An aircraft assembly fixture

Abstract

This invention relates to the field of assembly tool technology, specifically disclosing an aircraft assembly fixture, including a clamping assembly for clamping a loading chamber during assembly. The clamping assembly includes a base, with a fixed platform and an end support at each end of the base. The end support supports the wire connection portion of the loading chamber and has a positioning boss. During assembly, the outer end face of the wire connection portion of the loading chamber abuts against the positioning boss. A screw is screwed onto the fixed platform, with a sliding sleeve connected to the end of the screw near the end support. A push rod is inserted into the end of the sliding sleeve near the end support. During assembly, the push rod clamps the loading chamber. The push rod has a centering structure that ensures the push rod is coaxial with the loading chamber during assembly. The clamping assembly also includes a directional pin to prevent the loading chamber from rotating. During assembly, turning the screw pushes the push rod to clamp the loading chamber. The centering structure keeps the push rod and the loading chamber coaxial, preventing misalignment. The directional pin prevents the loading chamber from rotating. When the loading chamber is clamped and screwed onto the connector, the wire will not be sheared.

Description

Technical Field

[0001] This invention relates to the field of assembly tool technology, specifically to an aircraft assembly fixture. Background Technology

[0002] Some aircraft employ a split design, with the head and a loading chamber at each end. The loading chamber contains filler material. The head and loading chamber are connected by a connecting tube, which is a through-type structure. The head and the connecting tube are connected by threads, as are the loading chamber and the connecting tube. The head and the loading chamber are connected by wires. One end of the wire is connected to the center of the head, and the other end is connected to the end of the loading chamber. Because the loading chamber contains filler material, the wires do not pass directly through the filler material. Instead, wire grooves are set on the side wall of the loading chamber shell, and the wires are laid in the wire grooves. If the connecting tube is directly tightened during assembly of the connecting tube and the loading chamber, it is easy for friction to cause the loading chamber to rotate, resulting in the wires being sheared, leading to faults such as damage to the wire insulation, short circuits, or open circuits. Summary of the Invention

[0003] To address the problem that when the connecting sleeve of the aforementioned split-type aircraft is screwed onto the loading chamber, it causes the loading chamber to rotate, resulting in the cutting of the connecting wire between the head and the loading chamber, the present invention provides an aircraft assembly fixture that can keep the loading chamber fixed during assembly.

[0004] To solve the above-mentioned technical problems, the present invention features the following structural characteristics: it includes a clamping assembly for clamping the loading chamber of the aircraft during assembly. The clamping assembly includes a base, one end of which is provided with a fixed platform, and the other end of which is fixedly provided with an end support for supporting the loading chamber wire connection part at the end of the loading chamber during assembly. A positioning boss is fixedly provided on the end support for abutting against the outer end face of the loading chamber wire connection part during assembly and preventing the loading chamber from moving away from the fixed platform. A screw threaded through the fixed platform is connected to the fixed platform. A sliding sleeve is connected to the end of the screw near the end support, which can rotate relative to the screw and move synchronously with the screw. A push rod for clamping the loading chamber during assembly and which can disengage from the sliding sleeve is inserted into the end of the sliding sleeve near the end support. A centering structure is provided at the end of the push rod near the loading chamber for coaxiality with the loading chamber during assembly. The clamping assembly also includes a directional pin that can pass through the positioning boss and be inserted into the side wall of the loading chamber wire connection part during assembly to prevent the loading chamber from rotating.

[0005] With the above structure, before assembly, the aircraft's wires are pre-connected. The wires extending from the loading chamber pass through the connector and connect to the aircraft's head. Then, the loading chamber is tightened with a clamping assembly. When tightening the loading chamber, the aircraft's head is placed on one side of the clamping assembly. One end of the loading chamber's wire connection is placed on the end support, and the end face of the loading chamber's wire connection away from the connector rests against the positioning boss. The directional pin passes through the positioning boss and inserts into the side wall of the loading chamber's wire connection, preventing the loading chamber from rotating. The screw is then turned to move it as far away from the loading chamber as possible. One end of the push rod passes through the connector and abuts against the center area of ​​the front wall of the loading chamber. Then, the screw is turned clockwise to move it closer to the loading chamber. When the screw moves closer to the loading chamber, the end of the push rod away from the loading chamber is aligned with the sliding sleeve. During the screw's movement, the push rod... Insert one end of the feed chamber into the slide groove and continue to tighten the screw to make the push rod press against the front wall of the feed chamber. At this time, the push rod will press the feed chamber tightly. The centering structure makes the push rod and the feed chamber coaxial during the pressing process, preventing the feed chamber from being pushed off-center. Under the action of the push rod and the directional pin, the feed chamber cannot rotate or move in other directions, and the feed chamber can remain stationary. Then tighten the connecting sleeve and screw it onto the feed chamber. During the screwing process, the rotation of the connecting sleeve will not drive the feed chamber to rotate, avoiding the wire being cut due to the rotation of the feed chamber, thus protecting the wire. After the connecting sleeve and the feed chamber are screwed together, turn the screw counterclockwise to move the screw away from the feed chamber. The pressing force of the push rod on the front wall of the feed chamber will disappear. Disconnect the push rod from the slide sleeve and remove the push rod. Then screw the head of the aircraft onto the connecting sleeve. The aircraft assembly is complete. The clamping assembly of the present invention can fix the position of the loading chamber during aircraft assembly. When the connecting cylinder is screwed to the loading chamber, it will not cause the loading chamber to rotate, thus avoiding the shearing of the wire caused by the rotation of the loading chamber.

[0006] The centering structure includes a centering pin that rests on the center of the front wall of the loading chamber during assembly. The centering pin includes a column, and the end face of the column near the front wall of the loading chamber has an outwardly protruding plug that can be inserted into the groove at the center of the front wall of the loading chamber.

[0007] A centering pin insertion hole is provided on the end face of the push rod near the front wall of the loading chamber. The length direction of the centering pin insertion hole is the same as the length direction of the push rod. The column can be inserted into the centering pin insertion hole and can slide along the length direction of the centering pin. A spring is provided in the centering pin insertion hole to push the centering pin towards the loading chamber. An elongated hole with the same length direction as the column is provided. A fixing pin is provided on the push rod through the elongated hole. The elongated hole can slide along the fixing pin.

[0008] The upper surface of the positioning boss is provided with a limiting slide for limiting the sliding direction of the directional pin and communicating with the slide groove on the side wall of the feed chamber wire connection part.

[0009] The directional pin includes a plug that can be inserted into the slide groove. One end of the plug is fixedly connected to a stop block whose size is larger than the cross-sectional size of the slide groove. When the plug is inserted into the slide groove, the stop block is located in the limiting slide.

[0010] The sliding sleeve has a push rod insertion hole on its end face near the loading chamber.

[0011] The screw is provided with a fixed connector at one end near the loading chamber. The sliding sleeve is provided with a screw insertion hole into which the connector can be inserted. The outer surface of the connector is provided with a second arc-shaped groove in a circumferential direction. The inner surface of the screw insertion hole is provided with a first arc-shaped groove in a circumferential direction corresponding to the second arc-shaped groove. The first arc-shaped groove and the second arc-shaped groove are joined to form an annular channel. The annular channel is filled with a plurality of spheres.

[0012] The base is also fixedly provided with a central support platform that supports the end of the loading chamber away from the positioning boss. The central support platform is located between the fixed platform and the end support platform.

[0013] A side rod that abuts against the base during assembly is fixedly connected to the surface of the top rod.

[0014] The base is also provided with a support mechanism for supporting the head of the aircraft during assembly. The support mechanism includes an end bracket for supporting the open end of the head and a V-shaped bracket for supporting the head wire connection. The end bracket is connected to a positioning plate to prevent the head from tilting and sliding off the support mechanism.

[0015] The aircraft assembly fixture of this invention is equipped with a clamping assembly. When the aircraft's connecting sleeve is screwed into the loading chamber, the clamping assembly can fix the position of the loading chamber, preventing the loading chamber from rotating and being sheared. The directional pin has the function of preventing the loading chamber from rotating. A centering pin is provided on the contact surface between the push rod and the front wall of the loading chamber. When the plug of the centering pin is inserted into the groove at the center position of the front wall of the loading chamber, the push rod and the loading chamber are coaxial. The pressure applied by the push rod to the front wall of the loading chamber is located in the center, the loading chamber is balanced by force, and the loading chamber is more stable and less prone to being pushed off course. When the pressure applied by the screw to the front wall of the loading chamber increases, the centering pin is pressed into the centering pin insertion hole of the push rod. A spring is provided in the centering pin insertion hole. The spring compression gradually increases the elastic force of the spring on the centering pin, resulting in a gradually increasing pressure on the front wall of the loading chamber and a better tightening effect. When the screw is released, the pressure on the front wall of the loading chamber gradually decreases under the action of the centering pin and the spring, and the loading chamber rebounds. During the rebound, part of the rebound force is transferred to the connecting sleeve, achieving the effect of threaded tightening. An annular channel is formed between the connecting head of the sliding sleeve and the screw, and a ball is installed in the annular channel to reduce the sliding resistance when the connecting head and the sliding sleeve rotate relative to each other. The ball also plays a transmission role. When the screw moves, the ball moves with it, and the ball then drives the sliding sleeve to move. The tooling is also equipped with a support mechanism, which supports the nose of the aircraft during assembly. Attached Figure Description

[0016] Figure 1 A plan view of the clamping assembly for assembling tooling on an aircraft;

[0017] Figure 2 for Figure 1 View from direction A;

[0018] Figure 3 for Figure 1 BB cross-sectional diagram;

[0019] Figure 4 for Figure 3 Enlarged view at point F;

[0020] Figure 5 for Figure 1 A schematic diagram of the CC cross-section;

[0021] Figure 6 for Figure 1 DD cross-sectional schematic diagram;

[0022] Figure 7 This is a plan view of the tooling after the clamping components and supporting mechanism are combined.

[0023] Figure 8 for Figure 7 G-direction view;

[0024] Figure 9 for Figure 8 A schematic diagram of the HH cross-section;

[0025] Figure 10 for Figure 8 Schematic diagram of section II;

[0026] Figure 11 for Figure 8 A schematic diagram of the cross-section of the JJ;

[0027] Figure 12 This is a schematic diagram showing the aircraft's nose placed on the support mechanism during assembly, with the top rod connected to the loading chamber and the connecting cylinder not screwed to the loading chamber.

[0028] Figure 13 A schematic diagram showing the loading chamber being tightened by the push rod during aircraft assembly, and the connecting cylinder being screwed into the loading chamber;

[0029] Figure 14 This is a schematic diagram showing the assembly of an aircraft after the top rod has been removed and the head has been screwed into the connecting tube.

[0030] Figure 15 Side view of the directional pin;

[0031] Figure 16 for Figure 28Enlarged view of point O;

[0032] Figure 17 A schematic diagram showing the directional pin inserted into the slide groove;

[0033] Figure 18 This is a schematic diagram showing the push rod near the end of the loading chamber;

[0034] Figure 19 This is a schematic diagram of the centering pin.

[0035] Figure 20 This is a schematic diagram showing the centering pin after it has been installed at the end of the push rod.

[0036] Figure 21 for Figure 12 Enlarged view of point K;

[0037] Figure 22 for Figure 13 Enlarged view of point L;

[0038] Figure 23 This is an enlarged view of the screw connector.

[0039] Figure 24 This is a schematic diagram of the sliding sleeve.

[0040] Figure 25 This is a schematic diagram of the screw and sleeve after assembly. Figure 2 Enlarged view of point E;

[0041] Figure 26 for Figure 24 MM cross-sectional schematic diagram;

[0042] Figure 27 for Figure 25 A schematic diagram of the NN cross-section;

[0043] Figure 28 This is a schematic diagram of the aircraft components before they are assembled.

[0044] Figure 29 This is a schematic diagram of the assembled aircraft.

[0045] In the diagram: 1. Base; 2. End support; 3. Positioning boss; 31. Limiting slide; 4. Directional pin; 41. Insert block; 42. Stop block; 5. Middle support; 6. Top rod; 61. Centering pin; 611. Column; 612. Conical plug; 613. Elongated hole; 614. Annular notch; 615. Stop; 62. Side rod; 63. Centering pin insertion hole; 64. Spring; 65. Fixing pin shaft; 7. Sliding sleeve; 71. Top rod insertion hole; 72. Screw insertion hole; 73. Internal threaded hole; 74. First arc-shaped groove; 75. Screw; 8. Fixing platform; 9. Screw; 91. Connector; 92. Second arc-shaped groove; 93. Steel ball; 10. Fixing head; 11. Handle; 12. Positioning plate ; 13. End bracket; 14. Mounting base; 15. Connecting rod; 16. V-shaped bracket; 17. Support block; 100. Head; 101. Head wire connection part; 102. Head shell; 103. First external thread connection part; 200. Connecting sleeve; 201. Connecting section; 202. Second external thread connection part; 203. First internal thread connection part; 300. Loading chamber; 301. Loading chamber shell; 302. Loading chamber front wall; 303. Loading chamber wire connection part; 304. Wire groove; 305. Plug; 306. Second internal thread connection part; 307. Filler; 308. Conical groove; 309. Recessed opening; 310. Slide groove; 311. Stop surface; 400. Wire. Detailed Implementation

[0046] like Figure 16 , 28As shown in Figure 29, a split-type aircraft includes three parts: a head 100, a connecting tube 200, and a loading chamber 300. The head 100 and the loading chamber 300 are connected via the connecting tube 200. Both the head 100 and the connecting tube 200, and the connecting tube 200 and the loading chamber 300, are threaded connections. Specifically, the head 100 is conical, with the smaller end being a head wire connection part 101. A head shell 102 is connected to one side of the head wire connection part 101. The head shell 102 is conical, with the larger end of the head shell 102 being open. The device includes a first external threaded connection part 103; the connecting sleeve 200 has a through-type structure with open ends. One end of the connecting sleeve 200 is a first internal threaded connection part 203 that can be screwed onto the first external threaded connection part 103, and the other end is a second external threaded connection part 202. The diameter of the first internal threaded connection part 203 is smaller than the diameter of the second external threaded connection part 202. The first internal threaded connection part 203 and the second external threaded connection part 202 are connected by a connecting section 201; the loading chamber 300 includes a loading chamber outer shell 301, and a loading chamber outer shell 301. The shell 301 is cone-shaped. The loading chamber shell 301 is filled with filler 307. The larger end of the loading chamber shell 301 has a loading chamber front wall 302, which is arc-shaped and recessed towards the smaller end of the loading chamber shell 301. The loading chamber front wall 302 serves as the sidewall of the filling space for the filler 307. A conical groove 308 is formed at the center of the outer surface of the loading chamber front wall 302. The center of the loading chamber front wall 302 can be determined by the conical groove 308. The outer surface of the loading chamber front wall 302 referred to here is not... The surface in contact with the filler 307 has a second internal thread connection 306 at its large end, which can be screwed onto the second external thread connection 202. A filling chamber wire connection 303 is located inside the small end of the filling chamber shell 301. A plug 305 is located outside the filling chamber wire connection 303, serving as the sidewall of the filling space for the filler 307. A groove 310 is formed on the sidewall of the filling chamber wire connection 303, with the length direction of the groove 310 parallel to the axial direction of the filling chamber shell 301. Figure 16As shown, a recess 309 is provided on the side wall of the loading chamber shell 301. The recess 309 is located at the starting end of the slide groove 310 and communicates with the slide groove 310. The starting end of the slide groove 310 refers to one end of the outer end face of the loading chamber wire connection part 303. The outer end face of the loading chamber wire connection part 303 refers to the surface that contacts the positioning boss 3 described below. A baffle 311 is formed at the recess 309 on the side wall of the loading chamber shell 301. The head 100 is connected to the loading chamber 300 by a wire 400. The wire 400 passes through the intermediate connector 200, and one end of the wire 400 is connected to the center of the head wire connection 101. To prevent the wire 400 from twisting or coiling during screwing, a pivot is provided at the connection point between the wire 400 and the head wire connection 101. The other end of the wire 400 is connected to the loading chamber wire connection 303. Since the loading chamber 300 is filled with filler 307, the wire 400 does not pass through the filler 307. A wire groove 304 is provided on the inner surface of the loading chamber shell 301, and the wire 400 is laid in the wire groove 304. After assembly, the head 100, connector 200, and loading chamber 300 of the aircraft are coaxial.

[0047] Reference Figure 1-27 The present invention provides an aircraft assembly fixture for assembling the aforementioned split-type aircraft. It includes a clamping component that clamps the loading chamber 300 during aircraft assembly, preventing the loading chamber 300 from rotating or moving in other directions, thus keeping the loading chamber 300 fixed. The fixture may also include a support mechanism that supports the head 100 of the aircraft during assembly.

[0048] Reference Figure 1-7 12-27, The clamping assembly includes a base 1, one end of which has a fixed platform 8, and the other end has a fixed end support 2. A horizontal screw 9 is threaded onto the fixed platform 8, passing through the fixed platform 8 and pointing towards the end support 2. During assembly, the end support 2 supports the feed chamber wire connection part 303. The upper surface of the end support 2 has a fixed positioning boss 3, which is higher than the end support 2. During assembly, the outer end face of the feed chamber wire connection part 303 abuts against the positioning boss 3, preventing the feed chamber 300 from moving away from the fixed platform 8. The base 1 also has a middle support 5, located between the fixed platform 8 and the end support 2. The middle support 5 supports the end of the feed chamber 300 away from the positioning boss 3. Figure 5As shown, the upper surface of the middle support platform 5 is a concave arc shape, which is adapted to the shape of the supporting part of the loading chamber 300. When the loading chamber 300 is placed on the middle support platform 5, it is not easy to roll to the sides. The end of the screw 9 away from the end support platform 2 is provided with a fixing head 10. The fixing head 10 is provided with a handle 11. The handle 11 is fixedly installed on the fixing head 10. Turning the handle 11 clockwise or counterclockwise drives the screw 9 to rotate, so that the screw 9 moves closer to or away from the end support platform 2. The end of the screw 9 near the end support platform 2 is connected to a sliding sleeve 7. The sliding sleeve 7 can rotate relative to the screw 9. When the screw 9 rotates, the sliding sleeve 7 can remain stationary. When the screw 9 moves closer to or away from the end support platform 2, the sliding sleeve 7 moves synchronously with the screw 9. Since the screw 9 moves in a straight line, the sliding sleeve 7 moves in a straight line with the screw 9. The end of the sliding sleeve 7 near the end support platform 2 is inserted with a top. When assembling the aircraft, one end of the push rod 6 is inserted into the sliding sleeve 7, and the other end abuts against the front wall 302 of the loading chamber, so that the outer end face of the wire connection part 303 of the loading chamber is tightly abutted against the positioning boss 3, thereby pressing the loading chamber 300 tightly. The push rod 6 can disengage from the sliding sleeve 7. When the loading chamber 300 and the connecting sleeve 200 are screwed together, and then the head 100 is screwed together with the connecting sleeve 200, the push rod 6 disengages from the sliding sleeve 7 and is removed. During assembly, the push rod 6 is coaxial with the loading chamber 300 to prevent the loading chamber 300 from being pushed off-center, which would affect the assembly quality. A side rod 62 is fixedly connected to the surface of the push rod 6. During assembly, the end of the side rod 62 abuts against the upper surface of the base 1 to prevent the push rod 6 from rotating during the process of pressing the loading chamber 300. In the figure, the side rod 62 is perpendicular to the push rod 6. Of course, it can also be inclined and crossed, as long as it can abut against the upper surface of the base 1.

[0049] Reference Figure 1-7 12-17, the clamping assembly includes a directional pin 4 that prevents the loading chamber 300 from rotating. The directional pin 4 passes through the positioning boss 3 and is inserted into the side wall of the loading chamber wire connection part 303. Specifically, the upper surface of the positioning boss 3 is provided with a limiting slide 31 for limiting the sliding direction of the directional pin 4. After the directional pin 4 is placed in the limiting slide 31, it can only slide along the length direction of the limiting slide 31. The limiting slide 31 is connected to the slide groove 310, such as... Figure 4 As shown, the cross-section of the limiting slide 31 is a stepped groove. The width of the upper half of the limiting slide 31 is greater than the width of the lower half, and the width of the lower half of the limiting slide 31 is slightly greater than the width of the directional pin 4, so that the directional pin 4 can only slide back and forth along the groove. The directional pin 4 first enters the upper half of the limiting slide 31 and then enters the lower half. The stepped groove facilitates the insertion of the directional pin 4. Of course, it can also be designed as a groove of the same width, such as... Figure 15As shown, the directional pin 4 includes an insert block 41, one end of which is fixedly connected to a stop block 42. The stop block 42 can be integrally formed with the insert block 41. The insert block 41 can be inserted into the slide groove 310. The size of the stop block 42 is larger than the cross-sectional size of the slide groove 310, so the stop block 42 cannot be inserted into the slide groove 310. The length of the insert block 41 is less than or equal to the length of the slide groove 310, so the insert block 41 can be completely inserted into the slide groove 310. When the insert block 41 is completely inserted into the slide groove 310, the stop block 42 touches the stop surface 311 at the recess 309. The stop block 42 is located in the limiting slide 31, which blocks the stop block 42 from rotating, thereby preventing the loading chamber 300 from rotating. The directional pin 4 is inserted. The function of the recess 309 is to facilitate observation of the connection between the slide groove 310 and the limiting slide 31. If the recess 309 is not provided, it is not easy to determine whether the slide groove 310 is connected to the limiting slide 31.

[0050] Reference Figure 1-7 12-14, 18-22, the end of the push rod 6 near the loading chamber 300 is provided with a centering structure to make the push rod 6 coaxial with the loading chamber 300 during assembly, such as... Figure 18-22As shown, the centering structure includes a centering pin 61. During assembly, the centering pin 61 can abut against the center position of the front wall 302 of the loading chamber. The centering pin 61 includes a column 611. The end face of the column 611 near the front wall 302 of the loading chamber has an outwardly protruding conical plug 612. The conical plug 612 can be inserted into the conical groove 308. When the conical plug 612 is inserted into the conical groove 308 and fits against the surface of the conical groove 308, the push rod 6 is coaxial with the loading chamber 300. During the process of the push rod 6 pressing against the loading chamber 300, it can ensure that the push rod 6 is coaxial with the loading chamber 300 and avoid misalignment. The push rod 6 is close to the loading chamber. A centering pin insertion hole 63 is provided on the end face of the front wall 302. The length direction of the centering pin insertion hole 63 is the same as the length direction of the push rod 6. Specifically, the centering pin insertion hole 63 is located at the center of the cross-section of the push rod 6 and is coaxial with the push rod 6. The column 611 can be inserted into the centering pin insertion hole 63 and can slide along the length direction of the centering pin insertion hole 63. A spring 64 is provided in the centering pin insertion hole 63. The centering pin 61 compresses the spring 64, and the spring 64 applies a spring force to the centering pin 61. Specifically, an annular notch 614 is formed by circumferential cutting the outer circumference of the column 611 near the spring 64. The annular notch 614 is not circumferential with the column 611. A stop 615 is formed at the boundary of the cut section. A spring 64 is sleeved on the annular notch 614 section of the column 611 and abuts against the stop 615. The spring 64 is coaxial with the column 611, making the elastic force applied by the spring 64 to the centering pin 61 more uniform. Of course, the annular notch 614 can be omitted, and the end face of the column 611 directly presses the spring 64. The spring 64 applies an elastic force to the centering pin 61 in the direction of the loading chamber 300, that is, pushes the centering pin 61 towards the loading chamber 300. An elongated hole 613 is opened on the column 611, and the direction of the elongated hole 613 is the same as the length direction of the column 611. The push rod 6 is provided with a through hole. A fixing pin 65 passes through an elongated hole 613. The elongated hole 613 can slide back and forth along the fixing pin 65. During installation, the column 611 is first placed into the centering pin insertion hole 63, and then the fixing pin 65 is inserted into the side wall of the centering pin insertion hole 63 and the elongated hole 613. During the process of the push rod 6 pressing against the loading chamber 300, the centering pin 61 is gradually squeezed into the centering pin insertion hole 63 until the end face of the push rod 6 abuts against the front wall 302 of the loading chamber. In order to make the end face of the push rod 6 fit against the front wall 302 of the loading chamber, the end face of the push rod 6 near the loading chamber 300 is arc-shaped and can fit against the outer surface of the front wall 302 of the loading chamber.

[0051] Reference Figure 1-7 12-14, 23-27, The end face of the sliding sleeve 7 near the loading chamber 300 has a push rod insertion hole 71, into which the push rod 6 can be inserted to achieve the insertion of the push rod 6 and the sliding sleeve 7. The end of the screw 9 near the loading chamber 300 has a fixed connector 91. The cross-section of the connector 91 is circular, and the cross-section refers to the plane perpendicular to the length direction of the screw 9. The end face of the sliding sleeve 7 has a screw insertion hole 72, into which the connector 91 can be inserted. Figure 23-25 As shown, the push rod insertion hole 71 and the screw insertion hole 72 are located on two opposite end faces of the sliding sleeve 7, and the push rod insertion hole 71 and the screw insertion hole 72 are not connected. The outer surface of the connector 91 is provided with a second arc-shaped groove 92 circumferentially, and the inner surface of the screw insertion hole 72 is provided with a first arc-shaped groove 74 circumferentially. The first arc-shaped groove 74 and the second arc-shaped groove 92 are correspondingly arranged. After the first arc-shaped groove 74 and the second arc-shaped groove 92 are joined, an annular channel is formed. The annular channel is filled with multiple spheres, specifically steel balls 93. When the screw 9 rotates, the connector 91 rotates synchronously, while the sliding sleeve 7 remains stationary. The sliding sleeve 7 and the connector 91 rotate relative to each other. The steel balls 93 reduce sliding resistance and also act as a transmission mechanism. When the screw 9 moves back and forth, the connector 91 moves synchronously. The connector 91, through the steel balls 93, drives the sliding sleeve 7 to move synchronously. When the sliding sleeve 7 moves away from the end support 2, the push rod 6 can be inserted into the push rod insertion hole 71 or disengaged from it. When the sliding sleeve 7 moves closer to the end support 2, it can push the push rod 6 to press the loading chamber 300 tightly. Because there are multiple steel balls 93 in the annular channel, at least a few steel balls 93 will press against the inner surface of the sliding sleeve 7, keeping the position of the sliding sleeve 7 stable during movement and preventing it from shifting. Figure 24-27 As shown, the sliding sleeve 7 has an internally threaded hole 73, which communicates with the annular channel. The steel ball 93 enters the annular channel through the internally threaded hole 73. A screw 75 is screwed onto the internally threaded hole 73 to prevent the steel ball 93 from coming out. The screw 75 can be a slotted flat-end set screw, which does not need to be tightened, allowing the steel ball 93 to rotate freely. Since the push rod 6 does not rotate during the tightening process while the screw 9 rotates, standard bearings cannot be used, hence this sliding sleeve 7 structure.

[0052] Reference Figure 7-14The support mechanism is installed on the base 1, on one side of the clamping component. The support mechanism includes a mounting base 14 connected to the base 1. An end bracket 13 is connected to the side of the mounting base 14 near the loading chamber 300. The end bracket 13 supports the open end of the head 100, so that the first external threaded connection part 103 is close to the receiving cylinder 200 for easy screwing with the receiving cylinder 200. The upper surface of the end bracket 13 is concave arc-shaped to prevent the head 100 from rolling sideways. To prevent the head 100 from tilting and sliding off the support mechanism, a positioning plate 12 is fixedly connected to the side of the end bracket 13 near the loading chamber 300. When the head 100 is placed on the support structure, the large end of the head 100, i.e., the end face of the first external threaded connection part 103, abuts against the positioning plate 12. The other side of the mounting base 14 is connected to... The V-shaped bracket 16 supports the small end of the head 100, specifically the head wire connection part 101. The V-shaped bracket 16 also prevents the head 100 from rolling sideways. The V-shaped bracket 16 is higher than the end bracket 13, causing the head 100 to tilt downwards from the small end to the large end. Specifically, the mounting base 14 is connected to the base 1 by a bolt. When the V-shaped bracket 16 and the end bracket 13 are at a suitable angle, the mounting base 14 is fixedly connected to the base 1 with bolts. Two parallel connecting rods 15 are connected to the mounting base 14, passing through it. One end of the connecting rod 15 is connected to the end bracket 13 and the positioning plate 12, and the other end is connected to the support block 17. The V-shaped bracket 16 is fixedly connected above the support block 17, making the support mechanism a single unit. During aircraft assembly, the head 100 is placed on the support mechanism and will not roll to the sides or slip off.

[0053] Instructions for use: Refer to... Figure 12-14 28, 29. Before screwing the nose cone 100, connector 200, and loading chamber 300 of the aircraft, connect both ends of the wire 400 to the head wire connection part 101 and the loading chamber wire connection part 303 respectively. The section of the wire 400 passing through the loading chamber 300 is laid in the wire groove 304, and the wire 400 passes through the inside of the connector 200, as shown in the figure. Figure 28As shown; place the three parts of the aircraft onto the tooling, and before placing the screw 9, tighten it so that the sliding sleeve 7 is as far away from the end support 2 as possible, providing space for the placement of the loading chamber 300 and the docking of the top rod 6 with the loading chamber 300; place the head 100 on the support mechanism, with the small end of the head 100 on the V-shaped bracket 16 and the large end on the end bracket 13, and make the end face of the first external thread connection part 103 abut against the positioning plate 12; place the small end of the loading chamber 300 on the end support 2 and the large end on the middle support 5, and make the outer end face of the loading chamber wire connection part 303 abut against the positioning boss 3, observe the recess 309, so that the slide groove 310 is connected with the limiting slide 31, then put the directional pin 4 into the limiting slide 31 and insert the insert block 41 into the slide groove 310 until the stop block 42 touches the At this point, the loading chamber 300 will no longer rotate. One end of the push rod 6, equipped with a centering pin 61, passes through the connecting sleeve 200 and abuts against the front wall 302 of the loading chamber, allowing the conical plug 612 of the centering pin 61 to insert into the conical groove 308 of the front wall 302 of the loading chamber, thus aligning the push rod 6 with the loading chamber 300. The end of the side rod 62 abuts against the base 1 to prevent the push rod 6 from rotating during the tightening process. The second external threaded connection 202 of the connecting sleeve 200 aligns with the second internal threaded connection 306 of the loading chamber 300, but the connecting sleeve 200 is not screwed on. The push rod 6 remains horizontal and aligned with the push rod insertion hole 71 of the sliding sleeve 7. The handle 11 is turned clockwise, causing the screw 9 to move closer to the loading chamber 300. As the screw 9 moves closer to the loading chamber 300, the push rod 6 inserts into the push rod insertion hole 71, as shown in the image. Figure 12 As shown, continue to turn the handle 11 clockwise. The screw 9 pushes the push rod 6 closer to the loading chamber 300. The centering pin 61 of the push rod 6 begins to apply pressure to the front wall 302 of the loading chamber. According to the action and reaction forces, the front wall 302 of the loading chamber applies the same magnitude of reaction force to the centering pin 61, pressing the centering pin 61 into the centering pin insertion hole 63. There is a spring 64 in the centering pin insertion hole 63. As the length of the compressed spring 64 gradually shortens, the pushing force of the spring 64 on the centering pin 61 gradually increases, and the pressing force of the centering pin 61 on the front wall 302 of the loading chamber gradually increases. When the end face of the push rod 6 is in contact with the outer surface of the front wall 302 of the loading chamber, the force of turning the screw 9 increases rapidly. At this time, stop turning the screw 9. The loading chamber 300 is pressed tightly by the push rod 6, as shown in the figure. Figure 13As shown, by setting the centering pin 61, the push rod 6 and the loading chamber 300 remain coaxial during the tightening process. The push rod 6 will not deviate from the correct position and cause misalignment, ensuring assembly quality. By setting the spring 64 in the centering pin insertion hole 63, the pressure of the push rod 6 on the front wall 302 of the loading chamber gradually increases instead of rapidly increasing. The push rod 6 is less likely to deviate due to rapid pressure increase, resulting in a better tightening effect. At the same time, it also protects the front wall 302 of the loading chamber, making it less prone to deformation. After the loading chamber 300 is tightened, rotate the connecting sleeve 200 to screw the connecting sleeve 200 onto the loading chamber 300. After the connecting sleeve 200 is screwed onto the loading chamber 300, turn the handle 11 counterclockwise, and the screw 9 moves away from the loading chamber 300. As the loading chamber 300 moves in the direction of movement, the push rod 6 retracts. The movement trajectory of the centering pin 61 and the force between the centering pin 61 and the front wall 302 of the loading chamber are opposite to those during the tightening process, and will not be described in detail here. When the push rod 6 retracts, it abuts against the connecting sleeve 200, and the front wall 302 of the loading chamber springs back, returning part of the tightening force to the connecting sleeve 200, achieving the effect of threaded tightening and improving assembly quality. When the sliding sleeve 7 retracts to a position away from the loading chamber 300, the push rod 6 is disengaged from the push rod insertion hole 71. Then, the push rod 6 is removed, and the head 100 is aligned with the connecting sleeve 200. The head 100 is rotated and screwed onto the connecting sleeve 200. The aircraft assembly is complete. The assembled aircraft is as follows: Figure 14 As shown, then remove the directional pin 4.

[0054] The aircraft assembly fixture of the present invention fixes the position of the loading chamber of the aircraft with a clamping assembly. When the connecting sleeve is screwed onto the loading chamber, the loading chamber will not rotate or move in other directions, thus avoiding the shearing of the wires caused by the rotation of the loading chamber. The directional pin of the clamping assembly is inserted into the slot on the side wall of the wire mounting part of the loading chamber. The limiting slide limits the directional pin to prevent the loading chamber from rotating during assembly. The centering structure at the end of the push rod cooperates with the groove on the front wall of the loading chamber to keep the push rod and the loading chamber coaxial during the clamping process, preventing the assembly quality from being affected by the top deviation. The screw and the push rod will rotate relative to each other during the clamping process. By setting a sliding sleeve, the sliding sleeve and the screw can rotate relative to each other, while pushing the push rod to clamp the loading chamber. The connection between the sliding sleeve and the screw is filled with steel balls, which can reduce the sliding resistance when the sliding sleeve and the connection rotate relative to each other.

Claims

1. An aircraft assembly fixture, characterized in that: The assembly includes a clamping component for clamping the loading chamber (300) of the aircraft during assembly. The clamping component includes a base (1), one end of which is provided with a fixed platform (8), and the other end of which is fixedly provided with an end support (2) for supporting the loading chamber wire connection part (303) at the end of the loading chamber (300) during assembly. The end support (2) is fixedly provided with a positioning boss (3) that abuts against the outer end face of the loading chamber wire connection part (303) during assembly and prevents the loading chamber (300) from moving away from the fixed platform (8). A screw (9) is threadedly connected to the fixed platform (8) and passes through the fixed platform (8). (9) A sliding sleeve (7) is connected to one end near the end support (2), which can rotate relative to the screw (9) and move synchronously with the screw (9). A push rod (6) is inserted into one end of the sliding sleeve (7) near the end support (2) for pressing the loading chamber (300) during assembly and can be disengaged from the sliding sleeve (7). The end of the push rod (6) near the loading chamber (300) is provided with a centering structure that makes the push rod (6) coaxial with the loading chamber (300) during assembly. The pressing assembly also includes a directional pin (4) that can pass through the positioning boss (3) and be inserted into the side wall of the loading chamber wire connection part (303) during assembly to prevent the loading chamber (300) from rotating.

2. The aircraft assembly fixture according to claim 1, characterized in that: The centering structure includes a centering pin (61) that rests on the center of the front wall (302) of the loading chamber during assembly. The centering pin (61) includes a column (611). The end face of the column (611) near the front wall (302) of the loading chamber is provided with an outwardly protruding plug that can be inserted into the groove at the center of the front wall (302) of the loading chamber.

3. The aircraft assembly fixture according to claim 2, characterized in that: The top rod (6) has a centering pin insertion hole (63) on its end face near the front wall (302) of the loading chamber. The length direction of the centering pin insertion hole (63) is the same as that of the top rod (6). The column (611) can be inserted into the centering pin insertion hole (63) and can slide along the length direction of the centering pin insertion hole (63). The centering pin insertion hole (63) is provided with a spring (64) that pushes the centering pin (61) toward the loading chamber (300). The column (611) has an elongated hole (613) with the same length direction as the column (611). The top rod (6) has a fixed pin (65) that passes through the elongated hole (613). The elongated hole (613) can slide along the fixed pin (65).

4. The aircraft assembly fixture according to claim 1, characterized in that: The upper surface of the positioning boss (3) is provided with a limiting slide (31) for limiting the sliding direction of the directional pin (4) and communicating with the slide groove (310) on the side wall of the loading chamber wire connection part (303).

5. The aircraft assembly fixture according to claim 4, characterized in that: The directional pin (4) includes a plug (41) that can be inserted into the slide groove (310). One end of the plug (41) is fixedly connected to a stop (42) whose size is larger than the cross-sectional size of the slide groove (310). When the plug (41) is inserted into the slide groove (310), the stop (42) is located in the limiting slide (31).

6. The aircraft assembly fixture according to claim 1, characterized in that: The sliding sleeve (7) has a push rod insertion hole (71) on the end face near the loading chamber (300).

7. The aircraft assembly fixture according to claim 6, characterized in that: The screw (9) has a fixed connector (91) at one end near the loading chamber (300). The sliding sleeve (7) has a screw insertion hole (72) into which the connector (91) can be inserted. The outer surface of the connector (91) has a second arc-shaped groove (92) circumferentially formed. The inner surface of the screw insertion hole (72) has a first arc-shaped groove (74) circumferentially formed corresponding to the second arc-shaped groove (92). The first arc-shaped groove (74) and the second arc-shaped groove (92) are joined to form an annular channel, and the annular channel is filled with multiple spheres.

8. The aircraft assembly fixture according to claim 1, characterized in that: The base (1) is also fixedly provided with a middle support platform (5) that supports the end of the loading chamber (300) away from the positioning boss (3). The middle support platform (5) is located between the fixed platform (8) and the end support platform (2).

9. The aircraft assembly fixture according to claim 1, characterized in that: A side rod (62) that abuts against the base (1) during assembly is fixedly connected to the surface of the top rod (6).

10. The aircraft assembly fixture according to claim 1, characterized in that: The base (1) is also provided with a support mechanism for supporting the head (100) of the aircraft during assembly. The support mechanism includes an end bracket (13) for supporting the open end of the head (100) and a V-shaped bracket (16) for supporting the head wire connection part (101). The end bracket (13) is connected to a positioning plate (12) to prevent the head (100) from tilting and sliding off the support mechanism.

Images