CA1263238A - Combustion inhibitors - Google Patents
Combustion inhibitorsInfo
- Publication number
- CA1263238A CA1263238A CA000198625A CA198625A CA1263238A CA 1263238 A CA1263238 A CA 1263238A CA 000198625 A CA000198625 A CA 000198625A CA 198625 A CA198625 A CA 198625A CA 1263238 A CA1263238 A CA 1263238A
- Authority
- CA
- Canada
- Prior art keywords
- combustion inhibitor
- inhibitor according
- glycol
- less
- isocyanate
- 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
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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/26—Burning control
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Crystallography & Structural Chemistry (AREA)
- Organic Chemistry (AREA)
- Polyurethanes Or Polyureas (AREA)
- Compositions Of Macromolecular Compounds (AREA)
Abstract
A B S T R A C T
A combustion inhibitor for a solid propellant charge formed from a mixture of a polyether glycol or a polyester glycol and an isocyanate.
A combustion inhibitor for a solid propellant charge formed from a mixture of a polyether glycol or a polyester glycol and an isocyanate.
Description
~2~3Z38 I`his invention relates to inhibitors for solid propellants, and is particularly, hut not exclusively, concerned with solid propellants which have a low smoke exhaust.
Solid propellant rocket motors include a charge of propellant, an inhibitor on certain parts of 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 geometrical manner. The inhibitor needs to be chemically and physically compatible with the charge. The inhibitor may be completely or partially consumed during the firing of the rocket motor.
If a rocket motor emits smoke, the trail can betray the firing point of the missile, and its trajectory. Exhaust smoke obscures the target and missile from the person firing the missile which is particularly disadvantage-ous 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 parts, largely the charge inhibitor, prevent the achievement of a "smokeless"
exhaust.
Additionally propellant charges are widely used as gas generators or power cartridges for mechanical operations and in such circumstances smoke condensate is a nuisance because it can foul the area into which it is dis-charged 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, eg chemical stabilizers, plasticisers, ballistic modifiers, oxidisers such as ammonium perchlorate, and fuels such as aluminium powder.
By the present invention there is provided a combustion inhibitor for inhibiting ignition of a portion of a solid propellant charge after another portion thereof has been ignited comprising a mixture of a polyether glycol or a polyester glycol and an isocyanate.
P~
323~3 73117-~
Preferably tile gLycol is a polyether glycol of low molecular weight leas t'nan 1000 and a high ratio of oxygen to carbon content of about 0.7:1 and preferably approachLng 1:1. Such a polyether glycol should produce little smoke.
The combustion inhibitor may include a catalyst to increase the amount oE cross-linking between the glycol and the isocyanate; the catalyst is preferably specific to the isocyanate-glycol reaction, and an example of such a catalyst is phenyl mercuric acetate.
Plasticisers may be used to make a softer product, in which case they preferably have a low molecular weight of less than 500 and are preferably aliphatic with a high oxygen to carbon ratio, preferably not less than 1:1.
Examples of useful plasticisers are triethyl citrate, which has a molecular weight of 212 and triacetin which has a molecular weight oE 184.
The combustion :Lnhibitor may or may not include a molecular sieve or o o silica having a particle size from lA to lOA to reduce moisture effects, and these may be present in amounts up to 2% of the inhibitor.
PreEerably the isocyanate is a low molecular weight aliphatic iso-cyanate in order to produce less smoke than would be the case with an isocya-nate which i8 aromatic and/or is of higher molecular weight. In this context, a low molecular weight means a molecular weight of less than 500. An example of a low molecular weight aliphatic isocyanate is tri-methyl hexamethylene diisocyanate which has a molecular weight of 210.
There may be a filler or Eillers in the inhibi-tor and these may be chosen from compound having a low carbon to oxygen ratio of 1:1 or less, such as cellulose, carbohydrates, oxamide, polyoxymethylene, urea formaldehyde, urea oxalate, and tartaric acid. Other suitable fillers are in particulate form and are elemental carbon and oxides, hydroxides, carbonates, and nitrates of at least one element selected from:
.~
~L~6~8 (a) m.~ esium, cn1cium, z:inc, lt:ron~ rr" ca(imi~ n3 barinm;
(b) boron ~nd aluminiuln;
(c) silicon and tit1?nium;
(d) arsenic, antimony and bismuth; and (e) iron, cobalt and nickel.
The filler material and the size of ths particles are such that expo3ire of the fi]led inhibitor to the combustion of the propellant charge in the rocket .~otor chamber results in a product wholly gaseous or containing par-ticles which are of a size less than 1 micron or grea+e- than 15 microns.
It can be understood from the above that for a chosen filler material, onl.y a simple experiment is needed to deci.de if the ~izes of the particles of filler material in the cornbu;3tion inhibition materi;al are irnportant, and if so which sizes are appropriate.
rrhe present invention further provides a solid proPellant charge to which is bonded a combustion inhibitor comprising a mixture of a polyether glycol or a polyester glycol and an isocyanate.
~here is furthe:r provided by the present invention a method of manu-facturing a solid propellant charge comprising manufacturing a combustion inhibitor subst~tntially as described in any one of Examples 1 to 3 herein, and bonding it to a solid propellant.
Typical Examples of the intrention will noT.r be described.
Example 1 rrhere are mixed together 100 parts by ~Jeight of ICI Dalto Cast 2, a polyether glycol of general formula:
H -0- (CX2-C -0 ) CH-0- ( CX3 ) n
Solid propellant rocket motors include a charge of propellant, an inhibitor on certain parts of 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 geometrical manner. The inhibitor needs to be chemically and physically compatible with the charge. The inhibitor may be completely or partially consumed during the firing of the rocket motor.
If a rocket motor emits smoke, the trail can betray the firing point of the missile, and its trajectory. Exhaust smoke obscures the target and missile from the person firing the missile which is particularly disadvantage-ous 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 parts, largely the charge inhibitor, prevent the achievement of a "smokeless"
exhaust.
Additionally propellant charges are widely used as gas generators or power cartridges for mechanical operations and in such circumstances smoke condensate is a nuisance because it can foul the area into which it is dis-charged 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, eg chemical stabilizers, plasticisers, ballistic modifiers, oxidisers such as ammonium perchlorate, and fuels such as aluminium powder.
By the present invention there is provided a combustion inhibitor for inhibiting ignition of a portion of a solid propellant charge after another portion thereof has been ignited comprising a mixture of a polyether glycol or a polyester glycol and an isocyanate.
P~
323~3 73117-~
Preferably tile gLycol is a polyether glycol of low molecular weight leas t'nan 1000 and a high ratio of oxygen to carbon content of about 0.7:1 and preferably approachLng 1:1. Such a polyether glycol should produce little smoke.
The combustion inhibitor may include a catalyst to increase the amount oE cross-linking between the glycol and the isocyanate; the catalyst is preferably specific to the isocyanate-glycol reaction, and an example of such a catalyst is phenyl mercuric acetate.
Plasticisers may be used to make a softer product, in which case they preferably have a low molecular weight of less than 500 and are preferably aliphatic with a high oxygen to carbon ratio, preferably not less than 1:1.
Examples of useful plasticisers are triethyl citrate, which has a molecular weight of 212 and triacetin which has a molecular weight oE 184.
The combustion :Lnhibitor may or may not include a molecular sieve or o o silica having a particle size from lA to lOA to reduce moisture effects, and these may be present in amounts up to 2% of the inhibitor.
PreEerably the isocyanate is a low molecular weight aliphatic iso-cyanate in order to produce less smoke than would be the case with an isocya-nate which i8 aromatic and/or is of higher molecular weight. In this context, a low molecular weight means a molecular weight of less than 500. An example of a low molecular weight aliphatic isocyanate is tri-methyl hexamethylene diisocyanate which has a molecular weight of 210.
There may be a filler or Eillers in the inhibi-tor and these may be chosen from compound having a low carbon to oxygen ratio of 1:1 or less, such as cellulose, carbohydrates, oxamide, polyoxymethylene, urea formaldehyde, urea oxalate, and tartaric acid. Other suitable fillers are in particulate form and are elemental carbon and oxides, hydroxides, carbonates, and nitrates of at least one element selected from:
.~
~L~6~8 (a) m.~ esium, cn1cium, z:inc, lt:ron~ rr" ca(imi~ n3 barinm;
(b) boron ~nd aluminiuln;
(c) silicon and tit1?nium;
(d) arsenic, antimony and bismuth; and (e) iron, cobalt and nickel.
The filler material and the size of ths particles are such that expo3ire of the fi]led inhibitor to the combustion of the propellant charge in the rocket .~otor chamber results in a product wholly gaseous or containing par-ticles which are of a size less than 1 micron or grea+e- than 15 microns.
It can be understood from the above that for a chosen filler material, onl.y a simple experiment is needed to deci.de if the ~izes of the particles of filler material in the cornbu;3tion inhibition materi;al are irnportant, and if so which sizes are appropriate.
rrhe present invention further provides a solid proPellant charge to which is bonded a combustion inhibitor comprising a mixture of a polyether glycol or a polyester glycol and an isocyanate.
~here is furthe:r provided by the present invention a method of manu-facturing a solid propellant charge comprising manufacturing a combustion inhibitor subst~tntially as described in any one of Examples 1 to 3 herein, and bonding it to a solid propellant.
Typical Examples of the intrention will noT.r be described.
Example 1 rrhere are mixed together 100 parts by ~Jeight of ICI Dalto Cast 2, a polyether glycol of general formula:
H -0- (CX2-C -0 ) CH-0- ( CX3 ) n
2 o (CH2 ~ ~
\ 3 / n ~ ~6~
~0 parts of trimethyl he~ameth~/lene diisoc-yanate, f OCN-CH2 - C - C~I2-CH-CX -CH -NC0 50 p~rts triacetin as a plasticiser, forrQula 1l f H2-o-c-cH
C -- O -- C -- CH
1 If 0.2 parts phenyl mercuric acetate as a catalyst 50 parts ferric oxide as a filler and 1 part molecular sieve size 2~.
The mixture is mixed in the liquid state and is cast around a propellant grain before it sets.
Example 2 An altr3rnative mixture which can be used is 100 parts polyesterglycol, formula ¦-C-- ~ 2-C~-R-C0-0- (CX2-1H-0) ¦ 3 n R-C0-0- CH2-CX-0 ~
1H3 /n where R is an aromatic radical and the polyester glycol has a low molecular weight of less than 1000 and a high oxygen to carbon ratio above 0.7:1 and preferably approqchin~
~ 5 ~3~38 to~--th~r wi.th ~0 parts 4.-~ diphenyl me-thlne diisocyanate sv~ilable co~merclally ~rom ICI as ICT Suprasec DNC and h~lving th~ for~ula OCN - ~ ~ ~ C~2 ~ ~ ~ NCO, 0.2 parts phenyl melcuric acetate . ~ - COO-Hg-COO-CH~ as a catal~/3t, 50 par-ts triethyl citrate as a plasticiser CEI2 .C02( C2H5 ) j . 2(C2H5) C~2 . C2 ( C 2H5 ) 100 parts polyoxymethylene (CH20)n as a filler, and 2 parts molecular sieve size 10~.
The mixture is made up in liquid form as before at room temperature, and cast be-fore solidification. The mixture can be cast around a propellant grain.
Exam~
In a third example of this invention, -there are mixed together 100 parts by weight of ICI Dalto Cast 2, a polyether glycol of the general formula ~iven in Example 1 above 77 par-ts of trimethyl hexamethylene diisocyanate of formula given in Example 1 above 40 parts as plasticiser of dibutyl carbitol formal ( C4HgOC2H40C2H40 ) 2CH2 0.2 parts phenyl mercuric acetate as the catalyst and 88 parts of oxamide of formula (CONH2)2 as the filler.
The mixture is made up in liquid form at room temperature, and cast before i-t solidifies.
~,~6323~
One of the importar1t f,lture3 of the combu: tion inhil)i~or of th?
illVentlOII i9 i~s lo-,l smokc Olltput during burning. If particular mechanic--'properties such as strength or abrasion resistance are required, the filler content can be increased.
In a comparative test, a 150~ diameter solid propellant charge of cast double base propellant was provided with a combustion inhibitor of a qtandard cellulose base f'orm. It was fired with a 26 second burning time, and there was measured the obscuration of light transmission by the exhaust fumes in the direction along the axis of the charge. In this test, polarisec light is transmitted in the re~uired direction, and a photo~eter is used to indicate the percentage loss of light. The result found was that about 30 of the light was obscured.
Comparative tests were carried out with the same form of propellant charge but having an inhibitor based on each one of the three Exa~ples abo-.e.
In the same firing and measurement conditions, various obscuration measuremen-s were obtained which ran~ed from 0 to 5%. These tests clearly show the import~nt reduction in smoke production using the inhibitors of the ~xamples.
Another advantage of the invention is the fact that the inhibitor can be cast prior to solidification, which me~ns thqt it can be used to "pot"
grains of propellant, or can be casttof~rmmoulds into which the propellant can be subsequently cast.
For lo~ smoke output, the polymer and organic fillers are preferably aliph~tic compounds rather than aromatic. Also low molecular weights ard short chain len~gths with minimum chain branching are pre~erable for the same reason. A high oxygen to carbon ratio is essential for low smoke.
.~
\ 3 / n ~ ~6~
~0 parts of trimethyl he~ameth~/lene diisoc-yanate, f OCN-CH2 - C - C~I2-CH-CX -CH -NC0 50 p~rts triacetin as a plasticiser, forrQula 1l f H2-o-c-cH
C -- O -- C -- CH
1 If 0.2 parts phenyl mercuric acetate as a catalyst 50 parts ferric oxide as a filler and 1 part molecular sieve size 2~.
The mixture is mixed in the liquid state and is cast around a propellant grain before it sets.
Example 2 An altr3rnative mixture which can be used is 100 parts polyesterglycol, formula ¦-C-- ~ 2-C~-R-C0-0- (CX2-1H-0) ¦ 3 n R-C0-0- CH2-CX-0 ~
1H3 /n where R is an aromatic radical and the polyester glycol has a low molecular weight of less than 1000 and a high oxygen to carbon ratio above 0.7:1 and preferably approqchin~
~ 5 ~3~38 to~--th~r wi.th ~0 parts 4.-~ diphenyl me-thlne diisocyanate sv~ilable co~merclally ~rom ICI as ICT Suprasec DNC and h~lving th~ for~ula OCN - ~ ~ ~ C~2 ~ ~ ~ NCO, 0.2 parts phenyl melcuric acetate . ~ - COO-Hg-COO-CH~ as a catal~/3t, 50 par-ts triethyl citrate as a plasticiser CEI2 .C02( C2H5 ) j . 2(C2H5) C~2 . C2 ( C 2H5 ) 100 parts polyoxymethylene (CH20)n as a filler, and 2 parts molecular sieve size 10~.
The mixture is made up in liquid form as before at room temperature, and cast be-fore solidification. The mixture can be cast around a propellant grain.
Exam~
In a third example of this invention, -there are mixed together 100 parts by weight of ICI Dalto Cast 2, a polyether glycol of the general formula ~iven in Example 1 above 77 par-ts of trimethyl hexamethylene diisocyanate of formula given in Example 1 above 40 parts as plasticiser of dibutyl carbitol formal ( C4HgOC2H40C2H40 ) 2CH2 0.2 parts phenyl mercuric acetate as the catalyst and 88 parts of oxamide of formula (CONH2)2 as the filler.
The mixture is made up in liquid form at room temperature, and cast before i-t solidifies.
~,~6323~
One of the importar1t f,lture3 of the combu: tion inhil)i~or of th?
illVentlOII i9 i~s lo-,l smokc Olltput during burning. If particular mechanic--'properties such as strength or abrasion resistance are required, the filler content can be increased.
In a comparative test, a 150~ diameter solid propellant charge of cast double base propellant was provided with a combustion inhibitor of a qtandard cellulose base f'orm. It was fired with a 26 second burning time, and there was measured the obscuration of light transmission by the exhaust fumes in the direction along the axis of the charge. In this test, polarisec light is transmitted in the re~uired direction, and a photo~eter is used to indicate the percentage loss of light. The result found was that about 30 of the light was obscured.
Comparative tests were carried out with the same form of propellant charge but having an inhibitor based on each one of the three Exa~ples abo-.e.
In the same firing and measurement conditions, various obscuration measuremen-s were obtained which ran~ed from 0 to 5%. These tests clearly show the import~nt reduction in smoke production using the inhibitors of the ~xamples.
Another advantage of the invention is the fact that the inhibitor can be cast prior to solidification, which me~ns thqt it can be used to "pot"
grains of propellant, or can be casttof~rmmoulds into which the propellant can be subsequently cast.
For lo~ smoke output, the polymer and organic fillers are preferably aliph~tic compounds rather than aromatic. Also low molecular weights ard short chain len~gths with minimum chain branching are pre~erable for the same reason. A high oxygen to carbon ratio is essential for low smoke.
.~
Claims (15)
PROPERTY OR PRIVILEGE IS CLAIMED ARE DEFINED AS FOLLOWS:
1. A combustion inhibitor for inhibiting ignition of a portion of a solid propellant charge after another portion thereof has been ignited com-prising a mixture of a polyether glycol or a polyester glycol and an iso-cyanate.
2. A combustion inhibitor according to claim 1 wherein the glycol is a polyether glycol which has a low molecular weight of less than 1000 and a high oxygen to carbon ratio of above 0.7:1.
3. A combustion inhibitor according to claim 2 wherein the polyether glycol has an oxygen to carbon ratio approaching 1:1.
4. A combustion inhibitor according to claim 1 also including a catalyst to increase the amount of cross-linking between the glycol and the isocyanate.
5. A combustion inhibitor according to claim 4 wherein the catalyst is specific to the isocyanate/glycol reaction.
6. A combustion inhibitor according to claim 5 wherein the catalyst is phenyl mercuric acetate.
7. A combustion inhibitor according to claim 1 including at least one plasticizer having a low molecular weight of less than 500.
8. A combustion inhibitor according to claim 7 wherein the plasticiser is aliphatic with a high oxygen to carbon ratio of not less than 1:1.
9. A combustion inhibitor according to claim 1, 2 or 3 wherein the isocyanate is an aliphatic isocyanate of low molecular weight less than 500.
10. A combustion inhibitor according to claim 1, 2 or 3 wherein the isocyanate is trimethyl hexamethylene diisocyanate.
11. A combustion inhibitor according to claim 1, 2 or 3 containing at least one filler having a low carbon to oxygen ratio of 1:1 or less and selected from the group consisting of cellulose, carbohydrates, oxamide, polyoxymethylene, urea formaldehyde, urea oxalate and tartaric acid.
12. A combustion inhibitor according to claim 1, 2 or 3 containing a filler in particulate form and 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;
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;
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.
13. A solid propellant charge to which is bonded a combustion inhibitor as claimed in claim 1, 2 or 3.
14. A solid propellant charge to which is bonded a combustion inhibitor as claimed in claim 4, 5 or 6.
15. A solid propellant charge to which is bonded a combustion inhibitor as claimed in claim 7 or 8.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB22678/73A GB1605320A (en) | 1973-05-11 | 1973-05-11 | Improvements in or relating to combustion inhibitors |
| GB22678/73 | 1973-05-11 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1263238A true CA1263238A (en) | 1989-11-28 |
Family
ID=10183337
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA000198625A Expired CA1263238A (en) | 1973-05-11 | 1974-05-01 | Combustion inhibitors |
Country Status (7)
| Country | Link |
|---|---|
| AU (1) | AU588517B1 (en) |
| CA (1) | CA1263238A (en) |
| DE (1) | DE2422603C1 (en) |
| FR (1) | FR2633282B1 (en) |
| GB (1) | GB1605320A (en) |
| IT (1) | IT1209901B (en) |
| NO (1) | NO741641L (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2564457B1 (en) * | 1984-05-17 | 1986-09-26 | Poudres & Explosifs Ste Nale | COMBUSTION INHIBITOR BASED ON ALIPHATIC POLYURETHANE ELASTOMER FOR PROPERGOL, AND BLOCK COATED WITH THIS INHIBITOR |
| US6051087A (en) * | 1992-01-29 | 2000-04-18 | Cordant Technologies Inc. | Low smoke rocket motor liner compositions |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1200184B (en) * | 1963-11-16 | 1965-09-02 | Nitrochemie G M B H | Process for the production of solid propellants provided with an insulating layer |
| DE1809360C3 (en) * | 1968-11-16 | 1978-09-21 | Dynamit Nobel Ag, 5210 Troisdorf | Composition for the production of synthetic resins and endothermic decomposing substances containing, optionally heat-curable insulation layers on solid rocket propellants and a method for isolating these propellants using this compound |
| CH514515A (en) * | 1969-09-30 | 1971-10-31 | Oerlikon Buehrle Ag | Method for applying an insulating material to a solid propellant |
| BE790069A (en) * | 1971-10-15 | 1973-02-01 | North American Rockwell | IMPROVEMENTS TO SOLID PROPULSION AGENTS |
-
1973
- 1973-05-11 GB GB22678/73A patent/GB1605320A/en not_active Expired
-
1974
- 1974-05-01 CA CA000198625A patent/CA1263238A/en not_active Expired
- 1974-05-07 NO NO741641A patent/NO741641L/en unknown
- 1974-05-08 IT IT7450873A patent/IT1209901B/en active
- 1974-05-10 FR FR7416180A patent/FR2633282B1/en not_active Expired - Lifetime
- 1974-05-10 DE DE2422603A patent/DE2422603C1/de not_active Expired
- 1974-05-13 AU AU68853/74A patent/AU588517B1/en not_active Expired
Also Published As
| Publication number | Publication date |
|---|---|
| NO741641L (en) | 1989-05-18 |
| GB1605320A (en) | 1989-07-19 |
| AU588517B1 (en) | 1989-09-21 |
| NO113586C (en) | 1978-01-25 |
| DE2422603C1 (en) | 1989-11-23 |
| FR2633282B1 (en) | 1994-01-28 |
| FR2633282A1 (en) | 1989-12-29 |
| IT1209901B (en) | 1989-08-30 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| MKLA | Lapsed |