EP0349375A1 - Elektrischer Zünder für Flugkörper - Google Patents

Elektrischer Zünder für Flugkörper Download PDF

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Publication number
EP0349375A1
EP0349375A1 EP89401706A EP89401706A EP0349375A1 EP 0349375 A1 EP0349375 A1 EP 0349375A1 EP 89401706 A EP89401706 A EP 89401706A EP 89401706 A EP89401706 A EP 89401706A EP 0349375 A1 EP0349375 A1 EP 0349375A1
Authority
EP
European Patent Office
Prior art keywords
detonator
rocket
electric rocket
firing
priming
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.)
Withdrawn
Application number
EP89401706A
Other languages
English (en)
French (fr)
Inventor
André Winaver
Jean Boucard
Yves De Gouville
Henri Tron
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.)
Thomson Brandt Armements SA
Original Assignee
Thomson Brandt Armements SA
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 Thomson Brandt Armements SA filed Critical Thomson Brandt Armements SA
Publication of EP0349375A1 publication Critical patent/EP0349375A1/de
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C15/00—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges
    • F42C15/28—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges operated by flow of fluent material, e.g. shot, fluids
    • F42C15/295—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges operated by flow of fluent material, e.g. shot, fluids operated by a turbine or a propeller; Mounting means therefor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C19/00—Details of fuzes
    • F42C19/08—Primers; Detonators
    • F42C19/09—Primers or detonators containing a hollow charge

Definitions

  • the present invention relates to rockets for flying machines, in particular ground-to-ground or air-to-ground ammunition; more precisely, it relates to an electric rocket comprising power, armament, security, firing and priming elements, the constitution, positioning and operation of which make it possible to improve manufacturing, control, operational safety and security.
  • An electric rocket for flying machines such as an aviation bomb or a mortar projectile, has the function of arming the projectile within a predetermined period following the moment of release, then of generating a firing order at near or in contact with the target object.
  • Conventional rockets have different parts, generally six in number, namely: the rocket support, the power supply, the safety and arming device, the firing order generator, the firing device fire and the priming chain. These rockets require safety precautions. Indeed, the conventional use of a sensitive primary pyrotechnic charge in the priming chain, in particular at the level of the detonator, implies a sensitivity of the rocket to the effects of shocks, vibrations, thermal variations, radioelectric and ionizing radiation.
  • This sensitivity is present in all phases of use of the rocket; for example, during the manufacture of the rocket, one is obliged to take certain precautions, in particular with regard to the assembly and the controls of the elements of the priming chain, which constrain the mass production of this rocket .
  • the use of a sensitive primary pyrotechnic charge in a priming chain obliges the manufacturer to determine and carry out an architecture of the rocket comprising elements of protection reinforced against accidental environments such as, for example, fire in the hold or the shock resulting from "double feeding". These reinforced protections seem difficult to develop, and increase the cost of the rocket.
  • the main object of the invention is to use a priming chain without a sensitive primary pyrotechnic composition eliminating the difficulties mentioned above.
  • the object of the invention is an electric rocket characterized in that it comprises a support inside which is disposed a firing order generator connected to firing means triggering a priming chain comprising only secondary pyrotechnic compositions and the detonator of which is with a sprayed layer; the generator and the ignition means being supplied and made active by supply means controlled by security and arming means.
  • the electric rocket 1 is made up of different modules:
  • a support 1 represented by hatched lines; this support 1 is composed of several parts among which there are sealing means 2 protecting the priming chain, consisting of elements 3, 4 and 5, against the effects of a possible double supply and a cover 6 of the reinforcing relay 5 which protects the priming chain for the same reasons as those mentioned above. Priming of the reinforcing relay 5 through the cover 6 is possible thanks, for example, to the particular architecture, for example, in the form of a hollow charge, of the bottom of the detonator 4.
  • the supply means 7 is a regulated supply of the proximetric firing order generator 10
  • the supply means 9 is a low voltage / high voltage conversion device for the ignition means.
  • the supply means 7 is a turbo-alternator making it possible to test, by its operation, one of the arming conditions; this turbo-alternator 7 is provided with a turbine 16 which is driven by the admitted air current, after the rocket's hair has been disheveled, in an axial channel 17 thereof.
  • the supply means have been arranged so that, before complete arming, there is no potential energy on board the rocket capable of supplying the firing means composed of the elements 11, 12, 13 and 15 which will be described later and that the supply of the firing means is only possible by the security and arming means 18, 19, 20, 21 and 22 and this, due to a full and normal implementation of the ammunition.
  • the rocket includes a firing order generator 10; this generator can be, for example, a grazing impact detector, a proximeter, a chronometer, a magnetometer.
  • a firing order generator 10 this generator can be, for example, a grazing impact detector, a proximeter, a chronometer, a magnetometer.
  • the list of different generators that can be used to serve as a firing order generator is not exhaustive. Indeed, it may be, for the needs of the cause, that it is necessary to make combinations of different generators to obtain a firing order generator with desired characteristics.
  • the firing means constituting an important module of the rocket, they consist of a normalizer 11 which receives the order emitted by the firing generator 10, of a discharge switch 12 firing energy charged in the tank capacity 13; this switch 12 can be, for example, with a pyrotechnic motor by acting by piercing the solid dielectric separating from the main electrodes of the discharge circuit, the choice of switch 12 being a function of the operating time relative to the ignition generator 10 used.
  • the tank capacity 13 installed, for example, flat inside the rocket is an element making up the firing charge; it is the same for the selector switch 14 which defines the operating mode of the rocket; this switching selector 14 makes it possible to take, for example, two different options: - either the "proximity” option - either the "impact” option.
  • modules 12 and 15 are not both used.
  • the effect of the discharge switch 12 is replaced by the axis 15 of the turbo-generator 7, this axis being in connection with the turbine 16 of the turbo-alternator 7.
  • the firing means must also be adapted to the detonator represented by elements 3 and 4 and described later, in particular, as regards the power required by the excitation of the detonator.
  • the priming chain comprises a detonator represented by elements 3 and 4; this detonator (3 and 4), comprising sensitive primary pyrotechnic charges, in the conventional case, is, in our case, composed of exclusively secondary pyrotechnic charges to improve and simplify, by avoiding any misalignment of the priming chain, the systems security developed for the cause; these secondary pyrotechnic charges are typically the explosive charges permitted by the list cited in the Military Standard 1316 C of 3/1/1984, paragraphs 431 et seq.
  • the detonator 3 and 4 is, for example, a projected layer detonator.
  • this detonator 3 and 4 has been defined to make it possible to strengthen immunity to the effect of the double supply, this is why, sealing means 2 and a cover 6 have been so arranged in this rocket.
  • the shape of the detonator 3 and 4 has been produced so that the bottom of the detonator 4 has a particular architecture, for example, in the form of a hollow charge, allowing the priming of the next element of the priming chain, namely the reinforcing relay 5, through the cover 6.
  • the reinforcing relay 5 transmits the detonation, for example, at the charge of a projectile the internal structure of this charge is independent of the previously established choices, it can be, for example , explosive or incendiary.
  • this module The role of this module is, on the other hand, to arm the rocket by removing security, that is to say say by putting the firing means into operation thanks to its power supply; to achieve this, use is made, for example, of an operating controller 20, which, by means of a gear 21, is in relation to the axis 15 of the turbo-alternator 7 allowing, when the relays 22 establish the connection electric 24 between the low-voltage-high-voltage converter 9 and the turbo-alternator 7, the supply of the ignition means.
  • the accelerometer 19 is implemented, for example, by a transverse latch 18 which tests the suppression storage security, that is to say the rocket's disheveling.
  • the rocket is equipped with a cap preventing the various modules from starting up.
  • the cap of the rocket is removed which allows, firstly, the free circulation of air inside the rocket causing, when the rocket is animated with a movement, the setting in operation of the turbo-alternator 7 via the turbine 16 and which, in a second step, allows the operation of the accelerometer 19 thanks to the transverse latch 18 which releases it.
  • the turbine 16 of the turbo-alternator allows, on the one hand, to store energy inside the reservoir capacity 13 and, on the other hand, via the axis 15, it causes a gear 21 which transmits to the element 20 a downward translational movement, forcing the relay 22 to come into contact with the element 25 and this, provided that all the phases of launch and flight have gone well.
  • the accelerometer 19 tests the axial acceleration in space 23 until a desired value is obtained.
  • the other relay 22 comes to bear on the element 26 and the electrical connection 24, between the turbo-generator 7 and the converter 9 Low-voltage-High-voltage, is produced.
  • One manipulation, not to be forgotten before the use phase, is the positioning of the switching selector 14 which determines the operating mode of the rocket.
  • either element 12 or element 15 is used to activate the ignition energy located in the reservoir capacity 13; this energy triggers the detonator 3 and 4 which, thanks to a particular architecture, initiates a reinforcing relay 5 which transmits the detonation to the charge in presence.
  • a rocket according to the invention, is suitable for mortar projectiles launched by smooth or striped tubes and it is also possible to use this type of rocket while continuing not to use primary pyrotechnic composition, for example, in the lighting of projectiles.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Feeding, Discharge, Calcimining, Fusing, And Gas-Generation Devices (AREA)
EP89401706A 1988-06-28 1989-06-16 Elektrischer Zünder für Flugkörper Withdrawn EP0349375A1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8808645 1988-06-28
FR8808645A FR2633384A1 (fr) 1988-06-28 1988-06-28 Fusee electrique pour engins volants

Publications (1)

Publication Number Publication Date
EP0349375A1 true EP0349375A1 (de) 1990-01-03

Family

ID=9367787

Family Applications (1)

Application Number Title Priority Date Filing Date
EP89401706A Withdrawn EP0349375A1 (de) 1988-06-28 1989-06-16 Elektrischer Zünder für Flugkörper

Country Status (2)

Country Link
EP (1) EP0349375A1 (de)
FR (1) FR2633384A1 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2000031497A1 (de) * 1998-11-26 2000-06-02 Junghans Feinwerktechnik Gmbh & Co. Kg Mörserzünder mit einem windrad
FR2926631A1 (fr) * 2008-01-18 2009-07-24 Livbag Soc Par Actions Simplif Allumeur electro-pyrotechnique perforant et generateur en faisant usage

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2627160A (en) * 1947-04-01 1953-02-03 Macdonald Gilmour Craig Rocket igniter
US2764092A (en) * 1946-03-08 1956-09-25 Mark F Massey Impact fuze for projectiles
US3045524A (en) * 1958-06-23 1962-07-24 Richard H F Stresau Booster cup and method of making same
AU417767B2 (en) * 1966-09-12 1971-10-10 Lockheed Aircraft Corporation Exploding bridge wire initiator
FR2114099A5 (de) * 1970-11-16 1972-06-30 France Etat
FR2219705A5 (de) * 1973-02-28 1974-09-20 Kongsberg Vapenfab As
US4027593A (en) * 1976-02-12 1977-06-07 The United States Of America As Represented By The Secretary Of The Army Multi-directional system for electrical bomb fuzes
US4034674A (en) * 1975-12-24 1977-07-12 Motorola, Inc. Compact electrical fuze

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2764092A (en) * 1946-03-08 1956-09-25 Mark F Massey Impact fuze for projectiles
US2627160A (en) * 1947-04-01 1953-02-03 Macdonald Gilmour Craig Rocket igniter
US3045524A (en) * 1958-06-23 1962-07-24 Richard H F Stresau Booster cup and method of making same
AU417767B2 (en) * 1966-09-12 1971-10-10 Lockheed Aircraft Corporation Exploding bridge wire initiator
FR2114099A5 (de) * 1970-11-16 1972-06-30 France Etat
FR2219705A5 (de) * 1973-02-28 1974-09-20 Kongsberg Vapenfab As
US4034674A (en) * 1975-12-24 1977-07-12 Motorola, Inc. Compact electrical fuze
US4027593A (en) * 1976-02-12 1977-06-07 The United States Of America As Represented By The Secretary Of The Army Multi-directional system for electrical bomb fuzes

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2000031497A1 (de) * 1998-11-26 2000-06-02 Junghans Feinwerktechnik Gmbh & Co. Kg Mörserzünder mit einem windrad
US6481354B1 (en) 1998-11-26 2002-11-19 Junghan Feinwektechnik Gmbh & Co. Kg Mortar fuse with a rotatable fan
FR2926631A1 (fr) * 2008-01-18 2009-07-24 Livbag Soc Par Actions Simplif Allumeur electro-pyrotechnique perforant et generateur en faisant usage

Also Published As

Publication number Publication date
FR2633384A1 (fr) 1989-12-29

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