A die and method for cutting and drilling the inner liner of a composite fairing

Abstract

A die and method for drilling the inner liner of a composite material fairing, belonging to the field of composite material parts processing. The die comprises: a clamping device positioned and detachably fixed to the upper end face of the die body; an annular boss on the outer periphery of the upper end face of the die body; multiple clamping plates and multiple locators disposed on the annular boss; the clamping plates and multiple locators being positioned and detachably fixed to the annular boss; and multiple through holes on the side of the annular boss for drilling holes in the inner liner of the fairing by inserting a drill bit. The method involves: clamping and positioning the inner liner of the fairing to be drilled between the die body and the clamping device, and clamping it with multiple clamping plates and positioning it with multiple locators; mounting a milling cutter on the shaft of a handheld angle grinder, and then fitting a drilling tool bushing onto the outside of the milling cutter; starting the handheld angle grinder and performing the cutting operation using the milling cutter; removing the milling cutter and installing the drill bit for drilling. This invention is used for drilling the inner liner of a fairing.

Description

Technical Field

[0001] This invention relates to a cutting and drilling mold and method for the inner liner plate of a composite material fairing, belonging to the field of composite material parts processing technology. Background Technology

[0002] To ensure the continuity of the aircraft's shape, reduce air resistance, and minimize aerodynamic issues such as normal shock waves, while also meeting the requirements for radar beam penetration and protecting radar antenna equipment, fairings are typically designed in a spherical shape to reduce wind resistance. The inner lining of the fairing primarily serves a supporting function to ensure that the fairing has sufficient strength.

[0003] Traditional manufacturing of fairing inner liner plates (hereinafter referred to as parts) involves manual grinding, which suffers from poor precision and low efficiency. The selection of the clamping position is difficult, easily leading to deformation. This manufacturing method significantly affects the precision of the part's holes and overall shape, and also results in poor fit with the product (i.e., the fairing), leading to low part precision, easy dimensional deviations, failure to meet design requirements, and impacting the normal use of the part.

[0004] Therefore, it is necessary to design a more rationally structured cutting and drilling mold and its matching cutting and drilling method to meet the manufacturing requirements of the fairing inner liner parts. Summary of the Invention

[0005] The purpose of this invention is to solve the above-mentioned problems existing in the prior art by providing a cutting mold and method for the inner liner plate of a composite material fairing.

[0006] To achieve the above objectives, the present invention adopts the following technical solution:

[0007] A composite material fairing inner liner cutting and drilling mold includes a mold body, a clamping device, multiple clamping plates, and multiple locators. The clamping device is positioned and detachably fixed to the upper end face of the mold body. The clamping device and the mold body share a common centerline. An annular boss is provided on the outer periphery of the upper end face of the mold body. Multiple clamping plates are disposed on the annular boss of the mold body. The multiple clamping plates are positioned and detachably fixed to the annular boss of the mold body. Multiple locators are disposed on the annular boss of the mold body. The annular boss of the mold body has multiple through holes on its side for inserting a drill bit to drill holes in the fairing inner liner.

[0008] Furthermore, the mold body includes an upper truncated cone and an inverted lower truncated cone; the lower truncated cone has an annular boss on the outer periphery of its upper end face, the upper truncated cone is coaxially mounted on the lower truncated cone and the two are fixedly connected, a plurality of tool relief grooves are evenly distributed on the outer periphery of the annular boss, a mounting hole is provided in the middle of the upper end face of the upper truncated cone, and a screw hole is provided in the middle of the bottom surface inside the mounting hole.

[0009] Furthermore, the clamping device includes a disc and a cylindrical boss; the cylindrical boss is coaxial with and fixedly connected to the middle of the lower end face of the disc, and a through hole is provided in the middle of the upper end of the disc through the cylindrical boss. The cylindrical boss is matched and set in the mounting hole of the upper truncated cone. The clamping device is positioned with the mold body and is threadedly connected to the mold body through a knob inserted into the through hole.

[0010] Furthermore, the multiple clamping plates have the same structure and are all U-shaped. One side plate of the U-shaped clamping plate is shorter than the other side plate. The two opposite surfaces of the bottom plate of the U-shaped clamping plate are both horizontal. The outer surface of the long side plate of the U-shaped clamping plate is an arc-shaped concave surface. The lower end surface of the long side plate is a slope. The lower end surface of the short side plate of the U-shaped clamping plate is a plane. The lower end of the short side plate is set on an annular boss. The short side plates are respectively positioned and detachably fixedly connected to the annular boss.

[0011] Furthermore, multiple positioners have the same structure and each includes a positioner body, a positioning pin, and a handle. The positioner body includes a positioning block and a positioning plate, with the positioning block and the positioning plate fixedly connected in the middle. The annular boss has multiple mounting slots, each including a groove one on the top surface of the annular boss and a groove two on the outer side of the annular boss. The positioning block is set in the groove one, and the positioning plate is set in the groove two. The positioner body is positioned and detachably fixedly connected to the annular boss. The positioner body has a threaded hole that penetrates its thickness inside. The outer wall of the positioning pin has threads, and the positioning pin is screwed into the threaded hole. A handle is fixed to the end of the positioning pin.

[0012] Furthermore, multiple weight-reduction holes are evenly distributed on the side wall of the upper truncated cone.

[0013] Furthermore, multiple weight-reduction holes are evenly distributed on the disk.

[0014] Furthermore, a rubber pad is attached to the lower end of the disc.

[0015] A method for drilling the inner liner of a composite fairing, the method comprising the following steps:

[0016] Step 1: Press and position the inner liner of the fairing to be drilled between the mold body and the clamping device. The outer edge of the inner liner of the fairing to be drilled is pressed and fixed by multiple clamping plates. By rotating the handle of the locator, the locating pin is pressed against the inner liner of the fairing to achieve further precise positioning of the inner liner of the fairing.

[0017] Step 2: Install the milling cutter on the spindle of the handheld angle grinder, and then fit the drill bushing onto the outside of the milling cutter. The drill bushing is detachably and fixedly connected to the handheld angle grinder.

[0018] Step 3: Start the handheld angle grinder and use the milling cutter to cut the inner liner of the fairing to be drilled;

[0019] Step 4: After the cutting operation is completed, remove the milling cutter, install the drill bit on the spindle of the handheld angle grinder, and then fit the cutting tool bushing on the outside of the drill bit. The cutting tool bushing is detachably and fixedly connected to the handheld angle grinder.

[0020] Step 5: Start the handheld angle grinder and use the drill bit to drill a hole in the inner liner of the fairing to be drilled until the drilling is completed. Then remove the inner liner of the fairing.

[0021] Furthermore, the cutting tool bushing is made of alloy steel and is in the shape of a round tube. One end of the cutting tool bushing has a flange that rests against the handheld angle grinder, and the two are detachably and fixedly connected.

[0022] Compared with the prior art, the beneficial effects of the present invention are:

[0023] 1) Due to the high requirements for the fit between the inner liner of the fairing and the fairing surface, the accuracy of the hole diameter and hole position, as well as the accuracy of the part outline, the composite material fairing inner liner cutting and drilling mold and method of the present invention can meet the above requirements.

[0024] 2) Because the inner liner of the fairing is made of composite material, it is lightweight and has a complex shape. The positioning pin of the locator can quickly and accurately position the inner liner of the fairing, so that the precision of the parts after cutting and drilling is qualified and meets the usage requirements. It can also reduce the working time of workers and solve the problem of time-consuming and labor-intensive operation.

[0025] 3) Drilling operation: A handheld angle grinder-driven milling cutter is used for cutting and machining. A drill cutting tool bushing is specially developed for drilling based on the characteristics of composite parts. The drill cutting tool bushing is made of alloy steel and is precisely matched with the handheld angle grinder milling cutter. The drill cutting tool bushing and the handheld angle grinder are connected and the milling cutter is driven by a pneumatic motor. The milling cutter has a strong cutting force, and the drill cutting tool bushing can overcome the problems of large vibration and low machining accuracy, thus improving the machining speed and efficiency. It can meet the design requirements of high precision, high efficiency, low noise and low vibration. Attached Figure Description

[0026] Figure 1 This is an isometric view of a cutting and drilling mold for the inner liner of a composite material fairing according to the present invention;

[0027] Figure 2 This is a front view of a composite material fairing inner liner cutting die according to the present invention;

[0028] Figure 3 yes Figure 2 Top view;

[0029] Figure 4 yes Figure 2 The left view;

[0030] Figure 5 This is the front view of the model;

[0031] Figure 6 yes Figure 5 Top view;

[0032] Figure 7 yes Figure 5 The left view;

[0033] Figure 8 This is the front view of the clamp;

[0034] Figure 9 yes Figure 8 Top view;

[0035] Figure 10 yes Figure 9 View from direction A;

[0036] Figure 11 This is the front view of the clamping plate;

[0037] Figure 12 yes Figure 11 Top view;

[0038] Figure 13 yes Figure 12 View from direction B;

[0039] Figure 14 This is the main view of the locator;

[0040] Figure 15 yes Figure 14 Top view;

[0041] Figure 16 yes Figure 15 The C-direction view;

[0042] Figure 17 This is the main view of the drill cutting tool bushing;

[0043] Figure 18 yes Figure 17 DD section sectional view;

[0044] Figure 19 yes Figure 1 A magnified view of a portion at point E.

[0045] The component names and labels in the above figures are as follows:

[0046] 1. Mold body; 2. Clamping device; 3. U-shaped clamping plate; 4. Positioner; 5. Upper truncated cone; 6. Lower truncated cone; 7. Annular boss; 8. Tool groove; 9. Mounting hole; 10. Screw hole; 11. Weight reduction hole one; 12. Disc; 13. Cylindrical boss; 14. Knob; 15. Through hole one; 16. Weight reduction hole two; 17. Base plate; 18. Long side plate; 19. Arc-shaped concave surface; 20. Inclined surface; 21. Short side plate; 22. Positioning pin; 23. Handle; 24. Positioning block; 25. Positioning plate; 26. Cutting drill bushing; 27. Through hole two; 28. Flanged edge; 29. ​​Lifting ring. Detailed Implementation

[0047] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the invention, not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0048] Specific implementation method one: as follows Figures 1-16 , Figure 19 As shown, this embodiment describes a composite material fairing inner liner cutting and drilling mold, including a mold body 1, a clamping device 2, multiple clamping plates and multiple positioning devices 4;

[0049] The clamping device 2 is positioned (by pins) and detachably fixed (by screws) to the upper end face of the mold body 1. The clamping device 2 and the mold body 1 are on the same center line. The outer periphery of the upper end face of the mold body 1 is provided with an annular boss 7. Multiple clamping plates are set on the annular boss 7 of the mold body 1. The multiple clamping plates are positioned (by pins) and detachably fixed (by screws) to the annular boss 7 of the mold body 1. Multiple locators 4 are set on the annular boss 7 of the mold body 1. The multiple locators 4 are positioned (by pins) and detachably fixed (by screws) to the annular boss 7 of the mold body 1. The side of the annular boss 7 of the mold body 1 is provided with multiple through holes 27 for drilling holes in the inner liner of the fairing by inserting a drill bit. Multiple lifting rings 29 are fixed on the outer wall of the mold body 1 to facilitate mold handling.

[0050] Furthermore, the mold body 1 includes an upper frustum 5 and an inverted lower frustum 6; the lower frustum 6 has an annular boss 7 on its outer periphery of the upper end face, the upper frustum 5 is coaxially mounted on the lower frustum 6 and the two are fixedly connected (by welding), the annular boss 7 has a plurality of tool relief grooves 8 evenly distributed on its outer periphery, the upper frustum 5 has a mounting hole 9 in the middle of its upper end face, and the bottom surface of the mounting hole 9 has a screw hole 10 in the middle.

[0051] Furthermore, the clamping device 2 includes a disc 12 and a cylindrical boss 13; the cylindrical boss 13 is coaxial with the middle of the lower end face of the disc 12 and is fixedly connected (by welding); the middle of the upper end of the disc 12 is provided with a through hole 15 that passes through the cylindrical boss 13; the cylindrical boss 13 is matched and set in the mounting hole 9 of the upper truncated cone body 5; the clamping device 2 is positioned with the mold body 1 (by a pin) and is threadedly connected to the mold body 1 by a knob 14 that passes through the through hole 15 (the knob 14 is threadedly connected to the screw hole 10).

[0052] Furthermore, the multiple clamping plates have the same structure and are all U-shaped. One side plate of the U-shaped clamping plate 3 is shorter than the other side plate. The two opposite plates of the bottom plate 17 of the U-shaped clamping plate 3 are both horizontal. The outer side plate of the long side plate 18 of the U-shaped clamping plate 3 is an arc-shaped concave surface 19 (to be in contact with the inner lining plate of the fairing). The lower end surface of the long side plate 18 is a slope 20. The lower end surface of the short side plate 21 of the U-shaped clamping plate 3 is a plane. The lower end of the short side plate 21 is set on the annular boss 7. The short side plate 21 is positioned (by pins) and detachably fixed to the annular boss 7 (the bottom plate 17 of the U-shaped clamping plate 3 has screw holes and positioning holes on one side of the short side plate 21).

[0053] Furthermore, the multiple positioners 4 have the same structure and each includes a positioner body, a positioning pin 22, and a handle 23. The positioner body includes a positioning block 24 and a positioning plate 25, with the positioning block 24 and the positioning plate 25 fixedly connected in the middle. The annular boss 7 is provided with multiple mounting slots, each mounting slot including a groove one opened on the top surface of the annular boss 7 and a groove two opened on the outer side of the annular boss 7. The positioning block 24 is set in the groove one, and the positioning plate 25 is set in the groove two. The positioner body is positioned (by pins) and detachably fixedly connected (by screws) to the annular boss 7. The positioner body is provided with a threaded hole that penetrates its thickness inside. The outer wall of the positioning pin 22 is provided with threads, and the positioning pin 22 is screwed into the threaded hole. The end of the positioning pin 22 is fixed with a handle 23.

[0054] Furthermore, multiple weight-reduction holes 11 are evenly distributed on the side wall of the upper truncated cone 5.

[0055] Furthermore, multiple weight-reducing holes 16 are evenly distributed on the disk 12.

[0056] Furthermore, a rubber pad is attached to the lower end face of the disk 12 (for protecting the inner liner of the fairing).

[0057] The inner lining of the fairing is made of composite material.

[0058] The present invention utilizes the clamping device 2 for positioning and employs the cutting tool bushing 26 to improve machining accuracy and increase interchangeability.

[0059] Mold Body 1: Serving as the base of the entire mold, it is made entirely of Q235-AF steel. The overall outer surface of Mold Body 1 is manufactured using CNC machining based on pneumatic design. A machining program is created according to the 3D digital model, and the profile of Mold Body 1 (the upper end face of Mold Body 1) is machined using mechanical methods. Furthermore, drill holes are machined on the side of Mold Body 1 using five-axis CNC machining. After welding the joint of Mold Body 1 (i.e., the joint between the upper and lower truncated cones), stress relief treatment is required.

[0060] The main function of the mold 1 is to serve as a support base for the inner liner of the fairing, which can support the inner liner of the fairing. This makes it convenient to use the clamping device 2 and the positioning device 4 for subsequent cutting and drilling.

[0061] Clamping Device 2: The entire device is constructed from Q235-AF steel and welded together. Stress relief treatment is required after welding to ensure structural stability. Clamping Device 2 is machined according to its pneumatic shape and using CNC machining technology. Based on a machining program developed from a 3D digital model, the profile of Clamping Device 2 (upper end face) is precisely machined. Clamping Device 2 is fixed to the top of the mold body 1 using screws and pins. To protect the inner liner of the fairing, a rubber pad is attached to the contact area between the lower end face of Clamping Device 2 and the product to prevent damage to the inner liner during clamping operations.

[0062] U-shaped clamping plate 3: The entire piece is welded from Q235-AF steel. To ensure the stability of the structure after welding, the U-shaped clamping plate 3 requires stress relief treatment after welding. The U-shaped clamping plate 3 is manufactured according to its aerodynamic shape, based on a 3D digital model, and the middle surface (i.e., the lower end face of the U-shaped clamping plate 3) is precisely machined using CNC machining technology. This U-shaped clamping plate 3 adopts a quick-release design, using hand-tightened screws and pins for connection, improving work efficiency and ease of operation.

[0063] Positioner 4: Made of 45# steel, the side of the fairing inner liner is machined using a five-axis CNC machining method based on a three-dimensional digital model. Positioner 4 is fixed at the corresponding position in the mold body 1.

[0064] Specific implementation method two: such as Figures 1-18 As shown, this embodiment discloses a method for drilling the inner liner of a composite material fairing. The method is implemented using the mold described in Specific Embodiment 1, and includes the following steps:

[0065] Step 1: Press and position the inner liner of the fairing to be drilled (by pin and screw) between the mold body 1 and the clamping device 2. The outer edge of the inner liner of the fairing to be drilled is pressed and fixed by multiple clamping plates. By rotating the handle 23 of the locator 4, the positioning pin 22 is pressed against the inner liner of the fairing, so as to further accurately position the inner liner of the fairing.

[0066] Step 2: Install the milling cutter on the spindle of the handheld angle grinder, and then fit the drill cutting tool bushing 26 on the outside of the milling cutter (fitting accuracy is H7 / g6). The drill cutting tool bushing 26 is detachably and fixedly connected to the handheld angle grinder (by screws), and the milling cutter head is located outside the drill cutting tool bushing 26.

[0067] Step 3: Start the handheld angle grinder (driven by a pneumatic motor) and use the milling cutter to cut the inner liner of the fairing to be drilled (driven by the pneumatic motor of the handheld angle grinder).

[0068] Step 4: After the cutting operation is completed, remove the milling cutter, install the drill bit on the spindle of the handheld angle grinder, and then fit the cutting tool bushing 26 on the outside of the drill bit (fitting accuracy is H7 / g6). The cutting tool bushing 26 is detachably and fixedly connected to the handheld angle grinder (by screws), and the tip of the drill bit is located outside the cutting tool bushing 26.

[0069] Step 5: Start the handheld angle grinder (driven by a pneumatic motor) and use the drill bit to drill the inner liner of the fairing to be drilled (driven by the pneumatic motor of the handheld angle grinder) until the drilling is completed. Then remove the inner liner of the fairing.

[0070] Furthermore, the cutting tool bushing 26 is made of alloy steel and is in the shape of a round tube. One end of the cutting tool bushing 26 has a flange 28, which rests against the handheld angle grinder, and the two are detachably and fixedly connected (by screws).

[0071] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other forms without departing from its spirit or essential characteristics. Therefore, the embodiments should be considered illustrative and non-limiting in all respects, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of the equivalents of the claims are intended to be included within the present invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

[0072] Furthermore, it should be understood that although this specification describes embodiments, not every embodiment contains only one independent technical solution. This narrative style is merely for clarity. Those skilled in the art should consider the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. A cutting and drilling mold for the inner liner plate of a composite material fairing, characterized in that: Includes a mold body (1), a clamping device (2), multiple clamping plates and multiple locators (4); the clamping device (2) is positioned and detachably fixed to the upper end face of the mold body (1), the clamping device (2) and the mold body (1) share the same center line, the outer periphery of the upper end face of the mold body (1) is provided with an annular boss (7), multiple clamping plates are set on the annular boss (7) of the mold body (1), multiple clamping plates are positioned and detachably fixed to the annular boss (7) of the mold body (1), multiple locators (4) are set on the annular boss (7) of the mold body (1), multiple locators (4) are positioned and detachably fixed to the annular boss (7) of the mold body (1), the side of the annular boss (7) of the mold body (1) is provided with multiple through holes (27) for drilling holes in the inner liner of the fairing by inserting a drill bit. The clamping device (2) includes a disc (12) and a cylindrical boss (13); the cylindrical boss (13) is coaxial with the middle of the lower end face of the disc (12) and fixedly connected. The middle of the upper end of the disc (12) is provided with a through hole (15) that passes through the cylindrical boss (13). The cylindrical boss (13) is matched and set in the mounting hole (9) of the upper truncated cone body (5). The clamping device (2) is positioned with the mold body (1) and is threadedly connected to the mold body (1) through a knob (14) inserted into the through hole (15). Multiple positioners (4) have the same structure and each includes a positioner body, a positioning pin (22) and a handle (23); the positioner body includes a positioning block (24) and a positioning plate (25), the positioning block (24) and the positioning plate (25) are fixedly connected in the middle; the annular boss (7) is provided with multiple mounting slots, each mounting slot includes a groove one opened on the top surface of the annular boss (7) and a groove two opened on the outer side of the annular boss (7), the positioning block (24) is set in the groove one, the positioning plate (25) is set in the groove two, the positioner body is positioned and detachably fixedly connected to the annular boss (7), the positioner body is provided with a threaded hole that penetrates its thickness inside, the positioning pin (22) is provided with a thread on the outer wall, the positioning pin (22) is screwed into the threaded hole, and the end of the positioning pin (22) is fixed with a handle (23).

2. The composite material fairing inner liner cutting die according to claim 1, characterized in that: The mold body (1) includes an upper truncated cone (5) and an inverted lower truncated cone (6); the lower truncated cone (6) has an annular boss (7) on the outer periphery of its upper end face, the upper truncated cone (5) is coaxially mounted on the lower truncated cone (6) and the two are fixedly connected, and multiple tool relief grooves (8) are evenly distributed on the outer periphery of the annular boss (7), and a mounting hole (9) is provided in the middle of the upper end face of the upper truncated cone (5), and a screw hole (10) is provided in the middle of the bottom surface inside the mounting hole (9).

3. The composite material fairing inner liner cutting die according to claim 1, characterized in that: Multiple clamping plates have the same structure and are all U-shaped. One side plate of the U-shaped clamping plate (3) is shorter than the other side plate. The two opposite plates of the bottom plate (17) of the U-shaped clamping plate (3) are both horizontal. The outer side plate of the long side plate (18) of the U-shaped clamping plate (3) is an arc-shaped concave surface (19). The lower end surface of the long side plate (18) is a slope (20). The lower end surface of the short side plate (21) of the U-shaped clamping plate (3) is a plane. The lower end of the short side plate (21) is set on the annular boss (7). The short side plate (21) is positioned and detachably fixedly connected to the annular boss (7).

4. The composite material fairing inner liner cutting die according to claim 2, characterized in that: Multiple weight-reducing holes (11) are evenly distributed on the side wall of the upper truncated cone (5).

5. A composite material fairing inner liner cutting die according to claim 1, characterized in that: Multiple weight-reducing holes (16) are evenly distributed on the disc (12).

6. The composite material fairing inner liner cutting die according to claim 1, characterized in that: A rubber pad is attached to the lower end of the disc (12).

7. A method for drilling the inner liner plate of a composite material fairing, characterized in that: The method is implemented using the mold described in any one of claims 4-6, and the method includes the following steps: Step 1: Press and position the inner liner of the fairing to be drilled between the mold body (1) and the clamping device (2). The outer edge of the inner liner of the fairing to be drilled is pressed and fixed by multiple clamping plates. By rotating the handle (23) of the locator (4), the positioning pin (22) is pressed against the inner liner of the fairing, so as to further accurately position the inner liner of the fairing. Step 2: Install the milling cutter on the spindle of the handheld angle grinder, and then fit the cutting tool bushing (26) on the outside of the milling cutter. The cutting tool bushing (26) is detachably and fixedly connected to the handheld angle grinder. Step 3: Start the handheld angle grinder and use the milling cutter to cut the inner liner of the fairing to be drilled; Step 4: After the cutting operation is completed, remove the milling cutter, install the drill bit on the spindle of the handheld angle grinder, and then fit the cutting tool bushing (26) on the outside of the drill bit. The cutting tool bushing (26) is detachably and fixedly connected to the handheld angle grinder. Step 5: Start the handheld angle grinder and use the drill bit to drill a hole in the inner liner of the fairing to be drilled until the drilling is completed. Then remove the inner liner of the fairing.

8. The method for drilling the inner liner of a composite material fairing according to claim 7, characterized in that: The cutting tool bushing (26) is made of alloy steel. The cutting tool bushing (26) is in the shape of a round tube. One end of the cutting tool bushing (26) has a flange (28). The flange (28) rests against the handheld angle grinder, and the two are detachably and fixedly connected.

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