US3132442A

US3132442A - Toy missile and launcher

Info

Publication number: US3132442A
Application number: US122814A
Authority: US
Inventors: Barr Josiah Morrison
Original assignee: AMF Inc
Current assignee: AMF Inc
Priority date: 1961-07-10
Filing date: 1961-07-10
Publication date: 1964-05-12
Anticipated expiration: 1981-05-12

Description

May 12, 1964 J. M. BARR 3,132,442

Toy Mrssmz AND LAUNCHER Filed July 1o, 1961 4 Sheets-Sheet l May 12, 1964 J. M. BARR 3,132,442

TOY MISSILE AND LAUNCHER Filed July l0, 1961 4 Sheets-Sheet 2 l INVENTOR. www/Maze/fm/ ee May 12, 1964 J. M. BARR 3,132,442

TOY MISSILE AND LAUNCHER Filed July l0, 1961 4 Sheets-Sheet 5 May 12, 1964 Filed July l0 1961 J. M. BARR 3,132,442 TOY Mrssms AND LAUNCHER 4 Sheets-Sheet 4 p invention.

Patented May 12, 1964 A 3,132,442 'l'Y MISSILE AND LAUNCHER Josiah Morrison Barr, Manhattan Beach, Calif., assigner to American Machine (it Foundry Co., a corporation f New Jersey Filed July 10, 1951, Ser. No. 122,814

7 Claims. (Cl. tti- 77) This invention relates to toy missiles and more particularly to the equippingof toy aircraft, or other toys, with releasable, self-propelled missiles and missile launchers.

It is an object of this invention to provide a selfpropelled, releasable toy missile and a missile launcher for such toys as toy aircraft, or other movable or stationary toys, such as a toy comprising only a missile launcher equipped with aplurality or" missiles.

It is also an object of this invention to provide means for mounting and releasing toy missiles from toy aircraft and other toys.`

It is still another object of this invention to provide a remote control mechanism for releasing self-propelled missiles from a missile launcher.

Additional objects of this invention will be understood more clearly from the Idescription of the invention given in connection with the accompanying drawings.

The novel features which are believed to be character- `istic of the invention, both as 'to its organization and method of operation, together with further objects and advantages thereof, will be better understood from the following description considered in connection with the accompanying drawings in which several embodiments of the invention are illustrated by way of example. lt is to be expressly understood, however, that the drawings are vfor the purpose of illustration and description only, and are not intended as a definition of the limits of the FIG. 1 is a perspective view of a toy aircraft with the missiles mounted on the wings of the aircraft.

FIG. 2 is a top plan wiew of a missile.

FIG. 3 is Ia sectional View of a missile, missile launcher and oi the wing taken along line 3 3 show-n in PIG.` 1.

FIG. 4 is a transverse sectional View of the missile, missile launcher, and of a string used for releasing the missile lfrom the launcher.

` FIG. 5 is a perspective view of a stationary missile launcher. i

FIG. y6 is a perspective View of missile launching, or release, mechanism.

FIG. 7 is a perspective view of a toy automobile with two missiles mounted on the roof of the car.

FIG. 8 is a side view of the missile release mechanism for releasing missileswhen they are mounted on toy ve- `iicles, such `as the carillustrated in FlG. 7. j

The missile launcher can be mounted either on a toy aircraft or lon some other stationary or moving toy, as will become apparent from what follows: v j

Referring tothe drawings, the toy aircraft is illustra-ted at 1t). 'It `is a monoplane having wings 12 and 14, fuselage 16, engine 1S, propeller 20 and `a tail portion 22 with

appropriate rudder surfaces

24 and 26 for controlling the flight of the aircraft. The aircraft is provided with control wires 23 and 29 for controlling the ilight of the aircraft and it is also provided with a missile release string Si). One end of said string is held in the hand of the operator of the aircraft and the opposite end of the string is attached to the tip of wing 14 at a point 32, with the result that string 30 extends lalmost through the entire length, or span, of the wing sections 12 and 14 and beyond to the operator. Two missiles 34 and 36 are mounted under the wings and these missiles are releasable by pulling on string Eil in the manner which is described more in` detail below.

The top plan View of the missile is illustrated in FIG, `2. The missile includes a central, hollow tubular member Ztltl, which, in the preferred form, is a slotted tube, a front linger, or impact rod 201, which lits directly into the central tube 20u` with its inner end 292. Finger 2011 and tube 200 are provided with slots to accommodate a front iiight stabilizer 2li-4 which is provided with a ilat surface bounded by diverging edges 205 and Zilli, and converging edges 267 and 2%. The central tubular member 26) and the front impact rod 201 thus are connected to each other not only by slipping rod Zilli into the hollow cylinder 20u, but by also interconnecting these two members by means of the flight stabilizer 264, all three members Miti, 201 and 204 forming a rigidly connected assembly. The entire missile may be made either of wood or synthetic plastic, in which case itpmay be injection molded by using high impact styrene, high density polyethylene or acrylonitrile-butadiene-styrene.

The central tubular member Ztlt is provided with a 'slot 214B which extends from end-to-end of tube 260, terminating the rear end 211 and thefront end 212, which are produced by the insertion of rod 201 and stabilizer 218 into tube Zilli. Slot 2lb is used for inserting the missile launcher Silit, PEG. 3, into the slot in ,the manner indicated in FIG. 3. The missile is also provided with a helical coil spring 214i which forms a sliding lit Within tube 26h. Tube 2li@ is connected to the llight tail stabilizers of the missile including three

tail stabilizers

216, 217, and 215, which are rigidly connected by means of the front extensions, such as extension 22d on stabilizer 217, to the rear end of tube Zilli. The missile launcher 30@ is cemented to the wings l2 and `14 of aircraft 1li in the manner illustrated in FIG. 3. The launcher 31N) dorms a sliding iit with slot 2i@- in tube 26u.

In orderto mount the missile on the wings of the aircraft, spring 2id is slid tothe front portion of tube 20h, and it is thus compressed inthe manner indicated in FIG. 3. Spring 214 is held in a compressed state bythe front edge 302 of the missile launcher. The rear edge 394 of the launcher engages the rear edge 211 of the missile, and the missile is thus .held securely `on the launcher because of the pressure exerted by spring 21d on the front edge 3% of the launcher and the pressure engagement between the edges 3554 and 211.

Missile launcher 30h is provided with an `orifice 306 positioned close to its lower edge 388 and rear edge 304 and string Sil passes through oriiice 3%. The path followed by string Btl in passing through orifice Sile is illustrated in FIG., 4 where it is indicated that string Si) follows a U-shaped path intl because orice 3% and the lower edge 3% ofthe missile launcher extends into the tubular member 2li@ to such an extent that orifice Sill@ is positioned at the lower edge of the missile slot 210.

lt, therefore, yfollows that the missile can be released by pulling the string. When a pull is exe-med cn string 3l), the string will straighten itself out along a straight line path and thus eliminate the U-shaped pobtion 4W. When this takes place, then string Sil will exert `a pressure on the rear end of tube 200, and this will release edge 211 from its pressure engagement with Ithe edge 30d lof the missile launcher Buti, thus releasing the missile by slipping the rea-r portion of the missile from the launcher. The compressed spring 214 twill then at once be tree to expand and such expansion of spring 214 will impart a very high Aforward velociy to the missile because cf the pressure exemted by the spring on the front edge 2112 of the missile, with the result that the missile will ily ahead -of the plane, converting the potential energy of the spring into thehigh kinetic energy of the missile.

snaai-.1.2

Because of the ight stabilizer 204 and the three ight stabilizers 2.16, 217 and 218, the missile will have good dynamic stability and still follow a trajectory of its own immediately upon leaving `he plane.

It is possible to release either one or two missiles simutaneously by pulling on string 30. If only a slight pull is exerted on stning 30, then only the nearest missile 36, FIG. 1, is released. However, if a strong pull is exerted on string 30, then both missiles are released simultaneously.

FIG. l6 lalso illustrates a mechanism for releasing one missile at a time when the missile launcher includes a plurality of missiles. rThis type of missile launcher mechanism can also be used on aircraft when a plurality of mlssiles .are mounted. This type of release mechanism be `described later.

FIG. illustrates either -a stationary or rotatable missile launcher mounted on :a stand 500. 'Ilhe vertical column 501 may be either a stationary ior rotatable column. On top of the column there is mounted 1a plate 502 having a plurality `or" vertical bars 503-508, which correspond to bar 300 in FIG. 3. The only difference between the mounting of the missile in FIGS. 1-3 and that illustrated in FIG. 5 is that while in FIGS. 1-3, bar 300 is suspended from wing 12 or 14 and is hanging down from the wing; in FIG. 5 bars 503-508 rest on plate 502 and project upwardly from plate 502. In other Words, the missile launcher of FIGS. 1 3 has been inverted, or turned, 180 and the functioning of the launcher otherwise is identical to that illustrated in the earlier iigures. String 510 corresponds to string in the earlier ligures and it performs the same function as str-ing 30 in the earlier gures. The missile launcher of FlG. 5 can be made rotatable by rotating column 501 either by means of la spring :or a string which `can be wound around column 501. Also, two strings can be wound `around column 501, one string being wound in a clockwise direction while the other is wound in a counter-clockwise direction, so :as to turn this column either in ya clockwise direction or a counter-clockwise direction, thus aiming the launcher. This is illust-rated by

stml'ogs

517 and 514.

In FIG. 5, string 510, as -a rule, will release all the missiles iat the same time. A different 'arrangement may be used rfor releasing the missiles, in which case only one missile is released at a time, and this is illustrated in FIG. 6.

Referring to FIG. 6, plate 600 corresponds to plate 502 in FIG. 5 and the vertical bars 601-604 `correspond to the vertical bars 503-508. The missile shafts are illustra-ted at 60S-608. A raised boss 610 is provided `on plate 600 and plate 600 is `also provided with rectangularly-shaped bosses 611, 612 and 613, which are mounted anywhere between the bars 601 :and 604-, with one boss being mounted between the two adjacent rectangular bars 601-604. 'Ille missile launcher mechanism is then provided wit-l1 la string for each individual missile, four

strings

614, 615, 616 and 617 being illustrated in FIG. 6, because tour missiles are illustrated in the same ligure. String 614 then passes through

holes

620, 6211 and 622 of the

vertical bars

601, 602 and 603. It then passes through the upper hole 623 of bar 611 and then through the upper hole 624 of bar `604. When string 614 is pulled it will have no effect on the

missiles

605, 606 and 607, but it will release mis- Sile 608 because the string will be tightened and will follow a straight line path indicated by dotted line 62S which raises the tail end of the missile and thus releases it from bar 604 in the manner described previously.

The same is also true or all the remaining

strings

615, 616, and 617, which will release their own respective missiles when they are pulled either simultaneously or in succession, depending upon the desire of the operator to release either one missile at ya time or all of them simultaneously.

FIG. 7 illustrates the mounting of two missiles on a toy car 700, lwith the vertical plates 701 and 7 02 being mounted on the left and right sides respectively on top 704. Two

strings

705 and 706 are provided for releasing the missiles and the release mechanism is also provided with

brackets

710 and 711 which correspond to brackets 516 and 518 in FIG. 5. The strings then pass through :an opening in a bushing 708 and these

strings

705 and 706 are also illustrated FIG. 8 when they are connected to a crank shaft `800. Crank shaft S00 is geared by means of

gears

801 and 302 to a rear axle 803 of the toy car and when the toy car is actuated by a suitable mechanism such as =a spring, Iaxle 805 is rotated, with the result that the crank shaft 800 is also rotated through

gears

1 and 802. When the crank shaft reaches its lowest position with respect to the top of the car, strings 705 and 706 are tightened, with the result that the missiles are released.

In this case, the two missiles are released simultaneously, but they can be released separately by providing separate releases for each missile of the type illustrated in FIG. 8.

What I claim as new is:

1. A toy missile launching apparatus comprising (a) a missile launcher including front and rear missileengaging members spaced from each other by a iixed distance;

(b) a missile having a central hollow member,

(c) a slit in said hollow member for receiving said front and rear members, said slit having front and rear edges;

(d) a helical compression spring forming a sliding lit with, and mounted within, said hollow member,

(e) said compression spring being compressed in the forward portion of said hollow member when said missile is mounted on said launcher with the aid of said slit and said members, with the rear end of said compression spring engaging said front missile-engaging member and the rear edge of said slit engaging the rear missile-engaging member, and

(f) missile releasing means for sliding said missile ofi said rear member for releasing said missile from said launcher.

2. The toy missile launching apparatus as defined in claim l in which said missile releasing means includes a recess positioned in and close to the outer end of said rear missile-engaging member, a string passing through said recess, said string following a U-shaped path at the point 0f passing through said recess and through the adjacent portion of the slot of said missile, said string, when pulled, releasing said missile from said launcher and said front and rear members by pushing said missile oli said rear member and by launching said missile in forward direction from said launcher because of the release and pressure of said spring on said front member and also on said missile, whereby the potential energy of the spring is converted into the kinetic energy of said missile.

3. The missile launching apparatus as defined in claim l in which said missile releasing means also includes remote control means for releasing said missile from said launcher.

4. A toy aircraft comprising a wing, a missile launcher mounted under said wing, said launcher comprising a substantially rectangular plate having front and rear edges and a detent in the vicinity of the rear edge and bottom of said rectangular plate, a self-propelled missile mounted on said plate, said missile having a central tube with a slit extending through the length of said tube, a helical coil spring mounted in a sliding engagement with said tube, and front and rear flight stabilizing members connected to said tube, said rectangular plate fitting into said slit and into said tube when said missile is mounted on said plate with the coil spring being compressed between the front end of said tube and the front edge of said plate, and the rear end of said tube engaging the rear edge of said plate, and a string passing through said detent for remote control release of said missile from said plate.

5. A toy missile comprising (a) a single stage missile, said missile including (b) a hollow central member, and

air-tassa (c) a helical spring .mounted in sliding engagement Within said member, said spring constituting a part of said missile and flying with said missile upon release of said missile,

(d) said helical spring extending through the greater part of the length of said central member and (e) a front impact rod at the front end of said missile closing olf the front end of said hollow central member, and

(f) iiight control surfaces at the rear end of said central member closing off the rear end of said central member,

(g) said spring being sealed in said hollow central member by said impact rod and said Hight control surfaces.

6. A toy missile as dened in claim 5 which includes (a) a slit in said hollow central member,

(b) a missile launcher comprising a rectangular elongated member iitting into said slit,

(c) said elongated member having a length shorter than the length of said slit,

(d) said elongated member compressing said spring into the front portion or' said hollow central mem ber when said missile is mounted on said missili launcher with the aid of said slit.

7. A toy missile as defined in claim 5 and including 5 further (a) a missile launching member; and

(b) a slit extending through the length of said central member, said slit accommodating said missile launching member for engagement with and compression oi said spring when said missile is mounted on said missile launching member.

References Cited in the iile of this patent UNITED STATES PATENTS

Claims

1. A TOY MISSILE LAUNCHING APPARATUS COMPRISING (A) A MISSILE LAUNCHER INCLUDING FRONT AND REAR MISSILEENGAGING MEMBERS SPACED FROM EACH OTHER BY A FIXED DISTANCE; (B) A MISSILE HAVING A CENTRAL HOLLOW MEMBER, (C) A SLIT IN SAID HOLLOW MEMBER FOR RECEIVING SAID FRONT AND REAR MEMBERS, SAID SLIT HAVING FRONT AND REAR EDGES; (D) A HELICAL COMPRESSION SPRING FORMING A SLIDING FIT WITH, AND MOUNTED WITHIN, SAID HOLLOW MEMBER, (E) SAID COMPRESSION SPRING BEING COMPRESSED IN THE FORWARD PORTION OF SAID HOLLOW MEMBER WHEN SAID MISSILE IS MOUNTED ON SAID LAUNCHER WITH THE AID OF SAID SLIT AND SAID MEMBERS, WITH THE REAR END OF SAID COMPRESSION SPRING ENGAGING SAID FRONT MISSILE-ENGAGING MEMBER AND THE REAR EDGE OF SAID SLIT ENGAGING THE REAR MISSILE-ENGAGING MEMBER, AND