CN112693622B - Method for repairing aircraft wing surface screw-pulling loosening - Google Patents
Method for repairing aircraft wing surface screw-pulling loosening Download PDFInfo
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- CN112693622B CN112693622B CN202011610137.0A CN202011610137A CN112693622B CN 112693622 B CN112693622 B CN 112693622B CN 202011610137 A CN202011610137 A CN 202011610137A CN 112693622 B CN112693622 B CN 112693622B
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- 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
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Abstract
The application discloses a loose repairing method for an aircraft wing surface screw, which comprises the following steps: determining the specification of loosened drawing nails and the structural arrangement condition of a drawing nail connecting area; making repair measures according to the loosening conditions of the current loosened drawing nails, wherein the loosening conditions of the drawing nails comprise single drawing nails loosening and multiple drawing nails loosening, and making different drawing nails repair schemes according to different drawing nails loosening conditions; and cleaning the loosened nail drawing area according to the formulated nail drawing repair scheme, installing the bushing, installing the repair plate, and installing the matched repair nail drawing according to the nail drawing repair scheme. The embodiment of the application solves the problem of loosening of the drawing nails at one time, and realizes that the repaired drawing nails are free from loosening/falling off faults.
Description
Technical Field
The application relates to the technical field of aircraft wing surface connection, in particular to a method for repairing an aircraft wing surface screw.
Background
At present, the connection of old aircraft wing surfaces mainly adopts the riveting mode, and wherein at least one surface skin has adopted the nail to connect, but in long-term use the nail of taking out easily becomes flexible and drops, adopts the former model to take out the nail again soon to appear taking out the nail loose and move/the condition that drops again, and the rudder of having installed can't use the rivet again to rivet yet, in addition, in the above-mentioned process of taking out again, need separate the rudder surface from the aircraft, the mode of taking out is comparatively complicated.
Therefore, how to select a reliable extraction pin to reconnect the loosened/detached extraction pin becomes an urgent problem of airfoil connection.
Disclosure of Invention
The purpose of the application is as follows: the embodiment of the application provides a method for repairing the loosening of an aircraft airfoil suction nail, which can solve the problem of the loosening of the suction nail at one time and prevent the repaired suction nail from loosening/falling off.
The technical scheme of the application is as follows: the embodiment of the application provides a method for repairing the loosening of an aircraft airfoil surface suction nail, which comprises the following steps:
step 1, determining the specification of loosened drawing nails and the structural arrangement condition of a drawing nail connecting area;
step 2, making repair measures according to the loosening conditions of the current loosened drawing nails, wherein the loosening conditions of the drawing nails comprise single drawing nails loosening and multiple drawing nails loosening, and making different drawing nails repair schemes according to different drawing nails loosening conditions;
and 3, cleaning the loosened nail drawing area according to the nail drawing repair scheme formulated in the step 2, installing a bushing, installing a repair plate, and installing an adaptive repair nail drawing according to the nail drawing repair scheme.
Optionally, in the method for repairing the loose pin of the airfoil surface of the aircraft according to the above description, in step 1, the specification of the loose pin and the structural arrangement condition of the pin connection area are determined according to the original drawing or the user data of the aircraft.
Optionally, in the aircraft airfoil staple extraction and repair method described above, the staple extraction and repair scheme includes:
the shape and the size of the cleaning area before repair, the shape and the size of the repaired steel plate, the specification of the repaired bushing, the number and the specification of the repaired drawing nails, and the corrosion prevention treatment after repair is completed.
Optionally, in the method for repairing the aircraft airfoil surface screw loosening, the repairing bushing is in a conical ring structure, the cross section of the repairing bushing is in an isosceles trapezoid structure, the diameter of the conical hole is the same as the rod diameter of the repairing screw, and the diameter of the outer ring is the same as the diameter of the screw head of the repairing screw; the conical head of the repair bushing is reversely arranged at the position of the head of the disassembled extracting pin and is used for filling the conical gap formed by the head of the disassembled extracting pin on the airfoil surface skin.
Optionally, in the aircraft airfoil nail extraction and loosening repair method as described above, the shape and the size of the repair steel plate are the same as those of the cleaning area, and the repair steel plate is provided with through holes at the same positions as the nail extraction positions.
Optionally, in the aircraft airfoil staple extracting and loosening repair method as described above, the step 3 includes:
step 31, cleaning a paint layer of an airfoil skin according to the loosening condition of the current loosened drawing nails to form a cleaning area, and decomposing all drawing nails in the cleaning area, wherein the loosening drawing nails comprise loosening drawing nails and adjacent perfect drawing nails in the course of the loosening drawing nails;
step 32, gluing the repair bush on the assembly surface of the repair bush and the airfoil skin according to the cleaning area of the disassembled extraction nails on the airfoil skin during installation;
step 33, gluing the joint surface of the repairing steel plate and the airfoil skin during installation according to the cleaning area of the decomposed drawing nails on the airfoil skin; wherein the repairing steel plate is provided with a through hole with the same position as the decomposed nail drawing position;
step 34, mounting the repair drawing nail on the repair steel plate and the airfoil skin provided with the repair bushing, and gluing the outer surface of the repair drawing nail during mounting;
and 35, after the repair is completed, painting the surfaces of the repaired steel plate and the nail head of the repaired drawing nail.
Optionally, in the method for repairing the loose pins of the airfoil surface of the aircraft according to the above, the number of the repairing pins is the number of all pins in the cleaning area, and the specification of the repairing pins is selected from the following relations:
the original machine nail drawing adopts domestic nail drawing, and the corresponding relation of repairing nail drawing is as follows: the domestic 04-diameter drawing pin corresponds to the English 05-diameter drawing pin, and the domestic 05-diameter drawing pin corresponds to the English 06-diameter drawing pin; or alternatively, the process may be performed,
the original machine nail drawing adopts English nail drawing, and the repair nail drawing diameter is the same as that of the original machine nail drawing.
Optionally, in the aircraft airfoil pin pulling and loosening repair method, the pin length of the repair pin is determined according to the thickness of the repaired steel plate, the airfoil skin and the thickness of the original aircraft connection interlayer.
The beneficial effects of the application are as follows: according to the aircraft airfoil surface screw pulling and loosening repair method provided by the embodiment of the application, a set of methods capable of realizing in-situ repair of the loose/falling screw pulling of the control surface are summarized through a large number of experimental growths; according to the method for repairing the loosening of the screw, the control surface is not required to be separated from the machine, and only corresponding repairing measures are formulated according to the actual conditions of loosening/falling of the screw and the repairing principle obtained through test and are carried out on the machine. The repairing method provided by the embodiment of the application is used for repairing the loosened rivet, so that the reliable repairing effect can be ensured, the use and maintenance cost of the aircraft is reduced, and the reliability of the aircraft structure is improved. Compared with the repairing mode of directly replacing the drawing nails in the existing mode, the method for loosely repairing the drawing nails provided by the embodiment of the application can ensure the service life of the drawing nails, reduce the subsequent repairing cost and improve the bearing capacity of a repairing area.
Drawings
The accompanying drawings are included to provide a further understanding of the application and are incorporated in and constitute a part of this specification, illustrate and do not limit the application.
FIG. 1 is a flow chart of a method for repairing an aircraft airfoil staple extraction and loosening provided by an embodiment of the application;
FIG. 2 is a schematic illustration of a loosening condition of a suction nail in a method for repairing a loosening of a suction nail of an aircraft airfoil according to an embodiment of the present application;
FIG. 3 is a schematic illustration of a clean area in an aircraft airfoil staple loosening repair method according to an embodiment of the present application;
FIG. 4 is a schematic view of a repair bushing used in an aircraft airfoil staple loosening repair method according to an embodiment of the present application;
FIG. 5 is a schematic view of the mounting structure of a repair bushing and repair steel plate in an aircraft airfoil tack-free repair method according to an embodiment of the present application;
FIG. 6 is a schematic diagram of a structure after repair using the method for repairing an aircraft airfoil staple extraction and loosening provided by an embodiment of the application.
DETAILED DESCRIPTION OF EMBODIMENT (S) OF INVENTION
For the purpose of making the objects, technical solutions and advantages of the present application more apparent, embodiments of the present application will be described in detail hereinafter with reference to the accompanying drawings. It should be noted that, without conflict, the embodiments of the present application and features of the embodiments may be arbitrarily combined with each other.
The prior art already shows that the current nail-pulling repairing mode of the old aircraft wing surface is as follows: once the screw is loosened/fallen off, the screw is usually re-fed by using the screw with the original mark increased by one level. This repair can solve the problem temporarily, but once the screw is pulled out again, the screw is loosened/removed, and the repair is difficult to be carried out later. Because the nail hole is enlarged in the last repair, on one hand, the margin of the nail does not meet the design requirement, and the nail hole cannot be enlarged in the repair again; on the other hand, the diameter specification of the drawing nails is limited, and the drawing nails with larger numbers are beyond the standard selection range and are difficult to purchase.
Aiming at the problems existing in the existing aircraft wing surface nail drawing repair mode, the embodiment of the application designs a permanent repair method for loosening the aircraft wing surface nail drawing, which can solve the problem of loosening the nail drawing at one time, and simultaneously repair the original nail hole by a small amount, the aperture after the repair does not exceed the design requirement, and the repaired nail drawing is ensured not to have loosening/falling faults any more in the later use of the aircraft.
The following specific embodiments may be combined with each other, and some embodiments may not be repeated for the same or similar concepts or processes.
FIG. 1 is a flow chart of a method for repairing an aircraft airfoil staple in a loosening manner, provided by an embodiment of the application. The method for repairing the aircraft wing surface screw extraction loosening provided by the embodiment of the application can comprise the following steps:
step 1, determining the specification of loosened drawing nails and the structural arrangement condition of a drawing nail connecting area, wherein the structural arrangement condition of the drawing nail connecting area refers to the structure of the drawing nails along the thickness direction, for example, the thickness of a connecting interlayer;
step 2, making repair measures according to the loosening conditions of the current loosened drawing nails, wherein the loosening conditions of the drawing nails comprise single drawing nails loosening and multiple drawing nails loosening, and making different drawing nails repair schemes according to different drawing nails loosening conditions;
and 3, cleaning the loosened nail drawing area according to the nail drawing repair scheme formulated in the step 2, installing a bushing, installing a repair plate, and installing an adaptive repair nail drawing according to the nail drawing repair scheme.
The following details the specific implementation of each step in the method for repairing the loose pin of the aircraft airfoil according to the embodiment of the application.
As shown in fig. 2, a schematic diagram of a screw loosening situation in the screw loosening repair method for an aircraft airfoil according to an embodiment of the present application is shown, in which an airfoil skin shown in fig. 2 has a complete screw 1 and a loosened screw 2, a left diagram of fig. 2 shows a single screw loosening situation, and a right diagram of fig. 2 shows a plurality of screw loosening situations, where the plurality of screw loosening may be a plurality of continuous screw loosening as shown in fig. 2 or a plurality of discontinuous screw loosening.
In step 1 of the embodiment of the application, the specification of the loosened drawing pin and the structural arrangement condition of the drawing pin connecting area can be determined according to the original drawing paper or user data of the airplane.
The above embodiments have described that the loosening of the extraction includes single extraction loosening and multiple extraction loosening, and thus, the formulation of different extraction repair schemes may include: repair solutions for single extraction loosening and repair solutions for multiple extraction loosening.
It should be noted that, the common scheme content of the single screw loosening and the multiple screw loosening repair scheme includes: both schemes need to design the shape and size of the clean area before repair, the shape and size of the repaired steel plate, the specification of the repaired bushing, the number and specification of the repaired drawing nails, the anti-corrosion treatment after repair is completed, and the like.
In the above-mentioned nail drawing repair scheme, the specification of repairing the nail drawing can be selected from foreign English CR7774S series nail drawing, and the corresponding conditions of the repair nail drawing specification and the original machine nail drawing specification are:
1) If the original machine nail drawing is domestic nail drawing, the concrete corresponding relation of repairing nail drawing is as follows: the domestic 04-diameter drawing pin corresponds to the English 05-diameter drawing pin and the domestic 05-diameter drawing pin corresponds to the English 06-diameter drawing pin;
2) If the original machine nail is a English nail, the repair nail diameter is the same as the original machine nail.
In the above-mentioned nail drawing repair scheme, the length of the nail rod for repairing the nail drawing is determined according to the thickness of the repaired steel plate, the airfoil skin and the thickness of the original machine connecting interlayer.
Fig. 3 is a schematic diagram of a cleaning area in the aircraft airfoil nail extraction and loosening repair method according to an embodiment of the present application, in which the cleaning area 3 under different nail extraction loosening conditions is shown on an airfoil skin shown in fig. 3, the left diagram of fig. 3 illustrates the cleaning area 3 under a single nail extraction loosening condition, and the right diagram of fig. 3 illustrates the cleaning area 3 under a plurality of continuous nail extraction loosening conditions.
In a specific implementation of the embodiment of the present application, the criteria for determining the cleaning area 3 may be: and determining the area where the loosened drawing nails and adjacent intact drawing nails in the course direction of the loosened drawing nails are located as a cleaning area 3, wherein all the intact drawing nails 1 and the loosened drawing nails 2 in the cleaning area 3 are drawing nails 2a which need to be decomposed.
As shown in fig. 4, a schematic structural diagram of a repair bushing used in the method for repairing an aircraft airfoil by loosening a suction pin according to an embodiment of the present application is shown, wherein a left side view in fig. 4 is a front view of the repair bushing, and a right side view is a sectional view of the repair bushing. The repair bushing in the embodiment of the application is of a conical ring structure, the cross section of the repair bushing is of an isosceles trapezoid structure, the diameter d1 of the conical hole is the same as the rod diameter of the repair drawing nail, the diameter d2 of the outer ring is the same as the diameter of the nail head of the repair drawing nail, and h in fig. 4 is the height of the nail head of the drawing nail.
In practical application, the structure and the size of the repair bushing are the same as those of the original machine drawing pin, and the taper head of the repair bushing is reversely arranged at the position of the head of the disassembled drawing pin, so that the taper gap formed by the head of the disassembled drawing pin on the airfoil surface skin is filled. Fig. 5 is a schematic diagram of an installation structure of a repair bushing and a repair steel plate in the method for repairing the loose rivet of the aircraft airfoil according to the embodiment of the application. The airfoil skin 4 in fig. 5 is formed with a conical gap, a repair bushing 5 is mounted on the conical gap, a repair steel plate 6 is attached to the airfoil skin 4, the repair drawing nails 2b replace all the perfect drawing nails 1 and loose drawing nails 2 of the original cleaning area 3, and the interior of the airfoil skin 4 is a skin inner structure 4a.
Fig. 6 is a schematic structural diagram of an aircraft airfoil according to an embodiment of the present application after repair by the method for repairing the aircraft airfoil with a loose bolt. The position of the repaired steel plate after repair is illustrated in fig. 6, and it can be seen with reference to fig. 2 and 6 that the shape and size of the repaired steel plate 5 are the same as those of the cleaning region 3 in the embodiment of the present application.
The modification step in the embodiment of the present application, namely, the specific implementation manner of step 3 includes:
step 31, cleaning a paint layer of an airfoil skin according to the loosening condition of the current loosened drawing nails to form a cleaning area, and decomposing all drawing nails in the cleaning area, wherein the decomposed drawing nails comprise loosening drawing nails and adjacent perfect drawing nails in the course direction of the loosening drawing nails, and the decomposed drawing nails can refer to drawing nails in the cleaning area 3 shown in fig. 3;
step 32, manufacturing a repair bush according to the structure shown in fig. 4, and coating adhesive on an assembly surface (namely a contact surface of the repair bush and the airfoil skin) when the repair bush is installed according to the cleaning area of the disassembled drawing nails on the airfoil skin according to the structure shown in fig. 5, wherein the adhesive can be 2216B/A adhesive;
step 33, manufacturing a stainless steel repair steel plate according to the structure shown in fig. 6, and gluing the repair steel plate 6 according to the decomposed nail-drawing cleaning area 3 on the airfoil skin 4 according to the structure shown in fig. 6, wherein the glue can be 2216B/A glue on the joint surface of the repair steel plate 6 and the airfoil skin 4 during installation, and in addition, the repair steel plate 6 is provided with through holes with the same positions as the decomposed nail-drawing positions for repairing the nail-drawing 2B to replace the decomposed nail-drawing 2a in the original cleaning area 3.
Step 34, mounting the repair drawing nail on the repair steel plate and the airfoil skin provided with the repair bushing, and gluing the outer surface of the repair drawing nail during mounting, wherein the glue type can be 2216B/A glue;
and 35, after the repair is completed, painting the surfaces of the repaired steel plate and the nail head of the repaired drawing nail.
The embodiment of the application provides a method for repairing the wing surface screw-pulling looseness of an airplane.
According to the aircraft airfoil surface screw pulling and loosening repair method provided by the embodiment of the application, a set of methods capable of realizing in-situ repair of the loose/falling screw pulling of the control surface are summarized through a large number of experimental growths; according to the method for repairing the loosening of the screw, the control surface is not required to be separated from the machine, and only corresponding repairing measures are formulated according to the actual conditions of loosening/falling of the screw and the repairing principle obtained through test and are carried out on the machine. The repairing method provided by the embodiment of the application is used for repairing the loosened rivet, so that the reliable repairing effect can be ensured, the use and maintenance cost of the aircraft is reduced, and the reliability of the aircraft structure is improved.
Compared with the repairing mode of directly replacing the drawing nails in the existing mode, the method for loosely repairing the drawing nails provided by the embodiment of the application can ensure the service life of the drawing nails, reduce the subsequent repairing cost and improve the bearing capacity of a repairing area. In addition, the nail drawing and loosening repair method provided by the embodiment of the application has been verified on the control surface of the flying leopard fighter plane, and the actual use effect is good.
Although the embodiments of the present application are described above, the embodiments are only used for facilitating understanding of the present application, and are not intended to limit the present application. Any person skilled in the art can make any modification and variation in form and detail without departing from the spirit and scope of the present disclosure, but the scope of the present disclosure is to be determined by the appended claims.
Claims (5)
1. A method of repairing an aircraft airfoil staple loosening comprising:
step 1, determining the specification of loosened drawing nails and the structural arrangement condition of a drawing nail connecting area;
step 2, making repair measures according to the loosening conditions of the current loosened drawing nails, wherein the loosening conditions of the drawing nails comprise single drawing nails loosening and multiple drawing nails loosening, and making different drawing nails repair schemes according to different drawing nails loosening conditions;
step 3, cleaning the loosened nail drawing area according to the nail drawing repair scheme formulated in the step 2, installing a bushing, installing a repair plate, and installing an adaptive repair nail drawing according to the nail drawing repair scheme;
in the step 1, determining the specification of loose drawing nails and the structural arrangement condition of a drawing nail connecting area according to the original drawing of an airplane or user data;
the nail drawing repair scheme prepared in the step 2 comprises the following steps:
the shape and the size of the cleaning area before repair, the shape and the size of the repaired steel plate, the specification of the repaired bushing, the number and the specification of the repaired drawing nails, and the corrosion prevention treatment after repair is completed;
the step 3 comprises the following steps:
step 31, cleaning a paint layer of an airfoil skin according to the loosening condition of the current loosened drawing nails to form a cleaning area, and decomposing all drawing nails in the cleaning area, wherein the loosening drawing nails comprise loosening drawing nails and adjacent perfect drawing nails in the course of the loosening drawing nails;
step 32, gluing the repair bush on the assembly surface of the repair bush and the airfoil skin according to the cleaning area of the disassembled extraction nails on the airfoil skin during installation;
step 33, gluing the joint surface of the repairing steel plate and the airfoil skin during installation according to the cleaning area of the decomposed drawing nails on the airfoil skin; wherein the repairing steel plate is provided with a through hole with the same position as the decomposed nail drawing position;
step 34, mounting the repair drawing nail on the repair steel plate and the airfoil skin provided with the repair bushing, and gluing the outer surface of the repair drawing nail during mounting;
and 35, after the repair is completed, painting the surfaces of the repaired steel plate and the nail head of the repaired drawing nail.
2. The method for repairing the aircraft airfoil screw loosening as claimed in claim 1, wherein the repairing bush is of a conical ring structure, the cross section of the repairing bush is of an isosceles trapezoid structure, the diameter of the conical hole is the same as the rod diameter of the repairing screw, and the diameter of the outer ring is the same as the diameter of the screw head of the repairing screw; the conical head of the repair bushing is reversely arranged at the position of the head of the disassembled extracting pin and is used for filling the conical gap formed by the head of the disassembled extracting pin on the airfoil surface skin.
3. The method of repairing an aircraft airfoil nail extractor according to claim 2, wherein the shape and size of the repair steel sheet are the same as those of the cleaning area, and the repair steel sheet has through holes at the same positions as the nail extractor.
4. A method of repairing an aircraft airfoil pin according to any one of claims 1 to 3, wherein the number of repair pins is the number of all pins in the cleaning area, and the specification of the repair pins is selected from the group consisting of:
the original machine nail drawing adopts domestic nail drawing, and the corresponding relation of repairing nail drawing is as follows: the domestic 04-diameter drawing pin corresponds to the English 05-diameter drawing pin, and the domestic 05-diameter drawing pin corresponds to the English 06-diameter drawing pin; or alternatively, the process may be performed,
the original machine nail drawing adopts English nail drawing, and the repair nail drawing diameter is the same as that of the original machine nail drawing.
5. A method of repairing an aircraft airfoil pin according to any one of claims 1 to 3, wherein the pin length of the pin is determined based on the thickness of the repaired steel sheet, the airfoil skin, and the thickness of the original machine connection interlayer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011610137.0A CN112693622B (en) | 2020-12-29 | 2020-12-29 | Method for repairing aircraft wing surface screw-pulling loosening |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011610137.0A CN112693622B (en) | 2020-12-29 | 2020-12-29 | Method for repairing aircraft wing surface screw-pulling loosening |
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| Publication Number | Publication Date |
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| CN112693622A CN112693622A (en) | 2021-04-23 |
| CN112693622B true CN112693622B (en) | 2023-09-05 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011610137.0A Active CN112693622B (en) | 2020-12-29 | 2020-12-29 | Method for repairing aircraft wing surface screw-pulling loosening |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| FR2970433B1 (en) * | 2011-01-13 | 2013-01-04 | Aircelle Sa | PROCESS FOR REPAIRING AT LEAST ONE PART OF AN ACOUSTIC PANEL FOR A NACELLE |
| US9598183B1 (en) * | 2016-05-06 | 2017-03-21 | Kellstrom Defense Aerospace, Inc. | Aircraft wing repair systems and methods |
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| CN103950553A (en) * | 2014-04-25 | 2014-07-30 | 哈尔滨飞机工业集团有限责任公司 | Method for repairing countersunk crossed nest |
| EP3275645A1 (en) * | 2016-07-25 | 2018-01-31 | nolax AG | Sandwich component, method for the production of a sandwich component and use of a sandwich component |
| CN206171819U (en) * | 2016-11-09 | 2017-05-17 | 北京航空航天大学 | Repair subassembly of special screw pin fin of radar stealth sortie ware |
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| CN112693622A (en) | 2021-04-23 |
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