U.S. patent application number 16/587863 was filed with the patent office on 2020-01-23 for methods and system for deicing a surface.
The applicant listed for this patent is Unmanned AeroSpace Technologies Ltd.. Invention is credited to Yoav Heichal, Amir Snir.
Application Number | 20200023977 16/587863 |
Document ID | / |
Family ID | 51523285 |
Filed Date | 2020-01-23 |
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United States Patent
Application |
20200023977 |
Kind Code |
A1 |
Snir; Amir ; et al. |
January 23, 2020 |
METHODS AND SYSTEM FOR DEICING A SURFACE
Abstract
A method of an embodiment includes receiving data from a sensor
that is configured to supply data related to an ice layer thickness
on a skin surface, calculating the ice layer thickness, comparing
the ice layer thickness to a threshold thickness, vibrating the
skin surface using at least one mechanical element for a sufficient
duration, sufficient frequency, and sufficient displacement to
result in removal of a first portion of the ice layer thereby
resulting in at least a partially deiced skin surface, and heating
the partially deiced skin surface using at least one heating
element. The method of an embodiment further includes heating from
a leading edge of the skin surface to a trailing edge of the skin
surface and heating the surface to result in a sufficient
temperature increase in the skin surface for removal of a second
portion of the ice layer.
Inventors: |
Snir; Amir; (Kadima, IL)
; Heichal; Yoav; (Tikva, IL) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
Unmanned AeroSpace Technologies Ltd. |
Kadima |
|
IL |
|
|
Family ID: |
51523285 |
Appl. No.: |
16/587863 |
Filed: |
September 30, 2019 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
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15137570 |
Apr 25, 2016 |
10427798 |
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16587863 |
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14216643 |
Mar 17, 2014 |
9321536 |
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15137570 |
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61788792 |
Mar 15, 2013 |
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61789009 |
Mar 15, 2013 |
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61788893 |
Mar 15, 2013 |
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Current U.S.
Class: |
1/1 |
Current CPC
Class: |
B64D 15/22 20130101;
B64D 15/14 20130101; B64D 15/16 20130101 |
International
Class: |
B64D 15/22 20060101
B64D015/22; B64D 15/14 20060101 B64D015/14; B64D 15/16 20060101
B64D015/16 |
Claims
1. A method comprising: receiving first data from at least one
first sensor; wherein the at least one first sensor is configured
to supply data related to: (i) a thickness of an ice layer on a
coated skin surface; wherein the coated skin surface comprises a
coating on a surface of a skin; wherein the skin comprises a
composite including first and second layers, wherein one of the
first and second layers is a structural layer; calculating the
thickness of the ice layer; comparing the thickness of the ice
layer to a threshold thickness; based, at least in part, on the
comparing the thickness of the ice layer to the threshold
thickness, vibrating the coated skin surface using at least one
mechanical element for a sufficient duration, sufficient frequency,
and sufficient displacement so as to result in removal of a first
portion of the ice layer thereby resulting in at least a partially
deiced coated skin surface; wherein the at least one mechanical
element comprises a linear actuator, the linear actuator comprising
a cylinder coupled to a rotation mechanism, the linear actuator
configured to convert rotational movement of the rotation mechanism
to linear movement to linearly displace the cylinder; wherein the
sufficient frequency ranges from 0.01 to 1000 hertz; and wherein
the sufficient displacement of each of the at least one mechanical
elements ranges from 2 millimeter to 15 millimeters.
2. The method of claim 1, further comprising receiving second data
from at least one second sensor, wherein the at least one second
sensor is configured to supply data related to one or more of the
following: i) air flow at one or more locations on the coated skin
surface, ii) air temperature, iii) relative pressure, and/or iv)
humidity.
3. The method of claim 1, wherein the threshold thickness is at
least 0.3 millimeters.
4. The method of claim 1, wherein the sufficient duration of each
of the at least one mechanical elements ranges from 0.01 seconds to
5 seconds.
5. The method of claim 4, wherein the sufficient duration of each
of the at least one mechanical elements ranges from 0.01 seconds to
3 seconds.
6. The method of claim 1, wherein the sufficient frequency ranges
from 10 to 500 hertz.
7. The method of claim 1, wherein removal of the first portion of
the ice layer results in complete removal of the ice layer.
8. A system comprising: at least one mechanical element; wherein
the at least one mechanical element is configured to vibrate a
coated skin surface for a duration, a frequency, and a
displacement; wherein the coated skin surface comprises a coating
on a surface of a skin; wherein the skin comprises a composite
including first and second layers, wherein one of the first and
second layers is a structural layer; wherein the displacement of
each of the at least one mechanical elements ranges from 2
millimeter to 15 millimeters; wherein the at least one mechanical
element comprises a linear actuator, the linear actuator comprising
a cylinder coupled to a rotation mechanism, the linear actuator
configured to convert rotational movement of the rotation mechanism
to linear movement to linearly displace the cylinder; at least one
first sensor; wherein the at least one first sensor is configured
to provide first data related to a thickness of an ice layer on the
coated skin surface; a control system; wherein the control system
is configured to: (i) receive the first data; (ii) calculate a
thickness of an ice layer on the coated skin surface; (iii) compare
the thickness of the ice layer to a threshold thickness; and (iv)
based, at least in part, on the comparison of the thickness of the
ice layer to the threshold thickness, activate the at least one
mechanical element for a sufficient duration, sufficient frequency,
and sufficient displacement so as to result in removal of a first
portion of the ice layer thereby resulting in at least a partially
deiced coated skin surface.
9. The system of claim 8, wherein the at least one mechanical
element comprises a plurality of actuators; wherein the plurality
of actuators are positioned on an installation device; and wherein
the installation device is configured to be positioned within an
aerodynamic surface of an aircraft.
10. The method of claim 1, wherein the rotation mechanism comprises
a threaded component.
11. The method of claim 1, wherein the skin comprises an isolation
layer.
12. The method of claim 11, wherein the isolation layer comprises
at least one of fiberglass and Kevlar fiber.
13. The method of claim 1, wherein the cylinder extends
horizontally.
14. The method of claim 1, wherein the cylinder extends at any
angle between a horizontal orientation and a vertical
orientation.
15. A method comprising: vibrating a coated skin surface using at
least one mechanical element for a sufficient duration, sufficient
frequency, and sufficient displacement so as to result in removal
of a first portion of the ice layer thereby resulting in at least a
partially deiced coated skin surface, wherein the coated skin
surface comprises a coating on the surface of a skin, wherein the
skin comprises a composite including at least a first layer and a
second layer, the first layer and the second layer comprising
composite materials, wherein at least one of the first and second
layers is a structural layer; wherein the at least one mechanical
element comprises a linear actuator, the linear actuator comprising
a cylinder coupled to a rotation mechanism, the linear actuator
configured to convert rotational movement of the rotation mechanism
to linear movement to linearly displace the cylinder; wherein the
sufficient frequency ranges from 0.01 to 1000 hertz; and wherein
the sufficient displacement of each of the at least one mechanical
elements ranges from 2 millimeters to 15 millimeters.
16. The method of claim 15, wherein the rotation mechanism
comprises a threaded component.
17. The method of claim 15, wherein the cylinder extends at any
angle between a horizontal orientation and a vertical
orientation.
18. The method of claim 15, wherein the mechanical element further
comprises a cap positioned on and end of the cylinder.
19. The method of claim 19, wherein the linear actuator includes a
motor.
20. The method of claim 19, wherein the linear actuator includes
one of a chain or a belt connected to the motor to transfer
rotation of the motor to linear motion.
Description
RELATED APPLICATIONS
[0001] This application is a continuation of U.S. patent
application Ser. No. 14/216,643, entitled "METHODS AND SYSTEM FOR
DEICING A SURFACE", filed Mar. 17, 2014, which claims the benefit
of U.S. Provisional Application No. 61/789,009, entitled "METHODS
AND SYSTEM FOR DEICING A SURFACE", filed Mar. 15, 2013, U.S.
Provisional Application No. 61/788,792, entitled "MECHANICAL
DEICING", filed Mar. 15, 2013, U.S. Provisional Application No.
61/788,893, entitled "COMPOSITE", filed Mar. 15, 2013, which are
hereby incorporated by reference herein in their entirety for all
purposes.
TECHNICAL FIELD
[0002] The system and method relates to deicing of surfaces. In
some embodiments, the system and method relate to deicing of
surfaces of airborne vehicles.
BACKGROUND
[0003] Systems and methods for deicing airborne vehicles are
known.
SUMMARY OF INVENTION
[0004] In some embodiments, the method comprises receiving first
data from at least one first sensor; wherein the at least one first
sensor is configured to supply data related to a thickness of an
ice layer on a skin surface. In some embodiments, the method
further includes calculating the thickness of the ice layer and
comparing the thickness of the ice layer to a threshold
thickness.
[0005] In some embodiments, the method includes, based, at least in
part, on the comparing the thickness of the ice layer to the
threshold thickness, vibrating the skin surface using at least one
mechanical element for a sufficient duration, sufficient frequency,
and sufficient displacement so as to result in removal of a first
portion of the ice layer thereby resulting in at least a partially
deiced skin surface. In some embodiments, the method includes
heating the partially deiced skin surface using at least one
heating element. In some embodiments, the heating is conducted from
a leading edge of the skin surface to a trailing edge of the skin
surface. In some embodiments, the heating the partially deiced skin
surface results in a sufficient temperature increase in the
partially deiced skin surface for removal of a second portion of
the ice layer.
[0006] In some embodiments, the method includes receiving second
data from at least one second sensor. In some embodiments, the at
least one second sensor is configured to supply data related to one
or more of the following: i) air flow at one or more locations on
the skin surface, ii) air temperature, iii) relative pressure,
and/or iv) humidity.
[0007] In some embodiments, the threshold thickness is at least 0.3
millimeters. In some embodiments, the sufficient duration of each
of the at least one mechanical elements ranges from 0.01 seconds to
5 seconds. In some embodiments, the sufficient duration of each of
the at least one mechanical elements ranges from 0.01 seconds to 3
seconds.
[0008] In some embodiments, the sufficient frequency of ranges from
0.01 to 1000 hertz. In some embodiments, the sufficient frequency
ranges from 10 to 500 hertz.
[0009] In some embodiments, the sufficient displacement of each of
the at least one mechanical elements ranges from 1 millimeter to 20
millimeters. In some embodiments, the temperature increase of the
partially deiced skin surface is at least 2 degrees Celsius.
[0010] In some embodiments, the removal of the first portion and
the second portion of the ice layer results in complete removal of
the ice layer. In some embodiments, a residual ice layer is present
after removal of the first portion and the second portion of the
ice layer and the residual ice layer comprises a thickness of 0.5
millimeters to 10 millimeters.
[0011] In some embodiments, the method includes receiving first
data from at least one first sensor; wherein the at least one first
sensor is configured to supply data related to a thickness of an
ice layer on a skin surface. In some embodiments, the method
further includes calculating the thickness of the ice layer and
comparing the thickness of the ice layer to a threshold
thickness.
[0012] In some embodiments, the method further includes based, at
least in part, on the comparing the thickness of the ice layer to
the threshold thickness, vibrating the skin surface using at least
one mechanical element for a sufficient duration, sufficient
frequency, and sufficient displacement so as to result in removal
of a first portion of the ice layer thereby resulting in at least a
partially deiced skin surface. In some embodiments, the sufficient
frequency of ranges from 0.01 to 1000 hertz and the sufficient
displacement of each of the at least one mechanical elements ranges
from 1 millimeter to 20 millimeters.
[0013] In some embodiments, the method includes heating the
partially deiced skin surface using at least one heating element.
In some embodiments, the heating is conducted from a leading edge
of the skin surface to a trailing edge of the skin surface and the
heating the partially deiced skin surface results in a sufficient
temperature increase in the partially deiced skin surface for
removal of a second portion of the ice layer.
[0014] In some embodiments, the sufficient duration of each of the
at least one mechanical elements ranges from 0.01 seconds to 5
seconds.
[0015] In some embodiments, the system includes at least one
mechanical element. In some embodiments, the system includes at
least one mechanical element is configured to vibrate a skin
surface for a duration, a frequency, and a displacement. In some
embodiments, the system includes at least one heating device. In
some embodiments, the at least one heating device comprises at
least one heating element. In some embodiments, the at least one
heating device is configured to heat the skin surface from a
leading edge of the skin surface to a trailing edge of the skin
surface. In some embodiments, the at least one heating device is
configured, when positioned on the skin surface, to allow the skin
surface to be vibrated by the at least one mechanical element for
the duration, the frequency and the displacement.
[0016] In some embodiments, the system includes at least one first
sensor. In some embodiments, the at least one first sensor is
configured to provide first data related to a thickness of an ice
layer on the skin surface. In some embodiments, the system includes
a control system. In some embodiments, the system includes a
control system is configured to receive the first data, calculate a
thickness of an ice layer on the skin surface, compare the
thickness of the ice layer to a threshold thickness, based, at
least in part, on the comparison of the thickness of the ice layer
to the threshold thickness, activate the at least one mechanical
element for a sufficient duration, sufficient frequency, and
sufficient displacement so as to result in removal of a first
portion of the ice layer thereby resulting in at least a partially
deiced skin surface; and activate the at least one heating element
in the heating device so as to result in heating from a leading
edge of the skin surface to a trailing edge of the skin surface;
and heating the partially deiced skin surface sufficiently for
removal of a second portion of the ice layer.
[0017] In some embodiments, the heating device is a thermal mat. In
some embodiments, the thermal mat comprises at least two of the
following: a carbon fiber sheet, a foam sheet, and a conductive
strip.
[0018] In some embodiments, the control system is further
configured to calculating a first power required for deicing and
comparing the first power required for deicing to a second power
available to an aircraft.
[0019] In some embodiments, the at least one mechanical element
comprises an actuator.
[0020] In some embodiments, the at least one mechanical element
comprises a plurality of actuators. In some embodiments, the
plurality of actuators are positioned on an installation device and
the installation device is configured to be positioned within an
aerodynamic surface of an aircraft.
BRIEF DESCRIPTION OF THE DRAWINGS
[0021] The present invention will be further explained with
reference to the attached drawings, wherein like structures are
referred to by like numerals throughout the several views. The
drawings shown are not necessarily to scale, with emphasis instead
generally being placed upon illustrating the principles of the
present invention. Further, some features may be exaggerated to
show details of particular components.
[0022] FIG. 1 illustrates features of some embodiments of the
present invention.
[0023] FIG. 2A illustrates features of some embodiments of the
present invention.
[0024] FIG. 2B illustrates features of some embodiments of the
present invention.
[0025] FIG. 3 illustrates features of some embodiments of the
present invention.
[0026] FIG. 4 illustrates features of some embodiments of the
present invention. In some embodiment, FIG. 4 illustrates a nominal
procedure according to an embodiment of the present invention.
[0027] FIG. 5 illustrates features of some embodiments of the
present invention. In some embodiments, FIG. 5 illustrates a hybrid
procedure according to an embodiment of the present invention.
[0028] FIGS. 6A-6B illustrates features of some embodiments of the
present invention.
[0029] FIGS. 7A-7C illustrates features of some embodiments of the
present invention.
[0030] FIG. 8 illustrates features of some embodiments of the
present invention.
[0031] FIG. 9 illustrates features of some embodiments of the
present invention.
[0032] FIG. 10 illustrates features of some embodiments of the
present invention.
[0033] FIG. 11 illustrates features of some embodiments of the
present invention.
[0034] FIGS. 12A-12B illustrates features of some embodiments of
the present invention.
[0035] FIGS. 13A-13B illustrate features of some embodiments of the
present invention.
[0036] FIG. 14 illustrates features of some embodiments of the
present invention.
[0037] FIG. 15 illustrates features of some embodiments of the
present invention.
[0038] FIG. 16 illustrate features of some embodiments of the
present invention.
[0039] FIG. 17 illustrates features of some embodiments of the
present invention.
[0040] FIG. 18 illustrates features of some embodiments of the
present invention.
[0041] FIG. 19 illustrates features of some embodiments of the
present invention.
[0042] FIG. 20 illustrates features of some embodiments of the
present invention.
[0043] FIG. 21 illustrates features of some embodiments of the
present invention.
[0044] FIG. 22 illustrates features of some embodiments of the
present invention.
[0045] FIG. 23 illustrates features of some embodiments of the
present invention.
[0046] FIG. 24 illustrates features of some embodiments of the
present invention.
[0047] FIG. 25 illustrates features of some embodiments of the
present invention.
[0048] The figures constitute a part of this specification and
include illustrative embodiments of the present invention and
illustrate various objects and features thereof. Further, the
figures are not necessarily to scale, some to features may be
exaggerated show details of particular components. In addition, any
measurements, specifications and the like shown in the figures are
intended to be illustrative, and not restrictive. Therefore,
specific structural and functional details disclosed herein are not
to be interpreted as limiting, but merely as a representative basis
for teaching one skilled in the art to variously employ the present
invention.
DETAILED DESCRIPTION
[0049] The present invention will be further explained with
reference to the attached drawings, wherein like structures are
referred to by like numerals throughout the several views. The
drawings shown are not necessarily to scale, with emphasis instead
generally being placed upon illustrating the principles of the
present invention. Further, some features may be exaggerated to
show details of particular components.
[0050] The figures constitute a part of this specification and
include illustrative embodiments of the present invention and
illustrate various objects and features thereof. Further, the
figures are not necessarily to scale, some features may be
exaggerated to show details of particular components. In addition,
any measurements, specifications and the like shown in the figures
are intended to be illustrative, and not restrictive. Therefore,
specific structural and functional details disclosed herein are not
to be interpreted as limiting, but merely as a representative basis
for teaching one skilled in the art to variously employ the present
invention.
[0051] Among those benefits and improvements that have been
disclosed, other objects and advantages of this invention will
become apparent from the following description taken in conjunction
with the accompanying figures. Detailed embodiments of the present
invention are disclosed herein; however, it is to be understood
that the disclosed embodiments are merely illustrative of the
invention that may be embodied in various forms. In addition, each
of the examples given in connection with the various embodiments of
the invention which are intended to be illustrative, and not
restrictive.
[0052] Throughout the specification and claims, the following terms
take the meanings explicitly associated herein, unless the context
clearly dictates otherwise. The phrases "in one embodiment" and "in
some embodiments" as used herein do not necessarily refer to the
same embodiment(s), though it may. Furthermore, the phrases "in
another embodiment" and "in some other embodiments" as used herein
do not necessarily refer to a different embodiment, although it
may. Thus, as described below, various embodiments of the invention
may be readily combined, without departing from the scope or spirit
of the invention.
[0053] In addition, as used herein, the term "or" is an inclusive
"or" operator, and is equivalent to the term "and/or," unless the
context clearly dictates otherwise. The term "based on" is not
exclusive and allows for being based on additional factors not
described, unless the context clearly dictates otherwise. In
addition, throughout the specification, the meaning of "a," "an,"
and "the" include plural references. The meaning of "in" includes
"in" and "on."
[0054] In some embodiments, the method comprises receiving first
data from at least one first sensor; wherein the at least one first
sensor is configured to supply data related to a thickness of an
ice layer on a skin surface. In some embodiments, the method
further includes calculating the thickness of the ice layer and
comparing the thickness of the ice layer to a threshold
thickness.
[0055] In some embodiments, the method includes, based, at least in
part, on the comparing the thickness of the ice layer to the
threshold thickness, vibrating the skin surface using at least one
mechanical element for a sufficient duration, sufficient frequency,
and sufficient displacement so as to result in removal of a first
portion of the ice layer thereby resulting in at least a partially
deiced skin surface. In some embodiments, the method includes
heating the partially deiced skin surface using at least one
heating element. In some embodiments, the heating is conducted from
a leading edge of the skin surface to a trailing edge of the skin
surface. In some embodiments, the heating the partially deiced skin
surface results in a sufficient temperature increase in the
partially deiced skin surface for removal of a second portion of
the ice layer.
[0056] In some embodiments the first portion is 10% of the ice
layer and the second portion is 90% of the ice layer. In some
embodiments the first portion is 20% of the ice layer and the
second portion is 80% of the ice layer. In some embodiments the
first portion is 30% of the ice layer and the second portion is 70%
of the ice layer. In some embodiments the first portion is 40% of
the ice layer and the second portion is 60% of the ice layer. In
some embodiments the first portion is 50% of the ice layer and the
second portion is 50% of the ice layer. In some embodiments the
first portion is 60% of the ice layer and the second portion is 40%
of the ice layer. In some embodiments the first portion is 70% of
the ice layer and the second portion is 30% of the ice layer. In
some embodiments the first portion is 80% of the ice layer and the
second portion is 20% of the ice layer. In some embodiments the
first portion is 90% of the ice layer and the second portion is 10%
of the ice layer.
[0057] In some embodiments the first portion is 10% of the ice
removed from skin surface ("ice removed") and the second portion is
90% of the ice removed. In some embodiments the first portion is
20% of the ice removed and the second portion is 80% of the ice
removed. In some embodiments the first portion is 30% of the ice
removed and the second portion is 70% of the ice removed. In some
embodiments the first portion is 40% of the ice removed and the
second portion is 60% of the ice removed. In some embodiments the
first portion is 50% of the ice removed and the second portion is
50% of the ice removed. In some embodiments the first portion is
60% of the ice removed and the second portion is 40% of the ice
removed. In some embodiments the first portion is 70% of the ice
removed and the second portion is 30% of the ice removed. In some
embodiments the first portion is 80% of the ice removed and the
second portion is 20% of the ice removed. In some embodiments the
first portion is 90% of the ice removed and the second portion is
10% of the ice removed.
[0058] In some embodiments, the method includes receiving second
data from at least one second sensor. In some embodiments, the at
least one second sensor is configured to supply data related to one
or more of the following: i) air flow at one or more locations on
the skin surface, ii) air temperature, iii) relative pressure,
and/or iv) humidity.
[0059] In some embodiments, the threshold thickness is at least 0.3
millimeters. In some embodiments, the sufficient duration of each
of the at least one mechanical elements ranges from 0.01 seconds to
5 seconds. In some embodiments, the sufficient duration of each of
the at least one mechanical elements ranges from 0.01 seconds to 3
seconds.
[0060] In some embodiments, the sufficient frequency of ranges from
0.01 to 1000 hertz. In some embodiments, the sufficient frequency
ranges from 10 to 500 hertz.
[0061] In some embodiments, the sufficient displacement of each of
the at least one mechanical elements ranges from 1 millimeter to 20
millimeters. In some embodiments, the temperature increase of the
partially deiced skin surface is at least 2 degrees Celsius.
[0062] In some embodiments, the removal of the first portion and
the second portion of the ice layer results in complete removal of
the ice layer. In some embodiments, a residual ice layer is present
after removal of the first portion and the second portion of the
ice layer and the residual ice layer comprises a thickness of 0.5
millimeters to 10 millimeters.
[0063] In some embodiments, the method includes receiving first
data from at least one first sensor; wherein the at least one first
sensor is configured to supply data related to a thickness of an
ice layer on a skin surface. In some embodiments, the method
further includes calculating the thickness of the ice layer and
comparing the thickness of the ice layer to a threshold
thickness.
[0064] In some embodiments, the method further includes based, at
least in part, on the comparing the thickness of the ice layer to
the threshold thickness, vibrating the skin surface using at least
one mechanical element for a sufficient duration, sufficient
frequency, and sufficient displacement so as to result in removal
of a first portion of the ice layer thereby resulting in at least a
partially deiced skin surface. In some embodiments, the sufficient
frequency of ranges from 0.01 to 1000 hertz and the sufficient
displacement of each of the at least one mechanical elements ranges
from 1 millimeter to 20 millimeters.
[0065] In some embodiments, the method includes heating the
partially deiced skin surface using at least one heating element.
In some embodiments, the heating is conducted from a leading edge
of the skin surface to a trailing edge of the skin surface and the
heating the partially deiced skin surface results in a sufficient
temperature increase in the partially deiced skin surface for
removal of a second portion of the ice layer.
[0066] In some embodiments, the sufficient duration of each of the
at least one mechanical elements ranges from 0.01 seconds to 5
seconds.
[0067] In some embodiments, the system includes at least one
mechanical element. In some embodiments, the system includes at
least one mechanical element is configured to vibrate a skin
surface for a duration, a frequency, and a displacement. In some
embodiments, the system includes at least one heating device. In
some embodiments, the at least one heating device comprises at
least one heating element. In some embodiments, the at least one
heating device is configured to heat the skin surface from a
leading edge of the skin surface to a trailing edge of the skin
surface. In some embodiments, the at least one heating device is
configured, when positioned on the skin surface, to allow the skin
surface to be vibrated by the at least one mechanical element for
the duration, the frequency and the displacement.
[0068] In some embodiments, the system includes at least one first
sensor. In some embodiments, the at least one first sensor is
configured to provide first data related to a thickness of an ice
layer on the skin surface. In some embodiments, the system includes
a control system. In some embodiments, the system includes a
control system is configured to receive the first data, calculate a
thickness of an ice layer on the skin surface, compare the
thickness of the ice layer to a threshold thickness, based, at
least in part, on the comparison of the thickness of the ice layer
to the threshold thickness, activate the at least one mechanical
element for a sufficient duration, sufficient frequency, and
sufficient displacement so as to result in removal of a first
portion of the ice layer thereby resulting in at least a partially
deiced skin surface; and activate the at least one heating element
in the heating device so as to result in heating from a leading
edge of the skin surface to a trailing edge of the skin surface;
and heating the partially deiced skin surface sufficiently for
removal of a second portion of the ice layer.
[0069] In some embodiments, the heating device is a thermal mat. In
some embodiments, the thermal mat comprises at least two of the
following: a carbon fiber sheet, a foam sheet, and a conductive
strip.
[0070] In some embodiments, the control system is further
configured to calculating a first power required for deicing and
comparing the first power required for deicing to a second power
available to an aircraft.
[0071] In some embodiments, the at least one mechanical element
comprises an actuator.
[0072] In some embodiments, the at least one mechanical element
comprises a plurality of actuators. In some embodiments, the
plurality of actuators are positioned on an installation device and
the installation device is configured to be positioned within an
aerodynamic surface of an aircraft.
[0073] In some embodiments, the present invention includes a method
and system for preventing and/or reducing ice accumulation on
surfaces. In some embodiments, the surfaces may include, but are
not limited to, surfaces of manned or unmanned airborne vehicles
(UAV), wind turbines and/or other surfaces potentially subjected to
icing conditions. In some embodiments, the surfaces may include
surfaces of wings and/or propellers of manned or unmanned airborne
vehicles, wind turbines, and the like. In some embodiments, the
wings and/or propellers are formed of a "skin" having an outer
surface exposed to one or more environmental conditions.
[0074] In some embodiments, the manner or unmanned airborne
vehicles, wind turbines and the like are referred to as "protected
systems".
[0075] In some embodiments, the system and method is designed to
prevent and/or reduce accumulation of ice on surfaces subjected to
atmospheric conditions. In some embodiments, the atmospheric
conditions include, but are not limited to, freezing rain, sleet,
snow, hail, freezing temperatures, or other atmospheric condition
that can result in ice accumulation on an exposed surface.
[0076] In some embodiments, the method and system include at least
one sensor for detecting conditions such as environmental
conditions and/or conditions of the surface. In some embodiments,
the at least one sensor is positioned in a section of the skin of
the protected system (hereinafter referred to as "skin") exposed to
the environment. In some embodiments, the at least one sensor is
positioned in a section of the skin not exposed to the
environment.
[0077] In some embodiments, the at least one sensor may include
elements for detecting environmental conditions and/or mechanical
and/or thermal conditions of the skin surface. In some embodiments,
the at least one sensor is configured to detect conditions of the
skin and/or skin surface such as ice thickness, temperature, and/or
other related property. In some embodiments, the at least one
sensor is configured to detect environmental conditions including,
but not limited to, air flow speed at one or more locations along
the surface, air temperature, relative pressure, and/or
humidity.
[0078] In some embodiments, the at least one sensor may be
configured to detect the available power for deicing in the
protected system.
[0079] In some embodiments, the system and method may include one
or more mechanical elements. In some embodiments, the mechanical
elements are configured to vibrate the surface. In some
embodiments, the mechanical elements include one or more vibration
elements configured for vibrating the surface for a duration,
frequency and/or displacement capable of removing and/or reducing
the accumulation of ice on the surface. In some embodiments, the
one or more mechanical elements include actuators configured for
vibrating the surface.
[0080] FIG. 1 shows a non-limiting cross-section of a skin 105
having a skin surface 100 of the present invention. FIG. 1 also
shows a non-limiting example of an actuator-type mechanical element
110 of the present invention.
[0081] In some embodiments, the mechanical elements are positioned
in a section of the skin exposed to the environment. In some
embodiments, the mechanical elements are positioned in a section of
the skin not exposed to the environment.
[0082] In some embodiments, the mechanical elements are positioned
in a pattern so as to result in at least a partial removal,
reduction and/or at least a partial prevention of ice accumulation
on the skin surface.
[0083] In some embodiments, the mechanical elements 210 are
positioned along the surface. In some embodiments, the mechanical
elements 210 are positioned along the surface as shown in FIGS. 2A
and 2B.
[0084] In some embodiments, the system and method include one or
more thermal elements. In some embodiments, the thermal elements
are configured to heat the surface to a sufficient temperature so
as to result at least a partial removal, reduction and/or
prevention of ice accumulation on the skin surface.
[0085] In some embodiments, the thermal mats 220 are positioned in
a pattern along the surface so as to result in at least a partial
reduction and/or prevention of ice accumulation on the skin
surface. In some embodiments, the thermal elements include a
thermal mat. In some embodiments, the thermal mats 220 may be
positioned on the skin surface as shown in FIGS. 2A and 2B.
[0086] In some embodiments, the thermal mats 320 form part of the
skin 305 as shown in the cross-section of the skin 305 of FIG. 3.
In some embodiments, the skin 305 may include a surface coating
302, a thermal mat 320, an isolation layer 304, and/or a structural
carbon fiber layer 306. In some embodiments, the isolation layer
may be formed of fiberglass Kevlar fiber or equivalent. In some
embodiments, the thermal mat 320 may include carbon fiber,
conductive silver, and/or conductive copper and/or other conductive
material configured for conduction of electric energy to the
heaters for heating the surface.
[0087] In some embodiments, the surface may include two dimensional
m.times.n array. In some embodiments, the configuration may be an
alternate two dimensional layout as shown in the non-limiting
example of FIG. 2A. In some embodiments, the mechanical, thermal,
and/or sensory elements are configured to result in at least a
partial removal, reduction and/or prevention of ice accumulation on
the skin surface. In some embodiments, the size of m and/or n will
vary based on specific conditions such as environmental conditions,
etc.
[0088] In some embodiments, the system may further include at least
one control unit to monitor, calculate and/or assess the various
conditions such as the ice thickness on the surface, environmental
conditions, etc. In some embodiments, the at least one control unit
is configured to activate the mechanical and/or thermal elements
based, at least in part, on conditions detected by the at least on
sensor. In some embodiments, the at least sensor provides
information regarding the conditions to the at least one control
unit in real-time.
[0089] In some embodiments, the sensor and thermal elements are
combined. In some embodiments, the sensor and thermal elements are
both positioned in the thermal mat. In some embodiments, the
mechanical, sensor and/or heating elements are separated.
[0090] In some embodiments, the method includes: detecting a
thickness of ice on an surface of a protected system; detecting at
least one of: i) air flow at one or more locations on the surface,
ii) air temperature, iii) relative pressure and iv) humidity using
at least one sensor; detecting a quantity of power available for
deicing the skin surface; comparing the ice thickness to a
threshold level; vibrating the skin surface using one or more
mechanical elements for a sufficient duration, frequency, and
displacement so as to result in removal and/or reduction in the ice
thickness; removing, via breaking or equivalent, the ice from the
leading edge; continuing the removal process by heating the skin
from the leading edge to the trailing edge of the aerodynamic
surface for a sufficient time using at least one heating element so
as to result in a sufficient temperature increase in the skin
surface to melt a layer positioned between the ice and the skin
surface and thus allow the ice to by removed by the air flow.
[0091] In some embodiments, the method steps occur sequentially,
concomitantly, or independently. In some embodiments, the heating
step is conducted after the vibration step.
[0092] In some embodiments, the threshold level of ice is equal to
or greater than 1 millimeters. In some embodiments, the threshold
level of ice is equal to or greater than 0.5 millimeters. In some
embodiments, the threshold level of ice is equal to or greater than
0.3 millimeters. In some embodiments, the threshold level of ice is
equal to or greater than 0 millimeters. In some embodiments, the
vibrating step is conducted via mechanical pulsation using one or
more mechanical elements such as actuators.
[0093] In some embodiments, the vibrating step is conducted using
mechanical elements that are positioned in a spatial pattern and
temporal sequence, based, at least in part, on the projected use of
the protected system. In some embodiments, the project use of the
protected system may be defined, at least in part, by the mission
profile of the protected system.
[0094] In some embodiments, the vibrating step is conducted using
mechanical elements such as actuators. In some embodiments, each of
the mechanical elements may be operated for a duration ranging from
0.01 to 5 seconds, a frequency ranging from 0.01 to 1000 Hz, and/or
a displacement amplitude ranging from 1 to 20 mm. In some
embodiments, the duration, frequency, and/or displacement amplitude
of one or more mechanical elements varies based, at least in part,
on the conditions detected using the at least one sensor. As used
herein, "displacement", "displacement amplitude", and "amplitude"
may be used interchangeably.
[0095] In some embodiments, each of the mechanical elements may be
operated for a duration ranging from 0.01 to 5 seconds. In some
embodiments, each of the mechanical elements may be operated for a
duration ranging from 0.05 to 4 seconds. In some embodiments, each
of the mechanical elements may be operated for a duration ranging
from 0.1 to 3 seconds. In some embodiments, each of the mechanical
elements may be operated for a duration ranging from 0.5 to 2
seconds. In some embodiments, each of the mechanical elements may
be operated for a duration ranging from 1 to 1.5 seconds. In some
embodiments, each of the mechanical elements may be operated for a
duration ranging from 1.1 to 1.3 seconds.
[0096] In some embodiments, each of the mechanical elements may be
operated for a frequency ranging from 0.01 to 1000 Hz. In some
embodiments, each of the mechanical elements may be operated for a
frequency ranging from 10 to 500 Hz. In some embodiments, each of
the mechanical elements may be operated for a frequency ranging
from 20 to 300 Hz. In some embodiments, each of the mechanical
elements may be operated for a frequency ranging from 40 to 200 Hz.
In some embodiments, each of the mechanical elements may be
operated for a frequency ranging from 60 to 100 Hz. In some
embodiments, each of the mechanical elements may be operated for a
frequency ranging from 70 to 90 Hz.
[0097] In some embodiments, the mechanical elements may be operated
using a displacement amplitude ranging from 1 to 20 mm. In some
embodiments, the mechanical elements may be operated using a
displacement amplitude ranging from 2 to 15 mm. In some
embodiments, the mechanical elements may be operated using a
displacement amplitude ranging from 4 to 12 mm. In some
embodiments, the mechanical elements may be operated using a
displacement amplitude ranging from 6 to 10 mm. In some
embodiments, the mechanical elements may be operated using a
displacement amplitude ranging from 7 to 9 mm.
[0098] In some embodiments, the displacement amplitude ranges from
1 millimeter to 20 millimeters. In some embodiments, the
displacement amplitude ranges from 2 millimeters to 10 millimeters.
In some embodiments, the displacement amplitude ranges from 1
millimeter to 5 millimeters. In some embodiments, the displacement
amplitude ranges from 2 millimeters to 5 millimeters. In some
embodiments, the displacement amplitude ranges from 3 millimeters
to 5 millimeters. In some embodiments, the displacement amplitude
is 4 millimeters.
[0099] In some embodiments, the heating step is conducted using one
or more heating elements comprising at least one thermal mat. In
some embodiments, the heating step is conducted using heating
elements in a spatial pattern and temporal sequence based, at least
in part, on the projected use of the protected system. In some
embodiments, the project use of the protected system may be
defined, at least in part, by the mission profile of the protected
system.
[0100] In some embodiments, the heating step includes reducing
and/or preventing accumulation of residual ice present after the
vibrating step. In some embodiments, the heating step is conducted
so as to increase the temperature of the skin surface from below
the freezing point of one or more fluids including, but not limited
to water (hereinafter referred to as "freezing point") to greater
than 0 degrees Celsius. In some embodiments, the heating step is
conducted to heat the interface layer between the ice and the skin
surface sufficiently so as to result in sufficiently reducing the
bond between the ice and the skin surface to allow removal or
reduction in the ice thickness by flow of air along the skin
surface.
[0101] In some embodiments, the heating step is conducted so as to
increase the temperature of the skin surface from below the
freezing point to over 0 degrees Celsius. In some embodiments, the
heating step is conducted so as to increase the temperature of the
skin surface from below freezing point to over 4 degrees Celsius.
In some embodiments, the heating step is conducted so as to
increase the temperature of the skin surface from below freezing
point to over 3 degrees Celsius. In some embodiments, the heating
step is conducted so as to increase the temperature of the skin
surface from below freezing point to over 2 degrees Celsius. In
some embodiments, the heating step is conducted so as to increase
the temperature of the skin surface from below freezing point to
over 10 degrees Celsius.
[0102] In some embodiments, the heating step is conducted so as to
increase the temperature of the skin surface from below freezing
point to over >40 degrees Celsius (up to structural integrity
limitations). In some embodiments, the heating step is conducted so
as to increase the temperature of the skin surface from below
freezing point to over 30 degrees Celsius. In some embodiments, the
heating step is conducted so as to increase the temperature of the
skin surface from below freezing point to over -10 or more degrees
Celsius.
[0103] In some embodiments, the method results in ice residuals
having a thickness of less than 0.5 millimeters after deicing. In
some embodiments, the residuals have a thickness ranging from 0.5
millimeters and 1 millimeter. In some embodiments, the residuals
have a thickness ranging from 1 millimeter and 4 millimeters. In
some embodiments, the residuals have a thickness ranging from 1
millimeter and 2 millimeters.
[0104] In some embodiments, the power required for the present
invention ranges from 1% to 10% of the total power consumption
required for operation of the aircraft. In some embodiments, the
power required for the present invention is between 2% and 8%. In
some embodiments, the power required for the present invention is
between 2% and 6%. In some embodiments, the power required for the
present invention is between 2% and 4%. In some embodiments, the
power required for the present invention is between 1% and 3%.
[0105] In some embodiments, the method includes evaluation of the
ice thickness on the skin surface combined with additional
information from at least one sensor to initiate and optimize
mechanical and/or thermal ice removal steps. In some embodiments,
the method includes a combination of simultaneous heating (thermal)
and vibration (mechanical) using patterns of thermal/mechanical
elements positioned at the skin surface. The intensity and duration
of the heating and/or vibration is based, at least in part, on the
ice thickness, the environmental conditions or other condition
potentially affecting the deicing and/or condition capable of
detection using one or more sensors. In some embodiments, the
patterns of ice removal are selected based on historical or real
time data and analysis to reduce the bond between the ice and the
skin surface via the application of heat and/or vibration and thus
allow the removal of or reduction in the ice thickness by the flow
of air along the surface.
[0106] In some embodiments, the process of ice-accretion assessment
and removal may occur continuously throughout the duration of
operation of the protected systems. In some embodiments, a control
unit may be configured to implement the ice accumulation assessment
and removal process on an intermittent basis. In some embodiments,
the control unit implements the ice accumulation assessment and
removal process based, at least in part, on the mission profile of
the protected system, available power, environmental conditions,
and/or the distribution of ice on the skin surface.
[0107] Non-limiting examples of the method of the present invention
are shown on FIGS. 4 and 5.
[0108] In some embodiments, the present invention includes methods
and system for mechanical deicing. In some embodiments, the method
and system of deicing includes, but is not limited to installation
of one or more vibration mechanisms such as actuators.
[0109] In some embodiments, the one or more actuators may include
linear actuators as shown on FIGS. 6A-6B. In some embodiments, the
linear actuator 600 may include a motor 610, a cylinder 620, and
actuator assembly 630. In some embodiments, the linear actuator 600
uses the motor 610 to extend and retract the cylinder 620.
[0110] In some embodiments, the size of the cylinder 620 may be
adjusted based on the size of the aerodynamic surface.
[0111] In some embodiments, the linear actuator 600 includes an
actuator mechanism 700 shown on FIGS. 7A-7C. In some embodiments,
the actuator mechanism is positioned within the actuator assembly
630. In some embodiments, the actuator motor 640 is positioned
outside of the actuator assembly 650. In some embodiments, the
actuator mechanism 700 includes a sawtooth 710 having a mirror
surface 720. In some embodiments, the actuator mechanism further
includes a nut (not shown) having a surface (not shown) designed
for receiving the threaded surface 720. In some embodiments, the
actuator mechanism further includes one or more gears 730
positioned within the actuator assembly 630. In some embodiments,
the one or more gears 730 of the actuator mechanism may be
connected to one or more corresponding gears (not shown) attached
to the motor 610. In some embodiment, the one or more gears 730 of
the actuator mechanism is connected to the one or more gears of the
motor via a belt and/or a chain.
[0112] In some embodiments, the actuator mechanism further includes
a base 740 for supporting the cylinder 620. In some embodiments,
the sawtooth 710 is secured to a bottom surface of the base 740. In
some embodiments, also the mirror sawtooth 720 is secured to the
one or more gears 730 (not shown). In some embodiments, the
actuator may also include one or more ball bearings to reduce
rotational friction and support radial and/or axial loads in the
actuator. In some embodiments, the actuator mechanism 700 includes
a piston like mechanism 750. In some embodiments, the actuator
mechanism 700 includes a vertical sawtooth.
[0113] In some embodiments, the components of the actuator are
formed of low weight materials such as aluminum and/or
thermoplastics. In some embodiments, the components of the actuator
are formed from steel, brass, and/or aluminum.
[0114] In some embodiments, energizing the actuator 600 results in
the extension and/or retraction of the cylinder 620. In some
embodiments, the motor is energized resulting in rotation of the
one or more gears attached to the motor. In some embodiments, the
rotation of the one or more gears attached to the motor result in
rotation of the one or more gears 730 positioned within the
actuator assembly 630. In some embodiments, rotation of the one or
more gears 730 results in rotation of the nut (not shown) designed
for receiving the threaded surface 720 of the sawtooth 710. In some
embodiments, rotation of the nut results in the linear movement of
the cylinder 620 and base 740 along the sawtooth. In some
embodiments, rotation of the sawtooth results in the linear
movement of the caps 661 and 662. In some embodiments, the linear
movement of the cylinder 620 and base 740 results in extension of
the cylinder 620. In some embodiments, the linear movement of the
cylinder 620 and base 740 results in retraction of the cylinder
620.
[0115] In some embodiments, the one or more actuators are installed
in an aerodynamic surface including, but not limited to, a wing,
tail, propellers, and/or blade 810 of an aircraft as shown in FIG.
8. In some embodiments, the aircraft is an unmanned aerial vehicle
(i.e., a drone) or other unmanned vehicle. In some embodiments, the
system may be used in general aviation aircraft such as a small
airplane, helicopter or equivalent.
[0116] In some embodiments, the aerodynamic surface may include,
but are not limited to, surfaces of manned or unmanned airborne
vehicles (UAV), wind turbines and/or other surfaces potentially
subjected to icing conditions. In some embodiments, the surfaces
may include surfaces of wings and/or propellers of manned or
unmanned airborne vehicles, wind turbines, and the like. In some
embodiments, the wings and/or propellers are formed of a "skin"
having an outer surface exposed to one or more environmental
conditions.
[0117] In some embodiments, the manner or unmanned airborne
vehicles, wind turbines and the like are referred to as "protected
systems".
[0118] In some embodiments, the one or more actuators are
positioned so that the cylinder 620 of each actuator is positioned
against or within close proximity of an inner surface of the
aerodynamic surface 810 of an aircraft. In some embodiments, the
cylinder 620 of each actuator is positioned against or within close
proximity of an inner surface of an upper section 820 and lower
section 825 of the aerodynamic surface 810 of an aircraft. In some
embodiments, the caps 661 and 662 of each actuator is positioned
against or within close proximity of an inner surface of an upper
section 820 and lower section 825 of the aerodynamic surface 810 of
an aircraft.
[0119] In some embodiments, the cylinder 620 of each actuator is
positioned so as to result in movement of the upper section 820 of
the aerodynamic surface 810. In some embodiments, the cap 661 of
each actuator is positioned so as to result in movement of the
upper section 820 of the aerodynamic surface 810. In some
embodiments, the cylinder 620 of each actuator is positioned to be
adapted to cause controlled deformation amplitude of the upper
section 820 and lower section 825 of the aerodynamic surface. In
some embodiments, the cylinder 620 of each actuator is positioned
within close proximity of the leading edge 830 of the aerodynamic
surface 810. In some embodiments, the "leading edge" is the front
edge of the aerodynamic surface. In some embodiments, the caps 661
and 662 of each actuator is positioned within close proximity of
the leading edge 830 of the aerodynamic surface 810. In some
embodiments, the "leading edge" is the front edge of the
aerodynamic surface.
[0120] In some embodiments, the one or more actuators is secured to
an installation device 840 via one or more securing mechanism 850.
In some embodiments, the installation device 840 comprises a
rectangular sheet or equivalent. In some embodiments, the
installation device 840 further includes a bracketed section 842,
844 adapted to be installed in the aerodynamic surface. In some
embodiments, the securing mechanism 850 comprises one or more
brackets and screws.
[0121] In some embodiments, the installation device 840 includes
more than one actuator 901, 902, 903, and/or 904 as shown on FIG.
9. In some embodiments, the installation device 840 includes a
rectangular sheet 910 or equivalent for securing the more than one
actuator 901, 902, 903, and/or 904. In some embodiments, the more
than one actuator 901, 902, 903, and/or 904 are interconnected with
conduit 920. In some embodiments, conduit 920 provides mechanical
support of the more than one actuator 901, 902, 903, and/or 904. In
some embodiments, conduit 920 provides protection for the
electrical connections (not shown) that energize the more than one
actuator 901, 902, 903, and/or 904. In some embodiments, conduit
920 provides both mechanical support and protection of electrical
connections as described above.
[0122] In some embodiments, the installation device includes 1
actuator. In some embodiments, the installation device includes 2
actuators. In some embodiments, the installation device includes 3
actuators. In some embodiments, the installation device includes 4
actuators. In some embodiments, the installation device includes 5
actuators. In some embodiments, the installation device includes 6
actuators. In some embodiments, the installation device includes 7
actuators. In some embodiments, the installation device includes 8
actuators. In some embodiments, the installation device includes 9
actuators. In some embodiments, the installation device includes 10
actuators. In some embodiments, the installation device includes 11
actuators. In some embodiments, the installation device includes 12
actuators. In some embodiments, the installation device includes
more than 12 actuators.
[0123] In some embodiments, the present invention is a method
comprising installing a mechanical deicing system in an aerodynamic
surface of an aircraft, wherein the installing step comprises
attaching one or more actuators to an installation device, wherein
the installation device is adapted to be positioned within the
aerodynamic surface of the aircraft; and positioning the
installation device within the aerodynamic surface of the aircraft,
wherein the positioning step comprises inserting the installation
device from a side of the aerodynamic surface opposite a body of
the aircraft.
[0124] In embodiments, the actuators may be installed from the side
of the aerodynamic surface opposite the body of the aircraft. In
some embodiments, the actuators can be installed or removed
manually. In some embodiments, the installation device is installed
in grooves and/or tracks within the aerodynamic surface. In some
embodiments, the actuators can be removed if icing conditions are
not expected.
[0125] In some embodiments, the actuators may be installed in the
aerodynamic surface so as to result in little or no impact on the
aerodynamic surface's aerodynamics. In some embodiments, this
installation method is effective for long endurance aircraft having
laminar flow aerodynamic surfaces.
[0126] In some embodiments, the instant invention is method for
mechanically deicing an aerodynamic surface using one or more
actuators. In some embodiments, the method includes, but is not
limited to, positioning one or more actuators in close proximity to
a leading edge of an aircraft aerodynamic surface, where the
leading edge of the aircraft aerodynamic surface is at least
partially covered with ice, where each of the one or more actuators
include at least one cylinder; energizing the one or more actuators
so as to result in mechanical deformation of the aircraft
aerodynamic surface by extension of the cylinder (or length) of
each of the one or more actuators; deenergizing the one or more
actuators so as to result in retraction of the cylinder or the caps
of each of the one or more actuators; and repeating the energizing
step and deenergizing steps until substantially all of the ice has
been removed from the leading edge of the aircraft aerodynamic
surface. In some embodiments, an aircraft aerodynamic surface with
a leading edge at least partially covered in ice and an aircraft
aerodynamic surface having a leading edge with the ice removed
according to a method of the present invention is shown in FIGS. 10
and 11, respectively.
[0127] In some embodiments, the method includes deicing by
mechanically deforming the aerodynamic surface. In some
embodiments, the method includes adjusting the frequency and
amplitude of the actuator to impart sufficient kinetic energy in
the aerodynamic surface to fracture ice deposited on the
aerodynamic surface. In some embodiments, the frequency of the
actuator may be increased while the amplitude of the actuator may
be decreased resulting in no change in the kinetic energy imparted
to the aerodynamic surface. In some embodiments, the frequency of
the actuator may be decreased while the amplitude of the actuator
may be increased resulting in no change in the kinetic energy
imparted to the aerodynamic surface.
[0128] In some embodiments, the "amplitude" of the actuator is
defined as the distance the cylinder and/or caps of the actuator
travels from its original position to its extended position when
the actuator is energized. In some embodiments, the amplitude of
the actuator is measured in millimeters (mm). In some embodiments,
the cylinder and/or caps of the actuator extends vertically. In
some embodiments, the cylinder and/or caps of the actuator extends
horizontally. In some embodiments, the cylinder and/or caps of the
actuator extends at any angle between horizontal and vertical.
[0129] In some embodiments, the amplitude of the actuator is
related to the width of the leading edge. In some embodiments, the
amplitude of the actuator increases 5 millimeters for every 0.15
meter of leading edge width. In some embodiments, the amplitude of
the actuator is 4 millimeters for an aerodynamic surface having a
leading edge with a width of 0.12 meter. In some embodiments, the
amplitude of the actuator is 10 millimeters for an aerodynamic
surface having a leading edge with a width of 0.3 meters.
[0130] In some embodiments, the mechanical elements may be operated
using a displacement amplitude ranging from 1 to 20 mm. In some
embodiments, the mechanical elements may be operated using a
displacement amplitude ranging from 2 to 15 mm. In some
embodiments, the mechanical elements may be operated using a
displacement amplitude ranging from 4 to 12 mm. In some
embodiments, the mechanical elements may be operated using a
displacement amplitude ranging from 6 to 10 mm. In some
embodiments, the mechanical elements may be operated using a
displacement amplitude ranging from 7 to 9 mm.
[0131] In some embodiments, the displacement amplitude ranges from
1 millimeter to 20 millimeters. In some embodiments, the
displacement amplitude ranges from 2 millimeters to 15 millimeters.
In some embodiments, the displacement amplitude ranges from 4
millimeter to 12 millimeters. In some embodiments, the displacement
amplitude ranges from 6 millimeters to 10 millimeters. In some
embodiments, the displacement amplitude ranges from 7 millimeters
to 9 millimeters.
[0132] In some embodiments, the amplitude of the actuator ranges
from 1 millimeter to 10 millimeters. In some embodiments, the
amplitude of the actuator ranges from 2 millimeters to 10
millimeters. In some embodiments, the amplitude of the actuator
ranges from 1 millimeter to 5 millimeters. In some embodiments, the
amplitude of the actuator ranges from 2 millimeters to 5
millimeters. In some embodiments, the amplitude of the actuator
ranges from 3 millimeters to 5 millimeters. In some embodiments,
the amplitude of the actuator is 4 millimeters.
[0133] In some embodiments, the "frequency" of the actuator is
defined as the number of times actuator is energized and thus the
cylinder of the actuator is extended per unit time. In some
embodiments, the frequency of the actuator is measured in
hertz.
[0134] In some embodiments, the frequency of the actuators range
from 0.01 to 1000 Hz. In some embodiments, the frequency of the
actuators range from 10 to 500 Hz. In some embodiments, the
frequency of the actuators range from 20 to 300 Hz. In some
embodiments, the frequency of the actuators range from 40 to 200
Hz. In some embodiments, the frequency of the actuators range from
60 to 100 Hz. In some embodiments, the frequency of the actuators
range from 70 to 90 Hz.
[0135] In some embodiments, the installation device includes one or
more actuators. In some embodiments, the installation device
includes a bar or rod or equivalent for supporting the one or more
actuators. In some embodiments, the bar or rod is formed of a
material suitable for conditions associated with aviation such as
extreme temperatures, forces, or other condition. In some
embodiments, the bar or rod is formed of metal such as
aluminum.
[0136] In some embodiments, the installation device further
includes control circuits. In some embodiments, the control
circuits allow remote operation of the actuators. In some
embodiments, the installation device provides mechanical support of
the one or more control circuits. In some embodiments, the
installation device provides mechanical support for the one or more
control circuits and the one or more actuators. In some
embodiments, the installation device provides supports for one or
more control circuits, where each control circuit is positioned
adjacent to one of the one or more actuators.
[0137] In some embodiments, the installation device is configured
to be manually removed from the aerodynamic surface. In some
embodiments, the installation device and the control circuits and
the actuators secured thereto are removed from the aerodynamic
surface by removing the installation device.
[0138] In some embodiments, the installation device is a rod or bar
that may be removed along with the control circuits and the
actuators by exerting a force on one or both ends of the rod or
bar. In some embodiments, the installation device in the form of a
rod or bar is removed by pushing the rod or bar from the
aerodynamic surface. In some embodiments, the installation device
840 in the form of a rod or bar is removed by pulling the rod or
bar from the aerodynamic surface.
[0139] In some embodiments, removal of the installation device is
completed manually. In some embodiments, the removal of the
installation device is completed automatically using a mechanical
device.
[0140] In some embodiments, the installation device is adapted to
isolate the movement of the actuators to reduce or eliminate
vibration in the aerodynamic surface not targeted for deicing.
[0141] Various embodiments of the actuator positioned in an
aerodynamic surface are shown on FIGS. 12A-14. Various embodiments
of the actuator are shown on FIGS. 15-17.
[0142] In some embodiments, the method of the present invention
results in a residual ice thickness of less than 0.5 millimeters
after deicing. In some embodiments, the residual ice thickness
ranges between 0.5 millimeters and 1 millimeter. In some
embodiments, the residual ice thickness ranges between 1 millimeter
and 2 millimeters.
[0143] In some embodiments, the power required for the present
invention ranges from 1% to 7% of the total power consumption
required for operation of the aircraft. In some embodiments, the
power required for the present invention is between 2% and 4%. In
some embodiments, the power required for the present invention is
between 1% and 3%.
[0144] In some embodiments, the weight of the actuators ranges from
2% to 4% of total weight of the aircraft. In some embodiments, the
weight of the actuators ranges from 2.5% to 3.5% of the total
weight of the aircraft.
[0145] In some embodiments, various screen shots of a simulation of
the actuators used for mechanical deicing of an aerodynamic surface
that was captured by high speed detection equipment are shown on
FIGS. 18-21. In some embodiments, the temperature of the simulation
was -10 degrees Celsius and the ice thickness on the aerodynamic
surface was less than 3 millimeters.
[0146] In some embodiments, various screen shots of a simulation of
an actuator positioned in an aerodynamic surface was captured by
high speed detection equipment are shown on FIGS. 22-23. In some
embodiments, FIG. 22 shows an actuator with a cylinder in its
original position. In some embodiments, FIG. 23 shows an actuator
with a cylinder in its extended position.
[0147] In some embodiments, the system includes an axial vibrating
apparatus that includes a vibration mechanism. In some embodiments,
the vibration mechanism is installed as a single mechanism or in
pairs facing opposite directions. In some embodiments, the
vibration mechanism is controlled to vibrate in different
frequencies as required by skin and ice accumulated thereon.
[0148] In some embodiments, the vibrating apparatus is installed in
discrete locations inside the lift or steering device and along its
leading edge so that a sequential operation is acting along the
wing/tail at a determined interval for a determined period of
time.
[0149] In some embodiments, the single vibrating apparatus is
installed on a rail and travelling along the wing/tail while
operating continuously or in determined locations and for a
determined time.
[0150] In some embodiments, the vibrating apparatus is installed on
a rail and travelling along a limited distance of the wing/tail and
several such assemblies are covering the entire area to be deiced.
In some embodiments, the vibrating apparatus is installed and
positioned in the wing/tail to provide coverage of the entire area
potentially requiring deicing.
[0151] In some embodiments, the vibrating apparatus is defined as a
standalone mechanism. In some embodiments, the vibrating apparatus
is defined as a subsystem in a protected system. In some
embodiments, the vibrating apparatus is configured to transfer
electric motor rotational energy into axial movement by using one
or more saw tooth coupled devices, spheres, a piston and crank
mechanism.
[0152] In some embodiments, the vibrating mechanism is configured
to vibrate the leading edge of the skin in a frequency between 1 to
1K Hertz for a period of time between 0.1 to 60 seconds and every
30 to 1000 seconds.
[0153] In some embodiments, the mechanism remove ice below a
certain level based, at least in part, on maintenance of the
aerodynamics requirements of the protected system.
[0154] In some embodiments, the mechanism causes a determined
deflection of the relevant surface of the skin combined with a
vibration effect that may result in a sheer force combined with
vibration between the ice and the wing surface.
[0155] In some embodiments, the operational time is not limited,
the mechanism is light weight, and the energy consumption of the
vibration mechanism is low compared with the overall energy
requirements of the protected systems.
[0156] In some embodiments, the vibration mechanism is positioned
against the leading edge of the skin. In some embodiments, the
vibration mechanism is configured for easy manual assembly and
disassembly. In some embodiments, the vibration mechanism is
configured to be used in various types of weather conditions. In
some embodiments, the vibration mechanism is configured to be
installed such that the surfaces of the protected system can be
preserved.
[0157] In some embodiments, the vibration mechanism eliminates the
maintenance issues associated with non-smooth surfaces and their
negative effect on the aerodynamics of surfaces. In some
embodiments, smooth surfaces are the primary element in efficient
and low drag aerodynamics and undisturbed flow is preferred in
aircrafts aerodynamics enabling low drag and long endurance.
[0158] In some embodiments, the present invention includes an
apparatus for removing ice from wings while flying in icing
conditions. In some embodiments, the apparatus is positioned inside
the wing leading edge.
[0159] In some embodiments, one edge of the apparatus is resting
against or placed in a predefined gap against the inner side of the
leading edge. In some embodiments, the other side of the apparatus
is resting against another inner surface of the leading edge or
supported against a support mounted inside the leading edge.
[0160] In some embodiments, the apparatus is constructed of a motor
which converts energy to mechanical rotation of a shaft. In some
embodiments, the motor shaft is coupled with a rotating disc. In
some embodiments, the coupling between the shaft and the rotating
disc may further use a transmission and/or a clutching mechanism.
In some embodiments, the rotating disc plane is in the shape or
equipped with lumps, saw tooth and/or spheres which are positioned
against a non rotating disc. In some embodiments, the non rotating
disc plane is also in the shape or equipped with lumps, saw tooth
or spheres that are mated against the plane of the rotating
disc.
[0161] In some embodiments, rotation of the rotating disc with
respect to the non rotating or contra rotating disc results in a
reciprocating motion of the non rotating or contra rotating disc
which deflects the leading edge surface causing removal of the ice
accumulated on the leading edge of the protected system by
detaching and repelling the ice layer.
[0162] In some embodiments, the other plane of the non rotating or
contra rotating disc can be coated or coupled with a cushioning
material or structural member. In some embodiments, the other plane
of the non rotating or contra rotating disc is placed against the
inner side of the leading edge, contacting it or positioned in a
predetermined gap. In some embodiments, the location where the
apparatus interfaces the leading edge surface is predetermined as
the location causing optimal ice removal effect when subjected to
force which is created due to the reciprocating motion of the
apparatus members.
[0163] In some embodiments, for example, where the opposite
apparatus plane is positioned against the opposite surface of the
leading edge it will be placed in a location where the combined
effect is causing optimal ice removal. In some embodiments, the
mechanism will be positioned in the skin of the protected system
based, at least in part, on the projected location of the ice
accumulation on the skin surface.
[0164] In some embodiments, the opening in the apparatus housing is
integrated with the non rotational or contra rotating disc in a
manner so that the non rotational or contra rotating disc
rotational movement is limited thus allowing only axial
movement.
[0165] In some embodiments, the vibrational mechanism may operate
in different and/or multiple frequencies. In some embodiments, the
vibrational mechanism is controlled so as to prevent overloading
the skin.
[0166] In some embodiments, the apparatus is installed for assembly
and disassembly from the wing side while not influencing wing
aerodynamics.
[0167] In some embodiments, the apparatus can be installed
statically while an array of the vibrating mechanisms can be
positioned along the protected system having a defined distance
between them. In some embodiments, the apparatus is traveling on a
rail along the wing leading edge.
[0168] In some embodiments, the present invention includes an
aerodynamic skin formed of a composite configured for heating thus
preventing and/or reducing ice accumulation on surfaces. In some
embodiments, the surfaces may include, but are not limited to,
surfaces of manned or unmanned airborne vehicles (UAV), wind
turbines and/or other surfaces potentially subjected to icing
conditions. In some embodiments, the surfaces may include surfaces
of wings and/or propellers of manned or unmanned airborne vehicles,
wind turbines, and the like. In some embodiments, the wings and/or
propellers are formed of an aerodynamic "skin" having an outer
surface exposed to one or more environmental conditions.
[0169] In some embodiments, the manner or unmanned airborne
vehicles, wind turbines and the like are referred to as "protected
systems".
[0170] In some embodiments, the skin formed of a composite
(hereinafter "the composite") may be configured to allow for
heating and thus reduction in ice accumulation on the surfaces of
the protected systems. In some embodiments, the composite includes
a heating device that is positioned on or forms an integral part of
the composite of a protected system.
[0171] In some embodiments, the composite may include various
subsections as shown in FIG. 24. In some embodiments, the different
subsections are comprised of various layers as shown in FIGS.
24-25, 2A and 2B.
[0172] In some embodiments, one or more subsections of the
composite include at least one layer of heat-conductive material
having sufficient structural properties for use in a protected
system. In some embodiments, the layer is a carbon fiber sheet. In
some embodiments, the carbon fiber sheet may have an areal weight
ranging from 10 to 250 grams per square meter. In some embodiments,
the carbon fiber sheet may have an areal weight ranging from 10 to
100 grams per square meter. In some embodiments, the fiber sheet
may have an areal weight ranging from 50 to 200 grams per square
meter. In some embodiments, the fiber sheet may have an areal
weight ranging from 120 to 180 grams per square meter.
[0173] In some embodiments, the carbon fiber sheet may have a
layout of 0 degrees. In some embodiments, the carbon fiber sheet
may have a layout of 45 degrees. In some embodiments, the carbon
fiber sheet may have a layout of 90 degrees.
[0174] In some embodiments, the layer of carbon fiber sheet may be
at least partially coated with a conductive material such as a
conductive epoxy.
[0175] In some embodiments, one or more subsections of the
composite include electrical and thermal conductive layers. In some
embodiments, the electrical and thermal conductive layers may
include one or more conductive strips. In some embodiments, the
conductive strips may be formed of copper, nickel, silver, and/or
aluminum. In some embodiments, the strips may be 15
millimeters.times.0.1 millimeter. In some embodiments, the strips
may be 10 millimeters+0.5 millimeter. In some embodiments, the
strips may be 5 millimeters+1.0 millimeter.
[0176] In some embodiments, one or more subsections of the
composite may include an electrical and thermal insulation layer.
In some embodiments, the insulation layer is comprised of a
material such as fiberglass or Kevlar sheet. In some embodiments,
the fiberglass or Kevlar sheet may have an areal weight ranging
from 50 to 250 grams per square meter. In some embodiments, the
fiberglass or Kevlar sheet may have an areal weight ranging from 75
to 150 grams per square meter. In some embodiments, the fiberglass
or Kevlar sheet may have an areal weight ranging from 100 to 130
grams per square meter. In some embodiments, the fiberglass or
Kevlar sheet may have an areal weight of 120 grams per square
meter.
[0177] In some embodiments, the fiberglass or Kevlar sheet may have
a layout of 0 degrees. In some embodiments, the fiberglass or
Kevlar sheet may have a layout of 45 degrees. In some embodiments,
the fiberglass or Kevlar sheet may have a layout of 90 degrees.
[0178] In some embodiments, one or more subsection of the composite
may include one or more structural sheets. In some embodiments, the
one or more structural sheets may be formed of foam. In some
embodiments, the foam may include Rohacell foam sheet. In some
embodiments, the foam sheet thickness may range from 1 millimeter
to 10 millimeters. In some embodiments, the foam sheet thickness
may range from 3 millimeters to 8 millimeters. In some embodiments,
the foam sheet thickness may range from 5 millimeters to 7
millimeters. In some embodiments, the foam sheet thickness is 5
millimeters.
[0179] In some embodiments, at least one subsection includes a top
and bottom carbon fiber sheet layer. In some embodiments, at least
one subsection is comprised of an electrical and thermal conductive
layer and an electrical and thermal insulation layer positioned
between the carbon fiber sheet layers.
[0180] In some embodiments, at least one subsection includes a
carbon fiber sheet top layer and a foam sheet bottom layer. In some
embodiments, at least one subsection is comprised of an electrical
and thermal insulation layer and another carbon fiber sheet layer
positioned between the carbon fiber sheet and foam sheet
layers.
[0181] In some embodiments, at least one subsection includes a
carbon fiber sheet top layer and carbon fiber sheet bottom layer
with an electrical and thermal insulation layer in the middle.
[0182] In some embodiments, the composite with the heating elements
is configured as shown on FIG. 24. In some embodiments, the
composite is configured as shown on FIG. 25. In some embodiments,
the composite is configured as shown on FIG. 2A. In some
embodiments, the composite is configured as shown on FIG. 2B.
[0183] While a number of embodiments of the present invention have
been described, it is understood that these embodiments are
illustrative only, and not restrictive, and that many modifications
may become apparent to those of ordinary skill in the art. Further
still, the various steps may be carried out in any desired order
(and any desired steps may be added and/or any desired steps may be
eliminated).
[0184] In some embodiments, the composite forming the "leading
edge" (see FIG. 2A) with the heating elements is configured to
withstand aerodynamic forces and serve as a membrane configured for
efficient transfer kinetic and thermal energy to reduce or prevent
ice accumulation on the composite as shown in the non-limiting
examples of FIGS. 25, 2A, and 2B.
[0185] In some embodiments, the leading edge composite is composed
of heating and/or structural elements configured to heat and/or
vibrate the composite from 0.1-1000 Hz with a displacement
amplitude ranging from 1-10 millimeters as shown in the
non-limiting example of FIG. 25.
[0186] While a number of embodiments of the present invention have
been described, it is understood that these embodiments are
illustrative only, and not restrictive, and that many modifications
may become apparent to those of ordinary skill in the art. Further
still, the various steps may be carried out in any desired order
(and any desired steps may be added and/or any desired steps may be
eliminated).
* * * * *