EP0052675B1 - Einrichtung und Verfahren zur Abfeuerung von Raketen - Google Patents

Einrichtung und Verfahren zur Abfeuerung von Raketen Download PDF

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Publication number
EP0052675B1
EP0052675B1 EP80304163A EP80304163A EP0052675B1 EP 0052675 B1 EP0052675 B1 EP 0052675B1 EP 80304163 A EP80304163 A EP 80304163A EP 80304163 A EP80304163 A EP 80304163A EP 0052675 B1 EP0052675 B1 EP 0052675B1
Authority
EP
European Patent Office
Prior art keywords
coil
firing
rocket
magnetic core
driver
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
Application number
EP80304163A
Other languages
English (en)
French (fr)
Other versions
EP0052675A1 (de
Inventor
John Ramsay Florence
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.)
CESSIONE;WIDNEY AISH LIMITED
Original Assignee
Horstmann Gear Group Ltd
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
Priority to GB7923707A priority Critical patent/GB2055181B/en
Application filed by Horstmann Gear Group Ltd filed Critical Horstmann Gear Group Ltd
Priority to AT80304163T priority patent/ATE13224T1/de
Priority to DE8080304163T priority patent/DE3070627D1/de
Priority to EP80304163A priority patent/EP0052675B1/de
Publication of EP0052675A1 publication Critical patent/EP0052675A1/de
Application granted granted Critical
Publication of EP0052675B1 publication Critical patent/EP0052675B1/de
Expired legal-status Critical Current

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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
    • 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
    • F41A19/63—Electric firing mechanisms having means for contactless transmission of electric energy, e.g. by induction, by sparking gap
    • 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
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C21/00—Checking fuzes; Testing fuzes

Definitions

  • This invention relates to a rocket firing system and to a method of firing a rocket; the rocket firing system is positioned on a launcher device.
  • the invention provides a rocket firing system comprising a magnetic cord and a driver coil mounted co-axial therewith for inducing a firing voltage in a rocket firing circuit coil brought into inductive linkage with the core, characterised in that means are provided for effecting a pre-firing check, said means comprising a sensor coil inductively linked with the core and driver coil and a detector device connected to the sensor coil to determine the presence and state of a said rocket firing circuit coil.
  • the sensor coil is in two parts lying transversely of and closely adjacent the driver coil.
  • the firing system may be embodied in a rocket launcher device.
  • the invention provides a method of firing a rocket having an inductive firing circuit adapted to be magnetically linked by a firing system having a magnetic core and a driver coil, wherein first the core is brought to link magnetically with the firing circuit, then a low-power signal voltage is applied to the driver coil, the presence and state of the firing circuit being monitored by a signal regenerated in a sensor coil, and thereafter an operating power voltage is applied to the driver coil so as to induce a firing voltage in the firing circuit.
  • the firing system which is mounted on the rocket launcher comprises in essence a magnetic core D, which is surrounded by a driver coil A.
  • a sensor coil B mounted in close physical proximity to the coil A is a sensor coil B which is divided into two part 8, and B 2 .
  • the coil B has its magnetic axis perpendicular to that of coil A and to the core D.
  • the system is positioned on the launcher such that the core D aligns with a coil C mounted on a rocket positioned in the launcher.
  • the coil C is connected in circuit with a detonator match in the form of a low-voltage, high-current hot wire coil onto which has been deposited a heat sensitive pyrotechnic material.
  • the firing circuit driving coil C has an internal diameter larger than the core D, and when the rocket is in position, the core D enters the coil C and makes an inductive link therewith.
  • Coil A is connectible to a suitable alternating current supply and which is controlled at two power levels, a low power signal level for testing purposes and a full operating power level for firing.
  • the coil B is connected to a suitable voltage detection circuit.
  • the firing system is set up by moving core D with no rocket present and with the coil A energised at the signal level until the induced voltage in coil B is at a minimum. The core D is then locked in position.
  • the coil parts 8, and 8 2 are wound in position, and positioned so that one part will cut more flux than the other when the flux pattern becomes asymmetrically distorted by the presence of coil C. This gives a greater sensitivity, and since signal in coil B is a minimum in the balance of a rocket, allows the use of a threshold detector in the circuit to eliminate external effects.
  • the coil parts are preferably connected in a bridge circuit. A single sensor coil, or one co-axial with the core D, could in theory be used but is very much less sensitive.
  • two sensor coils coaxial with the core D are used, preferably in a bridge circuit.
  • Such a firing system is adapted well to being applied to a series of launchers, and testing and firing can be carried out remotely, either sequentially or in unison.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Measurement Of Length, Angles, Or The Like Using Electric Or Magnetic Means (AREA)

Claims (10)

1. Ein System zum Abfeuern einer Rakete mit einem Magnetkern (D) und einer koaxial angeordneten Antriebsspule (A) zum Induzieren einer Zündspannung in einer mit dem Kern in induktive Verbindung gebrachten Raketen-Zündkreisspule (C), dadurch gekennzeichnet, daß Mittel zum Herstellen einer Vor-Zündkontrolle vorgesehen sind, die aus einer induktiv mit dem Kern und der Antriebsspule (A) verbundenen Fühlerspule (B1, B2) und einer mit der Fühlerspule (B1, B2) verbundenen Detektoreinrichtung zur Bestimmung des Vorliegens und des Zustandes der Raketen-Zündkreisspule bestehen.
2. Ein System gemäß Anspruch 1, bei dem die Fühlerspule (B1, B2) aus zwei Teilen besteht, die quer zur Antriebsspule und in deren unmittelbaren Nähe angeordnet sind.
3. Ein System gemäß Anspruch 1, bei dem die Fühlerspule (B1, B2) aus zwei Teilen besteht, von denen jeder koaxial mit der Antriebsspule angeordnet ist.
4. Ein System gemäß Anspruch 2 oder 3, bei dem die Teile der Fühlerspule (B1, B2) an einen Brückenkreis angeschlossen sind.
5. Ein System gemäß einem der Ansprüche 2 bis 4, bei dem die Teile der Fühlerspule so gewickelt und angeordnet sind, daß nach Herstellen der induktiven Verbindung der Raketen-Zündkreisspule mit dem Magnetkern (D) ein Spulenteil einen kleineren Fluß aufweist als der andere.
6. Ein System gemäß einem der Ansprüche 2 bis 5, bei dem ein Schwellenwertdetektor mit den Fühlerspulenteilen verbunden ist.
7. Ein System gemäß einem der vorhergehenden Ansprüche, bei dem die Antriebsspule (A) an eine Wechselstromquelle angeschlossen ist und auf mindestens zwei Stromstärken geschaltet werden kann.
8. Ein Verfahren zum Abfeuern einer Rakete mit einem induktiven Zündkreis, der magnetisch mit einem Zündsystem mit einem Magnetkern (D) und einer Antriebsspule (A) verbunden werden kann, dadurch gekennzeichnet, daß zuerst der Magnetkern magnetisch mit dem Zündkreis in Verbindung gebracht wird, worauf eine Schwachstrom-Signalspannung an die Antriebsspule (A) angelegt wird, wobei das Vorliegen und der Zustand des Zündkreises durch ein in der Fühlerspule (B1, B2) erzeugtes Signal überwacht wird, und anschließend eine Betriebsstromspannung an die Antriebsspule (A) angelegt wird, um eine Zündspannung im Zündkreis zu erzeugen.
9. Ein Verfahren zum Abfeuern einer Rakete gemäß Anspruch 8, bei dem vor Herstellen der magnetischen Verbindung des Magnetkerns (D) mit dem Zündkreis das Zündsystem durch Anlegen der Schwachstrom-Signalspannung an die Antriebsspule (A) und Bewegen des Magnetkerns (D), bis die in der Fühlerspule (B1, B2) induzierte Spannung einen Mindestwert erreicht hat, eingestellt wird, worauf der Magnetkern (D) in seiner Lage fixiert wird.
10. Ein Verfahren zum Abfeuern einer Rakete gemäß Anspruch 8 oder 9, bei dem das Vorliegen und der gewünschte Zustand des Zündkreises in ein asymmetrisches Flußmuster gegenüber der Fühlerspule (B1, B2) bewirkt.
EP80304163A 1979-07-06 1980-11-20 Einrichtung und Verfahren zur Abfeuerung von Raketen Expired EP0052675B1 (de)

Priority Applications (4)

Application Number Priority Date Filing Date Title
GB7923707A GB2055181B (en) 1979-07-06 1979-07-06 Rocket firing system
AT80304163T ATE13224T1 (de) 1980-11-20 1980-11-20 Einrichtung und verfahren zur abfeuerung von raketen.
DE8080304163T DE3070627D1 (en) 1980-11-20 1980-11-20 A rocket firing system and a method of firing a rocket
EP80304163A EP0052675B1 (de) 1979-07-06 1980-11-20 Einrichtung und Verfahren zur Abfeuerung von Raketen

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB7923707A GB2055181B (en) 1979-07-06 1979-07-06 Rocket firing system
EP80304163A EP0052675B1 (de) 1979-07-06 1980-11-20 Einrichtung und Verfahren zur Abfeuerung von Raketen

Publications (2)

Publication Number Publication Date
EP0052675A1 EP0052675A1 (de) 1982-06-02
EP0052675B1 true EP0052675B1 (de) 1985-05-08

Family

ID=26079968

Family Applications (1)

Application Number Title Priority Date Filing Date
EP80304163A Expired EP0052675B1 (de) 1979-07-06 1980-11-20 Einrichtung und Verfahren zur Abfeuerung von Raketen

Country Status (2)

Country Link
EP (1) EP0052675B1 (de)
GB (1) GB2055181B (de)

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1235844A (en) * 1967-10-17 1971-06-16 Ml Aviation Co Ltd Electrical ignition of explosive devices

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3123002A (en) * 1964-03-03 Spool
GB640893A (en) * 1940-07-22 1950-08-02 Standard Telephones Cables Ltd Magnetic detectors, especially applicable to locomotive torpedoes
US2555384A (en) * 1948-01-14 1951-06-05 Gordon J Watt Electrically set mechanical time fuse
US4142442A (en) * 1971-12-08 1979-03-06 Avco Corporation Digital fuze
CH589838A5 (de) * 1975-03-10 1977-07-15 Oerlikon Buehrle Ag

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1235844A (en) * 1967-10-17 1971-06-16 Ml Aviation Co Ltd Electrical ignition of explosive devices

Also Published As

Publication number Publication date
GB2055181B (en) 1982-11-24
EP0052675A1 (de) 1982-06-02
GB2055181A (en) 1981-02-25

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