US3296927A - Guided missile - Google Patents

Guided missile Download PDF

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Publication number
US3296927A
US3296927A US402164A US40216464A US3296927A US 3296927 A US3296927 A US 3296927A US 402164 A US402164 A US 402164A US 40216464 A US40216464 A US 40216464A US 3296927 A US3296927 A US 3296927A
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US
United States
Prior art keywords
wire
missile
secured
sleeve
magazine
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
US402164A
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English (en)
Inventor
Olsson Olof
Nedeby Nils Gunnar
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
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Publication of US3296927A publication Critical patent/US3296927A/en
Anticipated expiration legal-status Critical
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
    • F41F3/042—Rocket or torpedo launchers for rockets the launching apparatus being used also as a transport container for the rocket
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/30—Command link guidance systems
    • F41G7/32—Command link guidance systems for wire-guided missiles
    • 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
    • F42B15/01—Arrangements thereon for guidance or control
    • F42B15/04—Arrangements thereon for guidance or control using wire, e.g. for guiding ground-to-ground rockets

Definitions

  • GUIDED MISSILE 2 Sheets-Sheet 2 INVENTORS OLOF' OLSSON N/LS GUNNHR NEDEBY BY MM ATTORNEYS 33916327 GUIDED MISSILE I OlohOlsson, Bofors, and Nils Gunnar Nedeby, Sodertalje, Sweden, assignors to Aktiebolaget Bofors, Bofors, Sweden, a Swedish company Filed Oct. 7,1964, Ser. No. 402,164 Claimspriority, application Sweden Oct. 16, 1963, 11,371/63. 7 Claims. (Cl. 89--1.8)
  • Thezpresent invention relates to rocket-type missiles which :are: launched from a stationary, usually groundbasedlaunching barrel which may be so designed that it can double as, a transport and storage container. More particularly, the invention relates to a guided rocket-type q missile whichis connected to a stationary, usually groundbasedtransmitterby one or several wire conductors.
  • the wire conductors serve. to transmit control signals from theitransmitter to: a suitable receiver on the missile to effect continuous guidance of the missile toward the target.
  • the conductor wires are initially stored in one or several magazines on the missile and are gradually withdrawn from the magazines when and. while the missile is airmotor is started.
  • the wires used in the. guidance systems afore-refcrred to are generally very fine wires for reasons of weight and flexibility, the wire diameters being usually in the order of 0.1 mm. Such fineiwires, tend to be torn oif which, of course, prevents guidance, ofa missile in flight.
  • a more specific object of the invention is to provide a ,novelaand improved device in which the wire portions tending to be exposed to the blast of the gases during the starting period are protected by a cover capable of withstanding the impact of the hot gases without appreciably interfering with the required low weight and high flexibility ofcthe wires.
  • FIGLI is a perspective view, partly broken open, of a missile and the launching container therefor equipped .witha wire-guiding device according to the invention
  • FIGLZ is a perspective, skeletonized view of the wire guiding device and of the parts of the container and the missile .directly coacting with the device, the respective containerand. missile parts being shown in phantom, and
  • FIG; 3 isa perspective detail view of FIG. 2 on an enlarged scale.
  • a rocket-type missile 1 of conventional design having a United States Patent "ice gas exhaust nozzle at one end.
  • the missile motor is not illustrated or described since it does not constitute part of the invention. It is sufiicient to visualize that a jet blast of gases will emanate from the nozzle of the missile when the missile motor is started.
  • the missile is shown as being placed in an elongated box or container 2 which serves both as a storage and transport container for the missile and as a launching barrel in a manner which is not essential for theunderstanding of the invention, but is well known in the art.
  • the launching box has a rear cover 3 and a front cover 4 which are removed when the missile is reduced for launching.
  • a frame 5 is secured to the rear end of box 2 by any suitable means such as bracket 6.
  • the frame supports a connector 7 which should be visualized as being suitably connected to a ground-based control transmitter which is not illustrated and should be visualized as being conventional.
  • Conductors 8 and 9 which are at least partly protected by insulation sleeves 10 and 11 respectively, extend from connector 7 as part of the circuit connections between the control transmitter on the ground and a suitable and conventional receiver (not shown) on the missile.
  • the circuit connections from the receiver to ground are completed by one or several conductor wires 27. These wires are initially wound up in suitable magazines 13 on the missile, one of the magazines being shown in FIG. 2. As the missile becomes airborne, the wires 27 are gradually withdrawn from the magazines so that the missile remains in continuous mechanical and electrical connection with the control transmitter.
  • Frame 5 mounts two substantially rigid bars 14 and 15 which extend along two opposite walls of the box toward its forward end. Insulation plates 16 and 17 respectively are secured to the ends of bars 14 and 15 opposite to frame 5. To simplify the illustration, the guiding device for only one of the wires 27 is shown in detail, but it should be understood that the guiding device for each of the conductor wires is substantially the same.
  • each of the bars forms a substantially U-channeled strip 18.
  • the branch or shank 19 of the strip terminates in an inwardly turned flange 21 which faces toward the interior of box 2.
  • a strip 22 of soft cushioning material such as foam rubber or other soft rubber, is inserted into the channel of U-strip 18 and is secured along its inner longitudinal edge, for instance by clamping the cushion strip between branches 19 and 20 of strip 18.
  • the width of the cushion strip is such that the strip is forced outwardly by flange 21 to form a lip 23, as is clearly shown in the figure.
  • Conductor wire 9 extending from connector 7 is passed through a hole 24 near the rear end of branch 20 of strip 18 and runs along the bight of the strip below the lower edge of cushion strip 22 to a hole 25 near the forward end of bar 15. The end of wire 9 is pulled out through a hole 25 near the front end of bar 15 and soldered to plate 17 at 26.
  • Conductor wire 27 extending from magazine 13 is also soldered to solder point 26, as will be more fully described hereinafter, so that there is electrical connection between wire 27 and connector 7, and thus between the receiver on the missile and the transmitter on the ground.
  • Wire 27 is extended through an outlet 28 of magazine 13 and a wire guide such as an eye 29 secured on the magazine body near the exhaust end thereof.
  • the portion of wire 27 extending from about eye 29 to solder point 26 is loosely encompassed by an insulation tube 30 made of a material capable of withstanding the blast action of the exhaust gases at least for a limited period.
  • a suitable material has been found to be a plastic known under the trade-name Systoflex. However, many other materials are known and readily available in the market.
  • the portion of the wire encompassed by tube 39 is the one which will be exposed to the blast of the bases when the missile is launched.
  • a major portion of tube 30 is initially fitted into the gap defined by rigid flange 21 and soft lip 23 whereby this sleeve portion is frictionally retained by the elasticity of the lip.
  • the retained portion of sleeve 30 extends from the rear end of bar 15 to a point close to the forward end of the bar where it is guided through a hole 31 in flange 21 and through an aligned hole 32 in insulation plate 17. It is then passed a few times through holes 33 and 34 in plate 17 to form several loops before wire 27 in sleeve 30 is joined to conductor wire 9 at solder point 26, as previously described.
  • the loops of sleeve 30 constitute in effect a strain relief for the solder connection of wire 27 at 26.
  • the wire guiding device of the invention further comprises frangible holding means shown in the form of a thin metal wire 35 which is secured at one end to the missile body, for instance by means of a second eye 36 near eye 29.
  • Wire 35 is tightly wound a number of times about the portion of sleeve 30 extending between eye 29 and the rear end of bar 15 whereby wire 35 impedes sliding of sleeve 30 and the wire 27 therein through eye 29 for a purpose which will be more fully described hereinafter.
  • a length of wire 27 with its insulation sleeve 30 is held in bar 15 by the frictional grip between flange 21 and lip 23 and it is also restrained on the missile by wire 35.
  • the tensile strength of this wire is so selected that it is higher than the strength of the frictional grip by which sleeve 30 is held in bar 15.
  • a wire-guiding device of a ground-controlled rockettype missile which is launched from a stationary launching barrel and when in flight is connected to a stationary transmitter by at least one conductor wire for transmitting control signals to the missile, said device comprising a wire magazine arranged to be secured on the missile, a wire guide arranged to be secured on the missile, a wire-retaining means arranged to be secured on the launching barrel, said retaining means including an elongated gripping member for gripping a wire portion with a frictional grip, a conductor wire extending from within said magazine through said wire guide to said gripping member and along the same and being secured at its outer end to said retaining means, and a protective pliable sleeve loosely encompassing the wire between a point thereof adjacent to said wire guide and a point adjacent to the secured outer end of the wire, whereby a wire portion between the wire guide on the missile and the secured end on said retaining means is protected by said sleeve from the exhaust gases generated when the missile is launched and is gradually pulled out of said gripping
  • a wire-guiding device of a ground-controlled rocket-type missile which is launched from a stationary launching barrel and when in flight is connected to a stationary transmitter by at least one conductor wire for transmitting control signals to the missile, said device comprising a wire magazine arranged to be secured on the missile, a wire guide arranged to be secured on the missile, a wire-retaining means arranged to be secured on said launching barrel, said retaining means including an elongated gripping member for gripping a wire portion with a frictional grip, a conductor wire extending from within said magazine through said wire guide to said gripping member and along the same and being secured at its outer end to said retaining means, a protective pliable sleeve loosely encompassing the wire between a point thereof adjacent to said wire guide and a point adjacent to the secured end of the wire, and frangible holding means holding said sleeve stationary in reference to said wire guide whereby a wire portion between said wire guide and the secured outer wire end on said retaining means is protected by said sleeve from
  • a wire-guiding device comprising a substantially rigid channeled element and a cushion strip fitted into said channeled element to form therewith a receiving gap for receiving the respective portion of the sleeve and the wire therein with a frictional grip.
  • a wire-guiding device wherein said channeled element has a substantially U-shaped cross section, one branch of said element terminating in an inwardly turned flange, said gap being defined between said cushion strip and said flange, and wherein said outer wire end is secured to said gripping member at one end thereof.
  • said frangible holding means comprises a restraining wire secured to said sleeve and held stationarily in reference to the wire guide, the tensile strength of said restraining wire being higher than the force required to pull the sleeve out of said gripping member but less than the tensile strength of the sleeve.
  • a ground-based stationary launching barrel an elongated rocket-type missile placed in said barrel for launching therefrom by exhaust gases of the missile, a wire magazine mounted upon the missile for withdrawal of conductor wire therefrom while the missile is missile wrearward of said magazine in reference to the exhaust end of the missile, a wire-retaining means, said retaining means including an elongated gripping member secured at .one end to an inside wall portion of said barrel and extending lengthwise of the missile, the forward end of: the gripping member being located forward of said wire: guidexand the other end rearward thereof, said conductor wire extending from said magazine through said wire guide.
  • said frangible holding means comprises a restraining wire secured to said missile and said sleeve, the tensile strength of said retaining wire being higher than the force required to pull the sleeve out of said gripping member but less than the tensile strength of the sleeve.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Insulating Bodies (AREA)
US402164A 1963-10-16 1964-10-07 Guided missile Expired - Lifetime US3296927A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SE1137163 1963-10-16

Publications (1)

Publication Number Publication Date
US3296927A true US3296927A (en) 1967-01-10

Family

ID=20293842

Family Applications (1)

Application Number Title Priority Date Filing Date
US402164A Expired - Lifetime US3296927A (en) 1963-10-16 1964-10-07 Guided missile

Country Status (9)

Country Link
US (1) US3296927A (OSRAM)
AT (1) AT252069B (OSRAM)
BE (1) BE654409A (OSRAM)
CH (1) CH414360A (OSRAM)
DE (1) DE1220763B (OSRAM)
FI (1) FI41627C (OSRAM)
FR (1) FR1410945A (OSRAM)
GB (1) GB1016410A (OSRAM)
NL (1) NL6411455A (OSRAM)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2103870A5 (OSRAM) * 1970-08-06 1972-04-14 Sarmac Sa
US4336740A (en) * 1978-12-29 1982-06-29 Hughes Aircraft Company Automatic blast actuated positive release missile detent
US4444087A (en) * 1982-01-28 1984-04-24 The Boeing Company Missile container and extraction mechanism
US4796833A (en) * 1987-03-31 1989-01-10 The Boeing Company Optical fiber guided tube-launched projectile system
WO1990005888A1 (en) * 1988-11-18 1990-05-31 Hughes Aircraft Company Bend limiting stiff leader and retainer system
FR2719372A1 (fr) * 1994-04-27 1995-11-03 Daimler Benz Aerospace Ag Dispositif pour le téléguidage de missiles ou de torpilles filoguidés.
EP0794117A1 (fr) * 1996-03-08 1997-09-10 AEROSPATIALE Société Nationale Industrielle Engin volant filoguide

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1578085B1 (de) * 1967-05-23 1971-06-09 Messerschmitt Boelkow Blohm Einrichtung zur zugfesten Verankerung einer Drahtverbindung fuer die UEbertragung von Lenksignalen von einer Leitstelle zu einem rueckstossgetriebenen Flugkoerper

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2103870A5 (OSRAM) * 1970-08-06 1972-04-14 Sarmac Sa
US4336740A (en) * 1978-12-29 1982-06-29 Hughes Aircraft Company Automatic blast actuated positive release missile detent
US4444087A (en) * 1982-01-28 1984-04-24 The Boeing Company Missile container and extraction mechanism
US4796833A (en) * 1987-03-31 1989-01-10 The Boeing Company Optical fiber guided tube-launched projectile system
WO1990005888A1 (en) * 1988-11-18 1990-05-31 Hughes Aircraft Company Bend limiting stiff leader and retainer system
US5022607A (en) * 1988-11-18 1991-06-11 Hughes Aircraft Company Bend limiting stiff leader and retainer system
AU620173B2 (en) * 1988-11-18 1992-02-13 Hughes Aircraft Company Bend limiting stiff leader and retainer system
FR2719372A1 (fr) * 1994-04-27 1995-11-03 Daimler Benz Aerospace Ag Dispositif pour le téléguidage de missiles ou de torpilles filoguidés.
EP0794117A1 (fr) * 1996-03-08 1997-09-10 AEROSPATIALE Société Nationale Industrielle Engin volant filoguide
FR2745786A1 (fr) * 1996-03-08 1997-09-12 Aerospatiale Engin volant filoguide

Also Published As

Publication number Publication date
FI41627C (fi) 1969-12-10
FR1410945A (fr) 1965-09-10
DE1220763B (de) 1966-07-07
FI41627B (OSRAM) 1969-09-01
BE654409A (OSRAM) 1965-02-01
NL6411455A (OSRAM) 1965-04-20
CH414360A (de) 1966-05-31
GB1016410A (en) 1966-01-12
AT252069B (de) 1967-02-10

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