Abstract:
The present invention provides a method for locating a machining position in a repair material that is arranged on a member including a machined portion formed by predetermined machining, the method including: a step of arranging a marker including a portion having a different propagation characteristic of an ultrasonic wave from that of a peripheral portion in the machined portion existing in the member before the repair material is arranged on the member; and a step of applying the ultrasonic wave to the member covered with the repair material and locating the machining position at a position of the marker captured by the ultrasonic wave after the repair material is arranged on the member.

Description:
BACKGROUND OF THE INVENTION 
       [0001]    1. Field of the Invention 
         [0002]    The present invention relates to a method for locating a machining position, which enables to apply machining originally applied to a repair target to a repair material used for repair at the same position. 
         [0003]    2. Description of the Related Art 
         [0004]    When an airframe of aircraft formed from a composite material is repaired, a composite patch is arranged in a recessed portion formed by scraping away a damaged point, and is shaped by curing the composite patch and an adhesive by heating while drawing a vacuum (for example, Japanese Patent Laid-Open No. 2014-100847). Ultrasonic testing is performed in order to examine a state of damage before repair, a quality after repair, or the like in a nondestructive manner. 
         [0005]    A method for generating a design of a repair member for efficiently repairing an extensive repair region has been proposed (Japanese Patent Laid-Open No. 2013-28332). 
         [0006]    When a fastener that fastens airframe parts is included in the repair region, a through-hole into which the fastener is inserted is machined in the composite patch after the composite patch is shaped by curing. At this time, it is necessary to form a hole at the same position as an original through-hole left on a back side of the composite patch. However, since the original through-hole is concealed by the composite patch, the original through-hole cannot be seen. 
         [0007]    Thus, a distance from a distinctive portion of the airframe to the fastener in the repair region is measured in advance, and a hole machining position on the composite patch is located based on the distance. Alternatively, the hole machining position is located by fabricating a positioning jig. 
         [0008]    In the case in which the distance from a distinctive portion of the airframe to the fastener in the repair region is measured, an appropriate distinctive portion does not always exist near the fastener, and an error proportional to the distance is included in a measurement value. There is also a possibility that an artificial measurement error occurs. 
         [0009]    On the other hand, when the positioning jig is used, location accuracy is high. However, it is necessary to fabricate a jig corresponding to a repair target every time, so that it takes time and cost for the repair. 
         [0010]    Thus, an object of the present invention is to provide a method that enables to accurately locate a machining position in a repair material while reducing a time and a cost required for repair. 
       SUMMARY OF THE INVENTION 
       [0011]    The present invention is a method for locating a machining position in a repair material that is arranged on a member including a machined portion formed by predetermined machining, the method including: a step of arranging a marker including a portion having a different propagation characteristic of an ultrasonic wave from that of a peripheral portion in the machined portion existing in the member, or ensuring a hollow in the machined portion before the repair material is arranged on the member; and a step of applying the ultrasonic wave to the member covered with the repair material and locating the machining position at a position of the marker captured by the ultrasonic wave after the repair material is arranged on the member. 
         [0012]    In accordance with the present invention, it is possible to easily locate the machining position by ultrasonic testing by using the marker or the hollow ensured in the machined portion without fabricating an expensive jig or without measuring a distance from a distinctive portion of an airframe to the machined portion. 
         [0013]    The repair material in the present invention can include a repair patch that covers the member, and an adhesive that bonds the repair patch to the member that is a repair target. 
         [0014]    In the present invention, the marker including air may be used. 
         [0015]    Since the air has a very different wave propagation characteristic from those of materials of the repair material and the repair target member, it is possible to easily locate the accurate machining position at the position of the marker that is made visible by the ultrasonic testing. 
         [0016]    In a case in which the machined portion is a through-hole that passes through the member or a hole that is formed in the member, an inside of the machined portion may be entirely filled and sealed by the marker and a seal material before the repair material is arranged on the member. Accordingly, when a damaged point is cut off, a tool is not caught on an edge of the machined portion, and the damaged point can be cut off in a desired shape. 
         [0017]    In a case in which the machined portion is a through-hole that passes through the member or a hole that is formed in the member similarly to the above case, the marker may have an indicating member in a form pointing to an axial center of the marker, or a hollow in a form pointing to the axial center. 
         [0018]    The indicating member or the hollow in the above form indicates an axial center of the through-hole or the hole based on a difference in a wave propagation characteristic with its peripheral portion. Thus, it is possible to accurately locate the machining position. 
         [0019]    The present invention is particularly suitable for a case in which the repair material having a repair patch formed from a fiber reinforced resin before curing is used. If a machined portion is formed in the repair patch (called a prepreg) in advance, a shape of the machined portion is changed when the repair patch is joined to the member by heat-curing. It is thus necessary to machine the repair patch after the repair patch is joined. In accordance with the present invention, it is possible to locate a position of the machined portion covered with the repair patch by the ultrasonic testing by using the marker after the repair patch is joined. 
         [0020]    A repairing method of the present invention including the above method for locating a machining position is a method using a repair material that is arranged on a member including a machined portion formed by predetermined machining, the method including: a first step of arranging a marker including a portion having a different propagation characteristic of an ultrasonic wave from that of a peripheral portion in the machined portion existing in the member before the repair material is arranged on the member; a second step of joining the repair material to the member; a third step of applying the ultrasonic wave to the member covered with the repair material and locating the machining position at a position of the marker captured by the ultrasonic wave; and a fourth step of applying machining to the machining position of at least the repair material out of the repair material and the member. 
         [0021]    In accordance with the present invention, a repair target can be restored by correctly applying machining to the same machining position as an original position. 
         [0022]    In a case in which the machined portion existing in the member is a through-hole that passes through the member, it is preferable that the method includes a sealing step of sealing an inside of the through-hole by a seal material before the repair material is arranged on the member, in the second step, the repair material is cured by heating while a pressure between the repair material and the member is being reduced, and in the fourth step, the marker and the seal material are removed by applying machining to the machining position throughout the repair material and the member. 
         [0023]    The pressure reduction in the heating is enabled by sealing the through-hole. It is possible to surely join the repair material to the member by pressing the repair material against the member by a pressure difference with an atmospheric pressure. 
         [0024]    It is also possible to remove the seal material and the marker at the same time as applying machining to the located machining position. 
         [0025]    In the above sealing step, the inside of the through-hole is preferably filled entirely and sealed by the marker and the seal material. 
         [0026]    Accordingly, when a damaged point is cut off, a tool is not caught on an edge of the through-hole, and the damaged point can be cut off in a desired shape. 
         [0027]    In another method for locating a machining position of the present invention, the machined portion is a through-hole that passes through the member, or a hole that is formed in the member, a hollow is left within the machined portion after the repair material is arranged on the member, and the method includes a step of applying an ultrasonic wave to the member covered with the repair material, and locating the machining position at a position of the hollow captured by the ultrasonic wave. 
         [0028]    The hollow left in a portion or the whole of the machined portion functions similarly to the above marker. 
         [0029]    In other words, when the hollow is not left within the machined portion, the position of the machined portion can be indicated by the above marker. 
         [0030]    The method for locating a machining position in a repair material, and the repairing method described above are suitable for repairing a member that constitutes an aircraft. 
         [0031]    In accordance with the present invention, it is possible to accurately locate the machining position in the repair material while reducing a time and a cost required for the repair. 
     
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         [0032]      FIGS. 1A-1F  are views for explaining repair steps according to an embodiment of the present invention; 
           [0033]      FIG. 2  is a flowchart illustrating the repair steps according to the embodiment of the present invention; 
           [0034]      FIG. 3A  is a view illustrating a state in which a through-hole included in a repair region of a member is filled with a marker and a resin material,  FIG. 3B  is a perspective view illustrating the marker, and  FIG. 3C  is a view illustrating another example of a seal material; 
           [0035]      FIG. 4A  is a view for explaining a heating step while reducing a pressure, and  FIG. 4B  is a view for explaining a step of locating a hole machining position by ultrasonic testing; 
           [0036]      FIGS. 5A-5C  show preferable markers in which  FIG. 5A  and  FIG. 5C  are plan views and  FIG. 5B  is a perspective view; 
           [0037]      FIGS. 6A to 6C  are views illustrating various examples of the marker; and 
           [0038]      FIG. 7  is a view illustrating a modification of the present invention. 
       
    
    
     DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS 
       [0039]    In the following, an embodiment of the present invention will be described by reference to the accompanying drawings. 
         [0040]    In the present embodiment, repair of a composite material that is used for an airframe of an aircraft is described. 
         [0041]    In the present specification, the “composite material” means a fiber reinforced resin containing reinforcing fibers such as carbon fibers and glass fibers. 
         [0042]    In the present embodiment, repair in a case in which a through-hole into which a fastener is inserted is included in a region of the airframe subjected to the repair is described. 
         [0043]      FIG. 1A  shows a panel  10  that is formed from a composite material. The panel  10  includes a plurality of layers laminated by an appropriate number according to a required thickness. Each of the layers is composed of a sheet-shaped fiber substrate, and a resin impregnated into the fiber substrate. 
         [0044]    The panel  10  may be also formed from a metal material such as aluminum alloy. 
         [0045]    The panel  10  is fastened to another member (not shown) by fasteners  11 . A through-hole  12  into which each of the fasteners  11  is inserted is formed in the panel  10  along a thickness direction. 
         [0046]    When the panel  10  is damaged by an impact, it is necessary to perform repair in a region necessary for ensuring sufficient strength/stiffness, including a damaged point. 
         [0047]    In the repair, ultrasonic testing is performed to examine a state of damage within the panel  10 . For example, delamination is considered as the damage within the panel  10  made of the composite material. 
         [0048]    A region  13  (an upper side of an alternate long and short dash line in  FIG. 1A ) in which the panel  10  is scraped away and removed is determined based on a size, a position, and a degree of the damage obtained by the ultrasonic testing ( FIG. 2 , step S 1 ). The removed region  13  includes the entire damage. A removed portion is replaced with a repair patch  14  ( FIG. 1D ) formed from a composite material. 
         [0049]    Before the damaged point is scraped away, the inside of the through-hole  12  that is at least partially included in the removed region  13  ( FIG. 1A ) is entirely filled with a resin material  15  as shown in  FIG. 1B . At this time, a marker  20  is arranged within the through-hole  12 , and is embedded in the resin material  15  ( FIG. 2 : step S 2 ). 
         [0050]    The resin material  15  is formed by putting a resin material having fluidity into the through-hole  12 , and curing the resin material. The cured resin material  15  has heat resistance enough to retain its shape even when the repair patch  14  is heated. 
         [0051]    Since the inside of the through-hole  12  is sealed by the resin material  15 , vacuum drawing can be performed when the repair patch  14  is heated. 
         [0052]    The marker  20  indicates a position where a hole continuing to the through-hole  12  is machined in the repair patch  14 . As shown in  FIGS. 3A and 3B , the marker  20  includes air AR within a substantially-cylindrical outer shell  20 A. An upper end and a lower end of the outer shell  20 A are closed, and a hollow is formed within the outer shell  20 A. The outer shell  20 A can be formed from any material such as resin and metal. 
         [0053]    The marker  20  is arranged within the through-hole  12  before the repair patch  14  ( FIG. 1D ) is arranged and joined to the panel  10  in order to subsequently locate a position of the through-hole  12  through which the fastener  11  is passed. The marker  20  is installed within the through-hole  12  so as to be positioned below the removed region  13  of the panel  10  in the through-hole  12 . It is preferable to substantially align an axial center of the outer shell  20 A with a hole axis (an axial center) of the through-hole  12 . 
         [0054]    The marker  20  has heat resistance enough to retain its shape even when the repair patch  14  is heated, and keep a state in which the air AR is included. After the repair patch  14  is joined to the panel  10 , a position where a hole is to be machined in the repair patch  14  is located by ultrasonic testing by using the marker  20 . 
         [0055]    In a state in which the through-hole  12  is filled with the resin material  15 , the damaged point is scraped away and removed by using a tool ( FIG. 1C ,  FIG. 2 : step S 3 ). Accordingly, the tool is not caught on an edge of the through-hole  12 , and a desired cut surface  16  having a truncated cone shape can be obtained. In order to ensure a sufficient junction area between the repair patch  14  and the base material (the panel  10 ), the cut surface  16  is formed at a gentle inclination angle. 
         [0056]    Although the through-hole  12  is positioned in a bottom surface  16 A of the cut surface  16  in  FIG. 1 , the through-hole  12  may be positioned in a slanting surface  16 B of the cut surface  16 . 
         [0057]    Subsequently, the repair patch  14  corresponding to the shape of the cut surface  16  is prepared, is arranged within a recessed portion  17  surrounded by the cut surface  16 , and is joined to the panel  10  ( FIG. 1D ,  FIG. 2 : step S 4 ). 
         [0058]    The repair patch  14  is formed from a prepreg before curing. The prepreg includes a plurality of layers laminated by an appropriate number according to a depth of the recessed portion  17 . Each of the layers is composed of a sheet-shaped fiber substrate, and a thermosetting resin such as epoxy, polyimide, polyurethane, and unsaturated polyester resins impregnated into the fiber substrate. 
         [0059]    As shown in  FIG. 4A , a film adhesive  18  containing a thermosetting resin is interposed between the repair patch  14  and an inner peripheral surface (the bottom surface  16 A and the slanting surface  16 B) of the recessed portion  17 . The repair patch  14  and the adhesive  18  are heated and cured by using a heater mat  19  or the like. 
         [0060]    Here, if a hole is originally formed at a position corresponding to the through-hole  12  in the repair patch  14  formed from the prepreg, and the repair patch  14  is fitted to a shape of the panel  10  by heat-curing, a shape of the hole is changed. Thus, it is difficult to originally form the hole in the repair patch  14 . 
         [0061]    In the heating, a surface of the repair patch  14  and its peripheral portion are covered with a back film  21 , and an internal pressure of the recessed portion  17  is reduced as shown in  FIG. 4A . A gap between the back film  21  and a surface of the panel  10  is sealed by a sealant (not shown). 
         [0062]    When the internal pressure of the recessed portion  17  is reduced by a vacuum pump (not shown) that is connected to a valve  23  provided at the back film  21 , the repair patch  14  is pressed against the panel  10  by a pressure difference with an atmospheric pressure. Thus, the repair patch  14  is shaped such that the surface of the repair patch  14  and the surface of the panel  10  are smoothly continuous without forming a difference in level. 
         [0063]    Since an inner portion of the repair patch  14  is densified by the pressure reduction, it is possible to avoid formation of bubbles (voids) on a bonded surface and within the repair patch  14 . Accordingly, the repair patch  14  is surely bonded to the panel  10 , and the strength/the stiffness are also secured. 
         [0064]    It is necessary to form the through-hole  12  into which the fastener  11  is inserted in the repair patch  14  after shaping the repair patch  14 . A hole needs to be machined (formed) in the repair patch  14  at the same position as that of the through-hole  12  originally formed in the panel  10  such that the hole continues to the through-hole  12  left in the panel  10  on a back side of the repair patch  14 . 
         [0065]    Since the through-hole  12  remaining in the panel  10  is concealed on the back side of the repair patch  14 , the through-hole  12  cannot be visually recognized from a front side  10 A of the panel  10 . 
         [0066]    In the repair performed in a state in which airframe parts are assembled together, it is difficult to access a back side  10 B of the panel  10 . Even if the through-hole  12  can be visually recognized by accessing the back side  10 B of the panel  10 , it is difficult to ensure a working space necessary for machining the hole in the panel  10  and the repair patch  14  through the through-hole  12 . 
         [0067]    Thus, the position where the hole is machined is located by using the ultrasonic testing that is also used for inspecting a repair quality ( FIG. 1E ,  FIG. 2 : step S 5 ). The air AR included in the marker  20  ( FIGS. 3A and 3B ) previously installed in the through-hole  12  has very different propagation characteristics of ultrasonic waves (referred to as wave propagation characteristics below) from those of the material of the outer shell  20 A around the air AR, the fiber reinforced resin used for the repair patch  14  and the panel  10 , and the resin of the resin material  15 . An ultrasonic testing apparatus makes the marker  20  visible by showing high sensitivity to an interface between the air AR in the marker  20  and its peripheral member where the wave propagation characteristics largely change. 
         [0068]      FIG. 4B  shows a manner in which the marker  20  is detected by bringing a probe  25  of the ultrasonic testing apparatus into contact with the surface of the repair patch  14 , and moving the probe  25  little by little along the surface. The probe  25  oscillates an ultrasonic wave, applies the ultrasonic wave to the repair patch  14  and the panel  10  in the thickness direction, and receives an ultrasonic wave returned from the application target. A signal waveform is displayed on a monitor connected to the probe  25  based on a correlation between the oscillated ultrasonic wave and the received ultrasonic wave. A position of the marker  20  can be easily located based on the signal waveform. 
         [0069]    By moving the probe  25 , a range in which the air AR exists within the marker  20 , that is, a shape and a size of the marker  20  are obtained. Even if a bubble exists within the repair patch  14 , the bubble is much smaller than the marker  20 . Even when a plurality of bubbles gather, the bubbles are distributed in an irregular shape. It is thus possible to clearly discriminate the bubble from the air AR in the marker  20 . 
         [0070]    Even when a position where a bubble  22  exists is overlapped with the position of the marker  20  as shown in  FIG. 1E , the position where the bubble  22  exists is removed by the hole machining that is subsequently performed as shown in  FIG. 1F , and thus, there occurs no problem. 
         [0071]    Even when an apparatus that imagines a signal obtained from a range scanned by the probe  25  with the probe  25  self-traveling from an origin position defined on the panel  10  or the repair patch  14  is used, the position of the marker  20  can be easily located based on a difference in shading in a displayed image or the like. 
         [0072]    The fibers and the resin in the panel  10 /the repair patch  14  have different wave propagation characteristics from those of each other, and the panel  10 /the repair patch  14  and the resin material  15  also have different wave propagation characteristics from those of each other. However, the difference in the wave propagation characteristics between the air AR and the panel  10 /the repair patch  14 /the resin material  15  around the air AR is strikingly larger than the differences. Thus, a position corresponding to the interface between the air AR and its peripheral portion is displayed in a state with a strong contrast without being obscured in the signal waveform or the image. That is, the position of the marker  20  can be located at a position with a strong contrast in the signal waveform or the image. 
         [0073]    The located position of the marker  20  corresponds to the position of the through-hole  12 . Accordingly, the hole machining position is located. Therefore, the hole is machined throughout the repair patch  14  and the panel  10  at the position of the marker  20  marked on the surface of the repair patch  14 , so that the through-hole  12  is formed continuously in the repair patch  14  and the panel ( FIG. 1F ,  FIG. 2 : step S 6 ). 
         [0074]    At this time, when the hole is machined with a diameter equal to or slightly larger than a diameter of the original through-hole  12 , the entire resin material  15  filling the through-hole  12  can be scraped away, and completely removed. At the same time, the marker  20  is also removed. 
         [0075]    Through the above steps, the through-hole  12  is formed at the original position. Thus, the fastener  11  ( FIG. 1A ) is passed through the through-hole  12  to fasten the panel  10  and another member ( FIG. 2 : step S 7 ), so that the repair is completed. 
         [0076]    In accordance with the present embodiment, it is possible to easily locate the accurate hole machining position on the repair patch  14  by the ultrasonic testing by using the marker  20  without preparing an expensive positioning jig or without manually marking a distance from a distinctive portion of the airframe to the fastener  11 . 
         [0077]    Since the hole machining position can be accurately located, it is possible to avoid a problem in which the hole is formed at a position deviated from the original position due to a measurement error, and the repair needs to be performed again. By machining the hole at the accurate position, it is possible to fully remove the resin material  15  that seals the through-hole  12  without leaving the resin material  15 . It is thus possible to avoid a decrease in the stiffness/the strength of the airframe due to the resin material  15  having no strength. 
         [0078]    The marker  20  of the present embodiment is not limited to a hollow member including the air AR, and a solid member formed from a metal material may be also employed as the marker. 
         [0079]    The wave propagation characteristics of the metal material of the marker and the fiber reinforced resin around the marker  20  differ to an extent that enables the marker  20  to be discriminated from its peripheral portion by the ultrasonic testing. The marker functions similarly to the above marker  20  based on the difference. 
         [0080]    It is preferable to prepare a plurality of types of markers having different diameters, as the marker  20 , according to the hole diameter of the through-hole  12 . 
         [0081]    It is also preferable to reduce a thickness of the marker  20  (a dimension along the hole axis of the through-hole  12 ) in order to respond to a case in which a remaining portion of the panel  10  after the removed region  13  ( FIG. 1A ) is removed is thin. 
         [0082]      FIGS. 5A and 5B  show a marker  26  different from the marker  20  of the above embodiment. 
         [0083]    The marker  26  has an indicating member  27  that indicates an axial center  20 X of the marker  26  within the outer shell  20 A including the air AR. The indicating member  27  can be formed from any material such as resin and metal. 
         [0084]    A diameter of the marker  26  may be measured to be larger than an actual diameter depending on measurement accuracy of the ultrasonic testing in some cases. Even in such a case, the axial center of the through-hole  12  is easily located by using the indicating member  27 . 
         [0085]    The indicating member  27  has a cross shape in which two portions  27 A and  27 B cross each other at a plane center of the marker  26  through which the axial center  20 X of the marker  26  passes. The shape is continuous in a direction of the axial center  20 X. 
         [0086]    The indicating member  27  may be also formed in a radial shape in which three or more portions cross each other at the plane center of the marker  26 . 
         [0087]    When the marker  26  is used, the indicating member  27  is made visible from its peripheral portion based on a difference in the wave propagation characteristics between the air AR in the marker  26  and the indicating member  27 . Since the marker  26  is arranged within the through-hole  12  such that the axial center  20 X substantially corresponds to the axial center of the through-hole  12 , an intersection  27 X of the indicating member  27  positioned at the axial center  20 X of the marker  26  almost exactly indicates the axial center of the through-hole  12 . 
         [0088]    Therefore, by machining the hole based on a position of the intersection  27 X of the indicating member  27  as the center, it is possible to easily form the through-hole  12  at the original position. 
         [0089]    The indicating member  27  of the marker  26  may be missing in the axial center  20 X of the marker  26  as shown in  FIG. 5C . In this case, four portions  271  to  274  constituting the indicating member  27  also point to the axial center  20 X of the marker  26  similarly to  FIG. 5A , and indicate the axial center of the through-hole  12  in which the marker  26  is arranged. Thus, the marker  26  functions similarly to the above marker  26 . 
         [0090]    The marker  26  can be modified into various forms as long as the wave propagation characteristics of the indicating member  27  and the peripheral portion differ to an extent that enables the indicating member  27  to be discriminated from the peripheral portion by the ultrasonic testing. 
         [0091]    For example, in a marker  28  shown in  FIG. 6A , a portion corresponding to the indicating member  27  in  FIGS. 5A and 5B  is formed as a hollow  281 . Since the hollow  281  is formed within a substantially-cylindrical marker body  280  formed from resin or metal, the marker  28  functions similarly to the marker  26  based on a difference in the wave propagation characteristics between the hollow  281  and the marker body  280 . 
         [0092]    In a marker  29  shown in  FIG. 6B , an indicating member  291  formed from a metal material and having a cross shape in section is embedded in a marker body  290  (indicated by diagonal lines) formed from a resin material. The marker  29  also functions similarly to the marker  26  based on a difference in the wave propagation characteristics between the resin material and the metal material. 
         [0093]    Moreover, even the indicating member  27  alone formed from resin or metal is allowed to function similarly to the marker  26  based on the difference in the wave propagation characteristics between the indicating member  27  and the peripheral portion as shown in  FIG. 6C . 
         [0094]    A patch obtained by pre-curing a fiber reinforced resin may be used instead of using the repair patch  14  formed from the prepreg, and the patch may be bonded to the panel  10 . Moreover, a patch formed from a metal material may be used. 
         [0095]    Sheet-shaped fiber substrates may be stacked up in the recessed portion  17  ( FIG. 1D ), and impregnated with a resin instead of using the repair patch  14 . 
         [0096]    The present invention is not limited to the embodiment according to the structural member of the aircraft described above, and can be used for repairing general structures formed from a composite material, such as blades of a wind turbine. 
         [0097]    There is also a case in which it is not necessary to fill the entire through-hole  12 . In this case, for example, a plug  24  having a smaller thickness than a height (a dimension in the thickness direction of the panel  10 ) of the through-hole  12  can be provided within the through-hole  12  to seal the through-hole  12  as shown in  FIG. 3C . 
         [0098]    Accordingly, a hollow  120  is ensured in a region other than a portion occupied by the plug  24  in the through-hole  12 . Since the position of the through-hole  12  can be located by the ultrasonic testing by using the hollow  120 , it is not necessary to arrange the above marker  20  or the like in the through-hole  12 . 
         [0099]    In an example shown in  FIG. 3C , it is not necessary to remove the resin material  15  ( FIG. 3A ) filling the through-hole  12  at the time of forming the hole. Thus, the through-hole  12  left in the panel  10  may be directly used without forming a hole again. In this case, a hole continuing to the through-hole  12  may be machined only in the repair patch  14 , and the plug  24  may be pushed out by the fastener  11 . 
         [0100]    Examples of a machined portion included in a repair region to which the present invention is applied include a non-through hole  31  shown in  FIG. 7 , a recessed portion, and a depression in addition to the through-hole  12 . The hole  31  not reaching a back side  32 B of a member  32  needs to be machined from a front side  32 A of the member  32 . The hole  31  is provided with, for example, a bush  33 . 
         [0101]    Since an inner portion of the hole  31  existing in the member  32  is hollow, and a position of the hole  31  can be located by performing the ultrasonic testing from a front side of a repair patch  34  that covers the hole  31 , a hole may be machined in the repair patch  34  at the position. 
         [0102]    In a case of the machined portion, such as the hole  31 , that does not pass through the member  32 , it is not necessary to seal the hole  31  for vacuum drawing. 
         [0103]    A repair material in the present invention is not limited to the one subjected to the pressure reduction in the heat-curing. The repair material is also not limited to the one needed to be cured by heating so as to be joined to a member that is a repair target. 
         [0104]    Therefore, even when the machined portion passes through the repair target member, the sealing of the machined portion is appropriately conducted. 
         [0105]    The constitutions described in the aforementioned embodiment may be also freely selected or appropriately changed into other constitutions without departing from the gist of the present invention.