US3803751A

US3803751A - Propelled toy arrangement

Info

Publication number: US3803751A
Application number: US00228279A
Authority: US
Inventors: R Pippin
Original assignee: Individual
Current assignee: Individual
Priority date: 1965-10-24
Filing date: 1972-02-22
Publication date: 1974-04-16
Anticipated expiration: 1991-04-16

Abstract

A missile arrangement including a self-propelled missile unit and one or more releasably held secondary units releasable from their held condition, the self-propelled missile unit having a fluid discharge orifice and a pressurizable substantially fluid tight fluid-pressure-responsively movable retention and release wall, which enables retention and release of the separable unit by respectively fluid-pressurizing and depressurizing the selfpropelled unit. A spring opposes pressure-responsive retention movement of the wall and resiliently urges the wall toward a release position. Several embodiments of a preferred springbiased fluid pressure responsive movable retention and release wall are illustrated, in the form of a flexible diaphragm retention and release wall.

Description

United States Patent Pippin, Jr.

11 .1 3,803,751 1*Apr. 16, 1974 1 PROPELLED TOY ARRANGEMENT [76] Inventor: Reginald F. Pippin, Jr., 7806 Ruxway Road, Towson, Md. 21204 Notice: The portion of the term of this patent subsequent to May 12, 1989,

has been disclaimed.

[22] Filed: Feb. 22, 1972 21 Appl. No.: 228,279

Related US. Application Data [62] Division of Ser. No. 36,120 May 11, 1970, which is a division of Ser. No. 504,299, Oct. 24, 1965, Pat. No.

Taubman 46/86 A 11/1965 Draglich 46/74 B x 5/1970 Pippin 463/74 R Primary ExaminerR0bert Peshock Assistant Examiner-R. Cutting Attorney, Agent, or F irm-Reginald F. Pippin,Jr.

[5 7] ABSTRACT A missilearrangement including a self-propelled missile unit and one or more releasably held secondary units releasable from their held condition, the selfpropelled missile unit having a fluid discharge orifice and a pressurizable substantially fluid tight fluid-pressure-responsively movable retention and release wall, which enables retention and release of the separable unit by respectively fluid-pressurizing and depressurizing the self-propelled unit.' A spring opposes pressureresponsive retention movement of the wall and resiliently urges the wall toward a release position. Several embodiments of a preferred spring-biased fluid pressure responsive movable retention and release wall are illustrated, in the form of a flexible diaphragm retention and release wall.

12 Claims, 10 Drawing Figures PAIENIE APR 1 61974 SHEET 10F 2 Fuss FIG. 9 w

PROPELLED TOY ARRANGEMENT This application is a divisional application of my copending application Ser. No. 36,120, filed May 11, 1970, which in turn is a divisional continuation-in-part of 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 fluidpressurized multi-unit missile, arrangement, which preferably takes the form of a reaction propelled missile unit and which effects retention and subsequent release of one or more releasably held units after decrease of fluid pressure in the self propelled missile unit.

It is a feature of the invention to provide a multi-unit toy missile arrangement in which a carried secondary unit on a self-propelled missile and depressurization movement and positioning of a substantially fluidsealed fluid-pressurizably-movable retention and release wall of the carrying missile unit, which movable retention and release wall is normally spring biased to its release condition, and which spring bias is opposed and overcome by propulsive pressurization of the missile unit during initial propulsion and travel of the multi-unit arrangement. The spring-resistance-biased fluidsealed fluidpressurizably-movable retention and release wall is illustrated in the preferred form of the flexible diaphragm wall which affords a fluid-sealed pressure-responsively movable retention and release wall for a secondary unit desired to be retained or held in a desired quiescent condition during an initial portion of flight and to be released for a selected purpose or function of the secondary unit, as may be desired, upon traversing an initial portion of the flight.

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 crossfsection view taken on line 2-2 of FlG. 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 FlG. 1,

materials may be used, considering the required functions of the parts, including rubber or plastics such as nylon, polyethylene, Delvin. acetal resin, polypropyh ene, 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 releasing in action. This type launcher 31 includes a nodule detent 37 in an 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 build-up 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 1 50, 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.

The nose section 21, which is preferably separately formed from the lower section l3, 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 frusto-conical with a plano-convex outer base end conforming to the general curvature of the adjoining outer surface ofa nose section 11. This general shape enables advantageous holding and launching and has the added feature of resembling the general shape of early nammed 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 41. 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 2 1d 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 level, 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 im parted 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 prede termined 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 releasably moves 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 1n the two the rocket axis, and such is preferred, it will be apparpreviously 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. 10) secured in a well or cavity 410 (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 25a-225a thereon and extending into a retention aperture 410 (FIG. 7) formed in the wall of well or cavity 410, 241a adjacent the base thereof. The

springs

25 and 225 may be inserted and secured in their retention wells or cavities 41a, 241a 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 FIGS. 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 fins 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, 22lb of the respective female opening 21b, 22]!) of the supporting and launching

missile

21, 221 etc., the self-propelled

satellite missiles

41, 241 being releasably retained within these female openings 21b, 22lb by the heretofore described action of the pressurizably 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 there0f, 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-returnable 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 ent that generally other launch directions, both transverse and longitudinal, may be provided for one or more satellite 'nissiles 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.

Also, it will be appreciated that other embodiments or forms of fluid-pressure-responsively releasably secured secondary units may be utilized, such as a releasable parachute unit as shown in FIGS. 8 and 9 of the reference original parent application Ser. No. 504,299, (now U.S. Pat. No. 3,510,980) in which instance the releasable parachute may be, and preferably is, secured as through shroud lines to the self-propelled carrier unit, or may be fully separable therefrom. Such parachute unit may, and preferably does, incorporate a fluid-pressure-responsively releasably held retention cover of suitable construction and configuration, if and asmay be desired, one illustrative form ofa suitable releasable cover releasably held by a fluid-sealed pressure-responsively movable retention-and-release wall being illustrated in FIGS. 8 and 9 of the referenced parent application Ser. No. 504,299. It will also be appreciated that while other forms of fluid-sealed fluidpressure-responsive retention-and-release walls may be utilized, such as a fluid-sealed movable piston wall as shown in said parent application Ser. No. 504,299, the preferred embodiment takes the-form of a flexible diaphragm wall. 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.

That which is claimed is: l. A propelled toy arrangement comprising a first self-propelled unit including a body having a pressurizable fluid chamber and a fluid discharge orifice in fluid connection between said chamber and the outside atmosphere, said body having a fluid-pressure-responsively movable retention-and-release wall in fluid connection with and movable in response to pressure in said chamber, a second unit releasably held and carried in a first secured condition relative to and by said first unit as a function of the position of said movable wall in response to internal fluid pressure in said body chamber, v and a spring acting on and opposing fluid-pressureresponsive retentive movement of said movable wall, said spring resiliently urging said movable wall section toward a release position for release of said releasable second unit from its said first secured condition. 2. A propelled toy arrangement according to claim 1,

said spring being a compression spring movable in.

tion-and-release wall. I 3. A propelled toy arrangeme'pt according to claim 1,

said spring being disposed for direct contact with said wall.

4. A propelled toy arrangement according to claim 1,

and a further member movable by said wall and releasably engagable with said releasable second unit to effect retention and release of said releasable second unit as a function of movement of said wall under the opposing forces of fluid pressure and said spring. g

5. A propelled toy arrangement according to claim 4,

said second unit having a detent-receiving recess formed therein,

said further member being a positive detent positively releasably engagable with said detentreceiying recess.

6. A propelled toy arrangement according to claim 4,

said further member comprising a slidable piston. 7. A propelled toy arrangement according to claim 1,

said wall being formed by a flexible diaphragm.

8. A propelled toy arrangement according to claim 7, I

release wall in fluid connection with and movable in response to pressure in said chamber, and a second non-fluid-pressurized unit releasably held and carried in a first releasably retained condition relative to and by said first unit as a function of the retentive positioning of said movable retentionand-release wall in response to internal fluid pressure in said body chamber, and being released from said first retained condition as a function of movement of said wall to a retracted release position upon decrease of fluid pressure in said chamber. 10. A propelled toy arrangement according to claim said retention-and-release wall comprising a flexible diaphragm wall. 11. A propelled toy arrangement according to claim 10,

said diaphragm wall being elastically deformable and self-returnable to a quiescent retracted release condition upon decrease of fluid pressure thereon.

12. A propelled toy arrangement according to claim 1 and a spring opposing retentive movement positioning of said diaphragm wall.

Claims

1. A propelled toy arrangement comprising a first self-propelled unit including a body having a pressurizable fluid chamber and a fluid discharge orifice in fluid connection between said chamber and the outside atmosphere, said body having a fluid-pressure-responsively movable retention-and-release wall in fluid connection with and movable in response to pressure in said chamber, a second unit releasably held and carried in a first secured condition relative to and by said first unit as a function of the position of said movable wall in response to internal fluid pressure in said body chamber, and a spring acting on and opposing fluid-pressure-responsive retentive movement of said movable wall, said spring resiliently urging said movable wall section toward a release position for release of said releasable second unit from its said first secured condition.

2. A propelled toy arrangement according to claim 1, said spring being a compression spring movable in compression to a compressive force reactive condition in oppositional response to positive fluid pressure in said fluid chamber and resultant retentive movement and positioning of said movable retention-and-release wall.

3. A propelled toy arrangement according to claim 1, said spring being disposed for direct contact with said wall.

4. A propelled toy arrangement according to claim 1, and a further member movable by said wall and releasably engagable with said releasable second unit to effect retention and release of said releasable second unit as a function of movement of said wall under the opposing forces of fluid pressure and said spring.

5. A propelled toy arrangement according to claim 4, said second unit having a detent-receiving recess formed therein, said further member being a positive detent positively releasably engagable with said detent-receiving recess.

6. A propelled toy arrangement according to claim 4, said further member comprising a slidable piston.

7. A propelled toy arrangement according to claim 1, said wall being formed by a flexible diaphragm.

8. A propelled toy arrangement according to claim 7, said flexible diaphragm forming a closed flexible wall of said chamber.

9. A propelled toy arrangement comprising a first self-propelled unit including a generally rigid body having a pressurizable fluid chamber and a fluid discharge orifice in fluid connection between said chamber and the outside atmosphere and being fixed in directional orientation during fluiD discharge therethrough, said first self-propelled unit having a fluid-sealed fluid-pressure-responsively movable retention-and-release wall in fluid connection with and movable in response to pressure in said chamber, and a second non-fluid-pressurized unit releasably held and carried in a first releasably retained condition relative to and by said first unit as a function of the retentive positioning of said movable retention-and-release wall in response to internal fluid pressure in said body chamber, and being released from said first retained condition as a function of movement of said wall to a retracted release position upon decrease of fluid pressure in said chamber.

10. A propelled toy arrangement according to claim 9, said retention-and-release wall comprising a flexible diaphragm wall.

11. A propelled toy arrangement according to claim 10, said diaphragm wall being elastically deformable and self-returnable to a quiescent retracted release condition upon decrease of fluid pressure thereon.

12. A propelled toy arrangement according to claim 10, and a spring opposing retentive movement positioning of said diaphragm wall.