EP0055139A1 - Chaff rocket - Google Patents
Chaff rocket Download PDFInfo
- Publication number
- EP0055139A1 EP0055139A1 EP81306104A EP81306104A EP0055139A1 EP 0055139 A1 EP0055139 A1 EP 0055139A1 EP 81306104 A EP81306104 A EP 81306104A EP 81306104 A EP81306104 A EP 81306104A EP 0055139 A1 EP0055139 A1 EP 0055139A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- chaff
- rocket
- packs
- pack
- spinning
- 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.)
- Withdrawn
Links
- 238000009987 spinning Methods 0.000 claims abstract description 17
- 238000002485 combustion reaction Methods 0.000 claims description 10
- 239000003380 propellant Substances 0.000 claims description 4
- 238000006243 chemical reaction Methods 0.000 claims description 2
- 239000011888 foil Substances 0.000 description 5
- 230000005484 gravity Effects 0.000 description 3
- 235000015842 Hesperis Nutrition 0.000 description 2
- 235000012633 Iberis amara Nutrition 0.000 description 2
- 230000001934 delay Effects 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 229910001385 heavy metal Inorganic materials 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 239000002923 metal particle Substances 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 238000005192 partition Methods 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
- F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
- F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
- F42B12/56—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies
- F42B12/70—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies for dispensing radar chaff or infrared material
Definitions
- the present invention relates to chaff rockets.
- Rockets may be used for distributing chaff, which may consist of very many small metal particles, metallized fibres or other material giving an echo on radar.
- chaff is not easy to distribute widely since individual particles have small mass and high air resistance, hence they quickly lose momentum during distribution. This can lead to a long "blooming time", “blooming time” meaning the time taken for a load of chaff to become distributed in a cloud of a certain size.
- the objection of the invention is to utilize the spin of a spinning rocket to achieve distribution of chaff.
- a chaff rocket comprising a load of chaff, means for ejecting the chaff from the rocket; means for propelling the rocket by propellant combustion; and means for spinning the rocket rapidly during flight by reaction of combustion efflux gas.
- the load of chaff may be ejected as a single batch which is spinning. Usually the ejection will be longitudinally of the rocket and distribution will occur longitudinally. Since the batch is spinning distribution will additionally occur radially giving a faster blooming time than if distibution were occurring only longitudinally.
- the load of chaff is provided in a plurality of individual packs.
- the packs arranged with their individual centres of gravity eccentric from the central axis of the rocket about which it is spinning so that, on ejection, they fly out radially.
- the packs may be open so that distribution of chaff itself starts as soon as the packs are ejected.
- each pack it is advantageous for each pack to have two openings, air being scooped in at one o p eningas the pack spins and the chaff being blown out of the other opening by the scooped air.
- the spin of the rocket is of two fold advantage, firstly in flinging the packs from the rocket and secondly in distributing the chaff from the packs.
- the packs may alternatively be closed and provided with a time delay device which enables them to fly out an appreciable distance before opening. Then they may open mechanically or they may be blown open pyrotechnically. In either case blooming is effectively speeded since the chaff is distributed from a number of spaced positions.
- To increase the distance flown out before opening part of each pack may be of a heavy metal such as lead to enable the pack to maintain its momentum in flight from the rocket.
- the rate of spin of the rocket must be high (typically 8,000 rpm) for effective distribution of chaff in an acceptable blooming time.
- the preferred means for spinning the rocket is angling of the propulsion jet nozzles.
- separate spin nozzles may be provided in addition to the. main propulsion nozzles.
- annular jet nozzle with spinning slits or fins disposed in the efflux gas stream such as is disclosed in our British Patent Application No.7937621.
- Active spinning is to be distinguished from passive spinning such as may be provided by angled rails in a launcher or by angled flight stabilization fins on which the air impinges during flight. Passive spinning means do not, as a rule, give a sufficiently high rate of spin (typically only 500 - 1,000 rpm), for an adequate blooming time.
- the rocket 1 of Figure 1 has a combustion chamber 2 and a pay-load chamber 3. Angled jet nozzles 4 opening from the combustion chamber are provided for propelling and spinning the rocket in flight, typically at 8,000 rpm for a 57 mm diameter rocket.
- a partition 5 between the combustion chamber 2 and the pay-load chamber 3 carries a fuse 6 which is ignited on ignition of the propellant charge 7. After a suitable inflight delay the fuse 6 ignites an ejection charge 8 which ejects a plurality of chaff packs 9 from the pay-load chamber 3. At the time of ejection, the chaff packs will be spinning with the rocket and consequently fly out radially of the flight path as described in more detail below.
- One rocket may carry a large number of chaff packs 9.
- fourteen are shown in Figure 1. They are semi-circular and loaded in.pairs with each successive pair set at right angles to the previous pair.
- Figure 2 shows three pairs of packs being loaded.
- Figure 3 shows a pair of packs in more detail.
- Each pack has a shell consisting of a semi-circular top 10 and a semi-circular bottom 11 with a back 12 connecting them, the three parts of the shell being formed of a single piece of bent sheet metal.
- a further U shaped piece 13 is connected between the top and the bottom at the fron of the pack.
- the chaff is contained within a foil wrapping 14 in the pack. The foil is exposed at openings 15, 16 on either side of the U piece 13.
- the foil is slit for release of the chaff once the pack is ejected.
- the individual packs are paired back-to-back, so that their combined centre of gravity 17 will be on the central axis of the rocket.
- the individual centres of gravity 18 are eccentrically positioned with the result thai. the packs fly out with a radial. component of velocity from the rocket when ejected. They continue to spin in flight with the result that air enters the opening 15 and distributes the chaff from the opening 16, with the anticlockwise spin shown in Figure 4, to form a chaff cloud 9.
- the chaff pack 20 shown in Figure 5 embodies a mechanical delay which prevents chaff being distributed therefrom until the pack has flown out radially some distance from the rocket.
- Individual packs 20 are inserted into the rocket in the same manner as the packs 9 of Figure 3.
- the packs 20 include upper and lower semi-circular plates 21, 22 between which foil wrapped chaff 23 is sandwiched.
- the plates 21, 22 have lips 24, 25 between which is left a gap 26.
- the pack is held together by an elastomeric band 27 tight by a tourniquet 28, which is accommodated in the gap 26.
- a strip 29 of lead bent to the semi-circular contour of the plates extends around the front of the pack outside the chaff but within the front edges of the plates.
- Figure 6 shows a pack 20 flying radially from the rocket.
- FIG 8. Another alternative pair of packs 31 is shown in Figure 8. They each have a shell 32 similar to that of pack 9 shown in Figure 3, except that the shell is fully open at the front.
- a fuse 33 is provided, which extends centrally along the entire load of chaff packs and is ignited immediately prior to ejection of the chaff packs from the rocket.
- Surrounding the fuse 33, within the shell 33 is a small charge 34 at the centre of foil wrapped chaff 35. On ejection the fuse 33 burns through with a slight delay to allow the pack to fly radially from the rocket for a certain distance, whereupon the charge 34 explodes distributing the chaff into a cloud 36.
- chaff packs may be used e.g. third or quarter circular as opposed to semi-circular. Other delays may be used.
- the chaff packs may be ejected mechanically as opposed to pyrotechnically.
Landscapes
- Engineering & Computer Science (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Radar Systems Or Details Thereof (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
A rocket (1) for distributing metallized chaff has a chamber (3) containing the chaff, means (8) for ejecting the chaff and means (4) for actively spinning the rocket (1) at high speed during flight so as to distribute the chaff effectively on release. The chaff is preferably contained in individual packets (9) which fly apart when ejected.
Description
- The present invention relates to chaff rockets.
- Rockets may be used for distributing chaff, which may consist of very many small metal particles, metallized fibres or other material giving an echo on radar. By its nature chaff is not easy to distribute widely since individual particles have small mass and high air resistance, hence they quickly lose momentum during distribution. This can lead to a long "blooming time", "blooming time" meaning the time taken for a load of chaff to become distributed in a cloud of a certain size.
- The objection of the invention is to utilize the spin of a spinning rocket to achieve distribution of chaff.
- According to the invention, there is provided a chaff rocket comprising a load of chaff, means for ejecting the chaff from the rocket; means for propelling the rocket by propellant combustion; and means for spinning the rocket rapidly during flight by reaction of combustion efflux gas.
- The load of chaff may be ejected as a single batch which is spinning. Usually the ejection will be longitudinally of the rocket and distribution will occur longitudinally. Since the batch is spinning distribution will additionally occur radially giving a faster blooming time than if distibution were occurring only longitudinally.
- Preferably, however, the load of chaff is provided in a plurality of individual packs. The packs arranged with their individual centres of gravity eccentric from the central axis of the rocket about which it is spinning so that, on ejection, they fly out radially.
- The packs may be open so that distribution of chaff itself starts as soon as the packs are ejected. In this case it is advantageous for each pack to have two openings, air being scooped in at one openingas the pack spins and the chaff being blown out of the other opening by the scooped air. Here the spin of the rocket is of two fold advantage, firstly in flinging the packs from the rocket and secondly in distributing the chaff from the packs.
- The packs may alternatively be closed and provided with a time delay device which enables them to fly out an appreciable distance before opening. Then they may open mechanically or they may be blown open pyrotechnically. In either case blooming is effectively speeded since the chaff is distributed from a number of spaced positions. To increase the distance flown out before opening part of each pack may be of a heavy metal such as lead to enable the pack to maintain its momentum in flight from the rocket.
- The rate of spin of the rocket must be high (typically 8,000 rpm) for effective distribution of chaff in an acceptable blooming time.Accordingly, the preferred means for spinning the rocket is angling of the propulsion jet nozzles. Alternatively, separate spin nozzles may be provided in addition to the. main propulsion nozzles. In another arrangement there is provided an annular jet nozzle with spinning slits or fins disposed in the efflux gas stream, such as is disclosed in our British Patent Application No.7937621. These means for imparting a high rate of spin to the rocket are all active spinning means in that the efflux gas from propulsion combustion is harnessed to spin the rocket. It is envisaged that other active spinning means may be used in that efflux gas from combustion separate from the propulsion combustion may be used. Active spinning is to be distinguished from passive spinning such as may be provided by angled rails in a launcher or by angled flight stabilization fins on which the air impinges during flight. Passive spinning means do not, as a rule, give a sufficiently high rate of spin (typically only 500 - 1,000 rpm), for an adequate blooming time.
- To help understanding of the invention an embodiment thereof will now be described, by way of example, with reference to the accompanying drawings in which:-
- Figure 1 is a diagrammatic longitudinal section of a rocket according to the invention;
- Figure 2 is a diagrammatic perspective view of chaff packs being inserted into the rocket of Figure 1;
- Figure 3 combines plan, side and end views of a pair of chaff packs as shown in Figure 2;
- Figure 4 is a perspective view of one chaff pack of Figure 3 distributing chaff;
- Figure 5 combines plan, side and end views of an alternative chaff pack having a mechanical opening arrangement;
- Figure 6 is a perspective view of the chaff pack of Figure 5 in flight;
- Figure 7 is a perspective view of the chaff pack of Figure 5 opened and distributing chaff;
- Figure 8 combines a plan, side and end view of another alternative chaff pack having a pyrotechnic opening arrangement; and
- Figure 9 is a perspective view of the chaff pack of Figure 8 after explosion to distribute the chaff.
- The rocket 1 of Figure 1 has a
combustion chamber 2 and a pay-load chamber 3. Angled jet nozzles 4 opening from the combustion chamber are provided for propelling and spinning the rocket in flight, typically at 8,000 rpm for a 57 mm diameter rocket. Apartition 5 between thecombustion chamber 2 and the pay-load chamber 3 carries afuse 6 which is ignited on ignition of thepropellant charge 7. After a suitable inflight delay thefuse 6 ignites anejection charge 8 which ejects a plurality ofchaff packs 9 from the pay-load chamber 3. At the time of ejection, the chaff packs will be spinning with the rocket and consequently fly out radially of the flight path as described in more detail below. - One rocket may carry a large number of
chaff packs 9. For example fourteen are shown in Figure 1. They are semi-circular and loaded in.pairs with each successive pair set at right angles to the previous pair. Figure 2 shows three pairs of packs being loaded. Figure 3 shows a pair of packs in more detail. Each pack has a shell consisting of asemi-circular top 10 and asemi-circular bottom 11 with aback 12 connecting them, the three parts of the shell being formed of a single piece of bent sheet metal. A further U shapedpiece 13 is connected between the top and the bottom at the fron of the pack. The chaff is contained within a foil wrapping 14 in the pack. The foil is exposed atopenings U piece 13. As the packs are inserted, the foil is slit for release of the chaff once the pack is ejected. The individual packs are paired back-to-back, so that their combined centre ofgravity 17 will be on the central axis of the rocket. However the individual centres ofgravity 18 are eccentrically positioned with the result thai. the packs fly out with a radial. component of velocity from the rocket when ejected. They continue to spin in flight with the result that air enters theopening 15 and distributes the chaff from theopening 16, with the anticlockwise spin shown in Figure 4, to form achaff cloud 9. - The
chaff pack 20 shown in Figure 5 embodies a mechanical delay which prevents chaff being distributed therefrom until the pack has flown out radially some distance from the rocket.Individual packs 20 are inserted into the rocket in the same manner as thepacks 9 of Figure 3. Thepacks 20 include upper and lowersemi-circular plates chaff 23 is sandwiched. Theplates lips gap 26. The pack is held together by anelastomeric band 27 tight by atourniquet 28, which is accommodated in thegap 26. Astrip 29 of lead bent to the semi-circular contour of the plates extends around the front of the pack outside the chaff but within the front edges of the plates. Figure 6 shows apack 20 flying radially from the rocket. Since thetourniquet 28 is no longer constrained in thegap 26 by the pack, being placed in back-to-back relationship with another such pack, it unwinds and releases theband 27. Figure 7 shows the position where the band has become loose and the pack has spun out of it. Theplates lead strip 29 separate leaving the chaff to form acloud 30. - Another alternative pair of
packs 31 is shown in Figure 8. They each have ashell 32 similar to that ofpack 9 shown in Figure 3, except that the shell is fully open at the front. At the centre of the back afuse 33 is provided, which extends centrally along the entire load of chaff packs and is ignited immediately prior to ejection of the chaff packs from the rocket. Surrounding thefuse 33, within theshell 33 is asmall charge 34 at the centre of foil wrappedchaff 35. On ejection thefuse 33 burns through with a slight delay to allow the pack to fly radially from the rocket for a certain distance, whereupon thecharge 34 explodes distributing the chaff into acloud 36. - The invention is not intended to be restricted to the details of the above described embodiments. Other configurations of chaff packs may be used e.g. third or quarter circular as opposed to semi-circular. Other delays may be used. The chaff packs may be ejected mechanically as opposed to pyrotechnically.
Claims (7)
1. A chaff rocket comprising a load of chaff, means for ejecting the chaff from the rocket; means for propelling the rocket by propellant combustion; and means for spinning the rocket rapidly during flight by reaction of combustion efflux gas.
2. A chaff rocket as claimed in claim 1 wherein the propellant efflux gas is directed through ducts to give a tangential component of motion.
3. A chaff rocket as claimed in claim 1 or claim 2 wherein the chaff is contained in a plurality of individual packs, which packs fly apart from each other, on ejection from the rocket, by virtue of the spinning action.
4. A chaff rocket as claimed in claim 3 wherein the packs having openings from which the chaff is distributed during flight.
5. A chaff rocket as claimed in claim 3 wherein the packs have delayed-action devices to release the chaff after some delay following ejection from the rocket.
6. A chaff rocket as claimed in claim 5 wherein the delayed-action devices are mechanical devices comprising tourniquet-held resilient bands.
7. A chaff rocket as claimed in any of claims 3 to 6 wherein the individual packs are semi-circular and are mounted back-to-back in pairs in the rocket.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB8041256 | 1980-12-23 | ||
GB8041256 | 1980-12-23 |
Publications (1)
Publication Number | Publication Date |
---|---|
EP0055139A1 true EP0055139A1 (en) | 1982-06-30 |
Family
ID=10518206
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP81306104A Withdrawn EP0055139A1 (en) | 1980-12-23 | 1981-12-23 | Chaff rocket |
Country Status (2)
Country | Link |
---|---|
EP (1) | EP0055139A1 (en) |
JP (1) | JPS57172199A (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2124740A (en) * | 1982-06-16 | 1984-02-22 | Diehl Gmbh & Co | Dipole system in a casing |
EP0124183A2 (en) * | 1983-05-03 | 1984-11-07 | Philips Norden AB | A cartridge for launching decoys |
DE19617701A1 (en) * | 1996-05-03 | 1997-11-20 | Buck Chem Tech Werke | Method of providing a dummy target |
WO2010082880A1 (en) * | 2009-01-16 | 2010-07-22 | Saab Ab | Cassette arranged for accommodating a pay load of pyrophoric material |
Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3308759A (en) * | 1963-02-04 | 1967-03-14 | Mb Assoc | Radar reflector rocket |
US3741125A (en) * | 1960-11-22 | 1973-06-26 | Us Navy | Stabilized rocket head |
US3765336A (en) * | 1972-01-28 | 1973-10-16 | Us Navy | Chaff bullet |
FR2275748A1 (en) * | 1974-06-20 | 1976-01-16 | Bofors Ab | VEHICLE INTENDED TO DISPERSAL INSTANTLY A LOAD OF REFLECTIVE MATERIAL |
US4195571A (en) * | 1979-04-02 | 1980-04-01 | The United States Of America As Represented By The Secretary Of The Army | Modular wheel dispenser |
FR2474699A1 (en) * | 1980-01-30 | 1981-07-31 | Ruggieri Ets | Electromagnetic dipole projectile for radar target signalling - employs gas generator piston to disperse cloud of dipoles via rifled tube |
Family Cites Families (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS5922503B2 (en) * | 1976-08-31 | 1984-05-26 | 俊司 阿部 | Method for producing rice crackers and snacks |
JPS54100200A (en) * | 1978-01-23 | 1979-08-07 | Tech Res & Dev Inst Of Japan Def Agency | Chaft bullet |
-
1981
- 1981-12-23 EP EP81306104A patent/EP0055139A1/en not_active Withdrawn
- 1981-12-23 JP JP20722981A patent/JPS57172199A/en active Pending
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3741125A (en) * | 1960-11-22 | 1973-06-26 | Us Navy | Stabilized rocket head |
US3308759A (en) * | 1963-02-04 | 1967-03-14 | Mb Assoc | Radar reflector rocket |
US3765336A (en) * | 1972-01-28 | 1973-10-16 | Us Navy | Chaff bullet |
FR2275748A1 (en) * | 1974-06-20 | 1976-01-16 | Bofors Ab | VEHICLE INTENDED TO DISPERSAL INSTANTLY A LOAD OF REFLECTIVE MATERIAL |
US4195571A (en) * | 1979-04-02 | 1980-04-01 | The United States Of America As Represented By The Secretary Of The Army | Modular wheel dispenser |
FR2474699A1 (en) * | 1980-01-30 | 1981-07-31 | Ruggieri Ets | Electromagnetic dipole projectile for radar target signalling - employs gas generator piston to disperse cloud of dipoles via rifled tube |
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2124740A (en) * | 1982-06-16 | 1984-02-22 | Diehl Gmbh & Co | Dipole system in a casing |
EP0124183A2 (en) * | 1983-05-03 | 1984-11-07 | Philips Norden AB | A cartridge for launching decoys |
EP0124183A3 (en) * | 1983-05-03 | 1985-07-03 | Philips Norden Ab | A cartridge for launching decoys |
DE19617701A1 (en) * | 1996-05-03 | 1997-11-20 | Buck Chem Tech Werke | Method of providing a dummy target |
US5835051A (en) * | 1996-05-03 | 1998-11-10 | Buck Werke Gmbh & Co. | Method for offering a phantom target |
DE19617701C2 (en) * | 1996-05-03 | 2000-01-13 | Buck Werke Gmbh & Co I K | Method of providing a dummy target |
WO2010082880A1 (en) * | 2009-01-16 | 2010-07-22 | Saab Ab | Cassette arranged for accommodating a pay load of pyrophoric material |
US9851183B2 (en) | 2009-01-16 | 2017-12-26 | Saab Ab | Cassette arranged for accommodating a pay load of pyrophoric material |
Also Published As
Publication number | Publication date |
---|---|
JPS57172199A (en) | 1982-10-22 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US4555971A (en) | Method and apparatus for covering a target area with ammunition | |
US4147108A (en) | Warhead | |
US4793260A (en) | Spin-stabilized bomblet-carrying projectile | |
GB2091855A (en) | Chaff rocket | |
US4768440A (en) | Warhead for missiles | |
EP0055139A1 (en) | Chaff rocket | |
EP1419358B1 (en) | Method for discharging ir and radar countermeasure means and/or laser reflectors from a dispenser intended for the purpose, and dispenser intended for discharging such countermeasure | |
US3227084A (en) | Fireworks container | |
US4754706A (en) | Munition scattering projectile | |
FR2343990A1 (en) | Launcher and disperser for radar-jamming electromagnetic filaments - holds filament packets together for delayed radial dispersion | |
US3584581A (en) | Spin launch rectangular-type canister | |
US4009661A (en) | Missile warheads | |
US3946672A (en) | Rocket propelled projectile | |
US4829905A (en) | Decoy deploying ICBM warhead | |
US7261039B1 (en) | Artillery Rocket Kinetic Energy Rod Warhead | |
US7004073B2 (en) | System for dispensing projectiles and submunitions | |
GB1588114A (en) | Airborne projectile container | |
US3678857A (en) | Aerosol disseminator | |
US3536010A (en) | Cartridges | |
US4296685A (en) | Warhead with slave missiles disposed in a firing tube | |
RU2190827C2 (en) | Cluster warhead | |
DE3038462C2 (en) | ||
JP3691103B2 (en) | Parent-child ammunition | |
RU2227893C1 (en) | Cluster warhead | |
RU2060002C1 (en) | Antihail rocket |
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 |
|
AK | Designated contracting states |
Designated state(s): BE DE FR IT SE |
|
17P | Request for examination filed |
Effective date: 19821230 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN |
|
18D | Application deemed to be withdrawn |
Effective date: 19850702 |
|
RIN1 | Information on inventor provided before grant (corrected) |
Inventor name: LEVELL, BRIAN |