CN119460147A - A method for repairing aircraft wall panels by layered damage - Google Patents
A method for repairing aircraft wall panels by layered damage Download PDFInfo
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- CN119460147A CN119460147A CN202411490930.XA CN202411490930A CN119460147A CN 119460147 A CN119460147 A CN 119460147A CN 202411490930 A CN202411490930 A CN 202411490930A CN 119460147 A CN119460147 A CN 119460147A
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- frame
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- crack
- milling
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B43/00—Operations specially adapted for layered products and not otherwise provided for, e.g. repairing; Apparatus therefor
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P6/00—Restoring or reconditioning objects
- B23P6/04—Repairing fractures or cracked metal parts or products, e.g. castings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B43/00—Operations specially adapted for layered products and not otherwise provided for, e.g. repairing; Apparatus therefor
- B32B43/003—Cutting
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/26—Attaching the wing or tail units or stabilising surfaces
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/20—Integral or sandwich constructions
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/40—Maintaining or repairing aircraft
-
- 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
- B05D2503/00—Polyurethanes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P2700/00—Indexing scheme relating to the articles being treated, e.g. manufactured, repaired, assembled, connected or other operations covered in the subgroups
- B23P2700/01—Aircraft parts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2255/00—Coating on the layer surface
- B32B2255/26—Polymeric coating
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2605/00—Vehicles
- B32B2605/18—Aircraft
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Life Sciences & Earth Sciences (AREA)
- Wood Science & Technology (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
Abstract
The invention provides a layered damage repair method for an aircraft panel, which takes a crack as a reference, wherein the crack is close to the inner side of a mouth frame, a mouth frame flange crack is completely removed at the inner side of the mouth frame along a direction parallel to the crack, the mouth frame flange crack is completely removed at the outer side of the mouth frame along a direction parallel to the crack if the crack is close to the outer side of the mouth frame, nondestructive detection is carried out on a mouth frame part, an oxidizing liquid is coated on the mouth frame part, a backing plate part is manufactured if a milling part is positioned at the inner side of the mouth frame, yellow anodization is carried out on the backing plate part, polyurethane primer is sprayed on the backing plate part, a mouth cover press ring part is manufactured if the milling part is positioned at the outer side of the mouth frame, milling is carried out on the mouth cover press ring part, the original mouth cover press ring part is replaced, sealant is coated on the milling part if the milling part is positioned at the inner side of the mouth frame, the contact surface of the backing plate part and the mouth frame milling part is then installed at the mouth frame milling part. The response time of quick repair of the outfield can be reduced, and the safety and reliability of the aircraft can be improved.
Description
Technical Field
The invention belongs to the technical field of aircraft wing structure repair, and particularly relates to a layered damage repair method for an aircraft wallboard.
Background
With the rapid development of aviation industry digital design and manufacturing technology, the aircraft structural design has largely adopted integral structural design, and an aircraft integral oil tank is an important structural component of an aircraft, so that if the aircraft integral oil tank is damaged and leaked in use, serious consequences are easily caused, the integral oil tank has extremely high tightness, meanwhile, the aircraft integral oil tank needs to be kept in good appearance and participates in integral stress of the aircraft, so that the maintenance and repair problems of the aircraft integral oil tank are solved well, the maintenance and repair time is shortened, and the aircraft integral oil tank has very important significance in improving the utilization rate of the aircraft, reducing the hidden flight trouble and reducing the maintenance and repair cost. The wall plate of the integral oil tank integrates the wing skin, the stringers, the studs, the butt joints and other attachable structural members (such as an oil filling port frame, an inspection port frame and the like) into a whole for integrally processing and forming. The wall plate has a complex structure, the surface of the part is a curved surface, and the required material blank is thicker, so that a method and a technological method of firstly flat plate machining and then integral bending forming are adopted, but the bending forming is a very complex elastoplastic deformation process, and the residual stress of the wall plate in the rebound process is still larger at the top and the root of the rib. Along with the increasingly severe service environment (humid sea atmosphere, heavy salt fog, large sea surface wind wave, large temperature difference and the like) of the aircraft, the material is more sensitive to stress corrosion cracking under severe corrosion specific conditions, so that stress corrosion cracks appear on the wallboard inspection opening frame.
The whole wallboard of the aircraft wing is the same as the aircraft in service life, the wallboard is usually provided with an elliptical maintenance flap, when a gap frame is cracked, the traditional repairing method is to cut off the section of the wallboard with the crack, or specially-made sealing elements, or replace a whole new wallboard, but the cut-off of the wallboard breaks the main force transmission path of the whole wallboard, the specially-made sealing elements are required to be opened again, the cost is high, the replacement of the new wallboard has high safety risks that the sealant at the sealing rib is difficult to degum, the deformation of a wing box can be caused after the cracked wallboard is removed, the new assembly fixture is required to ensure the wing box is required to be removed, and after the new wallboard is replaced, the butt joint two end faces of the wing box section are required to be finished again, so that the aperture of a connecting part is out of tolerance and the like, and the flying safety hidden trouble exists.
Disclosure of Invention
In order to solve the problems that when an aircraft frame in the prior art is cracked, a main force transmission path is broken due to the fact that a wallboard is cut off, the cost of a special sealing piece is high, and a large risk is brought by replacing a whole new wallboard, the invention provides a method for repairing the crack of the aircraft frame, the structural force transmission path is not changed, the strength design requirement is met, and the problems that the cut-off wallboard breaks the force transmission path, the cost of the special sealing piece is high, and the whole wallboard is replaced to bring safety risk are solved. The method is simple, convenient and quick, reduces the quick repair response time of the outfield, and improves the safety and reliability of the aircraft. The technical scheme is as follows:
In a first aspect, a method for repairing layered damage to an aircraft panel is provided, the method comprising:
Step1, taking a crack as a reference, completely removing the crack of the flange of the mouth frame on the inner side of the mouth frame along the direction parallel to the crack by milling if the crack is close to the inner side of the mouth frame, and chamfering two ends of the mouth frame after the crack is removed;
step 2, performing nondestructive testing on the removed mouth frame part, and if the flaw detection result is good and no internal damage or surface damage exists, executing step 3;
Step 3, coating an oxidizing solution on the removed mouth frame part, and then spraying a plurality of layers of polyurethane priming paint;
Step 4, if the milling part is positioned at the inner side of the mouth frame, manufacturing 1 backing plate part, wherein the shape of the backing plate part is matched with the milling shape at the inner side of the mouth frame, spraying a layer of polyurethane primer after yellow anodizing the backing plate part, if the milling part is positioned at the outer side of the mouth frame, manufacturing 1 mouth cover press ring part, milling the mouth cover press ring part to enable the inner side of the mouth cover press ring part to be locally thickened and matched with the milling shape at the outer side of the mouth frame, and replacing the original mouth cover press ring part with the mouth cover press ring part after milling, wherein the repairing work under the condition is finished;
step 5, if the milling part is positioned at the inner side of the mouth frame, coating a layer of sealant on the milling part of the mouth frame;
and 6, coating a layer of sealant on the contact surface of the backing plate part and the mouth frame milling part to ensure the sealing of the oil tank, and then installing the backing plate part on the mouth frame milling part.
Further, the method further comprises:
and 7, carrying out strength evaluation on the repaired wallboard mouth frame structure, judging whether the strength requirement is met, and if the strength requirement is met, determining that the wallboard mouth frame structure is successfully repaired.
Optionally, in step 7,
When the strength evaluation is carried out on the repaired wallboard mouth frame structure, the mouth frame is simplified into a beam element, the maximum axial force F=Sigma A eq at the mouth frame is calculated firstly, and then the maximum axial stress sigma 2＝F/Aeq 'at the mouth frame after repair is calculated according to the equivalent axial pulling and pressing sectional area A eq' of the mouth frame after repair, so that the safety margin M.S=Sigma 0.2/σ2 -1 is calculated based on the maximum axial stress at the mouth frame, and if the safety margin M.S is greater than 0, the success of the repair of the wallboard mouth frame structure is determined;
Where σ represents the tensile stress at the aperture frame, A eq represents the original aperture frame axial tension-compression equivalent cross-sectional area, and σ 0.2 represents the yield limit of the aperture frame material.
Optionally, in the step 1, rounded corners at two ends of the rear mouth frame are removed to be R10.
Optionally, in step 2, the nondestructive testing method is eddy current and ultrasonic flaw detection.
Optionally, the polyurethane primer in the step 3 and the step 4 is an S06-1010H polyurethane primer.
Optionally, the sealant in step 5 and step 6 is an XM-22 sealant.
Optionally, in step 6, the shim plate part is installed at the mouth frame milling location by a double-sided countersunk ring groove seal rivet.
Optionally, in step 4, the material of the backing plate part is the same as the material of the wall plate, and the material of the flap press ring part is the same as the material of the original flap press ring part.
The invention has the advantages that:
The repairing method of the invention specially prepares a backing plate part made of the same material as the wallboard or a flap pressing ring part similar to the original flap pressing ring. The structure force transmission route is not changed, the strength design requirement is met, and the problems that the cut-off wallboard breaks the force transmission route, the cost of a special sealing piece is high, and the whole wallboard is replaced to bring safety risks are solved. The method is simple, convenient and quick, reduces the quick repair response time of the outfield, and improves the safety and reliability of the aircraft.
Drawings
FIG. 1 is a partial schematic view of an inspection aperture frame for an upper panel of a wing;
FIG. 2 is a schematic illustration of an exemplary wing upper panel hatch mating;
FIG. 3 is a view of the smallest cross-sectional dimension of the reinforcing aperture frame;
FIG. 4 is a graph of crack length and depth;
FIG. 5 illustrates crack location and grinding;
FIG. 6 is a mouth frame milling area;
FIG. 7 is a schematic diagram of a shim plate part;
FIG. 8 is a schematic view of the connection of a wall plate to a backing plate component;
FIG. 9 is a schematic view of a flap press ring part;
FIG. 10 is a flow chart of a method for repairing layered damage to aircraft panels according to the present invention.
Detailed Description
The invention is described in further detail below with reference to specific embodiments and figures.
Referring to fig. 10, an embodiment of the present invention provides a method for repairing layered damage to an aircraft panel, the method comprising the steps of:
Step1, taking a crack as a reference, completely removing the crack of the flange of the mouth frame on the inner side of the mouth frame along the direction parallel to the crack by milling if the crack is close to the inner side of the mouth frame, and chamfering two ends of the mouth frame after the crack is removed;
step 2, performing nondestructive testing on the removed mouth frame part, and if the flaw detection result is good and no internal damage or surface damage exists, executing step 3;
Step 3, coating an oxidizing solution on the removed mouth frame part, and then spraying a plurality of layers of polyurethane priming paint;
Step 4, if the milling part is positioned at the inner side of the mouth frame, manufacturing 1 backing plate part, wherein the shape of the backing plate part is matched with the milling shape at the inner side of the mouth frame, spraying a layer of polyurethane primer after yellow anodizing the backing plate part, if the milling part is positioned at the outer side of the mouth frame, manufacturing 1 mouth cover press ring part, milling the mouth cover press ring part to enable the inner side of the mouth cover press ring part to be locally thickened and matched with the milling shape at the outer side of the mouth frame, and replacing the original mouth cover press ring part with the mouth cover press ring part after milling, wherein the repairing work under the condition is finished;
step 5, if the milling part is positioned at the inner side of the mouth frame, coating a layer of sealant on the milling part of the mouth frame;
and 6, coating a layer of sealant on the contact surface of the backing plate part and the mouth frame milling part to ensure the sealing of the oil tank, and then installing the backing plate part on the mouth frame milling part.
Example 1:
the crack description is that the oil tank inspection port frame (material: 1973T 2) with 4 ribs to 5 ribs of the upper wall plate of the right wing is shown in fig. 1 and 2, the typical circumferential cross section is shown in fig. 3, obvious circumferential cracks are found on the side end faces, and through eddy current and ultrasonic flaw detection, the initial judgment of crack failure conditions is as follows (1) the crack length is about 100mm, the maximum depth is about 15mm, the depths of the rest parts except the two ends are uniform, the minimum distance between the crack and the end faces of the stringer is 18mm, the crack is about 9mm from the upper surface of the port frame, the crack is about 6mm from the lower surface of the port frame, and the heights of the side end faces of the port frame from the upper surface and the lower surface are basically unchanged along the circumferential direction of the port frame, as shown in fig. 5.
Taking the crack as an example, the method for repairing the layered damage of the aircraft panel provided by the invention specifically comprises the following steps:
1) According to the position of the crack, taking the crack as a reference, completely milling the crack of the flange of the mouth frame on the inner side of the mouth frame along the direction parallel to the crack, milling the depth direction of the crack according to 19mm, and smoothly transiting the sharp angle R4;
2) After milling the flange of the mouth frame, carrying out nondestructive testing on the milling part, and if no internal damage and surface damage exist, continuing to execute according to the scheme, and if the damage exists, carrying out 1) again;
3) After inspection, coating oxidizing liquid on the milled part, and then spraying a plurality of layers of S06-1010H polyurethane priming paint;
4) 1 pad part is specially made according to the figure 7, the specially made pad material is 1973T2, the shape is determined according to the spanwise milling size, and after the pad is yellow anodized, the pad is coated with S06-1010H polyurethane primer;
5) Coating a layer of XM-22 sealant on the milling part of the mouth frame;
6) Before the base plate and the wallboard mouth frame are installed, the contact surface is coated with a layer of XM-22 sealant according to related technical conditions (such as the technical conditions for manufacturing the central wing, the middle and outer wing integral oil tank, and the like) to ensure the oil tank to be sealed.
7) The special backing plate part is connected with the mouth frame in a leveling mode according to the mode shown in fig. 8, the special backing plate part is connected with the mouth frame in a leveling mode through 5 ring groove sealing rivets with double-sided countersunk heads, the edge distance of the rivets at two ends in the length direction of a crack is 9mm, the middle of the rivets is 4 mm, the edge distance of the rivets in the depth direction of the crack is 7mm, redundant sealant at the mouth frame is removed after the backing plate is connected, and the rivets are manufactured according to the conditions that the angle is 90 degrees when the mouth frame and the metal sealing ring are countersunk, the countersunk diameter D=5 mm and the depth is smaller than 1.7 mm. In order to ensure the installation of the sealing ring, the double-buried rivet is smooth and flat after being connected, has no burrs and is flush with the original opening frame. And when the countersink phi 5 is performed, the part of the inlet frame R area is smoothly transited.
8) Intensity analysis
When the strength evaluation is carried out on the repaired wallboard mouth frame structure, the mouth frame is simplified into a beam element, the maximum axial force F=Sigma A eq at the mouth frame is calculated firstly, and then the maximum axial stress sigma 2＝F/Aeq 'at the mouth frame after repair is calculated according to the equivalent axial pulling and pressing sectional area A eq' of the mouth frame after repair, so that the safety margin M.S=Sigma 0.2/σ2 -1 is calculated based on the maximum axial stress at the mouth frame, and if the safety margin M.S is greater than 0, the success of the repair of the wallboard mouth frame structure is determined;
Wherein sigma represents the tensile stress at the mouth frame, A eq represents the axial pulling and pressing equivalent sectional area of the original mouth frame, and sigma 0.2 represents the yield limit of the mouth frame material.
A) Qualitative analysis:
The upper wall plate of the outer wing No. 2 is an integral machined part in the influence analysis, the material is 1973T2,
(Σ 0.2 =441 MPa), and the specific structure is shown in fig. 1.
As can be seen from FIG. 1, the two stringers of the wing are broken at both sides of the frame to transfer the load of the stringers and the load of the wall panels, so that the inspection frame is locally reinforced, the minimum cross-sectional dimension of the reinforced portion of the inspection frame is as shown in FIG. 3, and the reinforced inspection frame is mainly subjected to axial tension.
As can be seen from FIG. 5, the milled area is located near the center line of the frame, where it mainly acts to secure the inspection flap and is mainly subjected to the tensile and compressive stresses in the axial direction of the frame.
After the crack area is milled, the sectional area of the mouth frame is reduced, and the axial tensile stress of the mouth frame is increased.
B) Intensity evaluation:
specifically, the intensity evaluation includes the steps of:
1. Calculating the maximum axial force at the mouth frame:
Through a checked file of a finite element model and stress analysis of an outer wing in a certain type of airplane, the maximum axial tensile stress sigma= 137.93MPa and the maximum axial compressive stress sigma= 254.72MPa of the finite element full machine solution at the mouth frame.
As can be seen from fig. 3, the minimum cross-sectional area of the reinforcing frame:
A=A1+A2+A3＝(33-4.3-15)×21+15×(19+21)+4.3×(19-14+21)＝999.5mm2。
Cross-section centroid:
Cross-sectional bottom is located at a distance of 0 = 74.37mm from the chord line, equivalent cross-sectional area:
Aeq＝A×((18.15+74.37)/(33+74.37))2＝731.6mm2。
maximum axial force f=σa eq = 254.72 × 731.6 = 186353.15N at the mouth frame.
2. Calculating the equivalent sectional area after repair:
from fig. 5, it can be seen that the minimum cross-sectional area of the rear aperture frame is milled:
A'=A1'+A2'+A3'=21×(33-4.3-15+6)+(19+21)×(15-6)+(21+19-14)
×4.3=885.50mm2。
Cross-section centroid:
equivalent cross-sectional area:
Aeq'＝A'×((18.34+74.37)/(33+74.37))2＝660.20mm2。
The calculation shows that the minimum cross-sectional area of the mouth frame is reduced by 11.41 percent, and the minimum equivalent cross-sectional area of the mouth frame is reduced by 9.76 percent.
3. Calculating the maximum axial force and safety margin M.S after repair
σ2＝F/Aeq'=186353.15/660.20=282.27MPa。
M.S=σ0.2/σ2-1=441/282.27-1=0.56。
Meets the strength design requirement, and the wall plate and mouth frame structure is successfully repaired.
If the crack is near the outside of the mouth frame, the mouth cover compression ring part can be specially manufactured according to the figure 9 for repairing.
The foregoing has outlined rather broadly the more detailed description of the invention in order that the detailed description thereof that follows may be better understood, and in order that the present invention may be better understood. It should be noted that it will be apparent to those skilled in the art that several variations and modifications can be made without departing from the spirit of the invention, which are all within the scope of the invention. In addition, the invention is not fully described in the conventional technology.
Claims (9)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202411490930.XA CN119460147A (en) | 2024-10-24 | 2024-10-24 | A method for repairing aircraft wall panels by layered damage |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202411490930.XA CN119460147A (en) | 2024-10-24 | 2024-10-24 | A method for repairing aircraft wall panels by layered damage |
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| CN119460147A true CN119460147A (en) | 2025-02-18 |
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| CN202411490930.XA Pending CN119460147A (en) | 2024-10-24 | 2024-10-24 | A method for repairing aircraft wall panels by layered damage |
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Citations (8)
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|---|---|---|---|---|
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2024
- 2024-10-24 CN CN202411490930.XA patent/CN119460147A/en active Pending
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| US20090130327A1 (en) * | 2006-05-26 | 2009-05-21 | Airbus Deutschland Gmbh | Method for Repairing a Damaged Outer Skin Region on an Aircraft |
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| CN111703090A (en) * | 2020-07-03 | 2020-09-25 | 中国航空制造技术研究院 | Wedge-shaped embedded part for skin opening frame and using method |
| CN215109885U (en) * | 2020-10-30 | 2021-12-10 | 北京卫星制造厂有限公司 | Unmanned aerial vehicle combined material flap connection structure |
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Non-Patent Citations (1)
| Title |
|---|
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