U.S. patent application number 14/070183 was filed with the patent office on 2016-10-13 for amorphous metal riblets.
This patent application is currently assigned to The Boeing Company. The applicant listed for this patent is The Boeing Company. Invention is credited to Stephen Christensen, Diane C. Rawlings.
Application Number | 20160297515 14/070183 |
Document ID | / |
Family ID | 42353382 |
Filed Date | 2016-10-13 |
United States Patent
Application |
20160297515 |
Kind Code |
A9 |
Rawlings; Diane C. ; et
al. |
October 13, 2016 |
AMORPHOUS METAL RIBLETS
Abstract
An array of aerodynamic riblets is created by a plurality of
high stiffness tips with a layer supporting the tips in
predetermined spaced relation and adhering the tips to a vehicle
surface.
Inventors: |
Rawlings; Diane C.;
(Bellevue, WA) ; Christensen; Stephen; (Sammamish,
WA) |
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Applicant: |
Name |
City |
State |
Country |
Type |
The Boeing Company |
Chicago |
IL |
US |
|
|
Assignee: |
The Boeing Company
Chicago
IL
|
Prior
Publication: |
|
Document Identifier |
Publication Date |
|
US 20140332631 A1 |
November 13, 2014 |
|
|
Family ID: |
42353382 |
Appl. No.: |
14/070183 |
Filed: |
November 1, 2013 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
|
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12361918 |
Jan 29, 2009 |
8678316 |
|
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14070183 |
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Current U.S.
Class: |
1/1 |
Current CPC
Class: |
B32B 27/40 20130101;
B64C 1/38 20130101; B32B 27/38 20130101; B64C 21/10 20130101; Y10T
428/24355 20150115; B32B 15/20 20130101; B32B 27/288 20130101; Y02T
50/10 20130101; Y02T 50/166 20130101; B32B 27/34 20130101; F15D
1/0035 20130101; B32B 15/08 20130101; B32B 2605/18 20130101; Y10T
428/24612 20150115; B32B 27/283 20130101; B32B 2307/50 20130101;
B32B 7/12 20130101; B32B 25/08 20130101; B32B 2250/02 20130101;
B32B 3/08 20130101; B64C 2230/26 20130101; B32B 2307/702 20130101;
B32B 3/30 20130101; B32B 2307/416 20130101; F15D 1/004
20130101 |
International
Class: |
B64C 21/10 20060101
B64C021/10; B32B 15/08 20060101 B32B015/08; B32B 3/30 20060101
B32B003/30; F15D 1/00 20060101 F15D001/00; B64C 1/38 20060101
B64C001/38 |
Claims
1. An array of riblets comprising: a plurality of amorphous metal
tips having a dimension perpendicular to a vehicle surface of
approximately 0.002 inch and moduli of elasticity in a range of
about 10-30.times.106 lb/in2; a polymer layer supporting engaging
said amorphous metal tips in predetermined spaced relation, said
layer adhering to a the vehicle surface.
2. The array of riblets as defined in claim 1 wherein the amorphous
metal tips are formed from material selected from the set of an
alloy of Zr: 52.5 Ti: 5 Cu: 17.9 Ni: 14.6 Al: 10) or an alloy of
Zr: 58.5 Cu: 15.6 Ni: 12.8 Al: 10.3 Nb: 2.8.
3. The array of riblets as defined in claim 1 wherein a surface
layer of amorphous metal is continuously cast with the tips.
4. The array of riblets as defined in claim 3 further wherein the
polymer layer is deposited on the surface layer opposite the
tips.
5. The array of riblets as defined in claim 4 further comprising an
adhesive layer deposited on the polymer layer to form a multilayer
applique, said adhesive layer adhering the applique to the vehicle
surface.
6. The array of riblets as defined in claim 1 wherein each tip is
segmented in the flow direction.
7. The array of riblets as defined in claim 1 wherein each tip is
highly reflective providing a decorative feature on the vehicle
surface.
8. An array of riblets comprising: a plurality of amorphous metal
tips, each tip incorporating a base extending therefrom; an
elastomeric layer engaging the amorphous metal tips and supporting
said amorphous metal tips in predetermined spaced relation with the
base of each tip embedded in the elastomeric layer.
9. The array of riblets as defined in claim 6 further comprising an
adhesive layer deposited on the elastomeric layer to form a
multilayer applique, said adhesive layer adhering the multilayer
applique to the vehicle surface.
10. An aircraft structure comprising: an array of aerodynamic
riblets having a plurality of amorphous metal tips formed from
material selected from the set of Vitreloey 105 (Zr: 52.5 Ti: 5 Cu:
17.9 Ni: 14.6 Al: 10) or Vitreloy 106a (Zr: 58.5 Cu: 15.6 Ni: 12.8
Al: 10.3 Nb: 2.8) and highly reflective for a decorative feature,
each tip having a base and each tip segmented in the flow
direction; an elastomeric layer supporting said amorphous metal
tips in predetermined spaced relation, the base of each tip
embedded in the elastomeric layer; a preformed applique comprising
a metallic layer, a polymer support layer and an adhesive layer
deposited on the elastomeric layer opposite the tips to form a
multilayer applique said adhesive layer adhering the multilayer
applique to a surface of the aircraft.
11. A method for fabricating an array of riblets comprising:
forming a master tool having protuberances corresponding to a
desired riblet array: forming a complementary tool from the master
tool; casting a plurality of amorphous metal tips in the
complimentary tool; removing the cast amorphous metal tips from the
complementary tool; and, adhering the cast amorphous metal tips to
a surface.
12. The method of claim 11 further comprising: integrally casting
an amorphous metal surface layer intermediate the amorphous metal
tips.
13. The method of claim 12 further comprising: depositing a polymer
layer on the surface layer opposite the tips and depositing and
adhesive layer on the polymer layer.
14. The method of claim 11 further comprising: applying resist to
the complementary tool for segregating the amorphous metal tips;
and removing the resist subsequent to casting the amorphous metal
tips.
15. The method of claim 14 further comprising: casting an
elastomeric layer engaging the amorphous metal tips; and applying a
preformed applique to the elastomeric layer to form a riblet array
applique.
16. The method of claim 11 wherein the step of casting the
plurality of amorphous metal tips includes casting of a plurality
of tips and an intermediate surface layer as a cladding and further
comprising casting an elastomeric layer to the cladding.
17. The method of claim 11 wherein the step of casting the
plurality of amorphous metal tips comprises melt casting the
amorphous metal tips on the complementary tool.
18. A method for fabricating an array of aerodynamic riblets
comprising: forming a master tool having protuberances
corresponding to a desired riblet array: forming a complementary
tool from the master tool; casting an amorphous metal cladding in
the complimentary tool; casting a polymer layer of tip cores and
support layer forming a multilayer array of high stiffness riblets;
adhering the multilayer array of high stiffness riblets to an
aerodynamic surface; and, removing the complimentary tool from the
riblet array.
19. The method of claim 18 wherein the complimentary tool is formed
from silicon and the step of removing the complimentary tool
comprises stripping the silicon tool from the riblet array.
20. The method of claim 18 wherein the complimentary tool is formed
from a soluble polymer and the step of removing the complimentary
tool comprises dissolving the polymer tool from the riblet
array.
21. A method for fabricating an array of aerodynamic riblets for an
aircraft aerodynamic surface comprising: forming a master tool
having protuberances corresponding to a desired riblet array:
forming a complementary tool from the master tool; casting a core
layer having plurality of tip cores and a support layer in the
complimentary tool, said core layer selected from the set of a
polymer, selected from the subset of thermoplastic polyurethanes,
Polyetheretherkeytone (PEEK), Poloyetherkeytonekeytone (PEKK) or
polyamide, an elastomeric, selected from the subset of polyurethane
elastomers, polysulfide elastomers, epoxy-based elastomers,
silicones, fluoroelastomers, fluorosilicone elastomers,
Ethylene-Propylene-Diene Monomer (EPDM) elastomers, and polyhedral
oligosilsesquioxane (POSS)-modified polyurethane, or a shape memory
alloy (SMA), selected from the subset of
copper-zinc-aluminum-nickel, copper-aluminum-nickel,
nickel-titanium (NiTi) and pseudo-elastic beta titanium alloys;
removing the cast core layer from the complementary tool;
depositing an amorphous metal cladding over the cast core layer
forming an array of high stiffness riblets; depositing an adhesive
layer on the core layer opposite the tips to form a multilayer
applique and, adhering the multilayer applique to an aerodynamic
surface of an aircraft.
Description
REFERENCE TO RELATED APPLICATIONS
[0001] This application is a continuation of application Ser. No.
12/361,918 filed on Jan. 29, 2009 and is copending with U.S. patent
application Ser. No. 12/361,840 filed Jan. 29, 2009 entitled Rigid
Tipped Riblets and U.S. patent application Ser. No. 12/361,882
filed Jan. 29, 2009 entitled Shape Memory Riblets, all having a
common assignee with the present application, the disclosures of
which are incorporated herein by reference.
BACKGROUND INFORMATION
[0002] 1. Field
[0003] Embodiments of the disclosure relate generally to the field
of surface geometries for aerodynamic improvements to aircraft or
surfaces having a flow interface and more particularly to
embodiments and fabrication methods for use of amorphous metal
alloys to form aerodynamic riblets or other high-aspect-ratio
surface microstructures requiring high durability.
[0004] 2. Background
[0005] Increasing fuel efficiency in modern aircraft is being
accomplished through improvement in aerodynamic performance and
reduction of structural weight. Recent advances in the use of
microstructures such as riblets on aerodynamic surfaces have shown
significant promise in reducing drag to assist in reducing fuel
usage. Riblets have various forms but advantageous embodiments may
be ridge-like structures that minimize drag on the surface of an
aircraft. Riblets may be used in areas of a surface of an aircraft
where turbulent regions may be present. Riblets may limit
circulation causing a breakup of large scale vortices in these
turbulent regions near the surface in the boundary layer to reduce
drag.
[0006] In certain tested applications riblets have been pyramidal
or inverted V shaped ridges spaced on the aerodynamic surface to
extend along the surface in the direction of fluid flow. Riblet
structures have typically employed polymeric materials, typically
thermoplastics. However in service use such as on an aircraft
aerodynamic surface, polymers are relatively soft thus reducing the
durability of the surface. Existing solutions with polymeric tips
may readily deform hundreds of percent with fingernail pressure and
may be unrecoverable. Such structures may be undesirable in normal
service use on an aircraft or other vehicle. Additionally aircraft
surfaces are typically required to withstand interactions with
various chemicals including Skydrol.RTM., a hydraulic fluid
produced by Solutia, Inc. In certain applications elastomers that
resist or recover from severe deformation created at the tip may be
employed to form the riblets. However, many elastomers and other
polymers are not compatible with Skydrol.RTM. or other aircraft
fluids or solvents.
[0007] The practicality of riblets for commercial aircraft use
would therefore be significantly enhanced with a riblet structure
providing increased durability and aircraft fluids
compatibility.
SUMMARY
[0008] Exemplary embodiments provide a multilayer construction
having a first layer composed of a material with riblets, the first
layer material exhibiting a first characteristic of having high
stiffness and a second layer composed of a second material
exhibiting a second characteristic with capability for adherence to
a surface. The multilayer construction is employed in exemplary
embodiments wherein the riblets are implemented on a vehicle, the
riblets having long-term durability due to the properties of the
first layer.
[0009] In various embodiments, an array of aerodynamic riblets is
created by a plurality of high stiffness tips with a layer
supporting the tips in predetermined spaced relation and adhering
the tips to a vehicle surface. In exemplary embodiments, the high
stiffness tips are formed from material selected from the set of
nickel, chromium, metal alloy, glass, ceramic, silicon carbide and
silicon nitride. Additionally, the supporting layer may be
continuously cast with the tips as a surface layer. Alternatively,
a polymer support layer is deposited on the surface layer opposite
the tips. An adhesive layer deposited on the polymer support layer
forms a multilayer applique, and provides the capability for
adhering the applique to the vehicle surface.
[0010] In another exemplary embodiment, the supporting layer is an
elastomeric layer engaging the tips and a metal foil and a polymer
layer are provided intermediate the elastomeric layer and the
adhesive layer. The metal foil, polymer layer and adhesive layer
may be provided as a preformed applique. For exemplary embodiments
using the elastomeric layer, the tips each incorporate a base and
each base may be embedded in the elastomeric layer.
[0011] For greater flexibility in certain applications, each tip is
segmented in the flow direction.
[0012] An embodiment for an aircraft structure employs an array of
aerodynamic riblets having a plurality of amorphous metal tips
formed from material selected from the set of Vitreloey 105 (Zr:
52.5 Ti: 5 Cu: 17.9 Ni: 14.6 Al: 10) or Vitreloy 106a (Zr: 58.5 Cu:
15.6 Ni: 12.8 Al: 10.3 Nb: 2.8). The amorphous metal tips are
highly reflective for a decorative feature. Each tip includes a
base and each tip is segmented in the flow direction. An
elastomeric layer supports said amorphous metal tips in
predetermined spaced relation with the base of each tip embedded in
the elastomeric layer. A preformed applique which incorporates a
metallic layer, a polymer support layer and an adhesive layer is
deposited on the elastomeric layer opposite the tips to form a
multilayer applique. The adhesive layer adheres the multilayer
applique to a surface of the aircraft.
[0013] The embodiments disclosed are fabricated in an exemplary
method by forming a master tool having protuberances corresponding
to a desired riblet array and forming a complementary tool from the
master tool. A plurality of high stiffness tips is then cast in the
master tool using electroforming or other desirable deposition
technique. The cast tips are then removed from the complementary
tool and adhered to an aerodynamic surface.
[0014] In exemplary aspects of the method, resist is applied to the
complementary tool for a segregating the high stiffness tips and
removed subsequent to casting the high stiffness tips. An
elastomeric layer is the cast engaging the high stiffness tips and
a multilayer applique is applied to the elastomeric layer to form a
riblet array applique.
[0015] In exemplary embodiments of the method, the multilayer
applique comprises a metal foil, a polymer support layer and an
adhesive layer. An adhesive liner and masking may be employed for
handling. The riblet array may then be adhered to the aerodynamic
service by removing the adhesive liner and applying the riblet
array applique to the aerodynamic surface and removing the
masking.
[0016] In an alternative method, casting the plurality of high
stiffness tips includes melt casting of the plurality of tips and
an intermediate surface layer as a cladding. An elastomeric layer
is then cast to the cladding.
[0017] In yet another alternative method, fabricating an array of
aerodynamic riblets is accomplished by forming a master tool having
protuberances corresponding to a desired riblet array and then
forming a complementary tool from the master tool. An amorphous
metal cladding is then cast in the complimentary tool and a polymer
layer of tip cores and support layer is cast into the cladding
forming a multi layer array of high stiffness riblets. The
multilayer array of high stiffness riblet array to an aerodynamic
surface and the complimentary tool is then removed from the riblet
array.
[0018] In one aspect of the method embodiment, the complimentary
tool is formed from silicon and removing the complimentary tool is
accomplished by stripping the silicon tool from the riblet
array.
[0019] In another aspect of the method embodiment, the
complimentary tool is formed from a soluble polymer and removing
the complimentary tool is accomplished by dissolving the polymer
tool from the riblet array.
[0020] A method for fabricating an array of aerodynamic riblets for
an aircraft surface is accomplished by forming a master tool having
protuberances corresponding to a desired riblet array and forming a
complementary tool from the master tool. A core layer having
plurality of tip cores and a support layer is then cast in the
complimentary tool. The core layer is selected from the set of a
polymer, selected from the subset of thermoplastic polyurethanes,
PEEK, PEKK or polyamide, an elastomeric, selected from the subset
of polyurethane elastomers, polysulfide elastomers, epoxy-based
elastomers, silicones, fluoroelastomers, fluorosilicone elastomers,
Ethylene-Propylene-Diene Monomer (EPDM) elastomers, and polyhedral
oligosilsesquioxane (POSS)-modified polyurethane, or a shape memory
alloy (SMA), selected from the subset of
copper-zinc-aluminum-nickel, copper-aluminum-nickel,
nickel-titanium (NiTi) and pseudo-elastic beta titanium alloys. The
cast core layer is removed from the complementary tool. An
amorphous metal cladding is deposited over the cast core layer
forming an array of high stiffness riblets. An adhesive layer is
then deposited on the core layer opposite the tips to form a
multilayer applique. The multilayer applique is then adhered to an
aerodynamic surface of an aircraft using the adhesive layer.
BRIEF DESCRIPTION OF THE DRAWINGS
[0021] The features and advantages of embodiments disclosed herein
will be better understood by reference to the following detailed
description when considered in connection with the accompanying
drawings wherein:
[0022] FIG. 1 is an isometric view of a portion of an aerodynamic
surface such as a wing or fuselage skin showing exemplary riblets
extending in the flow direction;
[0023] FIG. 2A is a lateral section view perpendicular to the flow
direction of a first embodiment for high stiffness tipped
riblets;
[0024] FIG. 2B is a lateral section view of a modification of the
embodiment of FIG. 2A with an additional support layer;
[0025] FIG. 2C is a lateral section view of a modification of the
embodiment of FIG. 2A with high stiffness cladding over an
elastomer core;
[0026] FIG. 2D is a lateral section view of a modification of the
embodiment of FIG. 2A without an adhesive layer for direct
thermoplastic boding;
[0027] FIG. 2E is a lateral section view of an embodiment including
a multilayer structure incorporating a metallic layer.
[0028] FIG. 3 is a lateral section view of a second embodiment for
high stiffness tipped riblets with structural separation of the
riblets perpendicular to the flow path;
[0029] FIG. 4 is a lateral section view of a third embodiment for
high stiffness tipped riblets with reduced cross-section and with
separation perpendicular to the flow direction;
[0030] FIG. 5A is a top view of a portion of an aerodynamic surface
employing riblets of the first embodiment as shown in FIG. 2B;
[0031] FIG. 5B is a section view comparable to FIG. 2B for
reference with the features of FIG. 5A;
[0032] FIG. 6A is a top view of a portion of an aerodynamic surface
employing riblets of the second embodiment shown in FIG. 3 with
additional longitudinal separation of riblet sections;
[0033] FIG. 6B is a section view comparable to FIG. 3 for reference
with the features of FIG. 6A;
[0034] FIG. 7 is a flow diagram of processing steps for an
exemplary method of fabrication of amorphous metal riblets of the
first embodiment;
[0035] FIG. 8 is a flow diagram of processing steps for an
exemplary method of fabrication of amorphous metal riblets of the
second embodiment;
[0036] FIG. 9A is a flow diagram of processing steps for an
exemplary method of fabrication of amorphous metal riblets of a
third embodiment;
[0037] FIG. 9B is a flow diagram of processing steps for an
exemplary method of fabrication of amorphous metal riblets of a
forth embodiment;
[0038] FIG. 10 is a flow diagram describing use of the amorphous
metal riblets embodiments disclosed herein in the context of an
aircraft manufacturing and service method; and
[0039] FIG. 11 is a block diagram representing an aircraft
employing the amorphous metal riblets with embodiments as disclosed
herein.
DETAILED DESCRIPTION
[0040] The embodiments disclosed herein provide riblets constructed
with high stiffness materials that may be impacted by ground
support equipment or environmental hazards such as hail without
permanent deformation/damage. As used herein, high stiffness refers
to materials having moduli of elasticity in a range of about
10-30.times.10.sup.6 lb/in.sup.2 and preferably in the range of
about 10-20.times.10.sup.6 lb/in.sup.2 with typical examples being
the first transition metals of the first row in the periodic table
and alloys thereof. Deformation response of these stiff materials
may be somewhat ductile having a non-linear response in the elastic
region. These embodiments also allow a design change in riblets
providing the capability for them to be thinner and more
aerodynamically efficient. Amorphous metals may also be highly
reflective in the visible spectrum (a characteristic of amorphous
metals) enhancing the color/decorative features of the riblet
surface with a highly shiny appearance. Further, environmental
enhancements such as corrosion resistance and ice formation
prevention or reduction may be provided by an amorphous metal
cladding.
[0041] An exemplary embodiment of amorphous metal riblets, having a
structure as will be described in greater detail subsequently, is
shown as a portion of an aerodynamic surface for an aircraft in
FIG. 1. The aircraft 110 employs a structure with a surface 111,
shown enlarged, having multiple substantially parallel riblets 112
arranged parallel to the flow direction as represented by arrows
114. For the exemplary embodiment shown, the dimension 116
perpendicular to the surface 111 is approximately 0.002 inch while
the spacing 118 between the riblets is approximately 0.003 inch as
shown for example in FIGS. 2A and 2B. Spacing may vary depending on
the fluid dynamic properties of the air, water or other fluid for
which the application of riblets is employed. The aerodynamic
surface is typically, without limitation, curved and may be a
portion of a wing, an engine nacelle, a control surface, a fuselage
or other suitable surface. Therefore flexibility and conformability
of the riblets and any structure supporting and affixing the
riblets to the surface may be required. While described herein with
respect to an aircraft aerodynamic surface the embodiments
disclosed herein are equally applicable for drag reduction on
surfaces of other aerospace vehicles such as, without limitation,
missiles or rockets and other vehicles such as cars, trucks, buses
and trains moving in a gaseous fluid, commonly air, or on boats,
submarines, hydrofoils, fluid flow conduits or other surfaces
exposed to liquid fluid flow.
[0042] The embodiments disclosed herein recognize and provide the
capability for riblets that may resist various impacts and/or other
forces that may reduce riblet durability. Further, certain of the
different advantageous embodiments provide a multi-layer structure
that may have a support layer and a plurality of riblet tips
located on or extending from the support layer. The tips which form
the riblets may be fabricated, for example without limitation, by
casting amorphous metal alloys such as Vitreloey 105 (Zr: 52.5 Ti:
5 Cu: 17.9 Ni: 14.6 Al: 10) or Vitreloy 106a (Zr: 58.5 Cu: 15.6 Ni:
12.8 Al: 10.3 Nb: 2.8), which are well known for their moldability,
stiffness, inertness, and shiny surface. The cast surfaces could be
highly reflective in the visible spectrum (due to this
characteristic of amorphous metals) providing or enhancing a
color/decorative feature for a vehicle by addition of the riblet
surface. The materials of the multilayer structure are flexible and
may be formed as an applique separately or in combination with the
riblet tips for fastening to a surface to improve aerodynamics of a
vehicle such as an aircraft.
[0043] A first embodiment for amorphous metal riblets 112 is shown
in FIG. 2A. Individual tips 202 of the riblets protrude from a
surface layer 204 to provide a first layer 201 of the multilayer
construction. The protruding riblet tips 202 and continuous surface
layer 204 are formed by casting or deposition of an amorphous metal
layer or foil, as will be described in greater detail subsequently,
of the amorphous metal material chosen providing a first
characteristic of durability, environmental protection and/or
highly reflective appearance to additionally provide a decorative
feature. For the embodiment shown in FIG. 2A a second layer 203
created by an adhesive layer 206 is deposited on the surface layer
204. Exemplary adhesives for use in various embodiment may include,
without limitation, acrylic pressure sensitive adhesive, sylilated
polyurethane pressure sensitive adhesive; thermoplastic adhesive;
heat-reactive adhesive or epoxy adhesive. In alternative
embodiments, a supporting polymer layer 208 engages the surface
layer 204 intermediate the surface layer and adhesive layer 206 as
shown in FIG. 2B as a portion of the second layer. The supporting
polymer layer 208 may be a polymer film or other suitable material.
In certain embodiments polyetheretherketone (PEEK) is employed as
the film. The polymer, adhesive and/or other elements in the second
layer provide a second characteristic of resilience and the ability
to adhere to the surface.
[0044] FIG. 2C is an additional alternative embodiment wherein the
amorphous metal material is employed as a contoured surface
cladding 209 forming the tips 202' and surface layer 204'. A
polymer or elastomeric layer 210 is cast into the cladding 209 or
conversely the cladding 209 is cast over the elastomeric layer 210
to provide both a support layer 208' and light weight cores 212 for
the tips. Exemplary elastomers used in exemplary embodiments may
be, without limitation, polyurethane elastomers, polysulfide
elastomers, epoxy-based elastomers, silicones, fluoroelastomers,
fluorosilicone elastomers, Ethylene-Propylene-Diene Monomer (EPDM)
elastomers, or other polymers with lower strain to yield, for
example thermoplastic polyurethanes, PEEK, Polyetherketoneketone
(PEKK) or polyamide. This alternative embodiment may allow weight
reduction and flexibility of the structure may be further enhanced.
Additionally, a shape memory elastomeric material may be employed
for enhancing damage resistance and shape recovery.
[0045] In the form shown in FIG. 2A, 2B or 2C, the embodiment may
fabricated as an applique 211 which can then be adhered to the
aerodynamic surface using the adhesive layer 206.
[0046] In alternative embodiments, the surface layer 210' may be
directly adhered to or deposited on the aerodynamic surface 111.
FIG. 2D demonstrates an embodiment similar to that described with
respect to FIG. 2C however, no adhesive layer is employed.
Elastomeric layer 210' is a thermoplastic cast into the amorphous
metal cladding which allows direct bonding to the aircraft surface
with application of heat.
[0047] FIG. 2E demonstrates yet another embodiment wherein a
multilayer structure incorporating a metallic layer 220 such as
aluminum foil, a polymer layer 222 such as PEEK and an adhesive
layer 224 are adhered to support layer 210. The foil, polymer and
adhesive multilayer structure may be comparable to a current
lightning strike applique (LSA) 221 employed for composite aircraft
structural surfaces. A metal mesh or screen may be employed instead
of foil in alternative embodiments.
[0048] Another embodiment for amorphous metal riblets 112 is shown
in FIG. 3. With multiply curved surfaces, it may be desirable in
the first layer 301 for the individual riblet tips 302 to be
separated from each other substantially perpendicular to the flow
direction 114 for greater lateral flexibility. For the embodiment
shown, individual tips 302 protrude from an elastomeric layer 304.
Tips 302 have an internal angle 303 of approximately 30.degree. for
the exemplary embodiment of FIG. 3. A base 306 expands from each
tip 302. In certain embodiments the elastomeric layer 304 surrounds
the base 306 to provide greater structural continuity. In
alternative embodiments a bottom face 308 of the base 306 adheres
directly to the exposed surface of the elastomeric layer 304.
[0049] The second layer 303 is created by a multilayer structure,
which may be a preformed applique, incorporating a screen and/or
foil metallic layer 310 such as aluminum, a polymer layer 312 such
as PEEK and an adhesive layer 314 supports the elastomeric layer
304. As in the embodiment described with respect to FIG. 2E, the
aluminum layer provides a conducting material for lightning strike
protection in an exemplary aircraft usage of the embodiment.
[0050] The elastomer layer 304 supporting the amorphous metal
riblet tips 302 provides additional elastic sideways deformation
and recovery for the tips 302 when lateral forces are applied
thereby further enhancing the durability of the high stiffness
riblet tips. Additionally, the flexible elastomeric layer 304
allows greater ability to conform to complex shapes.
[0051] FIG. 4 demonstrates a third embodiment for the amorphous
metal riblets 112 which takes advantage of the structural
capability provided by the material from which the riblets are
formed to allow a sharper profile of tips 402. For the embodiment
shown in each of the tips 402 extends from a base 404 supported in
an elastomer layer 406. As with the embodiment described with
respect to FIG. 3 the base 404 of each tip 402 is surrounded by the
elastomer to structurally retain the base within the elastomer
layer 406. In alternative embodiments the extended bottom surface
408 of the base may be adhered to the surface of the elastomer
layer 406. The embodiment of FIG. 4 also employs riblets separated
perpendicular to the flow direction as in the embodiment of FIG. 3.
However, alternative embodiments a continuous surface layer from
which the tips extend as disclosed for the embodiment described
with respect to FIG. 1 may be employed.
[0052] As also disclosed in FIG. 4 the embodiment employs a
supporting polymer layer 410 on which the elastomer layer 406 is
adhered or deposited. An adhesive layer 412 extends from the
polymer layer 410 opposite the elastomer layer 406 forming a
multilayer applique 414.
[0053] FIG. 5A shows a top view of the embodiment as disclosed in
FIG. 2B. The riblets 112 formed by the tips 202 expand
longitudinally along surface layer 204 in the flow direction 114.
The thin surface layer 204 provides for flexibility in adhering to
curvature having tangents as represented by arrow 115 perpendicular
to the riblets. The amorphous metal materials employed in the
riblet applique may have advantages in providing a highly shiny
surface for decorative application and providing improved
durability to underlying composite structures by means of absorbing
impact energies. Additionally, the amorphous metal foil or cladding
209 may provide resistance to electromagnetic effects which
composite structure alone may not provide thereby substituting for
or supplementing LSA foil appliques and similar materials.
[0054] However as previously described, the surfaces on which the
riblets 112 may be employed may have complex or multiple curvatures
requiring greater flexibility. The embodiments previously described
may therefore be adapted as shown in FIG. 6A wherein the individual
tips 402 as described with respect to FIG. 4 and shown in modified
form in FIG. 6B are separated perpendicular to the flow direction
by spacing 118 with bases 406 attached to or captured within an
elastomer layer 404. This provides even greater flexibility for
adhering to surfaces with curvatures having tangents perpendicular
to the riblets as represented by arrow 115. The scale of the
drawings herein based on the small riblet dimensions makes the
surfaces appear flat even though they may be curved in larger
scale. Additionally the individual riblet tips 402 incorporate
longitudinal separation using gaps 602 to segment the riblets 112
to provide greater flexibility for adhering to surfaces having
curvatures with tangents parallel to the riblets 112. For the
embodiment shown gaps 602 may be substantially evenly spaced in the
riblets 112 at substantially equal longitudinal distances 604. In
alternative embodiments spacing on individual riblets 112 and
between riblets 112 may be uneven and chosen in a predetermined
manner to accommodate the surface curvature as required. In the
embodiment shown in FIG. 6B, a metal foil layer 414 is shown for
lightning protection when non-metallic tips 402 are employed.
[0055] FIG. 7 is a flow diagram showing a first exemplary
manufacturing process for a riblet structure as defined in the
embodiment described with respect to FIG. 2A. In step 701 a master
tool or replication of a master tool 712 is created using, as an
example without limitation, diamond machining of a copper form as
the master tool on which an acrylate film is cured as the
replication and then stripped to define spaced protuberances 714
corresponding to the desired riblet dimensions. The tool 712 as
shown in FIG. 7 may be a section of a flat tool or a roller
employed for roll-to-roll web processing. In alternative
embodiments, a roller may be employed, for example a nickel tool
partially submerged in the plating bath and as the foil is
deposited onto the "master" roll it is released/pulled off of the
roller which causes the roll to rotate exposing a clean portion of
the roller to the electroforming bath. A complimentary tool 716 is
created in step 702 by impression, melt casting or electroforming
on the master tool 712, which provides grooves 718 corresponding to
the riblet shape. Spacing between the grooves provides a
substantially flat intermediate surface 720 corresponding to the
dimension 118 desired between the riblets 112. In a web processing
format, the complimentary tool 716 may be silicon and be retained
on the cast tips as a protective masking. In step 703 amorphous
metal tips 202 and surface layer 204 are cast, rolled or deposited
onto the complimentary tool 716 followed by thermal processing to
optimize the glass structure. In certain embodiments, a release
compound is applied to the complimentary tool to assist in removal
of the cast riblet tips 202 and surface layer 204 from the tool.
Adhesive layer 206 is then applied in step 704 to the surface layer
204 opposite the amorphous metal tips 202. The adhesive layer 206
may be combined with a polymer layer and supplied as a preformed
applique 824 as shown in FIG. 8 which is then joined with the cast
surface layer 202. A removable adhesive liner 722 for handling of
the completed multilayer applique 723 is added as also shown in
step 704. The multilayer applique 723 is then removed from the
complimentary tool 716, and masking 724 may be applied to the
riblet array to protect the tips 202 during handling as shown in
step 705 Application to the aircraft surface 726 is accomplished by
removal of the adhesive liner 722 followed by attachment of the
adhesive layer of the applique to aircraft surface 726 as shown in
step 706.
[0056] FIG. 8 is a flow diagram showing a manufacturing process for
a riblet structure as defined in the embodiment described with
respect to FIG. 3. In step 801 a web tool 812 is created as
previously described with respect to FIG. 7 to define spaced
protuberances 814 corresponding to the desired riblet dimensions.
The tool as shown in FIG. 8 may be a section of a flat tool or a
roll tool employed for web processing. A complimentary tool 816 is
created in step 802 by impression on the web tool 812 which
provides grooves 818 corresponding to a riblet shape. Spacing
between the grooves provides a substantially flat intermediate
surface 820 corresponding to the dimension 118 desired between the
riblets tips 302. Amorphous metal tips 302 are cast or deposited
onto the tool 816 in step 803 including an intermediate web 303
between the tips 302. In step 804 resist 822 is applied to the
bases 306 of the riblet tips 302 in the complimentary tool 816. The
cast amorphous metal including the web is etched to remove the web
and shape the bases 306 of the tips 302 and the resist is then
removed in step 805 providing the spaced riblets in the tool 816.
For the embodiment shown the bases 306 are placed into relief
extending from the tool by the etching around the resist. The
elastomer layer 304 is then cast over the riblet bases 306 in step
806. In alternative embodiments casting of the amorphous metal tips
302 provides a base flush with the flat surface 820 for direct
adherence to the elastomer surface as previously described with
respect to FIG. 3. For the exemplary process shown with respect to
FIG. 8 a preformed applique 824 comprising the multilayer structure
of a metallic layer 310 such as aluminum foil, a polymer layer 312
and adhesive layer 314 is adhered to the cast elastomer in step
807. A removable adhesive liner 826 for preservation of the
adhesive during further processing is shown. The multilayer
structure is then removed from the complimentary tool 816 creating
a multilayer riblet array applique 829 exposing the amorphous metal
tips 302. Masking 828 is applied over the tips 302 and elastomer
layer 304 to assist in handling during additional processing. The
masking in exemplary embodiments may be, without limitation, a
solution cast releasable polymer such as silicon or an adhesive
film such as Mylar.RTM. with a low tack acrylic adhesive applied
during roll processing. Alternatively, a water/fluid soluble
polymer may be employed to allow removal of the masking by
dissolving with water or other fluid after installation.
[0057] The completed multilayer riblet array applique 829 may then
be applied to an airplane surface 830 by removing the adhesive
liner and adhering the adhesive layer 314 to the surface 830 as
shown in step 808. The masking 828 is then removed from the tips
302 and elastomer layer 304 providing the completed the riblet
surface.
[0058] The amorphous metal materials employed for the tips as
described in the embodiments and fabrication processes herein
allows very fine tip structure having dimensions 307 of around 15
to 25 microns at the base with a dimension 309 the extreme end of
the tips typically on the order of 100 nanometers (0.1 micron).
Finer tip geometries may be obtained with tooling and release
process refinement. Even thought the tips are very sharp, the very
fine spacing of the tips avoids cuts in normal handling by
installation personnel.
[0059] FIG. 9A is a flow diagram showing a manufacturing process
for a riblet structure as defined in the embodiment described with
respect to FIG. 2A. In step 901 a master tool 912 is created using,
as previously described with respect to FIG. 7. The tool as shown
in FIG. 9A may be a section of a flat tool or a roller employed for
roll-to-roll web processing. For the embodiment shown in FIG. 9A
amorphous metal is employed for the tips 202' and surface layer
204'. A complimentary tool 916 is created in step 902 by impression
on the master tool 912 which provides grooves 918 corresponding to
the riblet shape. Spacing between the grooves provides a
substantially flat intermediate surface 920 corresponding to the
dimension 118 desired between the riblets tips 202'. In web
processing applications, complimentary tool 916 may be formed from
silicon or a water/fluid soluble polymer may be employed. The
complimentary tool 916 then forms a masking layer for protection of
the cast riblets tips prior to application of the riblet array to
the aircraft surface. In step 903 amorphous metal film or cladding
209 is cast, deposited or roll formed into the complimentary tool
to form amorphous metal tips 202' and surface layer 204' in step
911. In certain embodiments, a release compound is applied to the
complimentary tool to assist in removal of the cast riblets 202'
and surface layer 204' from the complimentary tool 916. Elastomeric
layer 210 is then cast into the cladding 209 to provide both a
support layer 208' and light weight cores 212 for the tips 202' in
step 904. Adhesive layer 206 is then applied in step 904 to the
support layer 208' opposite the tips 202' in step 905 to create a
multilayer applique 921. A removable adhesive liner 920 for
handling of the completed applique is added as also shown in step
905. Application to the aircraft surface is accomplished as shown
in step 906 by removal of the adhesive liner 920 followed by
attachment of the adhesive layer 206 of the multilayer applique 921
to aircraft surface 922 at which time the complimentary web tool
916 is stripped from the array of riblet tips 202' and surface
layer 204'. For the alternative water/fluid soluble polymer tool,
the tool is removed by dissolving with water or other fluid after
installation.
[0060] In an alternative method for hard tooling to avoid release
issues between the amorphous metal cladding and the tooling, a
process shown in FIG. 9B is employed to form the polymer or
elastomeric support layer using the tooling and then deposit the
cladding over the support layer. In step 931 a master tool 912 is
created using, as previously described with respect to FIG. 9A. The
tool 912 as shown in FIG. 9B may be a section of a flat tool or a
roller employed for roll-to-roll web processing. A complimentary
tool 916 is created in step 932 by impression on the master tool
912 which provides grooves 918 corresponding to the riblet shape.
Spacing between the grooves provides a substantially flat
intermediate surface 920 corresponding to the dimension 118 desired
between the riblets tips 202'. A core layer 210 is then cast into
the complimentary tool 916 to provide both a support layer 208' and
light weight cores 212 in step 933. In certain embodiments, a
release compound is applied to the complimentary tool to assist in
removal of the core layer 210 from the tool 916. Adhesive layer 206
is then applied in step 934 to the support layer 208' opposite the
elastomeric tips cores 212. A removable adhesive liner 916 for
handling of the completed applique is added as also shown in step
934. In step 935, which may be conducted prior to the addition of
the adhesive and liner, the core layer 210 is removed from the
complimentary tool 916 and an amorphous metal film or cladding 209
such as Vitreloey 105 (Zr: 52.5 Ti: 5 Cu: 17.9 Ni: 14.6 Al: 10) or
Vitreloy 106a (Zr: 58.5 Cu: 15.6 Ni: 12.8 Al: 10.3 Nb: 2.8) is
deposited by sputtering or alternative deposition technique onto
the core layer 210 to form an array of high stiffness riblet tips
202' and surface layer 204' creating a multilayer applique 921. In
various embodiments, the core layer 210 may be a polymer, for
example without limitation, thermoplastic polyurethanes, PEEK, PEKK
or polyamide, an elastomeric, which may or may not have shape
memory properties, for example without limitation polyurethane
elastomers, polysulfide elastomers, epoxy-based elastomers,
silicones, fluoroelastomers, fluorosilicone elastomers,
Ethylene-Propylene-Diene Monomer (EPDM) elastomers, and polyhedral
oligosilsesquioxane (POSS)-modified polyurethane, or a shape memory
alloy (SMA), for example without limitation,
copper-zinc-aluminum-nickel, copper-aluminum-nickel,
nickel-titanium (NiTi), pseudo-elastic beta titanium alloys.
Application to the aircraft surface 922 is accomplished as shown in
step 936 by removal of the adhesive liner 922 followed by
attachment of the adhesive layer 206 of the multilayer applique 921
to aircraft surface 922.
[0061] Referring more particularly to FIGS. 10 and 11, embodiments
of the high stiffness riblets disclosed herein and the methods for
their fabrication may be described in the context of an aircraft
manufacturing and service method 1000 as shown in FIG. 10 and an
aircraft 1102 as shown in FIG. 11. During pre-production, exemplary
method 1000 may include specification and design 1004 of the
aircraft, which may include the riblets, and material procurement
1006. During production, component and subassembly manufacturing
1008 and system integration 1010 of the aircraft takes place. The
riblet appliques and their manufacturing processes as described
herein may be accomplished as a portion of the production,
component and subassembly manufacturing step 1008 and/or as a
portion of the system integration 1010. Thereafter, the aircraft
may go through certification and delivery 1012 in order to be
placed in service 1014. While in service by a customer, the
aircraft 1002 is scheduled for routine maintenance and service 1016
(which may also include modification, reconfiguration,
refurbishment, and so on). The riblet appliques as described herein
may also be fabricated and applied as a portion of routine
maintenance and service.
[0062] Each of the processes of method 1000 may be performed or
carried out by a system integrator, a third party, and/or an
operator (e.g., a customer). For the purposes of this description,
a system integrator may include without limitation any number of
aircraft manufacturers and major-system subcontractors; a third
party may include without limitation any number of venders,
subcontractors, and suppliers; and an operator may be an airline,
leasing company, military entity, service organization, and so
on.
[0063] As shown in FIG. 11, the aircraft 1102 produced by exemplary
method 1000 may include an airframe 1118 having a surface 111, as
described with respect to FIG. 1, and a plurality of systems 1120
and an interior 1122. Examples of high-level systems 1120 include
one or more of a propulsion systems 1124, an electrical and
avionics system 1126, a hydraulic system 1128, and an environmental
system 1130. Any number of other systems may be included. The high
stiffness tipped riblets supported by the embodiments disclosed
herein may be a portion of the airframe, notably the finishing of
skin and exterior surfaces. Although an aerospace example is shown,
the principles of the disclosure herein may be applied to other
industries, such as the automotive industry and the marine/ship
industry.
[0064] Apparatus and methods embodied herein may be employed during
any one or more of the stages of the production and service method
1000. For example, components or subassemblies corresponding to
production process 1008 may be fabricated or manufactured in a
manner similar to components or subassemblies produced while the
aircraft 1102 is in service. Also, one or more apparatus
embodiments, method embodiments, or a combination thereof may be
utilized during the production stages 1008 and 1010, for example,
by substantially expediting assembly of or reducing the cost of an
aircraft 1102. Similarly, one or more of apparatus embodiments,
method embodiments, or a combination thereof may be utilized while
the aircraft 1102 is in service, for example and without
limitation, to maintenance and service 1016.
[0065] Having now described various embodiments in detail as
required by the patent statutes, those skilled in the art will
recognize modifications and substitutions to the specific
embodiments disclosed herein. Such modifications are within the
scope and intent of the present disclosure as defined in the
following claims.
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