U.S. patent number RE47,176 [Application Number 14/136,854] was granted by the patent office on 2018-12-25 for propellers and propeller related vehicles.
This patent grant is currently assigned to Rehco, LLC. The grantee listed for this patent is Rehco, LLC. Invention is credited to Nicholas Grisolia, Keith Johnson, Jeffrey Rehkemper.
United States Patent |
RE47,176 |
Rehkemper , et al. |
December 25, 2018 |
Propellers and propeller related vehicles
Abstract
A propeller related vehicle in accordance with one embodiment of
the present invention is described as a helicopter having an
airframe housing a motor mechanism for powering a main propeller
attached to a main drive shaft that extends vertically through the
airframe and for powering a tail rotor. The helicopter further
includes a horizontal stabilizing mechanism attached between the
main propeller and the main drive shaft, which permits the main
propeller to freely pivot about the main drive shaft independently
from the airframe. As such when the main propeller is rotating and
the main propeller begins to pitch, the rotating main propeller has
a centrifugal force created by the rotation thereof and will tend
to pivot about the horizontal stabilizing mechanism in a manner
that offsets the pitch such that the helicopter remains in a
substantially horizontal position. In addition various main
propeller configurations may be employed that provide additional
self-stabilization.
Inventors: |
Rehkemper; Jeffrey (Chicago,
IL), Johnson; Keith (Roberts, WI), Grisolia; Nicholas
(Lake Geneva, WI) |
Applicant: |
Name |
City |
State |
Country |
Type |
Rehco, LLC |
Chicago |
IL |
US |
|
|
Assignee: |
Rehco, LLC (Chicago,
IL)
|
Family
ID: |
1000003532091 |
Appl.
No.: |
14/136,854 |
Filed: |
December 20, 2013 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
Issue Date |
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29158997 |
Jun 14, 2005 |
D506178 |
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29158996 |
Mar 22, 2005 |
D503142 |
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60348891 |
Jan 14, 2002 |
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60337670 |
Nov 7, 2001 |
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Reissue of: |
10189681 |
Jul 8, 2002 |
6659395 |
Dec 9, 2003 |
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Current U.S.
Class: |
1/1 |
Current CPC
Class: |
B64C
27/473 (20130101); B64C 27/43 (20130101); B64C
27/473 (20130101); B64C 27/43 (20130101); B64C
27/14 (20130101); B64C 27/14 (20130101); A63H
27/12 (20130101); B64C 27/52 (20130101); B64C
27/32 (20130101); B64C 27/52 (20130101); A63H
27/12 (20130101); B64C 27/32 (20130101) |
Current International
Class: |
B64C
27/32 (20060101); B64C 27/14 (20060101); B64C
27/473 (20060101); B64C 27/52 (20060101); B64C
27/43 (20060101); A63H 27/133 (20060101); A63H
27/00 (20060101) |
Field of
Search: |
;416/18,139,141,227A,231R ;244/17.19,17.11,17.23 ;446/37,36,57,58
;D21/442 |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
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2002352512 |
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May 2003 |
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AU |
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2431661 |
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May 2003 |
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CA |
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1558853 |
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Dec 2004 |
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CN |
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1318263 |
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May 2007 |
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CN |
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60208929 |
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Jul 2006 |
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DE |
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1441945 |
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Jan 2006 |
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EP |
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751837 |
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Jul 1956 |
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GB |
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3733366 |
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Jan 2006 |
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JP |
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03005415 |
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Feb 2005 |
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MX |
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Other References
Trademark Publication EM 000062088-0001 A1, published Dec. 23,
2003, Office for Harmonization in the Internal Market
(OHIM)--European Union Community Trademark Office. cited by
applicant .
Front page of HK 1070628 B (The Hong Kong Special Administrative
Region of the People's Republic of China), published Jun. 24, 2005,
and corresponding to CN 1318263 C. cited by applicant.
|
Primary Examiner: English; Peter C
Attorney, Agent or Firm: Sacharoff; Adam K. Much Shelist,
P.C.
Parent Case Text
CROSS-REFERENCE TO RELATED APPLICATIONS
This application claims the benefit of U.S. Provisional Patent
Application having Ser. No. 60/337,670 .[.and filed on.]..Iadd.,
filed .Iaddend.Nov. 7, 2001 and claims the benefit of U.S.
Provisional Patent Application having Ser. No. 60/348,891 .[.and
filed on.]..Iadd., filed .Iaddend.Jan. 14, 2002 and hereby
incorporates both provisional applications by reference.
This application further claims the benefit .Iadd.to and is a
continuation-in-part .Iaddend.of U.S. Design application having
Ser. No. 29/158,996 .[.and filed.]..Iadd., filed .Iaddend.Apr. 15,
2002 .[.and.]..Iadd., and now U.S. Pat. No. D503,142. This
application further .Iaddend.claims the benefit .Iadd.to and is a
continuation-in-part .Iaddend.of U.S. Design application having
Ser. No. 29/158,997 .[.and filed.]..Iadd., filed .Iaddend.Apr. 15,
2002.Iadd., and now U.S. Pat. No. D506,178 .Iaddend.and hereby
incorporates both design .[.applications.]. .Iadd.patents
.Iaddend.by reference.
Claims
We claim:
1. A .Iadd.toy .Iaddend.helicopter having an airframe .[.housing,
a.]. .Iadd.housing a .Iaddend.motor mechanism for powering a main
propeller attached to a main drive shaft that extends vertically
through the airframe and for powering a tail rotor, the .Iadd.toy
.Iaddend.helicopter further comprising a horizontal stabilizing
means attached between the main propeller and the main drive shaft,
which permits the main propeller to freely pivot .[.about.].
.Iadd.relative to .Iaddend.the main drive shaft independently from
the airframe, .[.wherein when the main propeller is rotating and
the main propeller begins to pitch, the rotating main propeller
having a centrifugal force created by the rotation thereof will
tend to pivot about the horizontal stabilizing means in a manner
that offsets the pitch such that the helicopter remains in a
substantially horizontal position.]. .Iadd.wherein the horizontal
stabilizing means comprises a rotor head secured to the main drive
shaft and a rotor mount mounted to the rotor head by only one pin
such that the main propeller pivots about only one axis relative to
the main drive shaft, wherein the main propeller is pivotally
supported by the horizontal stabilizing means and comprises a pair
of blades extending outwardly from the rotor mount and such that
the blades are mounted parallel to the pin, and wherein the
horizontal stabilizing means and the main propeller are arranged
with one another such that the toy helicopter remains in a
substantially horizontal position when a pitch of the main
propeller during rotation is offset by a centrifugal force acting
on the main propeller causing the propeller to pivot relative to
the main drive shaft about the pin of the horizontal stabilizing
means.Iaddend..
2. The .Iadd.toy .Iaddend.helicopter of claim 1, wherein the main
propeller .[.includes.]. .Iadd.further comprises.Iaddend.: .[.a
pair of blades extending outwardly from the horizontal stabilizing
means along a single axis, each blade having.]. .Iadd.each blade of
the pair of blades having .Iaddend.a leading edge, a proximal end
defined as an end proximal to the horizontal stabilizing means, and
a distal end; and .[.a safety arc attached to the proximal and
distal ends of each blade and positioned in front of the leading
edge of each blade.]. .Iadd.first and second safety arcs, the first
safety arc attached to the proximal and distal ends of one of the
blades and the second safety arc attached to the proximal and
distal ends of the other of the blades, wherein each of the safety
arcs is positioned forward of a respective leading edge of the
corresponding blade.Iaddend..
3. The .Iadd.toy .Iaddend.helicopter of claim 2, wherein .[.the
safety arc has a diameter that.]. .Iadd.each of the safety arcs
.Iaddend.transitions from a relatively flat horizontal surface
.[.by the.]. .Iadd.at the respective .Iaddend.proximal end into a
wider vertical surface .[.by the.]. .Iadd.at the respective
.Iaddend.distal end.
4. The .Iadd.toy .Iaddend.helicopter of claim 1, wherein the main
propeller includes: .[.a pair of blades extending outwardly from
the horizontal stabilizing means.]. .Iadd.each of the blades of the
pair of blades extending outwardly .Iaddend.along a horizontal
plane, each blade having a leading edge, a proximal end defined as
an end proximal to the horizontal stabilizing means and a distal
end; .[.a safety arc attached to the proximal and distal ends of
each blade and positioned in front of the leading edge of each
blade; and.]. .Iadd.first and second safety arcs, the first safety
arc attached to the proximal and distal ends of one of the blades
and the second safety arc attached to the proximal and distal ends
of the other of the blades, wherein each of the safety arcs is
positioned forward of the respective leading edge of the
corresponding blade; and .Iaddend. a pair of flybars extending
outwardly from .[.the horizontal stabilizing means.]. .Iadd.a
central portion of the main propeller .Iaddend.along said
horizontal plane, .[.wherein when the main propeller is rotating
and the main propeller begins to pitch, the flybars having an
increased centrifugal force created by the rotation thereof will
tend to pivot the blades about the horizontal stabilizing means in
a manner that offsets the pitch such that the helicopter remains in
a substantially horizontal position.]. .Iadd.wherein the flybars
and blades are arranged with one another such that a pitch of the
blades is offset by an increased centrifugal force created by
rotation of the flybars to act on and pivot the blades about the
pin of the horizontal stabilizing means to maintain a substantially
horizontal position of the toy helicopter.Iaddend..
5. The .Iadd.toy .Iaddend.helicopter of claim 1, wherein the main
propeller includes: .[.a pair of blades pivotally.]. .Iadd.the pair
of blades being pivotally supported by the horizontal stabilizing
means and .Iaddend.extending outwardly along a horizontal plane
from the horizontal stabilizing means, each .[.blade.]. .Iadd.of
the blades .Iaddend.having an end proximal to the horizontal
stabilizing means and a distal end; .[.a crossbar joint that is
secured to the proximal ends of the blades; a pair of crossbars
extending outwardly from the crossbar joint along the horizontal
plane, each crossbar having an end proximal secured to the crossbar
joint and a distal end;.]. a circular safety ring secured to .[.the
distal ends of each crossbar and having pivots for receiving.]. the
.[.distal ends of each blade; and.]. .Iadd.distal end of each of
the blades; and .Iaddend. .[.a flybar.]. .Iadd.a first flybar and a
second flybar each .Iaddend.extending outwardly .[.both.]. from a
leading edge .[.and.]. .Iadd.of a respective one of the blades and
a third flybar and a fourth flybar each extending from .Iaddend.a
trailing edge .[.defined in each blade.]. .Iadd.of a respective one
of the blades.Iaddend., each .[.flybar.]. .Iadd.of the four flybars
.Iaddend.extending along said horizontal plane, .[.wherein when the
main propeller is rotating and the main propeller begins to pitch,
the flybars having an increased centrifugal force created by the
rotation thereof will tend to pivot the blades about the horizontal
stabilizing means in a manner that offsets the pitch such that the
helicopter remains in a substantially horizontal
position.]..Iadd.wherein when the main propeller is rotating and
begins to pitch, the flybars having an increased centrifugal force
acting thereupon and created by the rotation will pivot the blades
about the horizontal stabilizing means in a manner that offsets the
pitch such that the toy helicopter remains in a substantially
horizontal position.Iaddend..
.[.6. The helicopter of claim 1, wherein the main propeller
includes: two pair of blades pivotally extending outwardly along a
horizontal plane from the horizontal stabilizing means, such that
one pair of blades is perpendicular to the other pair of blades,
each blade having an end proximal to the horizontal stabilizing
means and a distal end; a circular safety ring having pivots for
receiving the distal ends of each blade; and a flybar extending
outwardly from a leading edge defined in each blade, wherein when
the main propeller is rotating and the main propeller begins to
pitch, the flybars having an increased centrifugal force created by
the rotation thereof will tend to pivot the blades about the
horizontal stabilizing means in a manner that offsets the pitch
such that the helicopter remains in a substantially horizontal
position..].
7. The .Iadd.toy .Iaddend.helicopter of claim .[.4, 5, or 6.].
.Iadd.4 or 5.Iaddend., wherein the flybars include weighted ends to
increase the centrifugal force created by the rotation thereof.
.[.8. The helicopter of claim 1, wherein the horizontal stabilizing
means is defined as a pivotal main rotor head mounted to the main
drive shaft, and a main propeller mount extending downwardly from
the main propeller; the main propeller mount pivotally mounted to
the pivotal main rotor head such that the main propeller may pivot
about the main drive shaft..].
9. A self-stabilizing propeller .Iadd.assembly .Iaddend.for use in
.[.an rotary-type aircraft wherein the propeller is rotatably
attached to a drive shaft and rotates in a plane, the propeller
comprising:.]. .Iadd.a toy rotary aircraft, the propeller assembly
including: a propeller mounted via a pin to a drive shaft for
rotation in a plane and for pivotal movement about only one axis
relative to the drive shaft; .Iaddend. a pair of blades .Iadd.of
the propeller .Iaddend.extending outwardly from each other .[.along
a single axis.]. .Iadd.such that each of the blades is mounted
parallel with the pin.Iaddend., each blade having a leading edge, a
proximal end defined as an end proximal to the other blade, and a
distal end; and .[.a safety arc attached to the proximal and distal
ends of each blade and positioned in front of the leading edge of
each blade.]. .Iadd.first and second safety arcs, the first safety
arc extending forward of the leading edge of a first one of the
blades and attached to the proximal and distal ends of the first
one of the blades and the second safety arc extending forward of
the leading edge of a second one of the blades and attached to the
proximal and distal ends of the second one of the blades.Iaddend.,
each safety arc having a predetermined weight, wherein .[.when the
propeller is rotating the weight of the.]. .Iadd.a weight of each
of the .Iaddend.safety arcs creates a centrifugal force .[.that
tends to offset.]. .Iadd.that offsets .Iaddend.a pitch force
exhibited by the propeller when rotating such that the propeller
.[.has a tendency to remain.]. .Iadd.remains .Iaddend.in
substantially the same plane.
10. The .[.helicopter.]. .Iadd.self-stabilizing propeller assembly
.Iaddend.of claim 9, wherein .[.the safety arc has a diameter
that.]. .Iadd.each of the safety arcs .Iaddend.transitions from a
relatively flat horizontal surface .[.by the.]. .Iadd.at the
respective .Iaddend.proximal end into a wider vertical surface
.[.by the.]. .Iadd.at the respective .Iaddend.distal end.
.[.11. An aircraft having an airfame housing a motor mechanism for
powering at least one substantially horizontal orientated
propeller, each propeller is attached to a corresponding drive
shaft that extends vertically through the airframe, the aircraft
further comprising at least one horizontal stabilizing means
attached between one of the propellers, of the at least one
propeller, and the corresponding drive shaft, which permits the
propeller to freely pivot about the corresponding drive shaft
independently from the airframe, wherein when said propeller is
rotating and said rotating propeller begin to pitch, the rotating
propeller having a centrifugal force created by the rotation
thereof will tend to pivot about the horizontal stabilizing means
in a manner that offsets the pitch such that the aircraft remains
in a substantially horizontal position..].
.[.12. The helicopter of claim 11, wherein at least one of the at
least one propeller includes: a pair of blades extending outwardly
from the horizontal stabilizing means along a single axis, each
blade having a leading edge, a proximal end defined as an end
proximal to the horizontal stabilizing means, and a distal end; and
a safety arc attached to the proximal and distal ends of each blade
and positioned in front of the leading edge of each blade..].
.[.13. The helicopter of claim 12, wherein the safety arc has a
diameter that transitions from a relatively flat horizontal surface
by the proximal end into a wider vertical surface by the distal
end..].
.[.14. The helicopter of claim 11, wherein at least one of the at
least one propeller includes: a pair of blades extending outwardly
from the horizontal stabilizing means along a horizontal plane,
each blade having a leading edge, a proximal end defined as an end
proximal to the horizontal stabilizing means and a distal end; a
safety arc attached to the proximal and distal ends of each blade
and positioned in front of the leading edge of each blade; and a
pair of flybars extending outwardly from the horizontal stabilizing
means along said horizontal plane, wherein when the main propeller
is rotating and the main propeller begins to pitch, the flybars
having an increased centrifugal force created by the rotation
thereof will tend to pivot the blades about the horizontal
stabilizing means in a manner that offsets the pitch such that the
helicopter remains in a substantially horizontal position..].
.[.15. The helicopter of claim 11, wherein the main propeller
includes: a pair of blades pivotally extending outwardly along a
horizontal plane from the horizontal stabilizing means, each blade
having an end proximal to the horizontal stabilizing means and a
distal end; a crossbar joint that is secured to the proximal ends
of the blades; a pair of crossbars extending outwardly from the
crossbar joint along the horizontal plane, each crossbar having an
end proximal secured to the crossbar joint and a distal end; a
circular safety ring secured to the distal ends of each crossbar
and having pivots for receiving the distal ends of each blade; and
a flybar extending outwardly both from a leading edge and a
trailing edge defined in each blade, each flybar extending along
said horizontal plane, wherein when the main propeller is rotating
and the main propeller begins to pitch, the flybars having an
increased centrifugal force created by the rotation thereof will
tend to pivot the blades about the horizontal stabilizing means in
a manner that offsets the pitch such that the helicopter remains in
a substantially horizontal position..].
.[.16. The helicopter of claim 11, wherein the main propeller
includes: two pair of blades pivotally extending outwardly along a
horizontal plane from the horizontal stabilizing means, such that
one pair of blades is perpendicular to the other pair of blades,
each blade having an end proximal to the horizontal stabilizing
means and a distal end; a circular safety ring having pivots for
receiving the distal ends of each blade; and a flybar extending
outwardly from a leading edge defined in each blade, wherein when
the main propeller is rotating and the main propeller begins to
pitch, the flybars having an increased centrifugal force created by
the rotation thereof will tend to pivot the blades about the
horizontal stabilizing means in a manner that offsets the pitch
such that the helicopter remains in a substantially horizontal
position..].
.[.17. The helicopter of claim 14, 15, or 16, wherein the flybars
include weighted ends to increase the centrifugal force created by
the rotation thereof..].
.[.18. The helicopter of claim 11, wherein the horizontal
stabilizing means is defined as a pivotal main rotor head mounted
to the main drive shaft, and a main propeller mount extending
downwardly from the main propeller; the main propeller mount
pivotally mounted to the pivotal main rotor head such that the main
propeller may pivot about the main drive shaft..].
.[.19. A self-stabilizing aircraft having at least one propeller
comprising: a motor mechanism in communication with at least one
drive shaft, each drive shaft corresponding to one of the
propellers, of the at least one propeller, a rotor head mounted to
each drive shaft; and each propeller having a propeller mount that
is pivotally attached to the rotor head of the corresponding drive
shaft, such that each propeller pivots about the corresponding
drive shaft freely and independently from the aircraft, wherein
when the propeller is rotating and the propeller begins to pitch,
the rotating propeller having a centrifugal force created by the
rotation thereof will tend to pivot about the corresponding drive
shaft in a manner that offsets the pitch such that the aircraft
remains in a substantially horizontal position..].
.[.20. The self-stabilizing aircraft of claim 19, wherein at least
one of the propellers, includes: a pair of blades extending
outwardly from each other along a single axis, each blade having a
leading edge, a proximal end defined as an end proximal to the
other blade, and a distal end; and a safety arc attached to the
proximal and distal ends of each blade and positioned in front of
the leading edge of each blade..].
.[.21. The self-stabilizing aircraft of claim 19, wherein at least
one of the propellers, includes: a pair of blades extending
outwardly from the propeller mount of said propeller; and a pair of
flybars extending outwardly from said propeller mount..].
.[.22. The self-stabilizing aircraft of claim 19, wherein at least
one of the propellers, includes: a pair of blades extending
outwardly from the propeller mount of said propeller, each blade
having a leading edge, a proximal end defined as an end proximal to
said propeller mount and a distal end; a safety arc attached to the
proximal and distal ends of each blade and positioned in front of
the leading edge of each blade; and a pair of flybars extending
outwardly from said propeller mount..].
.[.23. The self-stabilizing aircraft of claim 19, wherein at least
one of the propellers, includes: a pair of blades extending
outwardly from the propeller mount of said propeller, each blade
having an end proximal to said propeller mount and a distal end; a
crossbar joint that is secured to the proximal ends of the blades;
a pair of crossbars extending outwardly from the crossbar joint,
each crossbar having an end proximal secured to the crossbar joint
and a distal end; a circular safety ring secured to the distal ends
of each crossbar and having pivots for receiving the distal ends of
each blade; and a flybar extending outwardly both from a leading
edge and a trailing edge defined in each blade..].
.[.24. The self-stabilizing aircraft of claim 19, wherein at least
one of the propellers, includes: two pair of blades extending
outwardly from the propeller mount of said propeller, such that one
pair of blades is perpendicular to the other pair of blades, each
blade having an end proximal to said propeller mount and a distal
end; a circular safety ring having pivots for receiving the distal
ends of each blade; and a flybar extending outwardly from each
leading edge defined in each blades..].
25. A propeller .Iadd.assembly for use in toy rotary aircraft, the
propeller assembly .Iaddend.comprising: a pair of blades extending
outwardly from each other .[.along a single axis.]., each blade
having a leading edge, a proximal end defined as an end proximal to
the other blade, and a distal end; .[.and a safety arc attached to
the proximal and distal ends of each blade and positioned in front
of the leading edge of each blade.]. .Iadd.a rotor mount extending
from an underside of the pair of blades for pivotally attaching via
only one pin to a rotor head secured to a main drive shaft defined
by the toy rotary aircraft such that the pair of blades pivot about
only one axis relative to the main drive shaft; the pair of blades
extending outwardly from each other such that each of the blades is
mounted parallel to the pin; and first and second safety arcs, the
first safety arc attached to the proximal and distal ends of one of
the blades and the second safety arc attached to the proximal and
distal ends of the other of the blades, wherein each of the safety
arcs is positioned forward of the respective leading edge of the
corresponding blade.Iaddend..
26. The propeller .Iadd.assembly .Iaddend.of claim 25, wherein
.[.the safety arc has a diameter that.]. .Iadd.each of the safety
arcs .Iaddend.transitions from a relatively flat horizontal
.[.surface by the.]. .Iadd.surface at the respective
.Iaddend.proximal end into a wider vertical surface .[.by the.].
.Iadd.at the respective .Iaddend.distal end.
27. The propeller .Iadd.assembly .Iaddend.of claim 25 further
comprising a pair of flybars extending outwardly from the proximal
ends of the blades.
28. .[.As is claimed in claim 1 or claim 11.]. .Iadd.The toy
helicopter of claim 1 .Iaddend.further comprising a means for
internally cooling the airframe defined by .[.having.]. a plurality
of vents positioned in the airframe and a combo gear in
communication with the motor mechanism, the combo gear having a
plurality of cooling blades positioned such that when the combo
gear rotates the cooling blades draw air through the plurality of
vents into the airframe.
.[.29. The aircraft of claim 19 wherein the aircraft further
includes an airframe housing the motor mechanism, and a means for
internally cooling the aircraft defined by having a plurality of
vents positioned in the airframe and a combo gear in communication
with the motor mechanism, the combo gear having a plurality of
cooling blades positioned such that when the combo gear rotates the
cooling blades draw air through the plurality of vents into the
airframe..].
.Iadd.30. The toy helicopter of claim 1 further comprising: a
circuit board in communication with the motor mechanism configured
to control the motor mechanism; and a transmitter/receiver in
communication with the circuit board. .Iaddend.
.Iadd.31. The toy helicopter of claim 30, further comprising a
power supply to power the motor mechanism and a charging jack
through which the power supply is rechargeable. .Iaddend.
.Iadd.32. The toy helicopter of claim 1, wherein the rotor head is
a U-shaped element. .Iaddend.
Description
FIELD OF THE INVENTION
This invention relates generally to propellers and propeller
related vehicles and more particular to vehicles, such as air, land
and water vehicles, that use or incorporate propellers to create
lift or as a means for propulsion, and for most aspects of the
present invention relate to air based vehicles designed for the toy
or hobby industry.
BACKGROUND OF THE INVENTION
While the present invention is related in part to vehicles
developed in the toy and hobby industry, the present invention, as
will become apparent, may easily be applicable for full sized
vehicles. There are many types of vehicles that use propellers as a
source of lift or as a means for propulsion. The more common types
of these vehicles are air/space based vehicles such as airplanes,
helicopters, or unconventional aircraft.
Air-based vehicles such as planes, helicopters and unconventional
aircraft that use propellers to create and sustain lift are well
known. In general such aircraft, especially aircraft designed for
the toy and hobby industry, require complex programming and
mechanics to control the flight path and are especially difficult
to control. In most instances, controlling these aircraft to fly in
a stable horizontal position takes countless hours of practice.
Examples of these prior art aircraft may be found in the following
U.S. Patents. U.S. Pat. No. 5,609,312 is directed to a model
helicopter that describes an improved fuselage with a structure
that supports radio-control components, drive train components and
such, in an attempt to provide a simple structure. U.S. Pat. No.
5,836,545 is directed to a rotary wing model aircraft that includes
a power distribution system that efficiently distributes engine
power to the rotary wings and tail rotor system. U.S. Pat. No.
5,879,131 is directed to a main propeller system for model
helicopters that are capable of surviving repeated crashes. U.S.
Pat. No. 4,604,075 is directed to a toy helicopter that includes a
removable control unit, which a user may plug into the toy
helicopter.
These toys use at least one propeller rotating in a substantially
horizontal plane to create and sustain lift. In addition these
"aircraft" may have another propeller rotating at an angle from the
horizontal plane to counter the torque created from the rotating
horizontal propeller. Typically the second propeller is rotating in
a substantially vertical plane. One problem that arises is when the
propellers are rotating in the horizontal plane, variations such as
wind or power fluctuations may cause the propeller blades to pitch
further causing the aircraft to tip, turn, oscillate or bank. This
effect may be compensated for and corrected in various ways with
complicated programming and mechanics. However, as mentioned above
these have a tendency to make the aircraft too expensive or too
difficult to control, especially for children. The ability to even
maintain horizontal stability in these aircrafts is extremely
difficult.
As such a need exists to improve these aircrafts that utilize
propellers to create and sustain lift to overcome the problems
identified above. Such a need should be inexpensive and easy to
implement. The outcome should further provide for aircrafts that
are easy to control or manipulate without the need for complex
linkages, servos, gyros or other electromechanical devices.
In addition to the need to improve the stability and control of
these aircrafts, there is also an increased need to make such
aircraft safer. Oftentimes a child or user is injured when the user
comes in contact with a rotating propeller. As such there exists a
further need to make the propellers safer.
SUMMARY OF THE INVENTION
A propeller related vehicle in accordance with one embodiment of
the present invention is described as a helicopter having an
airframe housing a motor mechanism for powering a main propeller
and a tail rotor. The main propeller is attached to a main drive
shaft that extends vertically through the airframe. The helicopter
further includes a horizontal stabilizing means attached between
the main propeller and the main drive shaft, which permits the main
propeller to freely pivot about the main drive shaft independently
from the airframe. As such when the main propeller is rotating and
the main propeller begins to pitch, a centrifugal force created by
the rotation of the main propeller, tends to pivot the main
propeller about the horizontal stabilizing means in a manner that
offsets the pitch such that the helicopter remains in a
substantially horizontal position.
The main propeller of the propeller related aircraft may also
exhibit an increased means for self-stabilizing the aircraft. In
one embodiment, the main propeller may include a pair of blades
extending outwardly from the horizontal stabilizing means. Each
blade includes a leading edge, an end proximal to the horizontal
stabilizing means, and a distal end. The main propeller also
includes a safety arc attached to the proximal and distal ends of
each blade and positioned in front of the leading edge of each
blade. Furthermore, the safety arc has a diameter, which
transitions from a relatively flat horizontal surface by the
proximal end into a wider vertical surface by the distal end.
In another embodiment, the main propeller may include a pair of
blades extending outwardly from the horizontal stabilizing means
along a horizontal plane. Each blade has a leading edge, an end
proximal to the horizontal stabilizing means and a distal end. A
safety arc is also provided and attached to the proximal and distal
ends of each blade and positioned in front of the leading edge of
each blade. The main propeller also has a pair of flybars extending
outwardly from the horizontal stabilizing means along the
horizontal plane. As such when the main propeller is rotating and
the main propeller begins to pitch, the flybars having an increased
centrifugal force created by the rotation thereof will tend to
pivot the blades about the horizontal stabilizing means in a manner
that offsets the pitch such that the helicopter remains in a
substantially horizontal position.
In another embodiment, the main propeller includes a crossbar joint
pivotally attached to the horizontal stabilizing means. A pair of
blades extends outwardly along a horizontal plane from the blade
joint, wherein each blade has an end proximal to the crossbar joint
and a distal end. A pair of crossbars extends outwardly from the
crossbar joint along the horizontal plane. Each crossbar has an end
proximally secured to the crossbar joint and an end distal thereto.
A circular safety ring is secured to the distal ends of each
crossbar and has pivots for receiving the distal ends of each
blade. A flybar is extended outwardly both from a leading edge and
a trailing edge defined in each blade. Each flybar extends along
the horizontal plane, wherein when the main propeller is rotating
and the main propeller begins to pitch, the flybars having an
increased centrifugal force created by the rotation thereof will
tend to pivot the blades about the horizontal stabilizing means in
a manner that offsets the pitch such that the helicopter remains in
a substantially horizontal position.
In another embodiment, the main propeller includes a blade joint
pivotally attached to the horizontal stabilizing means. Two pair of
blades are extended outwardly along a horizontal plane from the
blade joint, such that one pair of blades is perpendicular to the
other pair of blades. Furthermore each pair of blades may pivot
independently of the other pair. Each blade has an end proximal to
the blade joint and a distal end. A circular safety ring includes
pivots for receiving the distal ends of each blade. A flybar is
extended outwardly from a leading edge defined in each blade,
wherein when the main propeller is rotating and the main propeller
begins to pitch, the flybars having an increased centrifugal force
created by the rotation thereof will tend to pivot the blades about
the horizontal stabilizing means in a manner that offsets the pitch
such that the helicopter remains in a substantially horizontal
position.
In addition thereto the flybars may include weighted ends to
increase the centrifugal force created by the rotation thereof. The
main propeller described above may be used in other propeller
related vehicles since each exhibits a means for stabilizing the
propeller in a single plane, or since the main propellers include
safety rings or arcs that decrease the likelihood a user may be
injured by a rotating propeller.
Numerous advantages and features of the invention will become
readily apparent from the following detailed description of the
invention and the embodiments thereof, and from the accompanying
drawings.
BRIEF DESCRIPTION OF THE DRAWINGS
A fuller understanding of the foregoing may be had by reference to
the accompanying drawings, wherein:
FIG. 1 is an exploded view of a propeller related vehicle in
accordance with the present invention illustrating a helicopter
with a horizontal stabilizing means and a main propeller configured
with two blades and half safety arcs in front of the leading edge
of each blade;
FIG. 2 is a enlarged perspective view of the horizontal stabilizing
means;
FIG. 3 is a perspective view of the helicopter illustrated in FIG.
1;
FIG. 4 is a perspective view of another embodiment of the present
invention illustrating a helicopter with a main propeller
configured with a pair of blades and half safety arcs and a pair of
flybars extending outwardly from the center of the main
propeller;
FIG. 5 is a perspective view of another embodiment of the present
invention illustrating a helicopter with a main propeller
configured with a pair of blades and a crossbar, and a full
circular safety ring, two pair of flybars also extend outwardly
from the ends of the blades, which are distal to the center of the
main propeller;
FIG. 6 is a perspective view of another embodiment of the present
invention illustrating a helicopter with a main propeller
configured with two pairs of blades, each pair perpendicular to
each other and independently pivotally attached to the helicopter
and a full circular safety ring, in addition each blade includes a
flybar extending perpendicularly from the ends of the blade, which
is distal from the center of the main propeller;
FIG. 7 is a perspective view of one embodiment of the present
invention illustrating a helicopter with a main propeller
configured with a pair of blades and a pair of flybars extending
outwardly from the center of the main propeller;
FIG. 8 is a perspective view of another embodiment of the present
invention illustrating an airplane utilizing the main propeller
configured in FIGS. 1 and 3; and
FIG. 9 is a perspective view of a combo gear that permits the
internal cooling of the airframe.
DETAILED DESCRIPTION OF THE INVENTION
While the invention is susceptible to embodiments in many different
forms, there are shown in the drawings and will be described
herein, in detail, the preferred embodiments of the present
invention. It should be understood, however, that the present
disclosure is to be considered an exemplification of the principles
of the invention and is not intended to limit the spirit or scope
of the invention and/or the embodiments illustrated.
A propeller related vehicle, is illustrated in but one embodiment
of the present invention as a helicopter 10, depicted in FIG. 1.
Like a typical helicopter the present embodiment includes an
airframe 12 that houses the electronics and mechanical components
as well as a chassis. The chassis is preferably designed as a two
piece chassis defined as an upper chassis 20 and a lower chassis
22. Attached to the lower chassis 22 are landing skids 24 such that
the helicopter 10 may rest on a given surface.
The helicopter 10 includes a main propeller 14 and a tail rotor 16
as a means for correcting counter-rotation. Both the main propeller
14 and the tail rotor 16 are powered by a motorized means 18,
discussed in greater detail below. The actual design, shape or
length of the main propeller 14 may vary with the size and weight
of the helicopter 10, such that an appropriate amount of lift is
generated for takeoff and sustained flight. The tail rotor 16
rotates at a pre-determined rotation that offsets the torque
created by the main propeller 14, when the main propeller 14 is
rotating at a maximum revolution per minute (Max RPM). The
predetermined rotation is determined upon a number of factors well
known in the art.
The motorized means 18 includes a power supply 26, such as a
battery pack, that powers a motor mechanism 28. The motorized means
18 is controlled through a circuit board 30. A transmitter/receiver
34 may also be employed such that the helicopter 10 may be remotely
operated. The power supply 26 is accessible through a door 32 in
the lower chassis 22.
The motor mechanism 28 drives a motor pinion 36 that is meshed to a
combo crown gear 38. The combo crown gear 38 is rotatably mounted
to the upper chassis 20. The combo crown gear 38 is also mounted to
one end of a main rotor drive shaft 40. The main rotor drive shaft
40 extends upwardly from the crown gear 38 through the upper
chassis 20. The other end of the main rotor drive shaft 40 is
attached to the main propeller 14 via a means for stabilizing the
helicopter in a horizontal position 42 (referred to herein as
horizontal stabilizing means 42) discussed in greater detail
below.
As mentioned above, the tail rotor 16 is also driven by the
motorized means 18. The crown portion of the combo crown gear 38 is
meshed to a tail rotor pinion 60, which rotates a tail drive shaft
62 that is mounted thereto. A tail boom 66 is clamped by a boom
clamp 64, or otherwise secured, to the upper chassis 20. For
stability a tail bushing 68 is positioned midway within the length
of the tail boom 66. The other end of the tail drive shaft 62 is
mounted to a tail rotor rear pinion 70. The tail rotor rear pinion
70 is meshed to and drives a tail rotor crown gear 72, which spins
a tail rotor axle 74. The tail rotor 16 is secured onto the tail
rotor axle 74 such that when the tail drive shaft 62 rotates, the
tail rotor 16 rotates. A tail rotor gear housing 76 is positioned
to enclose the tail rotor crown gear 72, the tail rotor rear pinion
70 and the tail rotor axle 74.
The helicopter 10 may be turned on/off via a switch 78 mounted
through a mounting plate 80 alongside the airframe 12 of the
helicopter 10. The on/off switch 78 may also include an access
cover 82 such that the switch 78 is not accidentally hit, for
instance if the helicopter 10 crashes. In addition, the power
supply 26 may be rechargeable through a charging jack 84. The
helicopter 10 may include vents 86 to permit air to cool the
motorized means 18 or power supply 26 when running. The ventilation
or cooling process is further accomplished by the unique and novel
combo gear 38.
As further illustrated in FIG. 9, the combo gear 38 includes a
centered bore 38a that permits the combo gear 38 to mount to the
.[.upper chassis 20.]. .Iadd.main drive shaft 40.Iaddend.. The
combo gear 38 also includes outside gearing 38b that meshes to the
motor pinion 36 and crown gearing 38c that meshes to the tail rotor
pinion 60. The combo gear 38 further includes fan blades 38d that
are positioned such that when the combo gear 38 is rotated by the
motor pinion 36 the fan blades 38d draw air through the vents 86
into the chassis. Thereby cooling the internal components of the
propeller related vehicle.
To further stabilize the upper chassis 20, a grill 88 is positioned
over the upper chassis 20 such that the grill 88 may be received by
an inside area of the airframe 12, when assembled.
The horizontal stabilizing means 42 is defined by mounting the main
propeller 14 on a .[.freely.]. pivotal main rotor head 44 (FIG. 2).
The main rotor head 44 permits the main propeller 14 to pivot about
.[.its center.]. .Iadd.a pivot pin 48.Iaddend.. In addition, the
rest of the helicopter 10 below the .[.freely.]. pivotal main rotor
head 44 .[.can pivot as a pendulum.]. .Iadd.pivots together about
the pivot pin 48 similar to a pendulum.Iaddend.. The main rotor
head 44.[., preferably an U-shaped joint,.]. .Iadd.is preferably
U-shaped and .Iaddend.is secured to a rotor mount 46 that is
further secured to the underside of the main propeller 14. The
rotor mount 46 is pivotally attached to the main rotor head 44, via
.[.a.]. .Iadd.the .Iaddend.pivot pin 48. The main rotor head 44 is
mounted to the main rotor drive shaft 40 such that when the main
rotor drive shaft 40 rotates, the main rotor head 44 rotates. This
causes the rotor mount 46 to spin, rotating the main propeller 14.
It is important to note that it is preferably mounted such that the
main propeller blades 50 are mounted parallel to the pivot
.[.point.]. .Iadd.pin .Iaddend.48. This allows the main propeller
14 .[.to pivot the same direction as the blades 50, so the blades
50 can self regulate themselves.]. .Iadd.and the blades 50 thereof
to pivot about a first axis defined by the pivot pin 48 and not
about a second axis non-parallel to the first axis so the blades 50
can self-regulate themselves.Iaddend.. The pivoting action .Iadd.of
the blades 50 .Iaddend.is thus forward and backwards .Iadd.relative
to the first axis defined by the pivot pin 48 .Iaddend.and not side
to side.
Referring now to FIG. 3, the main propeller 14, depicted in FIG. 1,
includes a pair of blades 50 with a pair of safety arcs 52 in front
of the leading edges 54 of both blades 50. Each safety arc 52
starts at the center of the main propeller 14 and moves away from
the leading edge 54 of the prop in either a circular or elliptical
shape. The safety arcs 52 then join with the outer edge 56 of the
respective blade 50. As the safety arcs 52 move outwardly toward
the outer .[.edge.]. .Iadd.edges .Iaddend.56 of the blades 50,
.[.it transitions.]. .Iadd.they transition .Iaddend.from a
relatively flat horizontal surface .[.into a broader, wider
vertical surface. The safety arc and the widening of the safety arc
are features where increasing the surface area distributes a force
of any impact over a wider area; serving to protect the blades 50
upon impact.]. .Iadd.to increase a surface area such that a force
applied thereto is spread over a wider area which may assist in
protecting the blades 50 during an impact.Iaddend.. In addition,
when operated by a child the safety arc 52 prevents a child from
having a hand or eye scratched by the outer edge 56 of a blade 50.
In addition the tail rotor 16 may have the same configuration as
the main propeller 12.
The safety arcs 52 in conjunction with the fact that the main
propeller 14 is .[.freely.]. pivotally attached to the helicopter
10 provides a helicopter that is self-stabilizing.[.,.]..Iadd.;
.Iaddend.in other words the main propeller 14 is kept in a
.[.substantial.]. .Iadd.substantially .Iaddend.horizontal position
when the helicopter 10 is operating. It is well known that in true
helicopter flight, as the helicopter gains airspeed, the leading
edge of the main propeller facing forward and rotating to the back
of the helicopter, lifts more than the opposite blade. This causes
the helicopter to bank, in the unequal lift. In the present main
propeller embodiment 14, the safety arcs 52 create a centrifugal
force that tends to offset a pitch force exhibited by the main
propeller 14 when rotating, such that the main propeller 14 has a
tendency to remain in substantially the same plane. .[.Since the
weight of the safety arcs 52.]. .Iadd.The weight of the safety arcs
52 may .Iaddend.add weight to the blades 50 to provide a greater
gyroscopic effect that stabilizes the main propeller 14.
When the main propeller 14 rotates, if the main propeller 14 begins
to pitch, the safety arcs 52 will begin to move off of the
horizontal plane. The weight of the safety arcs however, create a
gyroscopic effect causing the main propeller 14 to level out by
pivoting the blades 50 about the pivot pin 48 .[.from.]. .Iadd.of
.Iaddend.the horizontal stabilizing means 42. The blades 50 pivot
along .Iadd.with .Iaddend.the changing pitch of the main propeller
14 such that the main propeller 14 returns to rotating in a
substantially horizontal plane .Iadd.to assist in horizontally
stabilizing the helicopter 10 and maintaining the helicopter 10 in
substantially the same position.Iaddend.. .[.Thereby stabilizing
the helicopter 10 horizontally, keeping it level and in
substantially the same position..]. Similarly, if the body of the
helicopter 10 (below the horizontal stabilizing means 42) begins to
sway the horizontal stabilizing mean 42 will similarly compensate
and return the helicopter .Iadd.10 .Iaddend.to a substantially
horizontal position. As such, the present invention provides a
novel mechanical means for compensating for any change in the
horizontal position of the helicopter without the need for
expensive servos and programming.
During operation, the present invention will allow the helicopter
10 to lift straight up and maintain a hover or stationary position.
The helicopter 10 may include several forms of control, starting
with no control or "free flight," or it may be outfitted with
electronics having a microprocessor for "preprogrammed" or
"programmable" flight or it may be outfitted with a radio receiver
for use with a hand held remote transmitter or it may be any
combination of the above.
As mentioned above, the tail rotor 16 rotates at a predetermined
rotation that offsets the torque created by the main propeller 14,
when the main propeller 14 is rotating at a Max RPM. With a simple
inexpensive remote control unit, a user may be able to adjust the
speed of the main propeller 14. If the user decreases the speed of
the main propeller 14, the tail rotor 16 will be rotating at a rate
such that its counter rotation force is different during
deceleration then what is required to keep the helicopter 10 from
rotating at Max RPM or during acceleration. As such the helicopter
10 will begin to rotate about the main rotor drive shaft 40,
providing the user with a simple means of rotating or turning the
helicopter 10.
In another embodiment of the present invention, the helicopter may
include various main propeller and tail rotors. Referring now to
FIG. 4, a main propeller 100 is shown attached to a helicopter 98
via the horizontal stabilizing means 42. The main propeller 100
includes a pair of opposing positioned blades 50 with safety arcs
52, either elliptical or circular, in front of the leading edges 54
of both blades 52. In addition, extending outwardly from the center
of the main propeller 100 is a pair of fly bars 102 with weighted
ends 104. The fly bars 102 add extra stability to the main
propeller 100 and also reduce the effect wind may have on the main
propeller 100. When the main propeller 100 is rotating, centrifugal
force pulls the weighted ends 104 of the fly-bars 102 straight out,
making the main propeller 100 more stable by reducing the ease
.Iadd.at which .Iaddend.the main propeller 100 may pivot during
operation. The helicopter 98, illustrated in this embodiment may
also include a tail rotor 16 configured similarly to the helicopter
10 depicted in FIGS. 1-3. The helicopter 98 may also include
various landing gears 106. The landing gears 106 may include
.[.apertures.]. .Iadd.annular members .Iaddend.108 such that the
helicopter 98 may be properly positioned on a launching/landing pad
or base (not shown).
The base may function both to charge the power supply in the
helicopter and to energize the main propeller of the helicopter to
a sufficient RPM required for launching the helicopter from the
launching base. The launching base may also include batteries and a
timer circuit for charging the helicopter and may have a separate
motor for energizing the main propeller. The charger may either be
equipped to turn off after a certain amount of time or until the
battery reaches a certain voltage.
Referring now to FIG. 5, in another embodiment of the present
invention, a helicopter 120 may include a main propeller 122 that
has a .[.two blade 124.]. .Iadd.two-blade .Iaddend.configuration
with a full circular safety ring 126 and a set of flybars 128. The
full circular safety ring 126 is planar with both blades 124. The
safety ring 126 is secured to the center 130 of the main propeller
122 by a pair of crossbars 132. The crossbars 132 attach to a
crossbar joint 134 at the center 130 of the main propeller 122. The
safety ring 126 includes pivots 136 that receive the ends of the
blades 124, which are distal to the center 130 of the main
propeller 122. The pivots 136 and the crossbar joint 134 permit the
blades 124 to pivot independently from the safety ring 126. The set
of flybars 128 is attached to the ends of the blades 124, which are
proximal to the center 130 of the main propeller 122. In addition,
the flybars 128 may also include weighted ends 138. Since the
flybars 128 are secured to the blades 124, the flybars 128 will
pivot along with the blades 124.
The flybars 128, in conjunction with the single axis pivot of the
blades 124 will help keep the main propeller 122 in equilibrium
when the main propeller is spinning. As mentioned above, in
previous propeller embodiments, when the main propeller is
rotating, the blades 124 will pivot to compensate for any banking
or unequal lift forces. In addition, when spinning with the main
propeller 122, centrifugal force will pull the weighted ends 138 on
the flybars 128 outwardly; making the blades 124 more stable by
reducing the ease .Iadd.at which .Iaddend.the blades 124 may pivot.
Additionally, even if the flybars 128 did not include weighted ends
the centrifugal force would still pull on the flybars 128
themselves, increasing the stability of the main propeller 122.
In another embodiment, .Iadd.as depicted in .Iaddend.FIG. 6, a
helicopter 150 includes a main propeller 152 that has 4 pivotal
blades 154 with a full circular safety ring 156 and flybars 158
attached separately to each blade 154. The blades 154 are arranged
in two pairs (160 and 162), each pair (160 and 162) is set
perpendicular to each other. The safety ring 156 includes four
pivots 164, each pivot 164 positioned to receive an end of a blade
154, which is distal from the center 166 of the .[.helicopter
150.]. .Iadd.main propeller 152.Iaddend.. The center 166 of the
.[.helicopter 150.]. .Iadd.main propeller 152 .Iaddend.includes a
double joint 168 that acts in concert with the pivots 164 such that
the two pairs (160 and 162) of blades 154 may pivot independently
of each other. Extending outwardly from .[.the leading.]. .Iadd.a
trailing .Iaddend.edge 170 of each blade 154 is a flybar 158, which
may include a weighted end 172.
The dual-axis pivot created by the two pairs (160 and 162) of
independently pivoting blades 154 helps keep the main propeller 152
in equilibrium when the main propeller is rotating. In addition
when rotating, a centrifugal force pulls the flybars 158, and
especially the weighted ends 172, outwardly increasing stability by
reducing the amount of pivot the blades 154 may exhibit.
In yet another embodiment of the present invention, as depicted in
FIG. 7, a helicopter 180 includes a main propeller 182 that
includes a pair of blades 184 with a pair of perpendicular flybars
188 bisecting the blades 184 at the center 186 of the main
propeller 182. Each flybar 188 may also include .[.weighted ends.].
.Iadd.a weighted end .Iaddend.190. When the main propeller 182 and
flybars 188 rotate, the main propeller 182 may begin to pitch
causing the flybars 188 to move off of the horizontal plane. The
weighted ends 190 create a gyroscopic effect causing the flybars
188 to level out by pivoting about the pivot pin 48 .[.from.].
.Iadd.of .Iaddend.the horizontal stabilizing means 42. This causes
the main propeller 182 to pivot .[.along the flybars' 188 axis
changing.]. .Iadd.about the pivot pin 48 and change .Iaddend.the
pitch of the main propeller 182 such that the blades 184 and the
flybars 188 return to rotating in the same horizontal plane
.Iadd.to assist in horizontally stabilizing the helicopter 180 and
maintaining the helicopter 180 in substantially the same
position.Iaddend.. .[.Thereby stabilizing the helicopter 180
horizontally, keeping it level and in the same position..].
As should be readily apparent from the above description each of
the main propellers described above is mounted to the horizontal
stabilizing means 42, increasing the ability to keep the helicopter
in a level horizontal plane during operation. However, the
propellers may also be incorporated onto a helicopter that does not
include the horizontal stabilizing means 42, as each of the main
propellers described above, by themselves, assist in keeping a
helicopter in a substantially horizontal plane.
In addition, the helicopter may or may not take the form of
"traditional" helicopter styling and the technology used to make
the item fly could be used in other flying toys, such as airplanes
and other unconventional aircraft, such as but not limited to a
vehicle using two or more .[.horizontal propellers. FIG. 8,.].
.Iadd.propellers with a generally vertical orientation FIG. 8
.Iaddend.depicts an airplane 192 that includes a .[.propeller
194.]. .Iadd.pair of propellers 194 which may be
.Iaddend.configured similarly to one of the above embodiments.[.,
more particularly to a propeller 194 that includes.]..Iadd.. Each
propeller 194 may include .Iaddend.a pair of blades 196, each
.[.blades.]. .Iadd.blade .Iaddend.including a half safety arc 198
covering the leading edge 197 of each blade 196.
In addition, the present invention is applicable to an aircraft
having one or more propellers that rotate in a horizontal plane.
The aircraft would typically have an airframe for housing a motor
mechanism, which is used to power each propeller. Each propeller is
attached to a corresponding drive shaft that extends vertically
through the airframe. The aircraft further includes a horizontal
stabilizing means attached between each propeller and the
corresponding drive shaft, which permits the propeller to freely
pivot about the corresponding drive shaft independently from the
airframe. As such when a propeller that is rotating begins to
pitch, the rotating propeller has a centrifugal force created by
the rotation thereof that tends to pivot the propeller about the
horizontal stabilizing means in a manner that offsets the pitch
such that the aircraft remains in a substantially horizontal
position.
From the foregoing and as mentioned above, it will be observed that
numerous variations and modifications may be effected without
departing from the spirit and scope of the novel concept of the
invention. For example, the propellers, while shown may be used in
airplanes, may find further applications in other propeller driven
vehicles, either miniature or life-size, such as but not limited to
water driven vehicles (such as boats and submarines), land driven
vehicles (such as propeller operated cars) and other air driven
vehicles (such as rockets) as well as other products that use
propellers. It is to be understood that no limitation with respect
to the specific methods and apparatus illustrated herein is
intended or should be inferred.
* * * * *