EP0415043A1 - Plug connection - Google Patents

Plug connection Download PDF

Info

Publication number
EP0415043A1
EP0415043A1 EP90113295A EP90113295A EP0415043A1 EP 0415043 A1 EP0415043 A1 EP 0415043A1 EP 90113295 A EP90113295 A EP 90113295A EP 90113295 A EP90113295 A EP 90113295A EP 0415043 A1 EP0415043 A1 EP 0415043A1
Authority
EP
European Patent Office
Prior art keywords
missile
locking pin
compression spring
coupling part
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
EP90113295A
Other languages
German (de)
French (fr)
Other versions
EP0415043B1 (en
Inventor
Friedrich Plank
Klaus-Dieter Burdack
Bernd Kochta
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.)
Airbus Defence and Space GmbH
Original Assignee
Daimler Benz Aerospace AG
Messerschmitt Bolkow Blohm AG
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 Daimler Benz Aerospace AG, Messerschmitt Bolkow Blohm AG filed Critical Daimler Benz Aerospace AG
Publication of EP0415043A1 publication Critical patent/EP0415043A1/en
Application granted granted Critical
Publication of EP0415043B1 publication Critical patent/EP0415043B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
    • H01R13/00—Details of coupling devices of the kinds covered by groups H01R12/70 or H01R24/00 - H01R33/00
    • H01R13/62—Means for facilitating engagement or disengagement of coupling parts or for holding them in engagement
    • H01R13/629—Additional means for facilitating engagement or disengagement of coupling parts, e.g. aligning or guiding means, levers, gas pressure electrical locking indicators, manufacturing tolerances
    • H01R13/633—Additional means for facilitating engagement or disengagement of coupling parts, e.g. aligning or guiding means, levers, gas pressure electrical locking indicators, manufacturing tolerances for disengagement only
    • H01R13/635—Additional means for facilitating engagement or disengagement of coupling parts, e.g. aligning or guiding means, levers, gas pressure electrical locking indicators, manufacturing tolerances for disengagement only by mechanical pressure, e.g. spring force

Definitions

  • the invention relates to a plug connection according to the preamble of claim 1.
  • the invention has for its object to provide a connector of the type mentioned, which does not require separate external mechanisms to trigger it.
  • the main advantage of the invention is that the trigger parts are integrated with the fixed plug part attached to the starting tube and no separate electrical trigger energy is required.
  • the displaceable coupling part and the guide sleeve with the locking pin are easy to manufacture and can be accommodated in or on the plug housing without great structural outlay.
  • the electrical connection between the missile and the launch system is triggered automatically when the missile is released.
  • the invention is explained below with reference to the drawing.
  • the single figure shows a connector on a launch tube for a missile.
  • a missile 2 is housed ready to fire, which has an attachment part 3, which can also serve as a fin or rudder, for example.
  • a fixed plug 5 is attached to the starting tube 1 on a holder 4.
  • the plug connection parts of the plug 5, which cooperate with a loose plug part 6, are of a known type.
  • a coupling part 8 is slidably accommodated, which abuts a compression spring 9 and is provided with a groove 10.
  • a guide sleeve 11 is attached to the housing 7, in which a locking pin 12 and a compression spring 13 are accommodated.
  • the locking pin 12 can pass through a housing bore 14.
  • the coupling part 8 and the locking pin 12 are each shown in a locked and a released position.
  • the locking pin 12 is pressed through the attachment part 3 of the missile 2 into the groove 10 of the coupling part 8 tensioned against the compression spring 9.
  • the missile 2 is ready to launch.
  • the extension part 3 slides from the locking pin 12, which is pressed according to the right half shown by the compression spring 13 and thereby releases the groove 10, whereby the coupling part 8 by the compression spring 9 in his released position is shifted to the right.
  • a sliding contacts 16 are released, which cooperate with counter contacts 17 in the housing 7 and maintain the power supply to the missile 2 via a cable 18 until the missile 2 starts, and on the other hand the plug connection to the loose plug part 6 is broken. Immediate automatic electrical separation of the missile 2 from its power supply prevents harmful electromagnetic interference from acting on the missile from the outside.
  • the plug 5 is designed in a known manner as a shorting plug.

Landscapes

  • Details Of Connecting Devices For Male And Female Coupling (AREA)

Abstract

A fixed connector part 5 and a loose connector part 6, which can be plugged therein, are provided on a launch tube 1 for a missile 2. Installed in the housing 7 of the fixed connector part 5 is a coupling part 8, which can be displaced against a compression spring 9 and is provided with a groove 10 for holding a locking pin 12 which is inserted externally on the housing 7 in a guide sleeve 11, against a compression spring 13. Before the missile 2 is launched, a projecting part 3 presses the locking pin 12 into the groove 10, as a result of which the connector parts 5 and 6 are electrically connected to the missile 2 via contacts 16, 17 of the coupling part 8. When the missile is launched, this electrical connection is immediately separated by the locking pin 12 being pulled out of the groove 10 and the coupling part 8 being forced away by the compression spring 9.

Description

Die Erfindung bezieht sich auf eine Steckverbindung gemäß dem Oberbeg­riff des Anspruches 1.The invention relates to a plug connection according to the preamble of claim 1.

Beim Starten von Flugkörpern muß die für das Starten des Triebwerkes und andere Startfunktionen erforderliche elektrische Verbindung zum Start­rohr gelöst werden. Zum Lösen der Steckverbindung sind externe Mechani­ken bekannt, die durch ein besonderes elektrisches Auslösesignal betä­tigt werden müssen. Dieses beansprucht Raum und Gewicht sowie zusätzli­che elektrische Energie.When launching missiles, the electrical connection to the launch tube required for starting the engine and other launch functions must be disconnected. External mechanisms are known for releasing the plug connection, which have to be actuated by a special electrical trigger signal. This takes up space and weight as well as additional electrical energy.

Der Erfindung liegt die Aufgabe zugrunde, eine Steckverbindung der ein­gangs genannten Art zu schaffen, die keine gesonderten externen Mechani­ken zu ihrer Auslösung benötigt.The invention has for its object to provide a connector of the type mentioned, which does not require separate external mechanisms to trigger it.

Diese Aufgabe wird durch die im Anspruch 1 gekennzeichneten Merkmale ge­löst. Vorteilhafte Ausgestaltungen der Erfindung sind durch die Unteran­sprüche wiedergegeben.This object is achieved by the features characterized in claim 1. Advantageous embodiments of the invention are given by the subclaims.

Der wesentliche Vorteil der Erfindung besteht darin, daß die Auslösetei­le mit dem am Startrohr angebrachten festen Steckerteil integriert sind und es keiner gesonderten elektrischen Auslöseenergie bedarf. Das ver­schiebbare Kupplungsteil und die Führungshülse mit dem Verriegelungs­stift sind einfach zu fertigen und ohne großen baulichen Aufwand im bzw. am Steckergehäuse unterzubringen. Die Auslösung der elektrischen Verbin­dung zwischen Flugkörper und Abschußanlage erfolgt automatisch mit dem Abgang des Flugkörpers.The main advantage of the invention is that the trigger parts are integrated with the fixed plug part attached to the starting tube and no separate electrical trigger energy is required. The displaceable coupling part and the guide sleeve with the locking pin are easy to manufacture and can be accommodated in or on the plug housing without great structural outlay. The electrical connection between the missile and the launch system is triggered automatically when the missile is released.

Die Erfindung wird nachstehend anhand der Zeichnung näher erläutert. Die einzige Figur zeigt eine Steckverbindung an einem Startrohr für einen Flugkörper.The invention is explained below with reference to the drawing. The single figure shows a connector on a launch tube for a missile.

In einem Startrohr 1 ist ein Flugkörper 2 abschußbereit untergebracht, der ein Ansatzteil 3 aufweist, welches beispielsweise zugleich als Flos­se oder Ruder dienen kann. An dem Startrohr 1 ist an einer Halterung 4 ein fester Stecker 5 angebracht. Vom Stecker 5 sind der Übersichtlich­keit halber nur die Teile dargestellt, die zur Funktion der zu beschrei­benden Steckverbindung erforderlich sind. Die Steckverbindungsteile des Steckers 5, die mit einem losen Steckerteil 6 zusammenwirken, sind von bekannter Art. In einem Steckergehäuse 7 ist ein Kupplungsteil 8 glei­tend untergebracht, welches gegen eine Druckfeder 9 anliegt und mit ei­ner Nut 10 versehen ist. An dem Gehäuse 7 ist eine Führungshülse 11 an­gesetzt, in der ein Verriegelungsstift 12 und eine Druckfeder 13 unter­gebracht sind. Der Verriegelungsstift 12 kann durch eine Gehäusebohrung 14 hindurchführen. Das Kupplungsteil 8 und der Verriegelungsstift 12 sind jeweils in einer eingerasteten und einer gelösten Lage dargestellt. In der eingerasteten linken Lage ist der Verriegelungsstift 12 durch das Ansatzteil 3 des Flugkörpers 2 in die Nut 10 des gegen die Druckfeder 9 gespannten Kupplungsteiles 8 gedrückt. In dieser Stellung ist der Flug­körper 2 startbereit. Nach Abgang des Flugkörpers 2 in Richtung eines Pfeiles 15 gleitet das Ansatzteil 3 von dem Verriegelungsstift 12, der entsprechend der rechten dargestellten Hälfte durch die Druckfeder 13 nach oben gedrückt wird und dabei die Nut 10 freigibt, wodurch das Kupp­lungsteil 8 durch die Druckfeder 9 in seine gelöste Stellung nach rechts verschoben wird. Hierbei werden zu einem Schleifkontakte 16 freigegeben, die mit Gegenkontakten 17 im Gehäuse 7 zusammenwirken und bis zum Start des Flugkörpers 2 die Stromversorgung mit diesem über ein Kabel 18 auf­rechterhalten, zum anderen wird die Steckverbindung zum losen Stecker­teil 6 aufgehoben. Durch sofortige automatische elektrische Trennung des Flugkörpers 2 von seiner Stromversorgung wird verhindert, daß schädliche elektromagnetische Störungen von außen auf den Flugkörper einwirken kön­nen. Dazu ist der Stecker 5 in bekannter Weise als Kurzschlußstecker ausgebildet.In a launch tube 1 a missile 2 is housed ready to fire, which has an attachment part 3, which can also serve as a fin or rudder, for example. A fixed plug 5 is attached to the starting tube 1 on a holder 4. For the sake of clarity, only the parts of the connector 5 are shown which are necessary for the function of the connector to be described. The plug connection parts of the plug 5, which cooperate with a loose plug part 6, are of a known type. In a plug housing 7, a coupling part 8 is slidably accommodated, which abuts a compression spring 9 and is provided with a groove 10. A guide sleeve 11 is attached to the housing 7, in which a locking pin 12 and a compression spring 13 are accommodated. The locking pin 12 can pass through a housing bore 14. The coupling part 8 and the locking pin 12 are each shown in a locked and a released position. In the latched left position, the locking pin 12 is pressed through the attachment part 3 of the missile 2 into the groove 10 of the coupling part 8 tensioned against the compression spring 9. In this position the missile 2 is ready to launch. After leaving the missile 2 in the direction of an arrow 15, the extension part 3 slides from the locking pin 12, which is pressed according to the right half shown by the compression spring 13 and thereby releases the groove 10, whereby the coupling part 8 by the compression spring 9 in his released position is shifted to the right. Here, a sliding contacts 16 are released, which cooperate with counter contacts 17 in the housing 7 and maintain the power supply to the missile 2 via a cable 18 until the missile 2 starts, and on the other hand the plug connection to the loose plug part 6 is broken. Immediate automatic electrical separation of the missile 2 from its power supply prevents harmful electromagnetic interference from acting on the missile from the outside. For this purpose, the plug 5 is designed in a known manner as a shorting plug.

Claims (4)

1. Steckverbindung zur elektrisch leitenden Verbindung zwischen ei­nem Startrohr und einem Flugkörper mit einem am Startrohr befestigten festen Steckerteil und einem in den festen Steckerteil einsteckbaren lo­sen Steckerteil, gekennzeichnet durch die nachfolgend aufgeführten Merkmale:
- der feste Steckerteil (5) weist innen ein, zwischen einer eingera­steten Stellung und einer gelösten Stellung, mittels einer Druckfe­der (9) verschiebbares Kupplungsteil (8) auf;
- das Einrasten des Kupplungsteils (8) erfolgt von außen durch Ein­schieben eines Verriegelungsstiftes (12) gegen eine Druckfeder (13) in eine Nut (10) des Kupplungsteils;
- das Kupplungsteil (8) stellt in der eingerasteten Stellung mittels Kontakte (16, 17) die elektrische Verbindung zum Flugkörper (2) her.1. Plug connection for the electrically conductive connection between a launch tube and a missile with a fixed connector part fastened to the launch tube and a loose connector part which can be inserted into the fixed connector part, characterized by the features listed below:
- The fixed plug part (5) has a coupling part (8) which can be displaced by means of a compression spring (9) between an engaged position and a released position;
- The coupling part (8) engages from the outside by inserting a locking pin (12) against a compression spring (13) into a groove (10) of the coupling part;
- The coupling part (8) in the locked position by means of contacts (16, 17) establishes the electrical connection to the missile (2). 2. Steckverbindung nach Anspruch 1, dadurch gekennzeichnet, daß der Verriegelungsstift (12) zusammen mit der Druckfeder (13) am Gehäuse (7) des festen Steckerteils (5) in einer Führungshülse (11) gelagert ist.2. Plug connection according to claim 1, characterized in that the locking pin (12) together with the compression spring (13) on the housing (7) of the fixed plug part (5) is mounted in a guide sleeve (11). 3. Steckverbindung nach Anspruch 1, dadurch gekennzeichnet, daß der Verriegelungsstift (12) durch ein am Flugkörper (2) angebrachtes An­satzteil (3) in die Nut (10) des Kupplungsteils (8) eingeschoben und dort festgehalten ist.3. Plug connection according to claim 1, characterized in that the locking pin (12) by an attached to the missile (2) attachment part (3) in the groove (10) of the coupling part (8) is inserted and held there. 4. Steckverbindung nach den Ansprüchen 1 bis 3, dadurch gekenn­zeichnet, daß nach dem Start des Flugkörpers (2) der Verriegelungsstift (12) durch das Ansatzteil (3) freigegeben ist und eine sofortige elek­trische Trennung des festen Steckerteils (5) vom Flugkörper und vom lo­sen Steckerteil (6) erfolgt.4. Plug connection according to claims 1 to 3, characterized in that after the launch of the missile (2) the locking pin (12) is released by the extension part (3) and an immediate electrical separation of the fixed plug part (5) from the missile and from loose connector part (6).
EP90113295A 1989-08-26 1990-07-07 Plug connection Expired - Lifetime EP0415043B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3928245A DE3928245A1 (en) 1989-08-26 1989-08-26 CONNECTOR
DE3928245 1989-08-26

Publications (2)

Publication Number Publication Date
EP0415043A1 true EP0415043A1 (en) 1991-03-06
EP0415043B1 EP0415043B1 (en) 1994-10-12

Family

ID=6387938

Family Applications (1)

Application Number Title Priority Date Filing Date
EP90113295A Expired - Lifetime EP0415043B1 (en) 1989-08-26 1990-07-07 Plug connection

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Country Link
EP (1) EP0415043B1 (en)
DE (2) DE3928245A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0627786A1 (en) * 1993-06-02 1994-12-07 AEROSPATIALE Société Nationale Industrielle Process and system for the physical separation of two joint electrically connected bodies

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3599167A (en) * 1969-04-10 1971-08-10 Deutsch Co Elec Comp Three-unit electrical connector
US3843853A (en) * 1973-11-15 1974-10-22 Itt Electrical connector with switch and latch means therefore
US4291931A (en) * 1979-02-12 1981-09-29 Bunker Ramo Corporation Shear plane separable connector
US4820176A (en) * 1987-09-07 1989-04-11 Shiraishi Electric Corporation Electric power supply connector

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL282635A (en) * 1962-05-10
FR1590790A (en) * 1968-11-05 1970-04-20

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3599167A (en) * 1969-04-10 1971-08-10 Deutsch Co Elec Comp Three-unit electrical connector
US3843853A (en) * 1973-11-15 1974-10-22 Itt Electrical connector with switch and latch means therefore
US4291931A (en) * 1979-02-12 1981-09-29 Bunker Ramo Corporation Shear plane separable connector
US4820176A (en) * 1987-09-07 1989-04-11 Shiraishi Electric Corporation Electric power supply connector

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0627786A1 (en) * 1993-06-02 1994-12-07 AEROSPATIALE Société Nationale Industrielle Process and system for the physical separation of two joint electrically connected bodies
FR2706086A1 (en) * 1993-06-02 1994-12-09 Aerospatiale Method and system for the physical separation of two integral bodies electrically connected to one another

Also Published As

Publication number Publication date
DE3928245A1 (en) 1991-02-28
DE3928245C2 (en) 1991-12-12
DE59007438D1 (en) 1994-11-17
EP0415043B1 (en) 1994-10-12

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