US3182553A

US3182553A - Rocket launcher and end covering means therefor

Info

Publication number: US3182553A
Application number: US319073A
Authority: US
Inventors: Paul V Choate; Charles B Weeks
Original assignee: HESSE EASTERN Inc
Current assignee: HESSE EASTERN Inc
Priority date: 1961-11-13
Filing date: 1963-10-25
Publication date: 1965-05-11
Anticipated expiration: 1982-05-11
Also published as: CH400838A; US3138064A; NL278018A; GB992240A; DK117932B; DE1221112B

Description

a 1 ms w, m E l a W M J m F v mam M a 3 e C N e S. R m W RL W mm A Y B P V CHOATE ETAL ROCKET LAUNCHER AND END COVERING MEANS THEREFOR May 11, 1965 Original Filed Nov. 13, 1961 y 11, 1965 P. v. CHOATE ETAL 3,182,553

ROCKET LAUNCHER AND EN'D COVERING MEANS THEREFOR Original Filed Nov. 13, 1961 3 Sheets-Sheet 2 ms mo 2 w: mw M ..NSC E V. mm m mm" m E l 97 Q I H. mm 3 8 I II I IL I III I ww 2. mm mm 3 mm B I m 1 0 oh mm I x Nb 0 m9 v w a 6 mm 3 mm mw mm mm mm F x ow 8 m @E ATTORNEY y 1965 P. v. CHOATE ETAL, 3,18%553 ROCKET LAUNCHER AND END COVERING MEANS THEREFOR Original Filed Nov. 13, 1961 3 Sheets-Sheet 3 I02 58) I050 A 1 7 53 v 54 i INVENTORS CHARLES B. WEEKS Y PAUL V. CHOATE ATTORNEY United States Patent .0

3,182,553 RGUKET LAUNCHER AND END COVERlNG MEANS THEREFQR Paul V. Qhoate, Milton, and (Iharles B. Weeks, Reading,

Mass., assignors, lby mesne assignments, to Hesse- Eastern, Inc, Everett, Mass., a corporation of Delaware Original application Nov. 1?, 1961, Ser. No. 151,894, new Patent No. 3,122,059, dated Feb. 25, 1964. Divided and this application Get. 25, 1963, Ser. No. 3ll9,d73 4 Claims. (Cl. 591.7)

The present invention relates to launchers for rockets and particularly to such launchers that are adapted to be manufactured at relatively low cost and to be easily carried and effectively used by an infantryman against a tank or fortified position and to combinations of rockets with such launchers and to combinations of sights and such launchers. This application is a division of our co-pending application, Serial No. 151,894, filed November 13, 1961, now US. Patent No. 3,122,059.

The general objective of the invention is to provide such a launcher and this objective is attained by providing a launcher comprising a barrel consisting of first and second tubular sections interconnected to telescope between a shortened inoperative position and an extended operative position. The firing pin and firing spring are carried by the first section that constitutes the breech end of the launcher and the trigger mechanism is carried by the second section that constitutes the muzzle end of the launcher and is connected to the firing pin by an element attached to the second section. A trigger controlled release, which includes a sear, is carried by the second section. A member is connected to the element and is movable into and out of its engagement with the sear. The engagement of the movable member with the sear is ineffective to move the firing pin into its cocked position in the inoperative position of the launcher, the cocked firing pin position then being established by the extension of the sections to establish said operative launcher position.

The rocket launcher, in its shortened, inoperative position constitutes a container for a rocket and is readied for use by extending the launcher into its operative position, releasing the safety, and actuating the trigger. It is essential that the sections be so held, in their shortened position, as to prevent the rocket launcher from accidentally becoming operative and for assurance against malfunctioning, to close the breech and muzzle ends of the launcher. In accordance with the invention, this objective is attained by connecting the muzzle or front cover to a breech or rear cover by a resilient connector. The rear cover is locked to the breech end of the launcher by a release pin so the user has but to pull the release pin and free the rear cover. The front cover and connector then fall free of the launcher. The user then pulls the breech or first section rearwardly relative to the muzzle or first section to extend the launcher into its operative position. Releasable means are provided to interlock the section in the operative launcher position.

In the accompanying drawings there is shown an illustrative embodiment of the invention from which these and other of its objectives, novel features, and advantages will be readily apparent.

in the drawings:

FIGURE 1 is a side elevation of the rocket launcher in its shortened, inoperative position,

FIGURE 2 is a like view of the rocket launcher in its extended, operative position,

FIGURE 3 is a section, on an increased scale, taken approximately along the indicated lines 33 of FIG- URE 2,

FIGURE 4 is a fragmentary section, on an increased scale, through the firing pin housing and the rear of the 3,l82,553 Fatented May ll, 1965 breech section to show a projectile locked therein against unintended forward movement,

FIGURE 5 is a fragmentary view of the muzzle end of the second launcher section with the front sight shown in its erected position,

FIGURE 6 is a section taken approximately along the indicated lines 6-6 of FEGURE 5,

FZGURE 7 is a vertical section through the trigger mechanism housing,

FIGURE 8 is an exploded view showing the main parts thereof in perspective,

FEGURE 9 is a section taken vertically through the rear sight,

FIGURE 10 is a front view of the rear sight with its cap removed,

FIGURE 11 is a view of the breech end of the launcher with the rear cover in place,

FIGURE 12 is a fragmentary elevational view of the undersurface of the launcher showing certain details of the connector for the covers,

FIGURE 13 is an elevational view of a lock for holding a rocket against forward movement, and

FIGURE 14 is a fragmentary, horizontal section through the firing pin housing showing the lock against accidental rearward movement of the firing pin.

In accordance with the invention, a rocket launcher comprises first and second

tubular sections

29 and 21. The section 20 is the breech section and slidably fits within the section 21 which is the muzzle section and is shorter than the latter so that its forward end presents an annular shoulder 22.

The section Ed has at least one lengthwise diametrically opposed, groove 23 which terminates short of its ends and receives a pin 24 extending through an opening 25a in the band 25 on the rear end of the section 11. The pin 24 is fixed to the rear end of an arm 26 whose forward end is urged outwardly by a spring 27 backed by the mount 28 to which the arm 26 is pivoted as at 29, see FIGURE 3. At the forward end of the mount 28 there is a pivot 39 supporting a release 31 yieldably urged by a spring 32 to position its shoulder 33 under the arm 26 to block its movement against the action of the spring 27 thus to prevent the pin 24 from moving outwardly under the load exerted thereon during firing. The spring 32 also urges the end of the release 31 upwardly between the forked ends 26a of the arm 26 so that on manual engagement, the shoulder 33 is moved forwardly out of its position in which movement of the arm 26 is blocked. A thin strip 34 is attached to the arm 26 and overlies the release 31 so that when the forward portion of the boot 35, sealed to the tube 21 to prevent leakage, is pressed inwardly, disengagement of the release 31 and actuation of the arm 26 will result to move the pin 24 outwardly. When the

launcher sections

26 and 21 have been pulled apart to the maximum extent, the spring actuated pin 24 enters into a depression 213A at the front end of the groove 13 thus to lock the rocket sections in their extended posi tion as is necessary for use of the launcher while permitting them to be released so that the rocket sections may be again telescoped. An 0 ring 36 is located between the band 25 and the band 37 fast on the rear end of the rocket breech section Zil.

The upper surface of the section 21 also is provided with a generally indicated, trigger mechanism housing 38, and between the rearmost band 39 and the band 25 there is a channel 40 on the lower surface of the section 21. An arm 41 is pivotably connected to the rear of the channel 4%, supporting, at right angles, the rear cover 42 which is provided with a compressible seal face 4-3 and adjacent which there are transversely disposed channels 44, see FIGURES l and ll.

In practice, a cover 45 having a compressible seal face enemas inoperatively positioned launcher section and locked in that position by providing the cover 42 with an apertured tab '53 fitting over a rearwardly disposed projection 54 of the firing pin housing cover 54a. The projection 54 has a transverse bore which receives the keeper pin 55. An adjustable carrying sling 56 is attached to the yoke 47 and to the rear section 49. of the connector.

With this construction, the rocket launcher may be conveniently carried in its shortened, inoperative position and quickly prepared for use by pulling the pin and disengaging the cover tab 53 from the projection 54 and swinging the rear cover away therefrom. The front cover 45, the strap 48. and its

sections

49 and 50 fall free While the rear cover 42 swings downwardly out of the way. The launcher sections may then be extended for use as by holding the section 21 with one hand and pulling the section 28 by means of the loop 57 carried by the band 37 until the pin24 interlocks the sections when the operative launcher position is'established, as above described.

The band 37 supports a forwardly extending housing 58 which is spaced so as not to interfere with movement of i the section 21. A receiver 59, having a forwardly disposed opening, is mounted on the housing 58. In the inoperative position of the launcher sections, the receiver 59 houses the end of a generally indicated rear sight 69 whichispivoted as at 61 between arms 62 of a mount 63 attached to the rear of the housing 38 and urged into an erect position by a spring 64 against a stop 65 which the rearward edge of the mount 63 provides. As the rocket sections are extended, the rear sight 61) is freed to erect itself into its position of use.

It will be noted that there is a band 66 adjacent the frontend of the section21. The band 66 has spaced ears 67 for the pivot 68 of a generally indicated front sight 69 which is biased upwardly into an erect position of use by the spring 69a. The front sight 69 includes a mount 70 which receives the pivot 68 and carries a clear plastic being sealed by the seal 72. When the front cover 45 falls free, as above described, the spring 69a erects the front sight 69, with the mount 70 seated against the section 11 to provide a positive position of use.

It Willbe noted that the sheet 70 has a central vertical line 74 with vertically spaced, transverse graduations 75 marked thereon and that the target is visible therethrough, the graduations 75 decreasing in length as the indicated target distance increases. Markings 76 are also provided to assist the firer in leading moving targets.

The rear sight 60, see FIGURES 9 and 10, is shown as consisting of a member 78 of U-shaped cross section and having upper and lower openings 79 and 80, respectively.

A strip 81 is clamped thereto as by bolts 82 passing channel 78 and has a resilient detent arm 88 engageable' with either slot 86 to then bring itsslots 89 into registry with the appropriate one of the sight holes 85. In practice, the upper end ofv the sight is protected by a proteclg tive, safety rubber cap 90 having alined Windows 91 in its front and back walls and used to prevent any chance of the user being injured by contact with the rear sight 69 while sighting and firing the launcher.

The rear sight 68 is important to accuracy when its projectile, the generally indicated rocket 92 is powered by solid fuel as variations in performance result with the temperature. A higher trajectory is attendant cold weather so that the upper sight hole 85 is then used.

It will be noted that the rocket 92 has an intermediate shoulder 93 engageable with the shoulder 22 and thereby held against rearward movement, and that its rear part, see FIGURE 4, including its folded, pivoted fins 94, which are urged outwardly in flight by springs 95, is housed wholly by the section 20. In practice, it is desirable to prevent the rocket 92 from moving forwardly unless fired. To that end, see FIGURES 4 and 13, a lock 96 is provided that is apertured at 97 to be anchored by an attached fin 94. The lock 96 is formed from a metal strip and has an intermediate twist 98 so that the rear end 99 may pass through a slot 100 in the rear cover 42, the rear end 99 having a stop 101 engageable with the rear cover 542 of the firing pin housing 58. In practice, the keeper pin 55, for locking the rear cover 42, includes a parallel pin 55a for entry through the hole 99a in the exposed lock end 99. When the

pins

55 and 55a are removed, the launcher may be extended into its operative position and while the rocket is secured by the lock 96 in its launcher against forward movement, the thrust of its ignited charge is great enough to readily bend the lock 96 and its stop 1831 thus to free it. v i

It will be noted from FIGURE 4 that the housing 58 receives the cap 182 of a projectile igniter whose tube 103 extends downwardly through a passage 104 for connection with the main igniter of the motor (not shown) of the rocket 92. A firing pin 105, which may best be seen in FIGURE 4, is urged forwardly in a bore 106 by a spring 107, held within the housing 58, and the forward end of the pin 195 is connected to a cable 188 extending forwardly into the trigger housing 38 where it 7 passes over an element 109 in the form of an idler roller see FIGURES 7 and 8. The cable 108 is fastened to a reel 110 rendered self-winding by means of the springs V I 111. The firing pin 105 is shown as having ,at its rear end, a taper 105a and a contact portion 105b at its extremity for striking the igniter cap 182.

The roller 1129 is confined in transversely alined guide- .ways 112 in the housing 38 each having an inturned flange llfa overlying a slidable roller guide 114 for the slidable cocking actuator 115. The cocking actuator has ears 116 for engaging the roller 109 and is inovedforwardly against the action of its return spring 117 by means of the rod 118 which passes forwardly through the seal 119 and provided with a grip 119a for manual engagement by the user. The forward end 120 of the guide 114. and of the guideways 112 and the ears 116 are upwardly inclined so that in its forward position, the roller 109 is raised ahead of and'blocked against rearward movement by the sear 121 which is pivoted at 122 adjacent its rear end. It will be noted that the actuator 115 has a transverse pin 115a between the shou ders 114a of the guide 114 by which the guide 114 is moved forwardly slightly to permit the positioning of the roller 189 ahead of the sear 121 and by which the guide 114 is again moved forwardly when the grip 119a is released to permit the spring 117 to operate. The forward end of the sear 121 is connected as at 123 to trigger 124 pivoted at 125 between its ends andcovered with a protective, Waterproof boot 126. When the rearward portion of the trigger 124 is depressed, the sear 121 is raised to release the roller 109 which is then driven rearwardlyby the firing pin spring 107 unless the safety 127 is in its rearward position blocking sear movement. The safety 127 has a pull rod 128 extending through the seal 119 and terminating in a handle 129. In practice, a dethe launcher is thus extended the length of the cable is such that the firing pin spring 107 becomes fully loaded and the firing pin 105 is moved forwardly relative to the rear section into its cocked position. It is possible that should the roller 109 be in its full line position seated against the cocking actuator ears 116, it could be pulled forwardly manually but the spring 107 is of such strength that the risk of the actuator rod 118 slipping from the users grasp, with a consequential accidental release of the firing pin 105, is great.

Such an accident is prevented by means of a removable locking pin 131 which is inserted in a bore 132 in the firing pin housing 38, seeFIGURES 4 and 17. The pin 131 has a pointed end 133 so that it is operative to engage the taper 105a and to force the firing pin 105 forwardly. The pin 131 is also provided with an annular groove 134 which receives the end of the pin 105 so that it becomes locked against removal until the firing pin 105 is in its cocked position which, as above indicated, is possible only when the launcher is in its extended, operative position.

We claim:

1. In a rocket launcher, first and second tubular sections connected to telescope between a shortened, inop erative position and an extended, operative position, one end of said first section being the breech end of the launcher, the opposite end of the second section being the muzzle of the launcher, a pair of end covers, a strap having resiliency and including end connections, each with an appropriate one of said covers, the connection between said strap and said breech end cover being a hook detachably caught on the edge thereof, a pull-pin connection between said breech cover and said first section opposing the strap resiliency, the connection between the strap and the muzzle cover applying the strap resiliency to seat said muzzle cover against said muzzle end when the breech end cover connection is operative, said strap and muzzle cover being freed and the launcher sections being freed to be extended into said operative position when said pullpin is removed and said breech cover is opened.

2. In a rocket launcher, first and second tubular sections connected to telescope between a shortened, inoperative position and an extended, operative position, one end of said first section being the breech end of the launcher, the opposite end of the second section being the muzzle of the launcher, a pair of end covers, a strap having resiliency and including end connections, each with an appropriate one of said covers, the connection between said strap and said breech end cover being a hook detachably caught on the edge thereof, a pullpin connection between said breech cover and said first section opposing the strap resiliency, the connection between the strap and the muzzle cover being a yoke whereby the strap resiliency exerts cover-seating pressure transversely of the muzzle cover, said strap and muzzle cover being freed and the launcher sections being freed to be extended into said operative position when said pull-pin is removed and said breech cover is opened.

3. In a rocket launcher, first and second tubular sections connected to telescope between a shortened, inoperative position and an extended, operative position, one

end of said first section being the breech end of the launcher, the opposite end of the second section being the muzzle of the launcher, a pair of end covers, the end cover for said breech end including an arm disposed at right angles thereto and pivotally connected to the rear part of the second section, a strap having resiliency and including end connections, each with an appropriate one of said covers, the connection between said strap and said breech end cover being a hook detachably caught on the edge thereof, a pull-pin connection between said breech cover and said first section opposing the strap resiliency in a zone opposite to its connection with said strap hook, the connection between the strap and the muzzle cover applying the strap resiliency to seat said muzzle cover against said muzzle end when the breech end cover connection is operative, said strap and muzzle being freed and the launcher sections being freed to be extended into said operative position when said pull-pin is removed and said breech cover is opened.

4. In a rocket launcher, first and second tubular sections connected to telescope between a shortened, inoperative position and an extended, operative position, one end of said first section being the breech end of the launcher, the opposite end of the second section being the muzzle of the launcher, a pair of end covers, a strap having resiliency and including end connections, each with an appropriate one of said covers, a carrying strap attached to said first named strap between said connections, the connection between said first named strap and said breech end cover being a hook detachably caught on the edge thereof, a pull-pin connection between said breech cover and said first section opposing the strap resiliency, the connection between said first named strap and said muzzle cover applying the strap resiliency to seat said muzzle cover against said muzzle end when the breech end cover connection is operative, said first named strap and said muzzle cover being freed and the launcher sections being freed to be extended into said operative position when said pull-pin is removed and said breech cover is opened.

No references cited.

BENJAMIN A. BORCHELT, Primary Examiner.

Claims

1. IN A ROCKET LAUNCHER, FIRST AND SECOND TUBULAR SECTIONS CONNECTED TO TELESCOPE BETWEEN A SHORTENED, INOPERATIVE POSITION AND AN EXTENDED, OPERATIVE POSITION, ONE END OF SAID FIRST SECTION BEING THE BREECH END OF THE LAUNCHER, THE OPPOSITE END OF THE SECOND SECTION BEING THE MUZZLE OF THE LAUNCHER, A PAIR OF END COVERS, A STRAP HAVING RESILIENCY AND INCLUDING END CONNECTIONS EACH WITH AN APPROPRIATE ONE OF SAID COVERS, THE CONNECTION BETWEEN SAID STRAP AND SAID BREECH END COVER BEING A HOOK DETACHABLY CAUGHT ON THE EDGE THEREOF, A PULL-PIN CONNECTION BETWEEN SAID BREECH COVER AND SAID FIRST SECTION OPPOSING THE STRAP RESILIENCY, THE CONNECTION BETWEEN THE STRAP AND THE MUZZLE COVER APPLYING THE STRAP RESILIENCY TO SEAT SAID MUZZLE COVER AGAINST SAID MUZZLE END WHEN THE BREECH END COVER CONNECTION IS OPERATIVE, SAID STRAP AND MUZZLE COVER BEING FREED AND THE LAUNCHER SECTIONS BEING FREED TO BE EXTENDED INTO SAID OPERATIVE POSITION WHEN SAID PULLPIN IS REMOVED AND SAID BREECH COVER IS OPENED.