EP0806625A2 - Interface for digital information transfer between a missile and a launcher - Google Patents

Interface for digital information transfer between a missile and a launcher Download PDF

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Publication number
EP0806625A2
EP0806625A2 EP97107161A EP97107161A EP0806625A2 EP 0806625 A2 EP0806625 A2 EP 0806625A2 EP 97107161 A EP97107161 A EP 97107161A EP 97107161 A EP97107161 A EP 97107161A EP 0806625 A2 EP0806625 A2 EP 0806625A2
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EP
European Patent Office
Prior art keywords
missile
interface
data transmission
data
plug
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.)
Granted
Application number
EP97107161A
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German (de)
French (fr)
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EP0806625B1 (en
EP0806625A3 (en
Inventor
Hubert Lehr
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Bodenseewerk Geratetechnik GmbH
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Bodenseewerk Geratetechnik GmbH
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C17/00—Fuze-setting apparatus
    • F42C17/04—Fuze-setting apparatus for electric fuzes
    • 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
    • F41F3/055—Umbilical connecting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/007—Preparatory measures taken before the launching of the guided missiles

Definitions

  • the invention relates to an interface for digital data transmission between a missile and a launch device, in which the missile is held.
  • Missiles are held on the wings of aircraft in launchers (launcher). They are fired from these starting devices by igniting the engine. Before the launch, the missile is connected to the aircraft via one or more connecting lines (umbilical). These connecting lines are released during or before the launch. Via such a connecting line, the missile is supplied with electricity and cooling gas before the launch, so that the missile needs to be supplied by the missile's own aggregates only during the flight after the launch. The cooling gas is fed to a Joule-Thomson cooler for cooling a detector in the seeker head of a target-tracking missile. But there is also an exchange of digitally available data between the aircraft and the missile. This exchange of data takes place via a plug.
  • This connector is removed from the missile shortly before launch by a retraction mechanism removed and retracted into the starter.
  • the connections must be made manually when loading the launch device with the missile. This is a source of error.
  • retracting the connector by the mechanical withdrawal mechanism takes time. There must therefore be a delay between the launch command and the actual launch.
  • the invention has for its object to simplify the interface for digital data transmission between the missile and the aircraft, to make loading of the launch device with the missile easier and safer, and to avoid delays in launching the missile.
  • this object is achieved in that contactless data transmission devices interacting as an interface to the missile and launch device are provided.
  • the data interface does not contain any mechanical connections.
  • the coupling is established automatically when the missile is held in its correct position in the launch device. No plug connection needs to be made during the loading process. Likewise, the connection is released automatically at launch and without the need for a delay when the missile leaves the launcher.
  • Embodiments of the invention are the subject of the dependent claims.
  • 10 denotes a starting device.
  • a missile 12 is held in the launch device 10.
  • a data bus 14 is routed to a plug part 16.
  • the data bus carries data in a certain format, e.g. MIL STD 1553 B.
  • a data transmission module 18 is located on the plug part 16 for the contactless transmission of digital data.
  • the data transmission module works with infrared radiation and contains corresponding transmitters and receivers, as represented by blocks 20 and 22 in FIG.
  • the transmitters and receivers of the data transmission module 18 are connected via an IR link 24 to receivers or transmitters of a transmission and reception chip 26 on the missile 12.
  • the signals from the transmit and receive chip 26 are converted into the format of the data bus 14 by a converter 28 on the missile side and converted to a data bus 30 of the missile 12.
  • FIG. 2 shows an interface in a starting device according to the prior art.
  • the interface is shown in the operative position, ie in a position in which the connection to the missile is established.
  • the retraction mechanism 34 has an angle lever 38 which is pivotably mounted with a shaft 36.
  • the plug 32 is guided in a guide 40 and has pins 42 which protrude through a longitudinal slot 44 in the guide 40.
  • An arm 46 of the bell crank 38 engages with forked ends around the protruding pins 42.
  • the forked ends have two jaws 48 and 50.
  • the jaw 50 is formed by an angle lever which can be pivoted relative to the jaw 48 about a pivot bearing 52.
  • a tension spring 54 acts on the angle lever.
  • the spring 54 loads the connector 32 in the direction of its operative position and seeks to pivot the angle lever 38 counterclockwise in FIG.
  • a compression spring 56 which overcomes the tension spring, engages the other arm 58 of the angle lever 38 and attempts to pivot it clockwise. This is prevented in the active position of FIG. 2 by an angle lever 60, on one arm 62 of which a nose 64 connected to the angle lever 38 rests.
  • the angle lever 38 is held against the action of the compression spring 56 in a position in which the plug 32 is in its operative position.
  • the angle lever 60 is pivotable about a pivot point 66.
  • a tension spring 70 engages, which tries to hold the angle lever 60 in the locking position of FIG.
  • the angle lever 60 can be actuated by a plunger 72 actuated by a lifting magnet 61, as in FIG shown, are pivoted clockwise.
  • the arm 62 then releases the nose 64.
  • the angle lever 38 can be pivoted clockwise by the compression spring 56.
  • the arm 46 then pulls the plug 32 back over the jaw 48 and the pin 42, as shown in FIG.
  • the plug 32 (FIG. 2) contains the plug part 16, which is connected to the data bus of the aircraft via a cable 74.
  • the plug 32 in FIG. 2 also contains a plug part 76 containing the plug pins, which engages in a plug socket of the missile 12 in the operative position.
  • a guide pin 78 protruding above ensures correct engagement of the plug pins in the plug sockets.
  • the data transmission module 18 is now placed on the connector part 16 after the conversion.
  • the solenoid 61 is switched off.
  • the retraction mechanism 34 is in its retracted position shown in Figure 3.
  • the data transmission module 18 then closes with the Missile-side wall of the starting device 10. The launch of the missile is not affected in this position.
  • the space available for the data transmission module includes not only the space previously occupied by the plug part 76 but also the area into which the guide pin 78 protruded.

Abstract

The interface consists of data communications devices (18,26) on the launcher (10) and flying body (12) which communicate contactlessly. Both data communications devices are capable of transmitting and receiving data via an IR path (24). The data communications devices exchange data using infrared radiation as the carrier of the communicated data. A pull-out plug can be replaced by a data communications module of comparable dimensions in a retrospective fitting process.

Description

Die Erfindung betrifft eine Schnittstelle zur digitalen Datenübertragung zwischen einem Flugkörper und einem Startgerät, in welchem der Flugkörper gehaltert ist.The invention relates to an interface for digital data transmission between a missile and a launch device, in which the missile is held.

Flugkörper sind an den Tragflächen von Flugzeugen in Startgeräten (Launcher) gehaltert. Aus diesen Startgeräten werden sie durch Zünden des Triebwerks abgeschossen. Vor dem Abschuß ist der Flugkörper mit dem Flugzeug über eine oder mehrere Verbindungs-Leitungen (Umbilical) verbunden. Diese Verbindungsleitungen werden beim oder vor dem Abschuß gelöst. Über eine solche Verbindungs-Leitung erfolgt die Versorgung des Flugkörpers mit Strom und Kühlgas vor dem Abschuß, so daß die Versorgung des Flugkörpers durch flugkörpereigene Aggregate nur während des Fluges nach dem Abschuß zu erfolgen braucht. Das Kühlgas wird einem Joule-Thomson-Kühler zum Kühlen eines Detektors im Suchkopf eines zielverfolgenden Flugkörpers zugeführt. Es erfolgt aber auch ein Austausch von digital vorliegenden Daten zwischen dem Flugzeug und dem Flugkörper. Dieser Austausch von Daten erfolgt über einen Stecker. Dieser Stecker wird kurz vor dem Abschuß durch einen Rückzug-Mechanismus vom Flugkörper abgezogen und in das Startgerät zurückgezogen. Die Verbindungen müssen beim Beladen des Startgerätes mit dem Flugkörper manuell hergestellt werden. Das stellt eine Fehlerquelle dar. Außerdem erfordert das Zurückziehen des Steckers durch den mechanischen Rückzug-Mechanismus Zeit. Es muß daher eine Verzögerung zwischen Abschuß-Befehl und tatsächlichem Abschuß vorgesehen werden.Missiles are held on the wings of aircraft in launchers (launcher). They are fired from these starting devices by igniting the engine. Before the launch, the missile is connected to the aircraft via one or more connecting lines (umbilical). These connecting lines are released during or before the launch. Via such a connecting line, the missile is supplied with electricity and cooling gas before the launch, so that the missile needs to be supplied by the missile's own aggregates only during the flight after the launch. The cooling gas is fed to a Joule-Thomson cooler for cooling a detector in the seeker head of a target-tracking missile. But there is also an exchange of digitally available data between the aircraft and the missile. This exchange of data takes place via a plug. This connector is removed from the missile shortly before launch by a retraction mechanism removed and retracted into the starter. The connections must be made manually when loading the launch device with the missile. This is a source of error. In addition, retracting the connector by the mechanical withdrawal mechanism takes time. There must therefore be a delay between the launch command and the actual launch.

Der Erfindung liegt die Aufgabe zugrunde, die Schnittstelle für die digitale Datenübertragung zwischen Flugkörper und Flugzeug zu vereinfachen, die Beladung des Startgerätes mit dem Flugkörper einfacher und sicherer zu machen und Verzögerungen veim Abschuß des Flugkörpers zu vermeiden.The invention has for its object to simplify the interface for digital data transmission between the missile and the aircraft, to make loading of the launch device with the missile easier and safer, and to avoid delays in launching the missile.

Erfindungsgemäß wird diese Aufgabe dadurch gelöst, daß als Schnittstelle an Flugkörper und Startgerät zusammenwirkende berührungslose Datenübertragungs-Einrichtungen vorgesehen sind.According to the invention, this object is achieved in that contactless data transmission devices interacting as an interface to the missile and launch device are provided.

Auf diese Weise enthält die Daten-Schnittstelle keine mechanischen Verbindungen. Die Kopplung wird automatisch hergestellt, wenn der Flugkörper in seiner richtigen Position im Startgerät hehaltert ist. Bei dem Beladevorgang braucht keine Steckerverbindung hergestellt werden. Ebenso wird die Verbindung beim Abschuß automatisch und ohne Notwendigkeit einer Verzögerung gelöst, wenn der Flugkörper das Startgerät verläßt.In this way, the data interface does not contain any mechanical connections. The coupling is established automatically when the missile is held in its correct position in the launch device. No plug connection needs to be made during the loading process. Likewise, the connection is released automatically at launch and without the need for a delay when the missile leaves the launcher.

Ausgestaltungen der Erfindung sind Gegenstand der Unteransprüche.Embodiments of the invention are the subject of the dependent claims.

Ein Ausführungsbeipiel der Erfindung ist nachstehend unter Bezugnahme auf die zugehörigen Zeichnungen näher erläutert.

Fig.1
ist eine schematische Darstellung des Startgeräts und des Flugkörpers mit einer berührungslosen Schnittstelle für die Übertragung digitaler Daten.
Fig.2
zeigt einen an einem Startgerät nach dem Stand der Technik vorgesehenen, zurückziehbaren Stecker in einer Schnittstelle für die Übertragung digitaler Daten zwischen Flugzeug und Flugkörper.
Fig.3
zeigt eine berührungslose Schnittstelle, die durch Umrüstung des Startgeräts von Fig.2 erhalten wird.
An exemplary embodiment of the invention is explained below with reference to the accompanying drawings.
Fig. 1
is a schematic representation of the launch device and the missile with a non-contact interface for the transmission of digital data.
Fig. 2
shows a retractable connector provided on a starter according to the prior art in an interface for the transmission of digital data between the aircraft and the missile.
Fig. 3
shows a non-contact interface, which is obtained by retrofitting the starter of Fig.2.

In Fig.1 ist mit 10 ein Startgerät bezeichnet. In dem Startgerät 10 ist ein Flugkörper 12 gehaltert. Im Startgerät 10 ist ein Datenbus 14 zu einem Steckerteil 16 geführt. Der Datenbus führt daten in einem bestimmten Format, z.B. MIL STD 1553 B. An dem Steckerteil 16 sitzt ein Daten-Übertragungsmodul 18 zur berührungslosen Übertragung digitaler Daten. Das Daten-Übertragungsmodul arbeitet mit infraroter Strahlung und enthält entsprechende Sender und Empfänger, wie in Fig.1 durch die Blöcke 20 und 22 dargestellt ist.In FIG. 1, 10 denotes a starting device. A missile 12 is held in the launch device 10. In the starting device 10, a data bus 14 is routed to a plug part 16. The data bus carries data in a certain format, e.g. MIL STD 1553 B. A data transmission module 18 is located on the plug part 16 for the contactless transmission of digital data. The data transmission module works with infrared radiation and contains corresponding transmitters and receivers, as represented by blocks 20 and 22 in FIG.

Die Sender und Empfänger des Daten-Übertragungsmoduls 18 sind über eine IR-Strecke 24 mit Empfängern bzw. Sendern eines Sende- und Empfangs-Chips 26 an dem Flugkörper 12 verbunden. Die Signale von dem Sende- und Empfangs-Chip 26 werden durch einen Wandler 28 flugkörperseitig wieder in das Format des Datenbusses 14 umgewandelt und auf einen Datenbus 30 des Flugkörpers 12 umgesetzt.The transmitters and receivers of the data transmission module 18 are connected via an IR link 24 to receivers or transmitters of a transmission and reception chip 26 on the missile 12. The signals from the transmit and receive chip 26 are converted into the format of the data bus 14 by a converter 28 on the missile side and converted to a data bus 30 of the missile 12.

Fig.2 zeigt eine Schnittstelle in einem Startgerät nach dem Stand der Technik. Die Schnittstelle ist in Wirkstellung gezeigt, d.h. in einer Stellung, in welcher die Verbindung zu dem Flugkörper hergestellt ist. Dort sitzt ein Stecker 32 für die Übertragung der digitalen Daten an einem Rückzug-Mechanismus 34. Der Rückzug-Mechanismus 34 weist einen mit einer Welle 36 schwenkbar gelagerten Winkelhebel 38 auf. Der Stecker 32 ist in einer Führung 40 geführt und weist Zapfen 42 auf, welche durch einen Längsschlitz 44 der Führung 40 herausragen. Ein Arm 46 des Winkelhebels 38 greift mit gabelförmigen Enden um die herausragenden Zapfen 42. Die gabelförmigen Enden weisen zwei Backen 48 und 50 auf. Die Backe 50 ist dabei von einem Winkelhebel gebildet, der um ein Schwenklager 52 gegenüber der Backe 48 verschwenkbar ist. An dem Winkelhebel greift eine Zugfeder 54 an. Dadurch werden die beiden Backen 48 und 50 stets in Anlage an den Zapfen 42 gehalten. Die Feder 54 belastet den Stecker 32 in Richtung auf seine Wirkstellung und sucht den Winkelhebel 38 entgegen dem Uhrzeigersinn in Fig.2 zu verschwenken. Eine Druckfeder 56, welche die Zugfeder überwindet, greift an dem anderen Arm 58 des Winkelhebels 38 an und sucht diesen im Uhrzeigersinn zu verschwenken. Das wird in der Wirkstellung von Fig.2 durch einen Winkelhebel 60 verhindert, an dessen einem Arm 62 eine mit dem Winkelhebel 38 verbundene Nase 64 anliegt. Daurch wird der Winkelhebel 38 gegen die Wirkung der Druckfeder 56 in einer Stellung gehalten, in welcher der Stecker 32 in seiner Wirkstellung ist. Der Winkelhebel 60 ist um einen Schwenkpunkt 66 schwenkbar. An einem zweiten Arm 68 des Winkelhebels 60 greift eine Zugfeder 70 an, welche den Winkelhebel 60 in der Verriegelungs-Stellung von Fig.2 zu halten trachtet. Der Winkelhebel 60 kann durch einen von einem Hubmagneten 61 betätigten Stößel 72, wie in Fig.3 dargestellt, im Uhrzeigersinn verschwenkt werden. Der Arm 62 gibt dann die Nase 64 frei. Damit kann der Winkelhebel 38 von der Druckfeder 56 im Uhrzeigersinn verschwenkt werden. Der Arm 46 zieht dann über die Backe 48 und den Zapfen 42 den Stecker 32, wie in Fig.2 dargestellt, zurück. Das ist ein relativ komplizierter Rückzugs-Mechanismus. Das Zurückziehen erfordert eine bestimmte Zeit. Es muß also eine Verzögerung zwischen dem Einschalten des Hubmagneten 61 und dem eigentlichen Abschuß des Flugkörpers vorgesehen sein. Während dieser Verzögerungszeit ist aber die Verbindung zwischen Flugkörper und Startgerät 10 schon unterbrochen.2 shows an interface in a starting device according to the prior art. The interface is shown in the operative position, ie in a position in which the connection to the missile is established. There is a connector 32 for the transmission of the digital data on a retraction mechanism 34. The retraction mechanism 34 has an angle lever 38 which is pivotably mounted with a shaft 36. The plug 32 is guided in a guide 40 and has pins 42 which protrude through a longitudinal slot 44 in the guide 40. An arm 46 of the bell crank 38 engages with forked ends around the protruding pins 42. The forked ends have two jaws 48 and 50. The jaw 50 is formed by an angle lever which can be pivoted relative to the jaw 48 about a pivot bearing 52. A tension spring 54 acts on the angle lever. As a result, the two jaws 48 and 50 are always held in contact with the pin 42. The spring 54 loads the connector 32 in the direction of its operative position and seeks to pivot the angle lever 38 counterclockwise in FIG. A compression spring 56, which overcomes the tension spring, engages the other arm 58 of the angle lever 38 and attempts to pivot it clockwise. This is prevented in the active position of FIG. 2 by an angle lever 60, on one arm 62 of which a nose 64 connected to the angle lever 38 rests. As a result, the angle lever 38 is held against the action of the compression spring 56 in a position in which the plug 32 is in its operative position. The angle lever 60 is pivotable about a pivot point 66. On a second arm 68 of the angle lever 60, a tension spring 70 engages, which tries to hold the angle lever 60 in the locking position of FIG. The angle lever 60 can be actuated by a plunger 72 actuated by a lifting magnet 61, as in FIG shown, are pivoted clockwise. The arm 62 then releases the nose 64. Thus, the angle lever 38 can be pivoted clockwise by the compression spring 56. The arm 46 then pulls the plug 32 back over the jaw 48 and the pin 42, as shown in FIG. This is a relatively complicated withdrawal mechanism. Withdrawal takes a certain amount of time. There must therefore be a delay between the switching on of the solenoid 61 and the actual launching of the missile. During this delay time, however, the connection between the missile and the launch device 10 is already interrupted.

Es sind viele Startgeräte im Einsatz, die auf diese Weise aufgebaut sind. Es ist möglich, diese vorhandenen Startgeräte auf kontaktlose Übertragung der digitalen Daten umzurüsten. Das ist in Fig.3 dargestellt.There are many starting devices in use that are constructed in this way. It is possible to convert these existing starting devices to contactless transmission of the digital data. This is shown in Fig.3.

Der Stecker 32 (Fig.2) enthält den Steckerteil 16, der über ein Kabel 74 mit dem Datenbus des Flugzeugs verbunden ist. Der Stecker 32 in Fig.2 enthält weiter einen die Steckerstifte enthaltenden Steckerteil 76, der in der Wirkstellung in eine Steckerbuchse des Flugkörpers 12 eingreift. Ein darüber vorstehender Führunsstift 78 gewährleistet das korrekte Eingreifen der Steckerstifte in die Steckerbuchsen.The plug 32 (FIG. 2) contains the plug part 16, which is connected to the data bus of the aircraft via a cable 74. The plug 32 in FIG. 2 also contains a plug part 76 containing the plug pins, which engages in a plug socket of the missile 12 in the operative position. A guide pin 78 protruding above ensures correct engagement of the plug pins in the plug sockets.

Statt des Steckerteils 76 ist nun nach der Umrüstung das Daten-Übertragungsmodul 18 auf den Steckerteil 16 aufgesetzt. Der Hubmagnet 61 ist abgeschaltet. Der Rückzugs-Mechanismus 34 ist in seiner in Fig.3 dargestellten, zurückgezogenen Stellung. Das Daten-Übertragungsmodul 18 schließt dann mit der flugkörperseitigen Wandung des Startgerätes 10 ab. Der Abschuß des Flugkörpers wird in dieser Stellung nicht beeinflußt. Der für das Daten-Übertragungsmodul zur Verfügung stehende Raum umfaßt nicht nur den vorher von dem Steckerteil 76 eingenommenen Raum sondern auch den Bereich, in den der Führungsstift 78 hineinragte.Instead of the connector part 76, the data transmission module 18 is now placed on the connector part 16 after the conversion. The solenoid 61 is switched off. The retraction mechanism 34 is in its retracted position shown in Figure 3. The data transmission module 18 then closes with the Missile-side wall of the starting device 10. The launch of the missile is not affected in this position. The space available for the data transmission module includes not only the space previously occupied by the plug part 76 but also the area into which the guide pin 78 protruded.

Eine solche Umrüstung erfordert keine weiteren Änderungen an dem Startgerät. Es können daher vorhandene, mit einer Stecker-Verbindung als Schnittstelle arbeitende Startgeräte mit geringem Aufwand auf Flugkörper umgerüstet werden, bei denen eine kontaktlose Übertragung der digitalen Daten über eine Infrarot-Ankoppelung erfolgt. In dem umgerüsteten Zustand bleibt der Hubmagnet 61 stromlos.Such a changeover does not require any further changes to the starting device. It is therefore possible, with little effort, to convert existing starters, which work as an interface, to missiles in which the digital data are transmitted without contact via an infrared coupling. In the converted state, the solenoid 61 remains de-energized.

Claims (5)

Schnittstelle zur digitalen Datenübertragung zwischen einem Flugkörper und einem Startgerät, in welchem der Flugkörper gehaltert ist, dadurch gekennzeichnet, daß als Schnittstelle an Flugkörper (12) und Startgerät (10) zusammenwirkende berührungslose Datenübertragungs-Einrichtungen (18,26) vorgesehen sind.Interface for digital data transmission between a missile and a launch device, in which the missile is held, characterized in that contactless data transmission devices (18, 26) interacting as an interface to the missile (12) and launch device (10) are provided. Schnittstelle nach Anspruch 1, dadurch gekennzeichnet, daß die berührungslosen Datenübertragungs-Einrichtungen (18,26) beide zum Senden und Empfangen von Daten eingerichtet sind.Interface according to claim 1, characterized in that the non-contact data transmission devices (18, 26) are both set up for sending and receiving data. Schnittstelle nach Anspruch 1 oder 2, dadurch gekennzeichnet, daß die Datenübertragungs-Einrichtungen (18,26) zum Senden und/oder Empfangen von infraroter Strahlung als Träger der übertragenen Daten eingerichtet sind.Interface according to Claim 1 or 2, characterized in that the data transmission devices (18, 26) are designed to transmit and / or receive infrared radiation as carriers of the transmitted data. Schnittstelle nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, daß ein an einem Rückzug-Mechanismus (34) sitzender Abzug-Stecker (76) bei einen Umrüstvorgang durch ein Datenübertragungs-Modul (18) von vergleichbaren Abmessungen ersetzt ist.Interface according to one of claims 1 to 3, characterized in that a withdrawal plug (76) located on a withdrawal mechanism (34) is replaced by a data transmission module (18) of comparable dimensions during a conversion process. Schnittstelle nach Anspruch 4, dadurch gekennzeichnet, daß flugkörperseitig ein mit dem Datenübertragungs-Modul (18) fluchtender Sende- und Empfangs-Chip (26) angeordnet ist.Interface according to claim 4, characterized in that on the missile side one with the data transmission module (18) aligned transmit and receive chip (26) is arranged.
EP97107161A 1996-05-09 1997-04-30 Interface for digital information transfer between a missile and a launcher Expired - Lifetime EP0806625B1 (en)

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DE19618602A DE19618602A1 (en) 1996-05-09 1996-05-09 Interface for digital data transmission between a missile and a launch device
DE19618602 1996-05-09

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EP0806625A2 true EP0806625A2 (en) 1997-11-12
EP0806625A3 EP0806625A3 (en) 1998-12-02
EP0806625B1 EP0806625B1 (en) 2002-12-11

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DE59708921D1 (en) 2003-01-23
EP0806625B1 (en) 2002-12-11
DE19618602A1 (en) 1997-11-13
US5983771A (en) 1999-11-16
EP0806625A3 (en) 1998-12-02

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