阅读说明：本技术 一种飞机翼面抽钉松动修理方法 (Method for repairing airplane wing surface by pulling out nails and loosening ) 是由 达磊 吴斌 朱胜利 于 2020-12-29 设计创作，主要内容包括：本发明公开一种飞机翼面抽钉松动修理方法,包括：确定已松动抽钉的规格和抽钉连接区域的结构布置情况；根据当前已松动抽钉的松动情况制定修理措施,抽钉的松动情况包括单个抽钉松动和多个抽钉松动,按照不同的抽钉松动情况制定不同的抽钉修理方案；根据已制定的抽钉修理方案对已松动抽钉区域进行清理,安装衬套,安装修补板,并根据抽钉修理方案安装适配的修理抽钉。本发明实施例实现了一次性解决抽钉松动的问题,并且实现使已经修理过的抽钉不再出现松动/脱落故障。(The invention discloses a method for repairing airplane wing surfaces by loosening of extracted nails, which comprises the following steps: determining the specifications of loosened nail drawing and the structural arrangement condition of a nail drawing connection area; making repair measures according to the loosening condition of the current loosened nail drawing, wherein the loosening condition of the nail drawing comprises single nail drawing loosening and multiple nail drawing loosening, and making different nail drawing repair schemes according to different nail drawing loosening conditions; and cleaning the loosened nail pulling area according to the established nail pulling repair scheme, installing a bushing, installing a repair plate, and installing the adaptive repair nail pulling according to the nail pulling repair scheme. The embodiment of the invention realizes that the problem of loosening of the extracted nail is solved at one time, and the repaired extracted nail does not have loosening/falling faults.)

1. An aircraft airfoil pin-pulling loosening repair method is characterized by comprising the following steps:

step 1, determining the specifications of loosened nail drawing and the structural arrangement condition of a nail drawing connection area;

step 2, making repair measures according to the loosening condition of the current loosened nail drawing, wherein the loosening condition of the nail drawing comprises single nail drawing loosening and multiple nail drawing loosening, and making different nail drawing repair schemes according to different nail drawing loosening conditions;

and 3, cleaning the loosened nail pulling area according to the nail pulling repair scheme formulated in the step 2, installing a bushing, installing a repair plate, and installing an adaptive repair nail according to the nail pulling repair scheme.

2. The method for repairing the loosening of the aircraft airfoil nails by the drawing pins of the aircraft as claimed in claim 1, wherein in the step 1, the specifications of the loosened nails and the structural arrangement of the nail connection areas are determined according to original drawings or user data of the aircraft.

3. The aircraft airfoil pin extraction loosening repair method of claim 2 wherein the pin extraction repair protocol comprises:

the shape and size of the cleaning area before repair, the shape and size of the repair steel plate, the specification of the repair lining, the number and specification of repair extraction nails, and the anticorrosion treatment after repair.

4. The aircraft airfoil pin extraction loosening repair method as claimed in claim 3, wherein the repair bushing is a tapered ring structure with an isosceles trapezoid cross section, the diameter of the tapered hole is the same as the diameter of the rod of the repair extraction pin, and the diameter of the outer ring is the same as the diameter of the head of the repair extraction pin; and the conical head of the repair bushing is inversely arranged at the nail head position of the decomposed extracted nail and is used for filling the conical vacancy formed by the nail head of the decomposed extracted nail on the airfoil surface skin.

5. The aircraft airfoil pin extraction loosening repair method of claim 4 wherein the repair steel plate has the same shape and size as the cleaning area and has through holes at the same positions as the pin extraction locations.

6. The aircraft airfoil pin extraction loosening repair method of claim 5, wherein said step 3 comprises:

step 31, cleaning a paint layer of the airfoil skin according to the loosening condition of the loosened nails to form a cleaning area, and decomposing all the nails in the cleaning area, including the loosened nails and adjacent intact nails along the course of the loosened nails;

step 32, gluing the assembly surface of the repair lining and the airfoil skin during installation according to the disassembled cleaning area of the extraction nail on the airfoil skin;

step 33, gluing the jointing surface of the repairing steel plate and the airfoil skin during installation according to the decomposed cleaning area of the extracted nail on the airfoil skin; wherein the repairing steel plate is provided with a through hole with the same position as the disassembled nail pulling position;

step 34, mounting the repair drawing nail on the repair steel plate and the airfoil surface skin provided with the repair lining, and coating glue on the outer surface of the repair drawing nail during mounting;

and step 35, painting the surfaces of the repaired steel plates and the nail heads of the repaired extracted nails after the repair is finished.

7. The aircraft airfoil pin-pulling loosening repair method according to any one of claims 1 to 6, wherein the number of the repair pins is the number of all the repair pins in the cleaning area, and the specifications of the repair pins are selected according to a relation including:

the original machine is adopted to take out the nail in the country, the corresponding relation of repairing and taking out the nail is: the domestic 04-diameter drawn nails correspond to British 05-diameter drawn nails, and the domestic 05-diameter drawn nails correspond to British 06-diameter drawn nails; alternatively, the first and second electrodes may be,

the original machine drawing nail adopts British drawing nail, and the diameter of the repaired drawing nail is the same as that of the original machine drawing nail.

8. The aircraft airfoil pin-pulling loosening repair method as claimed in any one of claims 1 to 6, wherein the length of the pin shaft of the repair pin is determined according to the thickness of a repaired repair steel plate, the thickness of an airfoil skin and the thickness of an original machine connection interlayer.

Technical Field

The invention relates to the technical field of airplane airfoil connection, in particular to a method for repairing airplane airfoil by loosening a drawn nail.

Background

At present, the old airplane wing surfaces are mainly connected in a riveting mode, at least one surface skin is connected by adopting a drawn nail, but the drawn nail is easy to loosen and fall off in long-term use, at the moment, the situation of the drawn nail loosening/falling off can be caused soon after the original model drawn nail is adopted for re-drawing, and the installed rudder can not be riveted by using the rivet any more.

Therefore, how to select a reliable extraction nail to reconnect the loosened/fallen extraction nail has solved the problem of airfoil connection which is needed to be solved at present.

Disclosure of Invention

The purpose of the invention is as follows: the embodiment of the invention provides a method for repairing the loosening of a wing surface of an airplane by pulling out a nail, which can solve the problem of loosening of the nail by pulling out once and can prevent the repaired nail from loosening/falling.

The technical scheme of the invention is as follows: the embodiment of the invention provides a method for repairing the loosening of an airplane wing surface by pulling out nails, which comprises the following steps:

step 1, determining the specifications of loosened nail drawing and the structural arrangement condition of a nail drawing connection area;

step 2, making repair measures according to the loosening condition of the current loosened nail drawing, wherein the loosening condition of the nail drawing comprises single nail drawing loosening and multiple nail drawing loosening, and making different nail drawing repair schemes according to different nail drawing loosening conditions;

and 3, cleaning the loosened nail pulling area according to the nail pulling repair scheme formulated in the step 2, installing a bushing, installing a repair plate, and installing an adaptive repair nail according to the nail pulling repair scheme.

Optionally, in the method for repairing the loosened aircraft airfoil nails by pulling out the nails, in step 1, the specifications of the loosened nails and the structural arrangement of the nail pulling connection area are determined according to the original drawing or user data of the aircraft.

Optionally, in the method for repairing the airplane airfoil by loosening the extracted nail as described above, the extracted nail repairing scheme includes:

the shape and size of the cleaning area before repair, the shape and size of the repair steel plate, the specification of the repair lining, the number and specification of repair extraction nails, and the anticorrosion treatment after repair.

Optionally, in the method for repairing the aircraft airfoil by loosening the extracted nail as described above, the repair bushing is of a tapered annular structure, the cross section of the repair bushing is of an isosceles trapezoid structure, the diameter of the tapered hole is the same as the rod diameter of the repair extracted nail, and the diameter of the outer annular ring is the same as the nail head diameter of the repair extracted nail; and the conical head of the repair bushing is inversely arranged at the nail head position of the decomposed extracted nail and is used for filling the conical vacancy formed by the nail head of the decomposed extracted nail on the airfoil surface skin.

Optionally, in the method for repairing the aircraft airfoil by loosening the extracted nail as described above, the shape and size of the repair steel plate are the same as those of the cleaning area, and the repair steel plate is provided with a through hole at the same position as the extracted nail.

Optionally, in the method for repairing the airplane airfoil by loosening the extracted nail as described above, the step 3 includes:

step 31, cleaning a paint layer of the airfoil skin according to the loosening condition of the loosened nails to form a cleaning area, and decomposing all the nails in the cleaning area, including the loosened nails and adjacent intact nails along the course of the loosened nails;

step 32, gluing the assembly surface of the repair lining and the airfoil skin during installation according to the disassembled cleaning area of the extraction nail on the airfoil skin;

step 33, gluing the jointing surface of the repairing steel plate and the airfoil skin during installation according to the decomposed cleaning area of the extracted nail on the airfoil skin; wherein the repairing steel plate is provided with a through hole with the same position as the disassembled nail pulling position;

step 34, mounting the repair drawing nail on the repair steel plate and the airfoil surface skin provided with the repair lining, and coating glue on the outer surface of the repair drawing nail during mounting;

and step 35, painting the surfaces of the repaired steel plates and the nail heads of the repaired extracted nails after the repair is finished.

Optionally, in the method for repairing the airplane airfoil by pulling out and loosening the nails, the number of the repair pulling-out nails is the number of all the pulling-out nails in the cleaning area, and the specifications of the repair pulling-out nails are selected from a relationship including:

the original machine is adopted to take out the nail in the country, the corresponding relation of repairing and taking out the nail is: the domestic 04-diameter drawn nails correspond to British 05-diameter drawn nails, and the domestic 05-diameter drawn nails correspond to British 06-diameter drawn nails; alternatively, the first and second electrodes may be,

the original machine drawing nail adopts British drawing nail, and the diameter of the repaired drawing nail is the same as that of the original machine drawing nail.

Optionally, in the method for repairing the airplane wing surface by pulling out and loosening the nails as described above, the length of the nail shaft of the repair pulling nail is determined according to the thickness of the repaired steel plate, the thickness of the wing surface skin and the thickness of the original machine connecting interlayer.

The invention has the beneficial effects that: according to the aircraft wing surface screw pulling loosening repair method provided by the embodiment of the invention, a set of method for realizing the in-situ repair of the loosened/fallen screw pulling of the control surface is summarized through a large number of tests and searches; the method for repairing the loose taken-out nail does not need to separate the control surface from the machine, and only needs to make corresponding repairing measures according to the repairing principle summarized by tests and carry out repairing implementation on the machine according to the actual situation of loose taken-out nail/falling-out. The repair method provided by the embodiment of the invention is adopted to repair loosened nails, so that the reliable repair effect can be ensured, the use and maintenance cost of the airplane is reduced, and the reliability of the airplane structure is improved. Compared with the repair mode of directly replacing the drawn nail in the existing mode, the drawn nail loosening repair method provided by the embodiment of the invention can ensure the service life of the drawn nail, reduce the subsequent repair cost and simultaneously improve the bearing capacity of the repair area.

Drawings

The accompanying drawings are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the example serve to explain the principles of the invention and not to limit the invention.

FIG. 1 is a flow chart of a method for repairing an aircraft wing surface by loosening a pin drawn out according to an embodiment of the present invention;

FIG. 2 is a schematic diagram illustrating loosening of the extracted nail in the method for repairing loosening the extracted nail of the aircraft airfoil according to the embodiment of the invention;

FIG. 3 is a schematic view of a cleaning area in a method for repairing an aircraft airfoil by pin extraction loosening according to an embodiment of the present invention;

FIG. 4 is a schematic illustration of a repair liner used in a method of aircraft airfoil extraction pin loosening repair according to an embodiment of the present invention;

FIG. 5 is a schematic view of an installation structure of a repair lining and a repair steel plate in the method for repairing the loosening of the aircraft airfoil by the pin pulling provided by the embodiment of the invention;

FIG. 6 is a schematic structural diagram of an aircraft airfoil after repair by the method for repairing the aircraft airfoil by loosening the pins.

DETAILED DESCRIPTION OF EMBODIMENT (S) OF INVENTION

In order to make the objects, technical solutions and advantages of the present invention more apparent, embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be noted that the embodiments and features of the embodiments in the present application may be arbitrarily combined with each other without conflict.

The above background art already shows that the current method for repairing the old airplane wing surface by taking out the nail is as follows: once the loose/falling of the extracted nail occurs on the control surface, the extracted nail with the original brand number increased by one level is adopted for re-extraction. This repair measure can temporarily solve the problem, but once the nail extraction has once again become loose/detached, it is difficult to repair again at a later stage. Because the nail hole is enlarged when the nail hole is repaired last time, on one hand, the nail margin does not meet the design requirement, and the nail hole cannot be enlarged after the nail hole is repaired again; on the other hand, the diameter specification of the drawn nail is limited, and the drawn nail with a larger size is beyond the standard selection range and is difficult to purchase.

Aiming at the problems existing in the existing method for repairing the wing surface of the airplane by taking out the nails, the embodiment of the invention designs the method for permanently repairing the wing surface of the airplane by taking out the nails, which can solve the problem of taking out the nails for loosening at one time, meanwhile, the original nail holes are trimmed by a small amount, the hole diameter after trimming does not exceed the design requirements, and the problem that the repaired nail does not loosen or fall off any more in the later use of the airplane is ensured.

The following specific embodiments of the present invention may be combined, and the same or similar concepts or processes may not be described in detail in some embodiments.

FIG. 1 is a flow chart of a method for repairing an aircraft airfoil by loosening a pin drawn out according to an embodiment of the present invention. The method for repairing the loosened aircraft airfoil by pulling out the nails provided by the embodiment of the invention comprises the following steps:

step 1, determining the specifications of loosened nails and the structural arrangement condition of a nail-pulling connection area, wherein the structural arrangement condition of the nail-pulling connection area refers to the structure of the nails along the thickness direction, such as the thickness of a connection interlayer;

step 2, making repair measures according to the loosening condition of the current loosened nail drawing, wherein the loosening condition of the nail drawing comprises single nail drawing loosening and multiple nail drawing loosening, and making different nail drawing repair schemes according to different nail drawing loosening conditions;

and 3, cleaning the loosened nail pulling area according to the nail pulling repair scheme formulated in the step 2, installing a bushing, installing a repair plate, and installing an adaptive repair nail according to the nail pulling repair scheme.

The following provides a detailed description of each step of the method for repairing the aircraft wing surface by loosening the nails by pulling out the nails.

As shown in fig. 2, for a schematic diagram of a loose situation of a drawn nail in an aircraft airfoil loose repair method provided by an embodiment of the present invention, a skin of an airfoil shown in fig. 2 has a perfect drawn nail 1 and a loose drawn nail 2, a left diagram of fig. 2 illustrates a loose situation of a single drawn nail, a right diagram of fig. 2 illustrates a loose situation of multiple drawn nails, and multiple loose nails may be multiple continuous loose nails shown in fig. 2 or multiple discontinuous loose nails.

In step 1 of the embodiment of the invention, the specifications of loosened nail drawing and the structural arrangement condition of the nail drawing connection area can be determined according to original drawings or user data of the airplane.

The above embodiments have explained the loosening of the drawn nails including the loosening of a single drawn nail and the loosening of a plurality of drawn nails, and therefore, different drawn nail repair schemes may be made including: repair solutions for single pull stud loosening, and repair solutions for multiple pull stud loosening.

It should be noted that the common contents of the repair schemes of single-screw loosening and multiple-screw loosening include: both solutions require the design of the shape and size of the cleaning zone before repair, the shape and size of the repaired steel plate, the specifications of the repaired lining, the number and specifications of the repaired nails, the anti-corrosion treatment after repair, etc.

In the above-mentioned nail drawing repair scheme, the specification of the repair nail drawing can be selected from the drawing nails of the foreign british system CR7774S series, and the correspondence between the specification of the repair nail drawing and the specification of the original machine nail drawing is as follows:

1) if the original machine drawing nail is a domestic drawing nail, the specific corresponding relation of repairing the drawing nail is as follows: domestic 04-diameter drawn nails correspond to British 05-diameter drawn nails, and domestic 05-diameter drawn nails correspond to British 06-diameter drawn nails;

2) if the original machine drawn nail is the British drawn nail, the diameter of the repaired drawn nail is the same as that of the original machine drawn nail.

In the above-mentioned repair method, the length of the repair nail stem is determined according to the thickness of the repaired steel plate, the wing surface skin and the thickness of the original machine connecting interlayer.

Fig. 3 is a schematic diagram of a cleaning region in an aircraft airfoil pin-out loosening repair method according to an embodiment of the present invention, the cleaning region 3 is illustrated in fig. 3 on an airfoil skin in different pin-out loosening situations, the left diagram of fig. 3 illustrates the cleaning region 3 in a single pin-out loosening situation, and the right diagram of fig. 3 illustrates the cleaning regions 3 in a plurality of continuous pin-out loosening situations.

In the specific implementation of the embodiment of the present invention, the standard for determining the cleaning area 3 may be: and determining the loosened extracted nail and the area where the adjacent perfect extracted nail along the course of the loosened extracted nail are located as a cleaning area 3, wherein all the perfect extracted nails 1 and the loosened extracted nails 2 in the cleaning area 3 are extracted nails 2a needing to be decomposed.

Fig. 4 is a schematic structural view of a repair bush used in the method for repairing the wing surface of an aircraft by loosening the pin by pulling out the pin according to the embodiment of the present invention, wherein the left side of fig. 4 is a front view of the repair bush, and the right side is a sectional view of the repair bush. The repair lining in the embodiment of the invention is in a conical ring structure, the section of the repair lining is in an isosceles trapezoid structure, the diameter d1 of a conical hole is the same as the rod diameter of the repair screw, the diameter d2 of an outer ring is the same as the diameter of the head of the repair screw, and h in figure 4 is the height of the head of the repair screw.

In practical application, the structure and the size of the repair lining are the same as those of the original machine extraction nail, and the conical head of the repair lining is arranged at the nail head position of the decomposed extraction nail in an inverted mode, so that the conical vacancy formed by the nail head of the decomposed extraction nail on the airfoil surface skin is filled. Fig. 5 is a schematic view of an installation structure of a repair lining and a repair steel plate in the method for repairing the loosening of the aircraft airfoil by pulling the nails according to the embodiment of the invention. In fig. 5, a conical vacancy is formed in the airfoil skin 4, a repair bushing 5 is installed in the conical vacancy, a repair steel plate 6 is attached to the airfoil skin 4, a repair pull nail 2b replaces all intact pull nails 1 and loose pull nails 2 in an original cleaning area 3, and an inner skin structure 4a is arranged inside the airfoil skin 4.

Fig. 6 is a schematic structural diagram of an airplane airfoil repaired by the method for repairing the wing surface by loosening the nails after the repairing is completed. The location of the repaired repair steel plate is illustrated in fig. 6, and it can be seen from fig. 2 and 6 that the shape and size of the repair steel plate 5 are the same as those of the cleaning region 3 in the embodiment of the present invention.

The embodiment of the repairing step, namely step 3 in the embodiment of the invention comprises the following steps:

step 31, cleaning a paint layer of the airfoil skin according to the loosening condition of the current loosened nail-drawing to form a cleaning area, and decomposing all the nail-drawing in the cleaning area, wherein the decomposed nail-drawing comprises the loosened nail-drawing and adjacent intact nail-drawing along the course of the loosened nail-drawing, and the decomposed nail-drawing can refer to the nail-drawing 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 glue 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 extracted nail on the airfoil skin according to the structure shown in fig. 5, wherein the type of the glue can be 2216B/A glue;

step 33, manufacturing a stainless steel repair steel plate according to the method shown in fig. 6, and gluing the joint surface of the repair steel plate 6 and the airfoil skin 4 according to the disassembled and extracted cleaning area 3 on the airfoil skin 4 by using the structure shown in fig. 6, wherein the glue type can be 2216B/a glue, and in addition, the repair steel plate 6 is provided with a through hole with the same position as the disassembled and extracted nail for replacing the disassembled and extracted nail 2a in the original cleaning area 3 by using the repair extracted nail 2B.

Step 34, mounting the repair drawing nail on a repair steel plate and an airfoil surface skin provided with a repair lining, and coating glue on the outer surface of the repair drawing nail during mounting, wherein the type of the glue can be 2216B/A glue;

and step 35, painting the surfaces of the repaired steel plates and the nail heads of the repaired extracted nails after the repair is finished.

The embodiment of the invention provides a method for repairing the loosening of an airplane wing surface by pulling nails.

According to the aircraft wing surface screw pulling loosening repair method provided by the embodiment of the invention, a set of method for realizing the in-situ repair of the loosened/fallen screw pulling of the control surface is summarized through a large number of tests and searches; the method for repairing the loose taken-out nail does not need to separate the control surface from the machine, and only needs to make corresponding repairing measures according to the repairing principle summarized by tests and carry out repairing implementation on the machine according to the actual situation of loose taken-out nail/falling-out. The repair method provided by the embodiment of the invention is adopted to repair loosened nails, so that the reliable repair effect can be ensured, the use and maintenance cost of the airplane is reduced, and the reliability of the airplane structure is improved.

Compared with the repair mode of directly replacing the drawn nail in the existing mode, the drawn nail loosening repair method provided by the embodiment of the invention can ensure the service life of the drawn nail, reduce the subsequent repair cost and simultaneously improve the bearing capacity of the repair area. In addition, the method for repairing the flying leopard fighter plane by loosening the drawn nails is implemented and verified on the control plane of the flying leopard fighter plane, and has a good actual use effect.

Although the embodiments of the present invention have been described above, the above description is only for the convenience of understanding the present invention, and is not intended to limit the present invention. It will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention as defined by the appended claims.