U.S. patent application number 14/332963 was filed with the patent office on 2015-01-22 for parachute rocket toy.
The applicant listed for this patent is Easebon Services Limited. Invention is credited to Steven J. Huebl.
Application Number | 20150024653 14/332963 |
Document ID | / |
Family ID | 52343942 |
Filed Date | 2015-01-22 |
United States Patent
Application |
20150024653 |
Kind Code |
A1 |
Huebl; Steven J. |
January 22, 2015 |
PARACHUTE ROCKET TOY
Abstract
A parachute rocket toy in which the parachute is attached to the
rocket by spars is provided. A preferred embodiment uses semi-rigid
spars attached to a ring that surrounds the rocket body and may
slide along the body. 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 ring slides to the top of the rocket,
it pushes the spars, and thus the parachute, outward. A tail may be
wrapped around the parachute to hold it in place for launch and
ascent. After the tail unwraps, it may facilitate deployment of the
parachute.
Inventors: |
Huebl; Steven J.; (Jordon,
MN) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
Easebon Services Limited |
Kwun Tong |
|
HK |
|
|
Family ID: |
52343942 |
Appl. No.: |
14/332963 |
Filed: |
July 16, 2014 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
|
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61846898 |
Jul 16, 2013 |
|
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Current U.S.
Class: |
446/52 |
Current CPC
Class: |
A63H 27/005 20130101;
A63H 33/20 20130101 |
Class at
Publication: |
446/52 |
International
Class: |
A63H 27/00 20060101
A63H027/00; A63H 33/20 20060101 A63H033/20 |
Claims
1. A toy rocket, comprising: an elongate body; a connecting ring
slidably disposed around the body; a parachute reconfigurable
between a collapsed condition and an open condition; and a
plurality of at least partially rigid spars connecting the
parachute and the connecting ring.
2. The toy rocket of claim 1, wherein one or more fins extend from
the body.
3. The toy rocket of claim 1, wherein a tail extends from the
parachute.
4. The toy rocket of claim 1, wherein the body includes an interior
cavity for receiving fluids.
5. The toy rocket of claim 1, wherein at least one spar of the
plurality of at least partially rigid spars is connected to an edge
portion of the parachute.
6. The toy rocket of claim 1, wherein the plurality of at least
partially rigid spars are pivotably connected to the connecting
ring.
7. The toy rocket of claim 6, wherein each spar of the plurality of
rigid spars includes a ball configured for insertion into a
corresponding socket of the connecting ring.
8. The toy rocket of claim 1, wherein the connecting ring includes
at least one interior groove for mating with a rail disposed along
the body.
9. The toy rocket of claim 1, wherein a stopper member is affixed
to an end of the body.
10. The toy rocket of claim 9, wherein the stopper member restricts
movement of the connecting ring past the stopper member.
11. A method of using a toy rocket, comprising: providing a toy
rocket comprising an elongate rocket body attached to a parachute;
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; folding the parachute into
a collapsed configuration about the rocket body; 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.
12. The method of claim 11, further comprising wrapping a tail of
the parachute about the parachute in the collapsed condition.
13. The method of claim 11, wherein movement of the parachute in a
radially outward direction causes the parachute to reconfigure from
a collapsed configuration to an open configuration.
14. The method of claim 11, wherein the step of launching the toy
rocket comprises providing pressurized fluid into an interior
cavity of the body.
Description
RELATED APPLICATIONS
[0001] This application claims the priority to and benefit of U.S.
Provisional Patent Application No. 61/846,898, filed on Jul. 16,
2013, the entire contents of which are incorporated by reference as
if fully set forth herein.
FIELD
[0002] The present invention relates generally to toy rockets that
use parachutes and methods of preparing such rockets for
launch.
BACKGROUND
[0003] 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
[0004] 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.
[0005] 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.
[0006] 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.
[0007] 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.
[0008] In exemplary embodiments, one or more fins extend from the
body.
[0009] In exemplary embodiments, a tail extends from the
parachute.
[0010] In exemplary embodiments, the body includes an interior
cavity for receiving fluids.
[0011] 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.
[0012] In exemplary embodiments, the plurality of at least
partially rigid spars is pivotably connected to the connecting
ring.
[0013] 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.
[0014] In exemplary embodiments, the connecting ring includes at
least one interior groove for mating with a rail disposed along the
body.
[0015] In exemplary embodiments, a stopper member is affixed to an
end of the body.
[0016] In exemplary embodiments, the stopper member restricts
movement of the connecting ring past the stopper member.
[0017] 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.
[0018] In exemplary embodiments, the method further comprises
wrapping a tail of the parachute about the parachute in the
collapsed condition.
[0019] 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.
[0020] 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
[0021] Exemplary embodiments of the present invention will be
described with references to the accompanying figures, wherein:
[0022] FIG. 1 is a front view of a rocket of the present invention
with a parachute deployed.
[0023] FIG. 2 is a front view of a rocket with a parachute
retracted.
[0024] FIG. 3 is a front view of a rocket without a parachute
attached.
[0025] FIG. 4 is a bottom view of a deployed parachute.
[0026] FIG. 5A is a side view of an exemplary construction of a
spar connector ring.
[0027] FIG. 5B is a top view of an exemplary construction of a spar
connector ring.
[0028] FIG. 6 is a side view of a spar.
[0029] FIG. 7 is a top view of a tail.
[0030] FIG. 8A is a top view of another construction of a tail.
[0031] FIG. 8B is a top view of a further construction of a
tail.
[0032] FIG. 9 is a front view of another embodiment of a rocket of
the present invention with a parachute deployed.
[0033] FIG. 10 is a front view of a rocket with a parachute
retracted.
[0034] FIG. 11 is a front view of a rocket without a parachute
attached.
[0035] FIG. 12 is a top view of a deployed parachute.
[0036] FIG. 13 is a side view of a user holding a rocket by the
tail.
[0037] FIG. 14 is a side view of a user holding a rocket with the
spars retracted.
[0038] FIG. 15 is a side view of a user holding a rocket around the
spars.
[0039] FIG. 16 is a side view of a user beginning to fold a
parachute around a rocket body.
[0040] FIG. 17 is a side view of a user folding a parachute around
a rocket body.
[0041] FIG. 18 is a side view of a user holding a rocket with a
folded parachute.
DETAILED DESCRIPTION
[0042] 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.
[0043] The present invention is described with respect to the
following embodiments. The embodiments are illustrative only and
are not intended to limit the invention.
[0044] 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.
[0045] 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.
[0046] 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.
[0047] 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.
[0048] 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.
[0049] 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.
[0050] 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.
[0051] 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.
[0052] 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.
[0053] 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.
[0054] 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.
[0055] 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.
[0056] 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.
[0057] 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.
[0058] 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.
[0059] 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.
[0060] 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.
[0061] 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.
[0062] 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.
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