US3495497A - Coupling member for a missile firing and guiding device - Google Patents

Coupling member for a missile firing and guiding device Download PDF

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Publication number
US3495497A
US3495497A US729189A US3495497DA US3495497A US 3495497 A US3495497 A US 3495497A US 729189 A US729189 A US 729189A US 3495497D A US3495497D A US 3495497DA US 3495497 A US3495497 A US 3495497A
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United States
Prior art keywords
missile
coupling member
firing
tube
coupling
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Expired - Lifetime
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US729189A
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English (en)
Inventor
Arnold Stangl
Franz Pfister
Gunther Karpa
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Bolkow GmbH
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Bolkow GmbH
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    • 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
    • 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
    • F41F3/045—Rocket or torpedo launchers for rockets adapted to be carried and used by a person, e.g. bazookas
    • 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
    • F41F3/052—Means for securing the rocket in the launching apparatus

Definitions

  • the invention is directed to a tiring and guiding device for guided missiles and, more particularly, to a coupling member for securing the missile t a support element containing the firing and guiding means. During its tiring and flight period, the missile is guided, either with or without a wire connection, by the firing and guiding means contained within the support element.
  • the missile can be connected directly to the tiring and guiding device or it can be mounted in position while disposed within a tiring tube. Where a tiring tube is used it also serves as the packing or carrier for the missile.
  • the connection to the tiring and guiding device must be sulliciently rigid to permit the missile to follow all the directing movements of the firing device without any relative movement between the two. Further, the connection means must be capable of detachment from the support element of the tiring and guiding device immediately after firing without being influenced by the forces acting on the missile.
  • connection or coupling member forms a part of the missile tiring weapon, it must afford exact alignment for the missile with the firing and guiding means under all environmental and weather conditions.
  • the overall device must be easy and safe to handle, especially during the loading operation, that is, when placing the missile, either with 0r without its firing tube, on the ring device.
  • the reaction forces developed upon separation of the missile from the tiring device should be as small as possible.
  • a large number of missiles must be launched from a firing device without any deviation in the launching operation, it is necessary that no inaccuracies caused by wear be developed particularly in the parts of the coupling member secured to the support element or tiring device.
  • This condition is especially true for missiles to be guided to a target semiautomatically by the so-called target covering method.
  • the missile must be picked up immediately after it is launched by a position nder whose output voltages represent the location coordinates of the missile. Since the pick-up range of such position finders is small, for example, in the range of plus or minus 2, any small inaccuracies or deviations occurring during launching may prevent the proper pick-up of the missile by the position linder.
  • the coupling member connecting the firing tube with the support element must have a locking means which is capable of releasing both the missile from the firing tube and the firing tube from the coupling member at the correct times during the launching operations.
  • Another problem is the provision for electrical connections between the missile and the tiring device, such connections include ignition circuits and circuits for transmitting guiding signals to the missile in flight. It will be appreciated, of course, that the guiding circuits remain in use during the tlight of the missile.
  • Another object of the invention is to provide a missile device which can be carried and handled by one person.
  • Another object of the invention is to assure low friction detachment of the missile from the tiring device.
  • Yetl another object of the invention is to afford missile firing and guiding equipment which can be easily and safely handled during battle conditions with its attendant physical and pyschic strain.
  • a further object of the invention is to provide a locking member for securing the missile and its tiring tube in position prior to launching and for releasing the missile and the tiring tube properly during launching operations.
  • Another object of the invention is to supply an arrangement for the detachment of the firing tube after the missile has been launched and also for the removability of the coupling member after the displacement of the ring tube.
  • Another particular object of the invention is to provide a three-point attachment or connection of the coupling member to the support element to absorb the various forces acting on the coupling member during launching operations without any adverse effects.
  • Another object of the invention is to afford switch and circuitry means in combination with the locking device for properly igniting the missile when it is released from its locked position within the firing tube.
  • Another object of the invention is to supply a battery within the coupling deivce for assuring proper operation of the various circuitry means each time a missile is lanuched.
  • Another object of the invention is to provide an interlocking engagement between the liring tube and the coupling member to assure proper slidable disengagement of the tube after the missile has been launched.
  • a further object of the invention is to afford an arrangement for disengaging the firing tube from the coupling member which does not provide any possibility of opposing sections becoming locked or jammed during disengagement.
  • the present invention provides a coupling member to which the missile and its tiring tube is releasably attached and which can be mounted on the support element containing the firing and guiding means through a three-point attachment arrangement.
  • the coupling member combines one part secured to the firing tube and a second part attached in a three-point arrangement to the support element of the missile firing device.
  • the points or areas of separation between the two parts are under stress only during the separation of the missile from the tiring device. Accordingly, the parts can be made of very low-friction materials since each coupling member is used only once and accordingly wear resistance is of minor importance.
  • the coupling member securing the firing tube to the ring and guiding device is comprised of two parts.
  • the first part is a lock member attached to the ring tube and to the second part.
  • the second part also attached to the firing tube, is secured in a three-point attachment to the support element of the firing and guiding device.
  • the lirst part includes a mechanical locking device which prevents any movement of the other parts of the device until the missile is launched.
  • the coupling member is arranged to remain in locked engagement until the missile is red and a desirable rotation is given it as it is ejected from the iiring tube.
  • the tube is displaced from the coupling member simultaneously in a direction opposite to the firing direction. The securement of the firing tube to the coupling member during launching assures an adequate longitudinal rotation for the missile, such as is accomplished by riiling the interior of the firing tube.
  • Another feature of the invention is the use of latch means for securing the locking device to the coupling member and the firing tube and missile.
  • Incorporated into the coupling member is an explosive charge for releasing the latch means.
  • the explosive charge unlatches both the missile and the firing tube, the tiring tube is still restrained against any rotational movement.
  • the guide track for the separation o'f the firing tube from the coupling member is divided into two spaced parts. The two points or surfaces of separation of the firing tube and the coupling member are arranged so that the tiring tube can be displaced oppositely from the tiring direction of the missile in an undisturbed trajectory.
  • the separation surfaces of the firing tube and the coupling member are disposed in a groove an-d slide arrangement with cylindrically-shaped pins arranged in opposed semi-circularshaped grooves to assist in the separation operation.
  • the pins are preferably vmade of tetraiiuorethylene.
  • the oppositely facing surfaces of the firing tube and the coupling member in the groove and slide arrangement and the cylindricallyshaped pins are covered with a protective lm to protect them lfrom dirt and moisture during long periods of storage and also from the conditions existing under battle situations. The protective lm is destroyed as the missile is launched for effecting the efficient operation of the separation surfaces.
  • another feature of the invention is the disposition of the forward separation surfaces of the coupling member at a higher elevation than the rearward contacting surfaces for avoiding any likelihood of jamming between the firing tube and the coupling member when it is being displaced from the firing device. This feature is of particular importance in avoiding any danger to the person operating the device during the launching operations.
  • the three-point attachment of the coupling member with the supporting element is arranged so that each bearing point is essentially stressed in only one direction and is arranged to absorb one of the series of forces acting on the coupling member during the missile launching operation.
  • forces which occur perpendicularly to the longitudinal axis of the coupling member are absorbed by a plug connection located at the forward face of the coupling member and may also be assisted by the two sliding guides on the support element which engage grooves in the coupling member.
  • the slide guides and grooves located at the rearward portion of the coupling member also absorb any torque or rotational movement about the longitudinal axis of the coupling member.
  • the forces acting in the longitudinal direction of the coupling member are absorbed by a retractable knob on the support element which engages in a recess in the coupling member, further the knob establishes the locking engagement of the coupling member with the support element of the firing device.
  • the plug connection between the coupling member and the ring device affords the additional advantage of forming the electrical connection between the missile and the firing and guiding means and may contain an accumulator for releasing the coupling member from the support element after the completion of the launching and guiding operations.
  • Still another advantage of the coupling member is the incorporation of an activated battery into its structure for providing the current supply for the guiding device.
  • the reliability of the entire weapon system is increased since a new battery is employed for each missile launching.
  • the coupling member and the missile are mounted on the tiring and guiding device, the necessary electrical connections are established.
  • the wire extends between the missile within the tiring tube and the coupling member and, after launching when the coupling member is detached from the ring and guiding device, the device is ready for another missile without requiring any additional wiring connections.
  • the connection between the tiring tube and the coupling member is provided by a mechanical locking device.
  • the locking device consists of a rocker-type lever having a first latch at one end secured into the firing tube for holding the missile in place, at its other end, the lever has a second latch which is engaged within a bore in a rearward portion of the coupling member.
  • a pair of spring loaded pawls are mounted in the rocker-type lever and are arranged to close microswitches for activating the electric circuits of the firing device when the latches are released.
  • an exposive charge is located for displacing the rocker lever into its unlatched position for releasing the missile and tiring tube.
  • the mechanical locking device holds the missile in position in the tiring tube. It is released only when the missile is ready for firing. Further, the arrangement of the locking device provides not only for the release of the missile and the firing tube from the coupling member but it also affords the actuation of the electric circuit for the missile launching operation.
  • FIG. 1 is a simplified representation of the present invention illustrating the parts of the tiring and guiding device in a separated arrangement
  • FIG. 2 is a side view, partly in section, through the coupling member and locking device
  • FIG. 3 is a top view of the locking device, as shown in FIG. 2;
  • FIGS. 4 and 5 are end views of the surfaces of separation between the coupling member and the tiring tube.
  • FIG. l a missile firing and guiding device is illustrated with the different elements forming the device shown in a separated arrangement.
  • a portion of the supporting element of the device is formed by an underframe 1 to which are attached tripod legs 2.
  • the underframe 1 is adjustable in both the elevational and traverse directions through devices 3 and 4, however, since these devices do not form a part of the invention they are not described in detail.
  • a sight support 5 Connected to the under-frame 1 and forming a part of the support element of the device, is a sight support 5 which contains a sight 6 and means required for tracking and guiding the missile, however, these parts are not shown in detail since they do not form a part of the invention as such.
  • the ammunition package consists of a tiring tube 7 which is secured to the sight support 5 by lmeans of a coupling member 8.
  • a missile not shown, is positioned within the tiring tube.
  • the firing tube and the coupling member are provided with separation surfaces 9a, 9b which are described subsequently.
  • the righthand end of the tiring tube faces in the tiring direction.
  • the coupling member 8 is inserted in the tiring direction into a bowl-shaped recess 10 in the sight support 5 and is guided into position by the sliding guides 11 at the rear of the recess 1t) and an electrical plug connection 12 at its forward end.
  • a spring loaded knob 13 located toward the rear of the recess 10 provides a locking engagement with a recess 14 in the coupling member 8.
  • the coupling member 8 has a plug connector 15 which engages the electrical plug connection 12 in the sight support 5, note the plug 15 shown in FIG. 2 and the arrow in FIG. 1 which indicates the manner in which the plug 15 is inserted into the plug connection 12.
  • an activatable battery 16 Located within the coupling member 8 is an activatable battery 16 whose contacts are connected with coresponding electrical contacts of the plug receptacle 15. Further, as shown in FIG. 2, in the rearward portion of the coupling member 8, an explosive charge 18 is located within a bore 17 and a piston 43 is positioned within a bore 19 disposed generally perpendicularly to the bore 17. At the opposite end of the bore 19, mounted on top the coupling member 8 is a mechanical locking device 20.
  • Mechanical locking device 20 consists of a rocker-type lever 22 rotatable about an axis 21 located transversely of the longitudinal axis of the coupling member 8. At its forward end an upwardly disposed first latch 23 extends through an opening in the firing tube 7 and is secured within the tube into a recess in the missile. These features are not shown in the drawings. In this manner, the first latch in engaged position secures the firing tube and the missile in position on the tiring and guiding device;
  • a second latch 31 extends downwardly and has a spherical end engaged within the upper end of the bore 19 in the coupling member. Accordingly, at its forward end, the latch 23 secured the locking device to the firing tube and missile and at its rearward end it secures the locking device to the coupling member 8.
  • a leaf spring 24 attached to the housing of the locking device maintains the latch means within their engaged positions. It will be noted that at the rearward end of the coupling member the area or surfaces of separation 9a are provided between the locking device 20 and the coupling member 8.
  • pawls 27 and 28 loaded by helical springs 25 and 26. These pawls 27 and 28 are arranged to engage in a recess 29 in the lever when the lever is rocked about its axis 21 into the unlatched position. In the unlatched position, the pawls are urged by means of their helical springs into the recess 29 for holding the lever in its unloaded position, and at the same time actuate the microswitches 30 mounted in the locking device.
  • the microswitches 3() close the ignition circuits for the launching of the missile.
  • the contacts of the microswitches 30 are connected through lines 32 with the firing tube 7 and the missile contained within it and, in addition, by means of disengageable electric contacts 33, note FIG. 2, with the coupling member 8.
  • the contacts 33 may be replaced by sliding electrical contacts which provide the electrical connection between the mechanical locking device and the coupling member.
  • FIGS. 4 and 5 The previously mentioned areas or surfaces of separation 9a and 9b are shown in detail in FIGS. 4 and 5 and it will be noted that they are constructed differently in the forward position, that is, FIG. 4 illustrating the surface of separation 9b and the rearward position shown in FIG. 5 exhibiting the other surface of separation 9a.
  • FIG. 4 the forward portion of the coupling member -8 is shown connected to the firing tube 7.
  • the upper surface of the coupling member 8 is arranged to provide a rectangularly-shaped groove 35 which receives a slide 36 formed on the lower portion of the firing tube 7.
  • the groove 35 and the slide 36 which form the surfaces of separation 9b are provided with a space between their opposed faces.
  • semi-circular-shaped grooves 37, 38 are formed into which cylindrically-shaped pins 39 are inserted which act as the retaining and guiding means between the coupling member and the firing tube.
  • the separation surfaces 9a are disposed in a similar fashion to that shown in FIG. 4, however, the positions of the groove and slide members are reversed.
  • the locking device is secured to the firing tube and its downwardly facing surface is provided with a rectangularlyshaped groove 41.
  • the upwardly directed portion of the coupling member 8 is arranged as a slide member to t within the groove 41 in the locking device.
  • the oppositely facing surfaces of the groove 41 and the slide member 40 are spaced apart and semi-circular grooves 37 and 38 are formed in the opposite side surfaces of the groove and slide member and cylindrically-shaped pins 39 are disposed within these grooves and form the individual guiding and retension means between the slide member 40 and the groove 41.
  • a pair of oppositely facing grooves 42 arranged to fit in engagement with the sliding guides 11 in the sight support 5, see FIG. 1.
  • the separation surface 9b is disposed vertically above the separation surface 9a.
  • the arrangement of the grooves and slides on the firing tube 7 or its locking device 20 and on the coupling member 8 are reversed between separation surfaces 9a and 9b.
  • the dimension of the separation surfaces 9a, 9b are of suflicient length in the longitudinal direction to assure that the cylindrically-shaped pins 39 remain in engagement within the grooves 37, 38 during the launching of the missile and the resulting backward movement of the firing tube until the missile has received a sufficient rotational twist.
  • This twist if it is desired at all, is brought about in the usual case by riing on the interior of the firing tube which, however, can influence the missile only if the firing tube is secured against rotation about its longitudinal axis.
  • the ammunition assembly consisting of the firing tube 7, the missile disposed within the tube, and the coupling member 8 are inserted into the sight support 5 by the person operating the device with the forward end of the coupling member, that is, the plug receptacle 15, inserted into the plug connection 12 of the sight support 5.
  • the knob 13 on the sight support is tted into the recess 14 in the coupling member and the sliding guide 11 on the sight support t Within the grooves 42, see FIG. 5, on the coupling member.
  • connection between the plug parts 12 and 15 absorb the forces acting substantially normal to the longitudinal axis of the coupling member
  • connection formed by the sliding guides 11 on the sight support and the grooves 42 in the coupling member absorb the rotational or torque forces acting on the coupling member.
  • the interconnection of the knob 13 in the sight support and the recess in the coupling member absorb all the forces acting in the longitudinal direction of the coupling member.
  • the explosive charge 18 located in the coupling member is electrically ignited and creates a pressure wave which drives the piston upwardly within bore 19 and displaces the latch 31 out of the bore 19, against the force of the leaf spring 24.
  • the action of the latch 31 being moved upwardly within the bore 19 rocks the lever 22 about its axis 21 and displaces the latch 23 from its position locking the missile in place within the firing tube.
  • the latch 23 when moved downwardly also releases the firing tube 7.
  • the microswitches 30 are actuated and the electric ignition circuits for the launching of the missile are closed.
  • a gyro system for the position control of the missile is actuated by a power propelled charge, and a are charge for tracking the missile also is ignited.
  • a gas generator is usually contained within the .firing tube and it is also ignited by the microswitches and the pressure it produces drives the missile out of the ring tube and ignites the missile propulsion mechanism.
  • the arrangement of the missile and the ring tube 7 is such that as the missile is launched, the firing tube receives an acceleration force in a direction opposite to the firing direction and the firing tube detaches from the coupling member at the separation surfaces 9a, 9b and it is displaced rearwardly from the ⁇ firing and guiding device.
  • the coupling member remains connected to the sight support of the firing and guiding device.
  • the missile is connected to the coupling member lby the guide wire and it is directed to the target by means of signals transmitted through the guide wire from the guiding device.
  • a device for firing and guiding missiles including a support device ycontaining firing and guiding means, the improvement comprising a longitudinally extending coupling device detachably secured to said support device, a missile firing mount detachably mounted on said coupling device, and a first means, a second means and a third means, each arranged to provide a detachable engamement between said coupling device and Said support device, said first means being arranged to absorb forces acting substantially normal to the longitudinal axis of said coupling member, said second means being arranged to absorb rotational forces acting about the longitudinal axis of said coupling member, said third means being arranged to absorb forces acting in the direction of the longitudinal axis of said coupling device whereby as the missile is fired said missile firing mount is detached from said coupling device and after the missile firing has been completed said coupling device is detachable from said support device for replacement by a new missile firing mount and coupling device for ring another missile and wherein said first, second and third means provide a three point attachment between said first,
  • a device as set forth in claim 1, wherein means being arranged for releasably locking said missile firing mount to said coupling member, said means comprising a locking device attached to said missile firing mount, said locking device comprising a lever extending in the longitudinal direction of said coupling device and being arranged to pivot about an axis disposed transversely of the longitudinal axis of said coupling device, said lever being positionable between a first position in engagement with said coupling device and the missile positioned on said missile firing mount and a second position released from said coupling device and the missile, in the first position a first latch on said lever is arranged to secure the missile in position and a second latch longitudinally spaced from said first latch is engaged in locking relationship in said coupling device.
  • first latch projects obliquely from one end of said lever which is spaced longitudinally from the axis thereof and said second latch projects obliquely from said lever in a direction opposite to that of the direction in which said first latch projects and said second latch being spaced longitudinally from said first latch and being positioned on the opposite side of the axis of said lever from said first latch, and a spring member for urging said first latch and second latch into locking engagement with the missile and said coupling member, respectively.
  • microswitch means are positioned within said locking device and are arranged to close the ignition circuit in the support device containing firing and guiding means when said pawl means are engaged in the recess holding said lever in the second position.
  • said missile firing mount comprises a first section and a second section disposed in longitudinally spaced relationship relative to the longitudinal axis of said coupling member, and each of said sections arranged in slidable engagement with said coupling device.
  • said second section of said missile firing device incorporates said locking member and extends downwardly from said missile firing member and forms a longitudinally extending groove in its lower surface
  • said coupling member having an upwardly directed slide section arranged to fit within the groove in said second section, the opposed surfaces of said groove in said missile firing member and of said slide section of said coupling member disposed in closely spaced relationship, longitudinally extending semi-circular grooves formed in the opposed sides of said groove and slide section, and cylindrically-shaped rods disposed in said grooves for retaining said coupling member and said missile firing mount in engagement and for affording sliding relationship therebetween as said firing member is disengaged from said coupling member.
  • a battery is positioned within said coupling device and is arranged to provide current for operating the firing and guiding means.
  • said first means comprises an electrical plug connector having its axis disposed in parallel relationship with the longitudinal axis of said coupling device and being connected to said battery, and a mating electrical connector member in said support device arranged to receive and be interconnected with said electrical plug connector.
  • said second means comprises grooves extending in the longitudinal direction in said coupling member, and sliding guides secured to said support device and extending transversely of the longitudinal axis of said coupling device and being arranged to fit in sliding engagement within said grooves.
  • said third means comprises a recess in said coupling member having its axis disposed perpendicularly to the longitudinal axis ⁇ of said coupling device and a spring loaded knob in said support device extending perpendicularly to the longitudinal axis of said coupling device and arranged to nt in interlocking engagement within said recess in said coupling member.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Toys (AREA)
US729189A 1967-05-19 1968-05-15 Coupling member for a missile firing and guiding device Expired - Lifetime US3495497A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DEB0092604 1967-05-19

Publications (1)

Publication Number Publication Date
US3495497A true US3495497A (en) 1970-02-17

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ID=6986483

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Application Number Title Priority Date Filing Date
US729189A Expired - Lifetime US3495497A (en) 1967-05-19 1968-05-15 Coupling member for a missile firing and guiding device

Country Status (6)

Country Link
US (1) US3495497A (de)
CH (1) CH470647A (de)
DE (1) DE1578084C3 (de)
FR (1) FR1578960A (de)
GB (1) GB1223922A (de)
SE (1) SE347808B (de)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3753382A (en) * 1972-05-09 1973-08-21 Sarmac Sa Infantry weapon and its ammunition
US3754497A (en) * 1970-08-06 1973-08-28 Sarmac Sa Transporting and firing chest for self-propelled projectiles
JPS5433080B1 (de) * 1970-08-06 1979-10-18
US4404887A (en) * 1980-06-23 1983-09-20 General Dynamics, Pomona Division Recoil reducer
RU2107247C1 (ru) * 1996-12-05 1998-03-20 Конструкторское бюро приборостроения Устройство крепления ракетного снаряда
RU2545154C1 (ru) * 2014-01-09 2015-03-27 Николай Яковлевич Кириленко Устройство для запуска ракет

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3048596A1 (de) * 1980-12-23 1982-07-01 Dynamit Nobel Ag, 5210 Troisdorf Panzerabwehrhandwaffe
CH684967A5 (de) * 1991-11-25 1995-02-15 Eidgenoess W & F Bern Anpasseinheit für Panzerfaust.
RU2233420C2 (ru) * 2002-08-20 2004-07-27 Государственное унитарное предприятие "Конструкторское бюро приборостроения" Способ обеспечения электропитанием бортовой аппаратуры управляемой ракеты и управляемая ракета в транспортно-пусковом контейнере для его осуществления
CN107388893B (zh) * 2017-09-01 2019-04-19 西北工业大学 一种小型火箭弹发射装置

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2764066A (en) * 1953-08-28 1956-09-25 Jr Robert A Doak Contact-latch type firing mechanism for rocket launchers
US2972933A (en) * 1957-12-23 1961-02-28 Gen Dynamics Corp Missile hand launching system
US2978959A (en) * 1953-05-27 1961-04-11 Robert E Carlberg Self-aligning guide for loading in missile launching systems
US3331279A (en) * 1964-05-06 1967-07-18 Bofors Ab Launching assemblage for rocket missiles
US3389637A (en) * 1966-06-15 1968-06-25 Bolkow Gmbh Firing and guiding mechanism for jetpropelled missiles launched from launcher tubes

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2978959A (en) * 1953-05-27 1961-04-11 Robert E Carlberg Self-aligning guide for loading in missile launching systems
US2764066A (en) * 1953-08-28 1956-09-25 Jr Robert A Doak Contact-latch type firing mechanism for rocket launchers
US2972933A (en) * 1957-12-23 1961-02-28 Gen Dynamics Corp Missile hand launching system
US3331279A (en) * 1964-05-06 1967-07-18 Bofors Ab Launching assemblage for rocket missiles
US3389637A (en) * 1966-06-15 1968-06-25 Bolkow Gmbh Firing and guiding mechanism for jetpropelled missiles launched from launcher tubes

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3754497A (en) * 1970-08-06 1973-08-28 Sarmac Sa Transporting and firing chest for self-propelled projectiles
JPS5433080B1 (de) * 1970-08-06 1979-10-18
US3753382A (en) * 1972-05-09 1973-08-21 Sarmac Sa Infantry weapon and its ammunition
US4404887A (en) * 1980-06-23 1983-09-20 General Dynamics, Pomona Division Recoil reducer
RU2107247C1 (ru) * 1996-12-05 1998-03-20 Конструкторское бюро приборостроения Устройство крепления ракетного снаряда
RU2545154C1 (ru) * 2014-01-09 2015-03-27 Николай Яковлевич Кириленко Устройство для запуска ракет

Also Published As

Publication number Publication date
DE1578084B2 (de) 1975-04-24
CH470647A (de) 1969-03-31
DE1578084C3 (de) 1975-12-11
GB1223922A (en) 1971-03-03
DE1578084A1 (de) 1971-07-22
FR1578960A (de) 1969-08-22
SE347808B (de) 1972-08-14

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