EP0052675A1 - Einrichtung und Verfahren zur Abfeuerung von Raketen - Google Patents

Einrichtung und Verfahren zur Abfeuerung von Raketen Download PDF

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Publication number
EP0052675A1
EP0052675A1 EP80304163A EP80304163A EP0052675A1 EP 0052675 A1 EP0052675 A1 EP 0052675A1 EP 80304163 A EP80304163 A EP 80304163A EP 80304163 A EP80304163 A EP 80304163A EP 0052675 A1 EP0052675 A1 EP 0052675A1
Authority
EP
European Patent Office
Prior art keywords
coil
firing
core
rocket
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.)
Granted
Application number
EP80304163A
Other languages
English (en)
French (fr)
Other versions
EP0052675B1 (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 core and a driver coil mounted co-axial therewith, a sensor coil inductively linked with the core and driver coil, and a detector device connected to the sensor coil to determine the state of any further coil brought into inductive linkage with the core.
  • 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, a driver coil and a sensor 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 generated in the 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 parts B1 and B 2 .
  • 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 B 1 and B 2 are wound in position, and positioned so that one part will cut more flux than the other when the flux pattern becomes asymetrically 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)
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 true EP0052675A1 (de) 1982-06-02
EP0052675B1 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 (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
US3123002A (en) * 1964-03-03 Spool
FR2304053A1 (fr) * 1975-03-10 1976-10-08 Oerlikon Buehrle Ag Procede et installation pour regler la fusee detonatrice apres le depart de l'obus tire par un canon
US4142442A (en) * 1971-12-08 1979-03-06 Avco Corporation Digital fuze

Family Cites Families (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

Patent Citations (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
FR2304053A1 (fr) * 1975-03-10 1976-10-08 Oerlikon Buehrle Ag Procede et installation pour regler la fusee detonatrice apres le depart de l'obus tire par un canon

Also Published As

Publication number Publication date
GB2055181B (en) 1982-11-24
EP0052675B1 (de) 1985-05-08
GB2055181A (en) 1981-02-25

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