EP0652153B1 - Venting device for exhaust gasses of missiles on a ship - Google Patents
Venting device for exhaust gasses of missiles on a ship Download PDFInfo
- Publication number
- EP0652153B1 EP0652153B1 EP19940402355 EP94402355A EP0652153B1 EP 0652153 B1 EP0652153 B1 EP 0652153B1 EP 19940402355 EP19940402355 EP 19940402355 EP 94402355 A EP94402355 A EP 94402355A EP 0652153 B1 EP0652153 B1 EP 0652153B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- frame
- missile
- ship
- group
- protective cap
- 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 - Lifetime
Links
- 238000013022 venting Methods 0.000 title 1
- 239000007789 gas Substances 0.000 claims description 11
- 239000000567 combustion gas Substances 0.000 claims description 9
- 239000002131 composite material Substances 0.000 claims description 6
- 239000007769 metal material Substances 0.000 claims description 4
- 230000001681 protective effect Effects 0.000 claims 11
- 238000010304 firing Methods 0.000 description 7
- 238000002485 combustion reaction Methods 0.000 description 2
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 239000003546 flue gas Substances 0.000 description 1
- 239000011521 glass Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 230000003313 weakening effect Effects 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
- F41F3/0413—Means for exhaust gas disposal, e.g. exhaust deflectors, gas evacuation systems
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63B—SHIPS OR OTHER WATERBORNE VESSELS; EQUIPMENT FOR SHIPPING
- B63B19/00—Arrangements or adaptations of ports, doors, windows, port-holes, or other openings or covers
- B63B19/08—Ports or like openings in vessels' sides or at the vessels' bow or stern
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63G—OFFENSIVE OR DEFENSIVE ARRANGEMENTS ON VESSELS; MINE-LAYING; MINE-SWEEPING; SUBMARINES; AIRCRAFT CARRIERS
- B63G1/00—Arrangements of guns or missile launchers; Vessels characterised thereby
Definitions
- the invention relates to a device for discharging combustion gases generated during the launching of a missile by a weapon system installed on a ship.
- the subject of the invention is therefore a device for evacuating combustion gases from the missile (s) from a weapon system installed in particular on a ship, characterized in that it is constituted by a frame integrated into the hull of the ship. and conforming to its external shape, this frame delimiting at least one orifice obstructed by a cover, the cover being ejectable under the pressure of combustion gases when at least one missile of the weapons system is fired.
- the device according to the invention is such that the covers are made of a composite material and such that the frame structure is made of metallic or composite material.
- the device is such that around each cover or group of covers to be ejected during the firing of a missile the structure of the frame present on the internal face subjected to gas pressure, a shape converging towards the external face.
- the device is such that the cover or the group of covers to be ejected during the firing of a missile are fixed to the frame which surrounds it by calibrated bolts, of which failure occurs as soon as the gas pressure exceeds a predetermined threshold.
- the device is such that it comprises, for each cover or group of covers to be ejected, at least one coiled cable connecting this cover or this group of covers to the frame, the cable is then drop down at the time of ejection.
- the device is such that the frame delimits a rectangular orifice, or else such that the frame delimits four rectangular orifices two by two superimposed.
- the present invention provides a simple and effective solution to the problem; in principle, it consists in "weakening" the hull of the ship at predetermined locations, corresponding to the outlets of missile nozzles (generally at the level of the walls) and thus allowing the weakened zones to be ejected under the pressure of the gases of combustion which then escape through the hull of the ship.
- the hull while retaining a smooth appearance for opposing radars, comprises near each missile battery a frame comprising at least one cover, the frame being fixed to the hull of the ship.
- the gas pressure causes the ejection of at least one seal, while leaving intact the covers which may not be affected, the ejection of which will only occur during the following shots.
- the frame may include only one cover, a configuration sufficient for firing a missile.
- the framework will include several lids (at least as many as missiles to fire) and the arrangement of the lids will depend on the configuration of the missiles on the firing battery.
- Figure 1 is a view of the frame in the plane of the shell.
- Figure 2 is a view of the same frame in a plane perpendicular to the plane of the hull.
- Figure 3 is a view of an operculum and its recovery system after a shot, in a plane perpendicular to the plane of the hull.
- Figure 4 is a view of the device for ejecting a cover in a plane perpendicular to the plane of the shell.
- the structure of the frame 1 defines four lids 2.
- the frame 1 is inserted into the hull 3 of the ship by bolts 4 or rivets or any other means.
- the frame 1 therefore remains fixed to the hull 3 of the ship when the lids 2 are ejected.
- the lids 2 are fixed to the structure of the frame 1 by calibrated bolts 5 or other equivalent means, such as for example a click, (see FIG. 4), in order to maintain these lids 2 on the frame 1 as long as the pressure flue gas did not exceed a threshold related to the type of missile fired.
- This threshold should not be too low, so as to keep the seal 2 in place until the missile is fired: in fact, when the weapon system is not activated, the closing presence of cover 2 is necessary, not only to promote radar stealth but also to resist the rise of "sea packets" on deck.
- the threshold should also not be too high, this in order to cause the ejection of the cover 2 sufficiently early so that the high temperature of the combustion gases has not been able to damage the deck and the walls of the ship.
- the value of the pressure generated by the gas jet of the missile being high, that of the threshold can be easily calculated.
- the structure of the frame 1 present on its internal face, exposed to the jet of gases combustion, a shape converging towards the external face: this shape is due to deflectors 6, 7, 8, 9 which aim to channel the jet on the ejectable cover 2, as well as to avoid the ejection of the covers neighbors.
- This gas pipeline does not require a significant straightening of the jet, the deflectors 6, 7, 8, 9 used (unlike those mentioned previously for the conventional gas evacuation devices) do not penalize the size, the weight and the cost.
- the lids 2 can be provided with handles 10, so as to facilitate their handling and their positioning.
- the frame structure can be made of resistant metallic or composite material.
- the lids are preferably made of composite material, essentially for reasons of weight and thermal resistance: but it is possible to use other materials which are less technically suitable (metallic materials for example) or more expensive (special glasses, ceramics, etc.). .).
- the device according to the invention has the particularity of being able to operate autonomously and passively with respect to the missile. Indeed, no signal or command to open the hatch is necessary; it is the firing of the missile and the gas jet that it causes which causes the ejection of the cover or group of covers.
Description
L'invention concerne un dispositif d'évacuation des gaz de combustion générés lors du lancement d'un missile par un système d'armes installé sur un navire.The invention relates to a device for discharging combustion gases generated during the launching of a missile by a weapon system installed on a ship.
Les missiles des systèmes d'armes pour navires de guerre sont généralement tirés depuis le pont du navire. Dans ce cas, pour protéger le pont et les superstructures contre les gaz de combustion du missile , on utilise le plus souvent des déflecteurs de jet, déviant vers l'extérieur des jets de flammes issus des missiles ; l'utilisation des déflecteurs est cependant une solution pénalisante des points de vue de l'encombrement, du poids et du coût. Afin d'éviter l'emploi des déflecteurs de jets, on peut également envisager de placer judicieusement les missiles, de façon à ce que les gaz de combustion passent au-dessus du pont ou bien s'échappent par des orifices pratiqués dans les parois : mais cette solution a, entre autres inconvénients, celui d'augmenter la détectabilité du navire par les radars adverses (on sait en effet qu'un navire est d'autant plus "furtif" que sa coque présente une apparence lisse).Weapons systems missiles for warships are generally fired from the deck of the ship. In this case, to protect the bridge and the superstructures against the combustion gases of the missile, jet deflectors are most often used, deflecting outward jets of flames from the missiles; the use of deflectors is however a penalizing solution from the point of view of space, weight and cost. In order to avoid the use of jet deflectors, it is also possible to consider placing the missiles judiciously, so that the combustion gases pass over the deck or else escape through orifices made in the walls: but this solution has, among other drawbacks, that of increasing the detectability of the ship by opposing radars (we know indeed that a ship is all the more "stealthy" as its hull has a smooth appearance).
Le problème de l'évacuation des gaz de combustion des missiles doit donc être résolu en tenant compte des quatre contraintes que sont l'encombrement, le poids, le coût et l'apparence lisse.The problem of evacuating combustion gases from missiles must therefore be resolved by taking into account the four constraints of space, weight, cost and smooth appearance.
L'invention a donc pour objet un dispositif d'évacuation des gaz de combustion du ou des missiles d'un système d'armes installé notamment sur un navire, caractérisé en ce qu'il est constitué par un cadre intégré à la coque du navire et épousant sa forme extérieure, ce cadre délimitant au moins un orifice obstrué par un opercule, l'opercule étant éjectable sous la pression des gaz de combustion lorsqu'au moins un missile du système d'armes est mis à feu.The subject of the invention is therefore a device for evacuating combustion gases from the missile (s) from a weapon system installed in particular on a ship, characterized in that it is constituted by a frame integrated into the hull of the ship. and conforming to its external shape, this frame delimiting at least one orifice obstructed by a cover, the cover being ejectable under the pressure of combustion gases when at least one missile of the weapons system is fired.
De préférence, le dispositif selon l'invention est tel que les opercules sont constitués en un matériau composite et tel que la structure du cadre est en matériau métallique ou composite.Preferably, the device according to the invention is such that the covers are made of a composite material and such that the frame structure is made of metallic or composite material.
Dans une variante de réalisation selon l'invention, le dispositif est tel qu'autour de chaque opercule ou groupe d'opercules devant être éjecté lors de la mise à feu d'un missile la structure du cadre présente, sur la face interne soumise à la pression des gaz, une forme convergeant vers la face externe.In an alternative embodiment according to the invention, the device is such that around each cover or group of covers to be ejected during the firing of a missile the structure of the frame present on the internal face subjected to gas pressure, a shape converging towards the external face.
Dans une autre variante selon l'invention, le dispositif est tel que l'opercule ou le groupe d'opercules devant être éjecté lors de la mise à feu d'un missile sont fixés au cadre qui l'entoure par des boulons tarés, dont la rupture se produit dès que la pression des gaz dépasse un seuil prédéterminé.In another variant according to the invention, the device is such that the cover or the group of covers to be ejected during the firing of a missile are fixed to the frame which surrounds it by calibrated bolts, of which failure occurs as soon as the gas pressure exceeds a predetermined threshold.
Dans une autre variante selon l'invention, le dispositif est tel qu'il comporte, pour chaque opercule ou groupe d'opercules devant être éjectés, au moins un câble bobiné liant cet opercule ou ce groupe d'opercules au cadre, le câble se déroulant alors au moment de l'éjection.In another variant according to the invention, the device is such that it comprises, for each cover or group of covers to be ejected, at least one coiled cable connecting this cover or this group of covers to the frame, the cable is then drop down at the time of ejection.
Dans une autre variante de réalisation selon l'invention, le dispositif est tel que le cadre délimite un orifice rectangulaire, ou bien tel que le cadre délimite quatre orifices rectangulaires deux à deux superposés.In another alternative embodiment according to the invention, the device is such that the frame delimits a rectangular orifice, or else such that the frame delimits four rectangular orifices two by two superimposed.
Ainsi la présente invention apporte une solution simple et efficace au problème ; dans son principe, elle consiste à "fragiliser" la coque du navire à des endroits prédéterminés, correspondant aux sorties de tuyères de missiles (généralement au niveau des parois) et à permettre ainsi aux zones fragilisées d'être éjectées sous la pression des gaz de combustion qui s'échappent alors au travers de la coque du navire.Thus the present invention provides a simple and effective solution to the problem; in principle, it consists in "weakening" the hull of the ship at predetermined locations, corresponding to the outlets of missile nozzles (generally at the level of the walls) and thus allowing the weakened zones to be ejected under the pressure of the gases of combustion which then escape through the hull of the ship.
Pour ce faire, la coque, tout en conservant une apparence lisse pour les radars adverses, comporte à proximité de chaque batterie de missiles un cadre comprenant au moins un opercule, le cadre étant fixé à la coque du navire. Lors du tir d'un missile, la pression des gaz provoque l'éjection d'au moins un opercule, tout en laissant intacts les opercules éventuellement non concernés, dont l'éjection ne se produira qu'au cours des tirs suivants.To do this, the hull, while retaining a smooth appearance for opposing radars, comprises near each missile battery a frame comprising at least one cover, the frame being fixed to the hull of the ship. During the firing of a missile, the gas pressure causes the ejection of at least one seal, while leaving intact the covers which may not be affected, the ejection of which will only occur during the following shots.
Le cadre peut ne comprendre qu'un seul opercule, configuration suffisante pour le tir d'un missile. Le plus souvent toutefois, le cadre comprendra plusieurs opercules (au moins autant que de missiles à tirer) et la disposition des opercules dépendra de la configuration des missiles sur la batterie de tir.The frame may include only one cover, a configuration sufficient for firing a missile. Most often, however, the framework will include several lids (at least as many as missiles to fire) and the arrangement of the lids will depend on the configuration of the missiles on the firing battery.
D'autres caractéristiques et avantages apparaissent dans la description suivante d'un mode de réalisation non limitatif, en référence aux dessins annexés sur lesquels sont représentés quatre opercules arrangés en carré, éjectables rculeindividuellement lors de chaque tir de missile et placés dans une structure qui, dans ce cas, a la forme d'une croix encadrée.Other characteristics and advantages appear in the following description of a nonlimiting embodiment, with reference to the accompanying drawings in which are shown four lids arranged in a square, ejectable rculeindividually during each missile launch and placed in a structure which, in this case, has the shape of a framed cross.
La figure 1 est une vue du cadre dans le plan de la coque.Figure 1 is a view of the frame in the plane of the shell.
La figure 2 est une vue du même cadre dans un plan perpendiculaire au plan de la coque.Figure 2 is a view of the same frame in a plane perpendicular to the plane of the hull.
La figure 3 est une vue d'un-opercule et de son système de récupération après un tir, dans un plan perpendiculaire au plan de la coque.Figure 3 is a view of an operculum and its recovery system after a shot, in a plane perpendicular to the plane of the hull.
La figure 4 est une vue du dispositif d'éjection d'un opercule dans un plan perpendiculaire au plan de la coque.Figure 4 is a view of the device for ejecting a cover in a plane perpendicular to the plane of the shell.
Comme on peut le voir dans l'exemple représenté sur la figure 1, la structure du cadre 1 délimite quatre opercules 2. Le cadre 1 est inséré dans la coque 3 du navire par des boulons 4 ou rivets ou tout autre moyen. Le cadre 1 reste donc fixé à la coque 3 du navire lorsque les opercules 2 sont éjectés.As can be seen in the example shown in Figure 1, the structure of the
Les opercules 2 sont fixés à la structure du cadre 1 par des boulons tarés 5 ou d'autres moyens équivalents, comme par exemple un cliquetage, (voir figure 4), en vue de maintenir ces opercules 2 sur le cadre 1 tant que la pression des gaz de combustion n'a pas dépassé un seuil lié au type de missile tiré. Ce seuil ne doit pas être trop faible, de façon à maintenir l'opercule 2 en place tant que le missile n'est pas mis à feu : en effet, lorsque le système d'armes n'est pas activé, la présence obturante de l'opercule 2 est nécessaire, non seulement pour favoriser la furtivité radar mais aussi pour résister aux remontées de "paquets de mer" sur le pont. Le seuil ne doit pas non plus être trop élevé, ceci afin de provoquer l'éjection de l'opercule 2 suffisamment tôt pour que la température élevée des gaz de combustion n'ait pas été en mesure d'endommager le pont et les parois du navire. La valeur de la pression générée par le jet de gaz du missile étant élevée, celle du seuil peut être calculée facilement.The
Comme on peut le voir sur la figure 2, la structure du cadre 1 présente sur sa face interne, exposée au jet des gaz de combustion, une forme convergeant vers la face externe : cette forme est due à des déflecteurs 6, 7, 8, 9 qui ont pour but de canaliser le jet sur l'opercule 2 éjectable, ainsi que d'éviter l'éjection des opercules voisins. Cette canalisation des gaz n'exigeant pas un redressement important du jet, les déflecteurs 6, 7, 8, 9 utilisés (contrairement à ceux mentionnés précédemment pour les dispositifs classiques d'évacuation des gaz) ne pénalisent pas l'encombrement, le poids et le coût. Les opercules 2 peuvent être munis de poignées 10, de façon à faciliter leur manutention et leur mise en place.As can be seen in Figure 2, the structure of the
Il peut également être avantageux, selon les cas, de disposer d'une version du dispositif selon l'invention dans laquelle les opercules 2 sont récupérés, après leur éjection. Comme on peut le voir sur la figure 3, il suffit de prévoir au niveau de l'interface entre les opercules 2 et la structure du cadre 1 un système de câble bobiné 11, dont l'une des extrémités est liée à l'opercule 2 et l'autre à la structure du cadre 1. Ainsi, lors du tir d'un missile, l'opercule 2 éjecté entraîne le câble 11 en déroulement et peut être récupéré grâce à ce dernier.It may also be advantageous, depending on the case, to have a version of the device according to the invention in which the
La structure du cadre peut être réalisée en matériau métallique ou composite résistant. Les opercules sont réalisés de préférence en matériau composite, essentiellement pour des raisons de poids et de tenue thermique : mais on peut utiliser d'autres matériaux moins adaptés techniquement (matériaux métalliques par exemple) ou plus coûteux (verres spéciaux, céramiques, etc...).The frame structure can be made of resistant metallic or composite material. The lids are preferably made of composite material, essentially for reasons of weight and thermal resistance: but it is possible to use other materials which are less technically suitable (metallic materials for example) or more expensive (special glasses, ceramics, etc.). .).
Diverses modifications peuvent être apportées au dispositif décrit ci-dessus, sans sortir du cadre de l'invention. On peut concevoir, par exemple, d'éjecter à chaque tir de missile, non plus un opercule donné, mais un groupe d'opercules : la fragilisation par boulon taré (ou autre moyen) serait alors effectuée sur la périphérie de chaque groupe d'opercules.Various modifications can be made to the device described above, without departing from the scope of the invention. One can conceive, for example, of ejecting with each launch of a missile, no longer a given operculum, but a group of opercules: embrittlement by tared bolt (or other means) would then be carried out on the periphery of each group of covers.
Outre les avantages relatifs à l'encombrement, au poids, au coût et à la furtivité radar, le dispositif selon l'invention présente la particularité de pouvoir fonctionner de façon autonome et passive par rapport au missile. En effet, aucun signal ou commande d'ouverture de trappe n'est nécessaire ; c'est la mise à feu du missile et le jet de gaz qu'elle entraîne qui provoque l'éjection de l'opercule ou du groupe d'opercules.In addition to the advantages relating to the size, the weight, the cost and the radar stealth, the device according to the invention has the particularity of being able to operate autonomously and passively with respect to the missile. Indeed, no signal or command to open the hatch is necessary; it is the firing of the missile and the gas jet that it causes which causes the ejection of the cover or group of covers.
Claims (7)
- Device for exhausting combustion gases from at least one missile in a weapons system, installed, for example, on board a ship, characterized in that it comprises a frame (1) incorporated in the hull (3) of the ship and emulating its external shape, this frame (1) demarcating at least one orifice plugged with a protective cap (2), with the protective cap (2) being ejectable under the pressure of the combustion gases when at least one missile in the weapons system is fired.
- Device according to claim 1, characterized in that the protective caps (2) are made from a composite material and in that the structure of the frame (1) is made from a metal or composite material.
- Device according to claim 2, characterized in that around each protective cap (2) or group of protective caps that have to be ejected when the missile is fired the frame (1) structure on its internal face which is subjected to the pressure of the gases has a shape that converges towards the external face.
- Device according to claim 1, characterized in that the protective cap (2) or group of protective caps that have to be ejected when the missile is fired, are attached to the frame (1) which surround them by means of calibrated bolts (5) which break as soon as the pressure of the gases exceeds a pre-determined threshold.
- Device according to any of the preceding claims, characterized in that it comprises, for each protective cap (2) or group of protective caps that have to be ejected, at least one coiled cable (11) which joins this protective cap (2) or this group of protective caps to the frame (1), with the cable unwinding at the moment of ejection.
- Device according to any of the preceding claims, characterized in that the frame (1) demarcates a rectangular orifice.
- Device according to any of the claims 1 to 5, characterized in that the frame (1) demarcates four rectangular orifices arranged in 2 sets of two, one on top of the other.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR9313129 | 1993-11-04 | ||
| FR9313129A FR2711966B1 (en) | 1993-11-04 | 1993-11-04 | Device for evacuating combustion gases from missiles on a ship. |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP0652153A1 EP0652153A1 (en) | 1995-05-10 |
| EP0652153B1 true EP0652153B1 (en) | 1996-04-10 |
Family
ID=9452505
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP19940402355 Expired - Lifetime EP0652153B1 (en) | 1993-11-04 | 1994-10-20 | Venting device for exhaust gasses of missiles on a ship |
Country Status (5)
| Country | Link |
|---|---|
| EP (1) | EP0652153B1 (en) |
| DE (1) | DE69400133T2 (en) |
| ES (1) | ES2088313T3 (en) |
| FR (1) | FR2711966B1 (en) |
| TW (1) | TW367035U (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2933373B1 (en) * | 2008-07-03 | 2010-08-20 | Dcns | PRINCIPLE OF INTEGRATION, AGAINST ASYMMETRIC THREATS, OF MISSIL ARMS SYSTEMS ON FIXED RAMP FOR FURTHER SURFACE BUILDING |
| CN114459286A (en) * | 2021-08-06 | 2022-05-10 | 北京天兵科技有限公司 | Rocket tail flame guiding device |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4186647A (en) * | 1978-08-09 | 1980-02-05 | General Dynamics Corporation, Pomona Division | Multiple area rear launch tube cover |
| US4471684A (en) * | 1981-09-14 | 1984-09-18 | Fmc Corporation | Transom missile launcher module |
| GB2121149B (en) * | 1982-05-27 | 1985-07-24 | British Aerospace | Missile housing and launch arrangement |
| US5162605A (en) * | 1992-01-16 | 1992-11-10 | General Dynamics Corporation | Self-activated rocket launcher cell closure |
-
1993
- 1993-11-04 FR FR9313129A patent/FR2711966B1/en not_active Expired - Fee Related
-
1994
- 1994-10-20 EP EP19940402355 patent/EP0652153B1/en not_active Expired - Lifetime
- 1994-10-20 ES ES94402355T patent/ES2088313T3/en not_active Expired - Lifetime
- 1994-10-20 DE DE1994600133 patent/DE69400133T2/en not_active Expired - Fee Related
- 1994-12-30 TW TW086202089U patent/TW367035U/en unknown
Also Published As
| Publication number | Publication date |
|---|---|
| DE69400133D1 (en) | 1996-05-15 |
| FR2711966B1 (en) | 1995-12-22 |
| FR2711966A1 (en) | 1995-05-12 |
| TW367035U (en) | 1999-08-11 |
| EP0652153A1 (en) | 1995-05-10 |
| DE69400133T2 (en) | 1996-09-05 |
| ES2088313T3 (en) | 1996-08-01 |
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