US3646702A

US3646702A - Propelled toy arrangement

Info

Publication number: US3646702A
Application number: US36120A
Authority: US
Inventors: Reginald F Pippin Jr
Original assignee: Individual
Current assignee: Individual
Priority date: 1965-10-24
Filing date: 1970-05-11
Publication date: 1972-03-07
Anticipated expiration: 1989-03-07

Abstract

A missile arrangement including a first missile-launching unit having one or more female openings for receiving one or more separable propellable missile units. This first missile-launching unit is disclosed in the preferred form of a self-propelled missile having a fluid discharge orifice and a pressurizable fluid-pressure responsive flexible diaphragm which enables retention of the propellable missile unit within the female opening and release therefrom by respectively pressurizing and depressurizing the first unit. Embodiments with two separable propellable missile units are illustrated, embodying both selfpropulsion of the separable propellable missile unit or units, and passive propulsion by external propulsion means on, and/or effected by motive action of, the first launching unit.

Description

United States Patent Pippin, Jr.

[ 1 Mar. 7, 1972 [54] PROPELLED TOY ARRANGEMENT [63] Continuation-impart of Ser. No. 504,299, Oct. 24,

1965, Pat. No. 3,510,980.

3,218,756 11/1965 Draglich ..46/89 3,229,418 1/1966 Draglich ..46/88 Primary Examiner-Russell R. Kinsey Assistant Examiner-Robert F. Cutting [57] ABSTRACT A missile arrangement including a first missile-launching unit having one or more female openings for receiving one or more separable propellable missile units. This first missile-launching unit is disclosed in the preferred form of a self-propelled missile having a fluid discharge orifice and a pressurizable fluid- [52] U.S.Cl. 46/74A fl h h abl [5 In. CL 53h 27/06 pressure responsive 8X1. e lap ragm w 1c en es reten- [58] Field of Search 46/74 R 74 B 74 C tlon of the propellable mlsslle unlt wlthm the female openlng and release therefrom by respectively pressurizing and depressurizing the first unit. Embodiments with two separable [561 cted propellable missile units are illustrated, embodying both self- UNITED STATES PATENTS propulsion of the separable propellable missile unit or units, and passive propulsion by external propulsion means on, i

and/or effected by motive action of, the first launching unit. en 3,124,899 3/1964 Taubman ..46/86 13 Claims, 10 Drawing Figures 2| 4 4| 4| 2 A. 2 r :9 D !{27 W v 3 I l b I 1 2 43 7 a K 29 3 29 N I $279,- a 4 2| (1 2| d 4 3 I3 w I4 Q l I s 33 3 l5 4,150 F s PATENTEUMAR 71972 3,646,702

SHEET 1 [IF 2- INVENTOR REGINALD F. PIPP|N,JR

SHEET 2 OF 2 IV mm TD. N| EP V. mF D L A N G E P PATENTEDMAR '7 I972 PROPELLED TOY ARRANGEMENT This application is a continuation in part of my copending application Ser. No. 504,299, filed Oct. 24, 1965, now U.S. Pat. No. 3,510,980 dated May 12, 1970.

This invention relates to a propelled toy arrangement, and more particularly to a releasably fluid-pressurized missilelaunching arrangement, which preferably takes the form of a reaction propelled missile unit and which effects retention and subsequent release of and launching of one or more propelled missile units after decrease of fluid pressure in the misslelaunching unit.

It is a feature of the invention to provide a propelled toy arrangement in which one or more propelled missiles are releasably retained within one or more respective female openings on a launching unit which has a fluid pressurizable chamber a wall of which forms a flexible diaphragm movement of which wall diaphragm enables selective retention and release of the propelled missile as a function of pressurization and depressurization of the chamber in the launching unit.

Still a further feature is the provision of a toy missilelaunching toy in which the missile or missiles are launched from a selectively releasably pressurizable launching body, under the influence of propulsion means carried by the retained and released missile unit or units, and in which the missile unit or units are thus retained within and released from a female receiving opening formed in the launching body.

Another feature is the provision of a toy missile-launching and propulsion arrangement in which a missile or missiles are launched from a launching body under the influence of a selfcarried stored energy medium, and in which the launched missile or missiles are selectively retained and released as a function of pressurization and depressurization motion of a pressurizably movably retention diaphragm wall of the toy missilelaunching unit.

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

FIG. 1 is a longitudinal section view of a propelled toy rocket launcher and satellite missile embodiment according to the invention,

FIG. 2 is a cross section view taken on line 2-2 of FIG. 1,

FIG. 3 is a section view taken on line 3-3 of FIG. 1,

FIG. 4 is a section view taken on line 4-4 of FIG. 1,

FIG. 5 is a fragmentary section view of a modified missileholding and release arrangement,

FIGS. 6-9 are views similar to FIGS. l-4, illustrating a further modification,

FIG. 10 is a view similar to FIG. 5, illustrating still a further modification.

Referring now to the drawings, in FIG. 1 is shown a self- Q propelled liquid ejection-type reaction motor rocket toy 11 having a pressurizable liquid storage chamber 14 enclosed by annular sidewall 13, rear end wall 15 and

forward end wall

17, 19. Various suitable materials may be used, considering the required functions of the parts, including rubber or plastics such as nylon, polyethylene, Delvin, acetal resin,

polypropylene, etc. As in prior rocket toys of this general type the storage chamber 14 may be loaded through a discharge orifice with a charge of fuel in the form of liquid such as water W, and the chamber is subsequently pressurized and launched, normally in a generally vertical direction, from a suitable launcher. Various ground or initial launching arrangements may be used, such as that shown in the Holderer U.S. Pat. No. 3,046,694, or Krautkrawer U.S. Pat. No. 2,732,657.

The Holderer-type launcher is shown for purposes of illustration at 31, and is preferable since it is pressure-responsively self-releasing in action. This type launcher 31 includes a nodule detent 37 in a orifice-sealing stem 33 having a pressurizing bore 35 through which air and/or water may be pumped to effect desired pressurization of chamber 14, and subsequent self-release of the rocket 11 upon buildup of pressure beyond a given value within the chamber 14. Propulsion of the rocket 11 is effected by reaction from the discharge of liquid from the chamber 14 through orifice 15a, and in the illustrated and proferred embodiments stabilization of the rocket is effected by fins F, which are canted in the embodiment of FIGS. 1-4, to provide spin stabilization and other effects such as aiding in the launching of the satellites as will be described hereinafter. I

The nose section 21, which is preferably separately formed from the

lower section

13, 15, 17, 19 for ease of molding, may be secured to the lower section as by suitable adhesive, spin welding, etc., through a face junction with the upper surface of rigid wall section 19.

Rocket 11 also forms a launcher for one or more further missiles, and to this end rocket 11 in the illustrative embodiment carries two satellite, space capsule," or space ship missile members 41, the shape of which may be as desired, but which is preferably frustoconical with a planoconvex outer base end confonning to the general curvature of the adjoining outer surface of a nose section 11. This general shape enables advantageous holding and launching and has the added feature of resembling the general shape of early manned space capsules which are well remembered by children who may use this toy. The satellites 41 are each releasably held in their respective complementary female opening 21b by satellite missile-retaining means which in the illustrative and preferred embodiment takes the form of positive retention flexibly movable diaphragm wall which is urged into satellite missile retaining position by positive pressure in the liquid fuel storage chamber 14. In the illustrated embodiment each of these flexibly movable retention control wall diaphragms 17 acts to retain and release its respective missile unit 41 through an intermediary detent arrangement, although each may be directly effected through suitable modification. The detent arrangement takes the form of detent plungers riding in a respective guide bore 210 and having an enlarged lower end 27a and a smaller diameter detent end 27b which engages with a hole or recess 43 formed in the wall of satellite missile 4]. Compression springs 29 resiliently urge the detents away from satellite holding position, while positive pressure within chamber 14 effects movement of the detents upwardly against the compression springs 29 and toward engagement with shoulder stops 21d to effect holding engagement with the satellites 41, as shown in FIGS. 1 and 3. This upward movement is accomplished through upward flexing and expanding movement of flexible diaphragm sections 17 of the forward wall of chamber 14. Upon reduction of pressure in the chamber 14 below a critical leval, as a function of expulsion of the liquid W from the jet orifice 150, the springs 29 will overcome the upward force exerted on the

detent plungers

27a, 27b by the wall diaphragm sections 17 and the detents will be moved downward out of holding engagement with satellites 41, whereupon the satellites will be forcefully propelled outwardly from their respective compartments 21b, under the influence of the stored energy in previously compressed compression spring 25, and the centrifugal force exerted on the satellite missiles through the spin imparted to the rocket by canted fins F. If only spring ejection of the satellites is desired then fins F may be made straight as in the embodiment of FIGS. 6-9 to be subsequently described.

Due to the centrifugal ejection forces exerted on the off-axis satellites of FIG. 1 as a result of spin stabilization of the rocket by canted fins F it will be seen that one may also effect launching of the satellites from the rocket without employing spring 25, although this spring is most helpful and desirable in providing for greater launching distance of the satellites than is imparted by centrifugal force alone for a given spin rate. Likewise the spring 25 may be employed without the canted fins, particularly if direct radial or other predetermined straight line propulsion motion of the satellite missile is desired without rotary translatory motion imparted thereto.

A modified arrangement is shown in FIG. 5 in which the spring force is unequal on the two detents for the respective satellite missiles, thereby tending to effect movement of one detent out of holding engagement before the other. The satellite missiles 241 are retained in their compartments against the radially outward action of compressed compression spring 225 as in FIG. 1, through the medium of a common flexible wall diaphragm 217 which releasablymoves and holds detents 227b' and 227b" in engagement with respective detent receiving openings 243 in the satellite missiles as a function of pressurization and depressurization of the fluid pressurizable chamber in the rocket carrier and launcher vehicle 211.

Detents

227b and 227b", which may suitably be made of metal for desired strength, move in guide slots 263 and are integrally connected as a unit by an intermediate central connecting section 227a which is engaged by a compressed compression spring 251 disposed in a recess 223 above single unitary flexible diaphragm wall 217 and detent connecting section 227a. As recess 223 and spring 251 are off center with respect to detent section 227a the spring biasing action of spring 251 will be greatest on detent 227b" and this detent will thus tend to be moved down out of holding engagement with its respective satellite 241 before detent 227b, thereby releasing and enabling launching of this respective satellite before the other satellite missile. The unbalanced lateral reaction force exerted by launching a single satellite will cause the rocket to tile or yaw at that time, with probable change of rocket course, and subsequent launching of the other satellite will be along a different path than would have otherwise occurred with simultaneous release and launching.

The modifications of FIGS. 6-9 and 10, respectively, are similar to the embodiments of FIGS. 1-4 and 5, and accordingly do not require extensive description, as most of the elements or parts are the same as in the two previously described embodiments. In each of these two modifications, generally indicated at 1111 and 1211 in FIGS. 6-9 and 10, respectively, releasable storeable energy self-propulsion means is carried by the

satellite missiles

41 and 241 respectively. In these illustrative embodiments the releasable storeable energy self-propulsion means takes the form of a compression spring 25 (FIGS. 6-9) and 225a (FIG. secured in a well or cavity 41a (FIGS. 6-9) 241a (FIG. 10) formed in the

respective satellite missile

41 and 241. The storeable

energy compression spring

25 and 225 may be secured within their respective retention wells or cavities 41a, 241a, as by a tang extension 250, 225a thereon and extending into a retention aperture 41a (FIG. 7) formed in the wall of well or cavity 41a, 2410 adjacent the base thereof. The

springs

25 and 225 may be inserted and secured in their retention wells or cavities 41a, 2410 as by torsionally twisting and pressing such into the respective wells or cavities, and thereupon suitably effectively locking the spring tang extensions 25a, 225a in the respective retention apertures 41a.

The fins F in the embodiment of FIG. 6-7 are straight, and the satellite missiles 41 are self-propelled away from the

launcher missile

13, 21, etc., through the self-propelling action resulting from release of the stored energy of compression of the compressed springs 25, the spring and satellite missile action upon release by detents 27b being schematically illustrated in FIG. 6 in phantom lines and by the laterally directed motion arrows. It will, of course, be appreciated that canted tins and centrifugal force propulsion assist may also be used with either of the modifications of FIGS. 6 or 10 if desired, and that other stored energy means than compression springs 25, 225 may be employed within the purview of my invention. In preparing these embodiments for operation, the normally protruding self-propulsion compression springs 25, 225 are compressed into their retention wells 41a by end abutting engagement with the

inner wall

21b, 221b' of the respective female opening 21b, 22lb of the supporting and launching

missile

21, 221 etc., the self-propelled

satellite missiles

41, 241 being releasably retained within these

female openings

21b, 221!) by the heretofore described action of the pres surizably movable

flexible wall diaphragm

17, 217 and associated

detent

27, 227. Depressurization of the chamber 14 and associated wall diaphragm enables release and selfpropulsion of the

satellite missiles

41, 241 away from the primary missile forming the supporting and launching base therefor.

While the invention has been illustrated and described with respect to several illustrative physical embodiments thereof, it will be appreciated that various modifications may be made without departing from the scope and spirit of the invention. For instance, the flexible diaphragm wall section(s) could be made of highly elastic material and be self-retumable to a nonexpanded position, and by forming the satellite detents on the diaphragm or securing the detents to the movable diaphragm wall sections, or by otherwise forming the flexible wall diaphragm to directly engage and hold the satellite missile or missiles, the desired satellite or other releasable missile retention and release may be derived directly from the diaphragm elasticity or flexibility and with fewer parts. Also, while the satellites are disposed for launching substantially perpendicular to the rocket axis, and such is preferred, it will be apparent that generally other launch directions, both transverse and longitudinal, may be provided for one or more satellite missiles or other launched members. While two satellite missiles are shown and are normally adequate and preferred due to their balancing effect any desired number may be provided within the space available. Additionally, for ease of molding or otherwise forming the parts, the flexible

diaphragm wall sections

17, 217, etc., may be separately formed and suitably secured in sealed position as by a suitable cement, adhesive, or welding. It will thus be appreciated that the invention is not to be limited by the specific illustrative embodiments but only by the scope of the appended claims.

I claim:

1. A missile arrangement comprising a first unit having a female opening for releasably receiving a propellable missile second unit releasably securable to and propellable from said first unit,

a propellable missile unit having a portion thereof releasably engageable within said female opening,

fluid pressure responsively releasable unit-retaining means on said first unit and movable transversely within said female opening to releasably engage and retain said second unit with said first unit,

a fluid-pressurizable chamber in said first unit and in pressure responsively controlling relation to said releasable unit-retaining means,

and means for depressurizing said chamber to enable release of said propellable missile from said first unit.

2. A toy missile arrangement according to claim 1,

said fluid pressure responsively releasable unit-retaining means including a flexibly movable diaphragm forming a sidewall of said fluid pressurizable chamber.

3. A toy missile arrangement according to claim 2, said unitretaining means including a flexibly movable detent movable as a function of movement of said diaphragm.

4. A toy missile arrangement according to claim 2,

said second propellable missile unit having self-propulsion means effective to propel said propellable missile unit away from said first unit.

5. A toy missile arrangement according to claim 4,

said second propellable missile unit self-propulsion means comprising storeable-energy means on said second propellable missile unit.

6. A toy missile arrangement according to claim 5,

said storeable-energy means being operable to propel said second missile unit away from said first unit upon release of said second unit in response to depressurizing of said chamber in said first unit.

7. A toy missile arrangement according to claim 1,

said first unit being a self-propelled missile unit.

8. A toy missile arrangement according to claim 7,

said first unit including a selectively closable fluid propulsion discharge orifice connecting with said fluid-pressurizable chamber.

9. A toy missile arrangement according to claim 1,

said means for depressurizing said chamber including a selectively closable fluid-pressure-release orifice connecting with said fluid-pressurizable chamber.

10. A missile arrangement comprising a first unit having a female opening for releasably receiving a propellable missile second unit releasably securable to and propellable from said first unit,

fluid pressure responsively releasable unit-retaining means on said first unit and movable at and transversely relative to said female opening to effectively movably restrict a portion of the effective said female opening and to thereby releasably engage and retain said propellable missile second unit with said first unit,

a fiuid-pressurizable chamber in said first unit and in pressure responsively controlling relation to said releasable unit-retaining means,

11. A toy missile arrangement according to claim 10,

said unit-retaining means being movable transversely of said female opening to releasably constrict the effective said opening as a function of fiuid pressure in said fluid-pressurizable chamber, to thereby effect said releasable engagement and retention of said propellable missile second unit.

12. A missile arrangement comprising a first unit having a female opening for releasably receiving a propellable missile second unit releasable securable to and propellable from said first unit,

fluid pressure responsively releasable unit-retaining means on said first unit at and movable transversely of said female opening to change the effective lateral configuration of said opening and efiect releasable engagement and retention of said propellable missile second unit with said first unit,

13. A toy missile arrangement according to claim 12,

said unit-retaining means including a movable surface facing on said female opening and defining a movable wall portion therefor and releasably movably engageable with said propellable missile second unit.

Claims

1. A missile arrangement comprising a first unit having a female opening for releasably receiving a propellable missile second unit releasably securable to and propellable from said first unit, a propellable missile unit having a portion thereof releasably engageable within said female opening, fluid pressure responsively releasable unit-retaining means on said first unit and movable transversely within said female opening to releasably engage and retain said second unit with said first unit, a fluid-pressurizable chamber in said first unit and in pressure responsively controlling relation to said releasable unitretaining means, and means for depressurizing said chamber to enable release of said propellable missile from said first unit.

2. A toy missile arrangement according to claim 1, said fluid pressure responsively releasable unit-retaining means including a flexibly movable diaphragm forming a sidewall of said fluid pressurizable chamber.

3. A toy missile arrangement according to claim 2, said unit-retaining means including a flexibly movable detent movable as a function of movement of said diaphragm.

4. A toy missile arrangement according to claim 2, said second propellable missile unit having self-propulsion means effective to propel said propellable missile unit away from said first unit.

5. A toy missile arrangement according to claim 4, said second propellable missile unit self-propulsion means comprising storeable-energy means on said second propellable missile unit.

6. A toy missile arrangement according to claim 5, said storeable-energy means being operable to propel said second missile unit away from said first unit upon release of said second unit in response to depressurizing of said chamber in said first unit.

7. A toy missile arrangement according to claim 1, said first unit being a self-propelled missile unit.

8. A toy missile arrangement according to claim 7, said first unit including a selectively closable fluid propulsion discharge orifice connecting with said fluid-pressurizable chamber.

9. A toy missile arrangement according to claim 1, said means for depressurizing said chamber including a selectively closable fluid-pressure-release orifice connecting with said fluid-pressurizable chamber.

10. A missile arrangement comprising a first unit having a female opening for releasably receiving a propellable missile second unit releasably securable to and propellable from said first unit, a propellable missile unit having a portion thereof releasably engageable within said female opening, fluid pressure responsively releasable unit-retaining means on said first unit and movable at and transversely relative to said female opening to effectively movably restrict a portion of the effective said female opening and to thereby releasably engage and retain said propellable missile second unit with said first unit, a fluid-pressurizable chamber in said first unit and in pressure responsively controlling relation to said releasable unit-retaining means, and means for depressurizing said chamber to enable release of said propellable missile from said first unit.

11. A toy missile arrangement according to claim 10, said unit-retaining means being movable transversely of said female opening to releasably constrict the effective said opening as a function of fluid pressure in said fluid-pressurizable chamber, to thereby effect said releasable engagement and retention of said propellable missile second unit.

12. A missile arrangement comprising a first unit having a female opening for releasably receiving a propellable missile second unIt releasable securable to and propellable from said first unit, a propellable missile unit having a portion thereof releasably engageable within said female opening, fluid pressure responsively releasable unit-retaining means on said first unit at and movable transversely of said female opening to change the effective lateral configuration of said opening and effect releasable engagement and retention of said propellable missile second unit with said first unit, a fluid-pressurizable chamber in said first unit and in pressure responsively controlling relation to said releasable unit-retaining means, and means for depressurizing said chamber to enable release of said propellable missile from said first unit.

13. A toy missile arrangement according to claim 12, said unit-retaining means including a movable surface facing on said female opening and defining a movable wall portion therefor and releasably movably engageable with said propellable missile second unit.