US2870677A

US2870677A - Missile retaining device

Info

Publication number: US2870677A
Application number: US486039A
Authority: US
Inventors: Herrmann Fred
Original assignee: Individual
Current assignee: Individual
Priority date: 1955-02-03
Filing date: 1955-02-03
Publication date: 1959-01-27
Anticipated expiration: 1976-01-27

Description

Jan. 27, 1959 F. HERRMANN 2,870,677

' MISSILE RETAINING DEVICE Filed Feb. 3, 1955 INVENTOR. Fre Herrmann @10 finaa'rr mam-x5.

'riphery of the launching tube 1.

United States Patent MISSILE RETAINING DEVICE Fred Hermann, West Englewood, N. J., assignor to the United States of America as represented by the Secretary of the Army Application February 3, 1955, Serial No. 486,039 6 Claims. (Cl. 89-1.7)

This invention relates to a missile retaining device more specifically to a device for retaining a missile such as a rocket in its firing position in a launching tube.

It is a primary object of this invention to provide a missile retaining device of symmetrical design, compact and easily attached to a launching tube.

A further object of the invention is to provide a retaining device possessing substantially the same durability and life as the launching tube itself and having a high break loose yet requiring only a low initial force to load.

Another object of the invention is to provide a retaining device completely automatic in operation.

A still further object is to provide a retaining device.

cheaply constructed and easy to service.

Other objects and advantages will become apparent during the course of the following description and upon examination of the accompanying drawing in which:

Figure l is a longitudinal sectional view of a retain-- ing device constructed in accordance with the invention and applied to a launching tube as shown in a plane identified by line 1-1 of Figure 2, a

Figure 2 is an end view of the missile launching tube illustrated in Figure l,

Figure 3 is an exploded perspective'view of the various components of the retaining device, and Figure 4 is a plan view of one retaining device taken in the plane 44 of Figure l and looking in thedirection of the arrows.

Referring now more particularly to the drawings, ref- I erence character 1 denotes generally a launching tube provided with a series of longitudinally disposed fins 2 integral with the inner periphery of the tube and extending radially inwardly towards its axis. 3 to a distance such that their free edges are separated a distance equal. to the outside diameter of the bourrelet ring 4 of the boost; er portion of a missile 5. Legs 2 normally extend to the one end 8 being of concave contour to fit the outer pe-;

riphery of the bourreletring 4 of missile and the opposite' end 9 being of convex contour to fit the inner pe- The end 9 of the housing 7 is provided with a pair of longitudinally aligned threaded taps 10 to receive screws 11 whereby the house a ing is attached to the inner periphery of the rearward edge of the tube to prevent rotation of the housing and to securely fasten it to the tube 2. The housing 7 is provided with a pair of longitudinally aligned

wells

12 and 12a bored from the concave end 8 to a distance deep' enough to completely contain a pair of locking plungers 13 and 13a. The plungers 13 and 13a are axially bored at their upper ends as at 14 to provide a receptacle for coil springs 15 and 15a which act, 'in an obvious manner, to urge the plungers radially inwardly of the tube 2. Means for retaining the plungers 13 and 13a in the respective wells areprovided by cap screw 16 which is engaged in a threaded tap 17. As shown upon Figure 1 the head of screw 16 fits within a counterbore 18 extending axially with tap '17." Both mp 17 and counter- 2 I bore 18' are located centrally between

wells

12 and 12a and the well 18 is of a diameter greater than the separation of bores or

wells

12 and 12a so that the head of screw 16 when threaded into tap 17 overlaps bores 12 and 12a whereby the plungers are retained in their respective wells against the thrust of springs 15 and 15a. For this purpose concave notches 19 are formed on the lower part of the inner sides of plungers 13 and 13a as best seen in Figure 3. When the plungers are intheir position in the respective wells and the cap screw -16is threaded into assembled position, the head of screw 16' will rest in milled out spaces 19, and, in a manner obvious from inspection of Figures 1, 3 and 4, the plungers are retained in their respective bores and also prevented from turning therein. Due to springs 15 and 15a the plungers .are urged towards the bourrelet ring 4. The relative radial dimensions of

bores

12 and 12a and plungers 13 and 13a are such that the latter may be completely contained within the bores upon passage of the bourrelet ring 4 under them. As best viewed upon; Figures 1 and 3, the plungers 13 and 13a are provided with beveled surfaces 21 and 22. The planes of bevels 21 make a smaller angle with the axis of the respective plunger than the planes of bevels 22 thus making it easier to push the bourrelet ring 4 of missile 5 into position be tween the fingers 13 than to release it from such position. lodgement of the bourrelet ring 4 from between the plungers 13 and 13a when the missile 5 is in firing position.. Also, the plungers are provided with longitudinal slots 23 and 23a (see Figures 1 and 3) so that when the component parts of the retaining device 6 are in assembledrelation these slots are coplanar with one an-.

other and also with notches 24 cut in housing 7 to therehousing 7 to gases, suitable chamfers 25 have been cut on the edges of the housing. (See Figure 3.) I

W'hile only two retaining devices 6 have beenillus trated diametrically positioned within tube 2, more can, v

be added if desired, in which event they will beequiangularly spaced about the inner periphery of the tube, The tubes are preferable made of stainless or-other-cor rosion resistant steel.

. In order to mount a retainer on a launching cap 'screw 16 is threaded into place.

The operation of the device is completely automatic.

The missile 5 is inserted into the tube 1 in a rotational position which will let the fins 26 clear the retaining dcvices and fins 2 (see Figure 2), and then the-missile isg pushed in the tube until the bourrelet ring 4 snaps be-,

tween plungers 13 When the rocket is fired, the thrust down the tube.

It will be apparent from the foregoing thatI-have provided a simple, yet dependable retaining device which,

" is positive and'reliable in operation and extremely-easy to repair, service and replace; All plungers are duplicates and hence interchangeable. Hence it is not neces-y sary to replace the entire assembly'as any. part .canfbe;. l a 1Y; P d.- .Ths snl g oo rsq ireqgiis "a screw driver.

Bevels 21 will therefore prevent accidental dis-- tube,- the fins 2 are cut away at their rearward ends over-a; length equal to the length of a retaining device tobe. mounted. .Screws 11 are then inserted throughaholcs drilled in the tube and into taps 10. "The springs .15 and fingers 13 are then inserted into the wells 12 andthe It is to be understoodthat the form of the invention herewith shown and describedis to be taken as a preferred example of the same, and that various changes in the shape, size and arrangements of parts may be re-. sorted tofwithout' departing" from; the spirit of my invention; or the scope of the subjoined" claims;

1. a mechanism for releasably retaining a self-propelledmiss'ile inlaunching positi'onwithin a tube, a'hon ing adapted for" rigid securernent to the inner periphery ofsaid t'u'be, there being a pair of bores radially dispnsed in spaced relation in said' housing with their axes in a common plane through the axis of the tube, said housing having a notch in the wall between each said horeand the respective forward and rearward face there'- I of; a pair of plungers each fitting a respective bore;

h said plunger having a slot in its inner end said slots "g disposed in coplanar relation with one another to a continuous passage with said notches in said housing longitudinal of said tube, a coil spring in each bore urging'each plunger radially inwardly, and a cap sfe'rew' fixed with said housing between said bores and engaging both said plungers to prevent rotation'fof said plungers and limiting radial inward movement thereof under'ur' e'of said coil springs. i

' 2'. In a device for releasably retaining a self-propelled missile having abourrelet ring fixed coaxially' about its rearwardend, a launcher tube of greater diameter than- I the bourrelet ring, a housing rigidly secured to the inner periphery of said tube at the breech end thereof, there being first and second boresin said housing disposed radially ofsaidtube with their axes in a common plane through the axis of said'tube, said housing having a notch;

in-- the wall between each said bore and the respective forward and rearward face thereof, a pair of plungers each 'slidably mounted in a respective bore, each. said plunger'having a slot} in its inner end', said slots being disposed in coplanar relation with one another to form V a eon'tinuouspassage with said notches in said housing longitudinal of saidtube, spring means carried by said housing and urging ea ch'plunger radially inwardly, and a cap screw fixed with said housing and engaging both said plungers to prevent rotation and limit radial inrearward end 'in radially spaced relation therewithya launcher tube of greater diameter than said ring, at least one'hou'sing rigidly fixed to the inner periphery of said tube at the breech end thereof, there being a pair of spaced bores in said housing with their axes in a comrnon plane through the axis of'said tube, said'housing having a notch in the wall between each said bore and the respective forward and rearward face thereof, a pair of plungers each slidably' fitting a respective bore, each said plunger having a slot, in its inner end, said slots being disposed in coplanar relation with one another to forina continuous passage with said notches in said housing longitudinal of said tube, a spring in each bore urging its plunger radially inwardly, and a single screw threaded into said housing between said bores and havmg a head overlapping said bores, said head fitting recesses in said plungers whereby said plungers are prevented fromrotation and limited in outward movement, said ring releasably fitting between said plungers when the missile is in firing position in said tube.

[4. In a missile retaining devicefor indexing a missile in firingposition in a launching tube comprising, a housnig'jrig'idIy' securedto the inner wall of said tube, a pair oispring-biased indexing plungers slidably mounted with- .in apair of spaced bores in said housing disposed radially' to the longitudinal axis of the launching tube, said housing and said plungers having aligned slots along .ward movement thereof, said ring releasably fitting be-, tween said plungers when the missile is in launching potheir inner faces to form a continuous passage longitudinal of'said tube, and'a ca'p screw fixed with said housing and disposed medially between said bores and retaining said plungers in said bores 'and limiting their radial travel therein, said'plungeis' being completely contained in said bores; when biased outwardly by the pass-.

the radial direction no t greater than the corresponding; dimension of saidfins, there being a pair ofaxially spaced hor es in each housing having their axes radial to the axis of said tube each? said housing having a groove in the wall between the respectit'e forward and rearward" face thereof, a pair of plunger-s each slidably fitting a respective bore each said plunger having a groove in its inner end and being disposed in coplanar relation with: each other to form a continuous passage with'said grooves in said housing longitudinal of said tube, a cap screw threaded into said housing between said bores and having its head overlapping each bore, said plungers being.

cut away at their" radiallyinward ends to accommodate thehead' of said screw, whereby said plungers are prevented from rotation in" said bores andlimited to translation frorn'a first position entirelyhoused within said b'o'res, to a second position projecting a short distance only therefrom, f

' 6. The combination with a rocket launcher tube hav-; ing a plurality of equiangularly-spaced, longitudinally and radially-inwardlyextending guidefins whose longitudinal inward edges define a circle of substantially the same diameter as" a ioclifetT'toj be launched therefrom, at least twoof apair of diametrically opposed fins being'cut away at their. rearward ends to accommodate a pair of substantially rectangularhousings having avconeave inner face rigidly secured'to theiinnef peripheryof said launching tube, each said housing havinga pair of spaced-bores disposed radially of said tubethere being a groove in its inner face communicating between each said bore, and the respective forward and-rearward end of aid] housing, a plunger in" each said bore said'plunger having, a groove in its inner end disposed in longitudinal align; menfwith the corresponding. "groove in the adjacent. plunger, said grooves ijn.saidho usingforming continuous I passage parallel with thea-xis of'said tube, a coil qspring in each said" here, normally urgingsaid plungers in:

wardly, said plbng'ersbeing-beveled on their outer ends, in two angularlyrelated planes, said planes intersecting in a line perpendicular to means of said tube, the confronting bevelso said plungers beingv at alesser angleto lilngers, than the second bevels, and re- 2,460,929 Gofi 'Feb. 8, 194g,

701,984 Teree Feb. 15 1955",

2,712,270 Green- July 5, 19-55 a FOREIGN-PATENTS 1 9 14341 France June- 17, 19 14 fsl f o limiting movement of saidi'plungersin