U.S. patent application number 13/630451 was filed with the patent office on 2013-01-31 for durable transparent coatings for aircraft passenger windows.
This patent application is currently assigned to THE BOEING COMPANY. The applicant listed for this patent is THE BOEING COMPANY. Invention is credited to Craig E. Coak, Vasan S. Sundaram, Warren W. Wascher.
Application Number | 20130029139 13/630451 |
Document ID | / |
Family ID | 37983643 |
Filed Date | 2013-01-31 |
United States Patent
Application |
20130029139 |
Kind Code |
A1 |
Coak; Craig E. ; et
al. |
January 31, 2013 |
Durable Transparent Coatings for Aircraft Passenger Windows
Abstract
A duplex coating scheme and associated method of formation,
which includes a siloxane based soft coating and a plasma based
SiOxCy hard coating used in combination to improve the durability
of acrylic substrates used in aircraft window applications.
Inventors: |
Coak; Craig E.; (Kenmore,
WA) ; Sundaram; Vasan S.; (Issaquah, WA) ;
Wascher; Warren W.; (Kent, WA) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
THE BOEING COMPANY; |
Chicago |
IL |
US |
|
|
Assignee: |
THE BOEING COMPANY
Chicago
IL
|
Family ID: |
37983643 |
Appl. No.: |
13/630451 |
Filed: |
September 28, 2012 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
|
|
11289920 |
Nov 30, 2005 |
8313812 |
|
|
13630451 |
|
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Current U.S.
Class: |
428/336 ;
428/411.1; 428/446; 428/447; 428/500 |
Current CPC
Class: |
C23C 16/0272 20130101;
Y10T 428/31935 20150401; Y10T 428/24942 20150115; C23C 16/401
20130101; B05D 7/04 20130101; C08J 7/0427 20200101; C08J 2333/06
20130101; Y10T 428/31663 20150401; B05D 7/54 20130101; C08J 2483/00
20130101; B05D 1/62 20130101; Y10T 428/265 20150115; Y10T 428/31504
20150401; Y10T 428/31855 20150401 |
Class at
Publication: |
428/336 ;
428/411.1; 428/500; 428/447; 428/446 |
International
Class: |
B32B 5/00 20060101
B32B005/00; B32B 15/082 20060101 B32B015/082; B32B 15/00 20060101
B32B015/00; B32B 27/30 20060101 B32B027/30 |
Claims
1. A duplex coating comprising: a substrate; a soft coating; and a
hard coating; said soft coating applied to a surface of said
substrate, said hard coating applied to said soft coating.
2. The duplex coating of claim 1, wherein said substrate comprises
an acrylic substrate.
3. The duplex coating of claim 2, wherein said acrylic substrate
comprises a stretched acrylic substrate.
4. The duplex coating of claim 1, wherein the soft coating
comprises a polysiloxane adherent coating.
5. The duplex coating of claim 1, wherein the soft coating
comprises a thickness of between about 4 and 5 microns.
6. The duplex coating of claim 1, wherein the hard coating
comprises a plasma CVD based coating containing silicon.
7. The duplex coating of claim 1, wherein the hard coating
comprises a thickness of between about 4 and 5 microns.
8. The duplex coating of claim 1, wherein the hard coating
comprises a Diamondshield coating.
9. A duplex coating comprising: a stretched acrylic substrate; a
polysiloxane adherent coating; and a plasma CVD based coating
containing silicon; said polysiloxane adherent coating applied to a
surface of said stretched acrylic substrate, said plasma CVD based
coating containing silicon deposited on said polysiloxane coated
stretched acrylic substrate.
10. The duplex coating of claim 9, wherein the polysiloxane
adherent coating comprises a thickness of between about 4 and 5
microns.
11. The duplex coating of claim 9, wherein the plasma CVD based
coating containing silicon comprises a thickness of between about 4
and 5 microns.
12. The duplex coating of claim 9, wherein the plasma CVD based
coating containing silicon comprises a Diamondshield coating.
13-20. (canceled)
Description
BACKGROUND OF THE INVENTION
[0001] 1. Field of the Invention
[0002] This invention relates to protective coatings for stretched
acrylic windows, and more particularly to protective coatings which
maintain the optical quality and reduces crazing of the windows in
use.
[0003] 2. Background
[0004] Aircraft passenger windows are typically made of stretched
acrylic (i.e. acrylic substrate) due to its light weight,
flexibility and formability. However, acrylic is susceptible to
particle (e.g. sand) and water induced erosion and crazing.
Moreover, during flight, aircraft windows are subjected to
differential pressures caused by the difference in pressure between
the inside and the outside of the aircraft. The differential
pressure causes the windows to flex, and therefore can cause most
coatings to crack, allowing chemicals to attack the acrylic
substrate and in some cases allowing the coating to delaminate from
the acrylic substrate.
[0005] Windows can also be subjected to a variety of chemicals,
such as detergents and other chemicals used in aircraft
maintenance.
[0006] Presently, acrylic and other types of aircraft windows are
protected by sol-gel based polysiloxane coatings. The sol-gel
coatings are homogeneous mixtures of a solvent, an organosilane,
alkoxide and a catalyst that are processed to form a suitable
coating.
[0007] The sol-gel coatings provide high transmittance, but limited
durability against wear and UV induced degradation. The sol-gel
coatings exhibit only a moderate durability as judged from field
results. This is evident in FIG. 1 where the hard coating is not
present over a major portion of a window 100 taken off an airline
that was in service for about four years. Extensive scratches and
crazing 102 can also be seen.
[0008] Therefore, there is a need for a transparent, hard coating
with improved durability that would extend window life time. The
improved coating should also provide improved resilience against
chemicals commonly encountered in aircraft maintenance and also
improved weatherability characteristics.
SUMMARY OF THE INVENTION
[0009] The present invention provides a duplex coating scheme. In
one aspect of the invention, the coating scheme includes a siloxane
based soft coating and a plasma based SiO.sub.xC.sub.y hard coating
used in combination to improve the durability of aircraft
windows.
[0010] To circumvent durability issues associated with the
presently used siloxane (1, 2) based coatings, the present
invention provides a duplex coating that exhibits flexibility,
inertness to chemicals used in aircraft maintenance and extreme
durability and resistance to crazing.
[0011] In one aspect of the invention, a duplex coating is provided
which includes a polysiloxane adherent coating; and a plasma CVD
based coating containing silicon. The polysiloxane adherent coating
is applied to a surface of a stretched acrylic substrate. The
plasma CVD based coating is deposited on the polysiloxane coated
stretched acrylic substrate.
[0012] In another aspect of the present invention, a method of
forming a duplex coating on a substrate is provided. The method
includes depositing a polysiloxane adherent coating on a surface of
a substrate; and depositing a plasma CVD based coating on the
polysiloxane adherent coating.
[0013] The duplex coating of the present invention improves
weatherability, resistance to chemical exposure, wear resistance
and resistance to flexing induced crazing of stretched acrylic. The
wear resistance of the duplex coating, as measured by Taber Wear
testing (ASTM D 1044-99), has been shown to be more than an order
of magnitude better than the currently used siloxane coatings. The
duplex coating also improves flexing induced crazing of the acrylic
substrates.
[0014] The optical properties (light transmittance in the visible
region of the solar spectrum, clarity and haze) of an acrylic
substrate with the duplex coating have been shown to be about the
same as that of a window having a single polysiloxane coating.
[0015] Additional advantages, objects, and features of the
invention will be set forth in part in the detailed description
which follows. It is to be understood that both the foregoing
general description and the following detailed description are
merely exemplary of the invention, and are intended to provide an
overview or framework for understanding the nature and character of
the invention as it is claimed.
BRIEF DESCRIPTION OF THE DRAWINGS
[0016] The accompanying drawings are included to provide further
understanding of the invention, illustrate various embodiments of
the invention, and together with the description serve to explain
the principles and operation of the invention. In the drawings, the
same components have the same reference numerals. The illustrated
embodiment is intended to illustrate, but not to limit the
invention. The drawings include the following Figures:
[0017] FIG. 1 is an example of a used window;
[0018] FIG. 2 is a simplified illustration of an acrylic substrate
coated with a duplex coating in accordance with an embodiment of
the present invention;
[0019] FIG. 3 is a graph showing Taber wear test results for
stretched acrylic with polysiloxane and the duplex coating of the
present invention;
[0020] FIG. 4 is a simplified schematic of a three point flex
test;
[0021] FIG. 5 is a simplified schematic of a Load/Temperature Flex
Test Cycle for Coated Acrylic Coupons in accordance with an
embodiment of the present invention;
[0022] FIG. 6 is a graph showing change in dry adhesion index as a
result of exposure to various chemicals (marked in the figure) for
24 hours of a polysiloxane and duplex coated stretched acrylic in
accordance with an embodiment of the present invention;
[0023] FIG. 7 is a graph showing change in wet adhesion index as a
result of exposure to various chemicals (marked in the figure) for
24 hours of a polysiloxane and duplex coated stretched acrylic in
accordance with an embodiment of the present invention; and
[0024] FIG. 8 is a graph showing Taber wear test results after
chemical exposure for a polysiloxane and duplex layer coated
stretched acrylic in accordance with an embodiment of the present
invention.
DETAILED DESCRIPTION OF THE INVENTION
[0025] As illustrated in FIG. 2, the duplex coating 200 of the
present invention includes the combination of a first coating 202
and a second coating 204 deposited onto a substrate 206, such as an
acrylic substrate 206. In one embodiment, acrylic substrate 206 may
be a common aircraft passenger window 100.
[0026] In one embodiment, second coating 204 is deposited onto
acrylic substrate 206 using a plasma based Chemical Vapor
Deposition (CVD) coating process. The plasma CVD coating is a
relatively "hard" coating, which provides better wear resistance,
chemical inertness and the like, than other coatings generated by
wet chemical methods such as sol-gel coatings. The ion bombardment
effects which occur during plasma CVD of silicon based transparent
coatings have been shown to improve the hardness and durability of
the coatings. The ion bombardment during deposition tends to
enhance the surface mobility of the depositing species and hence
improve the optical quality, from the point of view of haze and
clarity, of the coating.
[0027] In accordance with the present invention, hard coating 204
may include a silicon based layer, such as for example, a
SiO.sub.xC.sub.y based layer or a Diamondshield layer available
from Diamonex Inc.
[0028] Although the plasma CVD based or hard coating 204 has
increased hardness and durability and improved optical
characteristics, first coating 202 is provided to provide improved
adhesion and flexibility characteristics to the plasma CVD based
hard coating 204, which alone exhibits poor adhesion to acrylic
substrate 206.
[0029] In accordance with the present invention, first coating or
"soft" coating 202 may include an adherent polysiloxane based
layer. Soft coating 202 provides a bonding layer and thus is formed
prior to depositing hard coating 204. In combination, soft coating
202 combined with hard coating 204 form duplex coating 200 in
accordance with the present invention.
[0030] Soft coating 202 need not be very thick to provide the above
identified benefit to hard coating 204. In one embodiment, soft
coating 202 may be between about 100 and 200 angstroms thick to be
sufficient to ensure the adhesion of hard coating 204 to acrylic
substrate 206. In one example, tests showed that stretched acrylic
substrate 206 with a thick soft coating 202 on the order of 4
microns performed well in wear tests.
[0031] Referring again to FIG. 2, in one exemplary embodiment,
stretched acrylic substrate 206 is first treated and coated with
soft coating 202. In this embodiment, soft coating 202 includes a 4
micron thick polysiloxane based adherent transparent coatings.
[0032] Next, a silicon based transparent hard coating 204, for
example, Diamondshield, is deposited on the soft coated acrylic
substrate 206 using an ion assisted plasma process. The deposition
process includes using silicon containing precursors, such as
hexamethydisiloxane and oxygen. The plasma CVD conditions, such as
gas flow, deposition pressure, plasma power and the like, may be
optimized to produce hard, transparent coatings in accordance with
well known plasma CVD principles.
[0033] In one embodiment, acrylic substrate 206, prior to being
loaded into a vacuum chamber for the application of hard coating
204, may be first chemically cleaned to remove contaminants such as
hydrocarbons and other undesirable materials. The cleaning process
may be accomplished using, for example, ultrasonic cleaning in
solvents or aqueous detergents. Once the desired vacuum conditions
are obtained, substrate 206 may be sputter cleaned using inert ions
and or oxygen ions. Once the cleaning step is complete, the hard
coat application can commence.
[0034] In one embodiment, for example in window applications, hard
coating 204 may be between 4 and 5 microns thick.
Coating Performance Evaluation:
[0035] With no intent to limit the present invention, to validate
the improved performance of duplex coating 200 versus the currently
used polysiloxane coating in applications using acrylic substrates,
the following comparisons are made.
[0036] To perform the comparison, a first group (Group I) of
stretched acrylic substrates is coated with a polysiloxane coating
to a thickness of about 4 microns. A second group (Group II) of
stretched acrylic substrates is first coated with a polysiloxane
coating to a thickness of 4 microns, followed by a plasma based
hard coating to a thickness of about 5 microns to form the Duplex
coated acrylic substrates of the present invention.
[0037] Wear Test:
[0038] Coated substrates (Group I & Group II) are tested for
wear in accordance with the procedure described in ASTM D-1044-99,
"Standard Test Method for Resistance of Transparent Plastics to
Surface Abrasion". This test consists of using two CS-10F wheels to
which a predetermined load of 500 gm is applied to each. The wheels
are made to abrade the coated acrylic substrate surfaces as it
rotates. The increase in haze is used as the criteria for measuring
the severity of abrasion. The tests are run until the haze
increased by 5% as a result of the abrasion. The results of tests
are shown in FIG. 3. As shown in the graph of FIG. 3, duplex
coatings exhibit improvement in wear resistance by more than an
order of magnitude when compared to a polysiloxane coating.
Flex Test:
[0039] A modified ASTM D-790 test protocol is used in conducting
the flex tests of coated components. Samples of dimensions
1''.times.12''.times.0.5'' with coatings (Group I & II) are
subjected to a three point bend test as shown in FIG. 4. The side
with the hard coating is facing downwards in this figure. A thin
film of 75 wt % sulfuric acid in water is applied to the coating
using a fiber glass filter and a Teflon tape. The test article is
subjected to a cyclic load/temperature profile as shown in FIG. 5.
An ultimate load of 3600 PSI is used in these tests. The tests are
continued until the coating cracks or the surface exhibits crazing
(whichever occurs first). The results show that while the
polysiloxane coated substrates (Group I) failed in 50 cycles, the
Duplex coated substrates (Group II) of the present invention show
no crack or craze even after 500 cycles.
Chemical Exposure Test:
[0040] Stretched acrylic substrates with duplex coating in
accordance with the present invention are exposed to chemicals that
are normally used in the performance of aircraft maintenance. The
samples are exposed to each chemical for a period of 24 hours
(exception: exposure to MEK was for 4 hours) and then tested for
adhesion (modified ASTM D 3330-BSS 7225) and % haze change due to
wear when tested per ASTM D-1044-99. The results are shown in FIGS.
6, 7, and 8 for the polysiloxane coated substrates (Group I) and
the duplex coated substrates (Group II). The samples with duplex
coatings exhibit no degradation in adhesion (as indicated by
adhesion index) or wear induced haze change as a result of chemical
exposure.
UV/Humidity Exposure:
[0041] Coated (Group I & Group II) substrates are exposed to
ultraviolet light (UV-A lamp with peak wavelength at 340
nm)/humidity for a total exposure of 300 KJ/m2 in accordance with
SAE J1960. The exposure consists of 40 minute light, 20 minute
light with front spray, 60 minute light and 60 minute dark with
front and back spray. Another set of samples from Groups I & II
are first exposed to various chemicals (per chemical test above)
and then subjected to UV/Humidity test protocol. In both of these
tests, the samples with the duplex coating showed no degradation as
a result of UV/humidity exposure and performed better than those
with single polysiloxane coating alone.
[0042] Accordingly, the scope of the present invention should not
be limited to the particular embodiments illustrated and described
herein, as they are merely exemplary in nature, but rather, should
be fully commensurate with that of the claims appended hereafter
and their functional equivalents.
* * * * *