US2824496A - Electric control system for singly and sequentially firing ballistic missiles - Google Patents

Electric control system for singly and sequentially firing ballistic missiles Download PDF

Info

Publication number
US2824496A
US2824496A US520304A US52030455A US2824496A US 2824496 A US2824496 A US 2824496A US 520304 A US520304 A US 520304A US 52030455 A US52030455 A US 52030455A US 2824496 A US2824496 A US 2824496A
Authority
US
United States
Prior art keywords
rocket
missile
contacts
rockets
firing
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 - Lifetime
Application number
US520304A
Other languages
English (en)
Inventor
Kuller Nils-Erik Gustaf
Thorildsson Karl-John Thorild
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.)
Saab Bofors AB
Original Assignee
Bofors AB
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 Bofors AB filed Critical Bofors AB
Application granted granted Critical
Publication of US2824496A publication Critical patent/US2824496A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C19/00—Details of fuzes
    • F42C19/06—Electric contact parts specially adapted for use with electric fuzes
    • 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
    • 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
    • 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
    • F41F3/0406—Rail launchers
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • F42B15/10—Missiles having a trajectory only in the air

Definitions

  • the present invention relates to an electric control system for singly and sequentially firing several ballistic missiles, and more particularly ballistic missiles such as airborne rockets or bombs which are mounted in clusters, but individually fired by activating a firing system which in turn ignites the propulsion charge of the missile.
  • Ballistic missiles of the kind herein referred to such as rockets are joined in clusters in which the individual rockets are stacked side by side, each rocket having its own firing system.
  • the clusters are suspended from an aircraft wing by fastening the uppermost rocket to the wing structure and the lower rockets to each other in a position such that the longitudinal axes of the rockets are at substantially a right angle to the longitudinal axis of the wing and substantially parallel to the axis of the fuselage.
  • the heretofore conventional arrangement of controlling the firing systems of the rockets is directly to connect the firing systems of all the rockets by individual cables to a central electrical control station including a source of current and suitably disposed within the fuselage.
  • the rockets are singly and sequentially fired by setting and operating the control station so that the firing system of the lowermost rocket only is activated.
  • one of the objects of the present invention is to provide a novel and improved electric control system of the general kind above referred to which permits individual firing of a plurality of missiles such as rockets without requiring separate cables leading directly to a common control station thereby eliminating the aforedescribed difiiculties and dangers inherent in the use of individual cables.
  • Another object of the invention is to provide a novel and improved electric control system in which the firing systems of all the rockets of a cluster are interconnected through the rocket bodies, but the firing system of the lowermost rocket only can be activated upon operation of the control station.
  • Still another object of the invention is to provide a novel and improved electric control system in which each firing system includes as component of the control system a safety member which is one position strongly locks the associated rocket to the next higher rocket and in another position lightly locks the said rockets together, said safety member being automatically moved into its position lightly locking the respective rockets when the rocket associated with it is rendered operative 2,824,496 Patented Feb. 25, 1958 ICC for actuation by the control station.
  • This arrangement affords the advantage of securing the rockets in position without interfering with the singly and sequentially firing of the same.
  • Fig. 1 is a fragmentary isometric sectional view of a cluster of rockets equipped with an electric control system according to the invention.
  • Fig. 2 is an isometric view of the cluster of rockets according to Fig. 1 shown suspended from the wing of an aircraft.
  • the cluster of rockets is shown as comprising two rockets, but it may contain initially more than two rockets.
  • the two rockets 1 and 2 comprise each a war head 3, an intermediate section 4 containing part of the electric control system according to the invention, a motor section 5 housing the propulsion charges, and a nozzle section 6 which includes four guide vanes or fins 7.
  • Each fin has a slot 8.
  • the slots of the upper two fins of each rocket are interlocked with the two lower fins of the next higher rocket of the cluster, and the two upper fins of the uppermost rocket of the cluster engage a bracket 10 suspended from the structure of wing 9.
  • the rear ends of all the rockets are joined so as to permit sliding forward movement of the rockets when the same are sequentially fired.
  • the forward end of the uppermost rocket is suspended from the wing structure by means of flanges 12 and 13 formed on a support 11 suitably secured to the wing. Flanges 12 and 13 are in slidable engagement with guide tracks 14 and 15. Each rocket has on its upper side such guide tracks 14 and 15 and on its lower side flanges 12 and 13'. As a result, each rocket can be joined to the next higher rocket or to the wing structure.
  • the coacting engaging and receiving coupling means thus provided on the rockets and the wing structure retain the entire cluster suspended from the wing. They also permit forward sliding of the rockets, but prevent rearward sliding of the rockets. It is of course possible and within the scope of the invention to vary the configuration of the coacting coupling means at the front and rear end of the rocket. It is only essential for the purpose of the invention that they permit and prevent respectively the aforesaid movements of the rockets relative to each other and to the wing structure.
  • the electric control system comprises a central control station 23 which is suitably disposed on the aircraft, generally within the fuselage for operation by a member of the crew.
  • the control station is diagrammatically shown as comprising a source of current 24 and an operating switch 25.
  • the control station is connected by wires 21 and 22 to contacts 19 and 20 insulated from each other and fitted with blank ends substantially flush in the side of support 11 facing and engaging the uppermost rocket 1.
  • Contacts 19 and 20 are in sliding engagement with contacts 26 and 27 fitted in the upper side of the rocket when rocket 1 is suspended from the wing structure.
  • Contact pairs 19, 20 and 26, 27 may be spring loaded so that reliable engagement is obtained between the coacting contacts.
  • Contacts 26 and 27 are connected to two contact arms 30 and 31 which are mounted insulated from each other in a body 32.
  • This body is fitted upon or constitutes part of a bar 33 which is axially displaceable in a bore extending through the body of the rocket-trans-' 3 versely of the'longitudinal axis thereof, or in other words transversely of the sliding direction of the rockets when the same are fired.
  • Contacts 34 and 35 are connected by wires 36 and 37 respectively to contacts 38 and 39. These contacts are similar to contacts 19 and 20 and are fitted in the body of the rocket, or more specifically in the part thereof forming coupling flanges 18 and 17. The blank ends of the contacts are substantially flush with the body of the rocket for engagement with contacts 26 and 27 fitted in the upper side of the next lower rocket and leading to contact arms 30 and 31 of the said rocket. V
  • the bar is urged downwardly by an upper loaded spring 46 into the position shown in Fig. l for the lower rocket 2, in which the lower tip of the bar protrudes from the bottom side of the body of rocket 2.
  • a lower spring 45 limits the downward movement of the bar.
  • the bar of each rocket coacts with the body of the next lower rocket so that it is held by the next lower rocket in its upper popition in which contact arms 30 and 31'engage contacts 34 and 35 leading to the respective contacts 38 and 39.
  • the bar of rocket 1 is shown in the upper position.
  • the upper end of the uppermost bar engages a recess 47 in support 11 and the upper end of each lower rocket engages a similar recess 48 in the bottom side of each lower rocket.
  • the tip of each bar is structurally weakened in relation to the remaining part of the bar, for instance by providing a slot 49.
  • the length of bar 33 is such that the strong or nonweakened part of the bar protrudes into the respective recess when the bar is in its upper position (rocket 1), and that the weakened tip only protrudes into-the respective recess when the bar is in its lower position (rocket 2), or in other words that the weakened part of the bar is situated between the bodies of an upper and a lower rocket or between the body of the uppermost rocket and the body of support 11.
  • bar 33 in addition to being a switching member constitutes a locking member which in its upper position firmly locks a rocket against a forward sliding movement relative to its support and in its lower position lightly locks each rocket against such sliding movement.
  • Rocket 1 now becomes the lowermost rocket and accordingly its bar 33 will move into the lower position V 4 thereby connecting contacts 40, 41 to connect the firing system 44 to control station 23.
  • any number of rockets may a be similarly suspended. Irrespective of the number of rockets in the cluster, the firing system of the lowermost rocket only is connected to the control station and the next higher rocket will be automatically armed when the lowermost rocket is fired.
  • circuit connections of the control system are all shown as wires it is evident that some of the circuit connections may be formed by the bodies of the rockets proper, provided the rocket bodies are made of electrical- 1y conductivematerial.
  • An electric control system for singly and sequentially firing ballistic missiles each having a firing system and joined in a cluster in side by side arrangement said control system comprising a switch means in each missile, each of said switch means including a pair of contacts and a switch member movable between a closed and open position relative to said pair of contacts and biased toward a closing position therewith, the said pair of contacts being connected in circuit with the respective firing system, a central control station including a source of current, control circuit means including said source of current, said pair of contacts in each missile and the switch member in each missile, the contact open position of the switch member of each missile to be fired later in the sequence being maintained by the presence of an adjacent missile to be fired previouslythereto, a part of each missile engaging with the said switch member of another missile to be sequentially fired next after the firing of said one missile holding said switch member in said open position, and the sequential firing of said one missile automatically releasing said switch member of said other missile to be next fired for movement by said bias into the position closing said pair of contacts connected with the respective firing system whereby upon
  • each missile engaging the switch members of other missiles are formed by the bodies of the missiles, the body of each missile retaining the switch member of the missile sequentially next posterior in the firing order in said open position relative to said pair of contacts in the control circuit, whereby the switch member in the missile next to be fired is released to be biased into said closed position with the contacts of the respective firing system.
  • each of said switch members is displaceably mounted in the respective missile and biased toward one position having one end protruding from the body of the missile, said one protruding position being the closed position of the switch member closing the contacts of the respective firing system, the body of the missile sequentially next anterior in the firing order retaining the switch member in said open position thereof against the action of the bias.
  • An installation for singly and sequentially firing airborneballastic missiles each having a firing system and suspended from the wing structure of an aircraft in form of a depending cluster, said installation comprising support means attachable to the wing structure for slidably supporting the uppermost missile, engaging and receiving coupling means on each missile, the coupling means of each two adjacent missiles slidably engaging each other for joining the missiles to form said depending cluster, a central control station including a source of current and adapted to be located in the aircraft, each missile including a switch means, each of said switch means comprising two pairs of contacts and a switch member movable between said two pairs of contacts and biased into a position closing one pair of said contacts, the said pair of contacts being connected in circuit with the firing system of the respective missle, each missile further having first two contact points located at the outside of the respective missile and connected with the contacts of the respective other pair of contacts and second two contact points located at the outside of the respective missile and connected with the switch member of the respective missile, third two contact points located at the outside of said support means and connected to
  • each of said switch members is biased into a position protruding from the respective missile on the side thereof facing the next lower missile, said position of the switch member being the position closing the contacts connected to the respective firing system, the body of each missile except the lowermost one retaining the switch member of the next higher missile in the position in which the switch member thereof closes the pair of contacts leading to the first two contact points of the respective missile,
  • each switch member is slidably guided within its missile transversely of the sliding direction thereof and comprises two contact arms insulated from each other, each of said contact arms being connected to one of the respective second contact points and engageable with one contact of either pair of contacts in the respective missile.

Landscapes

  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
US520304A 1954-07-09 1955-07-06 Electric control system for singly and sequentially firing ballistic missiles Expired - Lifetime US2824496A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SE335970X 1954-07-09

Publications (1)

Publication Number Publication Date
US2824496A true US2824496A (en) 1958-02-25

Family

ID=20308228

Family Applications (1)

Application Number Title Priority Date Filing Date
US520304A Expired - Lifetime US2824496A (en) 1954-07-09 1955-07-06 Electric control system for singly and sequentially firing ballistic missiles

Country Status (6)

Country Link
US (1) US2824496A (xx)
BE (2) BE539669A (xx)
CH (2) CH335971A (xx)
DE (1) DE1007635B (xx)
FR (2) FR1127307A (xx)
NL (4) NL198669A (xx)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2951421A (en) * 1958-01-28 1960-09-06 Gen Electric Frangible connector
US3026774A (en) * 1958-02-20 1962-03-27 Brevets Aero Mecaniques Firing devices for rockets carried in clusters by a launching machine, and in particular an aircraft
US3313207A (en) * 1965-04-02 1967-04-11 Arthur T Biehl Underwater weapon
US3415438A (en) * 1967-05-29 1968-12-10 United Shoe Machinery Corp Devices for preventing drop-fire
US4135455A (en) * 1977-02-03 1979-01-23 Tracor, Inc. Multiple payload cartridge employing single pair of electrical connections
US4736583A (en) * 1986-02-06 1988-04-12 Her Majesty The Queen In Right Of Canada As Represented By The Minister Of National Defence Rocket firing system for sequential firing of rocket motor groups
US5125319A (en) * 1990-04-03 1992-06-30 Dynamit Nobel Ag Transport safety system in a rocket launcher
US5263416A (en) * 1992-02-06 1993-11-23 Alliant Techsystems Inc. Primer propellant electrical ignition interconnect arrangement for single and multiple piece ammunition

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2458459A1 (fr) * 1979-06-07 1981-01-02 Thomson Brandt Dispositif d'accouplement mecanique et electrique pour charges, notamment militaires
SE8006725L (sv) * 1980-03-17 1981-09-18 Philips Svenska Ab Spridare
US8117955B2 (en) * 2006-10-26 2012-02-21 Lone Star Ip Holdings, Lp Weapon interface system and delivery platform employing the same

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2442766A (en) * 1945-03-08 1948-06-08 Bell Telephone Labor Inc Circuit controlling switch
US2591834A (en) * 1948-07-21 1952-04-08 Lockheed Aircraft Corp Retractable rocket launcher
US2706431A (en) * 1949-05-16 1955-04-19 Northrop Aircraft Inc Rocket jettison mechanism
US2788712A (en) * 1954-07-09 1957-04-16 Bofors Ab Locking arrangement for singly and sequentially releasing ballistic missiles

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2442766A (en) * 1945-03-08 1948-06-08 Bell Telephone Labor Inc Circuit controlling switch
US2591834A (en) * 1948-07-21 1952-04-08 Lockheed Aircraft Corp Retractable rocket launcher
US2706431A (en) * 1949-05-16 1955-04-19 Northrop Aircraft Inc Rocket jettison mechanism
US2788712A (en) * 1954-07-09 1957-04-16 Bofors Ab Locking arrangement for singly and sequentially releasing ballistic missiles

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2951421A (en) * 1958-01-28 1960-09-06 Gen Electric Frangible connector
US3026774A (en) * 1958-02-20 1962-03-27 Brevets Aero Mecaniques Firing devices for rockets carried in clusters by a launching machine, and in particular an aircraft
US3313207A (en) * 1965-04-02 1967-04-11 Arthur T Biehl Underwater weapon
US3415438A (en) * 1967-05-29 1968-12-10 United Shoe Machinery Corp Devices for preventing drop-fire
US4135455A (en) * 1977-02-03 1979-01-23 Tracor, Inc. Multiple payload cartridge employing single pair of electrical connections
US4736583A (en) * 1986-02-06 1988-04-12 Her Majesty The Queen In Right Of Canada As Represented By The Minister Of National Defence Rocket firing system for sequential firing of rocket motor groups
US5125319A (en) * 1990-04-03 1992-06-30 Dynamit Nobel Ag Transport safety system in a rocket launcher
US5263416A (en) * 1992-02-06 1993-11-23 Alliant Techsystems Inc. Primer propellant electrical ignition interconnect arrangement for single and multiple piece ammunition

Also Published As

Publication number Publication date
CH335970A (de) 1959-01-31
DE1007635B (de) 1957-05-02
NL198669A (xx)
NL89290C (xx)
FR1127307A (fr) 1956-12-13
BE539702A (xx)
NL89990C (xx)
BE539669A (xx)
CH335971A (de) 1959-01-31
FR1127662A (fr) 1956-12-21
NL198668A (xx)

Similar Documents

Publication Publication Date Title
US3451306A (en) Safe and arm ejection system
US2975676A (en) Missile launching systems for aircraft
US2824496A (en) Electric control system for singly and sequentially firing ballistic missiles
US3008376A (en) Launching device
US2755042A (en) Ejection seat catapult
US2930288A (en) Tandem rocket launcher and firing system
US3412640A (en) Rocket launcher
US3124072A (en) Missile propulsion
US3780616A (en) Set comprising an infantry weapon and its ammunition
US3575084A (en) Arming wire assembly
US2788712A (en) Locking arrangement for singly and sequentially releasing ballistic missiles
US4336740A (en) Automatic blast actuated positive release missile detent
US3158100A (en) Rocket propelled reconnaissance vehicle
US3504593A (en) Airborne rocket launcher
US4350074A (en) Mechanical and electrical coupling device for charges, particularly military charges
GB846246A (en) Improvements in rockets carried in clusters by a launching machine and in particular by an aircraft
US3495497A (en) Coupling member for a missile firing and guiding device
US2951664A (en) Stores ejection means
US2630740A (en) Apparatus for launching rocket bombs from aircraft
US3613617A (en) Rocket-thrown weapon
US3481246A (en) Munition dispenser
US3119335A (en) Projectiles fitted with and electric detonator operated by a generator of the inertia type
US4358983A (en) Blast enabled missile detent/release mechanism
US3115320A (en) Ejection seat catapult
US3041937A (en) Rocket control system