoke obscures the target and missile from the person firing the missile which is particularly dis-advantageous if the missile is being visually guided along the line of sight to its target. Thus, frequently one of the major requirements of a rocket motor is that smoke emission during combustion should be as low as possible.
This condition is provided by the use of double base propellant, but inert p~rts, largely the charge inhibitor, prevent the achievement of a "smokeless"
e~haust.
Ad~tionally propellant charges are widely used as g~s generators or power cartridges for mechanical operatio~q and in such circumstances smoke condensate is a nuisance because it can foul the area into which it is discharged, and cause interference with valve mechanisms and moving surfaces.
The term "double base propellant" where used in this specification includes nitrocellulose with nitroglycerine or other liquid nitric ester with or without other additives, chemical stabilisers, plasticisers, balli~tic js . ';
, . .
; `- 1 326597 73117-3 . . . modifiers, fuel~ such as aluminium powder, and oxidisers such as ammonium perchlorate.
By the present invention, there is provided a composition for use in conjunction with but distinct from a solid propellant charge, the composition including a copolymer of a hydrocarbon carbon-carbon chain-forming material with at least one component chosen from the group consisting of methyl methacrylate, methacrylic acid, acrylic acid, methyl acrylate~ and hydroxy ethyl methacrylate.
Preferably, the composition includes a copolymer of the hydrocarbon carbon-carbon chain-forming material with at least two components chosen from the group speclfied above.
The present invention also consists in the use of the composition referred to above as a combustion inhibitor for use bonded to a solid propellant charge. The present in~ention also provides a solid propellant charge having a combustion inhibitor bonded on at least part of the surface thereof, the combustion inhibitor including a copolymer of a hydrocarbon carbon-carbon chain-forming material wlth at least one component chosen from the group consisting of methyl methacrylate, methacrylic acid, acrylic acid, methyl acrylate, and hydroxy ethyl methacrylate.
By the term "hydrocarbon carbon-carbon chain-forming material" is meant a hydrocarbon material capable of polymerisation to form a long chain carbon to carbon back-bone polymerised material.
. ~ .
;... .: ., :::,: .
., :
-., ;:
' ;
~:; 73117-3 , .
. The hydrocarbon material is preferahly ethylene and may ~: he presenk in an amount of a~ least 75% of the copolymer matrix.
. There may be a filler or fillers in the inhibitor which may be chosen from compounds having a low carbon to oxygen ratio of 1:1 or less, such as cellulose, carbohydrates, oxamide, . polyoxymethylene, urea formaldehyde, urea oxalate, and tartaric .l acid. Other suitable fillers are in particulate form -3a-~" ~
/
'. ~ '.- ~
1 3~65~7 and are elemental carbon and oxides, hydroxides, carbonates, and nitrates of at least one element selected from:
~ (a) magnesium, calcium, zinc, strontium, cadmium and barium;
``~ (b~ boron and aluminium;
(c) silicon and titanium;
(d) arsenic, antimony and bismuth; and ~ (e) iron, cobalt and nickel.
:.j :~! If it i9 required to produce a smokeless or approximately smokeless charge, the filler material to be used in the inhibitor and the size of the particles are such that exposure of the filled inhibitor to the combustion of the propellant charge in the rocket motor chamber or other combustion chamber results in a product wholly gaseous or containing particles which are of a si~e less than 1 micron or greater than 15 microns~
It can be understood from the above that for a chosen filler material, only a simple experiment is needed to decide if the sizes of the particles ~; of filler material in the combustion inhibition material are important, and f so which sizes are appropriate.
When it is required to produce a smokeless inhibitor, the presence of ;J the fillers can reduce the carbon to oxygen ratio for the filled inhibitor 33 20 material to below 2:1, preferably below 1.5:1.
By way of example, examples of the invention will now be described.
Bxample 1 Ethylene, meth~crylic acid and methyl methacrylate are copolymerised.
The proportions are 15,at of metkacrylic acid, CH3-CH ~ -H + 15~ methyl i 25 methacrylate CH~-CH=Ç-H + 70~ ethylene CH2 = CH2. ~OOCH3 Alternatively the above copolymer can be modified by copolymerisation with the additire hydroxyethyl methacrylate CH2 = C, - C~20 OOC ~5 `l ``
, : ~
.
~` 1 326597 The above copolymers usin~ flllers of the type previously de~cribed can be loaded up to a level of 3:1 by wei~ht of filler to ~atrix, or higher.
~he filler and copolymer may be milled together to for~ a thoroughly mixed crepe. The mix of milled filler/polymer crepe is formed essentially by melting the copolymer mixture and mixing in the filler ~hich is encapsulated 3 by the molten copoly~er mixture. The molten copolymer and filler mixture is thereby formed into slabs, l~hich can be used for moulding or pressing sheets.
The product of the above method of mixing can also be granulated and re~
processed as the feed stook for extru~ion of tubes or shect.
~ 10 In an alternative method of forming the mi~ture, the copolymer and i fillers are separately ground to fine powder, and the powder mix is then formed into sheets and slabs under the action of pressure and heat, the temperature of the powder during the pressing operation being maintained at typically 110 to 150 C, at a pres~ure of typically 100 kilograms/cm or higher. The sheet~ and slabs can then be moulded to any desired shape to i provide inhibitors.
~xample 2 In a second example of the invention, 20 parts of acrylic acid l CH2 = ,C-H , 15 parts methyl acrylate C~2 = Ç-H and 65 parts of ethylene j~ COOH ~OOC~
C~2 = C~2 are copolymerised. To 100 parts of the copolymer mixture is added 50 parts polyoxymethylene (CH20)n.
The components are blended together and the blend is then pressed at - 130C to give sheets and slabs. Alternstively, any of the above methods described may also be used.
,.
The amount of copolymerisation may be ~djusted to alter the physical properties of the solid inhibitor and can control the rubberiness of the inhibitor.
If the smokelessness is not req11ired, any normal rubber or plastics additives may be used~ Also the inhibitor may be used for solid :, . . . .
,, , . ~ .
. .
,!
~ ~ 326597 propellants other than double base propellants, ie composite propellants.
~owever, one of the advanta~es of he inhibitors of the present invention ~rhen used with double base propellants in the particular form descrlbed above is that not only is the system virtually smokeless during combustion at elevated pressures normal in rocket motors9 but it i5 also smokele3s or nearly 50 in the after-burn condition of the motor including pressure decay period in the combustion chamber. This is o~ course a significant advantage.
If 8 high erosion resistance, or mechanical property such as high - modulus of elasticity, or high strength is required, then a greater proportion of filler up to ~OQ parts by weight or beyond compared to 100 parts by weight of organic compounds can be used.
Other back-bone carbon to carbon bond forming materials may be used than ethylene, although ethylene is preferred if smokelessness is an important requirement.
In a further method of manufacturing the product~ the powders of the copolymer and filler materials are pre-blended, and are then fed into a plastics screw-type extruder or extrusion !)ress. From this, there is : 20 extruded the copolymer composition, either in ~he physical form that is required, eg tube or sheet, or in for example sheet form for further processing to the required shape.
The compositions inthe present invention find application in the rocl~et motor combustion chamber for duties other than that of combustion inhibition.
Thus, different but appropriate filler materials may be used which adapt the composition to the a~propriate duty. A typical filler material is ~lass fibr or other fibrous reinforcement material in order to lmprove the mechanic-~l strength and/or stiffness of the composition. Other suitable filamentary reinforcement materials are chopped asbestos and carbon fibre. Dependin~
- 1 32~597 ~; upon the rec~ptivity ol` the com~o:3i-tion to the fil~er nlatcrinl concerned, the ratio of fi.ller to polymer may be up to 3:1 or higher.
The properties l,rhich can be obtained are illustrated by the compositio~3 `. having filler contents and physical properties given in the following table, .~` 5 all being based on a copolymer of 70wt~7o ethylene, 15wt5~ methacrylic acid and 1 5Nt5~ methyl me thacrylate .
Table :'', __ ............................ . .
Filler Tensile Strength2 Elongation . % contentin meganeutons/m %
_ . _ ~ ~ , , . O ~8 490 Polyoxymethylene 75 ~ .4 2. 2 Oxamide 40 17 . 5 2 70 Oxamide 75 9 . ~ 8 : Glas~ fibre 75 20 3 Glass fibre 30 15 220 ,, _ _ It is also possible to select a thermoplastic filler material, for example polyoxymethylene, and then to extrude or mould at an appropriate temperature. If the temperature is above the melting point of the fil'er :~i 10 material, then there is produced a co-moulding which largely displays the physical properties of the filler material in conjunction ~.1ith some rubbery :i , properties arising from the copolymer. If the ternperature is belo-r th~
meltin~ point, then there is obtained large~ the rubhery ~roperties of t:^e copolym~r. This ~?pplies to the use of any the:rmoplastic filler materi~l.
j . .
15 As an example, there was prep~red the copolymer 70wt~o ethylene, 15wt~
methacrylic acid and 15wt~ methyl methacrylate, and this was filled with 75$, ie 75 parts per hundred copolym~r9 of polyoxymethylene by mixing the '~ two to.ether in powder form. l.1hen the mixture was e~truded at 150C, there was produf~ed a filled therrnoplastic rubber largely showing the pro~ertie3 o~
20 the co~olymer. On the other hand, when the mixture wasex~udedat 170~, ther was prodllced a co-moulding in which the ten~ile strength ;was doubled~
, ,~9."~L, `~
r -The combustion inhibitors described in the Examples 1 and 2 given above were tested for smoke production by being applied to 150 mm diameter cast double base solid propellant charges, and fired with a burning time of 26 seconds. There was measured the obscuration of polarised light by the exhaust in the direction of the axis of the nozzle, this being done by a photometer. The results obtained showed an obscuration of 0 to 5 % for dif-ferent samples. Thls can be compared with the same tests carried out in the same conditions except with the use of a standard cellulosic type inhibitor on the 150 mm diameter cast double base solid propellant charge. In that case the obscuration was about 80 %.
The copolymers of the present invention have a particular applica-tion for use as combustion inhibitor materials, particularly arising from the low absorption of nitroglycerine from cast double base charges, their low density, usually lying in the range 1.1 to 1.2 dependin~g on the filler materials chosen, their good gas permeability, and good adhesive properties.
They are also readily formable. However, their mechanical properties are readily adjusted, both by selection of the copolymer itself, and the filler materials and other additives to be used in it, such th~t the mechanical properties can be matched both to those of a substrate such as a solid propellant charge, and also to the mechanical properties of other substrates such as other polymers or metal. The copolymers therefore find other duties in the onerous conditions prevailing in a rocket motor oombustion chamber, and for example can be used as high strength grain-holdbakc components.
a - 8 -
; The invention al90 provides a composition which9 as well as being capable of use as a combustion inhibitor, also has other applications in a rocket motor combustion chamber.
Solid propellant rocket motors include a charge of propellant, an inhibitor on certain parts o~ the charge to control the area of burning surface, and an outer case. The inhibitor is used to control locally the ! burning area of the propellant so that the charge burns in the desired `, 10 geometricel manner. The inhibitor needs to be chemically and physically compatible with the charge. The inhlbitor may be completely or partially consumed during the firing of the rocket motor.
If a rocket motor ernits smoke, the trail can betray the firing point of the missile, and its trajectory. E~haust smoke obscures the target and missile from the person firing the missile which is particularly dis-advantageous if the missile is being visually guided along the line of sight to its target. Thus, frequently one of the major requirements of a rocket motor is that smoke emission during combustion should be as low as possible.
This condition is provided by the use of double base propellant, but inert p~rts, largely the charge inhibitor, prevent the achievement of a "smokeless"
e~haust.
Ad~tionally propellant charges are widely used as g~s generators or power cartridges for mechanical operatio~q and in such circumstances smoke condensate is a nuisance because it can foul the area into which it is discharged, and cause interference with valve mechanisms and moving surfaces.
The term "double base propellant" where used in this specification includes nitrocellulose with nitroglycerine or other liquid nitric ester with or without other additives, chemical stabilisers, plasticisers, balli~tic js . ';
, . .
; `- 1 326597 73117-3 . . . modifiers, fuel~ such as aluminium powder, and oxidisers such as ammonium perchlorate.
By the present invention, there is provided a composition for use in conjunction with but distinct from a solid propellant charge, the composition including a copolymer of a hydrocarbon carbon-carbon chain-forming material with at least one component chosen from the group consisting of methyl methacrylate, methacrylic acid, acrylic acid, methyl acrylate~ and hydroxy ethyl methacrylate.
Preferably, the composition includes a copolymer of the hydrocarbon carbon-carbon chain-forming material with at least two components chosen from the group speclfied above.
The present invention also consists in the use of the composition referred to above as a combustion inhibitor for use bonded to a solid propellant charge. The present in~ention also provides a solid propellant charge having a combustion inhibitor bonded on at least part of the surface thereof, the combustion inhibitor including a copolymer of a hydrocarbon carbon-carbon chain-forming material wlth at least one component chosen from the group consisting of methyl methacrylate, methacrylic acid, acrylic acid, methyl acrylate, and hydroxy ethyl methacrylate.
By the term "hydrocarbon carbon-carbon chain-forming material" is meant a hydrocarbon material capable of polymerisation to form a long chain carbon to carbon back-bone polymerised material.
. ~ .
;... .: ., :::,: .
., :
-., ;:
' ;
~:; 73117-3 , .
. The hydrocarbon material is preferahly ethylene and may ~: he presenk in an amount of a~ least 75% of the copolymer matrix.
. There may be a filler or fillers in the inhibitor which may be chosen from compounds having a low carbon to oxygen ratio of 1:1 or less, such as cellulose, carbohydrates, oxamide, . polyoxymethylene, urea formaldehyde, urea oxalate, and tartaric .l acid. Other suitable fillers are in particulate form -3a-~" ~
/
'. ~ '.- ~
1 3~65~7 and are elemental carbon and oxides, hydroxides, carbonates, and nitrates of at least one element selected from:
~ (a) magnesium, calcium, zinc, strontium, cadmium and barium;
``~ (b~ boron and aluminium;
(c) silicon and titanium;
(d) arsenic, antimony and bismuth; and ~ (e) iron, cobalt and nickel.
:.j :~! If it i9 required to produce a smokeless or approximately smokeless charge, the filler material to be used in the inhibitor and the size of the particles are such that exposure of the filled inhibitor to the combustion of the propellant charge in the rocket motor chamber or other combustion chamber results in a product wholly gaseous or containing particles which are of a si~e less than 1 micron or greater than 15 microns~
It can be understood from the above that for a chosen filler material, only a simple experiment is needed to decide if the sizes of the particles ~; of filler material in the combustion inhibition material are important, and f so which sizes are appropriate.
When it is required to produce a smokeless inhibitor, the presence of ;J the fillers can reduce the carbon to oxygen ratio for the filled inhibitor 33 20 material to below 2:1, preferably below 1.5:1.
By way of example, examples of the invention will now be described.
Bxample 1 Ethylene, meth~crylic acid and methyl methacrylate are copolymerised.
The proportions are 15,at of metkacrylic acid, CH3-CH ~ -H + 15~ methyl i 25 methacrylate CH~-CH=Ç-H + 70~ ethylene CH2 = CH2. ~OOCH3 Alternatively the above copolymer can be modified by copolymerisation with the additire hydroxyethyl methacrylate CH2 = C, - C~20 OOC ~5 `l ``
, : ~
.
~` 1 326597 The above copolymers usin~ flllers of the type previously de~cribed can be loaded up to a level of 3:1 by wei~ht of filler to ~atrix, or higher.
~he filler and copolymer may be milled together to for~ a thoroughly mixed crepe. The mix of milled filler/polymer crepe is formed essentially by melting the copolymer mixture and mixing in the filler ~hich is encapsulated 3 by the molten copoly~er mixture. The molten copolymer and filler mixture is thereby formed into slabs, l~hich can be used for moulding or pressing sheets.
The product of the above method of mixing can also be granulated and re~
processed as the feed stook for extru~ion of tubes or shect.
~ 10 In an alternative method of forming the mi~ture, the copolymer and i fillers are separately ground to fine powder, and the powder mix is then formed into sheets and slabs under the action of pressure and heat, the temperature of the powder during the pressing operation being maintained at typically 110 to 150 C, at a pres~ure of typically 100 kilograms/cm or higher. The sheet~ and slabs can then be moulded to any desired shape to i provide inhibitors.
~xample 2 In a second example of the invention, 20 parts of acrylic acid l CH2 = ,C-H , 15 parts methyl acrylate C~2 = Ç-H and 65 parts of ethylene j~ COOH ~OOC~
C~2 = C~2 are copolymerised. To 100 parts of the copolymer mixture is added 50 parts polyoxymethylene (CH20)n.
The components are blended together and the blend is then pressed at - 130C to give sheets and slabs. Alternstively, any of the above methods described may also be used.
,.
The amount of copolymerisation may be ~djusted to alter the physical properties of the solid inhibitor and can control the rubberiness of the inhibitor.
If the smokelessness is not req11ired, any normal rubber or plastics additives may be used~ Also the inhibitor may be used for solid :, . . . .
,, , . ~ .
. .
,!
~ ~ 326597 propellants other than double base propellants, ie composite propellants.
~owever, one of the advanta~es of he inhibitors of the present invention ~rhen used with double base propellants in the particular form descrlbed above is that not only is the system virtually smokeless during combustion at elevated pressures normal in rocket motors9 but it i5 also smokele3s or nearly 50 in the after-burn condition of the motor including pressure decay period in the combustion chamber. This is o~ course a significant advantage.
If 8 high erosion resistance, or mechanical property such as high - modulus of elasticity, or high strength is required, then a greater proportion of filler up to ~OQ parts by weight or beyond compared to 100 parts by weight of organic compounds can be used.
Other back-bone carbon to carbon bond forming materials may be used than ethylene, although ethylene is preferred if smokelessness is an important requirement.
In a further method of manufacturing the product~ the powders of the copolymer and filler materials are pre-blended, and are then fed into a plastics screw-type extruder or extrusion !)ress. From this, there is : 20 extruded the copolymer composition, either in ~he physical form that is required, eg tube or sheet, or in for example sheet form for further processing to the required shape.
The compositions inthe present invention find application in the rocl~et motor combustion chamber for duties other than that of combustion inhibition.
Thus, different but appropriate filler materials may be used which adapt the composition to the a~propriate duty. A typical filler material is ~lass fibr or other fibrous reinforcement material in order to lmprove the mechanic-~l strength and/or stiffness of the composition. Other suitable filamentary reinforcement materials are chopped asbestos and carbon fibre. Dependin~
- 1 32~597 ~; upon the rec~ptivity ol` the com~o:3i-tion to the fil~er nlatcrinl concerned, the ratio of fi.ller to polymer may be up to 3:1 or higher.
The properties l,rhich can be obtained are illustrated by the compositio~3 `. having filler contents and physical properties given in the following table, .~` 5 all being based on a copolymer of 70wt~7o ethylene, 15wt5~ methacrylic acid and 1 5Nt5~ methyl me thacrylate .
Table :'', __ ............................ . .
Filler Tensile Strength2 Elongation . % contentin meganeutons/m %
_ . _ ~ ~ , , . O ~8 490 Polyoxymethylene 75 ~ .4 2. 2 Oxamide 40 17 . 5 2 70 Oxamide 75 9 . ~ 8 : Glas~ fibre 75 20 3 Glass fibre 30 15 220 ,, _ _ It is also possible to select a thermoplastic filler material, for example polyoxymethylene, and then to extrude or mould at an appropriate temperature. If the temperature is above the melting point of the fil'er :~i 10 material, then there is produced a co-moulding which largely displays the physical properties of the filler material in conjunction ~.1ith some rubbery :i , properties arising from the copolymer. If the ternperature is belo-r th~
meltin~ point, then there is obtained large~ the rubhery ~roperties of t:^e copolym~r. This ~?pplies to the use of any the:rmoplastic filler materi~l.
j . .
15 As an example, there was prep~red the copolymer 70wt~o ethylene, 15wt~
methacrylic acid and 15wt~ methyl methacrylate, and this was filled with 75$, ie 75 parts per hundred copolym~r9 of polyoxymethylene by mixing the '~ two to.ether in powder form. l.1hen the mixture was e~truded at 150C, there was produf~ed a filled therrnoplastic rubber largely showing the pro~ertie3 o~
20 the co~olymer. On the other hand, when the mixture wasex~udedat 170~, ther was prodllced a co-moulding in which the ten~ile strength ;was doubled~
, ,~9."~L, `~
r -The combustion inhibitors described in the Examples 1 and 2 given above were tested for smoke production by being applied to 150 mm diameter cast double base solid propellant charges, and fired with a burning time of 26 seconds. There was measured the obscuration of polarised light by the exhaust in the direction of the axis of the nozzle, this being done by a photometer. The results obtained showed an obscuration of 0 to 5 % for dif-ferent samples. Thls can be compared with the same tests carried out in the same conditions except with the use of a standard cellulosic type inhibitor on the 150 mm diameter cast double base solid propellant charge. In that case the obscuration was about 80 %.
The copolymers of the present invention have a particular applica-tion for use as combustion inhibitor materials, particularly arising from the low absorption of nitroglycerine from cast double base charges, their low density, usually lying in the range 1.1 to 1.2 dependin~g on the filler materials chosen, their good gas permeability, and good adhesive properties.
They are also readily formable. However, their mechanical properties are readily adjusted, both by selection of the copolymer itself, and the filler materials and other additives to be used in it, such th~t the mechanical properties can be matched both to those of a substrate such as a solid propellant charge, and also to the mechanical properties of other substrates such as other polymers or metal. The copolymers therefore find other duties in the onerous conditions prevailing in a rocket motor oombustion chamber, and for example can be used as high strength grain-holdbakc components.
a - 8 -
Claims (15)
1. A composition for use in conjunction with but distinct from a solid propellant charge, the composition including a copolymer of a hydrocarbon carbon-carbon chain-forming material with at least one component chosen from the group consisting of methyl methacrylate, methacrylic acid, acrylic acid, methyl acrylate, and hydroxy ethyl methacrylate.
2. A composition according to claim 1 including a copolymer of the hydrocarbon carbon-carbon chain-forming material with at least two components chosen from the group specified in claim 1.
3. A composition according to claim 1 wherein the hydrocarbon carbon-carbon chain-forming material is ethylene.
4. A composition according to claim 3 wherein the ethylene is present in an amount of at least 75% by weight of the copolymer matrix.
5. A composition according to claim 1 containing at least one filler material.
6. A composition according to claim 5 wherein the filler has a low carbon to oxygen ratio of 1:1 or less and is selected from the group consisting of cellulose, carbohydrates, oxamide, polyoxymethylene, urea formaldehyde, urea oxalate and tartaric acid.
7. A composition according to claim 5 wherein the filler is in particulate form and is selected from the group consisting of elemental carbon and oxides, hydroxides, carbonates, and nitrates of at least one element selected from:
(a) magnesium, calcium, zinc, strontium, cadmium and barium;
(b) boron and aluminium;
(c) silicon and titanium;
(d) arsenic, antimony and bismuth; and (e) iron, cobalt and nickel;
-9a-the filler material and the size of the particles being such that exposure of the filled inhibitor to the combustion of the propellant charge in the rocket motor chamber results in a product wholly gaseous or containing particles which are of a size less than 1 micron or greater than 15 microns.
(a) magnesium, calcium, zinc, strontium, cadmium and barium;
(b) boron and aluminium;
(c) silicon and titanium;
(d) arsenic, antimony and bismuth; and (e) iron, cobalt and nickel;
-9a-the filler material and the size of the particles being such that exposure of the filled inhibitor to the combustion of the propellant charge in the rocket motor chamber results in a product wholly gaseous or containing particles which are of a size less than 1 micron or greater than 15 microns.
8. A composition according to claim 5 wherein the filler is a filament-ary reinforcement material.
9. A composition according to claim 5 wherein the filler is a thermo-plastic material.
10. A combustion inhibitor for use bonded to a surface of a solid pro-pellant charge comprising a composition including a copolymer of a hydrocarbon carbon-carbon chain-forming material with at least one component chosen from the group consisting of methyl methacrylate, methacrylic acid, acrylic acid, methyl acrylate, and hydroxy ethyl methacrylate.
11. A combustion inhibitor comprising a composition as claimed in claim 2, 3 or 4.
12. A combustion inhibitor comprising a composition as claimed in claim 5, 6 or 7.
13. A solid propellant charge having a combustion inhibitor bonded on at least part of the surface thereof, the combustion inhibitor including a copolymer of a hydrocarbon carbon-carbon chain-forming material with at least one component chosen from the group consisting of methyl methacrylate, meth-acrylic acid, acrylic acid, methyl acrylate, and hydroxy ethyl methacrylate.
14. A solid propellant charge having a combustion inhibitor bonded on at least part of the surface thereof, the combustion inhibitor being a com-position as claimed in claim 2, 3 or 4.
15. A solid propellant charge as claimed in claim 13 wherein the pro-pellant is a double base propellant.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB22679/73 | 1973-05-11 | ||
| GB2267973A GB1605362A (en) | 1973-05-11 | 1973-05-11 | Improvements in or relating to combustion inhabitors. |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1326597C true CA1326597C (en) | 1994-02-01 |
Family
ID=10183356
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA000198626A Expired - Fee Related CA1326597C (en) | 1973-05-11 | 1974-05-01 | Combustion inhibitors |
Country Status (8)
| Country | Link |
|---|---|
| AU (1) | AU632274B2 (en) |
| CA (1) | CA1326597C (en) |
| DE (1) | DE2422601C1 (en) |
| FR (1) | FR2681858A1 (en) |
| GB (1) | GB1605362A (en) |
| IT (1) | IT1235558B (en) |
| NO (1) | NO741642L (en) |
| SE (1) | SE468767B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2557629C1 (en) * | 2014-06-27 | 2015-07-27 | Федеральное государственное унитарное предприятие "Центральный научно-исследовательский институт химии и механики" (ФГУП "ЦНИИХМ") | Method of fabrication of armour cover for insert charge of composite solid propellant for rocket motor and heat-barrier material |
-
1973
- 1973-05-11 GB GB2267973A patent/GB1605362A/en not_active Expired - Lifetime
-
1974
- 1974-05-01 CA CA000198626A patent/CA1326597C/en not_active Expired - Fee Related
- 1974-05-07 NO NO741642A patent/NO741642L/en unknown
- 1974-05-08 IT IT7450874A patent/IT1235558B/en active
- 1974-05-09 SE SE7406216A patent/SE468767B/en not_active IP Right Cessation
- 1974-05-10 FR FR7416181A patent/FR2681858A1/en active Pending
- 1974-05-10 DE DE2422601A patent/DE2422601C1/de not_active Expired - Lifetime
- 1974-05-13 AU AU68852/74A patent/AU632274B2/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2557629C1 (en) * | 2014-06-27 | 2015-07-27 | Федеральное государственное унитарное предприятие "Центральный научно-исследовательский институт химии и механики" (ФГУП "ЦНИИХМ") | Method of fabrication of armour cover for insert charge of composite solid propellant for rocket motor and heat-barrier material |
Also Published As
| Publication number | Publication date |
|---|---|
| IT1235558B (en) | 1992-09-11 |
| SE468767B (en) | 1993-03-15 |
| GB1605362A (en) | 1993-12-22 |
| DE2422601C1 (en) | 1993-07-01 |
| AU632274B2 (en) | 1992-12-24 |
| NO113607C (en) | 1978-01-25 |
| NO741642L (en) | 1992-08-12 |
| FR2681858A1 (en) | 1993-04-02 |
| SE7406216L (en) | 1992-11-06 |
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| Date | Code | Title | Description |
|---|---|---|---|
| MKLA | Lapsed |