EP0052675B1 - Système et méthode de mise à feu d'une roquette - Google Patents

Système et méthode de mise à feu d'une roquette 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
German (de)
English (en)
Other versions
EP0052675A1 (fr
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/fr
Publication of EP0052675A1 publication Critical patent/EP0052675A1/fr
Application granted granted Critical
Publication of EP0052675B1 publication Critical patent/EP0052675B1/fr
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.

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  • 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. Système de mise à feu d'une fusée, possédant un noyau magnétique (D) et une bobine d'attaque (A) montée coaxialement à celui-ci pour induire une tension de mise à feu dans une bobine (C) incorporée dans un circuit de mise à feu porté par la fusée et qui est amenée en état de couplage inductif avec le noyau, caractérisé en ce que des moyens sont prévus pour effectuer un contrôle avant la mise à feu, ces moyens comprenant une bobine capteur (B1, B2) couplée par induction avec le noyau et la bobine d'attaque (A) et un dispositif de détection connecté à la bobine capteur (B1, B2) pour déterminer la présence et l'état de la bobine incorporée dans le circuit de mise à feu porté par la fusée.
2. Système selon la revendication 1, où la bobine capteur (B1, B2) est en deux parties disposées transversalement par rapport à la bobine d'attaque et à faible distance de celle-ci.
3. Système selon la revendication 1, où la bobine capteur (B1, B2) est en deux partics disposées coaxialement par rapport à la bobine d'attaque.
4. Système selon la revendication 2 ou 3, où les parties de la bobine capteur (B1, B2) sont montées dans un circuit en pont.
5. Système selon l'une quelconque des revendications 2 à 4, où les parties de la bobine capteur sont enroulées et disposées de manière que l'une d'elles coupe une plus grande portion du flux que l'autre lorsqu'une bobine (C) incorporée dans le circuit de mise à feu porté par une fusée est amenée en état de couplage inductif avec le noyau magnétique (D).
6. Système selon l'une quelconque des revendications 2 à 5, où un détecteur de seuil est connecté aux parties de la bobine capteur.
7. Système selon l'une quelconque des revendications précédentes, où la bobine d'attaque (A) est reliée à une source de courant alternatif et peut être alimentée à au moins deux niveaux de puissance.
8. Procédé de mise à feu d'une fusée portant un circuit de mise à feu par induction conçu pour être couplé magnétiquement à un système de mise à feu possédant un noyau magnétique (D) et une bobine d'attaque (A), caractérisé en ce que l'on amène d'abord le noyau magnétique (D) en état de couplage magnétique avec le circuit de mise à feu porté par la fusée, on applique ensuite une tension de signal à faible puissance à la bobine d'attaque (A), avec vérification de la présence et de l'état du circuit de mise à feu à l'aide d'un signal engendré dans une bobine capteur (B1, B2), puis on applique à la bobine d'attaque (A) une tension à puissance de travail pour induire une tension de mise à feu dans le circuit de mise à feu.
9. Procédé de mise à feu d'une fusée selon la revendication 8, où, avant que le noyau magnétique (D) soit amené en état de couplage magnétique avec le circuit de mise à feu, on ajuste le système de mise à feu en appliquant la tension de signal à faible puissance à la bobine d'attaque (A) et en déplaçant le noyau magnétique (D) jusqu'à ce que la tension induite dans la bobine capteur (Bi, 82) soit à un minimum, et on fixe ensuite le noyau magnétique (D) en place.
10. Procédé de mise à feu d'une fusée selon la revendication 8 ou 9, où la présence et l'état désiré du circuit de mise à feu créent un flux magnétique dissymétrique par rapport à la bobine capteur (Bi, B2).
EP80304163A 1979-07-06 1980-11-20 Système et méthode de mise à feu d'une roquette Expired EP0052675B1 (fr)

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 (fr) 1979-07-06 1980-11-20 Système et méthode de mise à feu d'une roquette

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 (fr) 1979-07-06 1980-11-20 Système et méthode de mise à feu d'une roquette

Publications (2)

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

Family

ID=26079968

Family Applications (1)

Application Number Title Priority Date Filing Date
EP80304163A Expired EP0052675B1 (fr) 1979-07-06 1980-11-20 Système et méthode de mise à feu d'une roquette

Country Status (2)

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

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 (fr) * 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 (fr) 1982-06-02
GB2055181A (en) 1981-02-25

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