CN113665783B - Repair member for aircraft stringers and method of repairing an aircraft stringer - Google Patents
Repair member for aircraft stringers and method of repairing an aircraft stringer Download PDFInfo
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- CN113665783B CN113665783B CN202111179926.8A CN202111179926A CN113665783B CN 113665783 B CN113665783 B CN 113665783B CN 202111179926 A CN202111179926 A CN 202111179926A CN 113665783 B CN113665783 B CN 113665783B
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- 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
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/065—Spars
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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 invention relates to a repair for an aircraft stringer for docking and securing a stringer replacement to an aircraft stringer to be repaired, wherein the repair for an aircraft stringer comprises: a first side repair secured to the first side of the aircraft stringer at both ends and secured to the stringer replacement at an intermediate portion; and a second side repair secured at both ends to a second side of the aircraft stringer opposite the first side and secured at an intermediate portion to the stringer replacement. By this construction, double-sided repair of an aircraft stringer is enabled, suitable for local repair of an aircraft stringer, such as, but not limited to, repair of a stringer or a stringer in a confined space region having a height of less than 50 mm. In addition, this configuration reduces tolerance distribution requirements during stringer repairs, reduces repair difficulties and makes the repair process easy to implement. The invention also relates to a method of repairing an aircraft stringer.
Description
Technical Field
The present invention relates to a double-sided repair structure and repair method for an aircraft stringer, suitable for the local repair of various stringers, including but not limited to the repair of stringers below 50mm in height or stringers in small spatial areas. The allowance distribution is considered during repair, and a processing method for the small margin of the fastener and the interference between the nut and the R area is provided, so that the whole repair process is easy to realize.
The invention also relates to a method of repairing an aircraft stringer.
Background
Aircraft such as civil aircraft may cause damage to the stringers during production assembly and transportation due to improper installation or transportation. For the situation that the original strength of the aircraft stringer can be restored by replacing parts or repairing parts, the production progress and cost are affected if the aircraft stringer is replaced as a whole. During replacement of the stringers, hole deformation or other part damage may also result from fastener removal. After the model of the aircraft is put into operation, the long trusses are required to be repaired even if cracks or even cracks caused by corrosion or fatigue problems caused by environmental factors are broken, and the aircraft on the route only needs to replace a single long truss, so that a large number of parts are required to be disassembled, the stop time is too long, the economic cost loss caused by one day of stop is about 30 ten thousand yuan, the cost is high, and the aircraft is not acceptable by an airline company, so that a local repair scheme is often adopted. To ensure aerodynamic efficiency, for example, civil aircraft wing boxes are low in height (e.g., less than 50 mm), subject to space constraints, the "Z" or "J" stringers employed are also relatively low in height. In order to improve the structural design efficiency of the aircraft, the fasteners are also arranged as close to the R area of the rim and the web as possible, normal structural butt joint cannot be realized, the repair difficulty is further increased, and higher requirements are put forward for the reinforcing scheme.
In addition, when the wing or fuselage butt-joint stringers are short stringers, the repair space is narrow, and the conditions that the fasteners have short margins and nuts enter the R area are easy to occur. Meanwhile, the airplane stringers are bent along the axial direction, when the stringers are repaired, the requirements on tolerance distribution are high, the assembly is difficult due to three-face fitting, and the like, so that the repair difficulty is greatly increased, and the requirements on the stringer repair scheme are high. Therefore, the current general repair method has the problems of large weight of the repair structure, long repair time, poor manufacturability, easy occurrence of secondary damage in repair and the like. The present disclosure of patents or other publications at home and abroad is not related to this aspect.
In the patent of the invention filed by the applicant on 13 th 4 th 2020, publication number CN111392028A, a repair for a wing stringer and a method of repairing a wing stringer are disclosed. The repair disclosed therein is for the repair of the wing Z-stringer ends, and is a tailored one-piece repair.
The invention patent with publication number CN104386263A filed by Shenyang aviation aerospace university at 11/12 in 2014 discloses a splicing repair method of Z-shaped stringers on an aircraft, which adopts a graphite chip collecting and pollution-free processing device. The repair piece is a special stringer, and one end of the special stringer is provided with a stringer splicing piece. The application relates to repair of the ends of a wing Z-stringer and the repair is a tailored one-piece.
The disclosures in these documents all address the above-identified problems of the prior art, and thus there remains a need for a wing or fuselage stringer repair that overcomes one or more of the shortcomings of the prior art to reduce the difficulty of repair and to improve the efficiency and quality of wing or fuselage stringer repair.
Disclosure of Invention
The object of the present invention is to provide a repair for an aircraft stringer which ensures as little as possible of the aircraft downtime (AOG), increases the utilization of the aircraft, reduces the operating costs to the maximum extent and reduces the technical support pressure.
According to one aspect of the present invention, a repair for an aircraft stringer is provided for interfacing and securing a stringer replacement to an aircraft stringer to be repaired, wherein the repair for the aircraft stringer comprises: a first side repair secured to the first side of the aircraft stringer at both ends and secured to the stringer replacement at an intermediate portion; and a second side repair secured at both ends to a second side of the aircraft stringer opposite the first side and secured at an intermediate portion to the stringer replacement. With this construction, double sided or double sided repair of the aircraft stringers of an aircraft can be achieved, suitable for local repair of the aircraft stringers, such as, but not limited to, repair of stringers or stringers in small space areas, including those below 50mm in height. In addition, this configuration reduces tolerance distribution requirements during stringer repairs, reduces repair difficulties and makes the repair process easy to implement.
In accordance with the above aspect of the invention, the first side repair preferably may comprise an L-shaped member secured to the C-shaped region of the first side of the aircraft stringer against the upper stringer edge of the aircraft stringer; and a first plate secured to the aircraft stringer against a lower surface of the L-shaped member; additionally, the second side repair may include a Z-piece secured to the second side of the aircraft stringer against the stringer upper cap of the aircraft stringer; and a second plate secured to the aircraft stringer against a lower surface of the second Z-piece. The repair member of such a structure can be form-fitted to both sides of the aircraft stringer of the "J" shape or "Z" shape or the like, so that the structural shape of the aircraft stringer of the "J" shape or "Z" shape or the like can be more closely fitted to facilitate fastening of the repair member to the aircraft stringer.
According to the above aspect of the present invention, preferably, the first side repair may include: a first L-shaped member secured to the C-shaped region of the first side of the aircraft stringer against the upper stringer edge strip of the aircraft stringer; a second L-shaped member secured to the C-shaped region of the first side of the aircraft stringer against the lower surface of the first L-shaped member; and a first plate secured to the aircraft stringer against a lower surface of the second L-shaped member.
According to this aspect of the invention, preferably, the second side repair may include: a first Z-piece secured to a second side of the aircraft stringer against the stringer upper edge strip of the aircraft stringer; a second Z-piece secured to a second side of the aircraft stringer against a lower surface of the first Z-piece; and a second plate secured to the aircraft stringer against a lower surface of the second Z-piece.
The double-sided repair piece structure overlapped layer by layer is combined according to the cross section shape of the stringer, so that a C-shaped area of the stringer can be avoided, the double-sided repair piece structure is positioned at the lower part of the C-shaped area, the effective height for adjusting the centroid position of the cross section of the stringer is increased, and the gain repair effect is maximized by using minimum materials.
In accordance with the above aspect of the invention, the repair for an aircraft stringer preferably further comprises: and a third plate secured to the stringer replacement between the inner edge strip of the stringer replacement and the second Z. The double-sided repair structure considers the actual condition that the stringers are bent along the axial direction, and the tolerance distribution is optimized by adjusting the position of the third plate (or the groove plate) in the repair piece aiming at a narrow repair area, so that the assembly difficulty is greatly reduced.
According to the above aspect of the present invention, it is preferable that the repair for the aircraft stringer satisfies at least one of: the length of the first L-shaped piece in the longitudinal direction X is larger than that of the second L-shaped piece, and the length of the second L-shaped piece in the longitudinal direction X is larger than that of the first plate; the length of the first Z-shaped piece in the longitudinal direction X is greater than the length of the second Z-shaped piece, and the length of the second Z-shaped piece in the longitudinal direction X is greater than the length of the second plate. By this construction, on the one hand, a layer-by-layer installation of repair parts is facilitated, for example, firstly from both sides of the longer part (for example by means of fasteners), and on the other hand, a more uniform distribution of stresses between the stringer replacement part and the aircraft stringer to be repaired can be achieved, avoiding structural failures which may be caused by stress concentrations.
According to the above aspect of the invention, in order to better achieve stress distribution and centered installation of repair, it is preferred that the repair for the aircraft stringer meets at least one of the following: the centers of the first L-shaped piece, the second L-shaped piece and the first plate piece in the longitudinal direction X coincide with the center of the stringer replacing piece in the longitudinal direction X; the centers of the first Z-piece, the second plate and the third plate in the longitudinal direction X coincide with the center of the stringer replacement in the longitudinal direction X.
In accordance with the above aspect of the invention, preferably, the repair for the aircraft stringers includes threaded bores arranged in rows in the longitudinal direction X, and the stringer replacement is butted and secured to the aircraft stringer to be repaired by means of mating rows of threaded fasteners.
In accordance with the above aspect of the invention, the threaded fasteners preferably comprise three rows on the first side of the aircraft stringer, and each row of threaded fasteners is staggered in the longitudinal direction X on the inner edge strip, outer edge strip, and web of the stringer replacement. This further provides for more uniform distribution of stresses between the stringer replacement and the aircraft stringer to be repaired and facilitates installation of the fastener.
According to the above aspect of the present invention, preferably, the first plate member second plate member includes a rounded side portion that is fitted with the R region so as to be tightly fitted/engaged with the R region of the aircraft stringer, and the fastener pitch of the outside is ensured, so that the problems of smaller fastener margin and interference between the nut and the R region can be solved.
According to the above aspect of the invention, it is preferred that the repair for the aircraft stringer be longer in the longitudinal direction X than the stringer replacement, thereby avoiding the use of more repairs.
According to the above aspect of the present invention, it is preferable that the repair for the aircraft stringer satisfies at least one of: the lengths of the first side repair and the second side repair in the longitudinal direction X are equal; the lengths of the second L-shaped piece and the second Z-shaped piece in the longitudinal direction X are equal; or the third plate member and the second Z-shaped member are equal in length in the longitudinal direction X. In this way, the process of mounting and positioning the repair can be further simplified.
In accordance with the above aspects of the invention, the materials of the stringer replacement and the aircraft stringer may preferably be aluminum alloy materials and be J-stringers or Z-stringers; in addition, the material for the repair of the aircraft stringers may also be an aluminum alloy material. Thereby facilitating ensuring consistency in structural and other properties between the repair, stringer replacement and aircraft stringers, although the materials of the stringer replacement and aircraft stringers may be any materials known in the art and may be of any shape.
According to another aspect of the present invention, the present invention is directed to a method of repairing an aircraft stringer using a repair for an aircraft stringer according to the above aspect, the method may include the steps of:
a preparation step of cutting off damaged sections of the aircraft stringers and preparing corresponding stringer replacements;
positioning, namely aligning the stringer replacement part with the rest section of the aircraft stringer; and
a securing step of securing the stringer replacement to the remaining section of the aircraft stringer with a repair for the aircraft stringer.
According to the above aspect of the present invention, preferably, the fixing step may include: securing the first side repair and the second side repair in position with the remaining section of the aircraft stringer at the respective ends by means of a row of threaded fasteners; and securing the intermediate portions of the first side repair and the second side repair to the stringer replacement.
According to the above aspect of the present invention, preferably, the positioning step and the fixing step may further include: positioning the first L-shaped member, the first Z-shaped member, centered in the longitudinal direction X to coincide with the center of the stringer replacement and fixedly positioned at the respective ends with the remaining section of the aircraft stringer by means of a row of threaded fasteners; and aligning the second L-shaped member and the second Z-shaped member with the center of the stringer replacement in the longitudinal direction X and fixedly positioning the remaining section of the aircraft stringer at the respective ends with a row of threaded fasteners; the first and second plates are centered in the longitudinal direction X to coincide with the center of the stringer replacement, wherein the rounded sides of the first and second plates cooperate with the R-zone.
In summary, the repair of an aircraft stringer according to the invention enables double-sided repair or double-sided repair of an aircraft stringer of an aircraft and is suitable for the local repair of an aircraft stringer, in particular a short stringer. In addition, this configuration reduces tolerance distribution requirements during stringer repairs, reduces repair difficulties and makes the repair process easy to implement.
Drawings
FIG. 1 is a schematic perspective view of an aircraft stringer to be repaired with a damaged section in accordance with the present invention;
FIG. 2 is a schematic perspective view of a stringer replacement interfacing with an aircraft stringer to be repaired in accordance with the present invention;
FIG. 3 is a schematic perspective view of a repair for an aircraft stringer according to a non-limiting embodiment of the present invention;
FIG. 4 is a schematic cross-sectional view of a repair member secured to an aircraft stringer and stringer replacement in accordance with the present invention;
FIG. 5 is a schematic perspective view of a first L-shaped member according to a non-limiting embodiment of the present invention;
FIG. 6 is a schematic perspective view of a first Z-piece according to a non-limiting embodiment of the invention;
fig. 7 is a schematic perspective view of a first plate member according to a non-limiting embodiment of the present invention;
FIG. 8 is a schematic side view of a repair piece secured to an aircraft stringer and stringer replacement in accordance with the present invention;
FIG. 9 is a schematic view of a fastener for securing a repair to an aircraft stringer and stringer replacement in accordance with a non-limiting embodiment of the present invention;
FIG. 10 is a schematic illustration of an installation step for securing a repair to an aircraft stringer and stringer replacement in accordance with a non-limiting embodiment of the present invention;
FIG. 11 is a schematic illustration of another installation step for securing a repair to an aircraft stringer and stringer replacement in accordance with a non-limiting embodiment of the present invention; and
FIG. 12 is a schematic view of yet another installation step for securing a repair to an aircraft stringer and stringer replacement in accordance with a non-limiting embodiment of the present invention.
The figures are merely schematic and are not drawn to scale.
List of reference numerals in the figures and examples:
100-repair for aircraft stringers; comprising the following steps:
10-first side repair
11-first L-shaped piece
12-second L-shaped piece
13-first plate
20-second side repair
21-first Z-shaped piece
22-second Z-shaped piece
23-second plate
30-third plate
200-stringer replacement; comprising
201-replacement inner rim strip
202 a replacement piece outer edge strip
203-replacement web
300-aircraft stringers; comprises the following steps of;
301-stringer inner edge strip
302-stringer outer edge strip
303-stringer web
310-first side
320-second side
330-lesion segment
400-fasteners;
500-skin.
Detailed Description
It is to be understood that the invention may assume various alternative orientations and step sequences, except where expressly specified to the contrary. It should be further understood that the specific devices illustrated in the accompanying drawings and described in the specification are simply exemplary embodiments of the inventive concepts disclosed and defined herein. Thus, unless explicitly stated otherwise, the particular paths of motion, directions, or other physical features to which the various embodiments disclosed relate should not be considered limiting.
The terminology used herein for the purpose of describing embodiments of the invention is described below.
And (3) the following steps: near the fuselage or wing skin;
the following steps: away from the fuselage or wing skin;
length: the lengths described herein are along the longitudinal direction of the aircraft stringers (i.e., direction X);
thickness: the thicknesses described herein are in a direction perpendicular to the fuselage or wing skin (i.e., in the direction of direction Y).
The repair 100 for an aircraft stringer 300 in accordance with a non-limiting embodiment of the present invention is described in detail below with reference to the accompanying drawings to provide a more clear understanding of the principles and advantageous technical effects of the present invention.
FIG. 1 is a schematic perspective view of an aircraft stringer 300 to be repaired with a damaged section 330 in accordance with the present invention. During aircraft manufacturing, aircraft stringers may be damaged by installation or shipping, creating damaged sections 330, or may crack or even fracture due to corrosion or fatigue problems caused by environmental factors after the aircraft is put into operation, creating damaged sections 330.
After damage occurs, to reduce costs, a partial repair scheme is typically employed, i.e., the damaged section 330 of the aircraft stringer 300 is removed and replaced with the stringer replacement 200. FIG. 2 is a schematic perspective view of a stringer replacement 200 according to the present invention docked to an aircraft stringer 300 to be repaired.
In the embodiment shown in fig. 1 and 2, the aircraft stringer 300 is shown as having a "J" shaped cross section, but it should be understood that the aircraft stringer 300 having such a cross section is shown merely to better illustrate the principles of the present invention and not to limit the invention, and that the repair 100 according to the present invention may alternatively be used with other types of aircraft stringers, such as aircraft stringers having a "Z" shaped cross section, and the like.
For these aircraft stringers having a "J" or "Z" shaped cross-section, the present invention proposes a repair 100 for an aircraft stringer for repair from both sides. FIG. 3 is a schematic perspective view of a repair 100 for an aircraft stringer in accordance with a non-limiting embodiment of the present invention. As shown, the repair 100 has a first side repair 10 and a second side repair 20 that correspond to the shape of both sides of the aircraft stringer 300, respectively, so as to form fit to the aircraft stringer 300. It should be appreciated that the length of the repair 100 for an aircraft stringer in the longitudinal direction X may be greater than the length of the stringer replacement 200, thereby reliably securing the stringer replacement 200 to the aircraft stringer 300 and reducing the number of repairs required.
FIG. 4 is a schematic cross-sectional view of a repair 100 according to the present invention secured to an aircraft stringer 300 and stringer replacement 200.
As shown, aircraft stringer 300 is shown as a stringer having a J-shaped cross-section and includes a first side 310 and a second side 320 opposite first side 310 in the Z-direction, first side 310 may have a C-shaped region and second side 320 may have a Z-shaped region opposite the C-shaped region. Additionally, aircraft stringer 300 also includes stringer inner edge strips 301, stringer outer edge strips 302, and stringer webs 303. A skin 500 of a fuselage or wing is secured to the aircraft stringer 300 above the stringer outer cap 302. Repair member 100 interfaces and secures stringer replacement member 200 to aircraft stringer 300 to be repaired, respectively, from both sides of aircraft stringer 300. The first side repair 10 is secured at both ends to a first side 310 of the aircraft stringer 300 and is secured at an intermediate portion to the stringer replacement 200; and the second side repair 20 is secured at both ends to a second side 320 of the aircraft stringer 300 opposite the first side 310 and is secured in the middle to the stringer replacement 200.
According to a non-limiting embodiment of the invention and as shown in detail in fig. 3 and 4, the repair 100 may generally comprise 7 separate individual components, wherein the first side repair 10 comprises a first L-shaped member 11, a second L-shaped member 12 and a first plate member 13 arranged in a superimposed manner in the vertical direction Y shown in fig. 4.
Likewise, the second side repair 20 includes a first Z-shaped piece 21, a second Z-shaped piece 22, and a second plate piece 23 that are arranged in superposition in the vertical direction Y shown in fig. 4;
fig. 5-7 are schematic perspective views of a first L-shaped member 11, a first Z-shaped member 12 and a first plate member 13, respectively, according to a non-limiting embodiment of the present invention. The material of the first L-shaped member 11, the first Z-shaped member 12 and the first plate member 13 may be an aluminum alloy material, for example, a sheet metal member as shown in fig. 5 to 7 by press working. Although not shown in the figures, the first L-shaped member 11, the first Z-shaped member 12, and the first plate member 13 are each provided with an aperture for securing to the aircraft stringer 300.
The second L-shaped member 12, the second Z-shaped member 22 and the second plate member 23 may be the same shape as the first L-shaped member 11, the first Z-shaped member 12 and the first plate member 13 shown in fig. 5 to 7, but their lengths and thicknesses may be different. And likewise the material of the second L-shaped member 12, the second Z-shaped member 22 and the second plate member 23 may be an aluminum alloy material, for example, a sheet metal member as shown in fig. 5 to 7 by press working. Although not shown in the figures, the second L-shaped member 12, the second Z-shaped member 22, and the second plate member 23 are each provided with an aperture for securing to the aircraft stringer 300.
For example, in one non-limiting embodiment, the length of the first L-shaped member 11 in the longitudinal direction X may be greater than the length of the second L-shaped member 12, and the length of the second L-shaped member 12 in the longitudinal direction X is greater than the length of the first plate member 13. In another non-limiting embodiment, the thickness of the first L-shaped member 11 in the vertical direction Y may be smaller than the thickness of the second L-shaped member 12, and the thickness of the second L-shaped member 12 in the vertical direction Y may be smaller than the thickness of the first plate member 13.
Likewise, in one non-limiting embodiment, the length of the first Z-shaped piece 21 in the longitudinal direction X may be greater than the length of the second Z-shaped piece 22, and the length of the second Z-shaped piece 22 in the longitudinal direction X may be greater than the length of the second plate member 23. In another non-limiting embodiment, the thickness of the first zigzag member 21 in the vertical direction Y may be smaller than the thickness of the second zigzag member 22, and the thickness of the second zigzag member 22 in the vertical direction Y may be smaller than the thickness of the second plate member 23.
With continued reference to fig. 3 and 4, in particular, the first L-shaped member 11 is secured to the C-shaped region of the first side 310 of the aircraft stringer 300 against the stringer upper edge strip 301 of the aircraft stringer 300 in a form-fitting manner; the second L-shaped member 12 is secured to the C-shaped region of the first side 310 of the aircraft stringer 300 against the lower surface of the first L-shaped member 11 in the Y-direction (i.e., the surface opposite the surface against the aircraft stringer 300); the first plate 13 is secured to the aircraft stringer 300 against the lower surface of the second L-shaped member 12 in the Y-direction.
Likewise, first Z-piece 21 is secured to second side 320 of aircraft stringer 300 against the above-described stringer upper edge strip 301 of aircraft stringer 300; second Z-piece 22 is secured to second side 320 of aircraft stringer 300 against a lower surface of first Z-piece 21 in the Y-direction (i.e., the surface opposite the surface against aircraft stringer 300); and the second plate 23 is secured to the aircraft stringer 300 against the lower surface of the second Z-piece 22 in the Y-direction.
In addition, the repair 100 may also include a third plate 30, with the third plate 30 secured to the stringer replacement 200 between the inner edge strip 201 of the stringer replacement 200 and the second Z-member 22. The material of the third plate member 30 may be an aluminum alloy material, for example, a sheet metal member as shown in fig. 7 by press working. Although not shown in the figures, third panel 30 may be provided with apertures for securing to aircraft stringer 300.
The first plate 13, the second plate 23, and the third plate 30 may be processed to a desired thickness as needed, for example, by grinding or the like.
It should be appreciated that while in the embodiment illustrated in connection with the figures, the repair 100 may generally comprise 7 separate individual components, in alternative embodiments, the repair 100 may comprise other numbers of repairs, such as 3, 5, 6, 8, or 9, etc., without departing from the scope of the present disclosure. For example, in embodiments comprising 5 separate individual components, the first L-shaped member 11 and the second L-shaped member 12 may be formed as a single component, such as a single L-shaped member; while the first Z-piece 21 and the second Z-piece 22 may be formed as a single piece, e.g. as separate Z-pieces. Alternatively, additional components, such as a third L-shaped member, may be added between the first L-shaped member 11 and the second L-shaped member 12 to form a repair having 8 separate components, or further, additional components, such as a third Z-shaped member, may be added between the first Z-shaped member 21 and the second Z-shaped member 22 to form a repair having 9 separate components. For the sake of brevity, the invention is not intended to list a possible scenario, but a person skilled in the art may choose a suitable number of components depending on the actual situation without departing from the scope of the invention.
Additionally, while the present invention describes a repair 100 for an aircraft stringer with a "J" shaped cross section with reference to the drawings, and specifically describes an L-shaped member and a Z-shaped member, other shapes of repair are contemplated by those skilled in the art in an aircraft stringer with a "Z" shaped cross section or other types of aircraft stringers for form-fitting installation onto the aircraft stringer 300 and stringer replacement 200 from both sides of the aircraft stringer without departing from the scope of the present invention.
The inventor has appreciated that in the partial repair of aircraft stringer 300, even a larger number of threaded fasteners may be used, which may be faced with the problem of smaller fastener margins and interference between the nut and the R-zone. In accordance with a preferred embodiment of the present invention, the first 13 and second 23 panels may include a rounded portion at one side that mates with an R-zone, i.e., the rounded region between the upper stringer edge strip 301 and the stringer web 302 of the aircraft stringer 300. The above problems in the prior art can be solved by the way that the plate is matched with the R region.
According to a non-limiting embodiment of the invention and as a preferred example, the centers of the first L-shaped member 11, the second L-shaped member 12 and the first plate member 13 in the longitudinal direction X coincide with the center of the stringer replacement 200 in the longitudinal direction X; and the centers of the first, second, and third Z- pieces 21, 22, 23, and 30 in the longitudinal direction X coincide with the center of the stringer replacement 200 in the longitudinal direction X.
FIG. 8 is a schematic side view of a repair 100 according to the present invention secured to an aircraft stringer 300 and stringer replacement 200.
As shown, the first L-shaped member 11, the second L-shaped member 12, and the first plate member 13 of the repair member 100 are disposed superimposed on one side of the C-shaped region of the aircraft stringer 300 in the vertical direction Y, while the first Z-shaped member 21, the second Z-shaped member 22, and the second plate member 23 are disposed superimposed on the other side of the aircraft stringer 300 opposite the C-shaped region in the vertical direction Y, and the third plate member 30 is disposed between the inner edge strip 201 of the stringer replacement member 200 and the second Z-shaped member 22. The length of the first L-shaped member 11 in the longitudinal direction X is greater than the length of the second L-shaped member 12, and the length of the second L-shaped member 12 in the longitudinal direction X is greater than the length of the first plate member 13. The length of the first zigzag member 21 in the longitudinal direction X is greater than the length of the second zigzag member 22, and the length of the second zigzag member 22 in the longitudinal direction X is greater than the length of the second plate member 23. The length of the third plate member 30 in the longitudinal direction X is equal to the length of the first Z-shaped piece 21.
FIG. 9 is a schematic view of a fastener for securing a repair member to an aircraft stringer and stringer replacement in accordance with a non-limiting embodiment of the present invention. As shown, the repair 100 for an aircraft stringer includes threaded bores arranged in rows in the longitudinal direction X, and the stringer replacement 200 is docked and secured to the aircraft stringer 300 to be repaired by means of mating rows of threaded fasteners 400.
In accordance with a non-limiting embodiment of the present invention and as a preferred example, the threaded fasteners 400 comprise three rows on a first side (i.e., the side having the C-shaped region) of the aircraft stringer 300, and each row of threaded fasteners 400 are staggered in the longitudinal direction X on the inner edge strip 201, outer edge strip 202, and web 203 of the stringer replacement 200 to facilitate installation construction operations and to provide a more uniform stress distribution therebetween to approximate as closely as possible the structural and mechanical properties of an undamaged aircraft stringer.
Figures 10-12 illustrate various mounting steps for securing repair piece 100 to aircraft stringer 300 and stringer replacement 200, respectively, in accordance with a non-limiting embodiment of the present invention.
In a preparation step, the damaged section 330 of the aircraft stringer 300 is cut and the corresponding stringer replacement 200 is prepared.
In the positioning step, the stringer replacement 200 is positioned in alignment with the remaining sections of the aircraft stringer 300.
In addition, the positioning step may optionally further include: positioning the centers of the first L-shaped member 11, the first Z-shaped member 21 in the longitudinal direction X to coincide with the center of the stringer replacement 200; centering the second L-shaped member 12 and the second Z-shaped member 22 in the longitudinal direction X to coincide with the center of the stringer replacement; and/or centering the first plate 13 and the second plate 23 in the longitudinal direction X to coincide with the center of the stringer replacement 200,
in the securing step, the stringer replacement 200 is secured to the remaining section of the aircraft stringer 300 with the repair 100 for the aircraft stringer. For example, first side repair 10 and second side repair 20 are first fixedly positioned with the remaining section of aircraft stringer 300 at the respective ends by means of a row of threaded fasteners 400; the intermediate portions of the first side repair 10 and the second side repair 20 are then secured to the stringer replacement 200.
According to a non-limiting embodiment of the present invention and as shown in fig. 10-12. In the securing step shown in fig. 10, the centers of the first L-shaped member 11, the first Z-shaped member 21, and the third plate member 13 in the longitudinal direction X are positioned to coincide with the center of the stringer replacement 200 and are secured in position with the remaining sections of the aircraft stringer 300 at the respective ends by means of a row of threaded fasteners 400. As described above, the first L-shaped member 11, the first Z-shaped member 21, and the third plate member 13 may be the longest parts of the repair member 100.
In the securing step shown in FIG. 11, the second L-shaped member 12 and the second Z-shaped member 22 are centered in the longitudinal direction X coincident with the center of the stringer replacement 200 and are secured in place with the remaining sections of the aircraft stringer 300 at the respective ends by a row of threaded fasteners 400; as described above, the second L-shaped member 12 and the second Z-shaped member 22 may be shorter members than the first L-shaped member 11, the first Z-shaped member 21, and the third plate member 13.
In the securing step shown in fig. 12, the center of the first plate 13 and the second plate 23 in the longitudinal direction X is positioned coincident with the center of the stringer replacement 200, wherein the rounded sides of the first plate 13 and the second plate 23 cooperate with the R-zone.
Alternatively, and as shown, the threaded fasteners 400 may be staggered at the locations of the stringer inner edge strips 301, stringer outer edge strips 302, and stringer webs 303 to facilitate construction operations and to facilitate more uniform forces distributed between the repair 100 for an aircraft stringer, the stringer replacement 200, and the aircraft stringer 300.
By the repair member 100 for an aircraft stringer of the present invention, such that a portion of the repair member avoids the stringer within the C-shaped region, below the C-shaped region, the effective height for adjusting the position of the centroid of the cross-section of the stringer is increased, maximizing the gain repair effect with minimal material. The invention considers the actual situation that the airplane stringer is bent along the axial direction, and aims at a narrow repair area, and the tolerance distribution is optimized by adjusting the position of the third plate (groove plate) in the repair piece, so that the assembly difficulty is greatly reduced. Meanwhile, the invention provides a processing method for the interference between the nut and the R area, which has smaller margin of the fastener, and the whole repair process is easy to realize. The aircraft stringers can be constructed as a complete load bearing structure after repair without changing the force transfer relationship of the perimeter structure.
As used herein, the terms "first" or "second" and the like used to denote sequences are merely used to better understand the concept of the invention shown in the form of preferred embodiments by those of ordinary skill in the art, and are not intended to limit the invention. Unless otherwise indicated, all orders, orientations, or orientations are used solely for the purpose of distinguishing one element/component/structure from another element/component/structure, and do not denote any particular order, mounting order, direction, or orientation unless otherwise indicated. For example, in alternative embodiments, "first plate" may be used to refer to "second plate" and "lower surface" may alternatively be "upper surface".
In view of the above, the repair 100 for an aircraft stringer according to embodiments of the present invention overcomes the shortcomings of the prior art and achieves the intended aim.
While the repair of an aircraft stringer of the present invention has been described above in connection with a preferred embodiment, those of ordinary skill in the art will recognize that the above examples are for illustrative purposes only and are not intended to be limiting. Accordingly, the present invention may be variously modified and changed within the spirit of the claims, and all such modifications and changes are intended to fall within the scope of the claims of the present invention.
Claims (9)
1. A repair piece (100) for an aircraft stringer (300), the repair piece (100) for interfacing and securing a stringer replacement (200) to an aircraft stringer (300) to be repaired, the repair piece (100) comprising:
a first side repair (10) secured at both ends to a first side (310) of the aircraft stringer (300) and secured at an intermediate portion to the stringer replacement (200); and
a second side repair (20) secured at both ends to a second side (320) of the aircraft stringer (300) opposite the first side (310) and secured at an intermediate portion to the stringer replacement (200),
wherein the first side repair (10) comprises:
-a first L-shaped member (11) secured to a C-shaped region of the first side (310) of the aircraft stringer (300) against a stringer upper edge strip (301) of the aircraft stringer (300);
-a second L-shaped member (12) secured to the C-shaped region of the first side (310) of the aircraft stringer (300) against a lower surface of the first L-shaped member (11); and
a first plate (13) secured to the aircraft stringer (300) against a lower surface of the second L-shaped member (12).
2. The repair (100) for an aircraft stringer of claim 1, wherein the second side repair (20) comprises:
a first Z-piece (21) secured to a second side (320) of the aircraft stringer (300) against the stringer upper edge strip (301) of the aircraft stringer (300);
-a second Z-piece (22) secured to a second side (320) of the aircraft stringer (300) against a lower surface of the first Z-piece (21); and
-a second plate (23) secured to the aircraft stringer (300) against a lower surface of the second Z-piece (22).
3. The repair for an aircraft stringer (100) of claim 2, wherein the repair for an aircraft stringer (100) further comprises: a third plate (30) secured to the stringer replacement (200) between the inner edge strip (201) of the stringer replacement (200) and the second Z (22).
4. A repair (100) for an aircraft stringer according to claim 3 in which the repair (100) for an aircraft stringer meets at least one of:
-the length of the first L-shaped piece (11) in the longitudinal direction (X) is greater than the length of the second L-shaped piece (12), and-the length of the second L-shaped piece (12) in the longitudinal direction (X) is greater than the length of the first plate (13);
the length of the first Z-shaped piece (21) in the longitudinal direction (X) is greater than the length of the second Z-shaped piece (22), and the length of the second Z-shaped piece (22) in the longitudinal direction (X) is greater than the length of the second plate (23).
5. The repair for an aircraft stringer (100) of claim 4, wherein the repair for an aircraft stringer (100) meets at least one of:
-the centre of the first L-shaped piece (11), the second L-shaped piece (12) and the first plate (13) in the longitudinal direction (X) coincides with the centre of the stringer replacement (200) in the longitudinal direction (X);
the centers of the first Z-shaped piece (21), the second Z-shaped piece (22), the second plate piece (23) and the third plate piece (30) in the longitudinal direction (X) are coincident with the center of the stringer replacement piece (200) in the longitudinal direction (X).
6. The repair for an aircraft stringer (100) of any of claims 1-5, wherein the repair for an aircraft stringer (100) comprises threaded holes arranged in rows in a longitudinal direction (X) and the stringer replacement (200) is docked and secured to the aircraft stringer (300) to be repaired by means of mating rows of threaded fasteners (400).
7. The repair for an aircraft stringer (100) of claim 6, wherein the threaded fasteners (400) comprise three rows on a first side of the aircraft stringer (300), and each row of threaded fasteners (400) is staggered in the longitudinal direction (X) on an inner edge strip (201), an outer edge strip (202), and a web (203) of the stringer replacement (200).
8. A method of repairing an aircraft stringer (300) using a repair (100) for an aircraft stringer according to any of claims 1 to 7, the method comprising the steps of:
a preparation step of cutting off a damaged section (330) of the aircraft stringer (300) and preparing a corresponding stringer replacement (200);
a positioning step of aligning the stringer replacement (200) with a remaining section of the aircraft stringer (300); and
-a fixing step of fixing the stringer replacement (200) to the remaining section of the aircraft stringer (300) by means of the repair (100) for the aircraft stringer.
9. The method of repairing an aircraft stringer (300) of claim 8, wherein said securing step comprises:
-fixedly positioning the first side repair (10) and the second side repair (20) with the remaining section of the aircraft stringer (300) at respective ends by means of a row of threaded fasteners (400); and
-securing intermediate portions of the first side repair (10) and the second side repair (20) to the stringer replacement (200).
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| CN202111179926.8A CN113665783B (en) | 2021-10-09 | 2021-10-09 | Repair member for aircraft stringers and method of repairing an aircraft stringer |
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| CN202111179926.8A CN113665783B (en) | 2021-10-09 | 2021-10-09 | Repair member for aircraft stringers and method of repairing an aircraft stringer |
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Family Cites Families (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH08284428A (en) * | 1995-04-18 | 1996-10-29 | Ohbayashi Corp | Method for repairing existing steel frame material |
| US20070259171A1 (en) * | 2006-05-02 | 2007-11-08 | 3M Innovative Properties Company | Repair laminate for mounting brackets and method of using the same |
| US8844108B2 (en) * | 2011-07-12 | 2014-09-30 | The Boeing Company | Large area repair of composite aircraft |
| GB2517954B (en) * | 2013-09-05 | 2018-07-04 | Airbus Operations Ltd | Repair of a damaged composite aircraft wing |
| EP2873620B1 (en) * | 2013-11-14 | 2018-05-16 | Airbus Operations GmbH | Repair method for fuselage components of aircraft or spacecraft |
| CN104386263A (en) * | 2014-11-12 | 2015-03-04 | 沈阳航空航天大学 | Splicing and repairing method of Z-shaped stringer on airplane |
| GB201511402D0 (en) * | 2015-06-30 | 2015-08-12 | Short Brothers Plc | Repair including a chamfered bracket and a chamfered bracket component for reinforcing a damaged structural element made from composite materials |
| EP3519169A1 (en) * | 2016-09-27 | 2019-08-07 | Bombardier Inc. | Method for repairing a composite stringer with a composite repair cap |
| EP3321189B1 (en) * | 2016-11-11 | 2021-03-03 | Airbus Operations GmbH | Method for reconditioning of a damaged portion of a component and insert therefor |
| CN109110150A (en) * | 2018-08-10 | 2019-01-01 | 广州飞安航空科技有限公司 | A kind of Aircraft Metal Structure reinforcement repairing strength and stiffness accordance method and system |
| CN111392028A (en) * | 2020-04-13 | 2020-07-10 | 中国商用飞机有限责任公司 | Stringer repair for wing stringers and method of repairing wing stringers |
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