Fastener installation with restricted access

Abstract

The present application relates to access-restricted fastener installation and provides a method and apparatus for installing fasteners. The apparatus includes a panel system and an air system connected to the panel system. The panel system has a plurality of air passages and at least one opening. The air system directs air through the plurality of air passages, out of the opening, and in a selected direction generally parallel to the surface of the structure into which the fastener is to be installed, such that the air impinges on the exposed portion of the fastener shank.

Description

[0001] This application is a divisional application of Chinese patent application No. 201710083953.2 filed on February 16, 2017 and entitled “Access-restricted fastener installation”. Technical Field

[0002] The present disclosure relates generally to installing fasteners. More particularly, the present disclosure relates to methods and apparatus for installing a fastener in a hole of a structure to generate friction between the fastener and the hole, the friction preventing the fastener from falling out of the hole during installation. Background Art

[0003] Manually installing fasteners in areas where access is limited can be more difficult and time-consuming than desired. Manual fastener installation can be particularly difficult and tedious when building complex systems, such as aircraft. For some currently available aircraft, the installation of fasteners for longitudinal and radial attachment assemblies can be performed manually. For example, but not limited to, the installation of rivets for radial attachment assemblies of an aircraft's fuselage assembly can be performed by a first mechanic operating a drilling tool and a hammering tool on the exterior of the fuselage assembly and a second mechanic operating a bucking tool on the interior of the fuselage assembly.

[0004] Therefore, it is desirable to at least partially automate the process of installing these rivets. However, in areas with limited access where hundreds of fasteners may need to be installed, automating the process of installing rivets can be difficult. Therefore, it is desirable to have methods and apparatus that take into account at least some of the above-mentioned issues, as well as other possible issues. Summary of the Invention

[0005] In one illustrative embodiment, the apparatus includes a panel system and an air system connected to the panel system. The panel system has an opening and a plurality of air channels. The air system directs air through the plurality of air channels, out of the opening, and in a selected direction generally parallel to the surface of the structure into which the fastener is to be installed, such that the air impinges on the exposed portion of the fastener's shank.

[0006] In another illustrative embodiment, a method for installing a fastener is provided. The fastener is positioned within a hole in a structure. Air is directed in a selected direction relative to the fastener, wherein the fastener is positioned within the hole in the structure. The air generates friction between the fastener and the hole, which prevents the fastener from falling out of the hole. The fastener is then installed in the hole.

[0007] In another illustrative embodiment, a fastener retention system includes a plate system and an air system connected to the plate system. The plate system includes a guide plate, a cover plate set, a backing layer, and a plurality of openings. The guide plate has a profile that matches the surface profile of the surface of the structure. The cover plate set forms a plurality of air channels within the plate system. When the plate system is positioned relative to the structure, the backing layer protects the surface of the structure. A plurality of openings pass through the guide plate, the cover plate set, and the backing layer. An opening in the plurality of openings is configured to be positioned above a hole in a plurality of holes in the structure. The openings allow fasteners inserted into the holes to pass through the openings. When the air system is activated, the air system directs air through the plurality of air channels within the plate system to generate friction between each of the plurality of fasteners and a corresponding hole in the plurality of holes in the structure, the friction preventing each fastener from falling out of the corresponding hole.

[0008] The features and functions can be achieved independently in various embodiments of the present disclosure or may be combined in yet other embodiments in which further details can be seen with reference to the following description and drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0009] The novel features which are believed to be characteristic of the illustrative embodiments are set forth in the appended claims. However, the illustrative embodiments, together with their preferred modes of use, further objects and features thereof, will be fully understood by reference to the following detailed description of illustrative embodiments of the present disclosure when read in conjunction with the accompanying drawings, in which:

[0010] Figure 1 is an illustration of a manufacturing environment in block diagram form according to an illustrative embodiment;

[0011] Figure 2 is an illustration of a fastener retention system in block diagram form according to an illustrative embodiment;

[0012] Figure 3 is an illustration of an isometric view of an aircraft in accordance with an illustrative embodiment;

[0013] Figure 4 According to the illustrative embodiment Figure 3 An illustration of an isometric view of an interior surface of a portion of a fuselage;

[0014] Figure 5 According to the illustrative embodiment Figure 4 a section of the inner surface of that part of the fuselage and from Figure 4 Illustration of the fastener retention system;

[0015] Figure 6 According to the illustrative embodiment Figures 4 and 5 an illustration of a first side of a fastener retention system;

[0016] Figure 7According to the illustrative embodiment Figure 6 an illustration of a second side of the fastener retention system;

[0017] Figure 8 According to the illustrative embodiment Figure 6 Illustration of the second side of the fastener retention system with the Figure 7 The cushioning layer;

[0018] Figure 9 is according to an illustrative embodiment relative to Figure 4 The inside of the fuselage will Figure 6 Illustration of a fastener retention system maintaining two frame pusher assemblies in proper position;

[0019] Figure 10 is an illustration of an isometric view of a frame pusher assembly according to an illustrative embodiment;

[0020] Figure 11 According to the illustrative embodiment Figure 9 an illustration of an enlarged view of a fastener retention system;

[0021] Figure 12 is an illustration of a cross-sectional view of a fastener retention system positioned relative to a hole into which a fastener has been inserted, according to an illustrative embodiment;

[0022] Figure 13 is an illustration of a process for installing a fastener in the form of a flowchart according to an illustrative embodiment;

[0023] Figure 14 is an illustration of a process for installing a fastener in the form of a flowchart according to an illustrative embodiment;

[0024] Figure 15 is an illustration of a process for installing a fastener in the form of a flowchart according to an illustrative embodiment;

[0025] Figure 16 is an illustration, in block diagram form, of an aircraft manufacturing and service methodology in accordance with an illustrative embodiment; and

[0026] Figure 17 is an illustration of an aircraft in the form of a block diagram in accordance with an illustrative embodiment. DETAILED DESCRIPTION

[0027] The illustrative embodiments recognize and take into account various factors that may need to be considered. For example, the illustrative embodiments recognize and take into account that it would be desirable to provide a method and apparatus for generating frictional forces that maintain fasteners in place within holes in a structure during installation to improve the ease and speed with which these fasteners can be installed. Specifically, the illustrative embodiments recognize that this type of method and apparatus can make it easier to automate the process of installing fasteners in areas where access is limited.

[0028] Thus, the illustrative embodiments provide methods and apparatus for installing fasteners. In one illustrative example, a method for installing a fastener is provided. A fastener is positioned within a hole in a structure. Air is directed in a selected direction relative to the fastener, wherein the fastener is positioned within the hole in the structure. The air creates friction between the fastener and the hole, which prevents the fastener from falling out of the hole. Thereafter, the fastener is installed in the hole. In this manner, the method uses air to maintain the fastener in the hole before and during installation.

[0029] In yet another illustrative example, a fastener retention system includes a plate system and an air system connected to the plate system. The plate system includes a guide plate, a cover plate set, a backing layer, and a plurality of openings. The guide plate has a profile that matches the surface profile of the surface of the structure. The cover plate set forms a plurality of air channels within the plate system. When the plate system is positioned relative to the structure, the backing layer protects the surface of the structure. A plurality of openings pass through the guide plate, the cover plate set, and the backing layer. An opening in the plurality of openings is configured to be positioned above a hole in a plurality of holes in the structure. The openings allow fasteners inserted into the holes to pass through the openings. When the air system is activated, the air system directs air through the plurality of air channels within the plate system to generate friction between each of the plurality of fasteners and a corresponding hole in the plurality of holes in the structure, which friction prevents each fastener from falling out of the corresponding hole.

[0030] In the illustrative examples described below, the same reference numerals may be used in more than one figure. Reference numerals that are repeated in different figures represent the same elements in the different figures.

[0031] Referring now to the drawings, and in particular, to Figure 1 , an illustration of a manufacturing environment is depicted in block diagram form in accordance with an illustrative embodiment. In this illustrative example, manufacturing environment 100 may be an environment in which structures 102 may be assembled to form aircraft 104.

[0032] In one illustrative example, structure 102 takes the form of fuselage 106. In some cases, during manufacturing and assembly, fuselage 106 may be referred to as a fuselage assembly. In one illustrative example, structure 102 may include two or more components.

[0033] Structure 102 has an interior side 108 and an exterior side 110. Interior side 108 may be defined by an interior mold line (not shown). Exterior side 110 may be defined by an exterior mold line (not shown). A plurality of fasteners 112 may be installed in a plurality of holes 114 in structure 102. Specifically, robotic device 116 may be used to drill holes 114 in structure 102 and install fasteners 112. Robotic device 116 may be positioned outside structure 102 relative to exterior side 110 of structure 102. In some illustrative examples, robotic device 116 may automate the entire drilling process, but only a portion of the fastener installation process.

[0034] In this illustrative example, fastener 118 is an example of one of plurality of fasteners 112. When fastener 118 has been fully installed, fastener 118 may take the form of rivet 120. Fastener 118 has a first end 122 and a second end 124. Fastener 118 may include a head 126 at first end 122 and a shank 128 extending from second end 124 of fastener 118 to head 126 of fastener 118. In some cases, shank 128 of fastener 118 may also be referred to as a handle.

[0035] In one illustrative example, fastener 118 may be designated for installation in hole 130 of plurality of holes 114 in structure 102. In this illustrative example, hole 130 has wall 132. Wall 132 may define the dimensions of hole 130 and be formed by structure 102.

[0036] After the plurality of holes 114 have been drilled in the structure 102, the plurality of fasteners 112 may be inserted into the plurality of holes 114 by the robotic device 116 at the exterior side 110 of the structure 102. However, the area along the interior side 108 of the structure 102 where the plurality of holes 114 are located may be an area with limited access. Thus, a second robotic device (not shown) may not be able to reach the plurality of holes 114 within the interior side 108 to assist in installing the plurality of fasteners 112. For example, while the robotic device 116 at the exterior side 110 may be used to perform drilling and hammering operations, another robotic device (not shown) may not be able to access the area within the interior side 108 of the structure 102 where the plurality of holes 114 are located in order to perform buckling operations. An operator may need to perform these buckling operations.

[0037] The fastener retention system 134 can be used to maintain the plurality of fasteners 112 in place within the plurality of holes 114 during the installation process. For example, but not limited to, as the robotic device 116 moves along the exterior side 110 of the structure 102 and an operator (not shown) moves along the interior side 108 of the structure 102, the fastener retention system 134 can prevent the plurality of fasteners 112 from falling out of the plurality of holes 114 to completely install each of the plurality of fasteners 112 one at a time. The fastener retention system 134 is used within the interior side 108 of the structure 102. The fastener retention system 134 is used below Figure 2 Described in more detail in .

[0038] Still refer to Figure 1 , the plurality of holes 114 may be located between the first frame 136 and the second frame 138 of the structure 102. The first frame pusher assembly 140 and the second frame pusher assembly 142 may be used to maintain and hold the fastener retention system 134 in a selected position between the first frame 136 and the second frame 138. The first frame pusher assembly 140 and the second frame pusher assembly 142 are connected to the first frame 136 and the second frame 138, respectively.

[0039] The first frame pusher assembly 140 may include, for example, but not limited to, a support member 144, a pin set 146, a frame bracket 150, and a torque member 152. The support member 144 is the primary structural component of the first frame pusher assembly 140. The pin set 146 may be inserted into a coordinating hole set 148 in the first frame 136 to connect the first frame pusher assembly 140 to the first frame 136.

[0040] The frame bracket 150 can be used to control the positioning of the torque member 152. Specifically, the frame bracket 150 can be movably attached to the support member 144. The torque member 152 can be connected to the frame bracket 150 so that movement of the frame bracket 150 along the support member 144 moves the torque member 152 relative to the support member 144.

[0041] A torque member 152 may be used to indirectly connect the support member 144 to the fastener retention system 134. In one illustrative example, the torque member 152 takes the form of a torque-limiting thumbscrew 154. The torque-limiting thumbscrew 154 may be rotated to apply a force to the fastener retention system 134 that pushes the fastener retention system 134 against the inner side 108 of the structure 102 to maintain the fastener retention system 134 in place.

[0042] The second frame pusher assembly 142 may be implemented in a manner similar to the first frame pusher assembly 140 . However, the second frame pusher assembly 142 may be configured to attach to the second frame 138 .

[0043] Now refer to Figure 2 , a diagram of a fastener retention system 134 is depicted in block diagram form according to an illustrative embodiment. In this illustrative example, fastener retention system 134 may be positioned relative to inner side 108 of structure 102. For example, using Figure 1 The first frame pusher assembly 140 and the second frame pusher assembly 142 may maintain the fastener retention system 134 in place.

[0044] Fastener retention system 134 includes a plate system 200 and an air system 202 connected to plate system 200. Plate system 200 may include a plurality of openings 204. An opening in plurality of openings 204 may be configured to be positioned over a corresponding hole in structure 102. Further, an opening in plurality of openings 204 may be shaped to allow a fastener inserted into the corresponding hole to pass through the opening.

[0045] In one illustrative example, when plate system 200 is positioned over plurality of holes 114 in structure 102, opening 208 in plurality of openings 204 may be positioned over hole 130. Opening 208 may be shaped to allow fastener 118 to pass through. Figure 1 The robotic device 116 is easily inserted into the hole 130.

[0046] The panel system 200 may include guide panels 210, a cover panel set 212, and a backing layer 214. The guide panels 210 may have a profile that matches the surface profile of the interior 108 of the structure 102. The cover panel set 212 may help form a plurality of air channels 216 within the panel system 200.

[0047] In one illustrative example, a plurality of air channels 216 are formed between guide plate 210 and cover plate set 212. In another illustrative example, a plurality of air channels 216 are formed within cover plate set 212.

[0048] When the panel system 200 is positioned relative to the structure 102, the backing layer 214 can be used to protect the surface of the inner side 108 of the structure 102. Figure 1 With the first frame pusher assembly 140 and the second frame pusher assembly 142, the panel system 200 can be maintained in a selected position relative to the inner side 108 of the structure 102. Figure 1 The cushioning layer 214 protects the surface of the inner side 108 of the structure 102 as the first and second frame pusher assemblies 140 , 142 push the panel system 200 upward against the inner side 108 .

[0049] As shown, air system 202 can be activated or deactivated. When activated, air system 202 delivers air 218 to a plurality of air channels 216 within panel system 200. Air 218 can be provided by a compressed air source 221. Specifically, air system 202 can include a plurality of air connectors 224 connecting compressed air source 221 to a plurality of air channels 216. As used herein, a plurality of air connectors 224 includes one or more air connectors. In some illustrative examples, compressed air source 221 can be considered part of air system 202, while in other illustrative examples, compressed air source 221 can be separate from air system 202.

[0050] A plurality of air channels 216 within panel system 200 terminate at plurality of openings 204, allowing air 218 to flow out of plurality of openings 204. In one illustrative example, robotic device 116 may insert fastener 118 into hole 130 when air system 202 is activated. Air 218 flowing out of openings 208 may generate friction 220 between fastener 118 and hole 130, which may prevent fastener 118 from falling out of hole 130.

[0051] For example, the head 126 of the fastener 118 may have a larger diameter than the hole 130, but the shaft 128 may have a smaller diameter than the hole 130. The fastener 118 may be inserted into the hole 130, with the shaft 128 inserted first. The hole 130 may be a clearance-matching hole that allows the fastener 126 to slide in and out of the hole 130. The structure 102 may be configured such that when the fastener 118 is inserted into the hole 130, gravity first pulls on the head 126 of the fastener 118. In the absence of the friction force 220, gravity may cause the fastener 118 to fall out of the hole 130.

[0052] More specifically, when the fastener 118 is positioned in the hole 130 such that the force of gravity pulling on the head 126 at the first end 122 of the fastener 118 is greater than the resistance or load at or near the second end 124 of the fastener 118, the fastener 118 may fall out of the hole 130. The friction force 220 generated by the air 218 may increase this resistance, thereby preventing the fastener 118 from falling out of the hole 130.

[0053] Specifically, the plurality of air channels 216 directs air 218 so that the air 218 flows out of the opening 208 in a selected direction 225. The selected direction 225 may be a direction that is substantially perpendicular to the shaft 128 of the fastener 118. The air flowing out of the opening 208 in the selected direction 225 pushes the fastener 118 upward against a portion of the wall 132 of the hole 130, thereby generating a friction force 220 sufficient to maintain the fastener 118 in a proper position relative to the hole 130.

[0054] In this manner, when air system 202 is activated, robotic device 116 can robotically insert each of plurality of fasteners 112 into plurality of holes 114 one by one, thereby maintaining the inserted fasteners in place. Robotic device 116 and an operator using a buckling tool can then perform operations to completely install each of plurality of fasteners 112. Specifically, it can be considered that by using plate system 200 positioned internally relative to inner side 108 of structure 102 and relative to Figure 1 An external robotic device 116 is positioned outside 110 of structure 102 to clamp selected areas of structure 102 to facilitate hammering and buckling operations.

[0055] Figure 1 Manufacturing environment 100 and Figures 1 to 2 The illustration of the fastener retention system 134 in FIG. 1 is not meant to imply physical or architectural limitations to the manner in which the illustrative embodiments may be implemented. Other components may be used in addition to or in place of the components shown. Some components may be optional. Additionally, blocks are presented to illustrate some functional components. When implemented in the illustrative embodiments, one or more of these blocks may be combined, separated, or combined and separated into different blocks.

[0056] In some illustrative examples, robotic device 116 may be used to drill plurality of holes 114 in structure 102 before fastener retention system 134 is positioned relative to interior 108 of structure 102. In other illustrative examples, robotic device 116 may robotically drill plurality of holes 114 in structure 102, wherein plate system 200 of fastener retention system 134 is positioned relative to interior 108 of structure 102 using first frame pusher assembly 140 and second frame pusher assembly 142. In some cases, only one frame pusher assembly may be required to maintain plate system 200 of fastener retention system 134 in position.

[0057] Now refer to Figure 3 , an illustration of an isometric view of an aircraft is depicted in accordance with an illustrative embodiment. In this illustrative example, aircraft 300 may be Figure 1 An example of an embodiment of the aircraft 104 in the embodiment may include a Figure 1 An example of a platform of components in structure 102.

[0058] As shown, aircraft 300 may include wings 302 and wing 304 attached to fuselage 306. Fuselage 306 may be Figure 13. Aircraft 300 may include engine 308 attached to wing 302 and engine 310 attached to wing 304. Fuselage 306 may have tail section 312. Horizontal stabilizer 314, horizontal stabilizer 316, and vertical stabilizer 318 are attached to tail section 312 of fuselage 306.

[0059] Now refer to Figure 4 , depicted according to an illustrative embodiment Figure 3 FIG. 306 is an isometric view of an interior surface of a portion of a fuselage 306. In this illustrative example, the Figure 3 The portion 400 of the inner surface 402 of the fuselage 306 of the aircraft 300. The portion 400 of the inner surface 402 of the fuselage 306 may be formed by an inner surface having one or more skin panels. Specifically, the inner surface 402 of the fuselage 306 may be Figures 1 to 2 An example of one implementation of the inner side 108 in FIG.

[0060] In this illustrative example, fastener retention system 404 is positioned relative to inner surface 402. Fastener retention system 404 may be Figures 1 to 2 An example of one embodiment of the fastener retention system 134 in FIG. Buckling tool 406 and buckling tool 408 are shown positioned relative to fastener retention system 404. In the following Figure 5 Segment 410 of interior surface 402 of portion 400 of fuselage 306 and fastener retention system 404 are shown in greater detail.

[0061] Now refer to Figure 5 , depicted according to an illustrative embodiment Figure 4 a section 410 of the inner surface 402 of the portion 400 of the fuselage 306 and Figure 4 4. In this illustrative example, fastener retention system 404 is shown positioned between frame 500 and frame 502. Frame 500 and frame 502 may be, respectively, Figure 1 An example of an implementation of the first frame 136 and the second frame 138 in FIG.

[0062] Now refer to Figure 6 , depicted according to an illustrative embodiment Figures 4 and 5 6. Illustration of a first side of fastener retention system 404. In this illustrative example, fastener retention system 404 has a first side 600 and a second side 601.

[0063] As shown, the fastener retention system 404 includes a coordination hole 602 and a coordination hole 604. These coordination holes can be used to mate the fastener retention system 404 with the Figure 4The plurality of tack fasteners (not shown) are aligned with a plurality of holes (not shown) in the fuselage 306 of the embodiment of the present invention.

[0064] The fastener retaining system 404 includes a plurality of first openings 606 and a plurality of second openings 608. In one illustrative example, each of the plurality of first openings 606 and the plurality of second openings 608 is Figure 2 In another illustrative example, the plurality of first openings 606 and the plurality of second openings 608 are Figure 2 6. The fastener retention system 404 also includes slot openings 610, 612, 614, and 616.

[0065] As shown, the fastener retaining system 404 includes a plate system 615 and an air system 617. The plate system 615 and the air system 617 may be Figure 2 An example of an implementation of the panel system 200 and the air system 202 in FIG.

[0066] Air system 617 includes air connection 618 and air connection 620. These air connections may be connected to a compressed air source (not shown) via any number of hoses, tubes, or combinations thereof.

[0067] When the air system 617 is activated, the air system 617 can deliver air from a compressed air source (not shown) to a plurality of air channels (not shown) within the panel system 615. The panel system 615 includes a guide plate 622, which can be Figure 2 An example of one embodiment of the guide plate 210 in FIG.

[0068] Now refer to Figure 7 , depicted according to an illustrative embodiment Figure 6 6. In this illustrative example, the second side 601 of the fastener retention system 404 can be more clearly seen. As shown, the plate system 615 includes not only the guide plate 622, but also the cover plate set 700 and the backing layer 702. The cover plate set 700 and the backing layer 702 can be respectively Figure 2 An example of an implementation of the cover plate set 212 and the backing layer 214 in FIG.

[0069] Now go to Figure 8 , depicts an illustration of a second side of fastener retention system 404 with the fasteners removed, according to an illustrative embodiment. Figure 7 The liner layer 702 is removed in this figure. Figure 7 The cover plate assembly 700 can be seen through the backing layer 702. The cover plate assembly 700 is shown in dotted lines to illustrate the plurality of air channels 800.

[0070] The plurality of air channels 800 may be Figure 2 800 includes an example of one embodiment of the plurality of air channels 216 in the plurality of first openings 606. The plurality of air channels 800 includes an air channel 802 and an air channel 804. The air channel 802 can direct air into and out of the plurality of first openings 606. In particular, the air channel 804 is configured such that air flows out of each of the plurality of first openings 606 in a single direction. As an illustrative example, air (not shown) can flow out of the opening 806 of the plurality of first openings 606 in a selected direction 808.

[0071] Similarly, air channel 802 can direct air into and out of plurality of second openings 608. Specifically, air channel 802 is configured such that air flows out of each of plurality of second openings 608 in a single direction. As an illustrative example, air (not shown) can flow out of opening 810 of plurality of second openings 608 in a selected direction 812. Selected direction 808 and selected direction 812 can be Figure 2 An example of an implementation of the direction 225 selected in FIG.

[0072] Now refer to Figure 9 , an illustration of two frame pusher assemblies maintaining fastener retention system 404 in position relative to interior surface 402 of fuselage 306 is depicted in accordance with an illustrative embodiment. In this illustrative example, frame pusher assembly 900 and frame pusher assembly 902 are used to maintain fastener retention system 404 in position relative to interior surface 402. Frame pusher assembly 900 and frame pusher assembly 902 may be, respectively, Figure 1 1. Example implementations of the first frame pusher assembly 140 and the second frame pusher assembly 142 in FIG.

[0073] Now refer to Figure 10 , depicted according to an illustrative embodiment Figure 9 10. An illustration of an isometric view of frame pusher assembly 902. In this illustrative example, frame pusher assembly 902 includes support member 1000, pin 1002, pin 1004, frame bracket 1006, torque member 1008, and adjustment member 1010.

[0074] The support member 1000 may be Figure 1 An example of an embodiment of the support member 144 in FIG. Pins 1002 and 1004 may be Figure 1 Further, the frame bracket 1006 and the torque member 1008 can be respectively Figure 11 and 2. An example embodiment of the frame bracket 150 and torque member 152 in FIG.

[0075] In this illustrative example, pin 1002 and pin 1004 may be configured with Figure 9 The pins 1002 and 1004 and the coordinating holes (not shown) in the frame 502 can help the frame pusher assembly 902 to engage with the frame 502. Figure 9 Frame 502 in alignment and stabilization.

[0076] Further, the torque member 1008 is configured to engage Figure 9 , which is shown in FIG. 1008 , in the form of a torque limiting thumbscrew for the panel system 615. Rotating or applying torque to the torque member 1008 causes the torque member 1008 to push against the panel system 615, thereby pushing the panel system 615 upward against the fuselage 306. The amount of torque that can be applied to the torque member 1008 can be limited to prevent the panel system 615 from pushing against the fuselage 306 in a manner that undesirably affects the fuselage 306.

[0077] The frame bracket 1006 connects the torque member 1008 to the support member 1000. The adjustment member 1010 can be manipulated to move the frame bracket 1006 along the support member 1000 within a specified range of motion, and thereby move the torque member 1008 along the support member 1000 within a specified range of motion. In this way, the torque member 1008 can be adjusted relative to the support member 1000. Figure 9 The fastener retention system 404 is easily positioned.

[0078] Now refer to Figure 11 , an illustration of an enlarged view of fastener retention system 404 is depicted in accordance with an illustrative embodiment. In this illustrative example, torque member 1008 of frame pusher assembly 902 is shown engaged with panel system 615. Torque member 1100 of frame pusher assembly 902 is also shown engaged with panel system 615. Torque member 1008 and torque member 1100 together apply a force to panel system 615 that pushes panel system 615 upward against fuselage 306.

[0079] Now refer to Figure 12 , an illustration of a cross-sectional view of fastener retention system 404 positioned relative to a hole into which a fastener has been inserted is depicted in accordance with an illustrative embodiment. In this illustrative example, structure 1200 of fuselage 306 is depicted, with fastener 1202 inserted within hole 1203 in structure 1200. Structure 1200 includes first part 1201 and second part 1205. In one illustrative example, first part 1201 and second part 1205 may both be skin panels.

[0080] In this illustrative example, air is flowing out of fastener retention system 404 in selected direction 1206 toward stem 1204 of fastener 1202. Selected direction 1206 is substantially parallel to surface 1207 of structure 1200. Surface 1207 of structure 1200 may belong to second part 1205 in this illustrative example. In other illustrative examples, surface 1207 may be formed by surfaces of both first part 1201 and second part 1205.

[0081] Furthermore, selected direction 1206 is generally perpendicular to shank 1204 of fastener 1202. Specifically, air is blown from fastener retention system 404 such that the air impacts an exposed portion of shank 1204 of fastener 1202. This exposed portion may be the portion of fastener 1202 extending through surface 1207 of part 1205. This air pushes shank 1204 of fastener 1202 against the wall of hole 1203 in the direction of arrow 1208, thereby generating friction force 1210 between fastener 1202 and hole 1203. Further, directing air against shank 1204 of fastener 1202 in selected direction 1206 generates a torsional force 1214 that is counteracted by structure 1200, as indicated by arrow 1217.

[0082] Friction force 1210 can be sufficient to counteract gravity force 1211 pulling down on fastener 1202. In one illustrative example, gravity force 1211 can be decomposed into two vector components. For example, component 1213 and another vector component of gravity force 1211 (not shown) can together form gravity force 1211. Component 1213 of gravity force 1211 extends generally parallel to centerline 1215 of hole 1203. Friction force 1210 is generated generally parallel to centerline 1215 of hole 1203. Friction force 1210 is generated such that friction force 1210 is equal to or greater than component 1213 of gravity force 1211. In this manner, friction force 1210 counteracts component 1213 of gravity force 1211 to prevent fastener 1202 from slipping out of hole 1203.

[0083] In this manner, friction force 1210 may be sufficient to maintain fastener 1202 in position within hole 1203 even when ram 1212 is not positioned against the head of fastener 1202. Thus, fastener retention system 404 may be used to maintain fastener 1202 in position within hole 1203 until a hammering operation and a buckling operation can be performed to fully install fastener 1202 to form a rivet.

[0084] In other illustrative examples, air may be directed against stem 1204 of fastener 1202 in a direction that is not substantially perpendicular to stem 1204. For example, without limitation, blowing compressed air toward stem 1204 in a direction slightly offset from perpendicular to stem 1204 may generate sufficient friction force 1210 to counteract the pull of gravity 1211 that would cause fastener 1202 to slide out of hole 1203 in the absence of friction force 1210.

[0085] In some illustrative examples, plate system 615 may be reconfigured so that air is blown out of fastener retention system 404 in selected direction 1216. Blowing air in selected direction 1216 may create friction force 1218 that is substantially parallel to centerline 1215 of hole 1203. The air may be directed against stem 1204 of fastener 1202 to generate friction force 1218 sufficient to counteract component 1213 of gravity 1211.

[0086] Figures 3 to 12 The illustrations in the drawings are not meant to imply physical or architectural limitations to the manner in which the illustrative embodiments may be implemented. Other components in addition to or in place of the ones shown may be used. Some components may be optional.

[0087] Figures 3 to 12 The different components shown in the Figures 1 to 2 The components shown in block form in FIG. 1 are illustrative examples of how they may be implemented as physical structures. Figures 3 to 12 Some components in Figures 3 to 12 The components in the Figures 1 to 2 Use together with the components in , or a combination of the two.

[0088] Now refer to Figure 13 , an illustration of a process for installing a fastener is depicted in the form of a flowchart in accordance with an illustrative embodiment. Figure 13 The process shown can be used Figures 1 to 2 The fastener retention system 134 described in is implemented.

[0089] The process may begin by positioning a panel system relative to a structure (operation 1300). In operation 1300, the structure may be the fuselage of an aircraft. An air system coupled to the panel system may be activated (operation 1302). When the air system is activated, air may be delivered by the air system through a plurality of air channels within the panel system (operation 1304). The air generates friction between each of a plurality of fasteners and a corresponding hole in a plurality of holes in the structure, the friction preventing each fastener from falling out of the corresponding hole (operation 1306), with the process terminating thereafter.

[0090] Specifically, in operation 1306, friction prevents the plurality of fasteners from falling out of the plurality of holes during installation of the plurality of fasteners. In other words, friction maintains the fasteners in the holes between the time the fasteners are seated in the holes and the time the rivet is finally formed.

[0091] Now refer to Figure 14 , an illustration of a process for installing a fastener is depicted in the form of a flowchart in accordance with an illustrative embodiment. Figure 14 The process shown can be used Figures 1 to 2 The fastener retention system 134 described in is implemented.

[0092] The process may begin by connecting a first frame pusher assembly to a first frame and a second frame pusher assembly to a second frame at an inboard side of the fuselage (operation 1400). Positioning a panel system relative to the inboard side of the fuselage (operation 1402). Connecting the first frame pusher assembly and the second frame pusher assembly to the panel system to maintain the panel system in a selected position relative to the inboard side of the fuselage (operation 1404).

[0093] An air system connected to the panel system may be activated to deliver air through a plurality of air channels within the panel system such that the air flows out of each of the plurality of openings of the panel system in a selected direction (operation 1406). A plurality of fasteners may be inserted into a plurality of holes in the fuselage by a robotic device positioned outside the fuselage (operation 1408). The air flowing out of each of the plurality of openings of the panel system generates friction between each of the plurality of fasteners and the corresponding hole, the friction preventing each fastener from falling out of the corresponding hole (operation 1410), with the process terminating thereafter.

[0094] Now refer to Figure 15 , an illustration of a process for installing a fastener is depicted in the form of a flowchart in accordance with an illustrative embodiment. Figure 15 The procedure shown in Figures 1 to 2 The fastener retention system 134 described in is implemented.

[0095] The process may begin by placing a fastener in a hole in a structure (operation 1500). Air is directed in a selected direction relative to the fastener, wherein the fastener is located in the hole in the structure (operation 1502). The air creates friction between the fastener and the hole, which prevents the fastener from falling out of the hole (operation 1504). Thereafter, the fastener is installed in the hole to form a rivet (operation 1506), with the process terminating thereafter.

[0096] Operation 1504 can be performed by directing air so that the air strikes an exposed stem of the fastener on the inner side of the structure. The air striking the stem causes the fastener to tilt toward the wall of the hole in the structure, thereby generating friction between the fastener and the wall of the hole. Specifically, the friction includes a friction component that is at least equal and opposite to the weight component pulling on the fastener.

[0097] Furthermore, performing the above operation 1506 may include sending several commands to the robotic device to perform a riveting operation on the fastener located in the hole while applying the friction force to the fastener. The riveting operation may include performing a hammering operation using the robotic device and performing a buckling operation using a tool held by an operator.

[0098] The flowcharts and block diagrams in the different depicted embodiments illustrate the architecture, functionality, and operation of some possible implementations of the apparatus and method by way of illustrative embodiments. In this regard, each box in the flowchart or block diagram may represent a module, segment, function, and / or operation or a part of a step.

[0099] In some alternative implementations of the illustrative embodiments, one or more functions indicated in the blocks may occur out of the order indicated in the figures. For example, in some cases, two blocks shown in succession may be executed substantially simultaneously, or the blocks may sometimes be executed in the reverse order, depending on the functionality involved. Furthermore, other blocks may be added in addition to the blocks shown in a flowchart or block diagram.

[0100] Illustrative embodiments of the present disclosure may be employed in Figure 16 Aircraft manufacturing and service method 1600 is shown and Figure 17 The background of the aircraft 1700 is shown. Figure 16 , an illustration of an aircraft manufacturing and service method is depicted in accordance with an illustrative embodiment. During pre-production, aircraft manufacturing and service method 1600 may include Figure 17 Specification and design 1602 of the aircraft 1700 and material procurement 1604.

[0101] During production, Figure 17 Component and subassembly manufacturing 1606 and system integration 1608 of the aircraft 1700. Thereafter, Figure 17 The aircraft 1700 in can be certified and delivered 1610 for entry into service 1612. During use by a customer 1612, arrangements are made Figure 17 Aircraft 1700 in the process undergoes routine repair and maintenance 1614, which may include modification, reconfiguration, refurbishment, and other repair or maintenance.

[0102] Each of the processes of aircraft manufacturing and service method 1600 may be performed or carried out by a system integrator, a third party, and / or an operator. In these examples, the operator may be a customer. For purposes of this description, a system integrator may include, but is not limited to, any number of aircraft manufacturers and major system subcontractors; a third party may include, but is not limited to, any number of vendors, subcontractors, and suppliers; and an operator may include, but is not limited to, an airline, a leasing company, a military entity, a service organization, and the like.

[0103] Now refer to Figure 17 , depicts a diagram of an aircraft in which an illustrative embodiment may be implemented. In this example, aircraft 1700 is comprised of Figure 16 17. Aircraft manufacturing and service method 1600 is shown and may include airframe 1702 having multiple systems 1704 and inboard 1706. Examples of systems 1704 include one or more of propulsion system 1708, electrical system 1710, hydraulic system 1712, and environmental system 1714. Any number of other systems may be included. Although an aerospace example is shown, different illustrative embodiments may be applied to other industries, such as the automotive industry.

[0104] exist Figure 16 The apparatus and methods embodied herein may be employed during at least one of the stages of aircraft manufacturing and service method 1600. Specifically, during any of the stages of aircraft manufacturing and service method 1600, the apparatus and methods embodied herein may be employed. Figure 1 Fastener Retention System 134 Installation Figure 1 For example, but not limitation, during at least one of component and subassembly manufacturing 1606, system integration 1608, and routine repair and maintenance 1614, or some other phase of aircraft manufacturing and service method 1600, the plurality of fasteners 112 may be used. Figure 1 Fastener Retention System 134 Installation Figure 1 Further, it is possible to use a plurality of fasteners 112. Figure 1 Fastener Retention System 134 Installation Figure 1 The plurality of fasteners 112 are used to construct the fuselage 1702 of the aircraft 1700 .

[0105] In an illustrative example, Figure 16 The parts or subassemblies produced in parts and subassembly manufacturing 1606 may be used when the aircraft 1700 is Figure 16 As another example, during the production phase (such as Figure 16One or more apparatus embodiments, method embodiments, or a combination thereof may be utilized during component and subassembly manufacturing 1606 and system integration 1608 in the aircraft 1700. Figure 16 One or more apparatus embodiments, method embodiments, or a combination thereof may be utilized during use 1612 and / or during repair and maintenance 1614. Using several of the different illustrative embodiments may significantly expedite assembly of aircraft 1700 and / or reduce the cost of aircraft 1700.

[0106] Thus, in summary, according to a first aspect of the present invention there is provided:

[0107] A1. A device comprising:

[0108] a panel system (200) having a plurality of air channels (216) and openings (208); and

[0109] An air system (202) is connected to the panel system (200) and directs air (218) through a plurality of air passages (216), out of the opening (208), and in a selected direction (225) generally parallel to the surface of the structure (102) into which the fastener (118) is to be installed, so that the air (218) impinges on the exposed portion of the shank (128) of the fastener (118).

[0110] A2. Also provided is the apparatus of paragraph A1, wherein the air system (202) directs the air (218) in a selected direction (225) generally parallel to the structure (102) to generate a friction force (220) that prevents the fastener (118) from falling out of the hole (130) in the structure (102) into which the fastener (118) is to be installed. A3. Also provided is the apparatus of paragraph A1, wherein the selected direction (225) is generally perpendicular to the shaft (128) of the fastener (118).

[0111] A4. Also provided is the apparatus of paragraph A1, wherein the plate system (200) includes:

[0112] A plurality of openings (204) including an opening (208).

[0113] A5. Also provided is the apparatus of paragraph A1, wherein the opening (208) is shaped to allow a tool to be positioned against the fastener (118) during installation of the fastener (118) within the hole (130) in the structure (102).

[0114] A6. Also provided is the apparatus of paragraph A1, wherein the plate system (200) includes:

[0115] A guide plate (210) has a profile that matches the surface profile of the surface of the structure (102).

[0116] A7. Also provided is the apparatus of paragraph A6, wherein the plate system (200) further comprises:

[0117] A cover plate assembly (212) is provided, wherein a plurality of air channels (216) are formed between the guide plate (210) and the cover plate assembly (212).

[0118] A8. Also provided is the apparatus of paragraph A6, wherein the air system (202) includes:

[0119] A number of air connections (224) are attached to the guide plate (210).

[0120] A9. Also provided is the apparatus of paragraph A1, wherein the plate system (200) includes:

[0121] A cover plate assembly (212) is provided, wherein a plurality of air channels (216) are formed in the cover plate assembly (212).

[0122] A10. Also provided is the apparatus of paragraph A1, wherein the plate system (200) includes:

[0123] A backing layer (214) protects the surface of the structure (102) when the panel system (200) is positioned relative to the structure (102).

[0124] A11. Also provided is the apparatus of paragraph A1, wherein the air system (202) includes:

[0125] A number of air connections (224) are attached to the plate system (200) for connecting a compressed air source (221) to the plurality of air channels (216).

[0126] A12. Also provided is the apparatus of paragraph A1, further comprising:

[0127] A frame pusher assembly (140, 142) for maintaining the panel system (200) in a selected position relative to the structure (102).

[0128] A13. Also provided is the apparatus of paragraph A12, wherein the frame pusher assembly (140, 142) includes:

[0129] a support member (144);

[0130] a pin set (146) for attaching the support member (144) to the frame (136, 138) of the structure (102); and

[0131] A torque member (152) is provided for connecting the frame pusher assembly (140, 142) to the plate system (200).

[0132] A14. Also provided is the apparatus of paragraph A13, wherein the frame pusher assembly (140, 142) further comprises:

[0133] A frame bracket (150) is movably attached to the support member (144), wherein the torque member (152) is attached to the frame bracket (150) such that moving the frame bracket (150) relative to the support member (144) moves the torque member (152) relative to the support member (144).

[0134] A15. Also provided is the apparatus of paragraph A1, wherein the structure (102) is a fuselage (106).

[0135] A16. Also provided is the apparatus of paragraph A1, wherein when the air (218) is directed in a selected direction (225), the fastener (118) is fully installed in the hole (130) in the structure (102) to form the rivet (120). A17. Also provided is the apparatus of paragraph A1, wherein the air system (202) directs the air (218) by blowing the air (218) in a direction (225) toward the fastener (118) or drawing the air (218) in a direction away from the fastener (118).

[0136] A18. Also provided is the apparatus of paragraph A1, wherein the plate system (200) includes:

[0137] a guide plate (210) having a profile that matches the surface profile of the surface of the structure (102);

[0138] A cover plate assembly (212), wherein a plurality of air channels (216) are formed between the guide plate (210) and the cover plate assembly (212) or within the cover plate assembly (212);

[0139] a backing layer (214) that protects the surface of the structure (102) when the panel system (200) is positioned relative to the structure (102); and

[0140] A plurality of openings (204) including openings (208), wherein the plurality of openings (204) pass through the guide plate (210), the cover plate set (212), and the backing layer (214), wherein the openings (208) are configured to be positioned above the holes (130) in the plurality of holes (114) in the structure (102), and wherein the openings (208) allow fasteners (118) inserted into the holes (130) to pass through the openings (208).

[0141] According to a further aspect of the present invention there is provided:

[0142] B1. A method for installing a fastener (118), the method comprising:

[0143] placing (1500) a fastener (118) within a hole (130) of a structure (102);

[0144] directing (1502) air (218) in a selected direction (225) relative to the fastener (118), wherein the fastener (118) is located in the hole (130) of the structure (102);

[0145] generating (1504) a friction force (220) between the fastener (118) and the hole (130) by the air (218), the friction force (220) preventing the fastener (118) from falling out of the hole (130); and

[0146] The fastener (118) is installed (1506) in the hole (130).

[0147] B2. Also provided is the method of paragraph B1, wherein generating (1504) the friction force (220) by the air robotic device comprises:

[0148] The exposed portion of the stem (128) of the fastener (118) is impacted by air (218).

[0149] B3. Also provided is the method of paragraph B2, wherein generating (1504) friction force (220) from air (218) includes:

[0150] The stem (128) of the fastener (118) is tilted toward the wall of the hole (130) to generate a friction force (220) between the fastener (118) and the wall of the hole (130).

[0151] B4. Also provided is the method of paragraph B1, wherein directing (1502) the air (218) includes:

[0152] delivering air (218) from a compressed air source (221) through a plurality of air connections (224) attached to the panel system (200) into a plurality of air passages (216) within the panel system (200); and

[0153] Air (218) is directed through the plurality of air channels (216) and exits the panel system (200) at openings (208) of the panel system (200) in a selected direction (225).

[0154] B5. Also provided is the method of paragraph B1, further comprising:

[0155] The plate system (200) is positioned (1300) relative to the structure (102).

[0156] B6. Also provided is the method of paragraph B5, wherein positioning (1300) the plate system (200) includes:

[0157] The plate system (200) is aligned with a plurality of tack fasteners positioned around a plurality of holes (114) in the structure (102).

[0158] B7. Also provided is the method of paragraph B5, further comprising:

[0159] At least one frame pusher assembly (140, 142) is used to maintain the panel system (200) in a selected position relative to the structure (102).

[0160] B8. Also provided is the method of paragraph B5, further comprising:

[0161] A plurality of holes (114) are drilled robotically in a structure (102), wherein the plate system (200) is positioned relative to the structure (102).

[0162] B9. Also provided is the method of paragraph B5, wherein positioning (1300) the plate system (200) includes:

[0163] The plate system (200) is positioned relative to the inner mold line of the structure (102).

[0164] B10. Also provided is the method of paragraph B5, further comprising:

[0165] A selected range of structures (102) is clamped using a plate system (200) positioned relative to an inside (108) of the structure (102) and a robotic device (116) positioned relative to an outside (110) of the structure (102).

[0166] B11. Also provided is the method of paragraph B1, further comprising:

[0167] The fasteners (118) are robotically inserted into holes (130) in the structure (102).

[0168] B12. Also provided is the method of paragraph B1, further comprising:

[0169] When the friction force (220) is applied to the fastener (118), several commands are sent to the robotic device (116) to perform a riveting operation on the fastener (118) within the hole (130).

[0170] B13. Also provided is the method of paragraph B1, further comprising:

[0171] performing a riveting operation on the fastener (118) within the hole (130) by a robotic device (116) positioned at the exterior side (110) of the structure (102) while a friction force (220) is applied to the fastener (118); and

[0172] A friction force (220) is maintained while performing a flexion operation at the inner side (108) of the structure (102).

[0173] According to a further aspect of the present invention there is provided:

[0174] C1. A fastener retention system (134), comprising:

[0175] A plate system (200) comprising:

[0176] a guide plate (210) having a profile that matches the surface profile of the surface of the structure (102); a cover plate set (212) that forms a plurality of air channels (216) within the plate system (200);

[0177] a backing layer (214) that protects the surface of the structure (102) when the panel system (200) is positioned relative to the structure (102); and

[0178] A plurality of openings (204) passing through the guide plate (210), the cover plate set (212), and the backing layer (214), wherein an opening (208) of the plurality of openings (204) is configured to be positioned above a hole (130) of the plurality of holes (114) in the structure (102), and wherein the opening (208) allows insertion into the hole (130)

[0179] The fastener (118) passes through the opening (208); and

[0180] An air system (202) is connected to the panel system (200), wherein when the air system (202) is activated, the air system (202) directs air (218) through a plurality of air channels (216) within the panel system (200) to generate a friction force (220) between each fastener (118) in the plurality of fasteners (112) and a corresponding hole (130) in the plurality of holes (114) in the structure (102), the friction force (220) preventing each fastener (118) from falling out of the corresponding hole (130).

[0181] The description of different illustrative embodiments has been provided for purposes of illustration and description, and is not intended to be exhaustive or limiting of the embodiments of the disclosed form. Many modifications and variations will be apparent to those skilled in the art. Further, different illustrative embodiments may provide different features compared to other desired embodiments. The selected embodiment or embodiments are chosen and described in order to best explain the principles of the embodiments, their practical application, and to enable others skilled in the art to understand that the disclosure of various embodiments with various modifications is also suitable for specific intended uses.

Claims

1. A device for installing a fastener, the device comprising: a panel system having a plurality of air channels and openings; as well as an air system connected to the panel system and directing air through the plurality of air channels, out of the openings, and in a selected direction generally parallel to a surface of a structure into which the fasteners are to be installed so that the air impinges on exposed portions of the shanks of the fasteners, wherein the air system directs air in said selected direction generally parallel to the structure comprises directing air at the fastener stem in a first direction relative to the fastener stem with the fastener positioned in the hole of the structure, thereby generating friction between the fastener and the hole caused by the air, the friction preventing the fastener from falling out of the hole; Air is directed at the stem of the fastener in a second direction relative to the stem of the fastener to generate a torsional force on the fastener that counteracts the structure, wherein the first direction is different from the second direction.

2. The device of claim 1, wherein the selected direction is substantially perpendicular to the shaft of the fastener.

3. The apparatus of claim 1 , wherein the plate system comprises: The plurality of openings comprises openings.

4. The apparatus of claim 1, wherein the opening is shaped to allow a tool to be positioned against the fastener during installation of the fastener within a hole in a structure.

5. The apparatus of claim 1 , wherein the plate system comprises: A guide plate has a profile that matches the surface profile of the surface of the structure.

6. The apparatus of claim 5, wherein the plate system further comprises: A cover plate assembly, wherein a plurality of air channels are formed between the guide plate and the cover plate assembly.

7. The apparatus of claim 5, wherein the air system comprises: A plurality of air connectors are attached to the guide plates.

8. The apparatus of claim 1 , wherein the plate system comprises: A cover plate assembly is provided, wherein a plurality of air channels are formed in the cover plate assembly.

9. The apparatus of claim 1 , wherein the plate system comprises: A backing layer protects the surface of the structure when the panel system is positioned relative to the structure.

10. The apparatus of claim 1, wherein the air system comprises: A plurality of air connectors are attached to the plate system for connecting a source of compressed air to the plurality of air channels.

11. The apparatus according to claim 1 , further comprising: A frame pusher assembly is provided for maintaining the panel system in a selected position relative to the structure.

12. The apparatus of claim 11 , wherein the frame pusher assembly comprises: Supporting members; a pin set for attaching the support member to the frame of the structure; as well as A torque member is provided for connecting the frame pusher assembly to the plate system.

13. The apparatus of claim 12, wherein the frame pusher assembly further comprises: A frame bracket is movably attached to the support member, wherein a torque member is attached to the frame bracket such that moving the frame bracket relative to the support member moves the torque member relative to the support member.

14. The apparatus of claim 1, wherein the structure is a fuselage.

15. The apparatus of claim 1, wherein when the air is directed in a selected direction, the fastener is fully installed in the hole in the structure to form a rivet.

16. The apparatus of claim 1, wherein the air system directs air by blowing air in a direction toward the fastener or drawing air in a direction away from the fastener.

17. The apparatus of claim 1, wherein the plate system comprises: a guide plate having a profile that matches the surface profile of the surface of the structure; a cover plate assembly, wherein a plurality of air channels are formed between the guide plate and the cover plate assembly or within the cover plate assembly; a backing layer that protects a surface of the structure when the panel system is positioned relative to the structure; as well as a plurality of openings, comprising openings, wherein the plurality of openings pass through the guide plate, the set of cover plates, and the backing layer, wherein the openings are configured to be positioned above holes in the plurality of holes in the structure, and wherein the openings allow the fasteners inserted into the holes to pass through the openings.

18. A fastener retention system, comprising: A board system comprising: a guide plate having a profile that matches a surface profile of a surface of the structure; a cover plate assembly forming a plurality of air channels within the plate system; a backing layer that protects the surface of the structure when the panel system is positioned relative to the structure; and a plurality of openings passing through the guide plate, the set of cover plates, and the backing layer, wherein openings of the plurality of openings are configured to be positioned over holes of the plurality of holes in the structure, and wherein the openings allow fasteners inserted into the holes to pass through the openings; and an air system connected to the panel system, wherein when the air system is activated, the air system directs air through a plurality of air channels within the panel system to direct the air at the stem of each of the plurality of fasteners in a first direction relative to the stem of each of the plurality of fasteners so as to generate a friction force between each of the plurality of fasteners and a corresponding one of the plurality of holes in the structure, the friction force preventing each fastener from falling out of the corresponding hole, and to direct the air at the stem of each of the plurality of fasteners in a second direction relative to the stem of each of the plurality of fasteners so as to generate a torsional force on each fastener that is offset by the structure, wherein the first direction is different from the second direction.

19. A method for installing a fastener, the method comprising: placing fasteners in holes in the structure; directing air at the shaft of the fastener in a first direction relative to the shaft of the fastener when the fastener is positioned in the hole of the structure, thereby generating a frictional force between the fastener and the hole by the air to prevent the fastener from falling out of the hole; directing air at the stem of the fastener in a second direction relative to the stem of the fastener to produce a torsional force on the fastener that is counteracted by the structure, wherein the first direction is different from the second direction; installing the fastener in the hole; as well as Positioning the panel system relative to the structure.

20. The method of claim 19, wherein positioning the panel system comprises: The plate system is aligned with a plurality of tack fasteners positioned around a plurality of holes in the structure.

21. The method according to claim 19, comprising: At least one frame pusher assembly is used to maintain the panel system in a selected position relative to the structure.

22. The method of claim 19, further comprising: A plurality of holes are robotically drilled into the structure with the plate system positioned relative to the structure.

23. The method of claim 19, further comprising: A selected range of clamps are provided for clamping the structure using the plate system positioned relative to the inside of the structure and the robotic device positioned relative to the outside of the structure.

24. The method of claim 19, wherein generating the friction force through the air comprises: The exposed portion of the shank of the fastener is impinged by the air.

25. A method for installing a fastener, the method comprising: placing fasteners in holes in the structure; directing air at the shaft of the fastener in a first direction relative to the shaft of the fastener when the fastener is positioned in the hole of the structure, thereby generating a frictional force between the fastener and the hole by the air to prevent the fastener from falling out of the hole; directing air at the stem of the fastener in a second direction relative to the stem of the fastener to produce a torsional force on the fastener that is counteracted by the structure, wherein the first direction is different from the second direction; installing the fastener in the hole; as well as The fastener is robotically inserted into the hole in the structure.

26. A method for installing a fastener, the method comprising: placing fasteners in holes in the structure; directing air at the shank of the fastener in a first direction relative to the shank of the fastener with the fastener positioned in the hole of the structure, thereby generating a frictional force between the fastener and the hole by causing the air to strike an exposed portion of the shank of the fastener that prevents the fastener from falling out of the hole; directing air at the stem of the fastener in a second direction relative to the stem of the fastener to produce a torsional force on the fastener that is counteracted by the structure, wherein the first direction is different from the second direction; installing the fastener in the hole; and Positioning the plate system relative to the structure, Wherein positioning the plate system comprises: The plate system is aligned with a plurality of tack fasteners positioned around a plurality of holes in the structure.

27. A method for installing a fastener, the method comprising: placing fasteners in holes in the structure; directing air at the shank of the fastener in a first direction relative to the shank of the fastener with the fastener positioned in the hole of the structure, thereby generating a frictional force between the fastener and the hole by causing the air to strike an exposed portion of the shank of the fastener that prevents the fastener from falling out of the hole; directing air at the stem of the fastener in a second direction relative to the stem of the fastener to produce a torsional force on the fastener that is counteracted by the structure, wherein the first direction is different from the second direction; installing the fastener in the hole; positioning the panel system relative to the structure; and At least one frame pusher assembly is used to maintain the panel system in a selected position relative to the structure.

28. A method for installing a fastener, the method comprising: placing fasteners in holes in the structure; directing air at the shank of the fastener in a first direction relative to the shank of the fastener with the fastener positioned in the hole of the structure, thereby generating a frictional force between the fastener and the hole by causing the air to strike an exposed portion of the shank of the fastener that prevents the fastener from falling out of the hole; directing air at the stem of the fastener in a second direction relative to the stem of the fastener to produce a torsional force on the fastener that is counteracted by the structure, wherein the first direction is different from the second direction; installing the fastener in the hole; and Positioning the plate system relative to the structure, wherein directing the air at the stem of the fastener in the first direction comprises: delivering the air from a compressed air source through a plurality of air connections attached to the panel system into a plurality of air channels within the panel system; as well as The air is directed through the plurality of air channels and out of the panel system at an opening of the panel system in the first direction.

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