Aircraft tail rod machining fixing seat

Abstract

The utility model discloses an aircraft tail rod machining fixing seat which comprises a base, a clamping mechanism is arranged on the base, the clamping mechanism comprises a supporting frame, two sets of hinged frames, an air cylinder, a connecting piece and a clamping block, the supporting frame is installed on the base, the hinged frames are oppositely arranged and rotatably installed at the two ends of the supporting frame, and the air cylinder is installed on the clamping block. The two ends of the air cylinder are rotationally connected with the bottom ends of the two hinge frames correspondingly, the connecting piece is installed at the top ends of the two hinge frames, the clamping block is installed on the connecting piece through the quick assembly mechanism, and the quick assembly mechanism comprises an outer sleeve, a clamping block, a push spring, an insertion rod, a clamping groove and a quick disassembly mechanism. The technical problems that in the background technology, an integrated fixing design lacks necessary flexibility and cannot adapt to fixing of tail rods of different sizes and specifications are solved.

Description

TECHNICAL FIELD

[0001] The utility model relates to the field of aerospace technology more particularly, it relates to a kind of aircraft tail rod processing fixed seat. BACKGROUND

[0002] In the field of aerospace, the design and maintenance of aircraft are extremely high in accuracy and flexibility, especially the processing and installation link of aircraft tail rod, as an important part of aircraft control system, the accurate fixing of tail rod has a direct impact on the stability and safety of aircraft, however, according to prior art, aircraft tail rod processing fixed seat often adopts fixed integrated design scheme, this design can provide stable fixing effect in some cases, but there are obvious limitations in practical application, first, fixed integrated design is not convenient for the quick disassembly and installation of clamping block, in the processing of aircraft tail rod, different specifications of tail rod need to be processed and fixed, integrated design makes this process cumbersome and time-consuming, greatly reduces the maintenance efficiency, for the research and development environment that needs to quickly replace tail rod to experiment different flight configurations, this design is obviously unreasonable;

[0003] On the other hand, the existing integrated design scheme cannot meet the fixing needs of tail rods of different specifications, with the continuous progress of aviation technology, different types of aircraft have different requirements for the specifications and performance of tail rods, integrated fixed design lacks necessary flexibility, cannot adapt to the fixation of tail rods of different sizes and specifications, limits the diversity and adaptability of aircraft design, especially when facing complex and changeable flight tasks, the limitation of this design is more of a bottleneck to improve the performance and function of aircraft, therefore, in order to adapt to the rapid development of aerospace technology, finding a new fixed seat design scheme that can be quickly disassembled and installed and can adapt to tail rods of various specifications has become an urgent problem to be solved in the industry. CONTENT OF UTILITY MODEL

[0004] (I) technical problem solved

[0005] In view of the problems in the prior art, the utility model provides an aircraft tail rod processing fixed seat to solve the technical problem that the integrated fixed design lacks necessary flexibility and cannot adapt to the fixation of tail rods of different sizes and specifications mentioned in the background art.

[0006] (II) technical scheme

[0007] To achieve the above object, the utility model provides following technical scheme: a kind of aircraft tail rod processing fixed seat, including base, clamping mechanism is arranged on the base, the clamping mechanism includes support frame, hinged frame, cylinder, connecting piece and clamping block, the support frame is installed on base, the hinged frame is provided with two groups of opposite settings and is rotatably installed at support frame two ends, the cylinder two ends are rotatably connected two groups hinged frame bottom end, the connecting piece is installed at two groups hinged frame top end, the clamping block is installed on connecting piece by being provided with quick -mounting mechanism, the quick -mounting mechanism includes outer sleeve, clamping block, push spring, plug rod, clamping groove and quick -release mechanism, the outer sleeve is installed at connecting piece top end, the clamping block is provided with multiple groups and is arranged in outer sleeve, the push spring is installed at multiple groups clamping block outside, the plug rod is installed in clamping block side wall, the clamping groove is provided with multiple groups and is distributed in plug rod outer wall.

[0008] The utility model further sets up, multiple group clamping block inboard are equipped with soft pad, can protect the surface of the clamped object, avoid scratching or other damage, especially suitable for the article of surface relatively smooth or easy to damage.

[0009] The utility model further sets up, multiple group clamping block outside is equipped with positioning rod, the positioning rod is provided with multiple groups, positioning hole is seted up on the connecting piece, the positioning hole is provided with multiple groups and is matched with multiple group positioning rod, so that the assembly of whole mechanism is more accurate, guarantees the structural stability and working accuracy of device, especially in the occasion that high-precision positioning is required.

[0010] The utility model further sets up, the top surface in the outer sleeve is equipped with compression spring, the bottom end of compression spring is equipped with top ring, provides power support for the reset or adjustment of mechanism when required, enhances the use flexibility of device.

[0011] The utility model further sets up, the top surface of the outer sleeve is equipped with limit block, the top end of plug rod is equipped with limit slot, the limit block and limit slot are all provided with polygon and are matched, this design effectively prevents the deviation or rotation of component during movement, ensures the accuracy and reliability of mechanical operation, is especially important for mechanical system that needs to be accurately controlled.

[0012] The utility model further sets up, multiple group push spring outer end is equipped with limit sleeve, multiple group limit sleeve is fixedly connected outer sleeve inner wall, multiple group limit sleeve is all equipped with limit slot, multiple group clamping block outside is equipped with limit block, multiple group limit block is slidably connected with multiple group limit slot respectively, improve the ability of device to adapt to different working conditions, also make the adjustment of device more flexible and efficient.

[0013] The utility model further sets up, quick detach mechanism includes unlocking sleeve, unlocking block, block and thread cover, unlocking sleeve sliding installation is in outside cover bottom end, unlocking block is provided with multiple groups and installs in unlocking sleeve bottom surface, block installation is in multiple group the top surface of the clamping block, thread cover rotation installation is in outside cover top surface with unlocking sleeve outer wall screw connection.

[0014] The utility model further sets up, the sliding groove is seted up in the outer wall of the plug rod, the sliding groove is provided with multiple groups and is connected with multiple unlocking block sliding, is applicable to the application scene that needs to frequently change or adjust position, has improved the convenience and efficiency of operation greatly.

[0015] (Three) beneficial effects

[0016] Compared with the prior art, the utility model provides a kind of aircraft tail rod processing fixed seat, with following beneficial effects:

[0017] 1, clamping mechanism is designed by support frame, hinged frame, cylinder, connecting piece and clamping block, realizes the stable clamping of aircraft tail rod, support frame provides solid foundation for the whole mechanism, the design of hinged frame makes clamping mechanism can adapt to tail rod of different sizes, the use of cylinder provides power support for clamping mechanism, makes clamping action more stable and reliable, connecting piece is the core of the connection of each part, ensure the cooperative work of whole clamping mechanism, and clamping block is realized by the cooperation with connecting piece, the direct fixation of tail rod, and the soft pad installed in the inside protects tail rod surface not to be damaged.

[0018] 2, quick installation mechanism is designed by outside cover, clamping block, push spring, plug rod, clamping groove and quick detach mechanism, provides a kind of quick and stable clamping block installation mode, outside cover is as the peripheral structure of quick installation mechanism, provides support and protection for internal component, the design of clamping block makes clamping block can be quickly installed in specified position, push spring provides elastic support for clamping block, ensures the stability and reliability of installation, the design of plug rod and clamping groove ensures that clamping block can be accurately assembled in place, and the cooperation of limiting block and limiting groove further improves the precision and stability of assembly.

[0019] 3, quick detach mechanism is designed by unlocking sleeve, unlocking block, block and thread cover, provides a kind of quick, convenient clamping block dismounting mode for user, the sliding design of unlocking sleeve makes it can be realized by simple rotating operation to unlock, and the interaction of unlocking block and block ensures that clamping block can be easily pushed, to realize quick unlocking, the use of thread cover not only provides the adjusting means of unlocking force, also increases the controllability and safety of whole dismounting process, so that user can quickly replace corresponding specification clamping block according to tail rod of different specifications. DRAWINGS

[0020] Figure 1It is the whole structure schematic view of the aircraft tail rod machining fixing seat in the utility model.

[0021] Figure 2 It is the structure schematic view of the clamping block dismounting state in the utility model.

[0022] Figure 3 It is the sectional structure schematic view of the quick mounting mechanism in the utility model.

[0023] Figure 4 It is the sectional structure schematic view of the limiting sleeve in the utility model.

[0024] Figure 5 It is the structure schematic view of the quick dismounting mechanism in the utility model.

[0025] In the drawing: 1, base; 2, support frame; 3, hinged frame; 4, air cylinder; 5, connecting piece; 6, clamping block; 7, external sleeve; 8, clamping block; 9, push spring; 10, insertion rod; 11, clamping groove; 12, soft pad; 13, positioning rod; 14, positioning hole; 15, compression spring; 16, top ring; 17, limiting block; 18, limiting groove; 19, limiting sleeve; 20, limiting groove; 21, limiting block; 22, unlocking sleeve; 23, unlocking block; 24, abutting block; 25, threaded sleeve; 26, sliding groove. DETAILED DESCRIPTION

[0026] It should be noted that the embodiments in the present application and the features in the embodiments can be combined with each other without conflict. The present application will be described in detail below with reference to the drawings and in combination with embodiments.

[0027] It should be noted that, unless otherwise specified, all technical and scientific terms used in the present application have the same meaning as generally understood by those skilled in the art to which the present application belongs.

[0028] In the present application, unless otherwise specified, the directions used such as "up, down" are generally with respect to the directions shown in the drawings, or with respect to the vertical, perpendicular or gravity directions; similarly, for the convenience of understanding and description, "left, right" are generally with respect to the left and right shown in the drawings; "inner, outer" refer to the inner and outer with respect to the contour of each component itself, but the above directional words are not used to limit the present application.

[0029] Please refer to Figures 1-5The utility model provides a kind of aircraft tail rod processing fixed seat, including base 1, clamping mechanism is provided on base 1, clamping mechanism includes support frame 2, hinged frame 3, cylinder 4, connecting piece 5 and clamping block 6, support frame 2 is installed on base 1, hinged frame 3 is provided with two groups of opposite settings and is rotatably installed at support frame 2 two ends, cylinder 4 two ends are rotatably connected two groups of hinged frame 3 bottom end, connecting piece 5 is installed at the top end of two groups of hinged frame 3, clamping block 6 is installed on connecting piece 5 by being provided with quick -mounting mechanism, quick -mounting mechanism includes external sleeve 7, clamping block 8, push spring 9, plug rod 10, clamping groove 11 and quick -release mechanism, external sleeve 7 is installed at the top end of connecting piece 5, clamping block 8 is provided with multiple groups of settings in external sleeve 7, push spring 9 is installed on the outside of multiple clamping blocks 8, plug rod 10 is installed on the side wall of clamping block 6, clamping groove 11 is provided with multiple groups of distribution in the outer wall of plug rod 10.

[0030] Multiple clamping blocks 6 are provided with soft pad 12 inside, and the soft pad 12 is provided to provide a soft contact surface for the clamped object, to avoid damage or wear caused by direct contact with the hard clamping block 6.

[0031] Multiple clamping blocks 6 are provided with positioning rods 13 on the outside, and the positioning rods 13 are provided with multiple groups, and the connecting piece 5 is provided with positioning holes 14, and the positioning holes 14 are provided with multiple groups and are matched with the multiple positioning rods 13, and the positioning rods 13 and the positioning holes 14 are matched to realize accurate positioning between the clamping block 6 and other components, and the positioning rod 13 is inserted into the positioning hole 14 to ensure the fixation of the clamping block 6 in a specific position.

[0032] The inner top surface of the external sleeve 7 is provided with a compression spring 15, and the bottom end of the compression spring 15 is provided with a top ring 16, and the compression spring 15 is connected with the external sleeve 7 through the top ring 16 at the bottom end, to provide a elastic support force for the whole mechanism.

[0033] The inner top surface of the external sleeve 7 is provided with a limiting block 17, and the top end of the plug rod 10 is provided with a limiting slot 18, and the limiting block 17 and the limiting slot 18 are both polygonal and matched, and the polygonal design of the limiting block 17 and the limiting slot 18 not only enhances the stability of the connection, but also achieves the purpose of limiting through accurate shape matching.

[0034] Multiple push springs 9 are provided with limiting sleeves 19 on the outer end, and the multiple limiting sleeves 19 are fixedly connected to the inner wall of the external sleeve 7, and the multiple limiting sleeves 19 are provided with limiting grooves 20 inside, and the multiple clamping blocks 8 are provided with limiting blocks 21 on the outside, and the multiple limiting blocks 21 are respectively slidably connected with the multiple limiting grooves 20, and the push spring 9 provides power for the limiting sleeve 19, and the limiting sleeve and the clamping block 8 are dynamically fixed and adjusted through the sliding connection of the limiting groove 20 and the limiting block 21.

[0035] In this embodiment, first install the specified model of the clamp block 6 on the connecting piece 5, insert the plug rod 10 through the connecting piece 5 into the external sleeve 7, align and insert the multiple sets of positioning rods 13 with the multiple sets of positioning holes 14 to position the insertion angle of the clamp block 6, limit the insertion position of the plug rod 10 through the limiting block 17 and the limiting groove 18, when the top end of the plug rod 10 pushes the top ring 16 to extrude the compression spring 15, the multiple sets of clamping blocks 8 are pushed into the clamping groove 11 by the push spring 9 to clamp and fix the plug rod 10, when the clamping block 8 moves, the limiting block 21 on the outside slides in the limiting groove 20 to keep the stability of the clamping block 8 during movement, complete the installation of the clamp block 6, place the aircraft tail rod inside the two sets of clamp blocks 6, control the cylinder 4 to make its telescopic end extend, push the bottom end of the two sets of hinged frames 3 through the two ends of the cylinder 4, make the two sets of hinged frames 3 rotate along the connecting point of the support frame 2, at this time, the top end of the two sets of hinged frames 3 pushes the two sets of clamp blocks 6 to clamp and fix the aircraft tail rod, reduce the damage of the clamp block 6 to the tail rod through the soft pad 12.

[0036] Please refer to Figures 3-5 , as an embodiment of the quick release mechanism: the quick release mechanism includes an unlocking sleeve 22, an unlocking block 23, a resisting block 24 and a threaded sleeve 25, the unlocking sleeve 22 is slidingly installed at the bottom end of the external sleeve 7, the unlocking block 23 is provided with multiple sets of installation at the bottom surface of the unlocking sleeve 22, the resisting block 24 is installed at the top surface of the multiple sets of clamping blocks 8, and the threaded sleeve 25 is rotationally installed at the top surface of the external sleeve 7 and is in threaded connection with the outer wall of the unlocking sleeve 22.

[0037] The outer wall of the plug rod 10 is provided with a sliding groove 26, and the sliding groove 26 is provided with multiple sets of sliding connection with the multiple sets of unlocking blocks 23, so as to realize the control of the mechanical locking state, and this design allows the unlocking or locking mechanism to be realized by relative movement.

[0038] More specifically, when it is necessary to fix tail rods of different specifications, it is necessary to replace the clamp block 6, rotate the threaded sleeve 25 to make it in threaded connection with the outer wall of the unlocking sleeve 22, drive the unlocking sleeve 22 to slide along the external sleeve 7, thereby pushing the multiple sets of unlocking blocks 23 to slide along the sliding groove 26 to abut against the multiple sets of resisting blocks 24, push the clamping block 8 to move outward to disengage from the clamping groove 11 through the abutment of the arc surfaces on the unlocking block 23 and the resisting block 24, release the clamping and fixing of the plug rod 10, then the compression spring 15 is elastically reset to push the top end of the plug rod 10 through the top ring 16, so that it disengages from the external sleeve 7, then the plug rod 10 can be pulled out of the connecting piece 5, and the disassembly of the clamp block 6 is completed.

[0039] In summary, the overall device in use or operation: first install the specified model of the clamp block 6 on the connecting piece 5, insert the plug rod 10 through the connecting piece 5 into the external sleeve 7, align the multiple sets of positioning rods 13 with the multiple sets of positioning holes 14 to insert and position the insertion angle of the clamp block 6, limit the insertion position of the plug rod 10 through the limiting block 17 and the limiting groove 18, when the top ring 16 is pushed by the top end of the plug rod 10 to extrude the compression spring 15, the multiple sets of clamping blocks 8 are pushed into the clamping groove 11 by the push spring 9 to clamp and fix the plug rod 10, when the clamping block 8 moves, the limiting block 21 on the outside slides in the limiting groove 20 to keep the stability of the clamping block 8 during movement, complete the installation of the clamp block 6, place the aircraft tail rod inside the two sets of clamp blocks 6, control the cylinder 4 to make its telescopic end extend, push the bottom end of the two sets of hinged frames 3 through the two ends of the cylinder 4, make the two sets of hinged frames 3 rotate along the connecting point of the support frame 2, at this time, the two sets of clamp blocks 6 at the top of the two sets of hinged frames 3 push the aircraft tail rod to clamp and fix it, and the soft pad 12 reduces the damage to the tail rod caused by the clamp block 6.

[0040] When it is necessary to fix different specifications of tail rods, the clamp block 6 needs to be replaced, the threaded sleeve 25 is rotated to be threadedly connected with the outer wall of the unlocking sleeve 22, drives the unlocking sleeve 22 to slide along the external sleeve 7, thereby pushing the multiple sets of unlocking blocks 23 to slide along the sliding groove 26 to abut against the multiple sets of abutting blocks 24, the clamping block 8 is pushed to move outward to disengage from the clamping groove 11 through the abutment of the arc surfaces arranged on the unlocking block 23 and the abutting block 24, the clamping and fixing of the plug rod 10 is released, then the compression spring 15 is elastically reset to push the top end of the plug rod 10 through the top ring 16, so that it disengages from the external sleeve 7, then the plug rod 10 can be pulled out of the connecting piece 5, and the disassembly of the clamp block 6 is completed.

[0041] In all the schemes mentioned above, the connection between the two components can be selected according to the actual situation, such as welding, bolt and nut cooperation connection, bolt or screw connection or other known connection mode, which will not be described one by one, and the welding is preferred for the fixed connection mentioned above, although the embodiments of the utility model have been shown and described, those skilled in the art can understand that the embodiments can be changed, modified, replaced and modified in various ways without departing from the principles and spirits of the utility model, and the scope of the utility model is defined by the appended claims and their equivalents.

Claims

1. An aircraft tail rod machining fixture base, comprising a base (1), characterized in that: The base (1) is provided with a clamping mechanism, the clamping mechanism includes support frame (2), hinged frame (3), air cylinder (4), connecting piece (5) and clamp block (6), the support frame (2) is installed on the base (1), the hinged frame (3) is provided with two groups of opposite settings and is rotatably installed at both ends of the support frame (2), the air cylinder (4) is rotatably connected to the bottom end of the two groups of hinged frame (3) at both ends respectively, the connecting piece (5) is installed at the top end of the two groups of hinged frame (3), the clamp block (6) is installed on the connecting piece (5) by being provided with a quick mounting mechanism, the quick mounting mechanism includes external sleeve (7), clamping block (8), push spring (9), plug rod (10), clamping groove (11) and quick release mechanism, the external sleeve (7) is installed at the top end of the connecting piece (5), the clamping block (8) is provided with a plurality of groups arranged in the external sleeve (7), the push spring (9) is installed on the outside of the plurality of clamping blocks (8), the plug rod (10) is installed on the side wall of the clamp block (6), and the clamping groove (11) is provided with a plurality of groups distributed on the outer wall of the plug rod (10).

2. The aircraft tail rod machining fixture of claim 1, wherein: Multiple groups of the inner side of the clamp block (6) are provided with soft pads (12).

3. The aircraft tail rod machining fixture of claim 2, wherein the plurality of sets of rods are arranged in a plurality of rows. 5 The outer side of the clamp block (6) is provided with a positioning rod (13), the positioning rod (13) is provided with a plurality of groups, and the connecting piece (5) is provided with a plurality of positioning holes (14) which are matched with the plurality of positioning rods (13).

4. The aircraft tail rod machining fixture of claim 3, wherein: The inner top surface of the external sleeve (7) is provided with a compression spring (15), and the bottom end of the compression spring (15) is provided with a top ring (16).

5. The aircraft tail rod machining fixture of claim 4, wherein: The inner top surface of the external sleeve (7) is provided with a limiting block (17), and the top end of the plug rod (10) is provided with a limiting groove (18), and the limiting block (17) and the limiting groove (18) are polygonal and matched.

6. The aircraft tail rod machining fixture of claim 5, wherein the plurality of sets of rods are arranged in a plurality of rows. 5 The outer end of the push spring (9) is provided with a limiting sleeve (19), a plurality of limiting sleeves (19) are fixedly connected to the inner wall of the external sleeve (7), a plurality of limiting grooves (20) are formed in the limiting sleeve (19), a plurality of limiting blocks (21) are arranged on the outer side of the clamping block (8), and a plurality of limiting blocks (21) are respectively and slidably connected with a plurality of limiting grooves (20).

7. The aircraft tail rod machining fixture of claim 6, wherein: The quick release mechanism includes an unlocking sleeve (22), an unlocking block (23), a resisting block (24) and a threaded sleeve (25), the unlocking sleeve (22) is slidably installed at the bottom end of the external sleeve (7), the unlocking block (23) is provided with a plurality of groups installed on the bottom surface of the unlocking sleeve (22), the resisting block (24) is installed on the top surface of the clamping block (8), and the threaded sleeve (25) is rotatably installed on the top surface of the external sleeve (7) and is in threaded connection with the outer wall of the unlocking sleeve (22).

8. The aircraft tail rod machining fixture of claim 7, wherein: The outer wall of the plug rod (10) is provided with a sliding groove (26), and the sliding groove (26) is provided with a plurality of groups and is in sliding connection with a plurality of unlocking blocks (23).

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