EP0309734A1 - Method for firing a projectile in the proximity of a target - Google Patents
Method for firing a projectile in the proximity of a target Download PDFInfo
- Publication number
- EP0309734A1 EP0309734A1 EP88113771A EP88113771A EP0309734A1 EP 0309734 A1 EP0309734 A1 EP 0309734A1 EP 88113771 A EP88113771 A EP 88113771A EP 88113771 A EP88113771 A EP 88113771A EP 0309734 A1 EP0309734 A1 EP 0309734A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- projectile
- target
- speed
- encounter
- trajectory
- 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.)
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
- F42C13/00—Proximity fuzes; Fuzes for remote detonation
- F42C13/04—Proximity fuzes; Fuzes for remote detonation operated by radio waves
Definitions
- the invention relates to a device for firing a projectile G in the vicinity of a target Z, with a device DS located in the projectile G for determining the encounter speed VB of the projectile G and the target Z.
- the ignition angle ZW (FIG. 1) of the sensor of a proximity fuse is set as a function of the speed of encounter between the projectile and the target, taking into account the main direction of action of the projectile fragments.
- This known device has the disadvantage that in addition to the mentioned device for determining the speed of encounter, a sensor for firing at the desired firing angle must be installed in the projectile.
- the object to be achieved with the present invention is to provide a device which is capable of firing the projectile precisely at the desired firing angle, the speed of encounter being precise, i.e. taking into account all factors and the "storage D" between floor and target does not have to be taken into account.
- the purpose of this measure is to make the igniter insensitive to electromagnetic interference sources.
- the igniter now measures the occurring Doppler frequencies fD1 and compares the ratio with the value previously determined by the fire control radar the ignition takes place.
- the ignition angle ZW must be independent of D.
- a projectile G moves on a trajectory A and a target Z moves on a trajectory B, wherein according to FIG. 1 the trajectories A and B are parallel to one another, according to FIG. 3 in point E. cut and are skewed towards each other according to Fig. 4.
- the distance D between the two trajectories A and B is constant and is referred to as deposit D.
- Projectile G misses target Z by this storage D.
- projectile G would have to fly on trajectory A 'in order to collide with target Z.
- the trajectory of the trajectory A is therefore also D.
- the trajectory D corresponds to the shortest distance between the trajectories A and B of the projectile G, respectively. of the target Z. If the two trajectories A and B lay two planes parallel to each other, they are at a distance D from each other.
- This angle ZW is formed by the trajectory A and the straight line GZ between floor G and target Z.
- this ignition angle ZW is dependent on the target speed VZ, on the projectile speed VG and on the mean radial splinter speed VR
- This ignition angle ZW is therefore independent of the storage D of the projectile G relative to the target Z.
- the encounter speed VB 1 between floor G and target Z is:
- the ignition angle ZW results from Fig. 2:
- the encounter speed is VB 2 :
- VB 2 VG cos ZW + VZ cos (FW + ZW) (equation 2).
- the ignition angle ZW can be determined: this results in the encounter speed VB 2 :
- the encounter speed is VB 3 :
- VB 3 VZ cos AW + VG cos ZW (equation 3).
- the ignition angle ZW can be determined: Furthermore, the angle AW between the target trajectory B and the straight line ZG between storey G and target Z can be determined:
- a Doppler sensor DS on the floor G, which emits a radar signal with the frequency f0 and receives a signal reflected by the target Z with the frequency f0 + fD.
- This Doppler sensor DS has a transmit / receive antenna SE which is connected to a mixer M.
- An oscillator OZ and a low-pass filter TP are connected to this mixer M on the one hand.
- the oscillator OZ is connected to a counter 2 via a divider T and the low-pass filter TP is also connected to the counter 2 via an amplifier V and a comparator K.
- a digital comparator 3 is present, to which on the one hand the counter 2 and on the other hand a memory 1 are connected. This digital comparator 3 emits an ignition signal ZS as soon as the quotient 2VB exceeds a given, previously measured value fD1.
- the ignition angle ZW and thus also the value cosZW changes. sinZW, as soon as the distance between target Z and floor G is not much greater than the distance D between trajectories A and D. From the above equations, in particular equations 1, 2 and 3, it can be seen that the firing angle ZW of the Encounter speed VB is dependent. The comparison of the encounter speeds with the aid of the comparator 3 thus enables the ignition at a given ignition angle ZW.
- the Doppler sensor DS of the flying projectile G As soon as the Doppler sensor DS of the flying projectile G is switched on, it emits a beam of frequency f0. The beam reflected from the target has the frequency f0 + fD. This value reaches the counter 2 via the low-pass filter TP, the amplifier V and the comparator K. From the counter 2 forwarded to the digital comparator 3. At the same time, the value 2VB g K stored in the memory 1 is also passed to the digital comparator 3. The two values are compared in comparator 3. As soon as the two values are the same, an ignition signal ZS is generated and the projectile G is fired.
- projectile G and target Z fly towards each other on parallel trajectories A and B, these two trajectories A and B being at a distance D from one another.
- this angle ZW reaches the desired value, i.e. the projectile should be fired.
Abstract
Description
Die Erfindung betrifft eine Vorrichtung zum Zünden eines Geschosses G in der Nähe eines Zieles Z, mit einem im Geschoss G befindlichen Gerät DS zur Bestimmung der Begegnungsgeschwindigkeit VB von Geschoss G und Ziel Z.The invention relates to a device for firing a projectile G in the vicinity of a target Z, with a device DS located in the projectile G for determining the encounter speed VB of the projectile G and the target Z.
Bei einer bekannten Vorrichtung dieser Art (siehe DE-A-25 27 368) wird der Zündwinkel ZW (Fig.1) des Sensors eines Annäherungszünders in Abhängigkeit der Begegnungsgeschwindigkeit zwischen Geschoss und Ziel eingestellt, wobei die Hauptwirkungsrichtung der Splitter des Geschosses berücksichtigt wird.In a known device of this type (see DE-A-25 27 368), the ignition angle ZW (FIG. 1) of the sensor of a proximity fuse is set as a function of the speed of encounter between the projectile and the target, taking into account the main direction of action of the projectile fragments.
Diese bekannte Vorrichtung hat den Nachteil, dass ausser dem erwähnten Gerät zur Bestimmung der Begegnungsgeschwindigkeit noch ein Sensor zum Zünden unter dem gewünschten Zündwinkel im Geschoss eingebaut sein muss.This known device has the disadvantage that in addition to the mentioned device for determining the speed of encounter, a sensor for firing at the desired firing angle must be installed in the projectile.
Solche Sensoren für Annäherungszünder, die bei dem gewünschten Zündwinkel ansprechen, sind bekannt (siehe US-A 3,046,892 und US-A 3,242,339).Such sensors for proximity detonators, which respond at the desired ignition angle, are known (see US Pat. No. 3,046,892 and US Pat. No. 3,242,339).
Diese bekannten Sensoren haben jedoch den Nachteil, dass sie von der Begegnungsgeschwindigkeit von Geschoss und Ziel unabhängig sind. Der Zündwinkel ZW wird meist fix eingestellt. Dies führt dazu, dass die Splitter am Ziel vorbeifliegen.However, these known sensors have the disadvantage that they are independent of the encounter speed of the projectile and the target. The ignition angle ZW is usually fixed. This causes the fragments to fly past the target.
Die Aufgabe, welche mit der vorliegenden Erfindung gelöst werden soll, besteht in der Schaffung einer Vorrichtung, welche in der Lage ist, das Geschoss genau bei dem gewünschten Zündwinkel zu zünden, wobei die Begegnungsgeschwindigkeit genau, d.h. unter Beachtung aller Faktoren berücksichtigt wird und die "Ablage D" zwischen Geschoss und Ziel nicht berücksichtigt werden muss.The object to be achieved with the present invention is to provide a device which is capable of firing the projectile precisely at the desired firing angle, the speed of encounter being precise, i.e. taking into account all factors and the "storage D" between floor and target does not have to be taken into account.
Diese Aufgabe wird dadurch gelöst, dass mit einem ortsfesten Feuerleitgerät die Begegnungsgeschwindigkeit VBg von Geschoss und Zie! nach der Flugzeit T der Granate so bestimmt wird, dass die Splitter das Ziel treffen. Der Wert
- wird während dem Abschuss der Granate G neben der Flugzeit T in den Zünder digital eingelesen und gespeichert.
- c - Lichtgeschwindigkeit,
- VBg - Begegnungsgeschwindigkeit, bei der die Splitter das Ziel treffen,
- f0-Sendefrequenz des Zünders,
- fD-Doppler-Frequenz.
- Nach T - t Sekunden wird der Annäherungssensor eingeschaltet.
- T-Flugzeit der Granate bis zur Zielkollision,
- t-Vorhaltezeit.
- is digitally read and stored in the detonator during the firing of the grenade G in addition to the flight time T.
- c - speed of light,
- VBg - encounter speed at which the fragments hit the target,
- f0 transmission frequency of the detonator,
- fD Doppler frequency.
- The proximity sensor is switched on after T - t seconds.
- T-flight time of the grenade to the target collision,
- t retention time.
Diese Massnahme hat den Zweck, den Zünder gegenüber elektromagnetischen Störquellen unempfindlich zu machen.The purpose of this measure is to make the igniter insensitive to electromagnetic interference sources.
Der Zünder misst nun die auftretenden Doppler-Frequenzen fD1 und vergleicht das Verhältnis
Da die Zielablage D vom Feuerleitrechner nur geschätzt werden kann, muss der Zündwinkel ZW unabhängig von D sein.Since the target location D can only be estimated by the fire control computer, the ignition angle ZW must be independent of D.
Ein Ausführungsbeispiel der erfindungsgemässen Vorrichtung zum Zünden eines Geschosses ist im folgenden anhand der beigefügten Zeichnung ausführlich beschrieben.An embodiment of the device for igniting a projectile is described in detail below with reference to the accompanying drawing.
Es zeigt:
- Fig.1 eine schematische Darstellung von Geschoss und Ziel im Zeitpunkt der Zündung, unter der Annahme, dass die Flugbahnen von Geschoss und Ziel parallel zueinander sind.
- Fig.2 ein Vektordiagramm mit den Geschwindigkeiten von Geschoss, Ziel und Splittern.
- Fig.3 dasselbe wie Fig.1, unter der Annahme, dass die Flugbahnen von Geschoss und Ziel schräg zueinander sind, sich aber in einer Ebene befinden.
- Fig.4 dasselbe wie Fig.1, unter der Annahme, dass die Flugbahnen von Geschoss und Ziel windschief zueinander sind.
- Fig.5 ein Blockschaltbild der erfindungsgemässen Vorrichtung zum Zünden des Geschosses.
- 1 shows a schematic representation of the projectile and target at the time of ignition, assuming that the trajectories of the projectile and target are parallel to one another.
- 2 shows a vector diagram with the speeds of the projectile, target and splinters.
- Fig.3 the same as Fig.1, assuming that the trajectories of the projectile and target are oblique to each other, but are in one plane.
- Fig.4 the same as Fig.1, assuming that the trajectories of the projectile and target are skewed to each other.
- 5 shows a block diagram of the device according to the invention for igniting the projectile.
Gemäss Fig.1, 3 und 4 bewegt sich ein Geschoss G auf einer Flugbahn A und ein Ziel Z bewegt sich auf einer Flugbahn B, wobei gemäss Fig.1 die Flugbahnen A und B parallel zueinander sind, gemäss Fig.3 sich im Punkte E schneiden und gemäss Fig.4 windschief zueinander sind. Gemäss Fig.1 ist der Abstand D der beiden Flugbahnen A und B konstant und wird als Ablage D bezeichnet.1, 3 and 4, a projectile G moves on a trajectory A and a target Z moves on a trajectory B, wherein according to FIG. 1 the trajectories A and B are parallel to one another, according to FIG. 3 in point E. cut and are skewed towards each other according to Fig. 4. According to FIG. 1, the distance D between the two trajectories A and B is constant and is referred to as deposit D.
Um diese Ablage D verfehlt das Geschoss G das Ziel Z. Gemäss Fig.3 müsste das Geschoss G auf der Flugbahn A' fliegen, um mit dem Ziel Z zu kollidieren. Die Ablage der Flugbahn A beträgt somit ebenfalls D. Gemäss Fig.4 entspricht die Ablage D dem kürzesten Abstand zwischen den Flugbahnen A und B des Geschosses G, bezw. des Zieles Z. Werden durch die beiden Flugbahnen A und B zwei zueinander parallel gedachte Ebenen gelegt, so haben diese den Abstand D voneinander.Projectile G misses target Z by this storage D. According to FIG. 3, projectile G would have to fly on trajectory A 'in order to collide with target Z. The trajectory of the trajectory A is therefore also D. According to FIG. 4, the trajectory D corresponds to the shortest distance between the trajectories A and B of the projectile G, respectively. of the target Z. If the two trajectories A and B lay two planes parallel to each other, they are at a distance D from each other.
Beim Zünden des Geschosses G fliegen die Splitter S mit einer Geschwindigkeit VS in Richtung des Splitterabgangwinkels SW gegen das Ziel Z. Dieser Winkel SW ist von der Geschwindigkeit VG des Geschosses G und von der mittleren radialen Geschwindigkeit VR der Splitter S abhängig. Gemäss Fig.1 ist
Damit die Splitter S des Geschosses G das Ziel Z erreichen, muss das Geschoss G beim Zündwinkel ZW gezündet werden. Dieser Winkel ZW wird durch die Flugbahn A und die Gerade GZ zwischen Geschoss G und Ziel Z gebildet.So that the splinters S of the projectile G reach the target Z, the projectile G must be ignited at the ignition angle ZW. This angle ZW is formed by the trajectory A and the straight line GZ between floor G and target Z.
Gemäss Fig.2 ist dieser Zündwinkel ZW von der Zielgeschwindigkeit VZ, von der Geschossgeschwindigkeit VG und von der mittleren radialen Splittergeschwindigkeit VR abhängig und zwar ist
Somit ist dieser Zündwinkel ZW von der Ablage D des Geschosses G gegenüber dem Ziel Z unabhängig.This ignition angle ZW is therefore independent of the storage D of the projectile G relative to the target Z.
Gemäss Fig.1 beträgt die Begegnungsgeschwindigkeit VB1 zwischen Geschoss G und Ziel Z :
Gemäss Fig.4 lässt sich der Zündwinkel ZW bestimmen:
Gemäss Fig.5 befindet sich im Geschoss G ein Doppler-Sensor DS, der ein Radarsignal mit der Frequenz f0 ausstrahlt und ein vom Ziel Z reflektiertes Signal mit der Frequenz f0 + fD empfängt. Dieser Doppler-Sensor DS besitzt eine Sende - Empfangs - Antenne SE, die mit einem Mischer M verbunden ist. An diesem Mischer M ist einerseits ein Oszillator OZ und andererseits ein Tiefpass TP angeschlossen. Der Oszillator OZ ist über einen Teiler T an einem Zähler 2 angeschlossen und der Tiefpass TP ist über einen Verstärker V und einen Komparator K ebenfalls an den Zähler 2 angeschlossen. Ferner ist ein digitaler Komparator 3 vorhanden, an den einerseits der Zähler 2 und andererseits ein Speicher 1 angeschlossen sind. Dieser digitale Komparator 3 gibt ein Zündsignal ZS ab, sobald der Quotient 2VB einen gegebenen, zuvor gemessenen Wert fD1 überschreitet. Mit diesem Dopplersensor wird nun die BegegnungsgeschwindigkeitAccording to FIG. 5, there is a Doppler sensor DS on the floor G, which emits a radar signal with the frequency f0 and receives a signal reflected by the target Z with the frequency f0 + fD. This Doppler sensor DS has a transmit / receive antenna SE which is connected to a mixer M. An oscillator OZ and a low-pass filter TP are connected to this mixer M on the one hand. The oscillator OZ is connected to a
Andererseits wird von einem Feuerleitgerät die Begegnungsgeschwindigkeit VBg und der Zündwinkel ZW so bestimmt, dass unter Berücksichtigung:
- a) der Zielgeschwindigkeit VZ nach T Sekunden,
- b) der radialen Splittergeschwindigkeit VR,
- c) der Geschossgeschwindigkeit VG nach T Sekunden,
- d) dem Winkel FW (zwischen Flugbahnen A + B),
- die Splitter der Granate das Ziel treffen. Hierzu wird das Verhältnis
- während dem Abschuss der Granate in den Zünder übertragen.
- a) the target speed VZ after T seconds,
- b) the radial splinter speed VR,
- c) the bullet speed VG after T seconds,
- d) the angle FW (between trajectories A + B),
- the fragments of the grenade hit the target. This is the relationship
- transferred to the detonator while the grenade was fired.
Gemäss Fig.1, 3 und 4 ändert sich der Zündwinkel ZW und somit auch der Wert cosZW bezw. sinZW, sobald der Abstand zwischen Ziel Z und Geschoss G nicht viel grösser ist, als die Ablage D zwischen den Flugbahnen A und D. Aus den obigen Gleichungen, insbesondere den Gleichungen 1, 2 und 3, ist ersichtlich, dass der Zündwinkel ZW von der Begegnungsgeschwindigkeit VB abhängig ist. Somit ermöglicht der Vergleich der Begegnungsgeschwindigkeiten mit Hilfe des Komparators 3 die Zündung bei einem gegebenen Zündwinkel ZW.1, 3 and 4, the ignition angle ZW and thus also the value cosZW changes. sinZW, as soon as the distance between target Z and floor G is not much greater than the distance D between trajectories A and D. From the above equations, in
Die Wirkungsweise der beschriebenen Vorrichtung ist wie folgt:
- Beim Abschuss eines Geschosses G wird einerseits die Abschussgeschwindigkeit VGO des Geschosses G und andererseits die Geschwindigkeit VZ des Zieles mit Hilfe eines Feuerleitgerätes bekannter Bauart bestimmt. Aus diesen beiden Werten lässt sich die Begegnungsgeschwindigkeit VBg von Geschoss G und Ziel Z berechnen. Dieser berechnete Wert wird im Speicher 1 gespeichert, zum Beispiel in der Form
- When a projectile G is fired, the launch speed VGO of the projectile G and on the other hand the speed VZ of the target are determined with the aid of a known fire control device. The encounter speed VBg of floor G and target Z can be calculated from these two values. This calculated value is stored in memory 1, for example in the form
Sobald der Dopplersensor DS des fliegenden Geschosses G eingeschaltet wird, sendet er einen Strahl von der Frequenz f0 aus. Der vom Ziel reflektierte Strahl hat die Frequenz f0 + fD. Dieser Wert gelangt -über den Tiefpass TP, den Verstärker V und den Komparator K zum Zähler 2. Vom Zähler 2
Gemäss Fig.1 fliegen Geschoss G und Ziel Z auf parallelen Flugbahnen A und B aufeinander zu, wobei sich diese beiden Flugbahnen A und B im Abstand D voneinander befinden. Je mehr sich Geschoss G und Ziel Z einander annähern, um so grösser wird der Winkel ZW zwischen Geschossbahn A und der Geraden GZ zwischen Geschoss G und Ziel Z. Sobald dieser Winkel ZW den gewünschten Wert, d.h. den Zündwinkel ZW erreicht hat, soll das Geschoss gezündet werden.According to FIG. 1, projectile G and target Z fly towards each other on parallel trajectories A and B, these two trajectories A and B being at a distance D from one another. The closer floor G and target Z approach each other, the greater the angle ZW between floor path A and the straight line GZ between floor G and target Z. As soon as this angle ZW reaches the desired value, i.e. the projectile should be fired.
Claims (8)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CH3782/87 | 1987-09-29 | ||
CH378287 | 1987-09-29 |
Publications (1)
Publication Number | Publication Date |
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EP0309734A1 true EP0309734A1 (en) | 1989-04-05 |
Family
ID=4263365
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP88113771A Withdrawn EP0309734A1 (en) | 1987-09-29 | 1988-08-24 | Method for firing a projectile in the proximity of a target |
Country Status (6)
Country | Link |
---|---|
US (1) | US4895075A (en) |
EP (1) | EP0309734A1 (en) |
JP (1) | JPH01114700A (en) |
CN (1) | CN1009387B (en) |
CA (1) | CA1287685C (en) |
NO (1) | NO883978L (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0547391A1 (en) * | 1991-12-18 | 1993-06-23 | Oerlikon Contraves AG | Method for increasing the success probability for an anti-aircraft defence system using remote-controlled scattering projectiles |
EP0937960A1 (en) * | 1998-02-20 | 1999-08-25 | Tda Armements S.A.S. | Method for computing the firing time of a moving charge |
EP2989408B1 (en) | 2013-04-26 | 2021-03-17 | Rheinmetall Waffe Munition GmbH | Method for operating a weapon system |
Families Citing this family (7)
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US5696347A (en) * | 1995-07-06 | 1997-12-09 | Raytheon Company | Missile fuzing system |
US6279478B1 (en) * | 1998-03-27 | 2001-08-28 | Hayden N. Ringer | Imaging-infrared skewed-cone fuze |
US6722639B2 (en) | 2001-04-10 | 2004-04-20 | Koch-Glitsch, Lp | Liquid distributor in mass transfer column and method of installation and use |
DE60216784T2 (en) * | 2001-10-02 | 2007-10-31 | Orica Explosives Technology Pty. Ltd., Melbourne | REMOTE-CONTROLLED IGNITION SYSTEM WITH FREQUENCY DIVERSITY |
US7658031B2 (en) * | 2005-12-21 | 2010-02-09 | Bushnell, Inc. | Handheld rangefinder operable to determine hold over ballistic information |
CN104321930A (en) * | 2012-04-17 | 2015-01-28 | 凯萨股份有限公司 | Dielectric lens structures for interchip communication |
CN104834825A (en) * | 2015-05-22 | 2015-08-12 | 中国石油化工股份有限公司 | Method for assessing probability of hitting of fragments of horizontal type columnar explosion source |
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1988
- 1988-08-24 EP EP88113771A patent/EP0309734A1/en not_active Withdrawn
- 1988-09-07 NO NO88883978A patent/NO883978L/en unknown
- 1988-09-16 JP JP63230225A patent/JPH01114700A/en active Pending
- 1988-09-22 US US07/247,830 patent/US4895075A/en not_active Expired - Fee Related
- 1988-09-23 CA CA000578295A patent/CA1287685C/en not_active Expired - Lifetime
- 1988-09-29 CN CN88106990A patent/CN1009387B/en not_active Expired
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Cited By (5)
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EP0547391A1 (en) * | 1991-12-18 | 1993-06-23 | Oerlikon Contraves AG | Method for increasing the success probability for an anti-aircraft defence system using remote-controlled scattering projectiles |
US5322016A (en) * | 1991-12-18 | 1994-06-21 | Oerlikon-Contraves Ag | Method for increasing the probability of success of air defense by means of a remotely fragmentable projectile |
EP0937960A1 (en) * | 1998-02-20 | 1999-08-25 | Tda Armements S.A.S. | Method for computing the firing time of a moving charge |
FR2775341A1 (en) * | 1998-02-20 | 1999-08-27 | Tda Armements Sas | METHOD FOR CALCULATING THE MOMENT OF FIRE OF A MOBILE LOAD |
EP2989408B1 (en) | 2013-04-26 | 2021-03-17 | Rheinmetall Waffe Munition GmbH | Method for operating a weapon system |
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Publication number | Publication date |
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NO883978D0 (en) | 1988-09-07 |
NO883978L (en) | 1989-03-30 |
CN1009387B (en) | 1990-08-29 |
US4895075A (en) | 1990-01-23 |
JPH01114700A (en) | 1989-05-08 |
CN1034425A (en) | 1989-08-02 |
CA1287685C (en) | 1991-08-13 |
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