Front landing gear rotation shaft support positioning tool

Abstract

The utility model discloses a front landing gear rotating shaft support positioning tool belongs to the field of aviation equipment technology, and positioning core axle makes external thread is constituted by the positioning assembly of positioning axle sleeve, locating ring and locating nut, and two groups are arranged, and symmetrically sets up on the positioning core axle, and inserts the support joint of both sides in the positioning core axle, and utilizes positioning assembly respectively and clamps two support joints, and loosens the locating nut of one side but the position of positioning axle sleeve is immovable, and the side support joint is decomposed and utilizes positioning axle sleeve to determine the new support joint position, and tightens the locating nut after installation is completed, and utilizes the same method to change another side support joint, guarantees that both sides support joint is concentric coaxial, guarantees the accuracy and stability of the assembly position in the cabin of the airplane front landing gear.

Description

Technical Field

[0001] This utility model belongs to the field of aviation equipment technology and relates to a positioning tool for a nose landing gear pivot support. Background Technology

[0002] The nose landing gear is crucial for safe and reliable takeoff and landing, and the precise positioning of the nose landing gear pivot bearing is a key technology. Currently, the nose landing gear bay has separate openings at both ends. When replacing the nose landing gear pivot bearing on a certain aircraft model, the replacement process involves two additional degrees of freedom in positioning compared to other aircraft models. However, using the existing positioning fixtures for the pivot bearing joint installation easily leads to cracks at the ribs. These cracks are caused by the lack of concentric and coaxial precise positioning and assembly of the nose landing gear bay inner sidewall panel bearing joints. Therefore, the existing positioning fixtures are unsuitable for this aircraft model and require redesign and further optimization. Furthermore, the design must fully consider whether it can meet the positioning accuracy requirements of each degree of freedom. Utility Model Content

[0003] In view of this, the present invention provides a positioning fixture for the nose landing gear pivot support, which can ensure the accuracy and stability of the assembly position inside the aircraft nose landing gear bay.

[0004] The present invention adopts the following technical solution:

[0005] A positioning fixture for a front landing gear pivot support includes a positioning pin 1, a positioning bushing 2, a positioning ring 3, a positioning nut 4, a positioning mandrel 5, and a steel cable 6.

[0006] The positioning mandrel 5 is a long rod with external threads. Its length must be sufficient to allow both ends to be inserted into the support joints of the left and right side panels inside the front landing gear bay. One end of the positioning mandrel 5 has a positioning pin hole for inserting the positioning pin 1 to prevent the positioning mandrel 5 from falling out of the support joint. The other end has a steel cable hole, and a steel cable 6 is connected between the steel cable hole and the positioning pin 1 to prevent the positioning pin 1 from being lost.

[0007] The positioning bushing 2, positioning ring 3, and positioning nut 4 constitute a positioning assembly. Two sets of the positioning assembly are arranged opposite each other at both ends of the positioning mandrel 5. The positioning bushing 2 is a hollow cylindrical structure, its outer diameter set according to the inner hole of the support joint. Its inner hole is threaded to engage with the positioning mandrel 5 to adjust its position on the positioning mandrel 5. A boss is symmetrically formed on the outer circumference of one end near the end of the positioning mandrel 5. This end passes through the support joint of the inner wall panel of the front landing gear bay and rotates to make the end face of the boss fit against the inner side of the support joint. External threads are formed from the middle of the positioning bushing 2 to the other end for engagement with the positioning nut. The positioning nut 4 has an internal thread for threaded engagement with the positioning sleeve 2. The end face of the positioning nut 4 engages with the boss of the positioning sleeve 2 to clamp the support joint. The end face of the positioning nut 4 that fits against the support joint is recessed to reduce weight and avoid interference. The outer wall of the positioning nut 4 has multiple blind holes for assisting in turning the positioning nut 4 with the help of a force-applying tool. The two sets of positioning components engage with the same positioning spindle 5. The positions of the positioning components on the positioning spindle 5 ensure that the replacement of the support joints on both sides is concentric and coaxial. A positioning ring 3 is provided between the positioning nut 4 and the support joint.

[0008] The positioning pin 1 includes a baffle 7, a pin shaft 8, a pin rod 9, and a ring 10. The main body of the positioning pin 1 is the pin rod 9, with a groove on one end face for inserting the baffle 7. The pin rod 9 and the baffle 7 are rotatably connected by the pin shaft 8, so that the baffle 7 can be in two states: overlapping with the pin rod 9 and perpendicular to it. The other end of the pin rod 9 is equipped with a ring 10, which is used to connect the steel cable 6. In use, the baffle 7 is moved to overlap with the pin rod 9 and then inserted into the positioning pin hole on the positioning mandrel 5. Then, the baffle 7 is moved to be perpendicular to the pin rod 9 to prevent the positioning pin 1 from falling off.

[0009] The beneficial effects of this utility model are as follows: This utility model uses a positioning mandrel to replace the aircraft's nose landing gear, which is installed in the aircraft landing gear bay during the replacement of the support joint. This ensures that the positioning component at one end is fixed and completes the assembly of the support joint at the other end. After the assembly of this side is completed, the other side is assembled in the same way. This assembly and positioning method can ensure the accuracy and stability of the assembly position in the aircraft's nose landing gear bay. Attached Figure Description

[0010] Figure 1 This is a three-dimensional schematic diagram of the assembly of this utility model;

[0011] Figure 2 This is a schematic diagram of the assembly of this utility model;

[0012] Figure 3 This is a schematic diagram of the positioning pin of this utility model;

[0013] Figure 4 This is a schematic diagram of the positioning bushing of this utility model, wherein (a) is a sectional view and (b) is a view from direction A;

[0014] Figure 5 This is a schematic diagram of the positioning nut of this utility model;

[0015] Figure 6 This is a schematic diagram of the positioning mandrel of this utility model.

[0016] Among them, 1-locating pin; 2-locating bushing; 3-locating ring; 4-locating nut; 5-locating mandrel; 6-steel cable; 7-baffle; 8-pin; 9-pin rod; 10-circular ring. Detailed Implementation

[0017] To make the objectives, technical solutions, and advantages of this utility model clearer, the specific embodiments of this utility model will be described in detail below.

[0018] A positioning fixture for a front landing gear pivot support, such as Figure 1 and Figure 2 As shown, it includes a positioning pin 1, a positioning bushing 2, a positioning ring 3, a positioning nut 4, a positioning mandrel 5, and a steel cable 6.

[0019] like Figure 6 As shown, the positioning mandrel 5 is a long rod with external threads, 570mm in length, which can ensure that both ends of it can be inserted into the support joints of the left and right side panels inside the front landing gear bay at the same time. One end of the positioning mandrel 5 has a positioning pin hole for inserting the positioning pin 1 to prevent the positioning mandrel 5 from falling out of the support joint. The other end has a steel cable hole, and a steel cable 6 is connected between the steel cable hole and the positioning pin 1 to prevent the positioning pin 1 from being lost.

[0020] The positioning bushing 2, positioning ring 3, and positioning nut 4 constitute a positioning assembly. Two sets of the positioning assembly are provided, positioned opposite each other at both ends of the positioning mandrel 5; as follows... Figure 4 As shown, the positioning bushing 2 is a hollow cylindrical structure. Its outer diameter is set according to the inner hole of the support joint. The inner hole is threaded to engage with the positioning mandrel 5 to adjust its position on the positioning mandrel 5. A boss is symmetrically formed on the outer circumference of one end near the end of the positioning mandrel 5. This end passes through the support joint of the inner wall panel of the front landing gear bay and rotates to make the end face of the boss fit against the inner side of the support joint. External threads are formed from the middle to the other end of the positioning bushing 2 for threaded engagement with the positioning nut 4. Figure 5 As shown, the positioning nut 4 has an internal thread for threaded engagement with the positioning sleeve 2. The end face of the positioning nut 4 engages with the boss of the positioning sleeve 2 to clamp the support joint. The end face of the positioning nut 4 that fits against the support joint is recessed to reduce weight and avoid interference. The outer wall of the positioning nut 4 has multiple blind holes for assisting in turning the positioning nut 4 with the help of a force-applying tool. The two sets of positioning components engage with the same positioning spindle 5. The positions of the positioning components on the positioning spindle 5 ensure that the replacement of the support joints on both sides is concentric and coaxial. A positioning ring 3 is provided between the positioning nut 4 and the support joint.

[0021] like Figure 3 As shown, the positioning pin 1 includes a baffle 7, a pin shaft 8, a pin rod 9, and a ring 10. The main body of the positioning pin 1 is the pin rod 9, with a groove on one end face for inserting the baffle 7. The pin rod 9 and the baffle 7 are rotatably connected by the pin shaft 8, so that the baffle 7 can be in two states: overlapping with the pin rod 9 and perpendicular to it. The other end of the pin rod 9 is equipped with a ring 10, which is used to connect the steel cable 6. In use, the baffle 7 is moved to overlap with the pin rod 9 and then inserted into the positioning pin hole on the positioning mandrel 5. Then the baffle 7 is moved to be perpendicular to the pin rod 9 to prevent the positioning pin 1 from falling off.

[0022] The usage process is as follows:

[0023] First, insert both ends of the positioning mandrel 5, which is fitted with two sets of positioning components, into the holes in the left and right side panels inside the front landing gear bay, and insert the positioning pins 1 to prevent the positioning mandrel 5 from falling off. Insert the boss ends of the two positioning bushings 2 into the support joints on the two side panels respectively, rotate the positioning bushings 2 until the boss end face is in contact with the inside of the support joint, and tighten the two positioning nuts 4 respectively until the support joints on both sides are clamped. Loosen the positioning nut 4 on one side, but keep the positioning bushing 2 on that side stationary, disassemble the support joint on that side, and determine the installation position of the new support joint according to the positioning bushing 2. Since the positioning components on the other side have not moved, it can be ensured that the axis of the new support joint is consistent with the original support joint, that is, the radial position has not changed. Furthermore, since the position of the positioning bushing 2 on that side has not changed, it can be ensured that the axial position of the new support joint is consistent with the original support joint. After the new support joint on that side is installed, tighten the positioning nut 4 on that side to fix the position of the positioning components on that side. Loosen the positioning nut 4 on the other side and replace the support joint on the other side in the same way.

[0024] In summary, the above are merely preferred embodiments of this utility model and are not intended to limit the scope of protection of this utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this utility model should be included within the scope of protection of this utility model.

Claims

1. A positioning fixture for a front landing gear shaft support, characterized in that, Includes positioning bushing (2), positioning nut (4), and positioning mandrel (5); The positioning mandrel (5) is a long rod with external threads, and its length must be sufficient to allow both ends to be inserted into the support joints of the left and right side panels inside the front landing gear bay at the same time. The positioning bushing (2) and positioning nut (4) constitute a positioning assembly. There are two sets of positioning assemblies, which are arranged opposite to each other at both ends of the positioning mandrel (5). The positioning bushing (2) is a hollow cylindrical structure. Its outer diameter is set according to the inner hole of the support joint. The inner hole is threaded and threaded with the positioning mandrel (5) to adjust its position on the positioning mandrel (5). A boss is symmetrically made on the outer periphery of one end near the end of the positioning mandrel (5). After this end passes through the support joint of the inner wall of the front landing gear bay, it rotates so that the end face of the boss fits against the inner side of the support joint. The middle part of the positioning bushing (2) to the other end is threaded for threaded engagement with the positioning nut (4). The positioning nut (4) is threaded for threaded engagement with the positioning bushing (2). The end face of the positioning nut (4) engages with the boss of the positioning bushing (2) to clamp the support joint, which is used to achieve concentricity and coaxiality when replacing the support joints on both sides.

2. The positioning fixture for the front landing gear shaft support according to claim 1, characterized in that, A positioning ring (3) is provided between the positioning nut (4) and the support joint.

3. A positioning fixture for a front landing gear shaft support according to claim 1 or 2, characterized in that, The positioning nut (4) is recessed at one end of the support joint to reduce weight and avoid interference.

4. A positioning fixture for a front landing gear shaft support according to claim 1 or 2, characterized in that, The outer wall of the positioning nut (4) has multiple blind holes for use with the help of a force-applying tool to turn the positioning nut (4).

5. The positioning fixture for the front landing gear shaft support according to claim 1, characterized in that, The positioning mandrel (5) has a positioning pin hole at one end for inserting a positioning pin (1) to prevent the positioning mandrel (5) from falling out of the support joint.

6. The positioning fixture for the front landing gear shaft support according to claim 5, characterized in that, The positioning pin (1) includes a baffle (7), a pin shaft (8), and a pin rod (9). The main body of the positioning pin (1) is the pin rod (9), with a groove on one end face for inserting the baffle (7). The pin rod (9) and the baffle (7) are rotatably connected by the pin shaft (8), so that the baffle (7) has two states: overlapping with the pin rod (9) and perpendicular to it. After the baffle (7) is moved to overlap with the pin rod (9), it is inserted into the positioning pin hole on the positioning mandrel (5). Then the baffle (7) is moved to be perpendicular to the pin rod (9) to prevent it from falling off.

7. A positioning fixture for a nose landing gear shaft support according to claim 5, characterized in that, The other end of the positioning mandrel (5) is provided with a cable hole, and a cable (6) is connected between the cable hole and the positioning pin (1) to prevent the positioning pin (1) from being lost.

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