US3710677A - Rocket projector magazines - Google Patents

Rocket projector magazines Download PDF

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Publication number
US3710677A
US3710677A US00886151A US3710677DA US3710677A US 3710677 A US3710677 A US 3710677A US 00886151 A US00886151 A US 00886151A US 3710677D A US3710677D A US 3710677DA US 3710677 A US3710677 A US 3710677A
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US
United States
Prior art keywords
tubes
loading chamber
frame
setting means
axes
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
US00886151A
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English (en)
Inventor
C Mayer
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.)
Rheinmetall Air Defence AG
Original Assignee
Werkzeugmaschinenfabrik Oerlikon Buhrle AG
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Application filed by Werkzeugmaschinenfabrik Oerlikon Buhrle AG filed Critical Werkzeugmaschinenfabrik Oerlikon Buhrle AG
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C17/00—Fuze-setting apparatus
    • 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
    • F41A9/00—Feeding or loading of ammunition; Magazines; Guiding means for the extracting of cartridges
    • F41A9/29—Feeding of belted ammunition
    • F41A9/34—Feeding of belted ammunition from magazines
    • 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

Definitions

  • ABSTRACT A rocket projector magazine for rockets having an adjustable time fuze on the nose portion of each rocket.
  • a plurality of loading chamber tubes having each a 9/ 315, 89/1816, rocket. Adjusting means for said time fuzes'positioned V v outside the firing trajectory of the rockets. Means for [Si] Int. Cl. 3/04 producing a relative movement between the adjusting [58] Field of Search....89/6,6.5, 1.816, 1.815, 1.817, means and the loading chamber tubes so that the adjusting means engage and adjust the time fuzes of the rockets in the loading chamber tubes.
  • a rocket projector magazine comprises a plurality of loading chamber tubes, a rocket within each tube, an adjustable time fuse situated on the nose portion of each rocket, devices for adjusting the time fuses positioned outside the firing trajectory of the rockets, and means for producing a relative movement between the adjustment devices and the load chamber tubes so that the adjustment devices engage the time fuses of the rockets.
  • FIG. 1 is a perspective view of a rocketprojector magazine according to the invention.
  • FIG. 2 is a perspective view of an alternative embodiment of a rocket projector magazine according to the invention.
  • FIG. 3 and 4 are front elevations showing various positions of the loading chamber tubes in the magazine of FIG. 2.
  • FIG. 5 is a view along the cross section line V-V of FIG. 7 of a third embodiment of a rocket projector magazine according to the invention.
  • FIG. 6 is a view along the line VIVI of FIG. 7 and FIG. 7 is a view along the section line VII-VII of FIG. 6.
  • the frame 1 of the rocket projector magazine consists of a front wall 2 and two side walls 3 perpendicular to the front wall.
  • Threaded spindles 5, 6, 7 and 8 pass through the side walls 3 parallel to corner edges 4.
  • the spindles 5, 6, 7, 8 engage threads in support pieces 9.
  • a shaft 10 supports two bevel gears 11 which are in mesh, with gear wheels 12 connected to the spindles 5, 6.
  • Gear wheels 13 which are in mesh with the bevel gears 11 are supported on shafts 14 parallel to the front wall 2.
  • the gear wheels 13 are also in mesh with gear wheels 12 on the spindles 7 and 8.
  • a threaded spindle l5 and a bar 16 are disposed perpendicular to the front wall 2.
  • the threaded spindle 15 engages a thread in the support pieces 9.
  • the bar 16 is fastened to the other support pieces 9.
  • the spindle 15 engages threads within end portions 18, of two supports 17 arranged behind each other parallel to the front wall 2.
  • the bar 16 passes through other ends 19 of the supports 17.
  • Loading chamber tubes 20 are fastened to supports 17 so that the axes of the tubes are perpendicular to the front wall 2 and lie in one plane.
  • Firing tubes 21 are mounted in the front wall 2.
  • the firing tubes 21 have the same inner diameter as the loading chamber tubes 20 and are coaxial with the loading chambers (see left half of FIG. 1.)
  • Cylindrical adjusting devices 22 are fixed above and in front of the loading chamber tubes 20.
  • the diameters of the adjusting devices 22 are smaller than the inner diameters of loading chamber tubes 20.
  • the axes of the adjusting devices 22, are perpendicular to the front wall 2 and lie in a single plane parallel to that of the axes of the loading chamber tubes 20.
  • each loading chamber tube 20 An adjusting device is assigned to each loading chamber tube 20.
  • the axes of each loading chamber tube 20 and its associated adjusting device 22 lie in a single plane when the tubes 20 are in an adjusting position (as explained hereinafter.) This plane is parallel to that of the axes of the tubes 30 in their initial position and vertically above it.
  • the shafts 23-support worm gears 24 which are in contact with gears 25 supported on a shaft 26 whose axis is perpendicular to that of the shafts 23'.
  • a handle 27 is connected to the shaft 23.
  • loading chamber tubes 20 are provided with rectangular indentations 28 parallel to the loading tubes axis.
  • Each loading chamber tube 20 contains a rocket 29 on the noses of which are arranged time fuses 30 having rotatable setting rings 31.
  • a ring 32 is screwed onto the rear end. of each rocket 29. These rings 32 are for preadjusting the inclination of wings which provide aerodynamic braking and which are attached to the rockets 29.
  • the rockets 29 are secured inside the loading chamber tubes 20 so they cannot rotate.
  • the adjusting rings 32 have crowns 33 equipped with worm gear teeth.
  • a shaft 34 runs perpendicular the axes of the loading chamber tubes 20 1 and supports a number of worm gears 35.
  • the loading chamber tubes 20 are first lifted from the initial position shown in the left [half of FIG. 1. This operation is carried out turning the shaft 10. Rotation of these shafts causes the spindles 5, 6, 7 and 8 to rotate (through rotation of the shafts 14.) The supports 9 are moved upwards by the rotating spindles 5, 6, 7, 8 and the two supports 17 with loading chamber tubes 20 lifted. When the axes of the loading chamber tubes 20 are in line with those of the adjusting devices 22, the spindle 15 is rotated. The supports 17 are thereby moved forward with the loading chamber tubes 20 until their front ends surround the adjusting devices 22 (see FIG.
  • the setting means of the adjusting devices 22 now contact the setting rings 31 of the fuses 30.
  • the shaft 26 is now rotated by turning handle 27. This movement is transmitted through gears 25, 24 to the shafts 23 of all of the adjusting devices 22 causing all setting rings 31 to be turned at an angle corresponding to the required running time of the fuse clockwork.
  • the worm gear teeth of the crowns 33 of the adjusting rings 32 of each rocket 29 engage the associated gear wheel 35.
  • the adjusting rings 32 are turned to adjust the angle of rocket braking wings.
  • FIG. 2 there are mounted in a front wall 37 of a housing 36 of the rocket projector magazine a number of parallel firing tubes 21.
  • the firing tubes 21 are arranged in two rows 21,, 21 21 21 and 21 21 21,, 21
  • the firing tubes of each row are identical.
  • Loading chamber tubes 20, containing rockets 29 are situated behind and coaxially with respect to the firing tubes 21 as seen in FIG. 3.
  • loading chamber tubes 20 terminate in front of a rear wall 38 of the housing 36.
  • the back wall as has two slotlike openings 40 (only one of which is shown) level with the rear ends of the loading chamber tubes 20 which are arranged in two rows 20,, 20,, 20 20, and 20,,, 20 20,, 20,,, (corresponding to the two openings
  • Each pair ofloading chamber tubes such as 20, and 20 20, and 20,, of the two rows are connected by two spokes 39.
  • the two spokes 39 of each of the pairs 20,, 20 20,, 20 are attached to a rod 41,, 41 41, parallel to the axes of the loading chamber.
  • the rods 41 are rotatably mounted between a front wall 37 and the back wall 38 of the housing 36.
  • cranks 42 To the rear ends of the rods 41 are attached parallel cranks 42 linked by a bar 43. Each crank 42 is also of equal length. A handle 44 is connected to one of the cranks Two hollow threaded spindles 45, 46 are rotatably mounted and so that they are not longitudinally displaceable on the two rods 41, and 41,. The spindles 45, 46 are connected to sprocket gears 47, 48 over which passes a chain 49. The spindle 45 is driven by a worm gear 50 mounted on the rod 41. The worm gear 50 1 meshes with a gear 51 attached to a shaft 52 perpendicular to the rod 41.
  • a plate 53 parallel to the front wall 37 of the housing 36 has threaded bones which engage with the spindles 45, 46.
  • the rods 41 enter the plate 53 through bores 54.
  • the plate 53 carries adjustment devices 22 whose axes are parallel to the axes of the firing tubes 21.
  • the adjusting organs 22 are arranged in two rows 22, 22, and 22,, 22,, which are parallel to the two rows of loading chamber tubes 20 and lie between these. Each row has the same number of adjustment devices 22 as the row next to it has numbers of firing tubes 21.
  • the axes of the pairs of adjusting organs 22,, 22,, 22,, 22,, 22,, lie in planes which are parallel and contain the rods 41, 41,.
  • the distances of these adjusting organs 22,, 22,, 22,, 22,, from axes 41, 41, are thesame as the distances of loading chamber tubes 20,, 20, 20,, 20,, from the-rods 41 41,.
  • the gear wheels 56 rotating with shafts 57,58 drive- I through gear wheels 55 the shafts of adjustment devices Shafts of the adjustment devices 22 support worm gears 55.
  • the worgears 55 mesh with gear wheels 56 connected to shafts 57, 58.
  • the shafts 57, 58 are drivably connected with each other through spurgears 59, 60.
  • On the rods 41 are rotatably mounted sleeve shafts 61 which have a wormgear crown 62 and a spurwheel crown 63.
  • the sleeve shafts 61 are arranged between two shafts 64 which are mounted on the rear wall 58 and likewise have a wormgear crown 62 and a spurwheel crown 63.
  • the wormgear crowns 62 of sleeve shafts 61 and of shafts 64 mesh with gears 65 which are supported on a drive shaft 66.
  • the adjusting rings 32 of the rockets 29 have spur toothed crowns 67.
  • the loading chamber tubes 20 in their rest position are coaxial with the firing tubes 21.
  • the rockets 29 are pushed through openings 40 in the housing back wall 38 into the loading chamber tubes 20.
  • the rockets 29 are then secured so they cannot rotate.
  • the spurwheel crowns of the adjusting rings 32 are in contact with the indentations 28 of loading chamber tubes 20.
  • the crank handles 42 By simultaneously turning the crank handles 42 the axes 41 are rotated and consequently the spokes 39 with the pairs 20,, 20,, 20,, 20 of loading chamber tubes are movedinto the position shown in FIG. 4'. In this position the loading chamber tubes 20 are coaxially with respect to the adjustment devices 22.
  • shaft 66 By rotating shaft 66 the sleeve shafts 61 and the shafts 64 are moved and'the adjusting rings 32 of all the rockets 29 are rotated to displace the braking flights (not shown.) i
  • the sprocket wheel 47 which is attached to the spindle 45 is driven by the shaft 52 through the pair of meshing gear wheels 50, 51 and sprocket wheel 48 with spindle 46 by a chain'59.
  • the plate 53 is moved backwards by.
  • the plate 53 with the adjustment devices 22 is moved back into its initial position by the spindles 45,46.
  • the loading chamber tube pairs 20,, 20,, 20,, 20,, are turned back, through rotating of the cranks 42 and the rods 41,50 that. the loading chamber tubes 20 are coax-i ially with the firing tubes 21.
  • the rocketprojector is then ready for firing With reference to FIGS. 5 to 7 twelve parallel firing tubes 69 and loading chamber tubes 70 are coaxial and arranged inside a box-shaped frame 68 of a rocket projector. The axes of the tubes are parallel to the sides of the frame.
  • the corners of the frame are parallel to the longitudinal axes of three tubes 70,, 70 70;, 70 70 70. Between the front ends of the loading chamber tubes 70 and the back ends of the firing tubes 69 of all these sets of three are arranged rotatable slides 71.
  • the rotatable slides 71 consist of four tube pieces 72,, 72 72,, spaced at regular angular distances with respect to each other, which are connected by arms 73 to a hub 74.
  • a motor 75 is attached to a flange on a housing 76 which is connected to the frame 68.
  • Two bevel gears 77, 78 are rotatably mounted on a shaft 79 driven by the motor 75.
  • the gears 77, 78 mesh with a bevel gear 80 mounted in a housing.
  • Through a coupling 81 each of the two gears 77 and 78 can drive the shaft 79.
  • Four shafts 82 are situated parallel to the axes of the firing and loading chamber 69, 70 and are equidistant from the sides of the tubes.
  • the shafts 82 have a spur toothed crown 83.
  • On the shafts 82 are rotatably mounted longitudinally displaceable tubes 84.
  • a spindle 85 is in mesh with the bevel gear 78.
  • the spindle 85 is rotatably mounted on the shaft 79 and engages a threaded nut 86 having four spokes 87.
  • the spokes 87 engage grooves 89 of rings 88 at the front ends of tubes 84.
  • the hubs 74 of the rotatable slides 71 are mounted on the tubes 84.
  • Each of two supports 90 is directed radially at tubes 84 and connected thereto.
  • the pairs of supports 90 protrude through an opening91 into the interior of one of the tube pieces 72 of a slide 71.
  • Two meshing spurgears 92, 93 are mounted on the supports 90.
  • the gears 92 engage teeth 83 on the shafts 82.
  • the housings of the adjusting devices 22 are fastened to the supports 90 and protrude rearwardly from them.
  • the gears 93 are fixed to shafts 94 which drive the elements (not shown) of the adjusting devices 22.
  • the distance of the axes of the adjusting devices 22 and of the firing and loading chamber tubes 69, 70 from the axes of the hubs 74 of rotary slides 71 are equal.
  • a spur gear 95 is rotatably mounted on the shaft 79 and can be driven by the shaft through a coupling 97 and a sleeve shaft 96.
  • a brake 100 is associated with the gear 95.
  • Spur gears 98 engage the gear 95 and also a fixed crown 99 having a toothed interior.
  • Gears 98 are mounted in bridges 101 connected to a bevel gear 102 and a spur gear 103.
  • the spur gear 103 is mounted on the sleeve shaft 96.
  • Spur gears 104 are fixed to the hubs 74 of the rotable slides 71 and are in drive with the gear 103 through two meshing gears 105.
  • the bevel gear 102 is mounted on the shaft 79 and engages bevel gears 106.
  • the gears 106 are fixed to rods 107 mounted on a ring 108 which is rotatable around the shaft 79.
  • the rods 107 are also mounted on a crown 109 which surrounds the gears 106.
  • Crown 109 has a spur toothed exterior.
  • the gears 106 engage with a bevel gear 110 which can rotate about the shaft 79.
  • the bevel gears 110 can be driven by the shaft 79 through a coupling 111 and can be halted by a brake 112.
  • Four spur gears 113 engage the toothed crown 109 and are mounted onshafts 114 which can drive the shafts 82 through cardan shafts 115.
  • gear 102 drives gears 106 which mesh with stationary gear and consequently rotate jointly with the toothed crown 109 about the shaft 79. Toothed crown 109 drives the shafts 82 through gears 113 and shafts 114 and 115 so that there is no relative movement between the latter and the gears 92.
  • a rocket projector magazine comprising a frame, a plurality of loading chamber tubes in said frame having a rocket in each tube, a plurality of firing tubes mounted on said frame which firing tubes are aligned with said loading chamber tubes when said rockets are fired, an adjustable time fuse on the nose of each rocket, a plurality of fuse setting means mounted on said frame for the adjustment of said time fuses, said fuse setting means and said loading chamber tubes being movably mounted in said frame transversely and parallelto the axes of said firing tubes.
  • a rocket projector magazine wherein a support receives said loading chamber tubes, said support being mounted vertically and horizontally movable in said frame, said loading chamber tubes being arranged in a unitary plane in said support, the axes of said loading chamber tubes together with the axes of the associated fuse setting means being situated in a vertical plane, and threaded spindles mounted on said support producing a relative displacement between said fuse setting means and said loading chamber tubes.
  • a rocket projector magazine having a first support member, a second support member, said first support member being spaced from said second support member, said support members being mounted on said frame parallel to one another, a bar: on which said support members are guided .at one of their ends, afirst threaded spindle engaging said support members at the other ends thereof, support pieces in said frame,'in which said threaded spindle and said bar are mounted and additional threaded spindles engaging said support pieces mounted in said frame and are joined to each other in-a driving connection, so that spindle.
  • a rocket projector magazine according to claim 2 wherein said frame has a front wall and two side walls and said fuse setting means are mounted on a shaft rotatably mounted in the side walls adjacentisaid front wall.
  • a rocket projector magazine wherein said loading chamber tubes are arranged in two planes, a member rigidly connecting adjacent pairs of tubes, said pairs being pivotally mounted about their centers of gravity, said fuse setting means being arranged in two planes parallel to those of said tubes with their axes separated by a distance equal to that between the tube axes, and in which said means for producing a relative movement comprises a crank drive connected to said tubes and a threaded spindle for axial displacement of said fuse setting means.
  • a rocket projector magazine according to claim 1 in which said fuse setting means are arranged on rotatable slides and are movable to a position in front of said loading tubes and into said loading tubes.
  • a rocket pro ector magazine in which said plurality of loading chamber tubes has a said loading chamber tubes are movable perpendicular to their axes through saidadditional threaded spindles and in parallel to their axes through said first threaded rotary slide and a fuse setting means associated with it.
  • a rocket projector magazine according to claim 7 including common driving means for all rotatableslides which provides axial rotation and displacement from their axes.
  • a rocket projector magazine wherein said frame is square in cross-section enclosing said loading chamber tubes in whichfour tubes are arranged adjacent each wall of said frame, fuse Setting means for each group of three tubes at a corner of said frame, a rotatable arm displaceable axially is associated with each group of three tubes situated outside the fir ing trajectory of the rockets parallel to the tube axes-so that during a complete rotation of the arm said fuse setting means describes a circle containing the axes of each of the three tubes.
  • a rocket projector magazine according to claim 2 in which said fuse setting means are cylindrical and the outer diameter of said fuse setting means is smaller than the inner diameter of said loading chamber tubes.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
  • Handcart (AREA)
US00886151A 1968-12-19 1969-12-18 Rocket projector magazines Expired - Lifetime US3710677A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH1895168A CH502572A (de) 1968-12-19 1968-12-19 Raketenwerfer

Publications (1)

Publication Number Publication Date
US3710677A true US3710677A (en) 1973-01-16

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ID=4436344

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Application Number Title Priority Date Filing Date
US00886151A Expired - Lifetime US3710677A (en) 1968-12-19 1969-12-18 Rocket projector magazines

Country Status (11)

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US (1) US3710677A (de)
BE (1) BE743210A (de)
CA (1) CA919466A (de)
CH (1) CH502572A (de)
DE (1) DE1963035A1 (de)
ES (1) ES374674A1 (de)
FR (1) FR2026576A1 (de)
GB (1) GB1236298A (de)
NL (1) NL6918997A (de)
NO (1) NO130373B (de)
SE (1) SE370119B (de)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3981224A (en) * 1975-07-11 1976-09-21 The United States Of America As Represented By The Secretary Of The Army Missile trans porter-launcher
US4538723A (en) * 1984-08-22 1985-09-03 Harsco Corporation Battlefield magazine
US4538724A (en) * 1984-08-22 1985-09-03 Harsco Corporation Spiral band locking mechanism
USRE32602E (en) * 1984-08-22 1988-02-16 Harsco Corporation Spiral band locking mechanism
US6283005B1 (en) * 1998-07-29 2001-09-04 The United States Of America As Represented By The Secretary Of The Navy Integral ship-weapon module
ITTO20100439A1 (it) * 2010-05-26 2011-11-27 Oto Melara Spa Meccanismo di graduazione per spoletta
US9834999B2 (en) 2011-07-13 2017-12-05 King Kutter, Inc. Post hole digger
CN111547266A (zh) * 2020-05-13 2020-08-18 陕西中天火箭技术股份有限公司 一种多通道可折叠箱式低空探空火箭发射装置
US20240328751A1 (en) * 2023-04-03 2024-10-03 On-Point Defense Technologies, LLC Single armament control unit

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US709301A (en) * 1901-11-01 1902-09-16 Edwin Morris Capps Machine-gun.
US1687644A (en) * 1926-06-17 1928-10-16 Vickers Ltd Fuse-setting device for projectiles
US1796861A (en) * 1921-09-26 1931-03-17 George D Crabbs Prepared roofing
US2295573A (en) * 1938-06-16 1942-09-15 Schneider & Cie Fuse setting apparatus for artillery projectiles
US2930288A (en) * 1955-05-09 1960-03-29 Chance Vought Aircraft Inc Tandem rocket launcher and firing system

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US709301A (en) * 1901-11-01 1902-09-16 Edwin Morris Capps Machine-gun.
US1796861A (en) * 1921-09-26 1931-03-17 George D Crabbs Prepared roofing
US1687644A (en) * 1926-06-17 1928-10-16 Vickers Ltd Fuse-setting device for projectiles
US2295573A (en) * 1938-06-16 1942-09-15 Schneider & Cie Fuse setting apparatus for artillery projectiles
US2930288A (en) * 1955-05-09 1960-03-29 Chance Vought Aircraft Inc Tandem rocket launcher and firing system

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3981224A (en) * 1975-07-11 1976-09-21 The United States Of America As Represented By The Secretary Of The Army Missile trans porter-launcher
US4538723A (en) * 1984-08-22 1985-09-03 Harsco Corporation Battlefield magazine
US4538724A (en) * 1984-08-22 1985-09-03 Harsco Corporation Spiral band locking mechanism
WO1986001586A1 (en) * 1984-08-22 1986-03-13 Harsco Corporation Battlefield magazine
WO1986001587A1 (en) * 1984-08-22 1986-03-13 Harsco Orporation Spiral band locking mechanism
USRE32602E (en) * 1984-08-22 1988-02-16 Harsco Corporation Spiral band locking mechanism
US6283005B1 (en) * 1998-07-29 2001-09-04 The United States Of America As Represented By The Secretary Of The Navy Integral ship-weapon module
ITTO20100439A1 (it) * 2010-05-26 2011-11-27 Oto Melara Spa Meccanismo di graduazione per spoletta
EP2390618A1 (de) * 2010-05-26 2011-11-30 Oto Melara S.p.A. Mechanismus zum Einstellen eines Zünders
JP2011247578A (ja) * 2010-05-26 2011-12-08 Oto Melara Spa 信管取り付け用の機構
US8839705B2 (en) 2010-05-26 2014-09-23 Oto Melara S.P.A. Mechanism for setting a fuse
US9834999B2 (en) 2011-07-13 2017-12-05 King Kutter, Inc. Post hole digger
CN111547266A (zh) * 2020-05-13 2020-08-18 陕西中天火箭技术股份有限公司 一种多通道可折叠箱式低空探空火箭发射装置
US20240328751A1 (en) * 2023-04-03 2024-10-03 On-Point Defense Technologies, LLC Single armament control unit

Also Published As

Publication number Publication date
FR2026576A1 (de) 1970-09-18
SE370119B (de) 1974-09-30
BE743210A (de) 1970-05-28
NO130373B (de) 1974-08-19
CH502572A (de) 1971-01-31
DE1963035A1 (de) 1970-09-03
NL6918997A (de) 1970-06-23
ES374674A1 (es) 1972-01-01
CA919466A (en) 1973-01-23
GB1236298A (en) 1971-06-23

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