EP3234231B1 - Objektverarbeitung durch konversionsbeschichtung - Google Patents

Objektverarbeitung durch konversionsbeschichtung Download PDF

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Publication number
EP3234231B1
EP3234231B1 EP15813487.4A EP15813487A EP3234231B1 EP 3234231 B1 EP3234231 B1 EP 3234231B1 EP 15813487 A EP15813487 A EP 15813487A EP 3234231 B1 EP3234231 B1 EP 3234231B1
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EP
European Patent Office
Prior art keywords
chromate conversion
conversion coating
aircraft part
onto
aircraft
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EP15813487.4A
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English (en)
French (fr)
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EP3234231B8 (de
EP3234231A1 (de
Inventor
Sam Oliver ASHWORTH
Craig BOWDEN
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BAE Systems PLC
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BAE Systems PLC
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Publication of EP3234231B1 publication Critical patent/EP3234231B1/de
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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
    • C25D11/00—Electrolytic coating by surface reaction, i.e. forming conversion layers
    • C25D11/02—Anodisation
    • C25D11/022—Anodisation on selected surface areas
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C22/00—Chemical surface treatment of metallic material by reaction of the surface with a reactive liquid, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals
    • C23C22/05—Chemical surface treatment of metallic material by reaction of the surface with a reactive liquid, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals using aqueous solutions
    • C23C22/06—Chemical surface treatment of metallic material by reaction of the surface with a reactive liquid, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals using aqueous solutions using aqueous acidic solutions with pH less than 6
    • C23C22/24—Chemical surface treatment of metallic material by reaction of the surface with a reactive liquid, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals using aqueous solutions using aqueous acidic solutions with pH less than 6 containing hexavalent chromium compounds
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C22/00—Chemical surface treatment of metallic material by reaction of the surface with a reactive liquid, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals
    • C23C22/73—Chemical surface treatment of metallic material by reaction of the surface with a reactive liquid, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals characterised by the process
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C22/00—Chemical surface treatment of metallic material by reaction of the surface with a reactive liquid, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals
    • C23C22/82—After-treatment
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C22/00—Chemical surface treatment of metallic material by reaction of the surface with a reactive liquid, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals
    • C23C22/82—After-treatment
    • C23C22/83—Chemical after-treatment
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23F—NON-MECHANICAL REMOVAL OF METALLIC MATERIAL FROM SURFACE; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL; MULTI-STEP PROCESSES FOR SURFACE TREATMENT OF METALLIC MATERIAL INVOLVING AT LEAST ONE PROCESS PROVIDED FOR IN CLASS C23 AND AT LEAST ONE PROCESS COVERED BY SUBCLASS C21D OR C22F OR CLASS C25
    • C23F1/00—Etching metallic material by chemical means
    • C23F1/02—Local etching
    • 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
    • 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
    • C25D11/04—Anodisation of aluminium or alloys based thereon
    • 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
    • C25D11/04—Anodisation of aluminium or alloys based thereon
    • C25D11/06—Anodisation of aluminium or alloys based thereon characterised by the electrolytes used
    • C25D11/08—Anodisation of aluminium or alloys based thereon characterised by the electrolytes used containing inorganic acids
    • 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
    • C25D11/04—Anodisation of aluminium or alloys based thereon
    • C25D11/18—After-treatment, e.g. pore-sealing
    • C25D11/24—Chemical after-treatment
    • C25D11/246—Chemical after-treatment for sealing layers
    • 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
    • C25D11/38—Chromatising
    • 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
    • C25D11/04—Anodisation of aluminium or alloys based thereon
    • C25D11/06—Anodisation of aluminium or alloys based thereon characterised by the electrolytes used
    • C25D11/10—Anodisation of aluminium or alloys based thereon characterised by the electrolytes used containing organic acids
    • 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
    • C25D11/04—Anodisation of aluminium or alloys based thereon
    • C25D11/12—Anodising more than once, e.g. in different baths
    • 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
    • C25D11/36—Phosphatising

Definitions

  • the present invention relates to the processing of objects.
  • some regions of the surface of an aircraft part are chromate conversion coated, while the remaining regions of the parts of the surface of an aircraft part are anodised.
  • Typically, only the chromic acid anodised regions of the aircraft part are painted, while the chromate conversion coated regions of the aircraft part are left unpainted.
  • Figure 1 is a process flow chart showing certain steps of an example conventional process for painting an aircraft part.
  • the unpainted aircraft part is masked by selectively applying masking tape to certain regions of the aircraft part.
  • masking tape may be performed using 3M 425 Aluminium Foil Tape.
  • such masking processes including cutting making tape to desired shaped and applying the cut masking tape to the aircraft part, may take about 3 hours.
  • the masked unpainted aircraft part is anodised.
  • an anodic layer or oxide layer is formed on the unmasked surface of the aircraft part.
  • this step of anodising the aircraft part may take about 1 hour.
  • the anodised aircraft part is de-masked and cleaned.
  • the masking tape applied to the aircraft part at step s2 is removed.
  • any adhesive residue left on the aircraft part by the masking tape is wiped from the aircraft part. Solvents or other cleaning chemicals may be used to remove the adhesive residue.
  • this step of de-masking and cleaning the aircraft part may take about 1 hour.
  • the cleaned aircraft part is prepared for chromate conversion coating.
  • preparation of the aircraft part includes selectively masking (for example, using masking tape and/or paper) the aircraft part.
  • the anodised regions of the aircraft part may be masked.
  • the prepared aircraft part is chromate conversion coated.
  • the aircraft parts is chromate conversion coated by hand.
  • a human being manually applies a chromate conversion layer to the un-anodised regions of the surface of the aircraft part.
  • each region of the surface of the aircraft part is either chromate conversion coated or anodised.
  • the steps of preparing the aircraft part for chromate conversion coating, and chromate conversion coating the aircraft part may take about 2 hours.
  • the chromate conversion coated aircraft part is cleaned.
  • cleaning may include the use of clean, cold water.
  • this step of cleaning the chromate conversion coated aircraft part may take about 1 hour.
  • the cleaned aircraft part is masked by selectively applying masking tape to certain regions of the aircraft part.
  • masking tape In this example, only chromate conversion coated regions of the aircraft part are masked. Also, only anodised regions of the aircraft part are unmasked.
  • the masked aircraft part is painted.
  • paint is only applied to unmasked (i.e. anodised) regions of the aircraft part. Masked, chromate conversion coated regions of the aircraft part are left unpainted.
  • this step of painting the aircraft part may take about 3 hours.
  • the masking tape applied to the aircraft part at step s14 is removed after the paint has dried.
  • US2993847 discloses a method of treating the surface of aluminium parts which involves applying a chromate conversion coating to the entire surface, thereafter forming an alkali and acid resist mask on a portion of the coating, removing the unmasked coating from the aluminium surface by submerging the object in a caustic bath of sodium hydroxide, anodizing the unmasked aluminium surface of the object and finally removing the mask.
  • US2014/0319276 discloses an aircraft window clamp which has one portion which is anticorrosive and is made up of an anodized layer with a subsequent epoxy primer layer and another portion that has first and second bond surfaces that are made up of a chromate based conductive film.
  • US 6475610 discloses a method of treating an aluminium alloy aircraft component involving anodizing, applying a first organic coating, optionally applying a second organic coating, curing and applying release paper until the component is ready to be used.
  • the present inventors have realised that, using a conventional method such as that described in more detail above with reference to Figure 1 , paint tends not to adhere correctly to the aircraft part in certain regions.
  • the present inventors have realised that, at least during de-masking and cleaning process (such as that performed at step s6 of Figure 1 ), residue from the masking tape may remain on the aircraft part.
  • the present inventors have also realised that such masking tape residue may be spread to previously unmasked regions of the aircraft part during cleaning e.g. after or during a de-masking process.
  • masking tape residue tends to detrimentally effect the adhesion of paint to the aircraft part.
  • the present inventors have further realised that aircraft parts undergoing a conventional painting process, such as that described in more detail earlier above with reference to Figure 1 , tend to exhibit blemishes and/or superficial damage.
  • inspection tape used during paint adhesion tests may remove paint from that painted aircraft part.
  • tools such as scalpels
  • Use of such tools may cause damage, such as scratches, to the aircraft part which may introduce stress concentration points to a part.
  • the present invention provides a method of painting an object, wherein the object is at least part of an aircraft and wherein the at least part of the aircraft is a panel, frame, rib, trailing edge spar, or left hand horizontal tail, the method comprising: performing a chromate conversion coating process to dispose a chromate conversion coating onto the entirety of a surface of the object; partially masking the chromate conversion coating disposed on the object; performing an etching process to remove, from the object, an unmasked portion of the chromate conversion coating while retaining the masked portion of the chromate conversion coating on the object; performing an anodising process to dispose an anodic layer onto a region of the surface of the object from which the unmasked portion of the chromate conversion coating was removed; and applying a layer of paint onto the anodic layer and not onto the portion of the chromate conversion coating retained on the object.
  • the method may further comprise, after the second conversion coating process, de-masking the object.
  • the object may be made of a metal or alloy such as aluminium or aluminium alloy.
  • the first conversion coating may define an electrically conductive path through at least part of the coated object.
  • the first conversion coating may define an electrically conductive path through at least part of the part of an aircraft for the transmission of lightning strike energy.
  • the first conversion coating process may comprise: exposing at least part of the object to a cleaning substance; rinsing the object to remove the cleaning substance from the object; exposing at least part of the object to a first conversion coating substance, thereby disposing the first conversion coating onto the at least part of a surface of the object; and rinsing the object to remove residual first conversion coating substance from the object.
  • the etching process may comprise: exposing at least part of the object to a cleaning substance; rinsing the object to remove the cleaning substance from the object; exposing at least part of the object to an etching substance, thereby removing, from the object, an unmasked portion of the first conversion coating; and rinsing the object to remove residual etching substance from the object.
  • the second conversion coating process may comprise: exposing at least part of the object to a cleaning substance; rinsing the object to remove the cleaning substance from the object; exposing at least part of the object to a second conversion coating substance, thereby disposing the second conversion coating onto the at least part of a surface of the object; and rinsing the object to remove residual second conversion coating substance from the object.
  • Partially masking the first conversion coating disposed on the object may comprise applying vinyl tape (for example, a 3M 484 vinyl tape) onto part of the first conversion coating.
  • vinyl tape for example, a 3M 484 vinyl tape
  • the present invention provides the use of an apparatus for carrying out the method as described above and for painting an object, wherein the object is at least part of an aircraft and wherein the at least part of the aircraft is a panel, frame, rib, trailing edge spar, or left hand horizontal tail, the apparatus comprising: chromate conversion coating means adapted to dispose a chromate conversion coating onto the entirety of a surface of the object; masking means adapted to partially mask the chromate conversion coating disposed on the object; etching means adapted to remove, from the object, an unmasked portion of the chromate conversion coating while retaining the masked portion of the chromate conversion coating on the object; anodising means adapted to dispose an anodic layer onto a region of the surface of the object from which the unmasked portion of the chromate conversion coating was removed; and painting means adapted to apply a layer of paint onto the anodic layer and not onto the portion of the chromate conversion coating retained on the object.
  • the present invention provides a painted object that has been processed using a method as described above, wherein the painted object is at least part of an aircraft and the at least part of the aircraft is a panel, frame, rib, trailing edge spar, or left hand horizontal tail and the painted object comprises: a chromate conversion coating disposed onto a first region of a surface of an uncoated object, the first region being the entirety of a surface of an uncoated object; an anodic layer disposed onto a second region of a surface of an uncoated object, the second region being different to the first region, and the second region being a region from which the chromate coating has been removed; a layer of paint disposed onto the anodic layer and not onto the portion of the chromate conversion coating retained on the object.
  • the present disclosure also provides an aircraft comprising an object according to the preceding aspect.
  • the present disclosure also provides a method of producing an aircraft including a method of processing an object according to any of the preceding aspects, the object being at least part of the aircraft.
  • Figure 2 is a schematic illustration (not to scale) of a painted aircraft part 2.
  • the painted aircraft part 2 may be any appropriate aircraft part, for example, a trailing edge spar, left hand horizontal tail, STOVL, or an aircraft frame.
  • the painted aircraft part 2 comprises an initial aircraft part 4 to which coatings have been applied.
  • a surface of the initial aircraft part 4 comprises two regions, namely a first region 6 and second region 8.
  • the initial aircraft part 4 is made of a metal or alloy such as aluminium or aluminium alloy.
  • the painted aircraft part 2 comprises a chromate conversion coating or layer 10.
  • the chromate conversion layer 10 is disposed on the first region 6 of the surface of the initial aircraft part 4.
  • the chromate conversion layer 10 is a chromate conversion film formed from potassium dichromate.
  • the painted aircraft part 2 further comprises an anodic coating or layer 12.
  • the anodic layer 12 is disposed on the second region 8 of the surface of the initial aircraft part 4.
  • the painted aircraft part 2 further comprises a paint layer 14.
  • the paint layer 14 is disposed on the anodic layer 12 such that the anodic layer 12 is sandwiched between the paint layer 14 and the second region 8 of the surface of the initial aircraft part 4.
  • Figure 3 is a process flow chart showing certain steps of an embodiment of a process for painting an aircraft part.
  • the uncoated aircraft part i.e. the initial aircraft part 4 without the coatings 10, 12, 14 applied
  • the chromate conversion coated initial aircraft part 4 is masked by selectively applying masking tape to certain regions of its surface.
  • the masking tape used to mask the chromate conversion coated initial aircraft part 4 is 3M 484 electroplating and anodizing vinyl tape, often referred to as "yellow tape”.
  • the chromate conversion coating is stripped from the unmasked regions of the surface of the chromate conversion coated initial aircraft part 4.
  • the chromate conversion coating is stripped from the second region 8 of the surface of the initial aircraft part 4. Also, the chromate conversion layer 10 remains disposed on the masked first region 6 of the surface of the initial aircraft part 4.
  • the selectively stripped initial aircraft part 4 (with the chromate conversion layer 10 and masking tape applied to the first region 6 of its surface) is anodised.
  • Anodising the selectively stripped initial aircraft part 4 forms the anodic layer 12 only on the unmasked regions of the surface of the initial aircraft part 4.
  • the anodic layer 12 is formed on the second region 8 of the surface of the initial aircraft part 4 and not on the first region 6 of the surface of the initial aircraft part 4.
  • the below described process of applying paint to the aircraft part is performed within 16 hours of anodising the initial aircraft part 4.
  • the paint layer 14 is applied to the anodised initial aircraft part 4, thereby forming the painted aircraft part 2.
  • the paint layer 14 is only applied to the unmasked regions of the surface of the initial aircraft part 4.
  • the paint layer 14 is disposed on the anodic layer 12 on the second region 8 of the surface of the initial aircraft part 4.
  • the paint layer 14 is not applied to the first region 6 of the surface of the initial aircraft part 4.
  • the paint layer 14 may include multiple paint layers, e.g. a primer layer and a top coat.
  • Figure 4 is a process flow chart showing certain steps of an embodiment of a process of chromate conversion coating the entirety of the surface of the initial aircraft part 4.
  • the initial aircraft part 4 is prepared.
  • preparation of the initial aircraft part 4 includes, but is not limited, checking the initial aircraft part 4 for signs of damage (e.g. abrasions, nicks, scratches, etc.) or excessive contamination, and ensuring all heat treatments, machining, welding, brazing, forming, and flaw detection processes that have been performed on the initial aircraft part 4 have been performed satisfactorily.
  • the preparation process may be performed by a human being, or may be an automated process.
  • the damaged initial aircraft part 4 may be referred for further inspection or repair.
  • the initial aircraft part 4 is wholly submerged in alkaline cleaner.
  • the alkaline cleaner is Turco 4215 NCLT having a concentration of between 40g/l and 60g/l.
  • the temperature of the alkaline cleaner is between 45°C and 55°C.
  • the initial aircraft part 4 is submerged in the alkaline cleaner for between 2mins and 10mins.
  • the cleaned initial aircraft part 4 is drained.
  • the initial aircraft part 4 is not left to completely dry.
  • Draining of the alkaline cleaner from the cleaned initial part 4 tends to reduce or eliminate contamination of subsequent processing liquids by the alkaline cleaner.
  • the drained initial aircraft part 4 is rinsed.
  • rinsing of the drained initial aircraft part comprises spraying the initial aircraft part 4 using clean, cold, running water for between 5mins and 60mins.
  • Rinsing of the initial aircraft part 4 tends to ensure complete removal of any residual alkaline cleaner.
  • step s38 the rinsed initial aircraft part 4 is inspected.
  • the rinsed initial aircraft part 4 is inspected for a water break free surface. If a water break free surface of the initial aircraft part 4 is visible, the method proceeds to step s40. However, if a water break is observed on the initial aircraft part 4, the process returns to step s32.
  • This inspection of the initial aircraft part 4 may be performed by a human being or automatically.
  • the initial aircraft part 4 is wholly submerged in an etching solution.
  • the etching solution is an agitated acid solution.
  • the acid solution is a so-called “deoxidiser” solution which may be a "de-smut” solution.
  • the deoxidiser solution is Deoxidiser 7/17 (as Cr6+) having a concentration of between 4.5g/l and 10.5g/l.
  • the initial aircraft part 4 is submerged in the deoxidiser solution for between 5mins and 10mins.
  • step s42 the initial aircraft part 4 is rinsed. This rinsing process may be performed in the same or a similar way to that performed at step s36 for between 5mins and 60mins.
  • Rinsing of the initial aircraft part 4 tends to ensure complete removal of any residual deoxidiser solution.
  • the rinsed initial aircraft part 4 is wholly submerged in chromate conversion coating solution.
  • the chromate conversion coating solution is Alocrom 1200.
  • the initial aircraft part 4 is submerged in the chromate conversion coating solution for between 2mins and 3mins.
  • the chromate conversion layer 10 is applied across the whole surface of the initial aircraft part 4.
  • step s46 the chromate conversion coated initial aircraft part 4 is rinsed. This rinsing process may be performed in the same or a similar way to that performed at step s36 for between 2mins and 5mins without spray.
  • Rinsing of the initial aircraft part 4 tends to ensure complete removal of any residual chromate conversion coating solution.
  • step s48 the rinsed initial aircraft part 4 is completely dried.
  • the rinsed initial aircraft part 4 is air dried at a temperature of less than or equal to 60°C for at least 10mins.
  • step s50 the dried initial aircraft part 4 is inspected.
  • the dried initial aircraft part 4 is inspected for the presence of damage, detached deposit, and non-adherent or powdery coating. Detection of non-adherent or powdery chromate conversion coating may be performed by rubbing the surface of the coated initial aircraft part 4, for example, using a test paper such as Whatman, Style No. 40 filter paper.
  • the initial aircraft part may be re-processed, for example, using one or more of the above described process steps.
  • This inspection of the dried initial aircraft part 4 may be performed by a human being or automatically.
  • step s50 After the inspection process of step s50, the process proceeds to masking step s22 described in more detail earlier above with reference to Figure 3 .
  • the below described process of applying paint to the aircraft part is performed within 16 hours of the chromate conversion coating the initial aircraft part 4
  • a process of chromate conversion coating the entirety of the surface of the initial aircraft part 4 is provided.
  • Figure 5 is a process flow chart showing certain steps of an embodiment of a process of stripping the chromate conversion coating from the unmasked regions of the surface of the initial aircraft part 4.
  • step s52 the selectively masked chromate conversion coated initial aircraft 4 part is prepared.
  • preparation of the aircraft part 4 includes, but is not limited, checking the initial aircraft part 4 for signs of damage. In some embodiments, if damage or the like is detected on the initial aircraft part 4, no further steps of the painting process are performed, and the damaged initial aircraft part 4 may be referred for further inspection or repair.
  • the conversion coated area Prior to masking, the conversion coated area may be solvent wiped to ensure any debris collected between processes is removed and the masking adheres to the conversion coated surface.
  • Edges of masked areas may be sealed and masking tape boundaries may be overlapped with further masking tape. This tends to reduce or eliminate ingress of treatment liquids into masked areas of the aircraft part.
  • the preparation process may be performed by a human being, or may be an automated process.
  • the masked initial aircraft part 4 is wholly submerged in alkaline cleaner. This cleaning process may be performed in the same or a similar way to that performed at step s32 for 5-10 minutes.
  • the masked initial aircraft part 4 is drained. In this embodiment, the masked initial aircraft part 4 is not left to completely dry.
  • step s58 the drained initial aircraft part 4 is rinsed. This rinsing process may be performed in the same or a similar way to that performed at step s36 for between 4-6 minutes.
  • step s60 the rinsed initial aircraft part 4 is inspected. This inspection process may be performed in the same or a similar way to that performed at step s38.
  • the rinsed initial aircraft part 4 is wholly submerged in etching solution or stripping solution.
  • the etching solution is, for example, Aluminetch #2.
  • the initial aircraft part 4 is submerged in the etching solution for between 1min and 2mins.
  • the chromate conversion layer 10 is etched, i.e. removed, from the unmasked regions of the surface of initial aircraft part 4, for example, from the second region 8.
  • the timings tend to be such that minimal aluminium is removed and only conversion coating film is removed.
  • the etched initial aircraft part 4 is rinsed. This rinsing process may be performed in the same or a similar way to that performed at step s36 for between 2mins and 5mins.
  • Rinsing of the initial aircraft part 4 tends to ensure complete removal of any residual etching solution and stops any further etching.
  • the rinsed initial aircraft part 4 is wholly submerged in deoxidiser solution e.g. to perform a "de-smut" operation.
  • This deoxidising process may be performed in the same or a similar way to that performed at step s40 for a maximum of 30 seconds.
  • step s68 the de-oxidised initial aircraft part 4 is rinsed. This rinsing process may be performed in the same or a similar way to that performed at step s36 for between 4mins and 6mins.
  • step s68 After the rinsing process of step s68, the process proceeds to anodising step s26.
  • Figure 6 is a process flow chart showing certain steps of an embodiment of a process of anodising the selectively stripped initial aircraft part 4.
  • the selectively stripped initial aircraft 4 part is prepared. Preparation may be performed in the same or a similar way to that performed at step s30 or s52 above.
  • the selectively stripped initial aircraft part 4 is wholly submerged in alkaline cleaner. This cleaning process may be performed in the same or a similar way to that performed at step s32.
  • the selectively stripped initial aircraft part 4 is drained.
  • the masked initial aircraft part 4 is not left to completely dry.
  • step s76 the drained initial aircraft part 4 is rinsed. This rinsing process may be performed in the same or a similar way to that performed at step s36 for between 5mins and 60mins.
  • step s78 the rinsed initial aircraft part 4 is inspected. This inspection process may be performed in the same or a similar way to that performed at step s38.
  • the initial aircraft part 4 is wholly submerged in deoxidiser solution.
  • This deoxidation process may be performed in the same or a similar way to that performed at step s40.
  • step s82 the initial aircraft part 4 is rinsed. This rinsing process may be performed in the same or a similar way to that performed at step s42.
  • step s84 the rinsed initial aircraft part 4 is inspected.
  • the rinsed aircraft part is inspected for, for example, signs of contamination, defects, and damage.
  • This inspection process may be performed by a human being, or may be an automated process.
  • the damaged initial aircraft part 4 may be referred for further inspection or repair.
  • step s86 the rinsed, selectively stripped aircraft part 4 is connected to an anode.
  • step s88 the selectively stripped initial aircraft part 4 is wholly submerged in anodising electrolyte.
  • the anodising electrolyte comprises: free chromic acid having a concentration of between 30g/l to 50g/l; a sulphate (e.g. Na 2 SO 4 ) having a maximum concentration of 0.5g/l; a chloride (e.g. as NaCl) having a maximum concentration of 0.2g/l; and water.
  • the maximum total chromium content of the anodising electrolyte is 100g/l.
  • the operating temperature of the anodising electrolyte is between 35°C and 40°C.
  • a voltage is applied to the selectively stripped initial aircraft part 4 via the anode connected thereto.
  • the voltage applied to the anode is increased from 0V to 22V (+/- 2V) at a rate not exceeding 7V/min.
  • the maximum voltage of 22V (+/- 2V) is then maintained for between 30min and 60min.
  • the voltage is then reduced to less than or equal to 5V.
  • This reducing of the voltage to less than or equal to 5V, allows for the initial aircraft part 4 to be retained in the anodising electrolyte for an addition time period, for example, for an additional 5mins maximum, if desired.
  • the anodised initial aircraft part 4 is drained. In this embodiment, the anodised initial aircraft part 4 is not left to completely dry.
  • the anodised initial aircraft part 4 is rinsed at least once.
  • This rinsing process may be performed in the same or a similar way to that performed at step s36 for at least 5mins.
  • Rinsing e.g. multiple rinsing
  • the initial aircraft part 4 tends to ensure complete removal of any residual anodising electrolyte.
  • step s96 the rinsed initial aircraft part 4 is inspected. This inspection process may be performed in the same or a similar way to that performed at step s50.
  • the anodised initial aircraft part 4 is wholly submerged in a sealing solution.
  • the sealing solution is a dichromate seal.
  • the sealing solution comprises: potassium dichromate having a concentration of between 0.1g/l to 0.15g/l; a silicate having a maximum concentration of 7.5ppm; a sulphate having a maximum concentration of 90ppm; a chloride having a maximum concentration of 50ppm; and water.
  • the anodised initial aircraft part 4 is submerged in the sealing solution for 10mins (+/-2mins).
  • the operating temperature of the sealing solution is 91°C (+/- 3°C).
  • the rinsed initial aircraft part 4 is completely dried. This drying process may be performed in the same or a similar way to that performed at step s48.
  • the dried aircraft part 4 is inspected. This inspection process may be performed in the same or a similar way to that performed at step s50.
  • step s102 After the inspection process of step s102, the process proceeds to painting step s28. Further inspection processes may be performed after anodising has been performed, and prior to the painting of the unmasked regions of the initial aircraft part 4.
  • the above described process for painting an aircraft part advantageously tends to be much quicker than conventional process. For example, whereas conventional painting processes typically take around 11 hours to complete, the above described painting process may be performed in around 2.5hours. Thus, the above described method tends to provide significant time and cost savings.
  • the above described process tends to provide improved better paint adhesion to the aircraft part.
  • the masking tape used in the above described process tends not to be removed until the painting process has been completed. Thus, there tends to be no masking tape residue left beneath the paint layer from de-masking cleaning operations. This advantageously tends to improve paint adhesion.
  • the number of times an aircraft part is masked and de-masked during painting is advantageously reduced.
  • the number of times masking is removed from the aircraft part during painting tends to be advantageously reduced. This tends to reduce the use of tools (such as scalpels) to remove masking tape from the aircraft part. This tends to reduce the likelihood of damage (e.g. scratches etc.) to the surface of the aircraft part.
  • tools such as scalpels
  • the masking tape used in the above described process (which may be applied in a pre-cut form or may be cut at time of application to the aircraft part) is a vinyl type. This tends to allow for the use of plastic tools to remove the tape from the aircraft part following application.
  • the aluminium based foil used in conventional processes tends to be difficult to remove and tended to bake onto the surface of the aircraft part, for example, during the anodise process which exotherms as a result of the electrolytic process, or during a paint curing process.
  • the above described method tends to have a reduced use of solvents compared to conventional methods. Also, a need to manually (i.e. by hand) chromate conversion coat the aircraft part tends to be eliminated. Thus, detrimental health effects to humans caused by solvents etc. tend to be reduced.
  • the above described method may be wholly or partially automated.
  • the aircraft part may be mounted to a frame or jig and processed as described above by moving the frame or jig between treatment stations.
  • Automated application of, for example, the chromate conversion coating tends to produce higher quality and more repeatable finish.
  • the improved finish due at least in part to the improved finish, it tends to be possible to discern aircraft parts processed using the above described process from those processed using a conventional process. For example, it tends to be possible to discern aircraft parts conversion coated using the above described process from those conversion coated using a conventional process. Also, it tends to be possible to discern aircraft parts painted using the above described process from those painted using a conventional process.
  • the above described process may be implemented as a production line process.
  • the above described process may be implemented to process multiple aircraft parts simultaneously.
  • the chromate conversion coating is relatively electrically conductive whereas the anodic (or oxide) is relatively electrically resistive.
  • the chromate conversion coating defines an electrically conductive path through at least part of painted aircraft part. Such an electrically conductive path may be, for example, for transmitting a lightning strike safely through the aircraft.
  • the above described alkaline cleaning or deoxidising operations may be, for example, air powered (oil free), or liquid agitation processes.
  • the various treatment liquids, treatment times, voltage cycles, and treatment temperatures etc. are as described in more detail earlier above.
  • one or more different appropriate treatment liquids, and/or other types of treatment such as treatment using a gas or vapour
  • a different treatment time may be used instead of one or more of the above mentioned treatment times.
  • a different treatment temperature may be used instead of one or more of the above mentioned treatment temperatures.
  • a different voltage cycle may be used instead of one or more of the above mentioned voltage cycles.
  • a chromate conversion layer is applied to the aircraft part using a chromate conversion coating process.
  • a different type of conversion coating is applied to the aircraft in addition to the chromate conversion coating layer.
  • a phosphate conversion coating process, or an anodising process is used in addition to the chromate conversion coating process.
  • an anodic layer is applied to the aircraft part using an anodising process, which may be regarded as a type of conversion coating process.
  • anodising process which may be regarded as a type of conversion coating process.
  • a different type of conversion coating is applied to the aircraft part in addition to the anodic layer.
  • a tartaric anodic process, or a different anodising process is used in addition to the chromic acid anodising process.
  • the masking tape used to mask the chromate conversion coated initial aircraft part is 3M 484 electroplating and anodizing vinyl tape.
  • a different type of making tape is used to perform the masking process.
  • a different vinyl tape may be used, e.g. P21 "Green Tape" which, for example, may be used in masking processes performed up to about 220°C.
  • the type of masking tape used in the masking process may be selected depending upon properties of the masking tape and the object being masked. For example, a thicker and/or less flexible masking tape may selected for application onto and the masking of relatively flat surfaces of an object, and may, for example, be applied as a pre-cut template. In contrast, a thinner and/or more flexible masking tape may be selected for application onto and the masking of relatively highly curved surfaces of an object, such as double curved surfaces. Such selection of an appropriate making tape advantageously tends to facilitate the making process, and moreover tends to provide for an improved mask.
  • conversion coating may be used herein to refer to processes including, but not limited to: coatings for metals where the part surface is converted into the coating with a chemical or electro-chemical process, chromate conversion coatings, phosphate conversion coatings, bluing, black oxide coatings on steel, plating and anodizing. Conversion coating may be applied to any appropriate material including but not limited to titanium, magnesium, niobium, aluminium or tantalum parts. Anodizing may be regarded as a conversion coating process generated by a combination of both chemical conversion and electric current at an object's surface.

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  • Organic Chemistry (AREA)
  • Electrochemistry (AREA)
  • General Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Inorganic Chemistry (AREA)
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  • Application Of Or Painting With Fluid Materials (AREA)

Claims (9)

  1. Verfahren zum Lackieren eines Objekts (4), wobei das Objekt mindestens ein Teil eines Flugzeugs ist, und wobei der mindestens eine Teil des Flugzeugs ein Verkleidungsblech, ein Rahmen, eine Rippe, ein Hinterkantenholm oder ein linkes Höhenleitwerk ist, und das Verfahren umfasst:
    Durchführen eines Chromatkonversionsbeschichtungsprozesses zum Anordnen einer Chromatkonversionsbeschichtung (10) auf der Gesamtheit einer Oberfläche des Objekts (4);
    teilweises Maskieren der auf dem Objekt (4) angeordneten Chromatkonversionsbeschichtung (10)
    Durchführen eines Ätzprozesses zum Entfernen eines unmaskierten Abschnitts der Chromatkonversionsbeschichtung (10) vom Objekt (4), während der maskierte Abschnitt der Chromatkonversionsbeschichtung (10) auf dem Objekt (4) belassen wird;
    Durchführen eines Anodisierungsprozesses zum Anordnen einer Anodenschicht (12) auf einer Region der Oberfläche des Objekts (4), von welcher der unmaskierte Abschnitt der Chromatkonversionsbeschichtung (10) entfernt wurde; und
    Aufbringen einer Lackschicht (14) auf die Anodenschicht (12), aber nicht auf den Abschnitt der auf dem Objekt (4) belassenen Chromatkonversionsbeschichtung (10).
  2. Verfahren nach Anspruch 1, wobei das Verfahren nach dem Anodisierungsprozess ferner ein Demaskieren des Objekts (4) umfasst.
  3. Verfahren nach Anspruch 1 oder 2, wobei die Chromatkonversionsbeschichtung (10) einen elektrisch leitenden Pfad durch das beschichtete Objekt (2) definiert.
  4. Verfahren nach einem der Ansprüche 1 bis 3, wobei der Chromatkonversionsbeschichtungsprozess umfasst:
    Aussetzen wenigstens eines Teils des Objekts (4) gegenüber einer Reinigungssubstanz;
    Spülen des Objekts (4), um die Reinigungssubstanz vom Objekt (4) zu entfernen;
    Aussetzen wenigstens des Teils des Objekts (4) gegenüber einer Chromatkonversionsbeschichtungssubstanz, um dadurch die Chromatkonversionsbeschichtung (10) auf der Gesamtheit der Oberfläche des Objekts (4) anzuordnen; und
    Spülen des Objekts (4), um restliche Chromatkonversionsbeschichtungssubstanz vom Objekt (4) zu entfernen.
  5. Verfahren nach einem der Ansprüche 1 bis 4, wobei der Ätzprozess umfasst:
    Aussetzen wenigstens eines Teils des Objekts (4) gegenüber einer Reinigungssubstanz;
    Spülen des Objekts (4), um die Reinigungssubstanz vom Objekt (4) zu entfernen;
    Aussetzen wenigstens eines Teils des Objekts (4) gegenüber einer Ätzsubstanz, um dadurch einen unmaskierten Abschnitt der Chromatkonversionsbeschichtung (10) vom Objekt (4) zu entfernen; und
    Spülen des Objekts (4), um restliche Ätzsubstanz vom Objekt (4) zu entfernen.
  6. Verfahren nach einem der Ansprüche 1 bis 5, wobei der Anodisierungsprozess umfasst:
    Aussetzen wenigstens eines Teils des Objekts (4) gegenüber einer Reinigungssubstanz;
    Spülen des Objekts (4), um die Reinigungssubstanz vom Objekt (4) zu entfernen;
    Aussetzen wenigstens eines Teils des Objekts (4) gegenüber einer anodischen Substanz, um dadurch die Anodenschicht (12) auf dem wenigstens einen Teil einer Oberfläche des Objekts (4) anzuordnen; und
    Spülen des Objekts (4), um restliche anodische Substanz vom Objekt (4) zu entfernen.
  7. Verfahren nach einem der Ansprüche 1 bis 6, wobei das teilweise Maskieren der auf dem Objekt angeordneten Chromatkonversionsbeschichtung (10) ein Aufbringen eines Vinylbandes auf einen Teil der Chromatkonversionsbeschichtung (10) umfasst.
  8. Verwendung einer Vorrichtung zum Durchführen des Verfahrens nach einem der Ansprüche 1 bis 7 und zum Lackieren eines Objekts (4), wobei das Objekt mindestens ein Teil eines Flugzeugs ist, und wobei der mindestens eine Teil des Flugzeugs ein Verkleidungsblech, ein Rahmen, eine Rippe, ein Hinterkantenholm oder ein linkes Höhenleitwerk ist, und die Vorrichtung umfasst:
    Chromatkonversionsbeschichtungsmittel, ausgelegt zum Anordnen einer Chromatkonversionsbeschichtung (10) auf der Gesamtheit einer Oberfläche des Objekts (4);
    Maskierungsmittel, ausgelegt zum teilweisen Maskieren der auf dem Objekt (4) angeordneten Chromatkonversionsbeschichtung (10);
    Ätzmittel, ausgelegt zum Entfernen eines unmaskierten Abschnitts der Chromatkonversionsbeschichtung (10) vom Objekt (4), während der maskierte Abschnitt der Chromatkonversionsbeschichtung (10) auf dem Objekt (4) belassen wird;
    Anodisierungsmittel, ausgelegt zum Anordnen einer Anodenschicht (12) auf einer Region der Oberfläche des Objekts (4), von welcher der unmaskierte Abschnitt der Chromatkonversionsbeschichtung (10) entfernt wurde; und
    Lackiermittel, ausgelegt zum Aufbringen einer Lackschicht (14) auf die Anodenschicht (12), aber nicht auf den Abschnitt der auf dem Objekt (4) belassenen Chromatkonversionsbeschichtung (10).
  9. Lackiertes Objekt (2), das unter Verwendung eines Verfahrens nach einem der Ansprüche 1 bis 7 lackiert wurde, wobei das lackierte Objekt mindestens ein Teil eines Flugzeugs ist, und wobei der mindestens eine Teil des Flugzeugs ein Verkleidungsblech, ein Rahmen, eine Rippe, ein Hinterkantenholm oder ein linkes Höhenleitwerk ist, und das lackierte Objekt (2) umfasst:
    eine Chromatkonversionsbeschichtung (10), die auf einer ersten Region einer Oberfläche eines unbeschichteten Objekts (4) angeordnet ist, wobei die erste Region die Gesamtheit einer Oberfläche eines unbeschichteten Objekts (4) ist;
    eine Anodenschicht (12), die auf einer zweiten Region einer Oberfläche eines unbeschichteten Objekts (4) angeordnet ist, wobei die zweite Region von der ersten Region verschieden ist, und die zweite Region eine Region ist, von welcher die Chromatkonversionsbeschichtung (10) entfernt wurde;
    eine Lackschicht (14), die auf der Anodenschicht (12), aber nicht auf dem Abschnitt der auf dem Objekt (4) belassenen Chromatkonversionsbeschichtung (10) angeordnet ist.
EP15813487.4A 2014-12-17 2015-12-09 Objektverarbeitung durch konversionsbeschichtung Active EP3234231B8 (de)

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PCT/GB2015/053764 WO2016097695A1 (en) 2014-12-17 2015-12-09 Object processing by conversion coating

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US6475610B1 (en) * 1998-09-11 2002-11-05 Mcdonnell Douglas Corporation Method for coating faying surfaces of aluminum-alloy components and faying surfaces coated thereby
US20140319276A1 (en) * 2011-09-14 2014-10-30 Mitsubishi Aircraft Corporation Aircraft window and aircraft

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US2885273A (en) * 1956-03-14 1959-05-05 North American Aviation Inc Method of etching metallic materials
US2993847A (en) * 1958-04-04 1961-07-25 Burroughs Corp Aluminum treating process
US5698316A (en) * 1996-10-07 1997-12-16 The Boeing Company Apparatus and methods of providing corrosion resistant conductive path across non conductive joints or gaps
US20090311534A1 (en) * 2008-06-12 2009-12-17 Griffin Bruce M Methods and systems for improving an organic finish adhesion to aluminum components
US8398841B2 (en) * 2009-07-24 2013-03-19 Apple Inc. Dual anodization surface treatment
US8449784B2 (en) * 2010-12-21 2013-05-28 United Technologies Corporation Method for securing a sheath to a blade

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US6475610B1 (en) * 1998-09-11 2002-11-05 Mcdonnell Douglas Corporation Method for coating faying surfaces of aluminum-alloy components and faying surfaces coated thereby
US20140319276A1 (en) * 2011-09-14 2014-10-30 Mitsubishi Aircraft Corporation Aircraft window and aircraft

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AU2015365719A1 (en) 2017-06-29
GB2536098B (en) 2019-08-28
WO2016097695A1 (en) 2016-06-23
EP3234231B8 (de) 2020-11-04
EP3234231A1 (de) 2017-10-25

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