EP0052675B1 - A rocket firing system and a method of firing a rocket - Google Patents

A rocket firing system and a method of firing a rocket 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)
French (fr)
Other versions
EP0052675A1 (en
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 EP80304163A priority patent/EP0052675B1/en
Priority to DE8080304163T priority patent/DE3070627D1/en
Priority to AT80304163T priority patent/ATE13224T1/en
Publication of EP0052675A1 publication Critical patent/EP0052675A1/en
Application granted granted Critical
Publication of EP0052675B1 publication Critical patent/EP0052675B1/en
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.

Description

  • 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.
  • It is already known to fire rockets and other pyrotechnic devices by electrical means, in particular using an inductive linkage, see for example GB-A-1235844 which corresponds to the preambles of claims 1 and 8 of the present application. However, a complete system for firing rockets should preferably also enable a pre-firing check upon the presence of the rocket, and upon the effectiveness of the firing circuit of the rocket itself. Effective system embodying these features have not previously been known.
  • Accordingly, 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. Preferably, 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.
  • Further, 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.
  • In order that the invention shall be clearly understood an exemplary embodiment thereof will now be described with reference to the drawings in which:-
    • Figure 1 shows the physical disposition of the components of the firing system according to the invention; and
    • Figure 2 shows the electrical connections of the firing system.
  • 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. Mounted in close physical proximity to the coil A is a sensor coil B which is divided into two part 8, and B2. 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. In use, 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.
  • When a rocket is introduced into the launcher, with the signal power voltage applied to the coil A a signal current, well below the safety level of the firing circuit, will flow in coil C. This will result in a major distortion of the magnetic field of coil A and core D. The coil B will detect this change from the normal and the resultant voltage detected by the detection device will indicate the presence of a rocket, and the satisfactory state of the firing circuit on the rocket.
  • If the rocket is present, but the firing circuit is open-circuited, then no current will flow in the coil C and there will be only minor distortion of the magnetic field when the signal power voltage is applied to coil A.
  • In the preferred form shown, the coil parts 8, and 82 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.
  • In another preferred form 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.

Claims (10)

1. A rocket firing system comprising a magnetic core (D) and a driver coil (A) mounted co-axial therewith for inducing a firing voltage in a rocket firing circuit coil (C) 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 (Bi, 82) inductively linked with the core and driver coil (A) and a detector device connected to the sensor coil (Bi, 82) to determine the presence and state of a said rocket firing circuit coil.
2. A system according to claim 1, wherein the sensor coil (B1, B2) is in two parts lying transversely of and closely adjacent the driver coil.
3. A system according to claim 1, wherein the sensor coil (B1, B2) is in two parts each of which is co-axial with the driver coil.
4. A system according to claim 2 or 3, wherein the sensor coil (Bi, 82) parts are connected in a bridge circuit.
5. A system according to any of claims 2 to 4 wherein the sensor coil parts are wound and positioned so that, when a said rocket firing circuit coil is brought into inductive linkage with the magnetic core (D), one coil part cuts more flux than the other coil part.
6. A system according to any of claims 2 to 5 wherein a theshold detector is connected to said sensor coil parts.
7. A system according to any preceding claim wherein the driver coil (A) is connected to an alternating current supply and is switchable to at least two power levels.
8. A method of firing a rocket having an inductive firing circuit adapted to be magnetically linked by a firing system having a magnetic core (D) and a driver coil (A), the method being characterised in that first the magnetic core (D) is brought to link magnetically with the firing circuit, then a low-power signal voltage is applied to the driver coil (A), the presence and state of the firing circuit being monitored by a signal generated in a sensor coil (Bi, 82), and thereafter an operating power voltage is applied to the driver coil (A) so as to induce a firing voltage in the firing circuit.
9. A method of firing a rocket according to claim 8 wherein, before the magnetic core (D) is brought to link magnetically with the firing circuit, the firing system is set up by applying said low-power signal voltage to the driver coil (A) and moving the magnetic core (D) until the voltage induced in the sensor coil (Bi, 82) is at a minimum, the magnetic core (D) then being fixed in position.
10. A method of firing a rocket according to claim 8 or claim 9 wherein the presence and desired state of the firing circuit cause an asymmetrical flux pattern relative to the sensor coil (B1, B2).
EP80304163A 1979-07-06 1980-11-20 A rocket firing system and a method of firing a rocket Expired EP0052675B1 (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
GB7923707A GB2055181B (en) 1979-07-06 1979-07-06 Rocket firing system
EP80304163A EP0052675B1 (en) 1979-07-06 1980-11-20 A rocket firing system and a method of firing a rocket
DE8080304163T DE3070627D1 (en) 1980-11-20 1980-11-20 A rocket firing system and a method of firing a rocket
AT80304163T ATE13224T1 (en) 1980-11-20 1980-11-20 APPARATUS AND PROCEDURES FOR FIRING MISSILES.

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 (en) 1979-07-06 1980-11-20 A rocket firing system and a method of firing a rocket

Publications (2)

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

Family

ID=26079968

Family Applications (1)

Application Number Title Priority Date Filing Date
EP80304163A Expired EP0052675B1 (en) 1979-07-06 1980-11-20 A rocket firing system and a method of firing a rocket

Country Status (2)

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

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 (en) * 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
EP0052675A1 (en) 1982-06-02
GB2055181B (en) 1982-11-24
GB2055181A (en) 1981-02-25

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