US3785083A

US3785083A - Reaction toy arrangement and method

Info

Publication number: US3785083A
Application number: US00280824A
Authority: US
Inventors: R Pippin
Original assignee: Individual
Current assignee: Individual
Priority date: 1965-10-24
Filing date: 1972-08-15
Publication date: 1974-01-15
Anticipated expiration: 1991-01-15

Abstract

A fluid discharge reaction-propelled toy missile arrangement capable of formation in multiple stages or units releasably interconnected as a function of internal propulsive pressure in the succeeding stages or as a function of internal propulsive pressure in the succeeding stages or units, or capable of individual unit single stage use, if desired. A self-sealing lateral inlet valve separate and spaced from the fluid discharge propulsion orifice of an individual missile unit enables individual unit pressurization from an external fluid pressure source. Missiles are launched from a launching unit which may have a fluid pressurizing inlet and a fluid pressurizable releasable missile-holding connection, or may have other releasable missile-holding connection, and launch simulation enhancement can be provided, if desired, by controlled-release lateral liquid spray from one or more discharge orifices in the launching unit and separate from the fluid pressurizing inlet therefor.

Description

tates Paten Jan. 15, 11974 REACTION TOY ARRANGEMENT AND Reginald F. Pippin, Jr., 7806 Ruxway Rd., Towson, Md. 21204 Pippin, Jr.

METHOD [76] Inventor:

[22] Filed:

Aug. 15, 1972 Appl. N0.: 280,824

Related US. Application Data [62] Division of Ser. No. 102,294, Dec. 29, 1970, which is a division of Ser. No. 504,300, Oct. 24, 1965, Pat, No. 3,550,313.

[52] US. Cl 46/74 C [51 Int. Cl A63h 27/06 [58] Field of Search 46/74, 74 A, 74 B, 46/74 C [56] References Cited UNITED STATES PATENTS 2,733,699 2/1956 Krinsky 46/74 B 2,927,398 3/1960 Kaye et a1. 46/74 C 3,091,052 5/1963 Ryan 46/74 C 3,550,313 12 1970 Pippin 46/74 c 31 Iii: 5b

I w 23b 10- j a 4 z: I 1 Y5 J a a! 25 ll W 13 555 13b- M Primary Examiner-Louis G. Mancene Assistant Examiner-Robert F. Cutting [5 7] ABSTRACT A fluid discharge reaction-propelled toy missile arrangement capable of formation in multiple stages or units releasably interconnected as a function of internal propulsive pressure in the succeeding stages or as a function of internal propulsive pressure in the succeeding stages or units, or capable of individual unit single stage use, if desired. A self-sealing lateral inlet valve separate and spaced from the fluid discharge propulsion orifice of an individual missile unit enables individual unit pressurization from an external fluid pressure source. Missiles are launched from a launching unit which may have a fluid pressurizing inlet and a fluid pressurizable releasable missile-holding connection, or may have other releasable missile-holding connection, and launch simulation enhancement can be provided, if desired, by controlled-release lateral liquid spray from one or more discharge orifices in the launching unit and separate from the fluid pressurizing inlet therefor.

39 Claims, 9 Drawing Figures REACTION TOY ARRANGEMENT AND METHOD This is a division of co-pending application Ser. No. 102,294, filed Dec. 29, 1970, which is turn is a division of application Ser. No. 504,300, filed Oct. 24, 1965, now US. Pat. 3,550,313, dated Dec. 29, 1970.

This invention relates to a reaction toy arrangement and method, and more particularly to a fluid expulsion type reaction motor missile arrangement.

It is a feature of the invention to provide a fluid pressurizable discharge propulsion missile arrangement having a launcher, in which the fluid is caused to be stored under pressure in an internal chamber in the missile for subsequent reaction propulsion discharge through a discharge orifice, through injecting fluid under pressure through a pressurizing valve in the missile and spaced from the fluid discharge propulsion orifice of the missile, the pressurizing valve being preferably self-closing and disposed in a side wall of the missile.

Still a further feature is the provision of a multistagetoy interconnection arrangement in which the various stages are hermetically sealed from one another.

Another feature is the provision of a fluid discharge propellable multi-stage toy arrangement having various self-propellable and pressure-responsively releasably interconnected stages hermetically sealed from one another, at least one stage being capable of pressurization through a pressurizing valve in the stage and spaced from the fluid discharge propulsion orifice for the stage.

A still further feature is the provision of a selfpropelled toy missile arrangement having provision for fluid pressurization of an individual single missile, or a separate stage missile or missiles of a multi-stage composite missile, by pressurized fluid injection of fluid into the given missile through a valve in such missile and spaced from the propulsion discharge orifice thereof, with propulsion-discharge-orifice-sealing A further feature is the provision of a multi-unit toy missile arrangement with launcher in which the units are retained together as a function of internal fluid pressure in one of the units and which has a fluid pressure responsive connector, the one unit being selfpropellable to thereby propel the multi-unit assembly, the one unit having provision for fluid pressurization thereof by injection of fluid under pressure into an internal chamber therewithin and connecting with a fluid discharge propulsion orifice formed in such one unit, the fluid injection pressurization of the one unit being effected through a wall valve separate and spaced from the discharge propulsion orifice and preferably having means for self-closure upon completion of fluid injection pressurization therethrough.

A further feature is the provision of an improved method of pressurizing launched missiles preparatory to launch.

Still a further feature is the provision of a method of fluid injection pressurizing of a jet propelled toy missile while such is in a pre-launched condition and in which fluid is inserted through injection thereof into the missile body, under pressure, through a valve in the missile body and which is separate and spaced from the discharge orifice, the pressurized fluid injection being effected while the fluid discharge orifice is effectively sealed against fluid propulsive discharge, opening of the discharge orifice being subsequently enabled to means for sealing the propulsion discharge orifice of the given missile being thus fluid pressurized to effectively prevent propulsive discharge of the pressurizing fluid therethrough during fluid injection pressurization, and having means for enabling effective opening of the propulsion discharge orifice of the thus fluid-injection pressurized missile to enable self-propulsion thereof by self-pressure-responsive discharge of the pressurized fluid through its propulsion discharge orifice.

Still another feature is the provision of a selfpropelled multi-stage fluid discharge propulsion missile arrangement in which at least one of the individual missile stages is fluid pressurizable through a valve in a wall of the missile and spaced from the propulsion discharge orifice of the missile.

Still another feature is the provision of a selfpropelled multi-stage missile arrangement in which a plurality of the multiple stages of the missile arrangement are individually fluid pressurizable through a valve in the respective stage and separate from the propulsion discharge orifice for the given missile stage,

.with means for effectively closing each respective prothereby enable propulsive discharge of the injected pressurized fluid directly therethrough for propulsion of the missile by reaction discharge.

A further feature is the provision of a method as in the immediately foregoing paragraph for fluid injection pressurizing of a plurality of individually selfpropellable missiles or missile stages of a jointly selfpropellable missile.

A further feature is the provision of an improved method of connecting and pressurizing multiple sequential unit missile arrangements.

Still other objects, features and attendant advantages will become apparent to one skilled in the art from a reading of the following detailed description of several physical embodiments constructed in accordance with the invention, taken in conjunction with the accompanying drawings wherein:

FIG. 1 is a longitudinal section view of a multistage rocket toy according to the invention;

FIG. 2 is a longitudinal section view of a rocket stage modified for ease of molding manufacture;

FIG. 3 is a fragmentary view of a modified launcher and rocket arrangement;

FIG. 4 is a longitudinal section view of a further modified first stage rocket section;

FIG. 5 is a longitudinal section view of an additional modified first stage rocket section;

FIG. 6 is a fragmentary longitudinal section view of a modified fluid-pressure-responsive bulb connectorseal arrangement;

FIG. 7 is a section view taken on line 7-7 of FIG. 6;

FIG. 8 is a section view taken on line 8-8 of FIG. 6;

FIG. 9 is a fragmentary longitudinal section view of a further connector-seal arrangement modification.

Referring now to the Figures of the drawings, in FIG. 1 is shown a multistage rocket toy 10 which in the present embodiment incorporates three stages, although it will become apparent that with the present invention the number of stages is virtually unlimited within the propulsion capabilities of the given rocket size. The illustrative rocket includes three self-

separable stage

11, 21, 31, the lowermost or first stage 11 being releasably mounted on a launching pad 41 having a remote control pressure release launch-control valve 53 connected thereto through a hollow conduit 51.

Each separable stage or

section

11, 21 and 31 includes a cylindrical body having a pressurizable

liquid storage chamber

14, 24 and 34 respectively, enclosed by an annular side wall 13, 23, 33 respectively, and front and

rear end walls

15, 16; 25, 26; and 35, 36, respectively. Stabilizing fins 19, 29, 39 are formed or secured on the outer surface of the

respective stage sections

11, 21 and 31, and the final or upper stage 31 has a tapered or ogive shaped end 36 for decrease of air resistance during flight.

The forward end walls 16 and 26 of the first and second or penultimate stage sections 11 and 21 have a pressure-sensitive laterally flexible diaphragm wall male connector-seal in the illustrative form of a bulbous flexible nose protrusion 17, 27, respectively, which is as a function of pressure in the respective

liquid storage chamber

14, 24, pressurizable for rigidizing thereof and depressurizable for ease of flexing and discharge thereof from a respective female connection a, 25b, 25c; and 35a, 35b, 35c in the adjoining next

forward stage

21 and 31 respectively. Each bulbous nose protrusion 17, 27 includes a unitary relatively thin-walled integral diaphragm-like body structure having an intermediate enlarged annulus portion disposed between a smaller tip protrusion and a smaller annular portion adjacent the root end. The bulbous nose protrusions serve as pressure-responsive connector seals which lockingly engage and seal the respective female connecting and fluid discharge or

expulsion openings

25a, 25b, 25c; and 35a, 35b, 35c. In the illustrative embodiment, each female connecting and fluid discharge or expulsion opening includes an intermediate annular groove portion 25a, 35a disposed between a relatively smaller diameter liquid

discharge metering orifice

25b, 35b and a reduced diameter smoothly rounded rim portion 25c, 350. The flexible bulb connectorseals 17, 27 are preferably shaped to be generally complementary to the respective mating female openings, although it will be appreciated that differences in shape and size may be accommodated to a degree dependent upon the elasticity of the material forming the bulb-connector seals, in which event when the seal integrity and connection strength are effectively maintained the effective pressurized joint is therefore formed of effectively substantially complementary relation. Some degree of pressure-responsive distension is present in all materials, and the extent of distension employed, if any, will depend upon the extent of manufacturing or design mismating and the elastic distension capabilities of the material forming the bulb protrusions.

As used herein, the term bulbous" or bulb" as applied to pressurizable laterally flexible wall connector elements 17, 27, etc., is used in both the specific shape sense of a male shaped connector having an enlarged mid-section, and the generic action sense of a male shaped connector member generally which is capable of lateral swelling, and in each instance having an internal pressure responsive laterally flexible wall section which is pressurizable when in place within a fluid discharge orifice to afford pressure responsively releasable holding action therewith. The fluid-pressureresponsive laterally flexible diaphragm wall connector elements or members 17, 27, etc., may, of course, be formed with other configurations and constructions than the illustrated and preferred bulbous configurations and constructions.

Launching pad 41 is pressure-responsively connected to the female connecting and fluid discharge openings 15a, 15b, 150 of the first stage section 11 through the medium of a flexible bulb connector-seal 47 similar to interstage flexible bulb connector-seals 17 and 27.

Although the pressurizing of the

various chambers

14, 24, 34 and 45 will tend to properly seat the preinserted bulb connector-seals in their respective female openings it may be advantageous and desirable in some instances, particularly in the case of highly flexible bulb connector-seal embodiments to employ a connector bulb insertion aid 71 which may take the form of a rod 73 having a handle 75. The rod 71 may be inserted through the female fluid discharge opening 15b, 25b of a particular rocket section to push on and effect manipulation of the respective bulb connection-seal 17 or 27 into its corresponding adjoining next stage complementary

female opening

25a, 25b, 250 or 35a, 35b, 35c as the case may be. To enable use of insertion aid 71 with the interconnection between launcher pad 41 and the first stage section 11, the bottom wall 44 of pad 41 may be provided with a central removable plug 49 aligned with bulb connector-seal 47. Plug 49 may be formed with a double tapered nodule detent 49a for ease of insertion and removal and a recessed flat head 49b.

The

rocket stage sections

11, 21 and 31 and a launching pad 41 are each provided with a self-closing valve opening 13a, 23a, 33a and 43a, respectively, to enable pressurizing of the

respective chambers

14, 24, 34 and 45, after assembly of respective adjoining stages, although the launch pad chamber 45 may if desired be pressurized through valve 53 and conduit 51. Each of the self-closing valves includes pressure-responsive self-obturating

inner closure lips

13b, 23b, 33b, and 43b respectively and a flared outer guide opening as indicated at 130 may also be provided if desired. For purposes of illustration of differing locations for the valves, each of the

valves

13a, 23a, 33a is shown at a different location on its respective rocket stage section, although it will be appreciated that for a given assembly all

valve openings

13a, 23a and 33a would normally lie in the same general position on the respective different stage sections. A conventional valve needle 61 of the type commonly employed for inflating footballs, basketballs, etc., and a conventional air pump (not shown) may be used in conjunction with

valve openings

13a, 23a, 33a, and 43a to effect pressurizing of the

respective chambers

14, 24, 34 and 45.

It will be appreciated that inasmuch as the illustrated first and second stages 11 and 21 are interchangeable, it is a simple matter to reduce the number of stages to two or one by elimination of one or both of stages 11 through valve opening 43a or through line 51 to effect secure retaining connection and sealing of the launching pad 41 to the first stage 11 through pressureresponsive bulb and socket connection 47, a, 15b, 15c. Thereupon, water is added to partially fill storage chamber 24 in second stage section 21 while holding the second stage in inverted position, and the first stage bulb connector-seal is then inserted into the

opening

25a, 25b, 25c, after which the first stage chamber'l4 is pressurized through valve opening 13a to lock sections 21 to first stage section 11 and the assembly 11, 41. This same operation is then repeated for partial filling of third stage section 31, connection thereof to second stage section 21, and subsequent pressurizing of second stage 21 through valve opening 23a to lock

sections

21 and 31 together. The assembly operation is then completed by pressurizing final stage chamber 34 through valve opening 33a, and the assembly is then ready for launch.

The foregoing method of assembly is most advantageous when the bulb connector-seals 17 et al are of suf-' ficient rigidity to enable flexing insertion without the aid of tool 71, as only two pieces need be held together at a time in unsecured connected condition. However when it is necessary or desired to employ the insertion aid tool 71 on all interstage connections, a different assembly procedure may be employed. In thie instance the final stage section 31 is first partially filled with water while inverted and thereupon the second stage section 21 is connected thereto by inserting the bulb connector-seal 27 into the opening 35a, 35b, 350, using the tool 71 through second stage opening 25a, 25b, 25c to aid in this assembly. Water is then added through

opening

25a, 25b, 25c to partially fill second stage 21, and first stage 11 is connected to stage 21 through insertion of bulb connector-seal 17 into

opening

25a, 25b, 250, using tool 71 through opening 15a, 15b, 150. Water is then added to partially fill the storage chamber 14 of the first stage 11 while continuing to hold the

assembly

11, 21, 31 in inverted vertical position, and the launch pad 41 is then connected by removing the plug 49 and manipulating the tool through opening 46 to aid in positioning the bulb connector-seal within the mating connecting and fluid discharge opening 15a, 15b, 150 of the first stage section 11. Plug 49 is then replaced, and thereupon launching padchamber 44 is pressurized through either valve opening 43 or conduit 51 and valve 53. This secures first stage 11 and launch pad 41 together in sealed relation and chamber 14 is thereupon pressurized through valve opening 13a to secure stages 11 and 21 together, whereupon second stage 21 is the pressurized through valve opening 23a to lock and seal

stages

21 and 31 together, and final stage chamber 34 is then pressurized through valve opening 33c to ready the assembly for launching. It will be appreciated that in this last described method of assembly a holding jig or fixture may be used if desired to retain the various sections in position during assembly, although such may be accomplished by hand only if desired, particularly with the aid of a second person.

To launch the rocket 11 from the launch pad 41, the assembly 41, ll, 21, 31 is turned to a vertically upright position as shown in FIG. 1, and valve 53 is released to release the pressure within chamber 45. The pressure within chamber 14 of first stage 11 will then cause the flexible bulb connectorfseal to laterally collapse and be ejected from the opening 15a, 15b, 15c and liftoff will occur with the subsequent continuing discharge of liquid through metering orifice 15b. The rocket assembly will continue upward under the reaction force influence of the ejected water mass from orifice 15b until the pressure in chamber 14 drops sufficiently to enable the then greater pressure within chamber 24 (which was initially approximately similar to that of adjacent,

chambers 13 and 34), to overcome the holding action of bulb connector-seal 27 in opening a, 25b, 25c. Upon reaching this pressure difference the second and third section assembly will then separate from the first stage in a manner similar to that of first stage 11 and launch pad 41. The second and

third stage assembly

21, 31 will continue upward together until a similar pressure differential separation occurs between these two stages, and the third stage will thereupon continue upward alone under its own reaction motor thrust power through liquid ejection from metering orifice 35b. Upon exhaustion of the liquid from each of the stages the thrust will quickly drop to zero and the stage will thereafter drop to the launch area. Upon recovery of all stages the rocket 11 may be reassembled together with launch pad 41 and launched again.

For ease of manufacturing the various stages and the launcher may take various forms. For instance, as shown in FIG. 1, illustrating a modified construction of rocket stage section 111, the body 111 may be formed in several pieces which are then suitably bonded together to form the unitary body. In this modified embodiment the rear wall is formed separately from the side and

forward wall section

113, 116, as in the selfsealing valve 118 and the bulb connector-seal 117. The rear end wall is formed as two or more split laterally mating sections 115', 115", each having a concavoconcave intermediate groove surface 115a, small diameter concavo-convex metering orifice surface 1 15b and reduced diameter neck rim surface 15c. With this construction the separately formed pieces may be formed of different materials consistent with their required function. For instance, the bulb connector-seal 117 may be formed of softer more elastic material than body 113, as may self-sealing valve 118. Bulb connector-seal 118 is secured to the main body 113 through bonding of an intermediate neck portion 117C and flange retaining portion 1 l7d to the adjoining area surrounding opening l16 in end wall 116. Valve 118, which is preferably of soft pliant rubber, is inserted through an opening in side wall 113 and is bonded thereto and/or held in place by tight friction fit which aids in assuring self-sealing of the opening 1 18a. In addition it may be noted that each of the valve openings 118a, 18a, etc., of the various valves may be formed by puncturing with a sharp small diameter needle, or by other conventionally practiced self-closing valve construction techniques. Further, various other valve constructions may be employed for the valves 118, 18a, etc., as desired. it being desirable however that the valves be self-closing in the discharge direction;

FIG. 3 illustrates a modified launch pad arrangement which provides added simulated realism to the launching operation. In this modified embodiment the housing 243 for the pressurizable fluid chamber 245 of the launch pad 241 has radially extending liquid discharge orifices 244 formed at circumferentially spaced positions about the annular periphery thereof. The orifices 244 preferably have a flared inner seat end and are re leasably closed by substantially complementary pressure releasable plugs 242, each having a double tapered retention nodule end 242a seating on seat 244a. The plugs 242 are preferably additionally connected for safety and retention purposes to the launch pad 241 through the medium of a flexible cord or other flexible line 281 secured through spaced eyes 257 formed in the annular outer upstanding rim 253.

The launch pad 241 may be secured to the ground for stability, if desired, as with anchor pins 283 extending through the base 251 thereof. While not shown, a tool receiving opening and a removable plug may be provided in the bottom 251 of launch pad 241 as in FIG. 1 if so desired, it being preferred in such cases that the removable tool assistance plug be constructed and shaped for substantially more difficult removal than the plugs 242 so as to prevent undesired removal of the plugs during operation of the launch pad 241.

A female water hose connection is provided in the wall 243 as indicated at 248 for supply of water to and pressurizing of the chamber 245. Annulus wall 253 has an upwardly concavely curved surface 255 in the path of discharge from the orifices 244 and this surface 255 serves to deflect and disperse water from the orifices 244 upwardly.

In operation of the embodiment of FIG. 3, a rocket 211 partially filled with water is connected to launch pad 241 through insertion of bulb connector-seal 247 in the associated rear discharge and connection opening of the rocket body. Water is then added to chamber 245 through a hose (not shown) connected to hose connector 248 sufficient to pressurize the bulb 247 to operational sealing and holding condition, but insufficient to effect discharge of said plugs 242 from their orifices 244. The rocket 211 is then pressurized through its associated valve 213a, whereupon the water pressure is increased within chamber 245 by remote control from a conventional water faucet supply connection (not shown) to effect discharge of the plugs 242 and resulting spraying of water through the orifices 244. The radial jets of water will be deflected and dispersed upwardly in a generally ring-shaped pattern, the continuity of which is dependent to a degree upon the number of spacing of orifices 244. With a sufficient quantity and size of orifices in comparison to the available water flow rate into chamber 245, the resulting pressure drop will be sufficient to enable launching of rocket 211. However, launching can be assured by turning the faucet full open to eject the plugs 242 and effect the desired water spray action, and thereupon turning off the faucet, as the pressure in the chamber 245 will in the final condition be reduced to zero, assuring release and lift-off of the rocket 211 from launch pad 241.

In FIGS. 4 and 5 are shown two permissible, though to some degree less advantageous, modifications offirst stage sections of a multistage rocket according to the invention. In each instance the stage section incorporates a pressurizable flexible bulb connector-seal 317 for connection of two adjoining first and second stages 31! and 321, the bulb connector-seal 317 being of teardrop shape for ease of insertion and relatively greater resistance to removal. This facet is considered desirable in various instances for add stage bulb connectorseals, the somewhat less advantageous construction lying in the alternative constructions for connection to the launcher. In FIG. 4 the launcher connection is a flanged nozzle 315fformed on rear wall 315 and having a fluid discharge orifice 315b. With this construction the rocket 311 may be launched with the aid of a mechanical slide release launcher such as shown on U.S. Pat. No. 2,732,657. The discharge orifice 315b in the embodiment of FIG. 5 has a shallow small diameter annular groove 41512 formed in the discharge orifice 415b and is adapted to be launched with the aid of a modular stemmed launcher as provided in U.S. Pat. No. 3,046,694. Various other hybrid stage sections may be employed as desired, though such are generally considered less desirable 'than the arrangement in which all stages and the launch pad are connected and separated in a similar manner.

A modified bulb connector-seal 517 is shown in the rocket section embodiment 511 of FIGS. 6-8, wherein the bulb wall 517b has a tear-drop shape for relative ease of insertion in comparison to removal of the bulb connector-seal from its complementary female opening, and in which the bulb is longitudinally reinforced while providing collapsibly lateral flexibility of the wall 517b. This is effected by a longitudinal reinforcing rib unit having ribs 517d integrally connecting, or secured to, the tip and root end portion of bulb connector-seal 517 while being in disconnection therefrom in the intermediate enlarged girth flexible annular wall portion 517b.

FIG. 9 shows a further modified form of flexible bulb connector-seal 617 having a generally squat shape with a relatively large diameter securing rim annulus portion 617b' compared to the depth thereof and a relatively flattened flexible outer end surface 61712". The opening in wall 616 of rocket stage section 611 is relatively large so as to enable downwardly and inwardly rolling deflection and release of the retaining rim annulus portion 6l7b' from its complementary retention groove in response to decrease in pressure in the connecting liquid storage chamber of stage section 611. In this embodiment, as in FIG. 2, the bulb connector-seal 617 is formed separately from the main body of the associated rocket stage section 611, and is bonded thereto along retaining flange 617d and intermediate reduced diameter portion 617e, although in some instances it may be sufficient to bond only along flange 617d, in which latter instance the downwardly and inwardly rolling action of the bulb diaphragm connector-seal 617 may extend over a greater distance during stage separation.

While the invention has been illustrated and described with respect to various illustrative embodiments, various modifications and improvements may be made. For instance, the liquid inserted in any one or more of the missile units and/or launcher unit may be inserted through the pressurizing valve for the particular unit, in lieu of being loaded through the unit discharge orifice or separate launcher fill line or orifice. In addition, in a further modification or improvement, pressurizable flexible wall female inter-unit connectors may be employed in lieu of the illustrated pressurizable male connectors, in which instance the female connector may envelope and releasably engage in peripherally sealing relation a projecting rear section of a next succeeding missile unit or stage, which projecting section may include the discharge orifice section of such next succeeding unit, and thereby effectively closing such discharge orifice of the next succeeding unit during pressurized holding of such unit by the female connector. Also, the spray launcher may be provided with positive orifice-opening-and-missile-release-effecting means, such as a selectively longitudinally movable common release ring in releasable closure-controlling direct or indirect connection with a plurality of initially closed spray orifices, in lieu of the pressure responsively self-releasable multiple plug spray launcher as illustrated in FIG. 3. Accordingly, it is to be understood that the invention is not to be limited by the illustrative embodiments, but only by the scope of the appended claims.

That which is claimed is: 1. A jet propulsion toy arrangement comprising a self-propelled body having a pressurizable fluid chamber and a closable fluid jet discharge propulsion orifice connecting between said chamber and the outside atmosphere, a fluid pressurizing valve in said body and spaced from said jet discharge propulsion orifice, and launch-enabling means for said self-propelled body and enabling launching of said body after fluid pressurization thereof through said valve. 2. A jet propulsion toy arrangement according to claim 1,

said launch-enabling means including a propulsion orifice closure for closing said jet discharge propulsion orifice to enable pre-launch pressurization of said self-propelled body through said fluid pressurizing valve. 3. A jet propulsion toy arrangement according to claim 2,

and means to enable effective opening of said propulsion orifice after pressurization of said body through said fluid pressurizing valve, to enable jetpropelled launching of said body from said launchenabling means. A 4. A jet propulsion toy arrangement according to claim 3,

said means to enable effective opening of siad propulsion orifice after pressurization of said body including means for releasing said closure from effective closure relation with said orifice. 5. A jet propulsion toy arrangement according to claim 3,

said closure being directly engagable in orificeclosing relation with said jet discharge orifice of said self-propelled body, said means to enable effective opening of said propulsion orifice after pressurization of said body including means enabling release of said closure from engagement with said jet discharge propulsion orifice. 6. A jet propulsion toy arrangement according to claim 5,

said closure being engagable with said propulsion orifice in both orifice-closing and body-holding relation for pre-launch retention of said body on said launcher. 7. A jet propulsion toy arrangement according to claim 6,

said closure being releasably pressurizable to effect said orifice closure and said body retention, and means for selectively pressurizing said closure and releasing pressurization of, said closure. 8. A jet propulsion toy arrangement according to claim 6,

said pressurizing valve being self-closing against release of fluid therethrough after external pressurization therethrough.

9. A jet propulsion toy arrangement according to claim 6,

said pressurizing valve being self-closing and comprising a soft elastic material having a normally elastically self-closing passageway for enabling selective fluid pressurization therethrough with the aid of external orifice-opening and pressurizing means. 10. A jet propulsion toy arrangement according to claim 6,

said self-propelled body having an elongate shape with said jet discharge propulsion orifice being disposed in one longitudinal end thereof, said pressurizing valve being disposed in a longitudinally extending peripheral wall of said selfpropellable body. 11. A jet propulsion toy arrangement according to claim 6,

said pressurizing valve being self-closing against release of fluid therethrough after external pressurization therethrough from an external source. 12. A jet propulsion toy arrangement according to claim 5,

said pressurizing valve being self-closing and comprising a soft elastic material having a normally elastically self-closed passageway for enabling selective fluid pressurization therethrough with the aid of external orifice opening and pressurizing means. 13..A jet propulsion toy arrangement according to claim 5,

said self-propelled body having an elongate shape,

with said jet discharge propulsion orifice being disposed in one longitudinal end thereof, said pressurizing valve being disposed in and forming an effective portion of the longitudinal peripheral wall of said self-propelled body. 14. A jet propulsion toy arrangement according to claim 2,

said pressurizing valve being self-closing against release of fluid therethrough after external pressurization therethrough. 15. A jet propulsion toy arrangement according to claim 2,

said pressurizing valve being self-closing and comprising a soft elastic material having a normally elastically self-closed passageway for enabling selective fluid pressurization therethrough from a removable external source. 16. A jet propulsion toy arrangement according to claim 1,

said pressurizing valve being self-closing against release of fluid therethrough after completion of external pressurization therethrough. 17. A jet propulsion toy arrangement according to claim 1, I

said pressurizing valve being self-closing and comprising a soft elastic material having a normally elastically self-closed passageway for enabling selective fluid pressurization therethrough from a removable external source. 18. A jet propulsion toy arrangement according to claim 1,

said self-propellable body having an elongate shape,

with said jet discharge propulsion orifice being disposed in one longitudinal end thereof,

said pressurizing valve being disposed in and forming an effective pressure-retention portion of the longitudinally extending peripheral wall of said selfpropellable body, and which longitudinally extending wall forms a wall of said pressurizable fluid chamber. 19. A jet propulsion toy arrangement according to claim 18,

said pressurizing valve comprising a self-closing separate plug of soft elastic material secured in a relatively rigid longitudinally extending fluid-pressurizable peripheral wall of said self-propelled body and which wall forms a wall of said pressurizable fluid chamber. 20. A jet propulsion toy arrangement according to claim 18,

said self-propelled body having a releasable connector formed adjacent the longitudinal end thereof opposite said jet discharge orifice end. 21. A jet propulsion toy arrangement according to claim 20,

said releasable connector formed adjacent the longitudinal end of saids elf-propelled body being pressurizable and depressurizable to effect retention and release of a further body, said connector being also pressurizable by said pressurizing valve as a function of pressurizing said selfpropelled body. 22. A jet propulsion toy arrangement according to claim 21, further comprising a second releasably holdable body held by and released from said releasable connector as a function of the internal pressure at said connector. 23. A jet propulsion toy arrangement according to claim 22,

said second body being self-propelled and having a pressurizable fluid chamber and a closable fluid jet discharge propulsion orifice connecting between said chamber and the outside atmosphere and releasably engagable by said connector, said second self-propelled body having a fluid pressurizable valve therein and spaced from said jet discharge propulsion orifice. 24. A jet propulsion toy arrangement according to claim 23,

said fluid pressurizable valve in said second selfpropelled body being disposed in a longitudinally extending peripheral side wall of said second body, and said propulsion orifice being disposed at the rear of said second body and engagable by said connector. 25. A jet propulsion toy arrangement according to claim 24,

and a third releasably holdable body held by and released from said second self-propelled body through a pressure-sensitive releasable connector. 26. A jet propulsion toy arrangement according to claim 25,

said third releasably holdable body being a third selfpropelled body having a side pressurizing valve and a rear propulsion orifice closable as a function of connection with said second self-propelled body. 27. A jet propulsion toy arrangement according to claim 1,

said self-propelled body having a pressurizable connection connecting in pressurizable relation with said chamber,

and a second body releasably connectable and holdable by said pressurizable connection and being releasable as a function of decrease in pressure at said connection. 28. A jet propulsion toy arrangement according to claim 27,

said second body being self-propelled and having a pressurizable fluid chamber, a closable fluid discharge propulsion rear orifice, and a fluid pressurizing valve therein and spaced from said jet discharge propulsion orifice, said rear propulsion orifice being closable and openable as a function of connection with and release from said first self-propelled body.

29. A jet propulsion toy arrangement according to claim 2,

and fluid pressurizing means for inserting fluid under pressure through said separate fluid pressurizing valve and into said pressurizable fluid chamber to effect pre-launch pressurization of said chamber whereby fluid propulsion discharge may be effected through said propulsion orifice upon opening of said propulsion orifice.

30. A jet propulsion toy arrangement according to claim 29,

said fluid pressurizing means including a male valve insertion member having a fluid passageway therethrough for removable selective insertion in valveopening relation into said valve,

and a source of fluid under pressure for connection to said male valve insertion member. 31. The method of pressurizing and launching a toy rocket stage having a rear propulsion orifice and an internal pressurizable fluid chamber connecting with said rear jet propulsion orifice, comprising closing said rear jet propulsion orifice preparatory to pressurizlng and launching of said stage,

pressurizing said chamber through a fluid pressurizing valve in said stage and separate from said rear jet propulsion orifice,

and enabling opening of said rear jet propulsion orifice for launch and self-propulsion of said toy rocket stage by jet discharge through said propulsion orifice.

32. The method according to claim 31,

wherein said fluid pressurizing is effected through a lateral valve in said stage.

33. The method according to claim 32, further comprising connecting a second said stage to said firstmentioned stage through a pressurizable releasable connection on said first-mentioned stage and engagable in orifice-closing relation with said second stage,

said connecting of said stages being effected prior to pressurizing said first-mentioned stage,

thereafter pressurizing said chamber in said second stage through a fluid pressurizing valve therein and separate from said rear jet propulsion orifice therein,

and subsequently enabling opening of said rear jet propulsion orifice in said first-mentioned stage for launch and self-propulsion of said stages as a selfseparable unit.

34. The method according to claim 33,

further comprising connecting and pressurizing a further third said stage to said second stage according to the method of connecting and pressurizing said second stage and said first-mentioned stage,

and subsequently launching said stages as a unit by enabling opening of said rear jet propulsion orifice.

35. The method according to claim 34,

wherein said pressurizing is effected by inserting fluid under pressure through said pressurizing valves and separate from said propulsion discharge orifices.

36. The method according to claim 33,

37. The method according to claim 31,

wherein said pressurizing is effected by inserting fluid under pressure through said separate valve.

38. The method according to claim 37,

wherein said pressurizing is effected by inserting a male fluid-transmitting member into said valve and flowing fluid under pressure into said pressurizing chamber,

and thereupon withdrawing said male fluidtransmitting member to enable closing of said valve.

39. The method of pressurizing and launching a separable multiple body self-propelled unit, one of which separable multiple bodies has a rear jet propulsion orifice and an internal pressurizable fluid chamber and a pressurizable forward body-holding and releasing connection in effective fluid flow relation with said chamber, comprising uniting said bodies as a unit through said pressurizable forward connection and closing said rear jet propulsion orifice in said one body,

pressurizing said chamber and said pressurizable connection through a fluid pressurizing valve in said one body and separate from said rear jet propulsion orifice,

and enabling opening of said rear jet propulsion orifice for launch and self-propulsion of said multiple body unit by jet discharge through said propulsion orifice, and for subsequent pressure-responsive release of said connection during flight of said unit.

* l l =l

Claims

1. A jet propulsion toy arrangement comprising a self-propelled body having a pressurizable fluid chamber and a closable fluid jet discharge propulsion orifice connecting between said chamber and the outside atmosphere, a fluid pressurizing valve in said body and spaced from said jet discharge propulsion orifice, and launch-enabling means for said self-propelled body and enabling launching of said body after fluid pressurization thereof through said valve.

2. A jet propulsion toy arrangement according to claim 1, said launch-enabling means including a propulsion orifice closure for closing said jet discharge propulsion orifice to enable pre-launch pressurization of said self-propelled body through said fluid pressurizing valve.

3. A jet propulsion toy arrangement according to claim 2, and means to enable effective opening of said propulsion orifice after pressurization of said body through said fluid pressurizing valve, to enable jet-propelled launching of said body from said launch-enabling means.

4. A jet propulsion toy arrangement according to claim 3, said means to enable effective opening of said propulsion orifice after pRessurization of said body including means for releasing said closure from effective closure relation with said orifice.

5. A jet propulsion toy arrangement according to claim 3, said closure being directly engagable in orifice-closing relation with said jet discharge orifice of said self-propelled body, said means to enable effective opening of said propulsion orifice after pressurization of said body including means enabling release of said closure from engagement with said jet discharge propulsion orifice.

6. A jet propulsion toy arrangement according to claim 5, said closure being engagable with said propulsion orifice in both orifice-closing and body-holding relation for pre-launch retention of said body on said launcher.

7. A jet propulsion toy arrangement according to claim 6, said closure being releasably pressurizable to effect said orifice closure and said body retention, and means for selectively pressurizing said closure and releasing pressurization of said closure.

8. A jet propulsion toy arrangement according to claim 6, said pressurizing valve being self-closing against release of fluid therethrough after external pressurization therethrough.

9. A jet propulsion toy arrangement according to claim 6, said pressurizing valve being self-closing and comprising a soft elastic material having a normally elastically self-closing passageway for enabling selective fluid pressurization therethrough with the aid of external orifice-opening and pressurizing means.

10. A jet propulsion toy arrangement according to claim 6, said self-propelled body having an elongate shape with said jet discharge propulsion orifice being disposed in one longitudinal end thereof, said pressurizing valve being disposed in a longitudinally extending peripheral wall of said self-propellable body.

11. A jet propulsion toy arrangement according to claim 6, said pressurizing valve being self-closing against release of fluid therethrough after external pressurization therethrough from an external source.

12. A jet propulsion toy arrangement according to claim 5, said pressurizing valve being self-closing and comprising a soft elastic material having a normally elastically self-closed passageway for enabling selective fluid pressurization therethrough with the aid of external orifice opening and pressurizing means.

13. A jet propulsion toy arrangement according to claim 5, said self-propelled body having an elongate shape, with said jet discharge propulsion orifice being disposed in one longitudinal end thereof, said pressurizing valve being disposed in and forming an effective portion of the longitudinal peripheral wall of said self-propelled body.

14. A jet propulsion toy arrangement according to claim 2, said pressurizing valve being self-closing against release of fluid therethrough after external pressurization therethrough.

15. A jet propulsion toy arrangement according to claim 2, said pressurizing valve being self-closing and comprising a soft elastic material having a normally elastically self-closed passageway for enabling selective fluid pressurization therethrough from a removable external source.

16. A jet propulsion toy arrangement according to claim 1, said pressurizing valve being self-closing against release of fluid therethrough after completion of external pressurization therethrough.

17. A jet propulsion toy arrangement according to claim 1, said pressurizing valve being self-closing and comprising a soft elastic material having a normally elastically self-closed passageway for enabling selective fluid pressurization therethrough from a removable external source.

18. A jet propulsion toy arrangement according to claim 1, said self-propellable body having an elongate shape, with said jet discharge propulsion orifice being disposed in one longitudinal end thereof, said pressurizing valve being disposed in and forming an effective pressure-retentioN portion of the longitudinally extending peripheral wall of said self-propellable body, and which longitudinally extending wall forms a wall of said pressurizable fluid chamber.

19. A jet propulsion toy arrangement according to claim 18, said pressurizing valve comprising a self-closing separate plug of soft elastic material secured in a relatively rigid longitudinally extending fluid-pressurizable peripheral wall of said self-propelled body and which wall forms a wall of said pressurizable fluid chamber.

20. A jet propulsion toy arrangement according to claim 18, said self-propelled body having a releasable connector formed adjacent the longitudinal end thereof opposite said jet discharge orifice end.

21. A jet propulsion toy arrangement according to claim 20, said releasable connector formed adjacent the longitudinal end of said self-propelled body being pressurizable and depressurizable to effect retention and release of a further body, said connector being also pressurizable by said pressurizing valve as a function of pressurizing said self-propelled body.

22. A jet propulsion toy arrangement according to claim 21, further comprising a second releasably holdable body held by and released from said releasable connector as a function of the internal pressure at said connector.

23. A jet propulsion toy arrangement according to claim 22, said second body being self-propelled and having a pressurizable fluid chamber and a closable fluid jet discharge propulsion orifice connecting between said chamber and the outside atmosphere and releasably engagable by said connector, said second self-propelled body having a fluid pressurizable valve therein and spaced from said jet discharge propulsion orifice.

24. A jet propulsion toy arrangement according to claim 23, said fluid pressurizable valve in said second self-propelled body being disposed in a longitudinally extending peripheral side wall of said second body, and said propulsion orifice being disposed at the rear of said second body and engagable by said connector.

25. A jet propulsion toy arrangement according to claim 24, and a third releasably holdable body held by and released from said second self-propelled body through a pressure-sensitive releasable connector.

26. A jet propulsion toy arrangement according to claim 25, said third releasably holdable body being a third self-propelled body having a side pressurizing valve and a rear propulsion orifice closable as a function of connection with said second self-propelled body.

27. A jet propulsion toy arrangement according to claim 1, said self-propelled body having a pressurizable connection connecting in pressurizable relation with said chamber, and a second body releasably connectable and holdable by said pressurizable connection and being releasable as a function of decrease in pressure at said connection.

28. A jet propulsion toy arrangement according to claim 27, said second body being self-propelled and having a pressurizable fluid chamber, a closable fluid discharge propulsion rear orifice, and a fluid pressurizing valve therein and spaced from said jet discharge propulsion orifice, said rear propulsion orifice being closable and openable as a function of connection with and release from said first self-propelled body.

29. A jet propulsion toy arrangement according to claim 2, and fluid pressurizing means for inserting fluid under pressure through said separate fluid pressurizing valve and into said pressurizable fluid chamber to effect pre-launch pressurization of said chamber whereby fluid propulsion discharge may be effected through said propulsion orifice upon opening of said propulsion orifice.

30. A jet propulsion toy arrangement according to claim 29, said fluid pressurizing means including a male valve insertion member having a fluid passageway therethrough for removable selective insertion in valve-opening relation into said valve, anD a source of fluid under pressure for connection to said male valve insertion member.

31. The method of pressurizing and launching a toy rocket stage having a rear propulsion orifice and an internal pressurizable fluid chamber connecting with said rear jet propulsion orifice, comprising closing said rear jet propulsion orifice preparatory to pressurizIng and launching of said stage, pressurizing said chamber through a fluid pressurizing valve in said stage and separate from said rear jet propulsion orifice, and enabling opening of said rear jet propulsion orifice for launch and self-propulsion of said toy rocket stage by jet discharge through said propulsion orifice.

32. The method according to claim 31, wherein said fluid pressurizing is effected through a lateral valve in said stage.

33. The method according to claim 32, further comprising connecting a second said stage to said first-mentioned stage through a pressurizable releasable connection on said first-mentioned stage and engagable in orifice-closing relation with said second stage, said connecting of said stages being effected prior to pressurizing said first-mentioned stage, thereafter pressurizing said chamber in said second stage through a fluid pressurizing valve therein and separate from said rear jet propulsion orifice therein, and subsequently enabling opening of said rear jet propulsion orifice in said first-mentioned stage for launch and self-propulsion of said stages as a self-separable unit.

34. The method according to claim 33, further comprising connecting and pressurizing a further third said stage to said second stage according to the method of connecting and pressurizing said second stage and said first-mentioned stage, and subsequently launching said stages as a unit by enabling opening of said rear jet propulsion orifice.

35. The method according to claim 34, wherein said pressurizing is effected by inserting fluid under pressure through said pressurizing valves and separate from said propulsion discharge orifices.

36. The method according to claim 33, wherein said pressurizing is effected by inserting fluid under pressure through said pressurizing valves and separate from said propulsion discharge orifices.

37. The method according to claim 31, wherein said pressurizing is effected by inserting fluid under pressure through said separate valve.

38. The method according to claim 37, wherein said pressurizing is effected by inserting a male fluid-transmitting member into said valve and flowing fluid under pressure into said pressurizing chamber, and thereupon withdrawing said male fluid-transmitting member to enable closing of said valve.

39. The method of pressurizing and launching a separable multiple body self-propelled unit, one of which separable multiple bodies has a rear jet propulsion orifice and an internal pressurizable fluid chamber and a pressurizable forward body-holding and releasing connection in effective fluid flow relation with said chamber, comprising uniting said bodies as a unit through said pressurizable forward connection and closing said rear jet propulsion orifice in said one body, pressurizing said chamber and said pressurizable connection through a fluid pressurizing valve in said one body and separate from said rear jet propulsion orifice, and enabling opening of said rear jet propulsion orifice for launch and self-propulsion of said multiple body unit by jet discharge through said propulsion orifice, and for subsequent pressure-responsive release of said connection during flight of said unit.