US3166322A - Toy satellite system - Google Patents

Description

Jan. 19, 1965 1.. BRANNEMAN TOY SATELLITE SYSTEM 4 Sheets$heet 1 Filed Oct. 1, 1963 INVENTOR. LEONARD B IZANN E M AN ATTORNEYS Jan. 19, 1965 L. BRANNEMAN TOY SATELLITESYS TEM 4 Sheets-Sheet 2 Filed Oct. 1.

INVENTOR. LEONARDBRANNEMAN BY M 8m ATTORNEYS Jan. 19, 1965 L. BRANNEMAN TOY SATELLITE SYSTEM 4 Sheets-Sheet 3 Filed Oct. 1, 1963 m T N E V m ATTORN EYS 1955 I 1.. BRANNEMAN 3,166,322

TOY SATELLITE SYSTEM Filed Oct. 1, 1965 4 Sheets-Sheet 4 INVENTOR. LEONARD BQANNEMAN ATTORNEY$ Another object of the invention s United States Patent Office aissszz Patented Jan. 1%, I985 1 ,1 2 TGY SATELLITE- SYSTEM Leonard Brannernan, 9 Shelfield Road, Winchester, Mass.

Filed Get. 1, 1963, Set. No. 313,626 5 Claims. (Cl. 273--95) This invention relates to a novel toy satellite system.

The primary object of the invention is the provision of a highly realistic, amusing, and educative system of the kind indicated, which includes a simulated launching pad having a spring-operated launcher, a moon ship or multi-stage rocket having a first-stage, adapted to be launched by the launcher to and to be held magnetically by a space stratum, from which a simulated second-stage is spring-launched, by the first-stage, to a moon, to which the second-stage is held magnetically, the second-stage having spring-operated,launching'meansfor a satellite carried thereby, whereby the satellite is launched into an moves the same; around the planet.

planet. of the character indicated above, of a planet which contains an electrically driven magnet assembly which is energized by a solar battery, which is operable either by sunlight orelectriclight. V z

Otherirriportant objects and advantageous features of the provision, in a FIGURE 12 is a transverse section taken on the lin orbit around a planet, the planet having a rotating magnet assembly whichdriaws the. satellite to the planet and 2 0 12 12 of FIGURE 11. r 1

Referring in detail to the drawings,'the illustrated satellite system comprises a launching pad LP, one or more multi-stage rockets or moonships R, a space station ST, a moon M, and a planet P, suitably supported above and down-line from the launching pad.

The launching pad LP comprises a frusto-pyramidical stand 12 having a rectangular base plate 14, from whose corners fixed upwardly convergent legs 16 extend to and are fixed to the corners of a rectangular platform 18, the last being smaller in area than and centered relative to the base plate 14. A perpendicular first-stage launching tube is fixed, at its lower end, to the center of the base plate 14 and extends upwardly through acentered opening 22, provided in the platform 18, to a substantial heighttabove the platform. I

\ As shown in FIGURES 2 through 4, the launching tube 29 is open,iat its upper end, which has an upper edge which has, on its side thereof facing the space between S, an upstanding leg 24, on which is fixed aver-j *tical flat permanent magnet 28.

At a-level spaced below the platform 18 andabove the base plate 14, the launching tube iZtl-has anintcrnal the inventionwill be apparent from the following description and the accompanying drawings, wherein, for purposes of illustration only, a specific form of the invention is set forth indetail.

FIGURE 1 is a schematic perspective view of a satellite system of the present invention, showingia multi-st'age rocket intransit between the launching pad and .a space .station a second multi-stage held by the space section,

a second-stage of the latter being shown in transit to a moon, another second stage frna'gnetically held to the moon, and a satellite in transit between the second stage in transit to the planet,- and another satellite inlorbit around the planet;

FIGURE 2 is an enlarged vertical transverse section taken on the line 22 of FIGURE 1, showing the multistage rocket in place in the launcher, with'its trigger spring retained in inoperative position, and the launching spring retained in compressed condition;

FIGURE 3 isa fragmentary view, like FIGURE 2, showing the multi-stage". rocket emerging from the launcher, with its trigger spring released and its tilting magnet repelled by the tilting magnet of the launcher, for tilting the rocket, as shown in phantom lines, into a trajectory to reach the space station;

FIGURE 4 is a horizontal sectlon taken on theline 4-4 of FIGURE 2; r

FIGURE 5 is a vertical longitudinal sectiontaken on the line 5-5 of FIGURE 1, and a multi-stage rocket securedrnagnetically thereto, and a second stage being propelled therefrom; l 1

FIGURE 6 is a vertical transverse section taken on the line ,6-6 of FIGURE 5;

FIGURE 7 is a side elevation, partly broken away and in section, of the moon, showing the magnet holding a second-stage to the moon;

FIGURE 8 is a vertical longitudinal section showing the said second-stage launching the satellite;

FIGURE 9 is a vertical transverse section taken on the line 99 of FIGURE 8;

FIGURE 10 is an enlarged vertical transverse section taken on the line Ill-10 of FIGURE 1, showing a satellite adhered thereto and inorbit therearound;

11-11 of FIGURE lilgand ,partition 3%, formed with a; central opening 32,: through The rod 34 has a fixed, enlarged diameter collar as, on its lower end,

'which a cylindrical. plunger rod 34 works.

beingadapted to engage thepartition 36 as the spring 38 drives the rod 34 upwardly, and absorb the resultant shock and noise.

tube 265 and forcing the same downwardly until the pad" 4% is on a level below a radial bore 43, in the side wall of the tube 29. The bore 43 is providedto receive a removable stop pin 45, adapted to engage the top of the pad 4% and hold the rod 34 down in cocked position. The pin 45 has a ring 4'7, on its outer end, to which a releasing cord 49 is secured, which is; adapted to be pulled to retractthe pin 45 and release the plunger rod for propelling the rocket assembly R out of the launching tube. The multi-stage rocket R comprises a longitudinally elongated hollow cylindrical casing 44, having a uniform diameterside wall 46, and a rear end wall 48, provided with a centered air-vent opening 59. The side wall 46 is formed with a pair of diametrically opposed, longitudinal fins 52, which, as shown in FIGURE 4, are positioned in longitudinal guide slots 54, provided in the side wall of the launching tube 2%, for properly positioning the rocket R therein.

A second stage launching spring 56 is positioned in the casing 44, with its lower end suitably secured to the end wall 48, and with its upper end suitably secured around a reduced diameter boss 58, on the lower end of a cylindr-ical plunger 6d. The lower part of the plunger 6d is smaller in diameter than andcentered in the casing 44,

and has an enlarged diameter upper portion 62, which bears slidably against the side wall 46 of the casing 44.

The rod 34 has an enlarged diameter 3 head 42 on its upper end, above the partition. 30, which the space station ST.

An annular detent groove 645 encircles'the plunger below the'upper portion 62. g The detent groove 64 is provided to receive 'an intermediate detent lug 66 on a longitudinally elongated trigger leafspring 68, working-through slot 7t), in the casing side Wall as.

The spring? has its'u pper portion suitably fixed to the exterior of-theside wall 46, as indicated at 72,- and the lower portion of the spring is outwardly biased, away from the casing 44. An outwardly directed detent lug 74,-on. the lower end of the spring es, is engaged in a slot 76, in the bottom wall of a housing 82.

A downwardly tapering wedge 78 is fixed to the outer surface of the'uppe r part of the spring 68, and is part ofa time-delay assembly' fitl, which comprises a longitudinally elongated, relatively small cross section-rectangular hollow housing 82, which is atfixed to the side wall dd'and encloses thespring 63. The bottom Wall 8 50f the housing82 is formed with a second wedge 86 opposed to and reversed with respectto the wedge 73. An elon- 1 7 gated flexible and resilient capsule 83 extends alongand .is fixed to the inner-side of the wedge 86. I The capsule is closed and contains a body of fluid, suchas oil, whose volume is less than the'volumatiocapacity of'the capsule.

The capsule is provided, midway between its ends, with a partitionWall 92, which is formedwith a bleeder opening 95'.

, provided, on its rear end, with a pair of opposed arcuate spring fingersl iZ, whichireleasably retain a magnetizable spherical satellite S, which, in the unlaunched condition of the second stage $6, 'the satellite is protectively con- 'tained with the launching tube 104, as shown in FIG- URE 2, in which retraction, thespring Mil is compressed, and the intermediate triggerspring lug 13th is engaged in the notch 134 of the rod 136.

' As the rocketR reaches and magnetically adheres to 1 the space station S, the lower part'of its capsule having having embedded dhfileilhfill elongated bar rnagnet 148,

P, and has an end 159 exposed flush with the surface v: -ofQt-he bodyl-M. 'Asthe second stage %"-reaches the in, the launch position, shown in FIGURE 2,,the. captained inits inoperative position, against the casing side the upper partgof the capsule, through theybleeder hole sothatthetrigger' spring 63 is freed to swing outwardly, .and releasethe plunger etl, to drive out ofthe of the rocket R, they repel each other and tilt the rocket The'plunger 6% is formed, in its with a circular socket l-L02, in which is adapted to seat the open rear end of a relatively small diameter launching tube 164,

jsule is'under minimal compression, and its fluid lies'in the lower portion thereof, so that the spring 68 is main-"2 wall 26. When the socketR-is launched, the'wedge 78,-

in moving upwardly past'the-wedg'e 86, squeezes the lower part of the capsule" so that the fluid is forced up into The bottomwall of the'housingZlZ hasan opening 98, j at itslower, end, which exposes a flat permanent magnet 31% of opposite polarity to the, launchingttibdmagnt 238;, so that as these magnets pass each other," on-launch' t I I stellite with theplanet P. R, as indicatedin FIGURE 3', into trajectory to'reach' I ofi the second-stage 6; The launching tuoeltld is suremeterforward portion 168, which has a sliding lit in the I casing and a rearwardly tapered rear portion 11th.

rounded by a'body 1% of non-metallic resilient-material,

such as rubber or plastic material, which has a full diwhich is disposed in an upward angle toward the planet top of the moon M, it tumbles forwardly thereo-ver, as

indicated in FIGURE 7, and; on' 'reaching' thevicinity or the magnet end 15%, the disc magnet liteof the second stage 96 is attracted to andbecom'es magnetically adhered to the magnet endlStl, with its launchingtube 104 directed, at an upward angle toward the planetjP,

As the trigger spring 125 of the second stage 96 moves farther away from the launching tube 1M," its intermediate lug 1% is withdrawn fromthe' notch 134 in the plunger rod 136, so that plunger rod is driven part way out of the tube, and, on being arrested, the satellite 3 is released from between the spring fingers 142, and travels to the planet P. Y i

I As shown in the satellite S; comprises a "sphericalmagnet core rsz surrounded by a thick cover 154 t of resilient and compressible material, such as rubber or plastic material, soastoavoiddamaging contact of the As shown in FIGURES l0and 11, the planet P is spherical and comprises an outer plasticimaterial shell 156 and a concentric inner plastic material shellidd, which are spaced and connected by radial ribs 16%. Both of these shells can be'transparent. V

Relatively small magnets 1'74 are secured to the {inner surface of the inner shell 15%, which serve to retract and draw 'toward the planet P,'a satellitell58 nearing the A disc 1K2 of the diameter of the casing 54-, is atlixed to V and closes the forward end of the tube 394, and carries, on itsexposed surface, a flat disc magnet 114.

An elongated hollow rectangular housingv 116, shorter than the launching tube M54 is aflixed thereto, and has a closed forward end lit? and an open rear end 12%. A compressible resilient time-delay capsule 122, similar to the capsule $3, is affixed to the bottom wall 124 of the housing 116, and biases against an elongated fiat trigger leaf spring 112e, which is fixed, at its forward end, to the easing side wall 45, and is outwardly biased therefrom.

Thespring 126' extendsrearwardly out of the housing ill- 5, and has, on its rear end, an outwardly directed detent lug 128, which bears against the casing, side wall 46, and an intermediate inwardly extending detent lug 13h, whichin the inoperative position of the spring 126, engages through a slot 132', provided in the side wallof the tube 1%, andengages retainablyin a notch 134, intermediate the ends of an elongated plunger rod136, which works in the launching tubeltld. The'plunger rod 136 is shorter than the, tube lltl iand has a reduced, di- I ameter boss 133,011 its forward end, around which is se cured the adjacent end of acoilspring Md, whose other end is suitably secured to the disc H2. "The rod 136 is planet, and to assist in its being carried around the planet by a magnetic rotor 176. j j

The magnetic'rotor I176 is disposed within the inner shell 15% on a horizontal diameter of theplanet, and comprises an'elongated fiat barl7$ havingheavy thick magnet blocks 11% fixed thereon at the ends of the bar and positioned close to the inner shell 15%. The bar 178 is fixed, at its center, on a cup 1E2, which receives an up standing perpendicular shaft'lfi, to whichit is pinned, as indicated at 186. The shaft res is supportably journaledthrough the upper member. 133 of. a gear frame 1%, which, at its lower end, is fixed to a base frame 15 2 which is fixed, at its lower end, to the inner shell 15%. [in electric motor li ht is mounted upon the cross member 1% of the base frame 192 and has an upstanding shaft 198, which is operatively connected to speedreducing gearingfldtt, supported Within the gear frame 1% and operatively connected to'the rotor shaft 18 4, thereby the rotor 176 is rotated at a relatively slow speed. An outwardly facing solar battery 2&2 is fixed between the shells and connected to the motor.

The planet P is suspended,- as from a ceiling (not shown) or the-'like, by means of a wire or cord 21%, which is secured, asindicated at 2%, to the inner shell 15%, at the top thereof, andfpasses up through a hole 210 in the the planet outer underside is flush with the underside of the block 12. An upstanding eye 226 is secured in the top of the block 212, at a point forwardly of the middle of the block,

so that the space station assumes an upwardly and for wardly tilted position, when suspended by a cord or wire 222, connected to the eye 220, from a support such as a ceiling (not shown). The magnet 218 serves to attract a multi-stage rocket assembly R reaching the immediate vicinity of the space station ST to the space station and hold the same in contact therewith, by means of the attraction of the magnet 218 foran elongated fiat magnet 219 which is secured along the top of the casing 44 of the rocket assembly R. i

The fact that the space station magnet 218 has north and south poles serves to position the space station with its north pole pointing toward the terrestial north pole. Be-

cause of this position of the space station, the launching pad LP and the planet P must be lined up with the space station ST. Further, the space station ST must be positioned at the right height, relative to the trajectory of. a rocket assembly R propelled from the launching pad LP, so that the assembly R will reach the space station on a line below and close to its underside and the magnet 218 of the space station. The planet P must be suspended at such a height that a satellite propelled toward the satellite would arrive thereat ideally in the plane oi. the equator and at either side of the planet.

It will be understood that the invention herein disclosed, is not limited to the use of only one moon, and that all of the components can be used in multiple.

While there has been shown and described a preferred form of the invention, it is to be understood that the invention is not necessarily confined thereto, and that any change or changes in the structure of and in the relative arrangements of components thereof are contemplated as being within the scope of the invention as defined by the claims appended hereto.

What is claimed is:

1. A satellite system comprising a lunch pad, a space station spaced above and down-line from the launch pad, said station having a magnet on its underside, a moon in line with and spaced down-line from the space station and having a magnet on the side thereof remote from the station, a planet in line with and spaced down-line from the moon, said planet having rotating magnet means therein, a multi-stage rocket having a magnet on its upper side to be attracted to and held by the space station magnet when launched from the launching pad, said rocket having a second stage and means for launching the second stage toward the moon as the rocket reaches and is secured to the space station, said second stage having a magnet to be attracted to and held by the magnet of the moon, said second stage having a releasable'magnetizable satellite, and means for launching the satellite toward the planet as the second stage is secured to the moon, the satellite being adapted to be attracted and moved around the planet by its rotating magnet means.

2. A satellite system according to claim 1, wherein said launching pad comprises a vertical launching tube containing an upwardly spring-pressed plunger rod, and means for releasably holding the plunger rod in depressed cocked position, said rocket being releasably engaged in the' launching tube and resting upon said plunger rod, said rocket comprising a vertical tube smaller in diameter than the launching tube and having a vented bottom wall resting 'upon the plunger rod, an upwardly spring-pressed plunger sliding in the rocket tube, a trigger leaf spring fixed at its upper end to the side wall of the rocket tube and having a lower portion biased away from this side wall, said spring having an inwardly extending intermediate detent lug, the side wall having an opening passing the lug and the plunger having an annular groove receiving the lug in the compressed condition of the plunger, a longitudinal hollow housing fixed on the'side of the rocnet tube opposite the magnet, said housing having a bottom wall iormed with an opening, said spring having an outwardly extending lower detent lug at its lower end engaged through the bottom wall'opening and bearing against the sidewall of the launching tube, oppositely disposed and facing wedges on the housing bottom wall and the side wall of the rocket tube, a resilient and compressible time-delay capsule secured to one of the wedges and engaged with the other, said capsule containing liquid and having a partition wall intermediate its end provided with a blender opening, and said second-stage engaged in the rocket tube and resting uponthe plunger.

3. A satellite system according to claim 2, wherein the plunger has a centered socket in its upper end, said second-stage comprising a launching tube smaller in diameter than the rocket tube and having an open lower end engaged in said socket, said magnet on said second stage being a disc magnet closing the upper end of the secondstage tube, the second-stage tube being surrounded by a cylindrical body of compressible and resilient material sliding in the rocket'tube, a downwardly spring pressed plunger rod in the second-stage tube having a notch in one side thereof, a hollow housing fixed to and extending along one side of the second-stage tube and having an open lower end, said second-stage housing having a bottom wall, a trigger leaf spring fixed at its upper end to said bottom wall of said second stage housing and having a lower portion biased away from the side wall of said second stage housing, the side wall of the second- ,sule similarto the first-mentioned time delay capsule secured along the bottom wall of the second-stage housing and engaging the outerside of the second-stage trigger spring, said plunger rod in said second state having opposed spring fingers on its lower end, said satellite comprising a magnetizable sphere releasably engaged between the fingers.

4. A satellite system according to claim 3, wherein said second-stage trigger spring has an outwardly extending lug on its lower end adapted to engage the side wall of the rocket tube to hold the second-stage spring inwardly with its intermediate lug in retaining engagement with the plunger.

5. A satellite system according to claim 3, wherein said satellite comprises a magnetizable core and a nonmetallic resilient and compressible cover.

References Cited in the file of this patent UNITED STATES PATENTS 647,327 Rehlin Apr. 10, 1900 2,923,009 Fissel Feb..2, 1960 2,975,551 Oberinger Mar. 21, 1961 3,032,918 Giuliano May 8, 1962 3,108,395 Goldfarb Oct. 29, 1963 LOUIS R. PRINCE, Primary Examiner.

Claims (1)

1. A SATELLITE SYSEM COMPRISING A LAUNCH PAD, A SPACE STATION SPACED ABOVE AND DOWN-LINE FROM THE LAUNCH PAD, SAID STATION HAVING A MAGNET ON ITS UNDERSIDE, A MOON IN LINE WITH AND SPACED DOWN-LINE FROM THE SPACE STATION AND HAVING A MAGNET ON THE SIDE THEREOF REMOTE FROM THE STATION, A PLANET IN LINE WITH AND SPACED DOWN-LINE FROM THE MOON, SAID PLANET HAVING ROTATING MAGNET MEANS THEREIN, A MULTI-STAGE ROCKET HAVING A MAGNET ON ITS UPPER SIDE TO BE ATTRACTED TO AND HELD BY THE SPACE STATION SIDE WHEN LAUNCHED FROM THE LAUNCHING PAD, SAID ROCKET HAVING A SECOND STAGE AND MEANS FOR LAUNCHING THE SECOND STAGE TOWARD THE MOON AS THE ROCKET REACHES AND IS SECURED STAGE THE SPACE STATION, SAID SECOND STAGE HAVING A MAGNET TO BE ATTRACTED TO AND HELD BY THE MAGNET OF THE MOON, SAID SECOND STAGE HAVING A RELEASABLE MAGNETIZABLE SATELLITE, AND MEANS FOR LAUNCHING THE SATELLITE TOWARD THE PLANET AS THE SECOND STAGE IS SECURED TO THE MOON, THE SATELLITE BEING ADAPTED TO BE ATTACTED AND MOVED AROUND THE PLANET BY ITS ROTATING MAGNET MEANS.

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