US2725790A - Discharge tube for magazine rocket launcher - Google Patents

Description

Dec. 6, 1955 Filed NOV. 4, 1948 DISCHARGE L. O. BERGSTROM TUBE FOR MAGAZINE ROCKET LAUNCHER 2 Sheets-Sheet l @RII NVENTQFL Lms @SQME @E RGETRM Dec. 6, 1955 1 o. BERGSTROM DISCHARGE TUBE FOR MAGAZINE ROCKET LAUNCHER Filed Nov. 4, 1948 2 Sheets-Sheet 2 Fl'h.

IIIIIW.vmllllrllllftllllvlmm DISCHARGE TUBE FOR MAGAZINE ROCKET LAUNCHER Lars O. Bergstrom, Bofors, Sweden, assignor to Aktiebolaget Bofors, Bofors, Sweden Application November 4, 1948, Serial No. 58,247 Claims priority, application Sweden November 7, 1947 2 Claims. (Cl. 89-1.7)

The present invention relates to a rapid re rocket launcher.

The launcher of the present invention is suitable for use with pointed-nosed self-propelled rockets individually encased in open ended sleeves. The rockets are self-propelled in rapid succession through a common discharge tube. A magazine is provided for retaining the rockets and an automatic feeding device advances the rockets simultaneously in laterally spaced relationshiprtoward an ultimate or discharge position whichV is adjacent to and in alignment with the discharge tube.

The discharge rate of the rocket launcher of the present invention is considerably increased by the provision of an enlarged rearwardly haring portion in the discharge tube adjacent to the feeding device. This enlarged portion communicates with Vthe rocket which is in a penultimate position immediately adjacent to the ultimate or-discharge position and the flaring portion is shaped to receive and guide the nose of the rocket which is ready to advance from the penultimate position to the ultimate or discharge position and to direct this rocket into the discharge tube during the combined self-propelled forward movement of the rocket and its lateral advance toward the discharge position by the feeding device.

Thus, the aring portion of the discharge tube permits a rocket to commence its forward self-propelled movement as it moves laterally into alignment with the discharge tube and the interval between the discharges of successive rocketsis materially reduced. p

With the present rocket launcher, it is not necessary to advance each rocket successively to the dischargeposition, ignite the rocket, and then wait in the usual manner for it to enter the discharge tube completely before the next rocket may commence its self-propelled forward movement. While one rocket is in transit in the discharge tube, the next rocket is already in a self-propelled condition and is gradually moving forwardly into the enlarged portion of the discharge tube.

Various objects, features and advantages of the invention will become apparent upon reading the following specication together with the accompanying drawing forming a part hereof:

Referring to the drawing: p

Figure l is a diagrammatic side view of a preferred embodiment of the invention, shown partly in section.

Figure 2 is a transverse sectional view taken along the line lI-II of Fig. l, looking rearwardly in the direction of the arrows. p

Figure 3 is a plan sectional view taken along the line IlI III of Fig. 1. V

Figure 4 is an enlarged transverse sectional view taken along the line lV-IV of Fig. 3, looking forwardly in the direction of the arrows.

Figure 5 is an enlarged fragmentary view of the lower portion of Fig. 2.

Figure 6 is a transverse sectional view taken along the line VI VI of Fig. 3, looking rearwardly in the direction of the arrows.

Vntecl States Patent() formed of cardboard or the like and each sleeve 2 acts as a guide for its encased rocket 1 when the encased rocket first starts moving forwardly in the direction of re. The series of rockets 1 is laterally pressed toward the ultimate position of discharge at which each rocket 1 vacates its tubular sleeve 2. by means of a spring pressed lazy tongs 4. The lazy tongs 4 comprises a plurality of laterally extending compression springs 5 and centrally disposed compression springs 6 which act to extend the lazy tongs 4 and cause the encased rockets 1 to advance laterally and simultaneously toward the ultimate position of discharge. lf the magazine is placed vertically, the feeding may also be effected merely through gravity. At one end piece of the magazine there is fixed a discharge tube 7, the part of which located nearest to the magazine is tapered or flared, converging away from the magazine in the direction of fire so that this part when viewed in section along a plane paralleling the plane of the magazine forms approximately an oblique cone. The bottommost sleeve is retained in the position of discharge or ultimate position in alignment with the discharge tube 7 by two stops 8 provided with supporting rollers 9. Each stop 8 is controlled by a slotted arm 10, w 'ch is rigidly connected with a shaft 11 journalled in the bearing pieces 12 and 13, which are in turn mounted on the magazine 3. At the front end of the shaft 11 there is ixed a short arm l5 which is actuated by a nose 16 mounted on a release flap 17 pivotally mounted in one side of the discharge tube 7. To the rear end of the shaft 11 there is secured an arm 13, Fig. 4, provided with a notch 19 which engages a hook-shaped stop pawl 26. The arm i8 and shaft 11 to which it is keyed are yieldingly urged in a clockwise direction as viewed in Fig. 4 by a helical tension spring 21. A button-ended control rod 22 is connected to the pawl Ztl. The discharge tube 7 is encased by a protective tube 24 provided with a number of holes (not shown) for admitting cooling air.

27 designates U-shaped support beams for the magazine, 28 is a follower bar connected with the lazy tongs 4 and pushing the rockets towards the position of discharge, 29 is a wall portion, 30 is a flange,V 31 another liange, 32 is a bolt to which the tension spring 21 is secured and 33 is release means for the springs 6.

The device functions as follows: v

When in initial position, the discharge sleeves'of the rockets are held barred against lateral advance by the two stops 3 which are controlled by the shaft 11 through slotted arms 10. Shaft l1 is locked by the stop hook 20.

`The discharge of the rockets is normally started in such a manner that the rocket lying in the laterally most advanced discharge sleeve is ignited by switching on the conventional electric ignitor 5G. The rocket then moves longitudinally along the axial direction of the sleeve and presses out the pivotally mounted ap 17. At the end of this movement, the nose 1e of the ilap 17 actuates the stop arm 15 so that the shaft 11 is given a slight turn in the clockwise direction as viewed in Fig. 4. As a result, the pawl 20 is `released from the notch 19 in the arm It. VThe pawl 2), now free, is brought out of its locking position by a compression spring (not shown) which acts on the control rod 22. Unless restored manually as described below, the pawl 20 remains out of its locking position where it can engage in notch 19 throughout the entire period of automatic operation of the device. During this period of automatic operation each rocket l in entering the discharge tube 7 presses the flap 17 outwardly and holds it in this position until it has passed the flap 17. While the ilap 17 is pressed outwardly it arrests 'lateral advance of the rockets by holding the shaft 11 rotated in V'a eounterclockwise position Vas viewed in Figs. 4 and 6 or rotated in a clockwise position as viewed in Figs. 2 and 5. The shaft 11, while in this rotated position, maintains the stop members 8 in blocking position as illustrated in -Figs. 2 and 5 against the yielding action of tension spring 21 (Pig. 4). After the rocket inthe discharge tube '7 has passed ythe ilapf17, the spring 2l rotates the shaft 11 in the opposite `direction to withdraw the stop members S rom'their blocking positions and permit the empty sleeve 25 (Fig. 5) at the ultimate dischargek position to be ejected from the magazine as indicated in dotted outline (Fig. this ysleeve having just been completely vacated by the rear end portion of the discharged rocket which it previously encased before the ap 17 was released. At the same time -that the empty sleeve is being ejected from the magazine, the sleeve 26 in-the penultimate position advances laterally. Before the sleeve '26 in penultimate position reaches the ultimate position of discharge, however, its rocket is ignited by the ignitor Sil and the nose of-the'rocket enters the daring portion of the discharge tube 7. While the sleeve 26 advances laterally, the ignited rocket which it contains simultaneously advances laterally and moves forwardly along the direction of fire into the flaring portion of discharge tube '7 and in the course of this forward movement its nose is guided into the discharge tube 7 and thereafter it presses iiap leoutwardl-y so that the stop Vmembers 3 again move into blocking position before the forwardly moving rocket has vacated its sleeve at the ultimate discharge position.

The follower bar 28 of the lazy tongs 4 continuously presses on the sleeves Z so that the rockets are successively laterally advanced and discharged until the magazine 3 is empty. Because the rocket which is-advancing laterally from the penultimate position to the ultimate position is already ignited and moving forwardly in the direction of fire, the rockets may follow each other through the discharge tube 7 at extremely short intervals withoutwaiting for the next rocket which is to be discharged to reach and come to rest -in the ultimate position before it is ignited.

Ignition of the rockets may be .performed in any convenient manner, for example as shown in U. S. Patent No. 2,459,314. of conventional construction is shown positioned adjacent Lto the rear of the magazine 3 where it is arranged to ignite each rocket lI1 after it reaches the Vpenultimate position and prior to the time when it arrives 4at the ultimate position in alignment with the discharge tube '7. An energizing circuit for the ignitor 50 is shown comprising a source of electrical energy indicated as a battery landa control switch S2.

lf it is desired to stop the discharge of the rockets 1 before the magazine 3 is empty, the switch -52 is opened and upward pressure is exerted manually on the lower button-shaped end of control rod 22 (Fig. 4). Control rod 22. then moves the pawl 26 into engagement in notch 19 thus locking shaft 11 in the position where the stop members 3 are in the blocking position which they assume each time that flap 17 is pressed outwardly.

The device according to the invention involves among other the following advantages: The cardboard sleeve 25 or 26 kencasing each rocket, which sleeve can be said vto For purposes of illustration, an ignitor form the rst part of the discharging tube, binds the 65 foldable steering wings of the rocket and simplifies the electric current supply. The sleeve in combination with -the -tapernof-.therigid discharging `tube makes. an earlier discharge possible so that the tire rapidity is increased, since no inserting and fixing in a xed position is needed, as is the case in other automatic weapons. The sleeves are ejected only when the release ap 17, placed in the rigid discharging tube is not actuated by the latest rocket discharged fmmthemagaZine. At the start, the rockets are accelerated by the lsprings 6 which operate in the moving direction, so that the feeding obtains a great speed already from .the start. Even failing rockets are ejected, so that the discharging of the following rockets goes on automatically. When a rocketis not tired, it falls. down, as the stops .8 will not come to the non-locking position.

Having now described my invention, what I claim as new and desire to secure by Letters Patent is:

1. ln combination with a magazine for pointed-nosed self-propelledrockets, a common discharge tube through which said rockets are to be successively self-propelled, feeding means lfor simultaneously and successively advancing a'pluraility of said rockets in laterally spaced rela` tionship toward'an ultimate discharge position adjacent tothe rear -end of said ydischarge tube and in alignment therewith satwhich ultimate position the most advanced of said lrocket in said feeding means may completely enter 4and pass through said tube, and means connected to said feeding means and actuated by each rocket in the course of its passage through said discharge tube for advancing'said feeding means to br-ing the next rocket in saidV feeding means into said ultimate position, the provision of: a-rearwardly haring enlarged portion in said discharge tube `adjacent'to said feeding means, said flaring Aportion'cotnnnlnicating with the rocket which is in a'penultimate position adjacent to said ultimate position, -saidfflaring yportion being shaped to receive the nose of-'saidlrocket :in said penultimate position and guide it into -said discharge tube during the combined lateral advance V.of said ioeketby said feeding means from said penultimate positionto said lultimate position and forwardl movement which occurs when the said rocket is ignited as it leaves said penultimate position and prior to its arrival -at -said Vultimate position.

2.1'The combination according to claim l, in which said rocketnctuated means comprises a flap member pivotally mounted irrsaid .enlarged portion of said discharge tube, said flap member being actuated once by each rocket in the course'of its longitudinal movement out of its sleeve andvthroughssaid discharge tube.

References `Cited in the ijle of `this patent f-U'NITED STATES PATENTS

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