EP0731331B1 - Launcher for self-propelled missiles, in particular for artillery rockets - Google Patents

Launcher for self-propelled missiles, in particular for artillery rockets Download PDF

Info

Publication number
EP0731331B1
EP0731331B1 EP96102429A EP96102429A EP0731331B1 EP 0731331 B1 EP0731331 B1 EP 0731331B1 EP 96102429 A EP96102429 A EP 96102429A EP 96102429 A EP96102429 A EP 96102429A EP 0731331 B1 EP0731331 B1 EP 0731331B1
Authority
EP
European Patent Office
Prior art keywords
launch
support body
missile
contact pins
ready
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
Application number
EP96102429A
Other languages
German (de)
French (fr)
Other versions
EP0731331A3 (en
EP0731331A2 (en
Inventor
Heinrich Gertz
Wolfram Vaihinger
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Wegmann and Co GmbH
Original Assignee
Wegmann and Co GmbH
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Wegmann and Co GmbH filed Critical Wegmann and Co GmbH
Publication of EP0731331A2 publication Critical patent/EP0731331A2/en
Publication of EP0731331A3 publication Critical patent/EP0731331A3/en
Application granted granted Critical
Publication of EP0731331B1 publication Critical patent/EP0731331B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
    • F41A19/00—Firing or trigger mechanisms; Cocking mechanisms
    • F41A19/58—Electric firing mechanisms
    • F41A19/69—Electric contacts or switches peculiar thereto
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B14/00—Projectiles or missiles characterised by arrangements for guiding or sealing them inside barrels, or for lubricating or cleaning barrels
    • F42B14/06—Sub-calibre projectiles having sabots; Sabots therefor

Definitions

  • the invention relates to a launcher for self-propelled missiles, especially artillery missiles, with the features from the preamble of Claim 1.
  • Such a launcher is for example in document US-A-36 10 095.
  • the known launcher supports the rocket on the inner wall of the launch tube over several their circumference arranged over most of it their length extending support body made of balsa wood or some other light material.
  • the invention has for its object a launcher the in the preamble of the claim 1 to create the type described which on the one hand is the electrical signal transmission to the missile is carried out so that no tearing cable connections are accepted must and which on the other hand opens possibilities to to prevent the support body after leaving of the launch tube in contact with parts of the missile can guess.
  • a basic idea of the invention initially exists in training the support body so that the electrical Energy transfer over under the force of Compression springs standing contact pins are made in the Ready to fire condition on counter contacts on the inside of the launch tube and each with also under the force of compression springs Contact pins are electrically connected to the electrical mating contacts on the outside of the Missile.
  • the power of the used Compression springs only serve to provide the necessary Contact pressure on the electrical contact pins too produce.
  • the support bodies are like this trained that they leave the launch tube get a strong momentum across the direction of launch and thus thrown outwards, so that they are at a sufficient distance from the missile when the tail leaves the launch tube Has. This momentum is spring loaded Tappet is generated which supports the missile from pull the trigger.
  • the force of the compression springs used for this is much greater than the force of the contact pressure on the electrical contact pins generating Compression springs.
  • a ready to fire Missile F which is at its aft end an empennage L on the inner wall of the launch tube A supports himself while he is in his front area over a total of four at equal angular intervals its circumference arranged support body S1, S2 on the The inner wall of the launch tube A is supported.
  • electrical lines Z which are arranged in the inner wall of the launch tube 8 electrical contacts GK1 are connected, electrical signals fed in below explained by the support body S1 and S2 through to electrical contacts GK2, which are located in the outer surface of the missile F.
  • the signals are the in a known manner Missile engine fed and the missile F sets moving in the direction of launch.
  • Fig. 2 shows a moment just before the full exit of the missile F from the launch tube A. The missile F is still within the launch tube via the tail unit L. A supported while the support body S1 and S2 - and two more, not shown Support body - led out of the launch tube A. and are explained in more detail below Construction after the exit a strong Pulse in the direction of arrow Q, i.e. the transverse direction to Firing direction.
  • Fig. 3 shows that due to this impulse after the complete exit of the Missile F from the launch tube 8, the support body S1 and S2 as far from the missile F in the transverse direction have moved away that no collision with the Tail L more occurs.
  • FIGS. 4 to 10 Structure of the support body S1 in Fig. 1 to 3 in more detail explained.
  • the remaining support bodies are exactly in built the same way.
  • the support body S1 has an upper part 1 and a lower part 2 connected to each other via a screw connection 3 are detachably connected. Through the upper and lower part an interior 13 is formed within the support body delimited.
  • the top of the top 1 is at least in partial areas 1.1 to the inner surface of the launch tube adjusted while the bottom 2.1 of the Lower part 2 adapted to the outer shape of the missile F. is. 4 is the distance between the Bottom 2.1 of the lower part 2 and the top 1.1 of the upper part 1 is shown as a radius section R, the difference in caliber between the missile F and the launch tube A determined.
  • each plunger 4 arranged at its rear end on guide pieces 2.2 with guide surfaces 2.3 in the direction of the bottom 2.1 are movably guided.
  • On the guide pieces 2.2 strong helical compression springs are supported 5 starting at each other with their other end rest a collar 4.2 of the plunger 4 and thus exert a force such that each outer end 4.1 of the plunger 4 in the shown in the figures, not installed condition of the support body from openings from the bottom 2.1 of the lower part 2 protrudes by a predetermined amount.
  • the front ends 4.1 of the plunger 4 are on guide surfaces 2.4 performed in the lower part 2.
  • the support body attached to the missile is on Missile over a under the action of a compression spring 10 guided guide part 9, which is in Extends longitudinally and with its outer part 9.1 in a corresponding groove on the surface of the Missile engages (see Figures 5 and 7).
  • Each of the bottom contact pins 7 is associated with an upper one Contact pin 6 connected via a spiral conductor 8, of both the function of an electrical conductor as well as the function of a compression spring, against the effect of the outer ends 6.1 and 7.1 of the contact pins can be pushed back.
  • I'm ready to fire State are the outer ends 7.1 or 6.1 of the contact pins on corresponding mating contacts GK2 or GK1 (see Fig. 1) of the missile or the Launch tube, the required contact pressure is generated by the spiral ladders 8.
  • the spiral ladders 8 Of course is the one that acts as compression springs Spiral head 8 generated pressure much lower than that generated by the helical compression springs 5 Pressure to push off the support body after the Launch.
  • the contact pins 6 and 7 can in addition to the Ignition signals further signals for the transmission of electrical information between one outside the Launch tube lying control device and Missiles are directed.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
  • Elimination Of Static Electricity (AREA)

Description

Die Erfindung betrifft eine Abschußvorrichtung für selbstangetriebene Flugkörper, insbesondere Artillerieraketen, mit den Merkmalen aus dem Oberbegriff des Patentanspruchs 1.The invention relates to a launcher for self-propelled missiles, especially artillery missiles, with the features from the preamble of Claim 1.

Eine derartige Abschußvorrichtung ist beispielsweise in dem Dokument US-A-36 10 095 beschrieben. Bei der bekannten Abschußvorrichtung stützt sich die Rakete an der Innenwand des Abschußrohres über mehrere, an ihrem Umfang angeordnete, sich über den größten Teil ihrer Länge erstreckende Stützkörper ab, die aus Balsaholz oder einem anderen leichten Material bestehen.Such a launcher is for example in document US-A-36 10 095. In the known launcher supports the rocket on the inner wall of the launch tube over several their circumference arranged over most of it their length extending support body made of balsa wood or some other light material.

Da in der letzten Zeit Raketenantriebe im Hinblick auf die Startgeschwindigkeit erheblich verbessert worden sind, tritt bei den bekannten Abschußvorrichtungen das Problem auf, daß die Stützkörper nach dem Verlassen des Abschußrohres nicht etwa mit dem Leitwerk des Flugkörpers in Berührung kommen dürfen. Ein weiteres Problem besteht darin, daß bisher die elektrische Signalübertragung beim Zünden des Flugkörpers im Abschußrohr über Festkabelanschlüsse erfolgte, die beim Verlassen des Flugkörpers aus dem Abschußrohr abreißen, wobei der zurückbleibende Teil als Wegwerfartikel definiert war.Since recently rocket engines in view significantly improved on takeoff speed have occurred in the known launchers the problem that the support body after the Do not leave the launch tube with the tail unit of the missile may come into contact. A Another problem is that so far the electrical Signal transmission when the missile is fired in the launch tube via fixed cable connections when leaving the missile from the launch tube tear off, the remaining part as a disposable item was defined.

Der Erfindung liegt die Aufgabe zugrunde, eine Abschußvorrichtung der im Oberbegriff des Patentanspruchs 1 beschriebenen Bauart zu schaffen, bei welcher einerseits die elektrische Signalübertragung zum Flugkörper hin so durchgeführt wird, daß kein Abreißen von Kabelanschlüssen in Kauf genommen werden muß und die andererseits Möglichkeiten eröffnet, um zu verhindern, daß die Stützkörper nach dem Verlassen des Abschußrohres in Kontakt mit Teilen des Flugkörpers geraten können.The invention has for its object a launcher the in the preamble of the claim 1 to create the type described which on the one hand is the electrical signal transmission to the missile is carried out so that no tearing cable connections are accepted must and which on the other hand opens possibilities to to prevent the support body after leaving of the launch tube in contact with parts of the missile can guess.

Die Aufgabe wird hinsichtlich einer günstigeren Art der elektrischen Signalübertragung mit den Mitteln aus dem kennzeichnenden Teil des Patentanspruchs 1 gelöst. Eine vorteilhafte Weiterbildung der erfindungsgemäßen Abschußvorrichtung, bei der auch der Schutz des Flugkörpers vor den Stützkörpern gewährleistet ist, ist gemäß der weiteren Erfindung Gegenstand des Patentanspruchs 2. Vorteilhafte Weiterbildungen der erfindungsgemäßen Abschußvorrichtung sind in den Ansprüchen 3 und 4 beschrieben.The task is in terms of a cheaper type the electrical signal transmission with the means from the characterizing part of patent claim 1 solved. An advantageous development of the invention Launching device, in which the Protection of the missile from the support bodies guaranteed is the subject of the further invention of claim 2. Advantageous further developments the launcher according to the invention described in claims 3 and 4.

Ein Grundgedanke der Erfindung besteht zunächst darin, die Stützkörper so auszubilden, daß die elektrische Energieübertragung über unter der Kraft von Druckfedern stehende Kontaktstifte erfolgt, die im abschußbereiten Zustand an Gegenkontakten an der Innenseite des Abschußrohres anliegen und die jeweils mit ebenfalls unter der Kraft von Druckfedern stehenden Kontaktstiften elektrisch verbunden sind, die an elektrischen Gegenkontakten an der Außenseite des Flugkörpers anliegen. Die Kraft der verwendeten Druckfedern dient hierbei lediglich dazu, den nötigen Kontaktdruck an den elektrischen Kontaktstiften zu erzeugen. Nach einem ähnlichen Konstruktionsprinzip wird auch verhindert, daß die Stützkörper nach dem Verlassen des Abschußrohres in Kontakt mit Teilen des Flugkörpers geraten können. Die Stützkörper werden so ausgebildet, daß sie beim Verlassen des Abschußrohres einen starken Impuls quer zur Abschußrichtung erhalten und somit nach außen abgeschleudert werden, so daß sie sich in ausreichender Entfernung vom Flugkörper befinden, wenn das Leitwerk das Abschußrohr verlassen hat. Dieser Impuls wird durch federbelastete Stößel erzeugt, welche die Stützkörper vom Flugkörper abdrücken. Die Kraft der hierzu verwendeten Druckfedern ist wesentlich größer als die Kraft der dem Kontaktdruck an den elektrischen Kontaktstiften erzeugenden Druckfedern.A basic idea of the invention initially exists in training the support body so that the electrical Energy transfer over under the force of Compression springs standing contact pins are made in the Ready to fire condition on counter contacts on the inside of the launch tube and each with also under the force of compression springs Contact pins are electrically connected to the electrical mating contacts on the outside of the Missile. The power of the used Compression springs only serve to provide the necessary Contact pressure on the electrical contact pins too produce. Following a similar design principle is also prevented that the support body after the Leaving the launch tube in contact with parts of the Missile can get. The support bodies are like this trained that they leave the launch tube get a strong momentum across the direction of launch and thus thrown outwards, so that they are at a sufficient distance from the missile when the tail leaves the launch tube Has. This momentum is spring loaded Tappet is generated which supports the missile from pull the trigger. The force of the compression springs used for this is much greater than the force of the contact pressure on the electrical contact pins generating Compression springs.

Im folgenden wird anhand der beigefügten Zeichnungen ein Ausführungsbeispiel für eine Abschußvorrichtung nach der Erfindung näher erläutert.The following is based on the accompanying drawings an embodiment of a launcher explained in more detail according to the invention.

In den Zeichnungen zeigen:

  • Fig. 1 bis 3 in einer stark schematisierten, teilweise geschnittenen Darstellung eine Abschußvorrichtung für einen Flugkörper im Zustand vor dem Abschuß, sowie kurz vor und kurz nach dem vollständigen Austreten des Flugkörpers aus dem Abschußrohr;
  • Fig. 4 einen Stützkörper der Abschußvorrichtung nach Fig. 1 bis 3 in vergrößerter Seitenansicht;
  • Fig. 5 den Stützkörper nach Fig. 4 in einem Schnitt nach der Linie A-A in Fig. 4;
  • Fig. 6 den Stützkörper nach Fig. 4 in einem Schnitt nach der Linie B-B in Fig. 4;
  • Fig. 7 einen in Fig. 5 mit Z bezeichneten Teilbereich aus Fig. 5 in vergrößerter Darstellung;
  • Fig. 8 einen Schnitt durch den Stützkörper nach Fig. 4 gemäß der Linie C-C in Fig. 4;
  • Fig. 9 einen Schnitt durch den Stützkörper nach der Linie D-D in Fig. 8;
  • Fig. 10 eine Aufsicht auf den Stützkörper nach Fig. 4.
    • The drawings show:
  • Figures 1 to 3 in a highly schematic, partially sectioned illustration of a launch device for a missile in the state before launch, and shortly before and shortly after the missile has completely emerged from the launch tube;
  • 4 shows a support body of the launcher according to FIGS. 1 to 3 in an enlarged side view;
  • 5 shows the support body according to FIG. 4 in a section along the line AA in FIG. 4;
  • 6 shows the support body according to FIG. 4 in a section along the line BB in FIG. 4;
  • FIG. 7 shows a partial region designated by Z in FIG. 5 from FIG. 5 in an enlarged representation;
  • 8 shows a section through the support body according to FIG. 4 along the line CC in FIG. 4;
  • 9 shows a section through the support body along the line DD in FIG. 8;
  • 10 is a plan view of the support body of FIG. 4th

    • Es wird zunächst anhand der Fig. 1 bis 3 eine Abschußvorrichtung für Flugkörper in ihrem allgemeinen Aufbau und ihrer Wirkungsweise beschrieben.It is first a launcher with reference to FIGS. 1 to 3 for missiles in their general Structure and how it works described.

    Auf einem Grundgestell G sind ein oder mehrere Abschußrohre A angeordnet. Gemäß Fig. 1 befindet sich innerhalb des Abschußrohres A ein abschußbereiter Flugkörper F, der sich an seinem hinteren Ende über ein Leitwerk L an der Innenwand des Abschußrohres A abstützt, während er sich in seinem vorderen Bereich über insgesamt vier in gleichen Winkelabständen an seinem Umfang angeordnete Stützkörper S1, S2 an der Innenwand des Abschußrohres A abstützt. Zur Auslösung des Abschusses werden über elektrische Leitungen Z, die mit in der Innenwand des Abschußrohres 8 angeordneten elektrischen Kontakten GK1 verbunden sind, elektrische Signale zugeführt, die in weiter unten erläuterter Weise durch die Stützkörper S1 und S2 hindurch zu elektrischen Kontakten GK2 gelangen, welche sich in der Außenfläche des Flugkörpers F befinden.On a base frame G there are one or more launch tubes A arranged. 1 is located within the launch tube A a ready to fire Missile F, which is at its aft end an empennage L on the inner wall of the launch tube A supports himself while he is in his front area over a total of four at equal angular intervals its circumference arranged support body S1, S2 on the The inner wall of the launch tube A is supported. For triggering of the launch are made via electrical lines Z, which are arranged in the inner wall of the launch tube 8 electrical contacts GK1 are connected, electrical signals fed in below explained by the support body S1 and S2 through to electrical contacts GK2, which are located in the outer surface of the missile F.

    Die Signale werden in an sich bekannter Weise dem Raketenantrieb zugeführt und der Flugkörper F setzt sich in Abschußrichtung in Bewegung. Fig. 2 zeigt einen Augenblick kurz vor dem vollständigen Austritt des Flugkörpers F aus dem Abschußrohr A. Der Flugkörper F ist über das Leitwerk L noch innerhalb des Abschußrohres A abgestützt, während die Stützkörper S1 und S2 - sowie zwei weitere, nicht dargestellte Stützkörper - aus dem Abschußrohr A herausgeführt sind und aufgrund ihrer weiter unten genauer erläuterten Konstruktion nach dem Austritt einen starken Impuls in Pfeilrichtung Q, also der Querrichtung zur Abschußrichtung, erhalten. Fig. 3 zeigt, daß aufgrund dieses Impulses nach dem vollständigen Austritt des Flugkörpers F aus dem Abschußrohr 8 die Stützkörper S1 und S2 sich soweit vom Flugkörper F in Querrichtung wegbewegt haben, daß keine Kollision mit dem Leitwerk L mehr auftritt.The signals are the in a known manner Missile engine fed and the missile F sets moving in the direction of launch. Fig. 2 shows a moment just before the full exit of the missile F from the launch tube A. The missile F is still within the launch tube via the tail unit L. A supported while the support body S1 and S2 - and two more, not shown Support body - led out of the launch tube A. and are explained in more detail below Construction after the exit a strong Pulse in the direction of arrow Q, i.e. the transverse direction to Firing direction. Fig. 3 shows that due to this impulse after the complete exit of the Missile F from the launch tube 8, the support body S1 and S2 as far from the missile F in the transverse direction have moved away that no collision with the Tail L more occurs.

    Im folgenden wird anhand der Fig. 4 bis 10 der genauere Aufbau des Stützkörpers S1 in Fig. 1 bis 3 näher erläutert. Die übrigen Stützkörper sind genau in der gleichen Weise aufgebaut. The following is the more precise with reference to FIGS. 4 to 10 Structure of the support body S1 in Fig. 1 to 3 in more detail explained. The remaining support bodies are exactly in built the same way.

    Der Stützkörper S1 besitzt ein Oberteil 1 und ein Unterteil 2, die miteinander über eine Schraubverbindung 3 lösbar verbunden sind. Durch Ober- und Unterteil wird innerhalb des Stützkörpers ein Innenraum 13 abgegrenzt. Die Oberseite des Oberteils 1 ist mindestens in Teilbereichen 1.1 an die Innenfläche des Abschußrohres angepaßt, während die Unterseite 2.1 des Unterteils 2 an die Außenform des Flugkörpers F angepaßt ist. In Fig. 4 ist der Abstand zwischen der Unterseite 2.1 des Unterteils 2 und der Oberseite 1.1 des Oberteils 1 als Radiusabschnitt R eingezeichnet, der den Unterschied im Kaliber zwischen dem Flugkörper F und dem Abschußrohr A bestimmt.The support body S1 has an upper part 1 and a lower part 2 connected to each other via a screw connection 3 are detachably connected. Through the upper and lower part an interior 13 is formed within the support body delimited. The top of the top 1 is at least in partial areas 1.1 to the inner surface of the launch tube adjusted while the bottom 2.1 of the Lower part 2 adapted to the outer shape of the missile F. is. 4 is the distance between the Bottom 2.1 of the lower part 2 and the top 1.1 of the upper part 1 is shown as a radius section R, the difference in caliber between the missile F and the launch tube A determined.

    An der Außenseite des Oberteils 1 sind weiterhin Führungsnuten 1.3 angeordnet, durch die in nicht eigens dargestellter und bekannter Weise Halterungsbänder gezogen werden, mit denen die Stützkörper am Flugkörper befestigt werden, bevor dieser in das Abschußrohr eingesetzt wird. Nach dem Einsetzen des Flugkörpers in das Abschußrohr werden, nachdem sich die Stützkörper an der Innenwand des Abschußrohres abstützen, diese Bänder wieder herausgezogen.On the outside of the upper part 1 there are still guide grooves 1.3 arranged by the in not specifically illustrated and known manner support straps be pulled with which the support body on the missile be attached before this in the launch tube is used. After inserting the missile into the launch tube after the support body support on the inner wall of the launch tube, pulled these tapes out again.

    Im Unterteil 2 des Stützkörpers sind zwei Stößel 4 angeordnet, die an ihrem hinteren Ende an Führungsstücken 2.2 mit Führungsflächen 2.3 in Richtung auf die Unterseite 2.1 bewegbar geführt sind. An den Führungsstücken 2.2 stützen sich starke Schraubendruckfedern 5 ab, die mit ihrem anderen Ende jeweils auf einem Kragen 4.2 des Stößels 4 aufliegen und somit eine Kraftwirkung ausüben derart, daß jeweils das äußere Ende 4.1 des Stößels 4 im in den Figuren dargestellten, nicht eingebauten Zustand des Stützkörpers aus Öffnungen aus der Unterseite 2.1 des Unterteils 2 um ein vorgegebenes Stück herausragt. Die vorderen Enden 4.1 der Stößel 4 sind an Führungsflächen 2.4 im Unterteil 2 geführt. Beim Anbau der Stützkörper an den Flugkörper sitzen die äußeren Enden 4.1 der Stößel 4 auf der Oberfläche des Flugkörpers auf und sind im abschußbereiten Zustand gegen die Wirkung der Druckfedern 5 ganz in das Unterteil 2 eingedrückt. Beim Herausführen der Stützkörper aus dem Abschußrohr während des Abschießens wird der Stützkörper aufgrund der Kraft der Druckfedern 5 über die Stößel 4 mit einem starken Impuls vom Flugkörper abgedrückt.In the lower part 2 of the support body there are two plungers 4 arranged at its rear end on guide pieces 2.2 with guide surfaces 2.3 in the direction of the bottom 2.1 are movably guided. On the guide pieces 2.2 strong helical compression springs are supported 5 starting at each other with their other end rest a collar 4.2 of the plunger 4 and thus exert a force such that each outer end 4.1 of the plunger 4 in the shown in the figures, not installed condition of the support body from openings from the bottom 2.1 of the lower part 2 protrudes by a predetermined amount. The front ends 4.1 of the plunger 4 are on guide surfaces 2.4 performed in the lower part 2. When growing the Support bodies on the missile sit the outer ends 4.1 the plunger 4 on the surface of the missile and are ready to fire against the effect of the compression springs 5 completely in the lower part 2 indented. When the support body is brought out the launch tube during firing Support body due to the force of the compression springs 5 the plunger 4 with a strong impulse from the missile pulled the trigger.

    Der an den Flugkörper angesetzte Stützkörper ist am Flugkörper über ein unter der Wirkung einer Druckfeder 10 stehendes Führungsteil 9 geführt, das sich in Längsrichtung erstreckt und mit seinem äußeren Teil 9.1 in eine entsprechende Nut an der Oberfläche des Flugkörpers eingreift (s.Fig. 5 und 7).The support body attached to the missile is on Missile over a under the action of a compression spring 10 guided guide part 9, which is in Extends longitudinally and with its outer part 9.1 in a corresponding groove on the surface of the Missile engages (see Figures 5 and 7).

    Im folgenden wird die bereits erwähnte Übertragung elektrischer Signale vom Abschußrohr auf den Flugkörper über die Stützkörper genauer erläutert. Wie aus den Fig. 5 und 6 zu entnehmen, sind im Unterteil 2 mehrere in Richtung auf die Unterseite geführte und bewegbare untere elektrische Kontaktstifte 7 - im dargestellten Ausführungsbeispiel sind es fünf Kontaktstifte - angeordnet, die mit ihren äußeren Enden 7.1 aus der Unterseite 2.1 herausragen. In analoger Weise sind im Oberteil mehrere gegenüber der Oberseite geführte und bewegbare obere elektrische Kontaktstifte 6 angeordnet, deren äußere Enden 6.1 innerhalb von in Fig. 4 dargestellten Umfangsnuten 1.2 herausragen. Die unteren und oberen elektrischen Kontaktstifte sind in nicht besonders dargestellter Weise jeweils gegenüber dem Körper des Unterteils und des Oberteils isoliert, beispielsweise in der Art, daß sie aus Kunststoff mit einem elektrisch leitenden Kern hergestellt sind. Jeder der unteren Kontaktstifte 7 ist mit einem ihm zugeordneten oberen Kontaktstift 6 über einen Wendelleiter 8 verbunden, der sowohl die Funktion eines elektrischen Leiters als auch die Funktion einer Druckfeder ausübt, gegen deren Wirkung die äußeren Enden 6.1 bzw. 7.1 der Kontaktstifte zurückgedrückt werden können. Im abschußbereiten Zustand liegen die äußeren Enden 7.1 bzw. 6.1 der Kontaktstifte an entsprechenden Gegenkontakten GK2 bzw. GK1 (s.Fig. 1) des Flugkörpers bzw. des Abschußrohres an, wobei der erforderliche Kontaktdruck von den Wendelleitern 8 erzeugt wird. Selbstverständlich ist der durch die als Druckfedern wirkenden Wendel leiter 8 erzeugte Druck wesentlich geringer als der von den Schraubendruckfedern 5 erzeugte Druck zum Abstoßen der Stützkörper nach dem Abschuß.The following is the transfer already mentioned electrical signals from the launch tube to the missile explained in more detail about the support body. How from 5 and 6 can be seen in the lower part 2 several led towards the bottom and movable lower electrical contact pins 7 - im illustrated embodiment, there are five contact pins - arranged with their outer ends 7.1 protrude from the bottom 2.1. In analog There are several ways in the top opposite the top guided and movable upper electrical contact pins 6 arranged, the outer ends 6.1 within of circumferential grooves 1.2 shown in FIG. 4 stick out. The lower and upper electrical contact pins are not particularly shown in Way each against the body of the lower part and the top isolated, for example in the Art that they are made of plastic with an electrically conductive Core are made. Each of the bottom contact pins 7 is associated with an upper one Contact pin 6 connected via a spiral conductor 8, of both the function of an electrical conductor as well as the function of a compression spring, against the effect of the outer ends 6.1 and 7.1 of the contact pins can be pushed back. I'm ready to fire State are the outer ends 7.1 or 6.1 of the contact pins on corresponding mating contacts GK2 or GK1 (see Fig. 1) of the missile or the Launch tube, the required contact pressure is generated by the spiral ladders 8. Of course is the one that acts as compression springs Spiral head 8 generated pressure much lower than that generated by the helical compression springs 5 Pressure to push off the support body after the Launch.

    Über die Kontaktstifte 6 bzw. 7 können außer den Zündsignalen weitere Signale zur Übertragung von elektrischer Information zwischen einer außerhalb des Abschußrohres liegenden Steuereinrichtung und dem Flugkörper geleitet werden.About the contact pins 6 and 7 can in addition to the Ignition signals further signals for the transmission of electrical information between one outside the Launch tube lying control device and Missiles are directed.

    Claims (4)

    1. Launch device for self-propelled missiles (F), in particular artillery rockets, with at least one launch tube (A), in which the missile (F) for launch is arranged in the ready-for-launch condition in such a way that it is supported on the internal wall of the launch tube (A) via a tail unit (L) at its rear end and in the front region via several support bodies (S1, S2) arranged on its circumference, wherein the support bodies (S1, S2) adjoin the missile (F) in such a way that they are ejected from the launch tube (A) together with the missile (F) on launch, characterized in that each support body (S1) is constructed from an upper part (1) adjoining the internal wall of the launch tube (A) with its upper side (1.1) in the ready-for-launch condition and a lower part (2) adjoining the missile (F) with its underside (2.1) in the ready-for-launch condition and upper part (1) and lower part (2) are firmly connected together via detachable connections (3), and several movable lower electrical contact pins (7) guided in the direction of the underside (2.1) in an electrically insulated manner with respect to the support body (S1) are arranged in the lower part (2), which contact pins are under the effect of a compression spring (8) in each case, in such a way that their outer ends (7.1) project by a specified portion from openings on the underside (2.1) when the support body is not incorporated, whereas they are in contact with electrical counter-contacts (GK2) on the outside of the missile (F) in the ready-to-launch condition, and several movable upper electrical contact pins (6) guided in the direction of the upper side (1.1) in an electrically insulated manner with respect to the support body are arranged in the upper part (1), which contact pins are under the effect of a compression spring (8) in each case, in such a way that their outer ends (6.1) project by a specified portion from openings on the upper side (1.1) when the support body is not incorporated whereas they are in contact with electrical counter-contacts (GK1) on the inside of the launch tube (A) in the ready-to-launch condition and each upper electrical contact pin (6) is connected in an electrically conductive manner to at least one lower electrical contact pin (7).
    2. Launch device according to Claim 1, characterized in that at least two movable rams (4) guided in the direction of the underside (2.1) are arranged in the lower part, which rams are under the effect of a compression spring (5) in each case, in such a way that their outer ends (4.1) project by a specified portion from openings on the underside (2.1) of the lower part (2) when the support body (S1) is not incorporated whereas they are pressed completely into the lower part (2) against the effect of the compression springs (5) in the ready-for-launch condition.
    3. Launch device according to Claim 1 or 2, characterized in that upper part (1) and lower part (2) of the support body (S1) are connected together via screw connections (3).
    4. Launch device according to Claim 2, characterized in that the conductive connection between the upper electrical contact pins (6) and the lower electrical contact pins (7) takes place in each case via a helical conductor (8) exerting spring force on the contact pins (6, 7) connected together.
    EP96102429A 1995-03-07 1996-02-17 Launcher for self-propelled missiles, in particular for artillery rockets Expired - Lifetime EP0731331B1 (en)

    Applications Claiming Priority (2)

    Application Number Priority Date Filing Date Title
    DE19508008 1995-03-07
    DE19508008A DE19508008A1 (en) 1995-03-07 1995-03-07 Launching device for self-propelled missiles, in particular artillery missiles

    Publications (3)

    Publication Number Publication Date
    EP0731331A2 EP0731331A2 (en) 1996-09-11
    EP0731331A3 EP0731331A3 (en) 1996-11-27
    EP0731331B1 true EP0731331B1 (en) 1998-04-15

    Family

    ID=7755900

    Family Applications (1)

    Application Number Title Priority Date Filing Date
    EP96102429A Expired - Lifetime EP0731331B1 (en) 1995-03-07 1996-02-17 Launcher for self-propelled missiles, in particular for artillery rockets

    Country Status (2)

    Country Link
    EP (1) EP0731331B1 (en)
    DE (2) DE19508008A1 (en)

    Families Citing this family (7)

    * Cited by examiner, † Cited by third party
    Publication number Priority date Publication date Assignee Title
    DE102008017437A1 (en) * 2008-04-03 2009-10-08 Rheinmetall Waffe Munition Gmbh Sabot projectile
    IT1400621B1 (en) * 2010-05-13 2013-06-14 Oto Melara Spa COMMUNICATION SYSTEM DATA TO A SPOOL OF A FIRE WEAPON.
    EP3077759B1 (en) * 2013-12-06 2018-05-30 Rheinmetall Waffe Munition GmbH Contact device module, in particular for electrically contacting a weapon with ammunition which can be found in the weapon
    DE102014016340B3 (en) * 2014-11-05 2015-08-20 Bundesrepublik Deutschland, vertreten durch das Bundesministerium der Verteidigung, vertreten durch das Bundesamt für Ausrüstung, Informationstechnik und Nutzung der Bundeswehr Programming device for programming a programmable artillery ammunition
    FR3099393B1 (en) 2019-08-01 2022-07-08 Psa Automobiles Sa Stamping press with roller launch
    DE102021000884B4 (en) 2021-02-19 2023-07-27 Mbda Deutschland Gmbh PAYLOAD CARRIER AND GASKET KIT AND JOINING METHOD FOR SEALING A GAP
    CN113357963B (en) * 2021-06-15 2023-03-07 湖北航天技术研究院总体设计所 Method and system for controlling auxiliary supporting leg lowering of launching device

    Family Cites Families (11)

    * Cited by examiner, † Cited by third party
    Publication number Priority date Publication date Assignee Title
    DE310009C (en) *
    US2998780A (en) * 1956-05-28 1961-09-05 William B Anspacher High velocity, fin stabilized projectile, rifled barrel gun system
    US3120784A (en) * 1962-02-19 1964-02-11 William M Magers Booster contactor
    US3610095A (en) * 1967-06-29 1971-10-05 Us Army Rocket means for driving a free punch
    IL37041A (en) * 1971-06-14 1976-02-29 State Of Il Ministry Of Def Forward sabot for sub-calibre projectile with delayed detachment
    US4455916A (en) * 1982-02-22 1984-06-26 The United States Of America As Represented By The Secretary Of The Navy Armament shorting arrangement
    DE3211011A1 (en) * 1982-03-25 1983-09-29 Dynamit Nobel Ag, 5210 Troisdorf EXERCISE ROCKET
    DE3414911A1 (en) * 1984-04-19 1985-10-24 Dynamit Nobel Ag, 5210 Troisdorf Missile, especially a ballistic rocket
    US4638739A (en) * 1986-02-14 1987-01-27 The United States Of America As Represented By The Secretary Of The Army Sabot for an electromagnetically-accelerated, unguided hypervelocity penetrator
    USH405H (en) * 1987-08-24 1988-01-05 The United States Of America As Represented By The Secretary Of The Army Rocket/launcher interface
    DE3939037C2 (en) * 1989-11-25 1994-01-27 Diehl Gmbh & Co Gun shaped launch device for underwater projectile

    Also Published As

    Publication number Publication date
    EP0731331A3 (en) 1996-11-27
    DE19508008A1 (en) 1996-09-12
    DE59600152D1 (en) 1998-05-20
    EP0731331A2 (en) 1996-09-11

    Similar Documents

    Publication Publication Date Title
    DE9213376U1 (en) Shock weapon
    DE2558060A1 (en) SUPPORT BULLET FOR EJECTABLE BODY
    EP0731331B1 (en) Launcher for self-propelled missiles, in particular for artillery rockets
    DE2936861C2 (en) Cartridge for scattering decoy material, in particular from an aircraft
    DE2556075C2 (en) Cartridge for shooting target objects used as bait
    DE3888288T2 (en) Propellant charge for wing-stabilized projectile ammunition and process for its manufacture.
    DE2125149A1 (en) weapon
    DE3111830C2 (en) Flare rocket with a cylindrical container
    WO2004102107A9 (en) Rapid-fire weapon
    DE2757806C2 (en) Connection device between two stages of a self-propelled missile
    DE2829002A1 (en) Multiple headed missile system - moves initial- and after-action bodies apart axially before detonation
    DE3904625C2 (en)
    DE68923769T2 (en) Lighter.
    DE69207157T2 (en) Carrier projectile with a piston for ejecting a submunition
    DE3640485C1 (en) Bomblet (submunition)
    DE4105271C1 (en)
    DE2757664A1 (en) DEVICE FOR CHANGING THE AIRWAY OF ONE FLOOR
    DE69210485T2 (en) Projectile provided with a plurality of explosive charges
    DE2743770C2 (en) Device for the electrical ignition of a pyrotechnic charge
    DE1578472A1 (en) Safety and ignition device for floors
    DE1130735B (en) Rocket with a driving and a driven part
    DE2946156C2 (en)
    DE3929567C1 (en)
    DE2558836B2 (en) Electric projectile fuse
    DE3148170C2 (en) Shaped charge ammunition with slide-out spacer pin

    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

    Kind code of ref document: A2

    Designated state(s): BE DE FR GB IT NL

    PUAL Search report despatched

    Free format text: ORIGINAL CODE: 0009013

    AK Designated contracting states

    Kind code of ref document: A3

    Designated state(s): BE DE FR GB IT NL

    17P Request for examination filed

    Effective date: 19961115

    17Q First examination report despatched

    Effective date: 19970123

    GRAG Despatch of communication of intention to grant

    Free format text: ORIGINAL CODE: EPIDOS AGRA

    GRAG Despatch of communication of intention to grant

    Free format text: ORIGINAL CODE: EPIDOS AGRA

    GRAH Despatch of communication of intention to grant a patent

    Free format text: ORIGINAL CODE: EPIDOS IGRA

    GRAH Despatch of communication of intention to grant a patent

    Free format text: ORIGINAL CODE: EPIDOS IGRA

    GRAA (expected) grant

    Free format text: ORIGINAL CODE: 0009210

    AK Designated contracting states

    Kind code of ref document: B1

    Designated state(s): BE DE FR GB IT NL

    ITF It: translation for a ep patent filed

    Owner name: STUDIO INGG. FISCHETTI & WEBER

    REF Corresponds to:

    Ref document number: 59600152

    Country of ref document: DE

    Date of ref document: 19980520

    ET Fr: translation filed
    GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

    Effective date: 19980527

    PLBE No opposition filed within time limit

    Free format text: ORIGINAL CODE: 0009261

    STAA Information on the status of an ep patent application or granted ep patent

    Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

    26N No opposition filed
    REG Reference to a national code

    Ref country code: GB

    Ref legal event code: IF02

    PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

    Ref country code: NL

    Payment date: 20130218

    Year of fee payment: 18

    REG Reference to a national code

    Ref country code: NL

    Ref legal event code: V1

    Effective date: 20140901

    PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

    Ref country code: NL

    Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

    Effective date: 20140901

    PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

    Ref country code: DE

    Payment date: 20140711

    Year of fee payment: 19

    PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

    Ref country code: GB

    Payment date: 20140721

    Year of fee payment: 19

    Ref country code: FR

    Payment date: 20140724

    Year of fee payment: 19

    PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

    Ref country code: IT

    Payment date: 20140724

    Year of fee payment: 19

    PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

    Ref country code: BE

    Payment date: 20140722

    Year of fee payment: 19

    PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

    Ref country code: BE

    Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

    Effective date: 20150228

    REG Reference to a national code

    Ref country code: DE

    Ref legal event code: R119

    Ref document number: 59600152

    Country of ref document: DE

    GBPC Gb: european patent ceased through non-payment of renewal fee

    Effective date: 20150217

    REG Reference to a national code

    Ref country code: FR

    Ref legal event code: ST

    Effective date: 20151030

    PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

    Ref country code: IT

    Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

    Effective date: 20150217

    PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

    Ref country code: DE

    Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

    Effective date: 20150901

    Ref country code: GB

    Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

    Effective date: 20150217

    PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

    Ref country code: FR

    Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

    Effective date: 20150302