EP0076990B1 - Stabilizing fin assembly for projectile - Google Patents
Stabilizing fin assembly for projectile Download PDFInfo
- Publication number
- EP0076990B1 EP0076990B1 EP82109120A EP82109120A EP0076990B1 EP 0076990 B1 EP0076990 B1 EP 0076990B1 EP 82109120 A EP82109120 A EP 82109120A EP 82109120 A EP82109120 A EP 82109120A EP 0076990 B1 EP0076990 B1 EP 0076990B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- fins
- projectile
- propellant charge
- barrel
- assembly
- 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
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/02—Stabilising arrangements
- F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
- F42B10/20—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel deployed by combustion gas pressure, or by pneumatic or hydraulic forces
Definitions
- the present invention relates to a stabilizing fin assembly for a rotating or non-rotating projectile designed to be discharged from a rifled or smooth barrel by means of propellant charge gases, having a plurality of elongated fins, rotatably mounted at one end, which are arranged so that during the passage of the projectile through the barrel they are in the retracted position, in which the fins are placed on edge extending mutually in parallel and mainly in the lengthwise direction of the projectiles.
- the fins are normally extended by means of spring force or with the aid of lifting surfaces arranged on the fins which are affected by the wind velocity.
- the method is also known of utilising the gas pressure produced by the propellant charge for extension purposes.
- the pressure acts on a piston or the like which presses the fins outwards.
- the present invention is based on the new concept that it is possible to extend fins placed on edge without the use of either springs, pistons or lifting surfaces. More precisely, the inventive concept lies in a trapping of the propellant gases between the fins, and then in a sudden release of the trapped propellant gases, such that the entire surface of both sides of the fins is subjected to the out-rushing propellant gases which, thereby, jerk with them the fins because of the assisting frictional force.
- the space between the side surfaces of adjacent fins is during the passage of the projectile through the barrel at least partially open to the rear, permitting access by the propellant charge gases to the said space such that the entire surface of both sides of the fins is subjected to the propellant charge gases, said space being at the front at least partially sealed in respect to the surrounding atmosphere by means of a projectile girdle or guide pad arranged in front of the fins, said girdle or pad thereby trapping the propellant charge gases in the said space, whereby the passage of said projectile girdle or pad past the barrel muzzle results in the trapped propellant charge gases in the said space rushing outwards to the atmosphere surrounding the barrel and thereby jerking with them the fins into the extended position because of the assisting frictional force which is generated when the propellant charge gases pass along the surfaces of the fins.
- Figure 1 shows a projectile 2 inserted in a barrel 1 which via a conventional girdle 3 is attached to a cartridge case 4 containing a propellant charge 5.
- the barrel 1 can be either smooth or rifled and forms part of a weapon which is not shown, e.g. a mortar.
- the projectile 2 has a rear section 6 which extends into the sleeve 4 up to the propellant charge 5. At its rear end the rear section 6 is provided with six fin attachments 7 (see Figures 2, 7 and 8), in each of which an extended fin 8 which is located on edge against the rear section 6 is rotatably mounted around a pivot pin 9 which is shown schematically.
- the pivot pin 9 are provided with friction-reducing devices in the form of teflon washers 10 so as to increase the swivel capacity of the fins. It is also feasible to employ other types of friction-reducing devices. For drafting purposes the teflon washers 10 are illustrated only in Figure 7 and then only in one of the fin attachments 7.
- the fins 8 taper to the rear, so that a wedge-shaped gap 11 is formed between the rear section 6 and the edge 12 of the fins facing the projectile axis.
- the space 13 between the fins 8 is open at the back towards the propellant charge 5, as can be best seen from Figure 4.
- propellant charge gases are produced which attempt to discharge the projectile 2.
- the propellant charge gases fill on the one hand the space 13 between the fins and secondly the wedge-shaped gap 11.
- the propellant charge gases overcome the resistance to release of the girdle 3, the projectile moves out of the barrel 1 (on the left in Figure 1).
- the girdle 3 also performs a sealing function in that it permits only a negligible leakage of propellant charge gases to the atmosphere surrounding the barrel.
- the fins 8 have their centre of gravity G closer to the projectile axis than the centre of rotation 9 of the fins, so that the acceleration forces on the projectile during its discharge bring about a moment which attempts to hold in the fins 8 during passage through the barrel. This location of the centre of gravity is particularly advisable for rotating projectiles.
- the fins 8 can be skewed at a predetermined twist angle v as so as to maintain or bring about a desired degree of rotation.
- Figures 7 and 8 show how the fins 8 are mounted in oblique grooves 14 in the fin attachment 7.
- the rear section 6 has a supporting heel 15 on the skewed side of each fin 8 which prevents the fins being deformed as a result of the accelerational forces to which it is subjected during its passage through the barrel.
- Such supporting heels can possibly be arranged on both sides of the fins.
- this support function can be provided by grooves in the rear section 6.
- FIG. 2 illustrates a second embodiment of the invention which in principle differs from the embodiment shown in Figure 1 only in that the rear section of the projectile 2 is replaced by a guidance mechanism tube 16, shown partially in section, which tapers away forwards and which is open at the rear and which at the front by means for example of a screw connection is fastened to a centrally arranged heel 17 at the rear end of the projectile 2.
- the interior of tube 16 by this means forms a chamber 18 which is open rearwards towards the propellant charge 5.
- the tube 16 is provided with six longitudinal slots 19 through which the fins 8 can be partially introduced, as indicated by the dashed edge lines 12. Here the slots 19 provide support for the fins during the passage of the projectile through the barrel.
- the chamber 18 and the space 13 between the fins 8 is filled by the propellant charge gases from the propellant charge 5. This ensures firstly that a larger quantity of gas passes along the wind surfaces of the fins 8 as the gases rush out to the surrounding atmosphere, and secondly that the gases enclosed in the chamber 18 during their outward rushing motion bring about a pressure which is orientated directly towards the edge 12 of the fins 8 which increases the force which extends the fins.
- the chamber 18 and the space 13 between the fins 8 are both open at the rear.
- the chamber 18 can be sealed at the rear whilst the space 13 is open at the rear.
- the slots 19 are so dimensioned that they permit a flow of gas from the space 13 to the chamber 18 even when the fins 8 are introduced into the slots 19.
- the embodiment illustrated in Figure 3 differs from the embodiment shown in Figure 2 in that the conically-tapered, slotted guidance mechanism tube 16 is replaced by a guidance mechanism tube 20 of uniform thickness, the interior of which forms a cylindrical chamber 18a and which instead of slots has two apertures 21 all the way through, these being circular in the embodiment illustrated, located in the centre of each fin 8.
- the apertures 21 have roughly the same dimensions as the thickness of the fins 8.
- the propellant charge gases in the tube 20 bring about a concentrated compressive force on the edge 12 on the fins 8 which faces the projectile axis, so that a particularly high force is obtained which tends to extend the fins.
- the rear section 6 is, possibly via a strap or girdle which is not shown, and preferably exhibiting leakage, fastened into a cartridge case 4 with propellant charge 5.
- the rear section 6 and the tube 25 have a diameter which is somewhat smaller than the barrel 1, so that a ring-shaped gap 26 is formed between them.
- the tube 24 is provided with a strap or girdle 27.
- the fixed pivot of the fins is located at the rear end of the fins, as viewed in the retracted position of the fins.
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Toys (AREA)
- Saccharide Compounds (AREA)
Description
- The present invention relates to a stabilizing fin assembly for a rotating or non-rotating projectile designed to be discharged from a rifled or smooth barrel by means of propellant charge gases, having a plurality of elongated fins, rotatably mounted at one end, which are arranged so that during the passage of the projectile through the barrel they are in the retracted position, in which the fins are placed on edge extending mutually in parallel and mainly in the lengthwise direction of the projectiles.
- With known projectiles having stabilizing fin assembly which have fins which in the retracted position are on edge relative to the projectile axis, the fins are normally extended by means of spring force or with the aid of lifting surfaces arranged on the fins which are affected by the wind velocity. The method is also known of utilising the gas pressure produced by the propellant charge for extension purposes. Here the pressure acts on a piston or the like which presses the fins outwards.
- One example of such a known projectile having a pushing and lifting surface arranged on the fins is shown in the German patent specification No. 2,721,536.
- The present invention is based on the new concept that it is possible to extend fins placed on edge without the use of either springs, pistons or lifting surfaces. More precisely, the inventive concept lies in a trapping of the propellant gases between the fins, and then in a sudden release of the trapped propellant gases, such that the entire surface of both sides of the fins is subjected to the out-rushing propellant gases which, thereby, jerk with them the fins because of the assisting frictional force.
- Thus, in accordance with the invention the space between the side surfaces of adjacent fins is during the passage of the projectile through the barrel at least partially open to the rear, permitting access by the propellant charge gases to the said space such that the entire surface of both sides of the fins is subjected to the propellant charge gases, said space being at the front at least partially sealed in respect to the surrounding atmosphere by means of a projectile girdle or guide pad arranged in front of the fins, said girdle or pad thereby trapping the propellant charge gases in the said space, whereby the passage of said projectile girdle or pad past the barrel muzzle results in the trapped propellant charge gases in the said space rushing outwards to the atmosphere surrounding the barrel and thereby jerking with them the fins into the extended position because of the assisting frictional force which is generated when the propellant charge gases pass along the surfaces of the fins.
- Further developments of the invention are described in the subclaims.
- The invention will be described in greater detail by reference to the appended drawing.
- Figures 1-3 show in longitudinal section and partially in side view a first, second and third embodiment respectively of the invention. In the first embodiment the fins are mounted against a rear section of the projectile, whereas in the second and third embodiments the fins are mounted against a gas guidance tube.
- Figures 4-6 each illustrate a cross-section along the lines IV-IV, V-V and VI-VI respectively in Figures 1-3.
- Figures 7-8 show on a larger scale a skewing arrangement which is advantageous with the embodiment in accordance with Figures 1-3,
- Figure 7 illustrating the fins in the retracted position and Figure 8 in the extended position.
- Figure 9 shows a longitudinal section, half in side view, of the stabilizing assembly in accordance with a fourth embodiment of the invention, designed preferably for oversize head projectiles.
- Figure 10 illustrates a projectile having a stabilizing assembly in accordance with Figure 9 with the fins extended.
- In the various diagrams the same reference notation has been employed throughout for corresponding details in the various embodiments.
- Figure 1 shows a
projectile 2 inserted in abarrel 1 which via aconventional girdle 3 is attached to acartridge case 4 containing apropellant charge 5. Thebarrel 1 can be either smooth or rifled and forms part of a weapon which is not shown, e.g. a mortar. - The
projectile 2 has arear section 6 which extends into thesleeve 4 up to thepropellant charge 5. At its rear end therear section 6 is provided with six fin attachments 7 (see Figures 2, 7 and 8), in each of which an extendedfin 8 which is located on edge against therear section 6 is rotatably mounted around apivot pin 9 which is shown schematically. Thepivot pin 9 are provided with friction-reducing devices in the form ofteflon washers 10 so as to increase the swivel capacity of the fins. It is also feasible to employ other types of friction-reducing devices. For drafting purposes theteflon washers 10 are illustrated only in Figure 7 and then only in one of thefin attachments 7. - The
fins 8 taper to the rear, so that a wedge-shaped gap 11 is formed between therear section 6 and theedge 12 of the fins facing the projectile axis. - The
space 13 between thefins 8 is open at the back towards thepropellant charge 5, as can be best seen from Figure 4. When the propellant charge is ignited in the conventional manner, propellant charge gases are produced which attempt to discharge theprojectile 2. During this the propellant charge gases fill on the one hand thespace 13 between the fins and secondly the wedge-shaped gap 11. When the propellant charge gases overcome the resistance to release of thegirdle 3, the projectile moves out of the barrel 1 (on the left in Figure 1). During the passage of theprojectile 2 through thebarrel 1, thegirdle 3 also performs a sealing function in that it permits only a negligible leakage of propellant charge gases to the atmosphere surrounding the barrel. When thegirdle 3 passes the muzzle of the barrel (shown schematically at 1 a), the propellant charge gases however rush out of the barrel. That portion of the propellant charge gases which is present in thespace 13 between thefins 8 and in the gap-shaped space 11 then passes along the wind surfaces of thefins 8, which are located on edge, so that the fins are jerked by the gases into the extended position (see Figure 8) because of the assisting frictional force which is generated between the rapidly emerging gases and the fins. - Because the wedge-shaped space 11 is filled by propellant charge gases, an extending force is also imposed on the
fins 8, because the gases in space 11 exert a direct pressure against theedges 12 of the fins. - The
fins 8 have their centre of gravity G closer to the projectile axis than the centre ofrotation 9 of the fins, so that the acceleration forces on the projectile during its discharge bring about a moment which attempts to hold in thefins 8 during passage through the barrel. This location of the centre of gravity is particularly advisable for rotating projectiles. - If required the
fins 8 can be skewed at a predetermined twist angle v as so as to maintain or bring about a desired degree of rotation. This is illustrated in Figures 7 and 8 which show how thefins 8 are mounted inoblique grooves 14 in thefin attachment 7. Here therear section 6 has a supportingheel 15 on the skewed side of eachfin 8 which prevents the fins being deformed as a result of the accelerational forces to which it is subjected during its passage through the barrel. Such supporting heels can possibly be arranged on both sides of the fins. Alternatively, this support function can be provided by grooves in therear section 6. - To provide clarity in the illustrations, only one of the supporting
heels 15 is sketched in Figure 4. Similar skewing arrangements with supporting heels are advisably (but not necessarily) arranged also in the embodiments described in the following, although to ensure greater clarity in the drawings they are not shown. - Figure 2 illustrates a second embodiment of the invention which in principle differs from the embodiment shown in Figure 1 only in that the rear section of the
projectile 2 is replaced by aguidance mechanism tube 16, shown partially in section, which tapers away forwards and which is open at the rear and which at the front by means for example of a screw connection is fastened to a centrally arrangedheel 17 at the rear end of theprojectile 2. The interior oftube 16 by this means forms achamber 18 which is open rearwards towards thepropellant charge 5. Thetube 16 is provided with sixlongitudinal slots 19 through which thefins 8 can be partially introduced, as indicated by thedashed edge lines 12. Here theslots 19 provide support for the fins during the passage of the projectile through the barrel. - On ignition of the
propellant charge 5 in Figure 2, thechamber 18 and thespace 13 between thefins 8 is filled by the propellant charge gases from thepropellant charge 5. This ensures firstly that a larger quantity of gas passes along the wind surfaces of thefins 8 as the gases rush out to the surrounding atmosphere, and secondly that the gases enclosed in thechamber 18 during their outward rushing motion bring about a pressure which is orientated directly towards theedge 12 of thefins 8 which increases the force which extends the fins. - In the embodiment illustrated in Figure 2, the
chamber 18 and thespace 13 between thefins 8 are both open at the rear. - In accordance with a further modification of the embodiment shown in Figure 2 the
chamber 18 can be sealed at the rear whilst thespace 13 is open at the rear. Here theslots 19 are so dimensioned that they permit a flow of gas from thespace 13 to thechamber 18 even when thefins 8 are introduced into theslots 19. - The embodiment illustrated in Figure 3 differs from the embodiment shown in Figure 2 in that the conically-tapered, slotted
guidance mechanism tube 16 is replaced by aguidance mechanism tube 20 of uniform thickness, the interior of which forms acylindrical chamber 18a and which instead of slots has twoapertures 21 all the way through, these being circular in the embodiment illustrated, located in the centre of eachfin 8. Theapertures 21 have roughly the same dimensions as the thickness of thefins 8. - The rear end of the
tube 20 in the embodiment illustrated sealed by awall 22 which has a centralcircular aperture 23 all the way through which provides a direct connection between thepropellant charge 5 and the interior of theguidance mechanism tube 20. - As a result of the provision of the
apertures 21, the propellant charge gases in thetube 20 bring about a concentrated compressive force on theedge 12 on thefins 8 which faces the projectile axis, so that a particularly high force is obtained which tends to extend the fins. - In the case of projectiles where the fins because of their length do not have sufficient room in the cartridge case, it is advisable to provide a slotted tube around the fins so that the propellant charge gases can be more easily retained in the space between the fins and so that a better aerodynamic shape is obtained. This arrangement is illustrated in Figures 9 and 10, where a
tube 25 provided withslots 24 concentrically surrounds thefins 8. Theslots 24 are somewhat longer than thefins 8 and also located in the centre of these so that thefins 8 can be extended between them. With this embodiment essentially the entirelower edge 12 of thefins 8 rests against arear portion 6 on the projectile. In accordance with a modified embodiment, which is not illustrated, thefins 8 rest however only partially against therear section 6. Therear section 6 is, possibly via a strap or girdle which is not shown, and preferably exhibiting leakage, fastened into acartridge case 4 withpropellant charge 5. Therear section 6 and thetube 25 have a diameter which is somewhat smaller than thebarrel 1, so that a ring-shaped gap 26 is formed between them. In front of thefins 8 thetube 24 is provided with a strap orgirdle 27. - When the
projectile 2 has started to move in thebarrel 1 as a result of gases from the propellant charge 5 (on the right in Figure 9) the propellant charge gases flow via agap 26 in through theslots 24 and fill up the interior of thetube 25. Some degree of leakage past thestrap 27 can be permitted here, so that this can be omitted or if required can be replaced by a guide pad. - When, during the passage of the projectile through the barrel, the
fins 8 reach the barrel muzzle (not shown for reasons of clarity), the gases in thetube 25 rush outwards through theslots 24, taking with them the fins to extended position (see Figure 10) because of the entraining frictional force produced when the propellant charge gases pass along the guidance surfaces of thefins 8. - In all the embodiments illustrated and described the fixed pivot of the fins is located at the rear end of the fins, as viewed in the retracted position of the fins. However, it is also possible instead to locate the fixed pivot at the forward end of the fins, as viewed in the retracted position of the fins.
- All the embodiments illustrated and described are provided with suitable conventional locking devices for maintaining the fins in the extended position. However since such locking devices are on the one hand state of the art, and secondly do not comprise any part of the present invention, they have not been illustrated or described in greater detail.
Claims (8)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
SE8105952A SE428058B (en) | 1981-10-08 | 1981-10-08 | PROJECTIL WORKS |
SE8105952 | 1981-10-08 |
Publications (3)
Publication Number | Publication Date |
---|---|
EP0076990A2 EP0076990A2 (en) | 1983-04-20 |
EP0076990A3 EP0076990A3 (en) | 1983-05-18 |
EP0076990B1 true EP0076990B1 (en) | 1986-02-19 |
Family
ID=20344732
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP82109120A Expired EP0076990B1 (en) | 1981-10-08 | 1982-10-02 | Stabilizing fin assembly for projectile |
Country Status (5)
Country | Link |
---|---|
EP (1) | EP0076990B1 (en) |
DE (1) | DE3269205D1 (en) |
FI (1) | FI823432L (en) |
NO (1) | NO149942C (en) |
SE (1) | SE428058B (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6164594A (en) * | 1997-10-08 | 2000-12-26 | Etienne Lacroix Tous Artifices S.A. | Device for braking the fall of a load |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
IL72000A (en) * | 1984-06-04 | 1989-09-10 | Israel State | Projectile stabilization system |
SE444612B (en) * | 1984-12-13 | 1986-04-21 | Ffv Affersverket | GUIDELINES FOR FENOR EXPOSURE OF PROJECTIL |
SE518654C2 (en) * | 2000-07-03 | 2002-11-05 | Bofors Defence Ab | Methods and apparatus for artillery projectiles |
SE518656C2 (en) * | 2000-07-03 | 2002-11-05 | Bofors Defence Ab | Fine stabilized artillery grenade |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1405276A (en) * | 1918-07-10 | 1922-01-31 | John T Careaga | Expanding projectile |
NL155094B (en) * | 1969-07-15 | 1977-11-15 | Foersvarets Fabriksverk | CONTROL TUBE FOR A NON-SPINNING PROJECTILE. |
DE2721536A1 (en) * | 1977-05-13 | 1978-11-16 | Brunsch Kurt | Ballistic shell with vanes for stabilising flight path - gives greater accuracy whilst dispensing with rifled gun barrel bore |
-
1981
- 1981-10-08 SE SE8105952A patent/SE428058B/en not_active IP Right Cessation
-
1982
- 1982-10-02 DE DE8282109120T patent/DE3269205D1/en not_active Expired
- 1982-10-02 EP EP82109120A patent/EP0076990B1/en not_active Expired
- 1982-10-06 NO NO823362A patent/NO149942C/en unknown
- 1982-10-08 FI FI823432A patent/FI823432L/en not_active Application Discontinuation
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6164594A (en) * | 1997-10-08 | 2000-12-26 | Etienne Lacroix Tous Artifices S.A. | Device for braking the fall of a load |
Also Published As
Publication number | Publication date |
---|---|
NO823362L (en) | 1983-04-11 |
DE3269205D1 (en) | 1986-03-27 |
NO149942C (en) | 1984-07-18 |
NO149942B (en) | 1984-04-09 |
EP0076990A3 (en) | 1983-05-18 |
SE8105952L (en) | 1983-04-09 |
FI823432L (en) | 1983-04-09 |
SE428058B (en) | 1983-05-30 |
FI823432A0 (en) | 1982-10-08 |
EP0076990A2 (en) | 1983-04-20 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US3726231A (en) | Sabot bullet | |
US4676136A (en) | Apparatus for recoilless firing of projectiles from a lauching tube | |
US3902424A (en) | Projectile | |
GB2234331A (en) | Hollow charge liner. | |
GB2110799A (en) | An armour piercing projectile | |
US4075946A (en) | Armor piercing projectile | |
AU2005210782B8 (en) | Increment charge for fin-stabilized mortar projectile | |
US3177809A (en) | Semi-fixed artillery round | |
GB2063429A (en) | Projectile-firing weapons | |
US5725179A (en) | Expansion wave spin inducing generator | |
US2115028A (en) | Projectile and gun | |
EP0076990B1 (en) | Stabilizing fin assembly for projectile | |
EP1038152B1 (en) | Shrouded aerial bomb | |
US5148750A (en) | Unitary projectile | |
US6389977B1 (en) | Shrouded aerial bomb | |
US4967668A (en) | Puller sabot for long rod projectiles | |
US4611540A (en) | Mortar ammunition | |
US6408762B1 (en) | Clamp assembly for shrouded aerial bomb | |
US3318244A (en) | Cartridge | |
US6123289A (en) | Training projectile | |
US3662686A (en) | Rod and sabot assembly | |
EP0171473A1 (en) | A projectile stabilization system | |
US5328130A (en) | Stabilizer for a cannon projectile | |
GB2113362A (en) | Hollow charges | |
US4519316A (en) | Ammunition, preferably for machine cannons, including a projectile equipped with a tracer, with the lethal range of the projectile being limited if the target is missed |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
PUAL | Search report despatched |
Free format text: ORIGINAL CODE: 0009013 |
|
17P | Request for examination filed |
Effective date: 19821018 |
|
AK | Designated contracting states |
Designated state(s): CH DE FR GB LI |
|
AK | Designated contracting states |
Designated state(s): CH DE FR GB LI |
|
RAP1 | Party data changed (applicant data changed or rights of an application transferred) |
Owner name: AFFAERSVERKET FFV |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
AK | Designated contracting states |
Designated state(s): CH DE FR GB LI |
|
REF | Corresponds to: |
Ref document number: 3269205 Country of ref document: DE Date of ref document: 19860327 |
|
ET | Fr: translation filed | ||
PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
26N | No opposition filed | ||
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: LI Effective date: 19871031 Ref country code: CH Effective date: 19871031 |
|
GBPC | Gb: european patent ceased through non-payment of renewal fee | ||
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: FR Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 19880630 |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: PL |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: DE Effective date: 19880701 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: ST |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: GB Effective date: 19881121 |