CN111036520A - Method for in-situ reinforced repairing of airplane landing gear beam cracks - Google Patents
Method for in-situ reinforced repairing of airplane landing gear beam cracks Download PDFInfo
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- CN111036520A CN111036520A CN201911145856.7A CN201911145856A CN111036520A CN 111036520 A CN111036520 A CN 111036520A CN 201911145856 A CN201911145856 A CN 201911145856A CN 111036520 A CN111036520 A CN 111036520A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D—PROCESSES FOR APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D5/00—Processes for applying liquids or other fluent materials to surfaces to obtain special surface effects, finishes or structures
- B05D5/005—Repairing damaged coatings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D—PROCESSES FOR APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D1/00—Processes for applying liquids or other fluent materials
- B05D1/02—Processes for applying liquids or other fluent materials performed by spraying
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D—PROCESSES FOR APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D1/00—Processes for applying liquids or other fluent materials
- B05D1/32—Processes for applying liquids or other fluent materials using means for protecting parts of a surface not to be coated, e.g. using stencils, resists
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D—PROCESSES FOR APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D3/00—Pretreatment of surfaces to which liquids or other fluent materials are to be applied; After-treatment of applied coatings, e.g. intermediate treating of an applied coating preparatory to subsequent applications of liquids or other fluent materials
- B05D3/002—Pretreatement
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D—PROCESSES FOR APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D3/00—Pretreatment of surfaces to which liquids or other fluent materials are to be applied; After-treatment of applied coatings, e.g. intermediate treating of an applied coating preparatory to subsequent applications of liquids or other fluent materials
- B05D3/007—After-treatment
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D—PROCESSES FOR APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D3/00—Pretreatment of surfaces to which liquids or other fluent materials are to be applied; After-treatment of applied coatings, e.g. intermediate treating of an applied coating preparatory to subsequent applications of liquids or other fluent materials
- B05D3/12—Pretreatment of surfaces to which liquids or other fluent materials are to be applied; After-treatment of applied coatings, e.g. intermediate treating of an applied coating preparatory to subsequent applications of liquids or other fluent materials by mechanical means
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D—PROCESSES FOR APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D7/00—Processes, other than flocking, specially adapted for applying liquids or other fluent materials to particular surfaces or for applying particular liquids or other fluent materials
- B05D7/14—Processes, other than flocking, specially adapted for applying liquids or other fluent materials to particular surfaces or for applying particular liquids or other fluent materials to metal, e.g. car bodies
- B05D7/16—Processes, other than flocking, specially adapted for applying liquids or other fluent materials to particular surfaces or for applying particular liquids or other fluent materials to metal, e.g. car bodies using synthetic lacquers or varnishes
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D—PROCESSES FOR APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D7/00—Processes, other than flocking, specially adapted for applying liquids or other fluent materials to particular surfaces or for applying particular liquids or other fluent materials
- B05D7/24—Processes, other than flocking, specially adapted for applying liquids or other fluent materials to particular surfaces or for applying particular liquids or other fluent materials for applying particular liquids or other fluent materials
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D—PROCESSES FOR APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D7/00—Processes, other than flocking, specially adapted for applying liquids or other fluent materials to particular surfaces or for applying particular liquids or other fluent materials
- B05D7/50—Multilayers
- B05D7/56—Three layers or more
- B05D7/58—No clear coat specified
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- Wood Science & Technology (AREA)
- Mechanical Engineering (AREA)
- Coating By Spraying Or Casting (AREA)
Abstract
The invention discloses an in-situ reinforced repair method for airplane landing gear beam cracks, which is characterized in that a spray coating with a set size is directly sprayed on a crack area of an airplane landing gear beam to repair the cracks; the method adopts the cold spraying technology to spray a spraying layer with a set size on the airplane landing gear beam crack area, and the spraying layer sprayed on the airplane landing gear beam crack area according to the repairing method of the invention has higher combination degree, strength and hardness, so that the airplane landing gear beam crack area forms a stress layer with a set thickness, which is used for offsetting the load stress born by the airplane landing gear beam crack area, effectively reducing the propagation rate of the airplane landing gear beam crack, improving the fatigue resistance of the airplane landing gear beam, prolonging the service life of the airplane and providing powerful guarantee for military training.
Description
Technical Field
The invention relates to the technical field of airplane landing gear beam crack repair, in particular to an in-situ reinforced repair method for airplane landing gear beam cracks.
Background
The landing gear beam is used for connecting a main landing gear, mainly transfers the load of the main landing gear, is a main bearing component of a body structure, and directly endangers the flight safety once damaged. As the frequency and the strength of the airplane in active service are increased, the landing gear of a large number of airplanes has cracks of different degrees, and the army combat training is seriously influenced.
For cracks of structural parts, the conventional repair method is to disassemble the structural parts and then weld the structural parts, or to reinforce the structural parts by adopting a mode of drilling and assembling a reinforcing corner box. However, the landing gear beam is not easy to disassemble and disassemble from the landing gear, so that the disassembly, welding and repair cannot be implemented, and the landing gear beam is used as a main bearing component, so that the fatigue resistance of the landing gear beam can be obviously reduced if the angle box is adopted for drilling and assembling.
Disclosure of Invention
In view of the above, the invention provides an in-situ reinforced repairing method for cracks of an aircraft landing gear beam, which is characterized in that a cold spraying technology is adopted to spray a spraying layer with a set thickness on a crack region of the aircraft landing gear beam, so that the propagation rate of the cracks of the aircraft landing gear beam can be effectively reduced, the fatigue resistance of the aircraft landing gear beam is improved, and the service life of an aircraft is prolonged.
The technical scheme of the invention is as follows: an in-situ reinforced repairing method for the cracks of landing gear beam features that a spray layer with a certain size is directly sprayed on the crack region of landing gear beam to repair the cracks.
Preferably, the step of spraying the sprayed layer is:
the method comprises the following steps: dismantling
Dismantling non-bearing parts on the aircraft landing gear, which hinder the spraying construction operation;
step two: cleaning before spray repair
Cleaning the interior of a wing oil tank, removing a sealant and a paint layer in a crack area of an aircraft landing gear beam, removing an anodic oxidation layer on the surface of the aircraft landing gear beam, and cleaning;
step three: protection
Covering and protecting the interior of the crack area of the airplane landing gear beam to be sprayed and repaired; plugging and covering protection are carried out on an area containing a pipeline and an element structure; dividing the crack area of the airplane landing gear beam to be sprayed and repaired into a pre-aviation area and a post-aviation area by taking the airplane landing gear beam as a boundary, respectively carrying out isolation protection on the pre-aviation area and the post-aviation area, and sealing and plugging the holes of reinforcing ribs of the airplane landing gear beam and an upper wall plate;
step four: sand blasting
After checking and confirming that all protection and plugging are finished in the third step, carrying out sand blasting pretreatment on the area to be sprayed, and absorbing sand grains in the area to be sprayed after sand blasting is finished so as to enable the area to be sprayed to be roughened and the surface of the area to be sprayed to be free of pollution;
step five: adhesive temperature sensor
Respectively sticking patch type temperature sensors on the back and the side of a region to be sprayed of the aircraft landing gear beam, and monitoring the temperature change in the region to be sprayed in real time;
step six: spraying of paint
Spraying a spraying layer with a set thickness before and after the spraying of the area to be sprayed by adopting cold spraying equipment, and reserving a set polishing allowance, so that real-time air draft and dust removal are ensured in the spraying process;
in the whole spraying process, the surface mount type temperature sensor in the step five is used for monitoring the temperature of the spraying area of the aircraft landing gear beam in real time, so that the surface temperature of the aircraft landing gear beam is always lower than a set value;
step seven: polishing
After spraying, placing the aircraft landing gear beam for a set time, and polishing the surface of the spraying layer to be smooth;
step eight: cleaning the residue
After polishing, absorbing and removing dust, sand and metal chips in the spraying area, dismantling spraying operation tools and equipment on the machine, and dismantling the protective objects in the spraying area until no residue exists on the inspection machine;
step nine: restoring surface protective layers
Coating a machine oxide layer on the surface of the spraying layer of the aircraft landing frame beam and the paint removing area in the second step, oxidizing, coating two layers of machine paint, and sealing and protecting the surface after drying;
step ten: reinstalling installation
Restoring the non-bearing parts removed in the first installation step;
step eleven: post-spray cleaning
Removing pollutants caused by spraying operation on the aircraft landing gear beam;
step twelve: examination of
The thickness, the roughness and the pollutants of the sprayed layer of the aircraft landing gear beam are respectively detected, and the aircraft landing gear beam is ensured to meet the machine requirements.
Preferably, the method further comprises the following steps: and spraying a reinforcing layer with a set thickness on the spraying layer along the crack path.
Preferably, before spraying and repairing the first airplane and after spraying and repairing the last airplane in the batches of airplanes, respectively preparing a metallographic examination sample piece and more than two fatigue test pieces, and performing metallographic examination and fatigue performance test;
(1) metallographic examination
Adopting an aluminum alloy plate with the same technological parameters as those of the airplane landing gear beam to be sprayed and repaired as a metallographic examination sample piece, and spraying an aluminum layer with a set thickness as a spraying layer; performing metallographic examination on more than two sample blocks cut by the metallographic examination sample piece by referring to standard HB20195 of the metallographic examination; the detection result is qualified when the content, porosity and hardness of the oxides in the spraying layers of more than two sample blocks are all within the set threshold value;
(2) fatigue property test
The method comprises the following steps of adopting an aluminum alloy plate with the same technological parameters as those of an airplane landing gear beam to be sprayed and repaired as a fatigue test piece, machining a groove with a set size at the middle position of one side of the fatigue test piece, prefabricating a crack with a set length at the groove after machining is completed, and simulating a crack area on the airplane landing gear beam; and (3) carrying out fatigue test by adopting a stress spectrum of the landing gear beam, and regarding the test result as qualified by taking not less than 180 spectrum blocks on the stress spectrum of more than two fatigue test pieces.
Preferably, the helium with the purity not lower than 99.999 percent is selected as the spraying working gas in the sixth step.
Preferably, an aluminium alloy powder corresponding to the material and strength of the aircraft landing gear beam to be spray repaired is used.
Preferably, before spraying in the sixth step, a positioning tool is adopted for adjustment and the spraying area is confirmed.
Preferably, the number of the cold spraying equipment, the helium gas batch number and the material and batch number of the spraying powder used in the step six are recorded, and the number of the cold spraying equipment, the helium gas batch number or the material and batch number of the spraying powder are used for exchanging the number of the spraying equipment, the helium gas batch number or the spraying powder batch number or the material of the spraying powder in real time according to actual needs.
Preferably, the surface polishing in the seventh step is realized by controlling the surface roughness to be smaller than a set value.
Preferably, the surface grinding in step seven is performed by a hand-held pneumatic or electric grinding tool.
Has the advantages that:
(1) the cold spraying technology is adopted to spray the spraying layer with the set size on the airplane landing gear beam crack area, and the bonding degree, the strength and the hardness of the spraying layer sprayed on the airplane landing gear beam crack area according to the repairing method are higher, so that the airplane landing gear beam crack area forms a stress layer with the set thickness, the stress layer is used for offsetting load stress borne by the airplane landing gear beam crack area, the propagation rate of airplane landing gear beam cracks can be effectively reduced, the fatigue resistance of the airplane landing gear beam is improved, the service life of an airplane is prolonged, and powerful guarantee is provided for army combat training.
(2) The method sprays the strengthening layer with set thickness on the crack path of the crack area of the aircraft landing gear beam, can further slow down the crack propagation rate of the crack area of the aircraft landing gear beam, and further improves the fatigue resistance of the aircraft landing gear beam.
Drawings
FIG. 1 is a schematic view of a fatigue test specimen according to the present invention, wherein (a) is a front view and (b) is a plan view.
FIG. 2 is a schematic view of the separation of the crack zone of the landing gear beam of the aircraft of the present invention.
FIG. 3 is a schematic view of the pre-aircraft spray area and spray coating of the landing gear beam of the present invention.
FIG. 4 is a schematic illustration of the post-aircraft spray area and spray coating of the landing gear beam of the present invention.
Figure 5 is a cross-sectional view a-a of the inventive aircraft landing gear beam at the area of the crack in figure 4.
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
The embodiment provides an in-situ strengthening repair method for airplane landing gear beam cracks, which is characterized in that a cold spraying technology is adopted to spray a spraying layer with a set thickness on a crack area of the airplane landing gear beam, so that the propagation rate of the airplane landing gear beam cracks can be effectively reduced, the fatigue resistance of the airplane landing gear beam is improved, and the service life of an airplane is prolonged.
The method for repairing the cracks of the aircraft landing gear beam in the in-situ strengthening mode comprises the following steps:
the method comprises the following steps: metallographic examination and fatigue performance test before spray repair
According to the technical requirements of cold spraying, before carrying out aircraft spraying repair in batches, preparing a metallographic examination sample piece and more than two fatigue test pieces, and carrying out metallographic examination and fatigue performance test;
(1) metallographic examination
Adopting an aluminum alloy plate with the same technological parameters as those of the airplane landing gear beam to be sprayed and repaired as a metallographic examination sample piece, and spraying an aluminum layer with the thickness of 5mm as a spraying layer; cutting a metallographic examination sample piece into more than two sample blocks for metallographic examination according to standard HB20195 of the metallographic examination; the inspection result is qualified when the content, porosity and hardness of the oxides in the spraying layers of more than two sample blocks are all in the set range;
(2) fatigue property test
As shown in fig. 1, an aluminum alloy plate with the same technological parameters as those of the airplane landing gear beam to be sprayed and repaired is used as a fatigue test piece, a groove with the width of 1mm and the depth of 3mm is processed at the middle position of one side of the fatigue test piece, cracks with the length of about 5mm are prefabricated at the groove after the processing is finished and are used for simulating crack regions on the airplane landing gear beam, and aluminum alloy spraying layers with the length of 80mm, the width of 40mm and the thickness of more than 5mm are symmetrically sprayed on two sides of the fatigue test piece by adopting the same equipment, working personnel and technological parameters as those of the airplane landing gear beam during spraying and repairing, and are used for respectively simulating spraying and repairing of the airplane landing gear beam before and after the voyage; the stress spectrum of the landing gear beam is adopted for carrying out fatigue test, and the test result is qualified by taking the stress spectrum of more than two fatigue test pieces as no less than 180 spectrum blocks;
step two: dismantling
Dismantling non-bearing parts (such as a fuel tank port cover, a screw, a guide pipe and the like) which obstruct the spraying construction operation on the aircraft landing gear;
step three: cleaning before spray repair
Because the landing gear beam passes through the wing oil tank, the landing gear beam crack area is positioned in the wing oil tank, oil stain in the landing gear beam crack area in the wing oil tank is cleaned by gasoline, sealant and a paint layer in the landing gear beam crack area are removed by chemical solvent until the residues of the sealant and the paint layer are completely removed, and an anodic oxidation layer on the surface of the landing gear beam crack area is removed by polishing and cleaned;
step four: protection
Protecting the inside of the crack region of the airplane landing gear beam to be sprayed and repaired (such as covering by plastic cloth and other covering objects), and preventing dust from falling into the crack region of the airplane landing gear beam during spraying; integrally plugging an area containing structures such as pipelines and components and the like and covering and protecting the periphery of the area, so as to prevent dust from entering the structures such as the pipelines and the components and the like during spraying; as shown in fig. 2, the crack zone of the aircraft landing gear beam to be sprayed and repaired is divided into two zones of the front part (located at the front end in the sailing direction) and the back part (located at the back end in the sailing direction) by taking the landing gear beam as a boundary, and the two zones of the front part and the back part are respectively isolated and protected; the HM109 modified polysulfide sealant is adopted to seal and plug the holes of the aircraft landing frame beam and the reinforcing rib of the upper wall plate, so that the pollution influence on another area is prevented when spraying is carried out before or after the aircraft is in use;
step five: sand blasting
After checking and confirming that all protection and plugging in the fourth step are finished, carrying out sand blasting pretreatment on a region to be sprayed (a pre-aviation region and/or a post-aviation region isolated from a crack region of an airplane landing frame beam) by adopting sand blasting dust removing equipment, and absorbing sand grains in the region to be sprayed by adopting an industrial dust collector after sand blasting is finished so as to achieve the aims of roughening the region to be sprayed and cleaning the surface of the region to be sprayed;
step six: adhesive temperature sensor
Respectively sticking patch type temperature sensors on the back and the side of a region to be sprayed of the aircraft landing gear beam, and monitoring the temperature change in the region to be sprayed in real time;
step seven: spraying of paint
As shown in fig. 3-5, by using a machine-used movable cold spraying device, an industrial robot is used to clamp a spray gun to respectively spray a spraying layer (such as 5mm) with a set thickness before and after the aircraft of a beam crack region of an aircraft landing gear to be sprayed and repaired, and a set grinding allowance is reserved, so that the beam crack region of the aircraft landing gear forms a stress layer with a set thickness for offsetting load stress borne by the beam crack region of the aircraft landing gear, the propagation rate of the beam crack of the aircraft landing gear can be effectively reduced, and the fatigue resistance of the beam of the aircraft landing gear is improved; real-time air draft and dust removal are ensured in the spraying process;
in the whole spraying process, the surface mount type temperature sensor in the step six is used for monitoring the temperature of the spraying area of the aircraft landing gear beam in real time, so that the surface temperature of the aircraft landing gear beam is always lower than the set temperature;
helium with the purity not lower than 99.999 percent is selected as spraying working gas, so that a better spraying effect can be achieved;
the spraying powder is selected from aluminum alloy powder with good matching degree with the airplane landing gear beam to be sprayed and repaired, wherein the good matching degree of the aluminum alloy powder and the airplane landing gear beam to be sprayed and repaired is based on that the material components of the aluminum alloy powder and the airplane landing gear beam are similar and the mechanical strength of the airplane landing gear beam is in a set threshold value after the aluminum alloy powder and the airplane landing gear beam are combined;
step eight: polishing
After spraying, placing the aircraft landing gear beam for a set time for fully combining the spraying layer with the aircraft landing gear beam and polishing the surface of the spraying layer smoothly;
step nine: cleaning the residue
After polishing, sucking dust, sand and metal chips in the spraying area by using a dust collector, removing spraying operation tools and equipment on the machine, and removing the protective objects in the spraying area until no residue exists on the inspection machine;
step ten: restoring surface protective layers
Coating 1200S alodine on the surface of a spraying layer of the aircraft landing frame beam and a paint removing area in the third step, oxidizing the alodine, coating two layers of S06-0215 polyurethane primers, and coating HM109 modified polysulfide sealant on the surface for sealing protection after drying;
step eleven: reinstalling installation
Restoring the non-bearing parts removed in the mounting step II;
step twelve: post-spray cleaning
Removing pollutants caused by spraying operation on the aircraft landing gear beam;
step thirteen: examination of
The thickness, the roughness and the pollutants of the sprayed layer of the aircraft landing gear beam are respectively detected, and the aircraft landing gear beam is ensured to meet the machine requirements.
Fourteen steps: metallographic examination and fatigue performance test are carried out after spray repair
According to the technical requirements of cold spraying, after a batch of airplane spraying repair is carried out, preparing a metallographic examination sample piece and more than two fatigue test pieces, and carrying out metallographic examination and fatigue performance test by adopting the same equipment, working personnel and process parameters as those of the airplane landing gear beam during repair, wherein the specific operation refers to the step one;
further, for the spraying in the seventh step, a reinforcing layer with a set thickness (such as 4mm) is added to the crack path of the crack area for reinforcing the crack path.
Further, a positioning tool is adopted to adjust and confirm the spraying area (for example, a positioning die is adopted to fit a crack area as the spraying area) before the spraying layer in the step seven is sprayed, so that the spraying layer is ensured to meet the design requirement.
And further, the temperature monitoring in the step seven is realized by controlling the spraying interval time and the air supply volume of the mobile aircraft maintenance air conditioner.
Further, the serial number of the movable cold spraying equipment, the serial number of the helium gas batch and the material and the serial number of the spraying powder used in the step seven are recorded, so that the serial numbers of other spraying equipment, the serial numbers of the helium gas batch, the serial numbers of the spraying powder batch or the spraying powder material can be conveniently exchanged in real time according to actual needs.
Furthermore, the air draft dust removal in the seventh step is realized by connecting industrial dust collection equipment outside the aircraft landing gear beam (such as the openings of the six-rib web plate and the eight-rib web plate of the central wing), so that the air circulation in the operation space is ensured, the disturbance of the dust carrying gas is prevented from influencing the deposition of the subsequent spraying powder, the residual powder can be timely pumped away, and meanwhile, the aim of cooling the spraying area is fulfilled.
Further, for the surface polishing in the step eight, the surface roughness Ra is controlled to be smaller than a set value (such as 3.2 μm), the substrate cannot be damaged in the polishing process, and the sprayed layer cannot be knocked.
Further, aiming at the surface grinding in the step eight, a handheld pneumatic or electric grinding tool is adopted, and the surface is ground and then is finished by combining manual sand paper.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. An in-situ reinforced repairing method for the cracks of the landing gear beam features that the sprayed layer with predefined size is directly sprayed on the crack region of the landing gear beam to repair the cracks.
2. An aircraft landing gear beam crack in-situ strengthening repair method according to claim 1, wherein the step of spraying the sprayed layer comprises:
the method comprises the following steps: dismantling
Dismantling non-bearing parts on the aircraft landing gear, which hinder the spraying construction operation;
step two: cleaning before spray repair
Cleaning the interior of a wing oil tank, removing a sealant and a paint layer in a crack area of an aircraft landing gear beam, removing an anodic oxidation layer on the surface of the aircraft landing gear beam, and cleaning;
step three: protection
Covering and protecting the interior of the crack area of the airplane landing gear beam to be sprayed and repaired; plugging and covering protection are carried out on an area containing a pipeline and an element structure; dividing the crack area of the airplane landing gear beam to be sprayed and repaired into a pre-aviation area and a post-aviation area by taking the airplane landing gear beam as a boundary, respectively carrying out isolation protection on the pre-aviation area and the post-aviation area, and sealing and plugging the holes of reinforcing ribs of the airplane landing gear beam and an upper wall plate;
step four: sand blasting
After checking and confirming that all protection and plugging are finished in the third step, carrying out sand blasting pretreatment on the area to be sprayed, and absorbing sand grains in the area to be sprayed after sand blasting is finished so as to enable the area to be sprayed to be roughened and the surface of the area to be sprayed to be free of pollution;
step five: adhesive temperature sensor
Respectively sticking patch type temperature sensors on the back and the side of a region to be sprayed of the aircraft landing gear beam, and monitoring the temperature change in the region to be sprayed in real time;
step six: spraying of paint
Spraying a spraying layer with a set thickness before and after the spraying of the area to be sprayed by adopting cold spraying equipment, and reserving a set polishing allowance, so that real-time air draft and dust removal are ensured in the spraying process;
in the whole spraying process, the surface mount type temperature sensor in the step five is used for monitoring the temperature of the spraying area of the aircraft landing gear beam in real time, so that the surface temperature of the aircraft landing gear beam is always lower than a set value;
step seven: polishing
After spraying, placing the aircraft landing gear beam for a set time, and polishing the surface of the spraying layer to be smooth;
step eight: cleaning the residue
After polishing, absorbing and removing dust, sand and metal chips in the spraying area, dismantling spraying operation tools and equipment on the machine, and dismantling the protective objects in the spraying area until no residue exists on the inspection machine;
step nine: restoring surface protective layers
Coating a machine oxide layer on the surface of the spraying layer of the aircraft landing frame beam and the paint removing area in the second step, oxidizing, coating two layers of machine paint, and sealing and protecting the surface after drying;
step ten: reinstalling installation
Restoring the non-bearing parts removed in the first installation step;
step eleven: post-spray cleaning
Removing pollutants caused by spraying operation on the aircraft landing gear beam;
step twelve: examination of
The thickness, the roughness and the pollutants of the sprayed layer of the aircraft landing gear beam are respectively detected, and the aircraft landing gear beam is ensured to meet the machine requirements.
3. An aircraft landing gear beam crack in situ reinforcement repair method according to claim 1 or 2, further comprising: and spraying a reinforcing layer with a set thickness on the spraying layer along the crack path.
4. The method for in-situ reinforced repair of cracks in an aircraft landing gear beam according to claim 1 or 2, wherein before spray repair of the first aircraft and after spray repair of the last aircraft in a batch of aircraft, a metallographic specimen and more than two fatigue test pieces are prepared respectively, and metallographic examination and fatigue performance tests are performed;
(1) metallographic examination
Adopting an aluminum alloy plate with the same technological parameters as those of the airplane landing gear beam to be sprayed and repaired as a metallographic examination sample piece, and spraying an aluminum layer with a set thickness as a spraying layer; performing metallographic examination on more than two sample blocks cut by the metallographic examination sample piece by referring to standard HB20195 of the metallographic examination; the detection result is qualified when the content, porosity and hardness of the oxides in the spraying layers of more than two sample blocks are all within the set threshold value;
(2) fatigue property test
The method comprises the following steps of adopting an aluminum alloy plate with the same technological parameters as those of an airplane landing gear beam to be sprayed and repaired as a fatigue test piece, machining a groove with a set size at the middle position of one side of the fatigue test piece, prefabricating a crack with a set length at the groove after machining is completed, and simulating a crack area on the airplane landing gear beam; and (3) carrying out fatigue test by adopting a stress spectrum of the landing gear beam, and regarding the test result as qualified by taking not less than 180 spectrum blocks on the stress spectrum of more than two fatigue test pieces.
5. An in situ reinforced repair method for cracks in an aircraft landing gear beam as claimed in claim 2, wherein in step six the sprayed working gas is helium with a purity of not less than 99.999%.
6. A method for in situ reinforced repair of aircraft landing gear beam cracks according to claim 1 or claim 2, wherein aluminium alloy powder is used which corresponds to the material and strength of the aircraft landing gear beam to be spray repaired.
7. An aircraft landing gear beam crack in-situ strengthening repair method according to claim 1 or 2, wherein in step six, a positioning tool is used for adjusting and confirming the spraying area before spraying.
8. The method for in-situ reinforced repair of cracks in an aircraft landing gear beam as claimed in claim 2, wherein the cold spraying equipment number, helium batch number and material and batch number of the sprayed powder used in the step six are recorded for exchanging the spraying equipment number or helium batch number or the sprayed powder material in real time according to actual needs.
9. An aircraft landing gear beam crack in-situ strengthening repair method according to claim 2, wherein the surface grinding in step seven is performed by controlling the surface roughness to be less than a set value.
10. An aircraft landing gear beam crack in-situ strengthening repair method according to claim 2, wherein in step seven the surface grinding is performed using a hand-held pneumatic or electric grinding tool.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911145856.7A CN111036520A (en) | 2019-11-21 | 2019-11-21 | Method for in-situ reinforced repairing of airplane landing gear beam cracks |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911145856.7A CN111036520A (en) | 2019-11-21 | 2019-11-21 | Method for in-situ reinforced repairing of airplane landing gear beam cracks |
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| Publication Number | Publication Date |
|---|---|
| CN111036520A true CN111036520A (en) | 2020-04-21 |
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| CN201911145856.7A Pending CN111036520A (en) | 2019-11-21 | 2019-11-21 | Method for in-situ reinforced repairing of airplane landing gear beam cracks |
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| CN111942613A (en) * | 2020-07-16 | 2020-11-17 | 国营芜湖机械厂 | In-situ corrosion prevention process for airplane aluminum alloy component after crack cold spraying reinforcement repair |
| CN112171383A (en) * | 2020-09-03 | 2021-01-05 | 国营芜湖机械厂 | Surface pretreatment method for in-situ repair of on-board cold spraying |
| CN112522695A (en) * | 2020-10-06 | 2021-03-19 | 湖北超卓航空科技股份有限公司 | Method for repairing fatigue crack by cold spraying |
| CN112518157A (en) * | 2020-11-25 | 2021-03-19 | 中国航空工业集团公司沈阳飞机设计研究所 | Temperature control method for high-speed jet material increase repair of aluminum alloy structure |
| CN114346597A (en) * | 2021-12-17 | 2022-04-15 | 国营芜湖机械厂 | Remanufacturing and repairing process for aluminum alloy filter screen bracket of aircraft fuel electric pump |
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| CN111942613A (en) * | 2020-07-16 | 2020-11-17 | 国营芜湖机械厂 | In-situ corrosion prevention process for airplane aluminum alloy component after crack cold spraying reinforcement repair |
| CN112171383A (en) * | 2020-09-03 | 2021-01-05 | 国营芜湖机械厂 | Surface pretreatment method for in-situ repair of on-board cold spraying |
| CN112522695A (en) * | 2020-10-06 | 2021-03-19 | 湖北超卓航空科技股份有限公司 | Method for repairing fatigue crack by cold spraying |
| CN112522695B (en) * | 2020-10-06 | 2023-02-28 | 湖北超卓航空科技股份有限公司 | Method for repairing fatigue crack by cold spraying |
| CN112518157A (en) * | 2020-11-25 | 2021-03-19 | 中国航空工业集团公司沈阳飞机设计研究所 | Temperature control method for high-speed jet material increase repair of aluminum alloy structure |
| CN114346597A (en) * | 2021-12-17 | 2022-04-15 | 国营芜湖机械厂 | Remanufacturing and repairing process for aluminum alloy filter screen bracket of aircraft fuel electric pump |
| CN114346597B (en) * | 2021-12-17 | 2023-04-14 | 国营芜湖机械厂 | Remanufacturing and repairing process for aluminum alloy filter screen bracket of aircraft fuel electric pump |
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Application publication date: 20200421 |