Note: Descriptions are shown in the official language in which they were submitted.
CA 02679457 2012-04-30
TOY AIRCRAFT WITH MODULAR POWER SYSTEMS AND WHEELS
Background of the Disclosure
[0002] Examples of remotely controlled aircraft are disclosed in U.S. Patent
Nos.
3,957,230, 4,206,411 , 5,035,382, 5,046,979, 5,078,638, 5,087,000, 5,634,839,
6,612,893, 7,073,750 and 7,275,973, and in U.S. Patent Application Publication
Nos. 2004/0195438, 2006/0144995, and 2007/0259595. Examples of remotely
controlled aircraft utilizing differential thrust for flight control are
disclosed in U.S.
Patent Nos. 5,087,000, 5,634,839, 6,612,893 and 7,275,973 and U.S. Patent
Application Publication No. 2007/0259595. Examples of toy aircraft fabricated
from
interconnected flat panels are disclosed in U.S. Patent Nos. 2,347,561 ,
2,361,929,
3,369,319, 4,253,897, 5,853,312, 6,217,404, 6,257,946, and 6,478,650 and U.S.
Patent Application Publication Nos. 2007/0259595 and 2008/0014827. Examples of
toy aircraft powered by rechargeable capacitors are disclosed in U.S. Patent
No.
6,568,980, U.S. Patent Application Publication No. 2008/0014827, and in
International Publication No. WO 2004/045735. Examples of toy aircraft with
wheels
are disclosed in U.S. Patent Nos. 2,124,992, 2,131,490, 2,437,743, 2,855,070,
3,699,708, 3,871,126, 5,087,000, and 5,525,087.
Summary of the Disclosure
[0003] In some examples, toy aircraft may include an airframe, a modular power
system, first and second wheel supports, and first and second wheels. The
modular
power system may be configured for selective use with and selective removal
from
the airframe. The power system may include a propulsion unit that may be
operable
to propel the toy aircraft and a power unit that may include an energy source
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configured to supply energy to the propulsion unit. The airframe may include a
fuselage, a propulsion unit mount, and a power unit mount. The propulsion unit
mount may be disposed on the airframe and configured to removably retain the
propulsion unit. The power unit mount may be disposed on the fuselage and
configured to removably retain the power unit. The first and second wheel
supports
may extend from the power unit mount toward respective first and second wheel
mounts. The first and second wheels may be rotatably mounted to respective
ones
of the first and second wheel mounts.
[0004] In some examples, toy aircraft may include an airframe, a wheel
assembly,
and a modular power system. The airframe may include a fuselage, a propulsion
unit mount, and a power unit mount. The propulsion unit mount may be disposed
on
the airframe. The power unit mount may be disposed on the fuselage and include
first and second sides. The wheel assembly may include first and second wheel
supports and first and second wheels. The first wheel support may extend from
the
first side of the power unit mount toward a first wheel mount spaced from the
power
unit mount. The first wheel may be rotatably mounted to the first wheel mount.
The
second wheel support may extend from the second side of the power unit mount
toward a second wheel mount spaced from the power unit mount. The second
wheel may be rotatably mounted to the second wheel mount. The modular power
system may be configured for selective use with and selective removal from the
airframe. The power system may include a propulsion unit and a power unit. The
propulsion unit may be operable to propel the toy aircraft. The propulsion
unit mount
may be configured to removably retain the propulsion unit relative to the
airframe.
The power unit may include an energy source configured to supply energy to the
propulsion unit. The power unit mount may be configured to removably retain
the
power unit proximate the fuselage.
[0005] In some examples, toy aircraft may include an airframe, a modular power
system, a wheel support element, and first and second wheels. The airframe may
include a fuselage having first and second sides, a wing connected to the
fuselage,
first and second motor unit mounts, and a power unit mount. The wing may
include
first and second portions extending from the respective first and second sides
of the
fuselage. The first motor unit mount may be disposed on the first portion of
the wing.
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The second motor unit mount may be disposed on the second portion of the wing.
The power unit mount may be disposed on the fuselage. The power unit mount may
include first and second sides and an opening. The modular power system may be
configured for selective use with and selective removal from the airframe. The
power system may include a first motor unit, a first propeller driven by the
first motor
unit, a second motor unit, a second propeller driven by the second motor unit,
and a
power unit. The first motor unit mount may be configured to removably retain
the
first motor unit relative to the wing. The second motor unit mount may be
configured
to removably retain the second motor unit relative to the wing. The power unit
may
include an energy source configured to supply energy to the first and second
motor
units. The opening may be configured to removably receive and retain the power
unit proximate the fuselage. The wheel support element may be connected to the
power unit mount and may include a first wheel support, a second wheel
support,
and an axle. The first wheel support may extend from the first side of the
power unit
mount to a first distal end, and the second wheel support may extend from the
second side of the power unit mount to a second distal end. The axle may have
first
and second ends. The axle may be connected to the first and second wheel
supports proximate the respective first and second distal ends. The first and
second
wheels may be rotatably mounted to the axle proximate respective ones of the
first
and second ends of the axle.
Brief Description of the Drawings
[0006] Fig. 1 is a block diagram of a toy aircraft.
[0007] Fig. 2 is a block diagram of a modular power system suitable for use
with
the toy aircraft of Fig. 1.
[0008] Fig. 3 is a perspective view of a toy aircraft incorporating a modular
power
system.
[0009] Fig. 4 is a perspective view of a nonexclusive illustrative example of
a
remote control transmitter suitable for use with some nonexclusive
illustrative
examples of toy aircraft, such as the toy aircraft of Fig. 3.
[0010] Fig. 5 is an exploded view of the airframe of the toy aircraft of Fig.
3.
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[0011] Fig. 6 is a perspective view of a modular power system suitable for use
with toy aircraft, such as the toy aircraft and airframe of Figs. 3 and 5.
[0012] Fig. 7 is a detail view of a nonexclusive illustrative example of a
laterally-
supporting wing clip suitable for use with toy aircraft, such as the toy
aircraft and
airframe of Figs. 3 and 5.
[0013] Fig. 8 is a detail view of a nonexclusive illustrative example of a
wing
support clip and struts suitable for use with toy aircraft, such as the toy
aircraft and
airframe of Figs. 3 and 5.
[0014] Fig. 9 is a motor side perspective view illustrating installation of a
nonexclusive illustrative example of a first motor unit into a nonexclusive
illustrative
example of a first motor unit mount on the wing of a toy aircraft, such as the
toy
aircraft and airframe of Figs. 3 and 5.
[0015] Fig. 10 is a motor side perspective view illustrating the first motor
unit of
Fig. 9 in a partially installed position.
[0016] Fig. 11 is a rear side perspective view illustrating the first motor
unit of Fig.
9 in the partially installed position illustrated in Fig. 10.
[0017] Fig. 12 is a motor side perspective view illustrating the first motor
unit of
Fig. 9 rotated into an operative orientation.
[0018] Fig. 13 is a rear side perspective view illustrating the first motor
unit of Fig.
9 rotated into the operative orientation illustrated in Fig. 12.
[0019] Fig. 14. is a rear side view of a second motor unit, which corresponds
to
the first motor unit of Fig. 9, rotated into one of a plurality of operative
orientations
relative to a second motor unit mount.
[0020] Fig. 15 is a perspective view of another example of a toy aircraft
incorporating a modular power system.
[0021] Fig. 16 is an exploded view of the toy aircraft and modular power
system
of Fig. 15.
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[0022] Fig. 17 is a detail view illustrating the connection between a wing
strut and
a wing of the toy aircraft of Figs. 15-16.
[0023] Fig. 18 is a block diagram of a toy aircraft kit, including a modular
power
system and toy aircraft airframes.
[0024] Fig. 19 is a perspective view of a toy aircraft incorporating a modular
power system and a nonexclusive illustrative example of a wheel assembly.
[0025] Fig. 20 is a perspective view of the wheel assembly and power unit
mount
of the toy aircraft of Fig. 19.
[0026] Fig. 21 is a perspective view of the power unit mount of the toy
aircraft of
Fig. 19.
[0027] Fig. 22 is a perspective view of the wheel support element of the toy
aircraft of Fig. 19.
[0028] Fig. 23 is a perspective view of a toy aircraft incorporating a modular
power system and another nonexclusive illustrative example of a wheel
assembly.
[0029] Fig. 24 is a perspective view of the wheel assembly of the toy aircraft
of
Fig. 23.
[0030] Fig. 25 is a front view of the wheel assembly of Fig. 24.
[0031] Fig. 26 is a perspective view showing the wheel assembly attached to
the
toy aircraft of Fig. 23, with the power unit removed.
[0032] Fig. 27 is another perspective view showing the wheel assembly attached
to the toy aircraft of Fig. 23, and showing insertion of the power unit.
Detailed Description
[0033] A nonexclusive illustrative example of a toy aircraft according to the
present disclosure is shown schematically in Fig. 1 and indicated generally at
20.
Unless otherwise specified, toy aircraft 20 may, but is not required to,
contain at least
one of the structure, components, functionality, and/or variations described,
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illustrated, and/or incorporated herein. A toy aircraft 20 according to the
present
disclosure may include a power system 24 and an airframe 28.
[0034] As shown in the nonexclusive illustrative example presented in Fig. 1,
power system 24 may include at least one propulsion unit 32 and a power unit
34.
As will be more fully discussed below, power unit 34 may be configured to
supply
power to, and/or to at least partially control, the at least one propulsion
unit 32 such
that the at least one propulsion unit 32 is operable to propel toy aircraft
20. As
indicated in solid lines in Fig. 1, it is within the scope of the present
disclosure for
power system 24 to be a discrete or self-contained power system for a toy
aircraft.
By "discrete," it is meant that the discrete component is not integrally
formed with the
other component even though the components thereafter may be coupled or
otherwise secured together. By "self-contained," it is meant that the self-
contained
component is adapted to exist and/or at least partially function as a complete
or
stand-alone unit. For example, a self-contained component may be adapted to
exist
and/or at least partially function independent of any components external to
the self-
contained component. Thus, a self-contained power system, such as power system
24, may be adapted to exist and/or function as a complete or stand-alone unit
that is
independent of a particular toy aircraft 20 and/or a particular airframe 28.
For
example, as shown in the nonexclusive illustrative example of a self-contained
power
system presented in Fig. 1, power system 24 may include one or more discrete
but
linked and/or connected units, such as at least one propulsion unit 32 and a
power
unit 34, that is/are adapted to be mated to, and/or engaged with, a suitable
airframe
28.
[0035] As shown in the nonexclusive illustrative example presented in Fig. 1,
airframe 28 may include at least one first or propulsion unit mount 38, at
least one
second or power unit mount 40, and at least one wing 42. In some examples,
airframe 28 may additionally or alternatively include at least one fuselage
44. Thus,
it is within the scope of the present disclosure for toy aircraft 20 to have
at least one
wing and at least one fuselage, to have at least one wing and no fuselage,
such as
where toy aircraft 20 is configured as a flying-wing aircraft, or to have no
wing and at
least one fuselage, such as where toy aircraft 20 is a helicopter.
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[0036] Each of the at least one propulsion unit mounts 38 may be disposed on
the airframe 28 and configured to removably retain at least one propulsion
unit
relative to airframe 28. By "removably," it is meant that, even though the
retaining
component is capable of optionally permanently retaining the retained
component,
the retained component may optionally be repeatedly retained by and/or removed
from the retaining component without permanent and/or destructive alteration
to the
retaining component, the retained component, and/or the engagement
therebetween. In some nonexclusive illustrative examples of toy aircraft 20,
at least
one of the at least one propulsion unit mounts 38 may be configured to
removably
retain at least one propulsion unit relative to the wing 42.
[0037] The power unit mount 40 may be configured to removably retain at least
one power unit relative to airframe 28. In some nonexclusive illustrative
examples of
toy aircraft 20 that include at least one fuselage 44, the power unit mount 40
may be
configured to removably retain at least one power unit relative to at least
one of the
at least one fuselages of toy aircraft 20.
[0038] As indicated in dashed lines in Fig. 1, a toy aircraft 20 according to
the
present disclosure may be formed, created, and/or assembled when a power
system
24 is mated to, and/or engaged with, a suitable airframe 28. A suitable
airframe 28
may be any airframe configured to removably retain a power system 24, as
indicated
by line 50. For example, as shown in the nonexclusive illustrative example
presented in Fig. 1, a suitable airframe 28 may include at least one
propulsion unit
mount 38 configured to removably retain at least one of the at least one
propulsion
units 32 of power system 24, as indicated by line 52, and at least one power
unit
mount 40 configured to removably retain the power unit 34 of power system 24,
as
indicated by line 54.
[0039] In some nonexclusive illustrative examples, power system 24 may be a
self-contained modular power system for a toy aircraft. By "modular," it is
meant that
the modular system includes one or more components, where at least a portion
of
each component has a predetermined geometry that is configured to engage and
be
retained by a corresponding mount on and/or in a structure that may be
discrete from
the modular system. A self-contained modular power system 24 may be configured
for selective use with and/or selective removal from a suitably configured
airframe
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28. For example, a propulsion unit 32 of a self-contained modular power system
may be configured to engage and be removably retained on any suitable airframe
28
by a corresponding propulsion unit mount 38, which is configured to engage and
removably retain the propulsion unit 32. Correspondingly, a power unit 34 of a
self-contained modular power system may be configured to engage and be
removably retained on any suitable airframe 28 by a corresponding power unit
mount
40, which is configured to engage and removably retain the power unit 34.
[0040] A nonexclusive illustrative example of a self-contained or modular
power
system according to the present disclosure is shown schematically in Fig. 2
and
indicated generally at 24. Unless otherwise specified, power system 24 may,
but is
not required to, contain at least one of the structure, components,
functionality,
and/or variations described, illustrated, and/or incorporated herein. A
modular power
system 24 according to the present disclosure may include a power and control
or
power unit 34 and at least one propulsion unit 32. As shown in the
nonexclusive
illustrative example presented in Fig. 2, modular power system 24 may include
a pair
of propulsion units 32, such as a first propulsion or motor unit 58 and a
second
propulsion or motor unit 60.
[0041] Each of the propulsion units 32 may include a motor and a thrust
generating device, such as one or more propellers or ducted fans, that is
driven by
the motor. For example, as shown in the nonexclusive illustrative example
presented in Fig. 2, first motor unit 58 may include a first motor 62, which
drives a
first propeller 64, and second motor unit 60 may include a second motor 66,
which
drives a second propeller 68. In some nonexclusive illustrative examples, at
least
one of the first and second motors may be an electric motor. In some
nonexclusive
illustrative examples, at least one of the propulsion units 32 may include a
housing
70. For example, the first motor unit 58 may include a first housing 72 within
which
the first motor 62 is at least partially disposed. The second motor unit 60
may
include a second housing 74 within which the second motor 66 is at least
partially
disposed.
[0042] Power unit 34 may include an energy source 78 and, in some
nonexclusive illustrative examples, a control circuit 80. As shown in the
nonexclusive illustrative example presented in Fig. 2, the energy source 78 is
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connected to the control circuit 80 and/or to at least one of the first and
second
motors 62, 66, such that energy source 78 is configured to provide or supply
energy
to the control circuit 80 and/or to at least one of the first and second
motors 62, 66.
In some nonexclusive illustrative examples, power unit 34 may include a
housing 86
within which energy source 78 and/or control circuit 80 may be at least
partially
disposed.
[0043] In some nonexclusive illustrative examples, energy source 78 may be a
source of electric energy and/or current with at least one of the first and
second
motors 62, 66 being an electric motor. When energy source 78 is a source of
electric energy and/or current, energy source 78 may be electrically connected
to the
control circuit 80 and/or to at least one of the first and second motors 62,
66, such
that energy source 78 may be configured to provide or supply electric energy
and/or
current to the control circuit 80 and/or to at least one of the first and
second motors
62, 66. In some nonexclusive illustrative examples, energy source 78 may be an
electrical storage device. For example, energy source 78 may be a battery,
which
may be rechargeable, a capacitor, or the like. In some nonexclusive
illustrative
examples, energy source 78 may be an electrical energy generation or
production
device. For example, energy source 78 may be a fuel cell, a solar cell, or the
like.
[0044] The first and second motor units 58, 60 may be connected to the power
unit 34 with respective first and second pairs 88, 90 of electrical conducting
members. As suggested in Fig. 2, the first and second pairs 88, 90 of
electrical
conducting members may electrically connect the respective first and second
motors
62, 66 to the control circuit 80. In some nonexclusive illustrative examples,
the first
and second pairs 88, 90 of electrical conducting members may be flexible. For
example, the first and second pairs 88, 90 of electrical conducting members
may
include pairs of flexible metal wires.
[0045] With regard to power system 24 it is within the scope of the present
disclosure for the connections between the first and second motor units 58, 60
and
the power unit 34 to be limited to flexible members when power system 24 is
separated from airframe 28. For example, as shown in the nonexclusive
illustrative
example presented in Fig. 6, the connections between the first and second
motor
units 58, 60 and the power unit 34 may be limited to the first and second
pairs 88, 90
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of electrical conducting members. However, it should be understood that, even
when the connections between the first and second motor units 58, 60 and the
power unit 34 are limited to flexible members, power system 24 may include
flexible
connections other than the first and second pairs 88, 90 of electrical
conducting
members. Further, the power system 24, including the electrical connections
between the first and second motor units 58, 60 and the power unit 34, may be
configured for removal from the airframe 28 without electrically disconnecting
the first
and second motor units 58, 60 from the energy source 78.
[0046] In some nonexclusive illustrative examples, the first and second pairs
88,
90 of electrical conducting members may be insulated. For example, the first
and
second pairs 88, 90 of electrical conducting members may include pairs of
insulated
wires. In some nonexclusive illustrative examples, the individual wires in
each pair
of insulated wires may be separate, such as where the two individual wires in
each
pair are twisted together. In some nonexclusive illustrative examples, the
individual
wires in each pair of insulated wires may be paired together, such as within a
common sheath, conduit or other enclosing member.
[0047] When a self-contained or modular power system according to the present
disclosure, such as the modular power system 24 schematically presented in
Fig. 2,
is integrated with a suitable airframe 28 to form a toy aircraft, such as the
toy aircraft
20 schematically presented in Fig. 1, the modular power system is then adapted
to
propel the toy aircraft 20 and to control its flight. For example, as
illustrated in the
nonexclusive illustrative example presented in Fig. 2, control circuit 80,
which
connects the energy source 78 to the first and second motors 62, 66 of the
first and
second motor units 58, 60, may be configured to selectively deliver, or
regulate the
delivery of, energy from energy source 78 to the first and second motor units
58, 60.
In nonexclusive illustrative examples of power system 24 where energy source
78 is
a source of electric energy and/or current, control circuit 80 may be
configured to
selectively deliver, or regulate the delivery of, electric energy and/or
current from
energy source 78 to the first and second motor units 58, 60. Delivery or
supply of
energy and/or current from energy source 78 to the first and second motor
units 58,
60 renders motor units 58 and 60 operable to propel a toy aircraft 20 on which
the
modular power system 24 is removably retained. Further, by selectively
delivering or
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supplying energy and/or current to motor units 58 and 60, control circuit 80
is thus
configured to control operation of the first and second motor units 58, 60 and
thereby
control flight of a toy aircraft 20 on which the modular power system 24 is
removably
retained.
[0048] A modular power system 24, such as the one schematically presented in
Fig. 2, may be adapted to at least partially control the flight of a toy
aircraft 20 on
which the modular power system 24 is removably retained, such as through the
use
of differential thrust from the first and second motor units 58, 60. For
example,
control circuit 80 may control the flight of toy aircraft 20 by selectively
delivering, or
regulating the delivery of, energy and/or current from energy source 78 to the
first
and second motor units 58, 60. Control circuit 80 may cause toy aircraft 20 to
perform various flight maneuvers by jointly and/or independently varying the
thrust
output from the first and second motor units 58, 60. The degree of control
that may
be achieved with differential thrust from the first and second motor units 58,
60 may
be sufficient such that traditional movable aerodynamic control surfaces may
be
partially or entirely omitted from toy aircraft 20 such that the flight of toy
aircraft 20
may be controlled solely by controlling the thrust from the first and second
motor
units 58, 60.
[0049] An aircraft that is controllable by differential thrust, such as toy
aircraft 20,
may be referred to as propulsion controlled aircraft ("PCA"). The pitch (which
generally corresponds to up-and-down motion) of a PCA may be controlled by
concurrently increasing or decreasing the energy and/or current supplied to
the first
and second motor units 58, 60 to produce a concurrent increase or decrease in
the
thrust output from the first and second motor units 58, 60. For example,
increasing
the energy and/or current supplied to both the first and second motor units
58, 60
may cause toy aircraft 20 to enter a climb in addition to increasing the speed
of the
aircraft. Conversely, decreasing the energy and/or current supplied to both
the first
and second motor units 58, 60 may cause toy aircraft 20 to slow and enter a
descent. Toy aircraft 20 may be made to turn by increasing the energy and/or
current supplied to one of the first and second motor units 58, 60 relative to
the
energy and/or current supplied to other of the first and second motor units
58, 60,
which causes differential thrust output from the first and second motor units
58, 60
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and turning flight. For example, if the thrust output of first motor unit 58
is higher
than the thrust output of second motor unit 60, toy aircraft 20 may yaw and
roll
toward the second motor unit 60, which may result in a turn toward the second
motor
unit 60. Conversely, a higher thrust output from second motor unit 60, may
cause
toy aircraft 20 to yaw and roll toward the first motor unit 58, which may
result in a
turn toward the first motor unit 58.
[0050] Another nonexclusive illustrative example of a toy aircraft according
to the
present disclosure is shown in Figs. 3 and 5 and indicated generally at 20.
Unless
otherwise specified, toy aircraft 20 may, but is not required to, contain at
least one of
the structure, components, functionality, and/or variations described,
illustrated,
and/or incorporated herein. As shown in the nonexclusive illustrative example
presented in Figs. 3 and 5, toy aircraft 20 may be configured as a modular toy
aircraft that includes a power system 24, such as the nonexclusive
illustrative
example presented in Fig. 6, that is removably retained to an airframe 28.
[0051] As shown in the nonexclusive illustrative example presented in Figs. 3
and
5, at least a portion of one or more of the airframe components, such as wing
42,
fuselage 44, and horizontal stabilizer 92 (if present), may be fabricated from
at least
one flat panel of material. Suitable flat panels of material may include wood,
cardboard, extruded polystyrene or other polymer-based panels. In some
nonexclusive illustrative examples, some airframe components may be completely
formed from a flat panel of material. For example, as shown in the
nonexclusive
illustrative example presented in Figs. 3 and 5, airframe 28 may include a
horizontal
stabilizer 92 that is fabricated from a flat panel of material.
[0052] In some nonexclusive illustrative examples, at least a portion of at
least
one of the airframe components may be fabricated from an at least partially
resilient
material, such as an expanded polypropylene foam. For example, as shown in the
nonexclusive illustrative example presented in Figs. 3 and 5, a nose portion
94 of the
fuselage 44 may be include a nose cone 96 having an increased thickness
relative to
the fuselage 44. In some nonexclusive illustrative examples, nose cone 96 may
be
fabricated from expanded polypropylene foam.
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[0053] In some nonexclusive illustrative examples, one or more of the airframe
components may include a protective element. Such a protective element may be
configured to provide enhanced structural integrity and/or abrasion resistance
to at
least a portion of the airframe component on which it is disposed or affixed.
For
example, as shown in the nonexclusive illustrative example presented in Figs.
3 and
5, the fuselage 44 may include at least one skid protector 98. Such a skid
protector
98 may be fabricated from an injection molded plastic and secured to the
fuselage
44 using a suitable method or mechanism, such as friction, adhesive, and/or
one or
more mechanical fasteners, such as pins extending at least partially through
at least
a portion of the fuselage 44.
[0054] In some nonexclusive illustrative examples where airframe 28 is
assembled from components that are fabricated from flat panels of material, at
least
some of the airframe components may be at least partially frictionally
retained
relative to each other. For example, wing 42 and and/or horizontal stabilizer
92 may
be at least partially frictionally retained relative to fuselage 44. As shown
in the
nonexclusive illustrative example presented in Fig. 5, fuselage 44 may include
an
aperture or slot 102 that is configured to at least partially frictionally
receive the wing
42. The frictional engagement between the wing 42 and the slot 102 may be
enhanced if one or more of the dimensions of slot 102 are slightly smaller
than a
corresponding dimension of wing 42. For example, the height of slot 102 may be
slightly smaller than the thickness of wing 42. In some nonexclusive
illustrative
examples, wing 42 may include a structural feature, such as detent 104, that
is
configured to engage a corresponding portion of slot 102, such as the front
end 106
of the slot. As shown in the nonexclusive illustrative example presented in
Fig. 5,
wing 42 may be connected to the fuselage 44 by inserting wing 42, as indicated
by
arrow 108, through slot 102 until first and second portions 110, 112 of the
wing 42
extend from the respective first and second sides 114, 116 of the fuselage 44.
[0055] Where airframe 28 includes a horizontal stabilizer 92, the horizontal
stabilizer 92 may be at least partially frictionally retained relative to the
fuselage. For
example, as shown in the non-exclusive example presented in Fig. 5, the
horizontal
stabilizer 92 may be connected to the fuselage 44 by engaging the
corresponding
slots 118 and 120 on the respective ones of the horizontal stabilizer 92 and
the
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fuselage 44, as indicated by arrow 122. In some nonexclusive illustrative
examples,
the horizontal stabilizer 92 may be connected to the fuselage 44 by
transversely
inserting the horizontal stabilizer 92 through a slot in the fuselage 44, such
as similar
to the wing installation illustrated in Fig. 5. In some nonexclusive
illustrative
examples, the horizontal stabilizer 92 may be connected to the fuselage 44 by
a
combination of transverse insertion and longitudinal motion. For example, as
illustrated in the non-exclusive example presented in Fig. 16, which will be
more fully
discussed below, the horizontal stabilizer 92 may be connected to the fuselage
44 by
initially inserting the horizontal stabilizer 92 into a corresponding slot
124, as
indicated by arrow 126, followed by rearward translation of the horizontal
stabilizer
92 relative to the fuselage 44, as indicated by arrow 128.
[0056] In some nonexclusive illustrative examples, airframe 28 may include one
or more structural elements or reinforcing members 130 configured to at least
partially support the wing 42 relative to the fuselage 44. In some
nonexclusive
illustrative examples, at least one of the one or more reinforcing members 130
may
be fabricated as an injection or otherwise molded plastic clip. Reinforcing
members
130 may be configured to at least partially retain the wing 42 in a
predetermined
position relative to the fuselage 44. For example, as illustrated in the
nonexclusive
illustrative example presented in Figs. 3 and 5, at least one reinforcing
member 130
may be configured as a laterally-supporting wing clip 132, which will be more
fully
described below with respect to Fig. 7. Reinforcing members 130 may also
and/or
alternatively be configured to at least partially maintain the wing 42 in a
predetermined orientation relative to the fuselage 44. For example, as
illustrated in
the nonexclusive illustrative example presented in Figs. 3 and 5, at least one
reinforcing member 130 may be configured wing strut 134. Reinforcing members
130 may also and/or alternatively be configured to at least partially induce a
dihedral
into the wing 42. By "dihedral," it is meant the upward angle of a wing, from
the
fuselage or wing root to the wing tip, from a line that is perpendicular to
the fuselage.
For example, as illustrated in the nonexclusive illustrative example presented
in Figs.
3 and 5, at least one reinforcing member 130 may be configured as a wing
support
clip 136, which will be more fully described below with respect to Fig. 8.
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[0057] When airframe 28 includes one or more reinforcing members 130, the
fuselage 44 and/or the wing 42 may be configured to provide clearance for the
reinforcing members 130 during connection of the wing 42 to the fuselage 44.
For
example, as shown in the nonexclusive illustrative example presented in Fig.
5, slot
102 may include one or more enlarged regions 140 to clear the reinforcing
members
130.
[0058] Nonexclusive illustrative examples of suitable mounts for attaching a
power system 24, such as the nonexclusive illustrative example presented in
Fig. 6,
to an airframe 28 are illustrated in Figs. 3 and 5. Unless otherwise
specified, the
mounts for attaching power system 24 to an airframe 28, such as those
illustrated in
Figs. 3 and 5, may, but are not required to, contain at least one of the
structure,
components, functionality, and/or variations described, illustrated, and/or
incorporated herein.
[0059] As shown in the nonexclusive illustrative example presented in Fig. 5,
the
power unit mount 40 may be configured as a receptacle 144 disposed on the
fuselage 44. The receptacle 144 may be configured to removably retain the
power
unit 34 relative to the airframe 28 and fuselage 44. For example, receptacle
144
may include an opening 146 that is configured to removably receive at least a
portion
of power unit 34, such as at least a portion of the housing 86, as shown in
Fig. 3.
Further, the opening 146, power unit 34, and/or the fuselage 44 may be
configured
such that the power unit 34 is disposed at least partially external to the
fuselage 44
when it is retained in the opening 146.
[0060] The power unit 34 may include at least one barbed tab 148, as shown in
Fig. 6, that is configured to engage a corresponding opening 150 on receptacle
144,
as shown in Fig. 5, such that power unit 34 is retained by the receptacle 144,
as
shown in Fig. 3. In some nonexclusive illustrative examples, opening 146 may
be
configured to nondestructively removably receive at least a portion of power
unit 34.
By "nondestructively," it is meant that the nondestructively engaged elements
are not
damaged during nondestructive engagement or disengagement.
[0061] In some nonexclusive illustrative examples, the opening 146 may extend
fully through the power unit mount 40, such as between the first and second
sides
CA 02679457 2009-08-28
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346, 352 of the power unit mount, as shown in Figs. 5 and 21. The opening 146
may
extend through the fuselage 44 from the first side 114 of the fuselage 44 to
the
second side 116 of the fuselage 44, as shown in Fig. 5.
[0062] In some nonexclusive illustrative examples, the opening 146 of power
unit
mount 40 may be configured to receive the housing 86 of the power unit 34 in a
predetermined orientation. As such, opening 146 and housing 86 may include one
or more asymmetric features such that housing 86 may be received in opening
146
in a predetermined orientation, such as with a particular end of housing 86
oriented
towards the nose portion 94 of the fuselage 44. For example, at least one
corner of
opening 146 may be angled in correspondence with at least one corner of
housing
86 such that opening 146 is configured to receive housing 86 in a limited
number of
orientations. As shown in the nonexclusive illustrative example presented in
Figs. 5
and 6, a single corner 152 of opening 146 may be angled in correspondence with
a
single corner 154 of housing 86 such that opening 146 is configured to receive
housing 86 in a single predetermined orientation.
[0063] As shown in the nonexclusive illustrative example presented in Fig. 5,
the
propulsion unit mounts 38 may be configured as first and second motor unit
mounts
158, 160. The first and second motor unit mounts 158, 160 may be disposed on
the
respective first and second portions 110, 112 of wing 42, such as proximate
the
trailing edge 162 of wing 42. Each of the first and second motor unit mounts
158,
160 may be configured to removably receive and retain one of the first and
second
motor units 58, 60. In some nonexclusive illustrative examples, the first and
second
motor unit mounts 158, 160 may be configured to nondestructively removably
receive and retain the first and second motor units 58, 60. For example, each
of the
first and second motor unit mounts 158, 160 may include a receptacle, such as
an
aperture 164, as shown in Fig. 5, that is configured to receive a portion of
one of the
first and second motor units 58, 60, such as a mounting foot 166, as shown in
Fig. 6.
The details of the engagement between the first and second motor units 58, 60
and
the first and second motor unit mounts 158, 160 will be more fully discussed
below
with respect to Figs. 9-14.
[0064] In some nonexclusive illustrative examples, toy aircraft 20 may be
configured as a remotely controlled toy aircraft. For example, power system 24
may
16
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include a receiver 170 that is electrically connected to control circuit 80.
In such an
example, control circuit 80 may be configured to regulate current and/or
energy
supplied from energy source 78 to at least one of the first and second motor
units 58,
60, such as in response to an external signal received by the receiver. In
some
nonexclusive illustrative examples, toy aircraft 20 may be configured as a
radio-
controlled (RC) toy aircraft 20 with receiver 170 being a radio receiver that
is
electrically connected to control circuit 80. In some nonexclusive
illustrative
examples, radio receiver 170 may be disposed in power unit 34, with an antenna
172
extending therefrom, as shown in Figs. 3 and 6. The detailed operation of
remotely
controlled aircraft, including remotely controlled PCA are well known in the
art and
will not be discussed in detail herein. Further details regarding the
operation of
remotely controlled PCA may be found in U.S. Patent Nos. 5,087,000 and
6,612,893,
the complete disclosures of which are incorporated by reference in their
entirety for
all purposes.
[0065] When toy aircraft 20 is configured as an RC toy aircraft 20, it may be
paired with a suitable transmitter, such as the nonexclusive illustrative
example
transmitter 176 shown in Fig. 4. Transmitter 176 may include one or more input
devices, such as first and second control sticks 178, 180. The detailed
operation of
a remote control transmitter, such as transmitter 176, is well known in the
art and will
not be discussed in detail herein. Transmitter 176 may include a power switch
182.
In some nonexclusive illustrative examples, transmitter 176 may be configured
to
recharge the energy source 78 of power system 24. For example, transmitter 176
may include an appropriate charging connector 184 that is configured to
interface
with a charging connector 186 on power system 24, such as on the power unit
34. In
some nonexclusive illustrative examples where transmitter 176 is configured to
recharge the energy source 78, power switch 182 may be configured to select
between an ON mode (for remote control transmission), an OFF mode, and a
recharge mode. In some nonexclusive illustrative examples, such as where power
system 24 includes a rechargeable energy source 78, power system 24 may
include
a power switch 190. Power switch 190 may be configured to disconnect one or
more
of the first and second motors 62, 66 and/or control circuit 80 from energy
source 78,
such as during recharging of energy source 78.
17
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[0066] A nonexclusive illustrative example of a laterally-supporting wing clip
132
is illustrated in Fig. 7. Unless otherwise specified, the laterally-supporting
wing clip
132, may, but is not required to, contain at least one of the structure,
components,
functionality, and/or variations described, illustrated, and/or incorporated
herein. Clip
132, which may be fabricated from a molded plastic, includes a first or wing
engaging portion 194 and a second or fuselage engaging portion 196. As shown
in
the nonexclusive illustrative example presented in Fig. 7, the wing engaging
portion
194 may be connected to the fuselage engaging portion 196 by a region of
reduced
thickness 198. Such a region of reduced thickness 198 forms a living hinge,
which
enables the fuselage engaging portion 196 to be bent, such as out of plane,
relative
to the wing engaging portion 194, as suggested in dashed lines in Fig. 7.
[0067] As shown in the nonexclusive illustrative example presented in Fig. 7,
the
wing engaging portion 194 of clip 132 may include at least one socket 200 that
is
configured to extend through a corresponding hole in a wing 42, as suggested
in
Figs. 3 and 5. Each of the at least one sockets 200 may be configured to
frictionally
and/or mechanically engage a corresponding pin 202 on a backing clip 204. When
wing engaging portion 194 and backing clip 204 are engaged through
corresponding
holes in wing 42, as suggested in Figs. 3 and 5, clip 132 is retained relative
to wing
42.
[0068] As shown in the nonexclusive illustrative example presented in Fig. 7,
the
fuselage engaging portion 196 of clip 132 may include first and second arms
206,
208. The first and second arms 206, 208 may be connected to a central portion
210
of the fuselage engaging portion 196 by regions of reduced thickness 212,
which
may provide living hinges that enable bending of the first and second arms
206, 208
relative to the central portion 210, as suggested in dashed lines in Fig. 7.
As shown
in the nonexclusive illustrative example presented in Fig. 7, respective ones
of the
first and second arms 206, 208 may include a socket 214 and a corresponding
pin
216, which is configured for frictional and/or mechanical engagement with
socket
214. Mechanical engagement between pin 216 and socket 214 may occur where at
least a portion of pin 216, such as an end portion 217, has at least one
larger radial
dimension than socket 214. When the socket 214 and pin 216 of the first and
second arms 206, 208 are brought into frictional and/or mechanical engagement
18
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through an appropriate hole in fuselage 44, such as the hole 218 illustrated
in Fig. 5,
clip 132 is retained relative to fuselage 44, as shown in Fig. 3. In some
nonexclusive
illustrative examples one or more of the first and second arms 206, 208 may
include
a region of reduced thickness 220, which may at least partially facilitate
engagement
of pin 216 with socket 214.
[0069] Nonexclusive illustrative examples of wing struts 134 and a wing
support
clip 136 are presented in Fig. 8. Unless otherwise specified, wing struts 134
and
wing support clip 136, may, but are not required to, contain at least one of
the
structure, components, functionality, and/or variations described,
illustrated, and/or
incorporated herein.
[0070] Wing struts 134 may be configured as a first wing strut 222 or a second
wing strut 224, as suggested in the nonexclusive illustrative examples
presented in
Fig. 8. The first wing strut 222 may include a socket 226 and second wing
strut 224
may include a pin 228, where socket 226 is configured to frictionally and/or
mechanically engage and retain pin 228. When the first and second wing struts
222,
224 are engaged though a corresponding hole in the fuselage 44, as suggested
in
Figs. 3 and 5, the first and second wing struts 222, 224 are retained relative
to
fuselage 44. In some nonexclusive examples, the end regions 230 of struts 134
may
be flexibly connected to the central portion 232 of the strut, such as by
regions of
reduced thickness, which may form at least one living hinge. Each of the first
and
second wing struts 222, 224 may include a pin 234 that is configured to engage
a
corresponding socket 236 on the wing support clip 136.
[0071] As shown in the nonexclusive illustrative example presented in Fig. 8,
wing
support clip 136 may include at least one pin 238 that is configured to extend
through a corresponding hole in a wing 42, as suggested in Figs. 3 and 5. Each
of
the at least one pins 238 may be configured to frictionally and/or
mechanically
engage a corresponding socket 240 on a backing clip 242. When wing support
clip
136 and backing clip 242 are engaged through corresponding holes in wing 42,
as
suggested in Figs. 3 and 5, wing support clip 136 is retained relative to wing
42. In
some nonexclusive illustrative examples, such as for the wing support clip 136
shown in Fig. 8, the outer portions 244 of the wing support clip 136 may be
angled
relative to each other, rather than being coplanar. Thus, if such a wing
support clip
19
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136 is secured to the lower surface of a wing, as shown in the nonexclusive
illustrative example, presented in Figs. 3 and 5 (with sockets 236 and pins
238
extending through the wing), a dihedral angle will be induced into the wing.
Conversely, if such a wing support clip 136 is secured to the upper surface of
a wing
(with sockets 236 and pins 238 extending through the wing), an anhedral angle
will
be induced into the wing.
[0072] As shown in the nonexclusive illustrative example presented in Fig. 8,
wing
support clip 136 may include first and second arms 246, 248. The first and
second
arms 246, 248 may be connected to a central portion 250 of wing support clip
136 by
regions of reduced thickness, which may provide living hinges that enable
bending of
the first and second arms 246, 248 relative to the central portion 250, as
suggested
in dashed lines in Fig. 8. As shown in the nonexclusive illustrative example
presented in Fig. 8, respective ones of the first and second arms 246, 248 may
include a pin 252 and a corresponding socket 254, which is configured for
frictional
and/or mechanical engagement with pin 252. When the pin 252 and corresponding
socket 254 of the first and second arms 246, 248 are brought into frictional
and/or
mechanical engagement through an appropriate hole in fuselage 44, such as the
hole 256 illustrated in Fig. 5, wing support clip 136 is retained relative to
fuselage 44.
[0073] In some nonexclusive illustrative examples, the airframe 28 may be
configured to at least partially retain and/or restrain at least one of the
first and
second pairs of electrical conducting members 88, 90 relative to the airframe.
For
example, one or more retention devices, such as hooks 258, may be provided on
wing 42, such that the first and second pairs of electrical conducting members
88, 90
may be at least partially retained and/or restrained relative to the wing 42,
as
illustrated in Figs. 3 and 5. In some nonexclusive illustrative examples, the
hooks
258 may be incorporated into the wing support clip 136, as shown in Fig. 8.
[0074] Nonexclusive illustrative examples of first and second motor units 58,
60,
such as the first and second motor units 58, 60 of the nonexclusive
illustrative
example of a power system 24 shown in Fig. 6, being mounted to, or mounted to,
first and second motor unit mounts 158, 160 are presented Figs. 9-14. In
particular,
a nonexclusive illustrative example of mounting a first motor unit 58 to a
first motor
unit mount 158 is shown in Figs. 9-13, and a nonexclusive illustrative example
of a
CA 02679457 2009-08-28
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second motor unit 60 mounted to a second motor unit mount 160 is shown in Fig.
14.
Unless otherwise specified, first motor unit 58, first motor unit mount 158,
second
motor unit 60 and second motor unit mount 160 may, but are not required to,
contain
at least one of the structure, components, functionality, and/or variations
described,
illustrated, and/or incorporated herein. As shown or suggested in the
nonexclusive
illustrative examples presented in Figs. 9-14, each of the first and second
motor
units 58, 60 may include a mounting foot 166 and each of the first and second
motor
unit mounts 158, 160 may include an aperture 164 that extends from a first or
motor
side 262 to a second or rear side 264. The apertures 164 on the first and
second
motor unit mounts 158, 160 may be configured to receive the mounting foot 166
of a
corresponding one of the first and second motor units 58, 60.
[0075] The first or motor side 262 and the second or rear side 264 of the
first and
second motor unit mounts 158, 160 should not be understood to refer to a
particular
side of the wing 42. Rather, the first or motor side 262 refers to the side of
the motor
unit mount on which the motor of the motor unit resides when the motor unit is
received by the motor unit mount, as will be more fully discussed below. The
second
or rear side 264 refers to the side of the motor unit mount that is opposite
to the first
or motor side 262. The first or motor side 262 of at least one motor unit
mount may
be on an upper surface of wing 42, as illustrated in the nonexclusive
illustrative
example presented in Fig. 3, or the first or motor side 262 of at least one
motor unit
mount may be on a lower surface of wing 42, as illustrated in the nonexclusive
illustrative example presented in Fig. 15.
[0076] In some nonexclusive illustrative examples, the motor unit mounts may
be
configured to removably receive a corresponding one of the motor units in at
least
one predetermined orientation relative to the wing 42. When a motor unit is in
a
predetermined or operative orientation, the propeller may be configured and/or
oriented such that the propeller at least partially generates forward thrust
for toy
aircraft 20, as suggested in Figs. 3 and 15. For example, as shown in the
nonexclusive illustrative examples presented in Figs. 9-14, the first and
second
motor unit mounts 158, 160 may be configured to removably receive the
respective
ones of the first and second motor units 58, 60 in at least one predetermined
orientation relative to the wing 42.
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[0077] As shown in the nonexclusive illustrative examples presented in Figs. 9-
14 the apertures 164 on the first and second motor unit mounts 158, 160 and
the
mounting feet 166 of the first and second motor units 58, 60 may include one
or
more asymmetries. Such asymmetries may at least partially limit and/or
restrict the
possible orientations with which a motor unit mount may receive a motor unit.
For
example, as shown in the nonexclusive illustrative examples presented in Figs.
9-
14, the mounting foot 166 may include a larger or first end 266 that is
relatively wider
than a smaller or second end 268. The aperture 164 may correspondingly include
a
first or larger end 272 to accommodate the first end 266 of the mounting foot
166
and a second or smaller end 274 to accommodate the second end 268 of the
mounting foot 166. In some nonexclusive illustrative examples, the respective
mounting feet 166 of the first and second motor units 58, 60 may differ. For
example, as shown in the nonexclusive illustrative example presented in Fig.
9, the
larger or first end 266 of the mounting foot 166 of the first motor unit 58
may be
disposed proximate the propeller 64, while the smaller or second end 268 of
the
mounting foot 166 of the second motor unit 60 may be disposed proximate the
propeller 68, as shown in the nonexclusive illustrative example presented in
Fig. 14.
[0078] To engage the first motor unit 58 with the first motor unit mount 158,
the
first motor unit 58 is positioned over the motor side 262 of aperture 164, as
illustrated
in Fig. 9, with the first motor unit 58 oriented such that the first and
second ends 266,
268 of the mounting foot 166 are aligned with respective ones of the first and
second
ends 272, 274 of aperture 164. The mounting foot 166 is inserted into the
aperture
164, as indicated by arrow 278. When the mounting foot 166 is sufficiently
inserted
into aperture 164, as shown in Fig. 10, the mounting foot 166 protrudes beyond
the
rear side 264 of aperture 164, a shown in Fig. 11. Once sufficiently inserted
into
aperture 164, the first motor unit 58 is rotated relative to the first motor
unit mount
158, as indicated by arrow 280 in Fig. 12 (counterclockwise when viewed
looking
towards the motor side 262) and arrow 282 in Fig. 13 (clockwise when viewed
looking towards the rear side 264), until the motor unit 58 is aligned and/or
configured to at least partially generate forward thrust. Although the
nonexclusive
illustrative example presented in Figs. 9-13 includes rotation in one or more
particular directions, it should be understood that other examples may include
rotation in an opposite direction and/or other forms of movement such as
linear
22
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translations. In some nonexclusive illustrative examples, motor unit 58 is
aligned
and/or configured to at least partially generate forward thrust when the
propeller 64
may rotate without impacting the wing 42, as shown in Figs. 12 and 13.
[0079] The second motor unit 60 may be engaged with the second motor unit
mount 160 following a similar procedure to that discussed above with respect
to the
first motor unit 58 and first motor unit mount 158. As suggested in Fig. 14,
the
second motor unit 60 is oriented such that the first and second ends 266, 268
of the
mounting foot 166 are aligned with respective ones of the first and second
ends 272,
274 of aperture 164. The mounting foot 166 is inserted into the aperture 164
until
the mounting foot 166 protrudes beyond the rear side 264 of aperture 164, and
the
second motor unit 60 is rotated relative to the second motor unit mount 160,
as
indicated by arrow 283 in Fig. 14 (clockwise when viewed looking towards the
rear
side 264), until the motor unit 60 is aligned and/or configured to at least
partially
generate forward thrust. Although the nonexclusive illustrative example
presented in
Fig. 14 includes rotation in one or more particular directions, it should be
understood
that other examples may include rotation in an opposite direction and/or other
forms
of movement such as linear translations. In some nonexclusive illustrative
examples, motor unit 60 is aligned and/or configured to at least partially
generate
forward thrust when the propeller 68 may rotate without impacting the wing 42,
as
shown in Fig. 14.
[0080] In some nonexclusive illustrative examples, at least one of the first
and
second motor unit mounts 158, 160 may include one or more rotation restricting
devices that limit the rotation of the mounting foot 166 relative to the motor
unit
mount. For example, the first and second motor unit mounts 158, 160 may
include
one or more projections or studs 284, as shown in Figs. 11, 13 and 14. Such
rotation restricting devices may be configured to deter and/or preclude
undesired
rotation of the motor unit. For example, as shown in the nonexclusive
illustrative
example presented in Figs. 11 and 13, the studs 284 on the first motor unit
mount
158 are configured to prevent rotation of the first motor unit 58 in a
direction opposite
to that indicated by arrows 280 and 282 and/or rotation of the first motor
unit 58
beyond a certain point in the direction indicated by arrows 280 and 282. Such
restrictions on rotation of the first motor unit 58 may at least partially
preclude the
23
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first motor unit mount 158 from receiving and/or retaining the first motor
unit 58 in a
position and/or orientation in which the first motor unit 58 is rendered
inoperative,
such as where the wing 42 precludes rotation of the propeller 64. As shown in
the
nonexclusive illustrative example presented in Fig. 14, the studs 284 on the
second
motor unit mount 160 are configured to prevent rotation of the second motor
unit 60
in a direction opposite to that indicated by arrow 283 and/or rotation of the
second
motor unit 60 beyond a certain point in the direction indicated by arrow 283.
Such
restrictions on rotation of the second motor unit 60 may at least partially
preclude the
second motor unit mount 160 from receiving and/or retaining the second motor
unit
60 in a position and/or orientation in which the second motor unit 60 is
rendered
inoperative, such as where the wing 42 precludes rotation of the propeller 68.
[0081] In some nonexclusive illustrative examples, the first motor unit mount
158
may be configured to preclude receiving the second motor unit 60 in a position
and/or orientation in which the second motor unit 60 at least partially
generates
forward thrust and/or the second motor unit mount 160 may be configured to
preclude receiving the first motor unit 58 in a position and/or orientation in
which the
first motor unit 58 at least partially generates forward thrust. For example,
as may
be observed from comparison of the nonexclusive illustrative examples of the
second motor unit 60 and the first motor unit mount 158 presented in Figs. 9-
14, the
configuration of the aperture 164 and studs 284 of the first motor unit mount
158 in
combination with the orientation of the first and second ends 266, 268 of the
mounting foot 166 of the second motor unit 60 may at least partially preclude
the first
motor unit mount 158 from receiving the second motor unit 60 in a position
and/or
orientation in which propeller 68 may rotate without impacting the wing 42. As
may
be observed from comparison of the nonexclusive illustrative examples of the
first
motor unit 58 and the second motor unit mount 160 that are presented in Figs.
9-14,
the configuration of the aperture 164 and studs 284 of the second motor unit
mount
160 in combination with the orientation of the first and second ends 266, 268
of the
mounting foot 166 of the first motor unit 58 may at least partially preclude
the second
motor unit mount 160 from receiving the first motor unit 58 in a position
and/or
orientation in which the propeller 64 may rotate without impacting the wing
42.
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[0082] In some nonexclusive illustrative examples, the first motor unit mount
158
may be configured to preclude receiving the second motor unit 60 and/or the
second
motor unit mount 160 may be configured to preclude receiving the first motor
unit 58.
For example, the aperture 164 of the first motor unit mount 158 may be
configured to
preclude receiving the mounting foot 166 of the second motor unit 60 and/or
the
aperture 164 of the second motor unit mount 160 may be configured to preclude
receiving the mounting foot 166 of the first motor unit 58.
[0083] In some nonexclusive illustrative examples, the first motor unit mount
158
may be configured to render the second motor unit 60 inoperative if the second
motor unit 60 is received by the first motor unit mount 158 and/or the second
motor
unit mount 160 may be configured to render the first motor unit 58 inoperative
if the
first motor unit 58 is received by the second motor unit mount 160. For
example, the
first and second motor units 58, 60 and/or the first and second motor unit
mounts
158, 160 may include electrical and/or mechanical interlocks and/or
disconnects
configured to interrupt or otherwise disable and/or prevent the delivery of
power
and/or current to the first motor unit 58 when the first motor unit 58 is
received by the
second motor unit mount 160 and/or to the second motor unit 60 when the second
motor unit 60 is received by the first motor unit mount 158.
[0084] In some nonexclusive illustrative examples, at least one of the first
and
second motor unit mounts 158, 160 may be configured to retain the respective
one
of the first and second motor units 58, 60 in a selected one of a plurality of
predetermined orientations. For example, at least one of the first and second
motor
unit mounts 158, 160 may be configured to retain the respective one of the
first and
second motor units 58, 60 in a selected one of a plurality of rotational
orientations
relative to the wing 42 in which the respective one of the first and second
propellers
64, 68 at least partially generates forward thrust for toy aircraft 20. As
shown in the
nonexclusive illustrative example presented in Fig. 14, at least one of the
first and
second motor unit mounts 158, 160, such as the second motor unit mount 160,
may
include a plurality of protrusions or teeth 286 that are configured to engage
at least
one of the first and second ends 266, 268 of mounting foot 166. Such mounting
teeth 286 may provide a plurality of predetermined orientations for the motor
unit. A
nonexclusive illustrative example of a first predetermined orientation of a
motor unit
CA 02679457 2009-08-28
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is illustrated in solid lines in Fig. 14, and a nonexclusive illustrative
example of
another predetermined orientation of the motor unit is illustrated in dashed
lines in
Fig. 14. Although illustrated as a plurality of engagable teeth in the
nonexclusive
illustrative example presented in Fig. 14, any periodic and/or intermittent
series of
mechanical detents may be used, such as at least partially overlapping and/or
engaged rounded elements.
[0085] The plurality of predetermined orientations in which a first or second
motor
unit 58, 60 may be retained by a corresponding one of the first and second
motor
unit mounts 158, 160 may range over any suitable angle such as 5 degrees, 10
degrees, 15 degrees, 20 degrees, 30 degrees, or even 45 or more degrees. In
some
nonexclusive illustrative examples, the angular range of the plurality of
predetermined orientations may be symmetric about a plane or axis 288 that is
parallel to the fuselage 44. In some nonexclusive illustrative examples, the
angular
range of the plurality of predetermined orientations may permit relatively
greater
outward or inward rotation relative to axis 288. For example, where the edge,
either
forward or rearward, of the wing 42 that is proximate the motor unit mount is
swept,
either forward or rearward, the angular range of the plurality of
predetermined
orientations may be selected to exclude orientations in which the propeller
would
impact the wing 42.
[0086] Permitting oblique orientation and/or alignment of at least one of the
first
and second motor units 58, 60 relative to the wing 42 and/or the fuselage 44
may
permit trimming the flight of the toy aircraft 20 based on the corresponding
obliquely
oriented and/or aligned thrust vector or vectors from the propeller driven by
the
obliquely oriented motor unit or units. For example, at least one of the first
and
second motor units 58, 60 may be selectively angled and/or oriented such that
the
toy aircraft 20 tends to fly straight and/or such that the toy aircraft 20
tends to turn
during flight. In some nonexclusive illustrative examples, the effect of the
angling of
the first and second motor units 58, 60 may vary with the speed and/or
attitude of the
aircraft. In some nonexclusive illustrative examples, selectively angling
and/or
orienting at least one of the first and second motor units 58, 60 may permit
trimming
the flight characteristics of the aircraft, such as to compensate for
differing thrust
outputs of the left and right motors and/or other conditions that tend to
affect flight.
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For example, the toy aircraft 20 may be trimmed for a desired flight path,
such as
straight flight, by selectively angling and/or orienting at least one of the
first and
second motor units 58, 60 to compensate for such conditions as one or more
bent
portions of airframe 28, such as the wing 42 or the fuselage 44, that induces
a left
and/or right turning tendency into the toy aircraft 20. In some nonexclusive
illustrative examples, selectively angling and/or orienting at least one of
the first and
second motor units 58, 60 may permit and/or cause the toy aircraft 20 to
perform a
maneuver, such as a loop, roll, spin, circle, or the like, absent any control
input
during flight. For example, selectively angling and/or orienting at least one
of the first
and second motor units 58, 60 may cause the toy aircraft 20 to perform a loop,
roll,
spin, circle or other maneuver without any external control inputs or signals,
such as
signals from a remote control transmitter. By selectively angling and/or
orienting at
least one of the first and second motor units 58, 60 to a greater or lesser
extent, the
radius of the loop, roll, spin, circle or other maneuver may be selected
without any
external control inputs or signals.
[0087] Another nonexclusive illustrative example of a toy aircraft according
to the
present disclosure is shown in Figs. 15-16 and indicated generally at 20.
Unless
otherwise specified, toy aircraft 20 may, but is not required to, contain at
least one of
the structure, components, functionality, and/or variations described,
illustrated,
and/or incorporated herein.
[0088] As shown in the nonexclusive illustrative example presented in Figs. 15-
16, toy aircraft 20 may include first and second wings 292, 294. The first and
second
wings 292, 294 may be arranged in any suitable manner relative to the airframe
28
and/or fuselage 44, such as in tandem where one of the first and second wings
292,
294 is forward of the other of the first and second wings 292, 294, or in a
biplane
configuration, as shown in the nonexclusive illustrative example presented in
Figs.
15-16.
[0089] In some nonexclusive illustrative examples, at least one of the first
and
second wings 292, 294, such as the first wing 292, may generally be attached
to the
airframe 28 and/or fuselage 44 as generally described above and illustrated in
Fig.
16. In some nonexclusive illustrative examples, the second wing 294 may be
attached to the airframe 28 and/or fuselage 44 in a manner similar to that for
the first
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wing 292, or it may be installed differently. For example, as shown in the
nonexclusive illustrative example presented in Fig. 16, the second wing 294 ay
be
attached to the airframe 28 and/or fuselage 44 by inserting a portion 296 of
the
fuselage 44 into a slot 298 in wing 294, as indicated by arrow 300. In some
nonexclusive illustrative examples, at least one of the first and second wings
292,
294 may be at least partially supported relative to the fuselage 44 by one or
more
structural elements or reinforcing members 130, such as the laterally-
supporting
wing clips 132 shown in Figs. 15 and 16.
[0090] As shown in the nonexclusive illustrative example presented in Figs. 15-
16, the first and second wings 292, 294 may additionally or alternatively be
at least
partially supported relative to each other and/or relative to the airframe 28
and/or the
fuselage 44 by one or more struts 302. The struts 302, which may be uniform or
configured into one or more pairs of left and right struts, may engage
corresponding
sockets 304 on the first and second wings 292, 294, as shown in Fig. 16. As
shown
in the nonexclusive illustrative example presented in Fig. 17, the sockets 304
may
include an aperture 306 that is configured to receive an end 308 of a strut
302. In
some nonexclusive illustrative examples, strut 302 may be at least partially
retained
by an enlarged portion 310 of end 308 that engages a corresponding portion 312
of
aperture 306.
[0091] A nonexclusive illustrative example of a toy aircraft kit 314 according
to the
present disclosure is shown schematically in Fig. 17. Unless otherwise
specified, the
toy aircraft kit 314 and any of its component parts may, but are not required
to,
contain at least one of the structure, components, functionality, and/or
variations
described, illustrated, and/or incorporated herein. The toy aircraft kit 314
may
include a modular power system 24 and first and second toy aircraft airframes
316,
318, each of which may be adapted for selective use with the modular power
system
24.
[0092] The modular power system 24 may include a power unit 34, a first motor
unit 58, and a second motor unit 60. The power unit 34 may include an energy
source 72 and a control circuit 74. The first motor unit 58 may include a
first motor
62 and a first propeller 64. The second motor unit 60 may include a second
motor
66 and a second propeller 68.
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[0093] The first toy aircraft airframe 316 may include a first fuselage 44, a
first
wing 42, first and second motor unit mounts 158, 160, and a first power unit
mount
40. The first wing 42 may be configured to extend from the first fuselage 44.
The
first and second motor unit mounts 158, 160 may be disposed on the first wing
42,
and may be configured to removably retain respective ones of the first and
second
motor units 58, 60. The first power unit mount 40 may be disposed on the first
fuselage 44, and may be configured to removably retain the power unit 34.
[0094] The second toy aircraft airframe 318 may include a second fuselage 44,
a
second wing 42, third and fourth motor unit mounts 158, 160, and a second
power
unit mount 40. The second wing 42 may be configured to extend from the second
fuselage 44. The third and fourth motor unit mounts 158, 160 may be disposed
on
the second wing 42, and may be configured to removably retain respective ones
of
the first and second motor units 58, 60. The second power unit mount 40 may be
disposed on the second fuselage 44, and may be configured to removably retain
the
power unit 34.
[0095] In some nonexclusive illustrative examples, the first and second toy
aircraft airframes 316, 318, as included in the kit 314, may be at least
partially
unassembled and/or at least partially disassembled. For example, the first
wing 42
may be included in kit 314 while disassembled from the first fuselage 44,
and/or the
second wing 42 may be included in kit 314 while disassembled from the second
fuselage 44.
[0096] In some nonexclusive illustrative examples, the toy aircraft 20 may
include
a wheel assembly such as the nonexclusive illustrative example shown generally
at
320 in Figs. 19 and 20. Unless otherwise specified, the wheel assembly 320
may,
but is not required to, contain at least one of the structures, components,
functionalities, and/or variations described, illustrated, and/or incorporated
herein.
The wheel assembly 320 may include a first wheel 322, a second wheel 324, and
a
wheel support element 326, which may be connected to the power unit mount 40.
[0097] The wheel support element 326 may be configured to support the first
and
second wheels 324, 326 relative to the power unit mount 40. In some examples,
the
wheel support element 326, or any of its portions or components may comprise a
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plastic material, which may be injection molded. The wheel support element 326
may include first and second wheel supports 330, 332 and first and second
wheel
mounts 334, 336. As shown in the example presented in Figs. 19 and 20, each of
the first and second wheel supports 330, 332 may extend from the power unit
mount
40 toward respective first and second wheel mounts 334, 336, which may be
spaced
from the power unit mount 40.
[0098] Each of the first and second wheel supports 330, 332 may extend from a
proximal end 340 toward a distal end 342, as shown in Fig. 22. The proximal
end
340 may be proximate to and/or connected with the power unit mount 40. For
example, as shown in Fig. 20, the first wheel support 330 may extend from a
first
proximal end 344, which may be at and/or connected to a first side 346 of the
power
unit mount 40, to a first distal end 348. Likewise, as shown in Fig. 22, the
second
wheel support 332 may extend from a second proximal end 350, which may be at
and/or connected to a second side 352 of the power unit mount 40, to a second
distal end 354.
[0099] The first proximal end 344 of the first wheel support 330 may be
configured to engage or connect with the second proximal end 350 of the second
wheel support 332 at and/or through the power unit mount 40. For example, as
shown in Fig. 21, the power unit mount 40 may include at least one passage or
hole
358, which may extend from a first side 346 of the power unit mount 40 to a
second
side 352 of the power unit mount 40. As shown in Figs. 20 and 21, the hole 358
may
be proximate the opening 146 in the power unit mount 40, and in some examples,
the power unit mount 40 may include first and second or forward and aft holes
360,
362. As shown or suggested in Figs. 20 and 22, the first proximal end 344 of
the first
wheel support 330 may include a connecting element or pin 364 that may be
configured to extend through one of the holes 358 to the second proximal end
350 of
the second wheel support 332. The connecting element or pin 364 may be
integral
with or bonded to the first proximal end 344. The second proximal end 350 of
the
second wheel support 332 may include a socket 366 configured to frictionally
and/or
mechanically receive and/or engage the connecting element or pin 364. In some
examples, the connecting element or pin 364 may be adhesively bonded to the
second proximal end 350.
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[00100] In some examples, at least one of the first and second wheel supports
330, 332 may include a plurality of struts 368. For example, as shown in Figs.
19-
22, when the power unit mount 40 includes first and second holes 360, 362,
each of
the first and second wheel supports 330, 332 may include first and second
struts
370, 372. The first struts 370 of the first and second wheel supports 330, 332
may
collectively include a pin 364 and a socket 366 configured to frictionally
and/or
mechanically receive and/or engage the pin 360. For example, the pin 364 may
be
configured to extend through the first hole 360 from the first strut 370 of
the first
wheel support 330 to the socket 366 on the first strut 370 of the second wheel
support 332. Similarly, the second struts 372 of the first and second wheel
supports
330, 332 may collectively include a pin 364 and a socket 366 configured to
frictionally and/or mechanically receive and/or engage the pin 360. For
example, the
pin 364 may be configured to extend through the second hole 362 from the
second
strut 372 of the first wheel support 330 to the socket 366 on the second strut
372 of
the second wheel support 332.
[00101] In some examples, the wheel support element 326 may include an axle
374 having first and second ends 376, 378. As shown in Figs. 20 and 22, the
axle
374 may be connected to the first and second wheel supports 330, 332 proximate
the distal ends 342. The first and second wheel mounts 334, 336 may be
proximate
the respective first and second ends 376, 378 of the axle 374 such that the
first and
second wheels 322, 324 may be rotatably mounted proximate the respective first
and second ends 376, 378 of the axle 374. For example, as shown in Fig. 20,
the
first and second wheels 322, 324 may be rotatably mounted to the respective
first
and second ends 376, 378 of the axle 374 by way of a pin or pins 380. Each pin
380
may be frictionally, mechanically, and/or adhesively attached to the first
and/or
second ends 376, 378 of the axle 374.
[00102] Another nonexclusive illustrative example of a wheel assembly for the
toy
aircraft 20 is shown generally at 384 in Figs. 23-27. Unless otherwise
specified, the
wheel assembly 384 may, but is not required to, contain at least one of the
structures, components, functionalities, and/or variations described,
illustrated,
and/or incorporated herein. The wheel assembly 384 may include a first wheel
322,
a second wheel 324, and a wheel support element 386, which may be connected to
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the power unit mount 40.
[00103] The wheel support element 386 may be in the form of an elongate
member formed to an appropriate shape. For example, as suggested in Figs. 24
and 25, the wheel support element 386 may be a formed metal wire or rod. The
wheel support element 386 may include first and second wheel supports 330, 332
that have first and second distal ends 348, 354 configured for rotatable
mounting of
the first and second wheels 322, 324. Caps 388 may be provided to retain the
first
and second wheels 322, 324 on the first and second distal ends 348, 354.
[00104] The wheel support element 386 may be formed to engage the airframe 28.
For example, as shown in Figs. 24-27, the wheel support element 386 may
include a
gripping region 389, which may be configured to frictionally and/or
mechanically
engage the first and second sides 114, 116 of the fuselage 44 and/or the first
and
second sides 346, 352 of the power unit mount 40. In some examples, the
gripping
region 389 may be sized such that it induces a compressive force into the
fuselage
44 and/or the power unit mount 40. The compressive force may assist with
retaining
the wheel support element 386 relative to the airframe 28, such as by slightly
deforming and/or slightly crushing the fuselage 44 and/or the power unit mount
40.
[00105] The wheel support element 386 may include at least one supporting
feature configured to assist with maintaining the wheel support element 386 in
a
suitable position. The supporting features may resist and/or reduce bending or
rotation of the wheel support element 386, such as bending and/or rotation
about an
axis that is perpendicular to the fuselage 44. For example, as shown in Fig.
24, the
wheel support element 386 may include a horizontal extension or nose 390. The
nose 390 may engage a suitable portion of the power unit mount 40, such as a
notch
or recess 392 in a lower surface of the opening 146 in the power unit mount
40, as
shown in Figs. 26 and 27. The recess 392 may provide clearance between the
wheel support element 386 and the housing 86 of the power unit 34. As shown in
Figs. 24 and 25, the wheel support element 386 may additionally or
alternatively
include a side extension 394. The side extension 394 may be configured to
engage
a lower surface 396 of the housing 86, which may include a corresponding slot
or
indentation.
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[00106] The power unit mount 40 may include at least one mounting feature
configured to assist with maintaining the wheel support element 386 in a
suitable
position. The mounting features may resist and/or reduce bending or rotation
of the
wheel support element 386, such as bending and/or rotation about an axis that
is
perpendicular to the fuselage 44. For example, as shown in Fig. 27, the power
unit
mount 40 may include a pair of projecting guide members 398, which may engage
the wheel support element 386.
[00107] The wheel assembly 384 may be selectively mounted on the toy aircraft
20
by inserting one of the first and second wheels 322, 324 and a portion of the
wheel
support element 386 through the opening 146. The wheel support element 386 may
be positioned such that the nose 390 is aligned with the recess 392, as
suggested by
the dashed lines in Fig. 26, and the wheel support element 386 is aligned with
the
guide members 398. The wheel support element 386 may be moved downward into
its mounted position, as shown in Figs. 26 and 27, with the nose 390 in the
recess
392 and the wheel support element 386 engaged with the guide members 398. The
power unit 34 may be inserted into the opening 146, as suggested by the arrow
400
in Fig. 27.
[00108] It is believed that the disclosure set forth herein encompasses
multiple
distinct inventions with independent utility. While each of these inventions
has been
disclosed in its preferred form, the specific embodiments thereof as disclosed
and
illustrated herein are not to be considered in a limiting sense as numerous
variations
are possible. The subject matter of the disclosure includes all novel and non-
obvious combinations and subcombinations of the various elements, features,
functions and/or properties disclosed herein. Similarly, where the claims
recite "a" or
"a first" element or the equivalent thereof, such claims should be understood
to
include incorporation of one or more such elements, neither requiring nor
excluding
two or more such elements.
[00109] It is believed that the following claims particularly point out
certain
combinations and subcombinations that are directed to one of the disclosed
inventions and are novel and non-obvious. Inventions embodied in other
combinations and subcombinations of features, functions, elements and/or
properties may be claimed through amendment of the present claims or
presentation
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of new claims in this or a related application. Such amended or new claims,
whether
they are directed to a different invention or directed to the same invention,
whether
different, broader, narrower or equal in scope to the original claims, are
also
regarded as included within the subject matter of the inventions of the
present
disclosure.
34
