General-purpose bracket for bearing of fighter aircraft fuselage

Abstract

The utility model relates to the technical field of fuselage overhaul bracket, especially fighter fuselage bearing type general bracket, including staggered support mechanism, it includes stress base frame and two stress brackets of sliding setting in stress base frame upper end, the middle part of stress base frame is provided with the transverse staggered component for pushing two stress brackets staggered and will overhaul site leak, the both ends of stress base frame all are provided with the sliding guide assembly for guiding and limiting the stress bracket forward and backward movement, auxiliary support mechanism, it includes the arc embrace angle for the auxiliary support when the stress bracket forward movement cannot support the fuselage of too big angle of elevation, the outside of arc embrace angle is provided with lifting guide assembly, the lower end of arc embrace angle is provided with vertical lifting assembly. Solveed the problem that the prior art exists easy to shield the part to be overhauled and is difficult to combine with fuselage angle of elevation radian influence overhaul efficiency and support stability and operation safety hidden danger.

Description

Technical Field

[0001] This utility model relates to the field of fuselage maintenance bracket technology, and in particular to a universal fuselage bearing bracket for fighter jets. Background Technology

[0002] Existing fighter jet fuselage maintenance support brackets typically consist of a base frame, a load-bearing bracket, and basic support components. They are used to provide support during fuselage maintenance, and need to be compatible with the ground clearance of the lower part of the fuselage from 66cm to 1.06m, while meeting the load-bearing requirement of 9 tons. They achieve support and fixation of the fuselage through components such as anti-rollover clamps and load-bearing screws on the load-bearing bracket.

[0003] In practical use, this type of bracket can easily obscure the parts of the fuselage to be inspected after being fixed. It is necessary to repeatedly disassemble and adjust the position of the bracket to expose the inspection area, which is not only time-consuming and labor-intensive, but may also affect the stability of the support due to frequent movement. At the same time, the fighter jet fuselage has a certain angle of attack. When the load-bearing bracket is moved forward for adjustment, its support surface is difficult to fit with the arc of the fuselage angle of attack, which can easily create support gaps. Especially when the load is large, it may cause the fuselage to sway, which poses a safety hazard and seriously affects the efficiency of maintenance and operational safety. Utility Model Content

[0004] In view of the problems in the above or existing technologies that easily obstruct the parts to be inspected, are difficult to fit with the fuselage's elevation angle and curvature, affecting the inspection efficiency, lack of support stability, and operational safety hazards, this utility model is proposed.

[0005] To solve the above-mentioned technical problems, the present invention provides the following technical solution: a misaligned support mechanism, which includes a force-bearing base frame and two force-bearing brackets slidably disposed on the upper end of the force-bearing base frame. A transverse misalignment component for pushing the two force-bearing brackets to misalign front and back and exposing the maintenance part is provided in the middle of the force-bearing base frame. Sliding guide components for guiding and limiting the front and back movement of the force-bearing brackets are provided at both ends of the force-bearing base frame. The auxiliary support mechanism includes an arc-shaped bracket for providing auxiliary support to the fuselage that cannot support the excessive angle of elevation when the force-bearing bracket moves forward. A lifting guide component is provided on the outer side of the arc-shaped bracket to guide the arc-shaped bracket when it moves forward. A vertical lifting component is provided at the lower end of the arc-shaped bracket to provide longitudinal stable support for the fuselage.

[0006] As a preferred embodiment of the universal bearing bracket for fighter jet fuselage of this utility model, the transverse displacement assembly includes a fixed side plate fixedly installed at the front and rear ends of the force-bearing base frame. A protective box that is slidably connected to the lower end of the force-bearing bracket is fixedly installed in the middle of the fixed side plate. A transmission shaft is rotatably installed on one side of the inner cavity of the protective box. A worm gear is fixedly installed in the middle of the transmission shaft. A worm wheel is meshed on one side of the worm gear. The worm gear is used to drive the worm wheel to rotate in both directions.

[0007] As a preferred embodiment of the universal bearing bracket for fighter jet fuselage of this utility model, wherein: a gear is fixedly provided on the upper end of the worm gear, and racks are meshed on both sides of the gear and slidably connected to the upper side wall of the inner cavity of the fixed side plate; the toothless side of the rack is fixedly connected to the lower end of the two force-bearing brackets respectively.

[0008] As a preferred embodiment of the universal bearing bracket for fighter jet fuselage of this utility model, one end of the drive shaft is provided with a crank handle for rotating the drive shaft and thus realizing power transmission.

[0009] As a preferred embodiment of the universal bearing bracket for fighter jet fuselage of this utility model, the sliding guide assembly includes convex grooves formed at both ends of the force-bearing base frame. The inner cavity of the convex groove is slidably connected to the lower ends of the two force-bearing brackets. A limiting block is slidably disposed in the inner cavity of the convex groove and fixedly connected to the outer surface of the sliding end of the force-bearing bracket in the inner cavity of the convex groove. Several rollers are rotatably disposed in the inner cavity of the limiting block on the side away from the force-bearing bracket. The rollers are slidably connected to the inner cavity of the convex groove, thereby reducing the lateral sliding friction resistance of the force-bearing bracket.

[0010] As a preferred embodiment of the universal fuselage bearing bracket of this utility model, the lifting guide assembly includes a vertical fixing plate fixedly installed on the outer side of one end of the force-bearing base frame. The upper end of the vertical fixing plate is provided with an upwardly sloping arc-shaped lifting groove. The inner cavity of the arc-shaped lifting groove is slidably provided with a guide wheel that is rotatably connected to the arc-shaped bracket. The guide wheel is used to drive the arc-shaped bracket to move obliquely upward in the arc-shaped lifting groove and conform to the guide wheel of the fuselage elevation angle.

[0011] As a preferred embodiment of the universal bearing bracket for fighter jet fuselage of this utility model, the vertical lifting assembly includes a retractable rod fixedly disposed in the upper part of the force-bearing bracket. The inner cavity of the retractable rod is slidably provided with a lifting rod for vertical support of the lifting of the arc-shaped angle. The upper end of the lifting rod is rotatably provided with a fixed seat fixedly connected to the middle surface of the lower end of the arc-shaped angle. The fixed seat is used to rotate when the arc-shaped angle moves obliquely upward in an arc shape, so as to better fit the fuselage.

[0012] The beneficial effects of this utility model of a universal fuselage bearing bracket for fighter jets are as follows: 1. The two load-bearing brackets can be moved back and forth by the horizontal displacement misalignment component, which can expose the obscured parts to be inspected without repeatedly disassembling and assembling the brackets. This avoids the problem of reduced support stability caused by frequent bracket movement. At the same time, the convex groove, limit block and roller in the sliding guide component can greatly reduce the sliding friction resistance of the load-bearing brackets, making the misalignment adjustment smoother and less labor-intensive, significantly shortening the maintenance preparation time and reducing the safety risks caused by repeated operation.

[0013] 2. Utilizing the arc-shaped bracket in the auxiliary support mechanism in conjunction with the lifting guide component, it can move obliquely upward in an arc shape as the load-bearing bracket moves forward, precisely matching the arc angle of the machine body; the vertical lifting component, through vertical support and rotational adjustment, ensures that the arc-shaped bracket remains tightly fitted to the machine body during movement, eliminating support gaps and effectively solving the problem of unstable support when the machine body's angle of elevation is too large. Even under heavy loads, it can prevent the machine body from swaying, improving the safety and reliability of maintenance operations. Attached Figure Description

[0014] To more clearly illustrate the technical solutions of the embodiments of this utility model, the drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0015] Figure 1 This is a schematic diagram of the general-purpose bearing bracket for fighter jet fuselage.

[0016] Figure 2 This is a cross-sectional schematic diagram of the sliding guide assembly of the universal bearing bracket for fighter jet fuselage.

[0017] Figure 3 This is a schematic diagram showing the positions of the lifting guide assembly and the vertical lifting assembly of the universal bearing-type bracket for fighter jet fuselage.

[0018] Figure 4 This is a schematic diagram of the lateral displacement component of a universal bearing-type bracket for fighter jet fuselage.

[0019] Figure 5 This is an enlarged view of the lifting guide assembly and vertical lifting assembly of the universal bearing-type bracket for fighter jet fuselage.

[0020] In the diagram: 10. Load-bearing base frame; 11. Load-bearing bracket; 12. Lateral displacement assembly; 121. Fixed side plate; 122. Protective box; 123. Drive shaft; 124. Worm gear; 125. Worm wheel; 126. Gear; 127. Rack; 128. Handle; 13. Sliding guide assembly; 131. Convex groove; 132. Limiting block; 133. Roller; 20. Arc-shaped bracket; 21. Lifting guide assembly; 211. Vertical fixing plate; 212. Arc-shaped lifting groove; 213. Guide wheel; 22. Vertical lifting assembly; 221. Retracting rod; 222. Lifting rod; 223. Fixed seat. Detailed Implementation

[0021] To make the above-mentioned objectives, features and advantages of this utility model more apparent and understandable, the specific embodiments of this utility model will be described in detail below with reference to the accompanying drawings.

[0022] Example 1, referring to Figures 1-5 This is the first embodiment of the present utility model. This embodiment provides a universal bracket for the fuselage bearing of a fighter jet. It can achieve the effect of quickly performing maintenance by shifting the load-bearing bracket back and forth to make room for maintenance without repeated disassembly and repositioning of the load-bearing bracket. It includes a shifting support mechanism, which includes a load-bearing base frame 10 and two load-bearing brackets 11 slidably disposed on the upper end of the load-bearing base frame 10. A transverse shifting component 12 for pushing the two load-bearing brackets 11 back and forth to make room for maintenance is provided in the middle of the load-bearing base frame 10. The transverse displacement assembly 12 includes a fixed side plate 121 fixedly installed at the front and rear ends of the force-bearing base frame 10. A protective box 122 is fixedly installed in the middle of the fixed side plate 121 and slidably connected to the lower end of the force-bearing bracket 11. A drive shaft 123 is rotatably installed on one side of the inner cavity of the protective box 122. A worm gear 124 is fixedly installed in the middle of the drive shaft 123. A worm wheel 125 is meshed on one side of the worm gear 124. The worm gear 124 is used to drive the worm wheel 125 to rotate in both directions. A gear 126 is fixedly installed on the upper end of the worm wheel 125. A rack 127 is meshed on both sides of the gear 126 and slidably connected to the upper side wall of the inner cavity of the fixed side plate 121. The toothless side of the rack 127 is fixedly connected to the lower end of the two force-bearing brackets 11 respectively. A crank 128 is provided at one end of the drive shaft 123 to rotate the drive shaft 123 and thus realize power transmission.

[0023] Specifically, in this device, the worm gear 124 and worm wheel 125 can rotate in both directions, thereby driving the two force-bearing brackets 11 to move back and forth. The force-bearing brackets 11 are existing technologies, which include two anti-rollover corner brackets, two force-bearing channel steels, three fixing pins, four load-bearing screws, four sets of pressure bearings, and two crossbars that are slidably set in the protective box 122.

[0024] Furthermore, both ends of the load-bearing base frame 10 are provided with sliding guide components 13 for guiding and limiting the forward and backward movement of the load-bearing brackets 11. The sliding guide components 13 include convex grooves 131 formed at both ends of the load-bearing base frame 10. The inner cavity of the convex groove 131 is slidably connected to the lower ends of the two load-bearing brackets 11. A limiting block 132 is slidably arranged in the inner cavity of the convex groove 131 and is fixedly connected to the outer surface of the sliding end of the load-bearing bracket 11 in the inner cavity of the convex groove 131. Several rollers 133 are rotatably arranged in the inner cavity of the limiting block 132 on the side away from the load-bearing bracket 11. The rollers 133 are slidably connected to the inner cavity of the convex groove 131, thereby reducing the lateral sliding friction resistance of the load-bearing bracket 11.

[0025] The lower part of the crossbar at the lower end of the load-bearing base frame 10 and the lower end of the load-bearing bracket 11 is equipped with six casters, which can be used for aircraft with a fuselage height of 66cm to 1.06m above the ground and can bear a load of 9 tons. At the same time, several small ball bearings are set on the two anti-rollover corner arc surfaces in the load-bearing bracket 11, which can reduce friction when the load-bearing bracket 11 moves back and forth, making the load-bearing bracket 11 move more easily.

[0026] In use, the six casters at the bottom of the crossbar of the lower end of the load-bearing base frame 10 and the load-bearing bracket 11 are first used to move the entire bracket device to a suitable position under the fuselage of the fighter jet. The height of the load-bearing bracket 11 is adjusted by the existing load-bearing screw and pressure bearing of the load-bearing bracket 11 so that the anti-rollover angle on the load-bearing bracket 11 fits against the fuselage of the fighter jet. The small ball bearings on the arc surface of the anti-rollover angle can not only ensure stable support for the fuselage, but also reduce frictional resistance for the subsequent movement of the load-bearing bracket 11.

[0027] When it is necessary to inspect the part to be inspected that is blocked by the load-bearing bracket 11, the operator turns the handle 128 in the transverse displacement assembly 12. The handle 128 drives the transmission shaft 123 to rotate, and the worm 124 in the middle of the transmission shaft 123 rotates accordingly. Since the worm 124 and the worm wheel 125 mesh with each other, the rotation of the worm 124 will drive the worm wheel 125 to rotate in both directions, thereby causing the gear 126 fixed at the upper end of the worm wheel 125 to rotate synchronously.

[0028] Gear 126 has racks 127 meshing on both sides. The rotation of gear 126 will drive the racks 127 on both sides to slide in opposite directions on the upper side wall of the inner cavity of the fixed side plate 121. Since the toothless side of rack 127 is fixedly connected to the crossbar at the lower end of the two force-bearing brackets 11 respectively, the sliding of rack 127 will cause the two force-bearing brackets 11 to move back and forth on the force-bearing base frame 10.

[0029] During the back-and-forth movement of the two load-bearing brackets 11, the convex grooves 131 in the sliding guide components 13 at both ends of the load-bearing base frame 10 provide a sliding track for the load-bearing brackets 11. The limiting block 132 at the lower end of the load-bearing bracket 11 slides in the inner cavity of the convex groove 131. At the same time, several rollers 133 in the inner cavity of the limiting block 132 on the side away from the load-bearing bracket 11 are slidably connected to the inner cavity of the convex groove 131, which greatly reduces the lateral sliding friction resistance of the load-bearing brackets 11 and makes the movement of the load-bearing brackets 11 smoother and easier.

[0030] By misaligning the two load-bearing brackets 11, the parts to be inspected that were originally covered are exposed, forming an inspection area. Workers can then quickly carry out inspection operations in this area. After the inspection is completed, the crank handle 128 is turned in the opposite direction, and the two load-bearing brackets 11 are reset through the above transmission process, continuing to support the fighter jet fuselage.

[0031] Example 2, refer to Figures 1-5 This is the second embodiment of the present invention. Unlike the previous embodiment, this embodiment provides an auxiliary support mechanism for a universal bearing-type bracket for fighter jet fuselage. This solves the problem that the forward-moving force-bearing bracket cannot fully fit with the fuselage due to the fuselage's angle of attack. The auxiliary support mechanism includes an arc-shaped bracket 20 for assisting the support of the force-bearing bracket 11 when it cannot support the fuselage with an excessive angle of attack when it moves forward. A lifting guide assembly 21 is provided on the outer side of the arc-shaped bracket 20 to guide the arc-shaped bracket 20 when it moves forward. The lifting guide assembly 21 includes a vertical fixing plate 211 fixedly installed on the outer side of one end of the force-bearing base frame 10. An upward-sloping arc-shaped lifting groove 212 is opened at the upper end of the vertical fixing plate 211. A guide wheel 213 is slidably installed in the inner cavity of the arc-shaped lifting groove 212 and rotatedly connected to the arc-shaped bracket 20. The guide wheel 213 is used to drive the arc-shaped bracket 20 to move upward-slopingly in the arc-shaped lifting groove 212 and fit with the fuselage's angle of attack.

[0032] The lower end of the arc-shaped bracket 20 is provided with a vertical lifting assembly 22 for providing longitudinal stability support for the arc-shaped bracket 20 to the fuselage. The vertical lifting assembly 22 includes a retractable rod 221 fixedly installed in the upper part of the force-bearing bracket 11. The inner cavity of the retractable rod 221 is slidably provided with a lifting rod 222 for vertical support of the arc-shaped bracket 20. The upper end of the lifting rod 222 is rotatably provided with a fixing seat 223 fixedly connected to the middle surface of the lower end of the arc-shaped bracket 20. The fixing seat 223 is used to rotate when the arc-shaped bracket 20 moves obliquely upward in an arc shape, so as to fit more closely to the fuselage.

[0033] Specifically, the cooperation between the guide wheel 213 and the arc-shaped lifting groove 212 allows the arc-shaped bracket 20 to gradually fit into the fuselage as it moves with the force-bearing bracket 11. The upper end of the arc-shaped bracket 20 is set to a compressible form, so that the arc-shaped bracket 20 can fit into the fuselage better. At the same time, the vertical lifting component 22 allows the arc-shaped bracket 20 to rotate due to friction when it fits into the fuselage during movement, thus better fitting the fuselage's tilt angle curvature.

[0034] In use, when the fighter jet's fuselage angle of attack is large, causing the load-bearing bracket 11 to not fully conform to the fuselage after moving forward, the forward movement of the load-bearing bracket 11 will cause the vertical lifting assembly 22 to move forward synchronously. The retractable rod 221 in the vertical lifting assembly 22 is fixed to the upper part of the load-bearing bracket 11, and therefore moves forward with the load-bearing bracket 11. The lifting rod 222, which is slidably disposed in the inner cavity of the retractable rod 221, and the fixed seat 223, which is rotatably disposed at the upper end of the lifting rod 222, will also move forward accordingly. Since the fixed base 223 is fixedly connected to the lower middle surface of the arc-shaped bracket 20, the arc-shaped bracket 20 will move forward under the action of the force-bearing bracket 11. At this time, the guide wheel 213 on the outer side of the arc-shaped bracket 20 slides in the arc-shaped lifting groove 212 on the vertical fixed plate 211. The arc-shaped lifting groove 212 is an upward arc, and when the guide wheel 213 slides in it, it will guide the arc-shaped bracket 20 to move in an upward arc.

[0035] As the support bracket 11 continues to move forward, the arc-shaped bracket 20 gradually approaches the fuselage elevation angle direction under the action of the guide wheel 213 and the arc-shaped lifting groove 212, and finally fits into the fuselage elevation angle portion. During this process, the vertical lifting assembly 22 not only provides vertical support for the arc-shaped bracket 20, but also allows the arc-shaped bracket 20 to rotate around the fixed base 223 due to friction when it fits into the fuselage. The rotation of the arc-shaped clamp 20 allows it to better adapt to the curvature of the fuselage's elevation angle, further improving the fit. At the same time, since the upper end of the arc-shaped clamp 20 is designed to be compressible, it can be compressed and deformed to a certain extent according to the actual contact situation when it comes into contact with the fuselage, thereby fitting the fuselage surface more tightly.

[0036] When the maintenance work is completed and the load-bearing bracket 11 moves backward to reset, the arc-shaped bracket 20, guided by the guide wheel 213 and the arc-shaped lifting groove 212, moves diagonally downward along the opposite path, gradually detaching from the fuselage and returning to the initial position along with the load-bearing bracket 11.

[0037] In this way, the auxiliary support mechanism effectively solves the problem that the forward-moving force-bearing bracket 11 cannot fully fit with the fuselage due to the fuselage pitch angle curvature, ensuring that the fighter jet can be stably supported under various fuselage pitch angle conditions, and providing reliable protection for maintenance work.

[0038] It should be noted that the above embodiments are only used to illustrate the technical solution of this utility model and are not intended to limit it. Although this utility model has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions can be made to the technical solution of this utility model without departing from the spirit and scope of the technical solution of this utility model, and all such modifications or substitutions should be covered within the scope of the claims of this utility model.

Claims

1. A universal bearing-type bracket for fighter jet fuselage, characterized in that: include, The misalignment support mechanism includes a force-bearing base frame (10) and two force-bearing brackets (11) slidably disposed on the upper end of the force-bearing base frame (10). A transverse misalignment component (12) for pushing the two force-bearing brackets (11) to misalign back and forth and exposing the maintenance part is provided in the middle of the force-bearing base frame (10). Sliding guide components (13) for guiding and limiting the back and forth movement of the force-bearing brackets (11) are provided at both ends of the force-bearing base frame (10). The auxiliary support mechanism includes an arc-shaped bracket (20) for providing auxiliary support when the force-bearing bracket (11) cannot support the fuselage with an excessively large elevation angle when it moves forward. The outer side of the arc-shaped bracket (20) is provided with a lifting guide assembly (21) for guiding the arc-shaped bracket (20) when it moves forward. The lower end of the arc-shaped bracket (20) is provided with a vertical lifting assembly (22) for providing longitudinal stable support for the fuselage by the arc-shaped bracket (20).

2. The universal fuselage bearing bracket for fighter jets as described in claim 1, characterized in that: The transverse displacement assembly (12) includes a fixed side plate (121) fixedly installed at the front and rear ends of the force-bearing base frame (10). A protective box (122) is fixedly installed in the middle of the fixed side plate (121) and slidably connected to the lower end of the force-bearing bracket (11). A transmission shaft (123) is rotatably installed on one side of the inner cavity of the protective box (122). A worm (124) is fixedly installed in the middle of the transmission shaft (123). A worm wheel (125) is meshed on one side of the worm (124). The worm (124) is used to drive the worm wheel (125) to rotate in both directions.

3. The universal fuselage bearing bracket for fighter jets as described in claim 2, characterized in that: The worm gear (125) is fixedly provided with a gear (126) on its upper end. Both sides of the gear (126) are meshed with racks (127) that are slidably connected to the upper side wall of the inner cavity of the fixed side plate (121). The toothless side of the rack (127) is fixedly connected to the lower end of the two force-bearing brackets (11).

4. The universal fuselage bearing bracket for fighter jets as described in claim 2, characterized in that: One end of the drive shaft (123) is provided with a crank (128) for rotating the drive shaft (123) to achieve power transmission.

5. The universal fuselage bearing bracket for fighter jets as described in claim 1, characterized in that: The sliding guide assembly (13) includes convex grooves (131) formed at both ends of the force-bearing base frame (10). The inner cavity of the convex groove (131) is slidably connected to the lower ends of the two force-bearing brackets (11). A limiting block (132) is slidably arranged in the inner cavity of the convex groove (131) and fixedly connected to the outer surface of the sliding end of the force-bearing bracket (11) in the inner cavity of the convex groove (131). Several rollers (133) are rotatably arranged in the inner cavity of the limiting block (132) on the side away from the force-bearing bracket (11). The rollers (133) are slidably connected to the inner cavity of the convex groove (131) to reduce the lateral sliding friction resistance of the force-bearing bracket (11).

6. The universal fuselage bearing bracket for fighter jets as described in claim 1, characterized in that: The lifting guide assembly (21) includes a vertical fixing plate (211) fixedly installed on the outer side of one end of the force-bearing base frame (10). The upper end of the vertical fixing plate (211) is provided with an upwardly curved lifting groove (212). The inner cavity of the curved lifting groove (212) is slidably provided with a guide wheel (213) that is rotatably connected to the curved angle bracket (20). The guide wheel (213) is used to drive the curved angle bracket (20) to move obliquely upward in the curved lifting groove (212) and fit the guide wheel (213) of the fuselage elevation angle.

7. The universal fuselage bearing bracket for fighter jets as described in claim 1, characterized in that: The vertical lifting assembly (22) includes a retractable rod (221) fixedly installed in the upper part of the force-bearing bracket (11). The retractable rod (221) has a sliding lifting rod (222) for vertical support of the lifting of the arc-shaped bracket (20). The upper end of the lifting rod (222) is rotatably provided with a fixed seat (223) fixedly connected to the middle surface of the lower end of the arc-shaped bracket (20). The fixed seat (223) is used to rotate when the arc-shaped bracket (20) moves obliquely upward in an arc shape, so as to fit the body more closely.

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