EP4187000A1 - Komponentenverarbeitung - Google Patents

Komponentenverarbeitung Download PDF

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Publication number
EP4187000A1
EP4187000A1 EP21275169.7A EP21275169A EP4187000A1 EP 4187000 A1 EP4187000 A1 EP 4187000A1 EP 21275169 A EP21275169 A EP 21275169A EP 4187000 A1 EP4187000 A1 EP 4187000A1
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EP
European Patent Office
Prior art keywords
component
area
anodising
processing
coating composition
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Pending
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EP21275169.7A
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English (en)
French (fr)
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designation of the inventor has not yet been filed The
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BAE Systems PLC
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BAE Systems PLC
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Publication date
Application filed by BAE Systems PLC filed Critical BAE Systems PLC
Priority to EP21275169.7A priority Critical patent/EP4187000A1/de
Publication of EP4187000A1 publication Critical patent/EP4187000A1/de
Pending legal-status Critical Current

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    • C—CHEMISTRY; METALLURGY
    • C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
    • C25D—PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTION OF COATINGS; ELECTROFORMING; APPARATUS THEREFOR
    • C25D13/00—Electrophoretic coating characterised by the process
    • C25D13/04—Electrophoretic coating characterised by the process with organic material
    • C—CHEMISTRY; METALLURGY
    • C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
    • C25D—PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTION OF COATINGS; ELECTROFORMING; APPARATUS THEREFOR
    • C25D11/00—Electrolytic coating by surface reaction, i.e. forming conversion layers
    • C25D11/02—Anodisation
    • C25D11/022—Anodisation on selected surface areas

Definitions

  • the present invention relates to the processing of components.
  • Aircraft components may comprise distinct areas which are subjected to different processes.
  • One area of the component may be bonded to a separate sub structure, for example an internal frame and another area which is exposed to the environment, for example an outer surface of an aircraft part, may be painted with a coating compound.
  • components are anodised for two reasons; firstly, to enhance the adhesion of bonding primers and agents, and secondly, to provide an oxide protective layer to increase corrosion resistance of the component. Areas of the component which are to be exposed to the environment are then painted with a coating compound.
  • Anodising solutions which can provide both an enhanced bonding layer and corrosion resistance are typically hexavalent chromium based solutions, for example chromium trioxide (also known as chromium anhydride), and are compatible with existing aircraft paint systems however these anodising solutions are carcinogenic and are being phased out in many jurisdictions to comply with new health and safety legislation.
  • chromium trioxide also known as chromium anhydride
  • the masking and de-masking process is a time consuming task for skilled operators and can often lead to under masking the first area such that there is anodising overlap resulting in pitting of the component or worse, over masking the first area such that there are missing areas of anodising on the component thus said missing areas will corrode quicker in use.
  • the present inventors have realised that alternative anodising processes which do not use a chromic anodising solutions suffer from serious disadvantages such as an increase in process time (and therefore cost) due to the two stage anodising process and increased environmental waste from the resultant increase in masking consumables required during the process.
  • the chromate process is desirable due to its efficient nature requiring only a single anodising process using only one anodising solution which provides both an enhanced bonding layer and corrosion resistance without the need to remask the component or use a separate second anodising process and associated anodising solution.
  • the use of chromate is being phased out due to regulations of its use based on the toxicity and environmental impact of its use.
  • the present inventors have realised there is an increased chance of quality defects in a processed part due to the possibility of an operator failing to correctly mask, and thereby overlap the two stage anodising process, increasing the possibility of creating pitting on the component surface or leaving gaps in anodising on parts of the component which may lead to early corrosion.
  • the presence of defects may lead to rework of the component which involves having to strip the component back to the original surface and restart the entire process or even scrapping of the entire part.
  • the component may have to be replaced early in its operational service.
  • a chromate free method of processing a component comprising a first and second area, the method comprising: selectively depositing a curable anodising resistant coating composition onto the first area of the component; curing the anodising resistant coating composition to create a cured anodising resistant coating layer; anodising the component with an anodising composition to create an anodised layer on the second area, such that the cured anodising resistant coating layer provides a maskant preventing anodisation of the first area.
  • the process eliminates the need for a two stage anodising process. Therefore, the possibility of double anodising is mitigated thereby reducing significantly any chance of pitting as the cured anodising resistant coating layer acts as a maskant.
  • the cured anodising resistant coating layer provides a suitable corrosion resistance barrier on the first area of the component.
  • the component which comprises the first and second area, is subjected to the anodising process.
  • all areas which do not have the cured anodising resistant coating layer will be anodised. Therefore, the possibility of an area of the component not being subjected to anodising is mitigated. This significantly reduces the chance of a component being rejected for quality non-conformance as the entire area of the component, that is to say the first and second areas together, will either be coated in a cured anodising resistant coating layer (first area) or anodised (second area) therefore the component is entirely protected from corrosion.
  • the process also reduces waste, as masking consumables are reduced or entirely eliminated altogether.
  • the process requires less energy due to the elimination of the second stage anodising process.
  • the component may be made of a metal, metal alloy or composite component.
  • the component may be one used in a land, sea, space or air vehicle.
  • the component is an aerospace component.
  • the component may be an aircraft skin, panel or engine duct.
  • the component may be an internal component or a sub assembly, for example but not limited to, a spar, rib or bulkhead. More preferably, the component is a metal or composite aerospace component.
  • first area' and 'second area' have been used, these are considered non-limiting and merely indicate which area of the component is to be coated with an anodising resistant coating composition and which area is to be anodised.
  • the first and second area may not be merely limited to respective sides of a component, for example there may be a plurality of 'first' areas on a first side of a component.
  • the component may be of such a geometry that there are no defined 'sides', in such cases, the component surface may have a plurality of first and/or second areas.
  • the component may be an aluminium aircraft aileron skin comprising a first and second area such that in use, the first area is an outer skin of the aircraft, which will be exposed to the environment.
  • the second area is an inner surface of the aileron which is to be bonded to a substructure to form a sub assembly.
  • the anodising resistant coating composition is selectively deposited on to the first area of the component.
  • Such techniques may include painting using a brush, applicator, spraying, dipping, nozzle printing, electrostatic coating or electrophoretic deposition.
  • Processes may be manual or automated, in this document manual meaning by hand. Automated processes may be partly or fully automated, for example, by a cobot or robot.
  • an electrophoretic deposition process is used to selectively deposit an anodising resistant coating composition onto the first area of the component.
  • Non-conductive materials may be used providing they comprise some form of conductive element embedded within or located thereon, them, for example a metallic layer, metallic seed layer or an interwoven conductive material, for example within a composite.
  • a non conductive material for example a carbon fibre composite, which comprises a non-conductive binder matrix, may comprise an external conductive layer, for example, an aluminium layer.
  • Selective deposition may include depositing the anodising resistant coating composition onto a discreet region of a component, such as the first area, that is to say, without traditional masking techniques.
  • the anodising resistant coating composition may be selectively deposited by a printing process onto the first area of the component leaving the remainder of the component uncoated.
  • the component' first area may be partly dipped in an anodising resistant coating composition thereby leaving the undipped surface of the second area of the component uncoated.
  • selective deposition may be achieved through traditional masking techniques applied to mask the second area such that selective deposition is applied to only the first area of the component. The unmasked first area therefore receives a deposited layer of anodising resistant coating composition.
  • An electrophoretic deposition process yields a uniform, i.e. an even thickness of anodising resistant coating composition across the first area of the component.
  • the resultant thickness of the coating is in the range of from 1 to 500 microns, more preferably 10 to 100 microns, more preferably 10 to 50microns.
  • the anodising resistant coating composition may be an organic or inorganic composition.
  • the anodising resistant coating composition may comprise a film- forming resin.
  • film-forming resin refers to resins that can form a self-supporting continuous film on at least a horizontal surface of a substrate upon removal of any diluents or carriers present in the composition or upon curing at ambient or elevated temperature.
  • the anodising resistant coating composition may comprise a thermosetting film-forming resin, said resin may be cured or set irreversibly upon curing, for example by undergoing a process such as crosslinking.
  • anodising resistant coating composition may be an ionic electrodepositable composition, such as an anionic or cationic electrodepositable composition.
  • the ionic electrodepositable composition may be water dispersible polymers.
  • Examples of ionic electrodepositable composition may be base-solubilised, carboxylic acid containing polymers, neutralized interpolymers of hydroxyl-alkyl esters of unsatured carboxylic acids, unsaturated carboxylic acid and at least one other ethlenically unsaturated monomer, mixed esters of a resinous polyol as described in US3749657 incorporated herein by reference, phosphatised polyepoxide or phosphatised acrylic polymers.
  • the anodising resistant coating composition may be an epoxy or an epoxyurethane based composition.
  • the anodising resistant coating composition may be an anionic epoxy electrocoat primer based composition.
  • Aerocron TM 2100 anionic epoxy electrocoat primer as manufactured by PPG Industries Ohio Inc is particularly effective in providing an anodising resistant coating to the component.
  • the anodising resistant coating composition may comprise a curing agent.
  • the curing agent may be a blocked organic polyisocyanate or aminoplast.
  • the anodising resistant coating composition may comprise a filler or a plurality of fillers.
  • Such fillers may be dyes, pigments, stabilisers or a property inducing filler, for example a magnetic filler.
  • anodising resistant coating composition may be applied by the electrophoretic deposition process as per WO2013089903A1 by PPG Industries Ohio Inc, incorporated herein by reference.
  • the method may comprise the intermediate step of contacting the component with a pre-treatment solution before electrophoretic deposition.
  • the pre-treatment solution may comprise a group IIIB and/or IVB metal.
  • Such pre-treatment may provide a protective layer on the surface of the component.
  • the method may also comprise the intermediate step of contacting the component with an anionic or cationic resin-based post rinse composition comprising an anionic or cationic resin before electrophoretic deposition.
  • the addition of this step increases the 'throwpower' of the subsequently applied electrodeposition coating.
  • 'Throwpower' means the ability of the electrodeposited coating to be 'thrown' into component recesses and hard to reach geometries. An increased throwpower of the electrodeposited coating therefore means a more even coat thickness across the entire surface of the component thus there is provided a uniform finish on the part.
  • the component may be cured.
  • the curing process may take place in the presence of a catalyst, for example heat or UV.
  • a catalyst for example heat or UV.
  • the component is cured by heating at a temperature in the range of from 120°C to 250°C. More preferably, the component is cured at a temperature in the range of from 120°C to 190°C.
  • the curing time of the cure may be in the range of from 10 to 60 minutes.
  • the anodising composition may be any known suitable agent, and may be selected from an acid such as for example an acidic composition, one comprising phosphoric acid or sulphuric acid.
  • the anodising solution is sulphuric acid.
  • the cured anodising resistant coating layer prevents the first area of the component from being anodised as it is impermeable to anodisation, such that the underlying surface of the first area of the component does not form an oxide layer. Therefore, only the second area, which has no cured anodising resistant coating layer is subjected to anodisation to form an oxide layer thereon.
  • the method may also comprise the additional step of masking the second area of the component before depositing the anodising resistant coating composition onto the entire component.
  • the anodising resistant coating composition is cured.
  • the mask is then removed from the second area and subjected to anodising.
  • This additional step allows the entire component to be exposed to the electrophoretic deposition process and then removal of the mask on the second area to perform the anodising process, rather than selectively applying each process to the first and second area of the component respectively.
  • Such masking may be performed using 3M 425 aluminium foil tape.
  • the component that is to say the first and second areas, are both subjected to deposition with an anodising resistant coating composition; whereupon the second area which is to be anodised, has the anodising resistant coating composition removed or "stripped back" to the second area's original surface before undergoing an anodising process.
  • stripping back may be achieved with use of a solvent, physical abrasive or in any other way known by the skilled person. Where the second area is difficult to mask, or where there is only a small surface area of second area, it may be convenient to use the stripped back process.
  • the method may further comprise the step of applying a bonding primer to the second area of the component after anodising.
  • the bonding primer may be selected from a group comprising EC3900, BR127 or non chromate BR6747 as produced by Solvay Group ® .
  • the bonding primer is non-chromate BR6747 as this primer is REACH compliant.
  • the bonding primer may enhance the adhesion of a bonding layer or secondary paint layer onto the component.
  • the bonding primer may be applied to the second area of the component by manual painting, manual spraying, robotic spraying, dipping or electrostatic coating or in any other known way by the skilled person.
  • the method may comprise the additional step of bonding the second area of the component to a further component.
  • a further component may be another component as herein defined.
  • the further component may be bonded to a substructure, for example an aircraft rib or spar.
  • the bonding may include the use of adhesives, such as, for example Hysol TM as produced by Henkel ® .
  • the second area may be joined to another component by mechanical means, for example rivets, welds, and/or bolts.
  • the method comprises the additional step of applying an exterior coating composition to the first area of the component.
  • the exterior coating may be a final finish paint which in use, will be exposed to the outer environment.
  • the exterior coating composition may be an epoxy or epoxy polyurethane based composition.
  • the exterior coating composition may comprise more than one discreet layer of composition, for example the composition may be layered as; primer - intermediate layer - top coat as part of a paint system. This arrangement eases stripping of the top coat for repaint which may be especially useful on an aerospace component.
  • the exterior coating composition may comprise a filler or a plurality of fillers. Such fillers may be dyes, pigments, stabilisers or a property inducing filler, for example a magnetic filler.
  • the exterior coating is an epoxy polyurethane based composition.
  • the exterior coating may be applied directly to the cured anodising resistant coating layer.
  • a processed component comprising: a first area; and, a second area, wherein the first area comprises an anodising resistant coating composition and the second area comprises an anodised layer.
  • the first area may comprise an exterior coating composition deposited on the cured anodising resistant coating layer.
  • the second area may also comprise a bonding primer deposited on the surface of the anodised layer.
  • the processed component may be part of an aircraft, for example an aircraft panel.
  • a chromate free method of processing a component comprising:
  • Figure 1 is a process flow chart 100 showing certain steps of an example conventional process using a chromium based anodising process of the prior art for processing an aircraft part.
  • a component is first cleaned and rinsed prior to processing.
  • a deoxidising pre-treatment process will occur at step 104 prior to any anodising process to remove any existing oxide layer on the component surface.
  • nitric and sulphuric acids may be applied to the component to deoxidise the surface in a redox reaction.
  • the component is rinsed and dried to remove any remaining deoxidising substance form the surface of the component.
  • the component is anodised in a chromic acid anodising solution, for example chromium trioxide.
  • a chromic acid anodising solution for example chromium trioxide.
  • the component may be dipped in a bath comprising the solution. Typically, this step of anodising the component may take about 1 hour.
  • the anodised component is rinsed to remove any a residual anodising solution.
  • Solvents or other cleaning chemicals may be used to remove remaining anodising solution and the component dried.
  • the component is masked for painting such that the area to be exposed to the environment is left unmasked.
  • Such masking may be performed using 3M 425 aluminium foil tape.
  • such masking processes including cutting, making tape to a desired shape and applying the cut masking tape to the component may take about 3 hours.
  • the component is painted.
  • paint is only applied to unmasked areas of the component. Painting is typically carried out by spray techniques by a skilled operator taking care to overlap the spray sufficiently on the component without inducing dripping or running of the paint which would otherwise spoil the surface of the finished component. Typically, this step of painting the component may take about 3 hours.
  • the paint is cured.
  • the paint may be cured in air at room temperature or by addition of a catalyst or heat process.
  • the component is de masked. Solvents or other cleaning chemicals may be used to remove any left over adhesive residue from the masking tape. Typically this stage may take about 1 hour.
  • Figure 2 is a process flow chart 200 showing certain steps of an example conventional process using an alternative to chromium based anodising processes of the prior art for processing an aircraft part using a two stage anodising process.
  • step 202 to 206 are as steps 102 to 106 of Figure 1 .
  • the component is masked such that a first area is exposed (unmasked) ready for a first anodising process, and a second area is a masked area ready to be anodised in the second stage of the process.
  • Preparation of the masking materials and application to the component is similar to step 112 and takes about three hours.
  • the component is anodised in a first anodising solution.
  • the first anodising solution anodises the first area, to provide an improved surface for acceptance of a bonding agent, for example an adhesive, to a further component, such as a sub structure, for example, an aircraft spar.
  • step 212 the second area of the component is demasked according to step 118 of Figure 1 .
  • the first area of the component is masked such that the first area of step 208 is now completely covered thereby exposing the second area to be anodised in the second stage of the process.
  • the component is anodised in a second anodising solution.
  • the second anodising solution is selected to provide enhanced corrosion resistance to the second area of the component which in use, will be exposed to the environment, for example, the outer surface of an aircraft skin.
  • the first area of the component is demasked according to step 118 of Figure 1 .
  • Steps 220 and 222 are as steps 114 and 116 of Figure 1 .
  • Figure 3 shows an exemplary process 300 according to the invention for processing a component, in particular an aircraft part.
  • the component is an aluminium aircraft aileron skin comprising a first and second area such that in use, the first area of the component will be will be exposed to the environment i.e., the outer skin of the aircraft, and the second area bonded to a substructure, for example an aircraft rib sub assembly.
  • the method comprises the steps of; 302 cleaning and rinsing and component.
  • the component is deoxidised with a sulphuric acid solution in order to strip the aluminium surface of the component from any existing oxide layer thereby ensuring consistent deposition of an oxide layer during the later anodising process.
  • the component is rinsed and dried with water.
  • the component is painted by selectively depositing an anodising resistant coating composition onto the first area of the component That is to say, the surface of the aluminium part to which the composition is applied will not react to form an oxide layer during the anodisation process.
  • the anodising resistant coating composition is an epoxy urethane based composition applied by manual spraying.
  • the component is cured under heat for 40 minutes at 150°C.
  • the component is anodised in a phosphoric acid bath for 1 hour.
  • Figure 4 shows an alternative exemplary process 400 according to the invention for processing a component using an electrophoretic deposition method.
  • the component is as Figure 3 .
  • the terms 'anionic' and 'cationic' are used, these are considered non limiting and any step comprising each term may be interchangeable providing subsequent steps are compatible.
  • the electrodepositable coating composition is cationic vice versa in order to provide electrostatic attraction between the component and the coating composition.
  • the component is cleaned and rinsed.
  • cleaning may be carried out using mild or strong alkaline cleaners such as Chemkleen 163, Chemkleen 177 and Chemkleen 490MX which are commercially available from PPG Industries Ohio Inc.
  • the cleaner may be removed from the component by a water based rinse.
  • the component is deoxidised using a sulphuric acid solution.
  • the component is cleaned with Chemkleen 163 before being rinsed under water.
  • the second area of the component is masked with 3M 425 aluminium foil tape such that only the first area of the component will receive a coating compound during the electrophoretic deposition process. Even when a masking step is incorporated into the process, the time taken to process the component is still less than the process of Figure 2 as only one masking operating takes place as per Figure 1 .
  • the component undergoes an electrophoretic pre rinse.
  • the entire component is washed with a pre-treatment aqueous solution comprising a group IIIB metal and an electropositive metal.
  • Said electropositive metal refers to metals that are more electropositive than the component to be processed. i.e. they are less easily oxidized than the component.
  • the group IIIB metal is yttrium and the electropositive metal is copper sulfate.
  • the pre-treatment metal may be present in the solution in the range of from 10ppm to 5000ppm.
  • the entire component undergoes a cationic resin based post rinse process using Nupal 510 R.
  • the first area of the component is coated with Aerocron TM 2100, an anodising resistant coating compound.
  • the resultant thickness of the coating is in the range of from 10 to 50 microns.
  • the specific voltages and amperes of the process will be determined by the skilled person according to the size, nature and complexity of the component and with regard to the specific coating composition being used including its conductivity and viscosity. As an example, a voltage applied in such process may be in the range of from 1 to 500 volts and a current in the range of from 10 to 160 amperes per square meter.
  • the component is cured under heat for 40 minutes at 150°C.
  • the component is de-masked.
  • a solvent may be used to remove any exist ant adhesive residue left from the masking tape.
  • the component is anodised.
  • the component is immersed in a sulphuric acid bath for 1 hour.
  • the cured coating composition provides an effective barrier to the acid, and prevents the formation of an oxide layer on the first area of the component.
  • the cured coating composition effectively acting as a maskant against anodising.
  • the second area only is anodised. Even when a masking step is incorporated into the process, the time taken to process the component is still less than the process of Figure 2 as only one masking operating takes place as per Figure 1 .
  • Figure 5 shows a cross sectional view of a part processed aircraft part 500.
  • an aluminium aircraft component 502 comprising a first area 504 and a second area 506.
  • View A of Figure 5 shows a cross sectional view of the component showing discreet layers deposited on the component surface (not to scale).
  • the component has undergone selective deposition of an anodising resistant coating composition and anodisation such that the first area 504 comprises a cured layer of cured epoxy urethane 508 and the second area 506 comprises an oxide layer 510 after anodisation.
  • Figure 6 shows a cross sectional view of a fully processed aircraft part 600.
  • an aluminium component 602 comprising a first area 604 and a second area 606.
  • View B of Figure 6 shows a cross sectional view of the component showing discreet layers deposited on the component surface (not to scale).
  • the component has undergone selective deposition of an anodising resistant coating composition and anodisation such that the first area 604 comprises a cured layer of cured epoxy urethane 608 and the second area 606 comprises an oxide layer 610 after anodisation.
  • the first area 604 also comprises an epoxy based exterior coating composition comprising a pigment deposited on the surface of the cured epoxy urethane layer 608 such that the cured layer 608 effectively acts as a primer layer.
  • the second area 606 further comprises a bonding primer in the form of Hysol TM deposited on the surface of the oxide layer 610.
  • Figure 7 shows a fully processed aircraft part 700 in a final use location on an aircraft substructure.
  • the component 702 is an aluminium aircraft skin comprising a first area 704 on a first side of the skin and a second area 706 on a second side of the skin, wherein the first area 704 comprises a layer of cured epoxy urethane 708 and a further layer of an epoxy based exterior coating composition 712.
  • the second area 706 comprises an oxide layer 710, a bonding primer 714 deposited thereon wherein the component is joined to an adjacent component 716 by means of an adhesive.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Electrochemistry (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Application Of Or Painting With Fluid Materials (AREA)
EP21275169.7A 2021-11-25 2021-11-25 Komponentenverarbeitung Pending EP4187000A1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP21275169.7A EP4187000A1 (de) 2021-11-25 2021-11-25 Komponentenverarbeitung

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Application Number Priority Date Filing Date Title
EP21275169.7A EP4187000A1 (de) 2021-11-25 2021-11-25 Komponentenverarbeitung

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EP4187000A1 true EP4187000A1 (de) 2023-05-31

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Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3749657A (en) 1972-01-04 1973-07-31 Ppg Industries Inc Treatment of electrodeposition rinse water
WO2013089903A1 (en) 2011-12-13 2013-06-20 Ppg Industries Ohio, Inc. Resin based post rinse for improved throwpower of electrodepositable coating compositions on pretreated metal substrates
US20130153428A1 (en) * 2011-12-20 2013-06-20 Apple Inc. Metal Surface and Process for Treating a Metal Surface
US20170226650A1 (en) * 2016-02-04 2017-08-10 Xiaojiang Zhang Metallic picture print with the use of differentially oxidized and/or nitridized layers, and method for making the same
US20170342587A1 (en) * 2014-12-17 2017-11-30 Bae Systems Plc Object processing by conversion coating
EP3399851A1 (de) * 2015-12-30 2018-11-07 BYD Company Limited Aluminiumlegierungsgehäuse und herstellungsverfahren dafür

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3749657A (en) 1972-01-04 1973-07-31 Ppg Industries Inc Treatment of electrodeposition rinse water
WO2013089903A1 (en) 2011-12-13 2013-06-20 Ppg Industries Ohio, Inc. Resin based post rinse for improved throwpower of electrodepositable coating compositions on pretreated metal substrates
US20130153428A1 (en) * 2011-12-20 2013-06-20 Apple Inc. Metal Surface and Process for Treating a Metal Surface
US20170342587A1 (en) * 2014-12-17 2017-11-30 Bae Systems Plc Object processing by conversion coating
EP3399851A1 (de) * 2015-12-30 2018-11-07 BYD Company Limited Aluminiumlegierungsgehäuse und herstellungsverfahren dafür
US20170226650A1 (en) * 2016-02-04 2017-08-10 Xiaojiang Zhang Metallic picture print with the use of differentially oxidized and/or nitridized layers, and method for making the same

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
KERN P ET AL: "New developments in through-mask electrochemical micromachining of titanium", JOURNAL OF MICROMECHANICS AND MICROENGINEERING, INSTITUTE OF PHYSICS PUBLISHING, BRISTOL, GB, vol. 17, no. 6, 1 June 2007 (2007-06-01), pages 1168 - 1177, XP020120121, ISSN: 0960-1317, DOI: 10.1088/0960-1317/17/6/010 *

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