FIELD
The present invention relates generally to toy rockets that use parachutes and methods of preparing such rockets for launch.
BACKGROUND
Toy rockets have been known to provide amusement, particularly to children. Such rockets and their launchers are described in U.S. Patent Pub. Nos. 2006/0089075 and 2006/0225716. To prevent damage to the rocket and to provide greater entertainment, it is known that a parachute may be used to slow the rocket's descent. Examples of toy parachutes are described in U.S. Pat. Nos. 1,765,721, 2,937,474, 4,005,544 and 6,902,460. It is generally appreciated that a parachute that deploys faster will result in a longer descent. Prior art parachutes are attached to the rocket by string, as in U.S. Pat. No. 3,751,850, or rigid ribs, as in U.S. Pat. No. 2,008,107. Unfortunately, string may become easily tangled, which can cause difficulty and frustration when attempting to prepare for a launch. Tangled strings may also result in non-uniform parachute deployment. On the other hand, rigid spars suffer from increased weight, which may limit the achievable altitude, and may also suffer from greater susceptibility to breaking Both strings and rigid spars can lead to slow parachute deployment.
SUMMARY
A parachute rocket toy in which the parachute is attached to the rocket by spars is provided. The spars are attached to the rocket through a connector ring, which may slide along the body of the rocket. As the rocket reaches the apex of flight, the parachute deploys to slow the descent to Earth.
A preferred embodiment uses semi-rigid spars attached to the connector ring. As a portion of the parachute deploys, it may pull on the closest spars, which in turn pull the connector ring to the top of the rocket. As the connector ring slides to the top of the rocket, it pushes all the spars, and thus the parachute, outward, resulting in a faster and more uniform deployment. The spars avoid the problem of tangled strings and allow for quick reset for another launch.
Additionally, a tail may be wrapped around the parachute to hold it in a more aerodynamic and drag-free position for launch and ascent. The tail may unwrap during flight, after which the parachute may deploy. The deployment may be facilitated by the unwrapped tail.
According to an exemplary embodiment of the present invention, a toy rocket is disclosed, and comprises an elongate body; a connecting ring, a plurality of at least partially rigid spars. The connecting ring is slidably disposed around the body, and the parachute is reconfigurable between a collapsed condition and an open condition. The plurality of at least partially rigid spars connects the parachute and the connecting ring.
In exemplary embodiments, one or more fins extend from the body.
In exemplary embodiments, a tail extends from the parachute.
In exemplary embodiments, the body includes an interior cavity for receiving fluids.
In exemplary embodiments, at least one spar of the plurality of at least partially rigid spars is connected to an edge portion of the parachute.
In exemplary embodiments, the plurality of at least partially rigid spars is pivotably connected to the connecting ring.
In exemplary embodiments, each spar of the plurality of rigid spars includes a ball configured for insertion into a corresponding socket of the connecting ring.
In exemplary embodiments, the connecting ring includes at least one interior groove for mating with a rail disposed along the body.
In exemplary embodiments, a stopper member is affixed to an end of the body.
In exemplary embodiments, the stopper member restricts movement of the connecting ring past the stopper member.
According to an exemplary embodiment of the present invention, a method of using a toy rocket is disclosed, and comprises (a) providing a toy rocket comprising an elongate rocket body attached to a parachute; (b) sliding a connecting ring disposed around the body toward the tail end so that a plurality of at least partially rigid spars interconnecting the connecting ring and the parachute are disposed in a substantially vertical orientation; (c) folding the parachute into a collapsed configuration about the rocket body; and (d) launching the toy rocket so that after reaching an apex of height, the rocket body slides downwardly through the connecting ring so that the plurality of at least partially rigid spars move the parachute in a radially outward direction.
In exemplary embodiments, the method further comprises wrapping a tail of the parachute about the parachute in the collapsed condition.
In exemplary embodiments, movement of the parachute in a radially outward direction causes the parachute to reconfigure from a collapsed configuration to an open configuration.
In exemplary embodiments, the step of launching the toy rocket comprises providing pressurized fluid into an interior cavity of the body.
BRIEF DESCRIPTION OF THE DRAWINGS
Exemplary embodiments of the present invention will be described with references to the accompanying figures, wherein:
FIG. 1 is a front view of a rocket of the present invention with a parachute deployed.
FIG. 2 is a front view of a rocket with a parachute retracted.
FIG. 3 is a front view of a rocket without a parachute attached.
FIG. 4 is a bottom view of a deployed parachute.
FIG. 5A is a side view of an exemplary construction of a spar connector ring.
FIG. 5B is a top view of an exemplary construction of a spar connector ring.
FIG. 6 is a side view of a spar.
FIG. 7 is a top view of a tail.
FIG. 8A is a top view of another construction of a tail.
FIG. 8B is a top view of a further construction of a tail.
FIG. 9 is a front view of another embodiment of a rocket of the present invention with a parachute deployed.
FIG. 10 is a front view of a rocket with a parachute retracted.
FIG. 11 is a front view of a rocket without a parachute attached.
FIG. 12 is a top view of a deployed parachute.
FIG. 13 is a side view of a user holding a rocket by the tail.
FIG. 14 is a side view of a user holding a rocket with the spars retracted.
FIG. 15 is a side view of a user holding a rocket around the spars.
FIG. 16 is a side view of a user beginning to fold a parachute around a rocket body.
FIG. 17 is a side view of a user folding a parachute around a rocket body.
FIG. 18 is a side view of a user holding a rocket with a folded parachute.
DETAILED DESCRIPTION
The headings used herein are for organizational purposes only and are not meant to be used to limit the scope of the description or the claims. As used throughout this application, the words “may” and “can” are used in a permissive sense (i.e., meaning having the potential to), rather than the mandatory sense (i.e., meaning must). Similarly, the words “include,” “including,” and “includes” mean including but not limited to. To facilitate understanding, like reference numerals have been used, where possible, to designate like elements common to the figures.
The present invention is described with respect to the following embodiments. The embodiments are illustrative only and are not intended to limit the invention.
It will be appreciated by those in the art that the present invention may be employed with any aerial projectile for which it is desirable to attach a parachute.
The embodiment of the present invention depicted in FIG. 1 includes a rocket 26 connected to a parachute 3. Parachute 3 may be referred to as a canopy. Parachute 3 may be constructed of silk, nylon, deformable plastic, or other deformable materials known in the art. The rocket 26 can include a rocket body 5, which may be an elongated shaft or tube. Body 5 may be solid or hollow such that an interior cavity is defined in body 5. A stopper 4 is disposed at the end 101 of rocket 26. In embodiments, stopper 4 may have a flexible and/or resilient configuration such that stopper 4 presents a soft and/or collapsible structure.
As shown, fins 7 may be attached to the body 5 of the rocket 26. Fins 7 may be straight, angled, curved, or otherwise shaped and may provide guidance, stability, and/or spin, in addition to or alternative to other aerodynamic effects on rocket 26. In embodiments, fins 7 may be provided for ornamentation. In the embodiment of FIG. 1, the fins 7 are located at the base 102 (FIG. 3) or tail of the rocket 26. A pair of washers 8a and 8b may circumferentially engage the body 5 of rocket 26, and may be held in place by friction or otherwise coupled with the body 5 of rocket 26 by techniques known in the art, such as gluing, or may be held in place by stoppers on one or more ends of the washers 8a and 8b. In embodiments, fins 7 may be compressibly held between washers 8a and 8b such that fins 7 are prevented from sliding along the rocket body 5. In embodiments, washers 8a and 8b may overlie portions of fins 7 such that fins 7 are maintained in a desired position on body 5 of rocket 26. Washer 8b may also comprise a cushioned surface facing at least end 102. The cushioned surface may help reduce the impact force as the rocket falls back to earth and impacts the ground or another surface. In embodiments, the cushioned surface is a separate component from washer 8b. Washer 8b may be removable such that fins 7 can be removed, for example, if they become damaged or if the user wishes to change the aerodynamic effect caused by the fins 7 on the rocket 26.
Still referring to FIG. 1, as well as FIG. 2 and FIG. 3, rocket 26 includes an interior cavity having an outlet 100 at an end 102 of rocket 26. End 102 of rocket body 5 may be placed over a tube or other mating member that releases air, water, or other fluid, typically under pressure, into the interior cavity or against the base at end 102 of the rocket 26 in order to launch the rocket. Alternatively, a spring or other mechanism may be used to launch rocket 26. It will be appreciated by those in the art that an elastomeric material, e.g. rubber bands, may be used to launch rocket 26, such as with a sling shot system. In embodiments, compressed fluids may be released from outlet 100 to propel the rocket. In embodiments, solid or liquid state rocket engines may be used to propel the rocket 26.
In the embodiment depicted in FIG. 1, parachute 3 is connected to rocket body 5 through a plurality of spars 1. Spars 1 have an at least partially rigid configuration such that compressive forces may be exerted on spars 1. Accordingly, spars 1 may be semi-rigid or fully rigid members with one end operably attached to parachute 3 and the other end operably attached to the rocket 26, as further described below. In embodiments, spars 1 may not be single members but rather may comprise separate segments operatively connected to each other. In embodiments, hinges may connect the separate spar segments, which may be substantially similar to one another or may be of non-uniform length and/or non-uniform cross-sectional area. Spars 1 may be constructed from any lightweight material, ideally durable, including, for example, polymeric materials such as polyvinyl chloride, polyurethane, and /or polyethylene, to name a few. In embodiments, spars 1 may be composed of other at least semi-rigid materials, for example, metallic materials and/or composite materials such as paper.
Turning to FIG. 6, a detailed view of a spar 1 is illustrated. Spar 1 includes a shaft 13, which may be solid or hollow. In embodiments, when the shaft 13 is hollow, string or other flexible material may be used inside the shaft 13. In embodiments, the cross-section of the shaft 13 of spar 1 may be circular, triangular, rectangular, or may comprise some other number of sides, such as to form a pentagon or hexagon.
In embodiments, the spars 1 may be attached to parachute 3 by a number of mechanisms known in the art. Such parachute attachment means may include but are not limited to stitching, adhesive, tying, mechanical devices, such as hinges or other joints, snaps, a clasp, or a top and bottom plate joined together with the parachute material clamped by and between the two plates. The spars 1 may be attached to the edge of parachute 3 or to some other location on parachute 3. Each spar 1 may be attached at multiple locations to the parachute 3, such as an edge and an interior location. FIG. 4 shows the bottom of a deployed parachute 3, with the spars extended from connector ring 2 to the edges of the parachute 3.
In embodiments, the spars 1 may be connected to the rocket by pins, hinges, various joints, or other methods of attachment known in the prior art. The embodiment of spars 1 shown in FIGS. 1 and 6 contains a ball 14 at one end of shaft 13. The ball 14 may fit into a socket to form a ball-and-socket joint to connect a spar 1 to the rocket 26. FIG. 1 depicts a connector ring 2 having sockets 11 into which fit balls 14 of spars 1. In embodiments, the joints may be located on components other than a connector ring or even directly on the rocket body 5 itself. In the embodiment of FIG. 1, the ball and socket joint formed by socket 11 and ball 14 may allow the spar to pivot freely while remaining connected to rocket 26. In embodiments, the movement of spar 1 may be restricted, optionally by the shape of socket 11. For example, this restriction may limit spar 1 to rotation about only one axis. The degree of rotation of the spar 1 may also be restricted. In an exemplary embodiment containing a restriction of degree of rotation, the spar 1 cannot rotate past the horizontal position, where the horizontal position corresponds to an orientation of the spar that is perpendicular to the axis formed by the elongate body 5 of the rocket 26. In embodiments, the angle of a restriction may be greater or less than the horizontal restriction just described. Additionally, restrictions may be formed along multiple axes of rotation of spar 1.
In the embodiment shown in FIGS. 1-3 and illustrated more closely in FIGS. 5A and 5B, spars 1 are attached to rocket 26 via connector ring 2. Connector ring 2 is a ring with center hole 12. In this embodiment sockets 11 are located along the perimeter of connector ring 2. The spars 1 may connect to these sockets 11, as described above. Other attachment means for spars 1 are possible, including hinges, flexible joints, pins, and other connection methods known in the prior art, as described previously. Connector ring 2 may slide along body 5 of rocket 26. In embodiments, a groove or channel guides the movement of connector ring 2. For example, a groove may restrict rotation of connector ring 2 about the axis of rocket body 5. A raised guide rail extending axially on the surface of the body 5 may be employed, optionally for this same purpose. The connector ring 2 may be shaped to fit around the rocket and account for any grooves, rails, or other features along the surface of the rocket. It will be appreciated by those in the art that neither the rocket body 5 nor the connector ring 2 need be circular in cross-section but rather may have other cross-sectional shapes, for example three, four, five, six, or eight-sided cross-sections, to name a few. Accordingly, an exemplary rocket body 5 may have an octagonal cross section, and connector ring 2 may have a corresponding interior octagonal opening. In embodiments, the connector ring 2 may not be a ring at all in that it may not have an enclosed hole 12 through it. Connector ring 2 may be open on one or more sides. Connector ring 2 may comprise multiple components. In other embodiments, the spars 1 may be mounted individually to connecting fixtures. Such connecting fixtures may slide along rocket body 5, similar to the motion described below for connector ring 2.
Still describing the embodiment of FIGS. 1-4, as the rocket 26 reaches its apex, its speed in the initial direction of motion, e.g., upwardly, becomes zero and the rocket will then begin accelerating in a different direction (typically the reverse direction, towards the ground). In the embodiment of FIGS. 1-4, the rocket 26 is designed to reverse direction of motion without reversing its orientation, such that the body 5 of rocket 26 maintains an orientation with end 101 facing upwards and end 102 facing downwards (toward the ground), during the upward launch and downward return of rocket 26. In embodiments, rocket 26 may incorporate one or more features to facilitate the maintenance of such an orientation of rocket 26, for example, a counterweight or ballast.
When the rocket body 5 slows and/or reverses direction, the connector ring 2 may continue motion in the initial direction, e.g., upwards, at a different rate and/or for a time longer than the rocket body 5, for example, due to wind resistance on the connector ring 2, still-packed parachute 3, and/or tail 9, each of which presents a larger cross-sectional area than the body 5 of rocket 26. Such a difference in speed of descent will cause the body 5 to slide through connector ring 2 such that the connector ring 2 approaches the end 101 of the body 5 of rocket 26. In embodiments, the movement of connector ring 2 relative to rocket body 5 may be caused or amplified by differences in their masses. The mass of connector ring 2 may be relatively high or optionally relatively low compared to the combined mass of the other components of rocket 26, particularly body 5 and the components fixed to it.
The movement of connector ring 2 along rocket body 5 will also cause the connected bases of the spars 1 to move along the rocket body 5 towards end 101. In this regard, the spars 1 are caused to move radially outward as they pivot with respect to socket 11. Such motion causes the shafts 13 of the spars 1 to translate forces into the parachute 3 so that the parachute 3 is caused to spread out under the motion of the spars 1. Accordingly, since the spars 1 are at least partially rigid, the movement of the connector ring 2 along rocket body 5 causes the spars 1 to push the parachute 3 in an outward and/or upward fashion, which facilitates opening of the parachute 3. The movement of connector ring 2 towards end 101 thus may provide any of the following benefits: it may facilitate deployment of the parachute 3, it may decrease the parachute deployment time, or it may cause the parachute 3 to deploy closer to the highest altitude attained by the rocket 26. Additionally, the spar and connector system may facilitate more uniform deployment of the parachute. In embodiments, as one portion of the parachute 3 begins to open, it will lift the closest spar or spars 1, which will lift the entire connector ring 2, thus pushing out the remaining spars.
Accordingly, rocket 26 and parachute 3 are configured and arranged such that the parachute 3 deploys only after the rocket 26 reaches its apex of height following launch (due to the motion of connector ring 2), and so that the parachute 3 deploys quickly and efficiently thereafter (due to the forcing of spars 1). In this regard, a toy rocket 26 and accompanying parachute 3 are provided so that a user may observe the flight of rocket 26 to its maximum height following launch, and subsequently observe substantially the entirety of the descent of rocket 26 due to the quick manner in which parachute 3 deploys. Such a configuration is desirable because it provides the user with an optimum amount of time in which to view the rocket 26 between launch and return to the ground.
In embodiments, the connector ring 2 and rocket body 5 may reach their apexes together. The slidable connector ring 2 may allow the rocket body 5 to begin falling to earth while the parachute 3 deploys or begins to deploy at or near the apex of the trajectory and thus prevents the connector ring 2 from falling at the same speed as the rocket. In this scenario, the rocket body 5 falls downward and slides through connector ring 2 with approximately the acceleration due to gravity, less wind resistance. Meanwhile, the parachute 3 deploys and slows the downward acceleration of the parachute 3 itself, as well as the spars 1 and connector ring 2 attached thereto. Thus, if rocket 26 begins its descent at a faster rate than the parachute 3, then spars 1, connector ring 2, and stopper 4 will prevent the rocket from sliding completely through connector ring 2. Viewed with respect to the body 5 of rocket 26, stopper 4 will prevent connector ring 2 from sliding off the end 101 of the rocket body 5. When connector ring 2 engages stopper 4, the decelerating force of the parachute 3 will act upon the entire rocket 26, including rocket body 5.
In embodiments, rocket 26 may include a tail. Referring to FIG. 4, the tail 9 is attached at 10 to the top surface of the parachute 3. Similarly, FIG. 12 depicts a tail 17 fixed at a location 23 to the top of a parachute 21. In embodiments, a tail may be attached at the edge of the parachute or may be attached at an interior location on the parachute. In embodiments, the tail may be attached to the top surface of the parachute 3, the bottom surface, or an edge. In embodiments, a tail may be stitched to the parachute 3, glued, stapled, or fastened in another manner known in the art, or the tail may be formed from the same continuous piece of material as the parachute 3. In embodiments, an attachment area may be at one end of the tail or may be along any length of tail. In embodiments, tail 9 may include a wider portion 15 as indicated in FIG. 7. Either narrower end 16 or wider portion 15 may be attached to parachute 3. In embodiments tail 17 may also include only a narrow section 18, as shown in FIG. 8A, or an end of the narrow section 18 may be folded on itself either to form a thicker section or a loop 19 at one end of the tail 17, as depicted in FIG. 8B. The loop 19 may be formed by folding narrow section 18 and attaching the end to a location 20 along the body of narrow section 18 using means known in the art, such as stitching, gluing, or other known means. A tail may provide ornamentation and/or may increase amusement. In embodiments, a tail may serve to hold the parachute in a wrapped position, decreasing drag, for launch and/or ascent. The tail may also facilitate deployment of the parachute at an appropriate time by unwrapping the parachute as it travels farther. To this end, tail 9 with wide portion 15 or tail 17 with loop 19 may increase drag. Increased drag may facilitate faster unwrapping of the tail and parachute. It may also help slow the descent of the rocket once the parachute has deployed.
Referring to the embodiment of FIG. 1, in preparation for launch, the user holds the rocket 26 by the tail 102, with end 101 pointed downward, as illustrated in FIG. 13. Next, the user slides the connector ring 2 up towards end 102 until it reaches stopper 6, as shown in FIG. 14. Stopper 6 may be positioned as a guide to ensure that the connector ring 2 is located in a desirable location from which to fold the parachute 3. Stopper 6 may prevent the connector ring 2 from sliding off the end 102 of the rocket 26. In embodiments, stopper 6 and washer 8a may be the same component. After retracting the connector ring as in FIG. 14, the user grasps around both the body 5 of the rocket and the surrounding spars 1, as depicted in FIG. 15. With the other hand the user then pushes the center of the parachute 3 against end 101 of the rocket 26, as shown in FIG. 16. The user then drapes the parachute 3 around the body 5 of the rocket 26, with the center of the parachute 3 still pressed against end 101, according to FIG. 17. The user wraps the tail 9 around the parachute 3 to secure it to the body 5, as illustrated in FIG. 18. Optionally, the end of the tail 9 may be tucked under a spar 1.
In an alternative embodiment depicted in FIGS. 9-12, the rocket 27 contains nose 24 at end 101 of the rocket. Nose 24 may be constructed of soft foam, such as polyethylene, or may be formed of a hollow, soft, deformable rubber or plastic material containing an air cavity such that the wall of the nose may deform or collapse inward upon impact with a surface. The absorption of energy achieved by a soft nose may reduce likelihood of the rocket breaking upon impact with the ground or other objects. It may also reduce the likelihood of damage to any person or object impacted by the end 101 of the rocket 27 as it falls to the ground.
Still referring to the embodiment shown in FIGS. 9-12, rocket 27 includes parachute 21. Parachute 21 may have center hole 22. Hole 22 may improve performance of the parachute during descent, such as by providing a straighter line of descent. The hole 22 may be designed to adjust the rate of descent. A larger hole would result in a faster rate of descent. In preparation for launch, a user holds the nose 24 and slides the connector ring 2 up to the nose 24. End 102 of the body 5 of rocket 27 is placed through parachute center hole 22 as the connector ring 2 is moved towards nose 24. The tail 17 is then wrapped around the spars 1 and the body 5 of the rocket 27. The tail 17 may be wrapped around or above the parachute. It will be appreciated by those skilled in the art that wrapping the tail 17 around the outer folded edge of the parachute will reduce drag during flight. In embodiments, the profile of the tail 17 extending away from the body 5 in the wrapped condition may provide flight characteristics similar to that of a fin protruding from the body 5, for example, guidance, stability, and/or spin, in addition to or alternative to other aerodynamic effects. In embodiments, the wrapped condition of the parachute 3 may define a spiraled contour along a portion along the body 5 of the rocket 27 such that the rocket 27 is caused to spin during flight. Optionally, the end of tail 17 may be tucked under a spar 1 to secure it. The end 102 of the rocket 27 is then mated to the launch mechanism.
Upon launch, the nose 24 and end 101 form the leading end of the rocket 27. After launch and upon ascent of the rocket 27, the tail 17 unwraps. Depending on how quickly the tail 17 unwraps, the parachute 21 may deploy before the rocket reaches its apex, at the apex, or after the apex. If the parachute 21 deploys before the apex, the rocket 27 will slow and turn downward for descent. If the rocket 27 reaches the apex without deployment of the parachute 21, the rocket will likely turn downward on its own. To ensure that the nose 24 of the rocket remains at the leading end throughout flight, the nose 24 may be weighted. The deployment of the parachute 21 with the spars 1 and connector ring 2 may occur as described above for parachute 3. However, in this embodiment, the connector ring 2 will slide along body 5 until it reaches stopper 25. Stopper 25 may be located at or near end 102. Like stopper 4, stopper 25 can prevent the connector ring 2 from sliding off the rocket body 5. When the stopper 25 engages connector ring 2, the decelerating force of the parachute 21 may act upon the rocket body 5 and the affixed components. Now that embodiments of the present invention have been shown and described in detail, various modifications and improvements thereon will become readily apparent to those skilled in the art. Accordingly, the exemplary embodiments of the present invention, as set forth above, are intended to be illustrative, not limiting. The spirit and scope of the present invention is to be construed broadly.
Patent Application
20150024653
