US3122058A - Systems comprising a cluster of rockets carried by a launching machine - Google Patents

Systems comprising a cluster of rockets carried by a launching machine Download PDF

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Publication number
US3122058A
US3122058A US91822A US9182261A US3122058A US 3122058 A US3122058 A US 3122058A US 91822 A US91822 A US 91822A US 9182261 A US9182261 A US 9182261A US 3122058 A US3122058 A US 3122058A
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United States
Prior art keywords
rocket
rockets
support
igniting
terminals
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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 - Lifetime
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US91822A
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English (en)
Inventor
Wyser Giulio
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.)
Brevets Aero Mecaniques SA
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Brevets Aero Mecaniques SA
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Publication of US3122058A publication Critical patent/US3122058A/en
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Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/04—Rocket or torpedo launchers for rockets
    • F41F3/06—Rocket or torpedo launchers for rockets from aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D1/00—Dropping, ejecting, releasing or receiving articles, liquids, or the like, in flight
    • B64D1/02—Dropping, ejecting, or releasing articles
    • B64D1/04—Dropping, ejecting, or releasing articles the articles being explosive, e.g. bombs
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D1/00—Dropping, ejecting, releasing or receiving articles, liquids, or the like, in flight
    • B64D1/02—Dropping, ejecting, or releasing articles
    • B64D1/04—Dropping, ejecting, or releasing articles the articles being explosive, e.g. bombs
    • B64D1/06—Bomb releasing; Bomb doors
    • 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
    • F41A19/64—Electric firing mechanisms for automatic or burst-firing mode
    • F41A19/65—Electric firing mechanisms for automatic or burst-firing mode for giving ripple fire, i.e. using electric sequencer switches for timed multiple-charge launching, e.g. for rocket launchers

Definitions

  • the present invention relates to systems comprising a cluster of several rockets supported in series by a launching machine such as an aircraft, the term supported in series meaning that every rocket is supported by another rocket to be fired immediately after it, with the exception of the last rocket to be fired, which is supported directly by the launching machine.
  • the object of this invention is to provide a system of this kind which is better adapted to meet the requirements of practice than those known up to this time, in particular to control of the firing of successive rockets.
  • every rocket comprises on the one hand means forming, when the rockets are secured to one another, a continuous electric line extending through the series of rockets, from each of them to the next one and, on the other hand, an electric igniting device carried by each of the rockets and comprising an input terminal, means being provided for connecting this electric line with the input terminal of the igniting device of the first rocket to be launched, but keeping the respective input terminals of the igniting devices of the other rockets disconnected from said line.
  • each of these igniting devices is arranged in such manner as to require, in order to cause its rocket to be fired, at least two predetermined successive variations of the voltage at its input terminal, control means being provided for producing said voltage variations through said electric line.
  • FIG. 2 diagrammatically shows the three rockets and the electric ignition system according to a first embodiment of the invention.
  • FIG. 3 shows the electric igniting device of a rocket which is not suspended to another rocket.
  • FIGS. 4 and 5 are views similar to FIGS. 2 and 3 respectively but illustrating another embodiment of the invention.
  • the invention is concerned with a system of rockets suspended under the wing 1 of an aircraft.
  • the systems according to the invention comprise the following ele ments:
  • the above mentioned means may be of any suitable structure.
  • each of the rockets comprises a body 2, the rear portion 2a of which contains the nozzle through which escape the combustion gases of the propelling charge of the rocket.
  • Every rocket comprises, as shown by FIG. 1, a sliding tail unit 3 through which said rocket is suspended to the corresponding tail unit of the rocket located immediately above it, or, for the last rocket -I, to a support 4 rigidly carried by wing 1.
  • This tail unit 3 occupies, be fore the rocket is launched, a forward position where it acts both as a guide and as a support for the rocket body, the tail unit being carried along by said rocket body just when it is being launched and being then wedged against a frusto-conical bearing 212 provided near the rear end of body 2, where it remains during the flight of the rocket.
  • Each of the rockets, and also support 4 is provided with a pivotable flap 5 dimensioned and positioned in such manner that the flap 5 of a supporting rocket II, when it occupies its vertical downward position, extends across the propelling jet of the supported rocket III when it is fired, so as to be pushed back and retracted by this jet.
  • the flap 5 carried by support 4 in turn extends across the jet of the top rocket I of the cluster when this rocket I is fired.
  • Holding means of a known type are provided to permit the launching of a rocket only when the flap 5 extending behind its nozzle has been pushed back and retracted by the jet starting from this nozzle.
  • the aircraft carries a source of current 6 adapted to be connected through a contact 7 with a line 8 connected to the flap 5 carried by support 4.
  • Every flap 5 when it occupies its vertical downward position behind the nozzle of a rocket, acts, in this rocket, upon a switch 9 which extends to the flap 5 of said rocket the electric line starting from element 8 flap 5 and extending through the rockets located above the one that is being considered.
  • this electric line extends as far as the flap 5 of the first rocket to be launched, which flap is arranged in such manner that, due to the fact that it has been retracted by the launching of the preceding rocket, it connects, in said first rocket to be launched, said electric line with the terminal 10 of the electric igniting device of this rocket.
  • Each of the flaps 5 will act in the same manner when it is retracted by the launching of the preceding rocket.
  • every switch is arranged in such manner that, when it is not depressed by a flap 5 (that is to say before the rocket is supported by another rocket, or by support 4) it short-circuits, as shown by FIGS. 3 and 5, the terminals of primer 15, so that this primer cannot be excited.
  • the arrangement for this purpose is visible in FIGS. 3 and 5.
  • each of the ignit ing devices of the respective rockets is arranged in such manner as to require, in order to cause its rocket to be fired, at least two predetermined successive variations of the voltage at its input terminal, control means being provided for producing said voltage variations through said electric line.
  • the first rocket to be launched is merely prepared for launching whereas its launching only takes place when the second voltage variation is produced.
  • next rocket which has not been prepared cannot be fired even if the current which has produced the launching of the first rocket, is maintained. To launch this second rocket, it is therefore necessary to produce once more the two successive voltage variations that are required.
  • the first voltage variation is produced by feeding current from the electric source to the igniting device input terminal through the line, this feed of current constituting the preliminary operation which places the igniting device of the rocket into a state such that the subsequent voltage variation causes the passage through the primer of said device of a current sutficient to cause its operation.
  • the preliminary operation consists in supplying current to the primary winding of an electric transformer, the next operation, i.e. the igniting operation proper consisting in cutting off this current so as to produce in the secondary winding of the transformer a current sufificient to operate the primer.
  • terminal is connected through a conductor 11 to one end of the primary winding 12 of a transformer, the other end of this primary winding being grounded through a conductor 13, i.e. being connected to the metallic mass formed by the rocket bodies and the metal frame of the aircraft.
  • One of the ends of the secondary winding of said transformer is also grounded, whereas the other end of this secondary winding is connected to one of the terminals of primer 15, the other of these terminals being themselves grounded.
  • the preliminary operation consists in charging a capacitor and the ignition proper is achieved by discharging this capacitor through the primer.
  • terminal 10 is connected through a conductor 16, with the interposition of a rectifier 1'7 (for instance of the type making use of a semiconductor such as germanium or silicon), to one of the plates 18 of a capacitor the other plate 19 of which is grounded through a conductor 20, rectifier 17 being disposed to prevent the fiow of current from plate 18 toward terminal 10.
  • a rectifier 1'7 for instance of the type making use of a semiconductor such as germanium or silicon
  • Plate 18 is connected through conductor 21 to one of the terminals of primer 15, the other terminal of this primer being connected to terminal 10 through a conductor 22 in which is inserted a second rectifier 23 arranged to prevent the flow of current from terminal 10 toward primer 15.
  • the switch interposed between line 8 and contact 7 is arranged in such manner as to permit of connecting said line either with contact 7 and therefore source 6, or with a grounded contact 24.
  • the preliminary operation which consists in connecting line 8 with source 6, causes capacitor 18, 19 to be charged, whereas the second operation connecting line 8 with contact 24 causes this capacitor to be discharged.
  • the switch intended to cooperate either with contact 7 (FIGS. 2 and 3) or alternately with this contact 7 and with grounding contact 24 (FIGS. 4 and 5) may be ctuated in a suitable manner, either manually or automatically, so as to permit either to launch the rockets at any designed time intervals, or by bursts and generally in any suitable manner.
  • a launching support at least two rockets, a first one and a second one, holding means carried by said support for detachably securing said second rocket to said support, holding means carried by said second rocket for detachably securing thereto said first rocket, an electric igniting device carried by each of said rockets, each of said igniting devices having two terminals, a first one and a second one, a source of electric current carried by said support, said source having two terminals, the second terminals of said igniting devices being electrically connected with one of said source terminals, means carried by said rockets, when they are assembled together, forming an electric line extending from said support and leading to the first terminal of the first rocket igniting device, said line being unconnected with the first terminal of the second rocket igniting device as long as said first rocket is secured to said second rocket, means carried by said second rocket for connecting the first terminal of the igniting device thereof to said electric line when said first rocket is detached from said second rocket, each of said electric igniting
  • each of said igniting devices comprises a transformer having its secondary winding connected in series with said primer and its primary winding connected at one end with the first terminal of said igniting device and at its other end with the second terminal of said igniting device, said switch means being adapted to cut off said line from said source so as thus to produce the second voltage variation across the terminals of the igniting device.
  • each of said igniting devices comprises a transformer having a primary winding and a secondary winding, said secondary winding and said primer being in series with each other, the whole of these two last mentioned elements being connected with the second terminal of said igniting device, and said primary winding being inserted in series between the two respective terminals of said igniting device, said switch means being adapted to cut off said line from said source so as thus to produce the second voltage variation across the terminals of the igniting device.
  • each of said igniting devices comprises a capacitor, means responsive to the feed of current from said source to the first terminal of said igniting device for charging said capacitor, and means responsive to the grounding of said line for discharging said capacitor through said primer, this combination comprising a grounded contact on said support, said switch means being adapted to connect said line with said grounded contact.
  • each of said igniting devices comprises a capacitor having two plates, unidirectional conducting means leading from the iirst terminal of said igniting device to one of the plates of said capacitor, the other plate of said capacitor being connected with the second terminal of said igniting device, an electric primer connected in shunt with said unidirectional conducting means, and rectifier means in series with said primer arranged to prevent the flow of current through said primer from said igniting device first terminal to said capacitor first plate, this combination comprising a grounded contact on said support, said switch means being adapted to connect said line with said grounded contact.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Automotive Seat Belt Assembly (AREA)
  • Transmission Devices (AREA)
US91822A 1960-03-07 1961-02-27 Systems comprising a cluster of rockets carried by a launching machine Expired - Lifetime US3122058A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
LU38347 1960-03-07

Publications (1)

Publication Number Publication Date
US3122058A true US3122058A (en) 1964-02-25

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Country Status (6)

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US (1) US3122058A (en, 2012)
CH (1) CH368059A (en, 2012)
DE (1) DE1175115B (en, 2012)
ES (1) ES265329A1 (en, 2012)
GB (1) GB938739A (en, 2012)
LU (1) LU38347A1 (en, 2012)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3316451A (en) * 1964-12-07 1967-04-25 Robert L Silberman Intervalometer
US3670180A (en) * 1969-11-19 1972-06-13 Concord Control Inc Intervalometer
US4135455A (en) * 1977-02-03 1979-01-23 Tracor, Inc. Multiple payload cartridge employing single pair of electrical connections
FR2660749A1 (fr) * 1990-04-05 1991-10-11 Lacroix E Tous Artifices Systeme de declenchement sequentiel controle et automatique d'une pluralite de charges utiles pyrotechniques.
CN114180111A (zh) * 2021-10-30 2022-03-15 航天科工火箭技术有限公司 一种适应可重复使用火箭垂直回收后处理的供气系统设计

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2234335B (en) * 1980-07-07 1991-06-26 Marconi Co Ltd Systems for firing propellant charges

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1441451A (en) * 1923-01-09 Altes w
US2059243A (en) * 1934-07-25 1936-11-03 Harry E Kennedy Ignition system for internal combustion engines
US2125035A (en) * 1935-10-18 1938-07-26 Smits Wytze Beye Electric ignition system and sparking plug for internal combustion engines
US2275052A (en) * 1939-10-07 1942-03-03 Hasler A G Werke Fur Telephoni Magneto
US2297006A (en) * 1941-03-07 1942-09-29 Lane Wells Co Gun perforator firing system
FR1211583A (fr) * 1957-08-27 1960-03-17 Brevets Aero Mecaniques Perfectionnements apportés aux roquettes devant pouvoir être suspendues par grappes à un engin de lancement, notamment à un aérodyne
FR1221969A (fr) * 1958-02-20 1960-06-07 Brevets Aero Mecaniques Perfectionnements apportés aux roquettes devant pouvoir être suspendues par chaîne à un engin de lancement, notamment à un aérodyne

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL190260A (en, 2012) 1953-08-31
DE1056970B (de) 1958-04-05 1959-05-06 Diehl Fa Elektrischer Zuender
NL252349A (en, 2012) 1959-06-12

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1441451A (en) * 1923-01-09 Altes w
US2059243A (en) * 1934-07-25 1936-11-03 Harry E Kennedy Ignition system for internal combustion engines
US2125035A (en) * 1935-10-18 1938-07-26 Smits Wytze Beye Electric ignition system and sparking plug for internal combustion engines
US2275052A (en) * 1939-10-07 1942-03-03 Hasler A G Werke Fur Telephoni Magneto
US2297006A (en) * 1941-03-07 1942-09-29 Lane Wells Co Gun perforator firing system
FR1211583A (fr) * 1957-08-27 1960-03-17 Brevets Aero Mecaniques Perfectionnements apportés aux roquettes devant pouvoir être suspendues par grappes à un engin de lancement, notamment à un aérodyne
US2968222A (en) * 1957-08-27 1961-01-17 Brevets Aero Mecaniques Rockets carried in clusters by a launching machine and in particular by an aircraft
FR1221969A (fr) * 1958-02-20 1960-06-07 Brevets Aero Mecaniques Perfectionnements apportés aux roquettes devant pouvoir être suspendues par chaîne à un engin de lancement, notamment à un aérodyne

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3316451A (en) * 1964-12-07 1967-04-25 Robert L Silberman Intervalometer
US3670180A (en) * 1969-11-19 1972-06-13 Concord Control Inc Intervalometer
US4135455A (en) * 1977-02-03 1979-01-23 Tracor, Inc. Multiple payload cartridge employing single pair of electrical connections
FR2660749A1 (fr) * 1990-04-05 1991-10-11 Lacroix E Tous Artifices Systeme de declenchement sequentiel controle et automatique d'une pluralite de charges utiles pyrotechniques.
CN114180111A (zh) * 2021-10-30 2022-03-15 航天科工火箭技术有限公司 一种适应可重复使用火箭垂直回收后处理的供气系统设计

Also Published As

Publication number Publication date
ES265329A1 (es) 1961-08-16
GB938739A (en) 1963-10-02
CH368059A (fr) 1963-03-15
LU38347A1 (en, 2012)
DE1175115B (de) 1964-07-30

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