Supporting device convenient for mounting empennage of airplane

Abstract

The utility model discloses a supporting device facilitating installation of an airplane empennage, and particularly relates to the field of airplane assembling equipment. Comprising a fixing groove, and a baffle is vertically arranged in the fixing groove; the stress block is located above the fixing groove, and a first clamping groove is formed in the bottom surface. The supporting frame is connected to the bottom of the fixing groove, and a second clamping groove is formed in the supporting frame and communicates with the fixing groove; the first clamping groove and the second clamping groove are located on the same side of the baffle, and the side walls of the first clamping groove and the second clamping groove and the side wall of the baffle are located on the same plane. The driving mechanism is located in the fixing groove. The two first sliding blocks are connected to the baffle in a sliding mode and connected with the driving mechanism, and under the action of the driving mechanism, the two first sliding blocks are embedded into the first clamping groove and the second clamping groove along the baffle. And when the stress block is damaged after being used for a long time, replacement is convenient, and the practicability of the device is improved.

Description

Technical Field

[0001] This application relates to the field of aircraft assembly equipment, and more particularly to a support device for facilitating the installation of an aircraft tail fin. Background Technology

[0002] In the current process of installing aircraft tail fins, multiple sets of mounting brackets are generally used for support and fixation. However, in the current use of the support bracket, the stress block at the top of the support bracket is usually fixed to the support bracket body by welding. Although the installation is stable, the stress block is prone to damage because it is in direct contact with the aircraft tail fin. In addition, the existing stress block is not convenient to disassemble and replace with the support bracket body, which affects the normal use of the device. Utility Model Content

[0003] The main purpose of this application is to provide a support device for easy installation of aircraft tail fins, which aims to solve the problem that it is inconvenient to disassemble and replace the existing load-bearing blocks and support frame.

[0004] To achieve the above objectives, this application provides a support device for easy installation of an aircraft tail fin, including a fixing groove, in which a baffle is vertically arranged; a force-bearing block is located above the fixing groove, and a first slot is formed on its bottom surface; a support frame is connected to the bottom of the fixing groove, and a second slot is provided on the support frame, which communicates with the fixing groove; wherein the first slot and the second slot are located on the same side of the baffle, and the sidewalls of the first slot and the second slot are on the same plane as the sidewall of the baffle; a drive mechanism is located in the fixing groove; two first sliding blocks are slidably connected to the baffle and are respectively connected to the drive mechanism, and under the action of the drive mechanism, the two first sliding blocks are respectively embedded into the first slot and the second slot along the baffle.

[0005] Optionally, the drive mechanism includes a lead screw, one end of which extends into the fixed groove along the side wall of the fixed groove and is rotatably connected to the fixed groove; a movable sleeve, which is sleeved on the lead screw and threadedly connected to the lead screw; and two connecting rods, one end of each connecting rod being hinged to the movable sleeve and the other end being hinged to the corresponding first sliding block.

[0006] Optionally, the baffle, the first slot, and the second slot are provided with a first sliding groove that is adapted to the first sliding block.

[0007] Optionally, the driving mechanism and the two first sliding blocks are used as locking mechanisms. The locking mechanisms include two blocks, which are arranged on both sides of the baffle. Two first slots are correspondingly provided on the force-bearing block, and two second slots are correspondingly provided on the support frame.

[0008] Optionally, the shape of the force-bearing block is arc-shaped; a protective layer is provided on the surface of the force-bearing block that contacts the aircraft tail fin.

[0009] Optionally, the support frame includes: a first adjusting sleeve rod; a movable rod connected to the bottom of the fixed groove, with one end of the movable rod extending into the first adjusting sleeve rod; and a second slot formed on the movable rod; wherein the first adjusting sleeve rod includes: a first sleeve sleeved to the bottom of the movable rod, with a through hole provided on the side wall of the first sleeve; and a positioning element, one end of which passes through the through hole and is movably connected to the movable rod.

[0010] Optionally, the first adjusting rod further includes a spring located inside the first sleeve, with one end connected to the bottom of the movable rod and the other end connected to the bottom of the first sleeve.

[0011] Optionally, the movable rod is provided with a positioning groove, and one end of the positioning element passes through the through hole and is located in the positioning groove.

[0012] Optionally, the support frame further includes: a second sliding block connected to the bottom of the movable rod and located inside the first sleeve, the second sliding block being provided with a first positioning hole adapted to the positioning member; and the inner wall of the first sleeve being provided with a second sliding groove adapted to the second sliding block.

[0013] Optionally, the first adjusting sleeve rod further includes: a second sliding block connected to the bottom of the first sleeve, the second sliding block having a second positioning hole; the support frame further includes: a second adjusting sleeve rod, the structure of the second adjusting sleeve rod being the same as that of the first adjusting sleeve rod, the second sliding block being located inside the first sleeve of the second adjusting sleeve rod; a positioning element of the second adjusting sleeve rod, one end of which extends into the second positioning hole through a corresponding through hole; and a support platform connected to the bottom of the second adjusting sleeve rod.

[0014] Compared with the prior art, the beneficial effects of this application are as follows:

[0015] This utility model discloses a support device for easy installation on an aircraft tail fin. By rotating a handle, a lead screw moves a movable sleeve, causing the first sliding block to gradually enter the slots inside the force-bearing block and the movable rod under the action of the first sliding groove. This strengthens the fixation and facilitates replacement when the force-bearing block is damaged after prolonged use, improving the device's practicality. By pulling the movable rod, the device's height can be adjusted under the action of the second sliding block and the second sliding groove. Rotating the positioning component allows it to embed into the positioning groove, facilitating fixation and preventing the movable rod from falling under excessive force, which could cause the device to malfunction. The inclusion of a spring enhances the device's stability. When the positioning component is removed, the spring acts as a shock absorber, preventing the first sleeve and movable rod from suddenly falling under gravity and causing damage. Furthermore, the device allows the movable rod to be gradually stored into the first sleeve, and then the first sleeve to be gradually stored into the bottom second sleeve, reducing the footprint when not in use. Attached Figure Description

[0016] Figure 1This is a schematic diagram of a support device for easy installation of an aircraft tail fin according to this application;

[0017] Figure 2 for Figure 1 A magnified view of a section at point A in the middle;

[0018] Figure 3 for Figure 1 A schematic diagram of the drive mechanism;

[0019] Figure 4 for Figure 1 A magnified view of a section at point B.

[0020] The realization of the purpose, functional features and advantages of this application will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0021] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0022] The first embodiment of this utility model provides a support device for easy installation of an aircraft tail fin, such as... Figure 1 As shown, the device includes a force-bearing block 22, a fixing groove 13, a support frame 1, a drive mechanism, and two first sliding blocks 5. The fixing groove 13 has a baffle 6 vertically installed inside it. The force-bearing block 22 is located above the fixing groove 13, and a first slot 3 is formed on its bottom surface. The support frame 1 is connected to the bottom of the fixing groove 13, and a second slot 24 is provided on the support frame 1, communicating with the fixing groove 13. The first slot 3 and the second slot 24 are located on the same side of the baffle 6, and the sidewalls of the first slot 3 and the second slot 24 are on the same plane as the sidewall of the baffle 6. The drive mechanism is located inside the fixing groove 13. The two first sliding blocks 5 are slidably connected to the baffle 6 and are respectively connected to the drive mechanism. Under the action of the drive mechanism, the two first sliding blocks 5 are respectively embedded into the first slot 3 and the second slot 24 along the baffle 6.

[0023] Furthermore, such as Figure 2-3As shown, the driving mechanism includes a lead screw 11, a movable sleeve 10, and two connecting rods 8. One end of the lead screw 11 extends into the fixed groove 13 along the side wall of the fixed groove 13 and is rotatably connected to the fixed groove 13. The movable sleeve 10 is attached to the lead screw 11 and is threadedly connected to the lead screw 11. One end of each connecting rod 8 is hinged to the movable sleeve 10 via a second hinge shaft 9, and the other end is hinged to the corresponding first sliding block 5 via a first hinge shaft 7. The included angle between the connecting rod 8 and the first sliding block 5 is greater than 90 degrees.

[0024] In this embodiment, the rotation of the lead screw 11 causes the movable sleeve 10 to move axially along the lead screw 11. This, in turn, drives the first sliding block 5 into the first slot 3 and the second slot 24 via the two connecting rods 8, locking the force-bearing block 22 and the support frame 1, thus strengthening the fixation. Furthermore, if the force-bearing block 22 becomes damaged after prolonged use, rotating the lead screw 11 in the reverse direction moves the first sliding block 5 away from the first slot 3 and the second slot 24, unlocking the force-bearing block 22 and the support frame 1 for easy replacement and improved device practicality. Additionally, to facilitate the rotation of the lead screw, a handle 12 is connected to the other end of the lead screw 11. The handle 12 is located outside the fixed slot 13; rotating the handle 12 rotates the lead screw.

[0025] Furthermore, the baffle 6, the first slot 3, and the second slot 24 are provided with a first sliding groove 4 that matches the first sliding block 5, allowing the two first sliding blocks 5 to slide in the first sliding groove 4, preventing the first sliding blocks 5 from deviating and being unable to enter the first slot 3 and the second slot 24. The first sliding block 5 forms an embedded fixing structure with the first slot 3 and the second slot 24 through the first sliding groove 4. By setting the first sliding block 5 and the first slot 3 and the second slot 24 as rectangles, the force-bearing block 22 can be prevented from rotating and falling off, which can play a limiting role, thereby strengthening the fixation between the force-bearing blocks 22 and preventing them from falling off during use, thus improving the stability of the device.

[0026] To further ensure the stability of the connection between the force-bearing block 22 and the support frame 1, the driving mechanism and the two first sliding blocks 5 are used as locking mechanisms. Two locking mechanisms are set up, with the specific structure as follows: the two locking mechanisms are set on both sides of the baffle 6, and the first sliding block 5 corresponding to each locking mechanism is slidably connected to the side wall of the baffle 6 respectively; the force-bearing block 22 is provided with two first slots 3, and the support frame 1 is provided with two second slots 24.

[0027] For example, the force-bearing block 22 is arc-shaped. To ensure a stable connection between the force-bearing block 22 and the fixing groove 13, a first thread is provided on the outer wall of the bottom end of the force-bearing block 22, and a second thread adapted to the first thread is provided on the inner wall of the fixing groove 13. By providing the first and second threads, the fixing groove 13 and the force-bearing block 22 can be initially fixed. The height of the second thread is equal to half the height of the fixing groove 13 to avoid affecting the rotation of the lead screw 11. In addition, a protective layer 2 is provided on the surface of the force-bearing block 22 that contacts the aircraft tail fin. The protective layer 2 is made of rubber, which has cushioning properties to protect the aircraft tail fin and prevent damage during support, thus providing protection.

[0028] The support frame 1 includes a first adjusting sleeve rod and a movable rod 14. The movable rod 14 is connected to the bottom of the fixed groove 13, and one end of the movable rod 14 extends into the adjusting sleeve rod. A second slot 24 is formed on the movable rod 14. The first adjusting sleeve rod includes a first sleeve 18 and a positioning element 21. The first sleeve 18 is sleeved on the bottom of the movable rod 14, and a through hole is provided on the side wall of the first sleeve 18. One end of the positioning element 21 passes through the through hole and is movably connected to the movable rod 14. For example, the positioning element 21 can be a bolt.

[0029] In this embodiment, the movable rod 14 is positioned with the first sleeve 18 by extending the positioning member 21 into the through hole, or the positioning member 21 is moved away from the through hole and the movable rod 14 is stored inside the first sleeve 18, thereby adjusting the height of the support frame 1. It can be used according to different needs, improving the practicality of the device, and making it convenient to store the support frame 1, so as to minimize the floor space occupied.

[0030] Furthermore, the movable rod 14 is provided with multiple positioning grooves 15, and one end of the positioning member 21 passes through the through hole and is located in the positioning groove 15. Inserting the positioning member 21 into the positioning groove 15 further adjusts the height of the support frame 1. Two positioning members 21 may be provided, located on both sides of the first sleeve 18 respectively, and two corresponding through holes and positioning grooves 15 are also provided, achieving positioning on both sides and further improving stability.

[0031] In one embodiment, such as Figure 4 As shown, the first adjusting sleeve also includes a spring 19, located inside the first sleeve 18, with one end connected to the bottom of the movable rod 14 and the other end connected to the bottom of the first sleeve 18. By setting the spring 19, it is possible to prevent the movable rod 14 and the first sleeve 18 from being affected by gravity and undergoing free fall after the positioning component 21 is removed, which could cause damage to the inside of the support frame 1. The spring 19 can act as a buffer, converting the pressure into elastic potential energy, thereby avoiding this problem.

[0032] Furthermore, the support frame 1 also includes a second sliding block 16, connected to the bottom of the movable rod 14 and located inside the first sleeve 18. The second sliding block 16 is provided with a first positioning hole that matches the positioning member 21; the inner wall of the first sleeve 18 is provided with a second sliding groove 17 that matches the second sliding block 16. The movable rod 14 is driven by the second sliding block 16 to move along the second sliding groove 17 inside the first sleeve 18, thereby achieving guidance. In addition, first fixing blocks 20 are fixed on both sides of the first sleeve 18, and the first fixing blocks 20 are located outside the through hole. The purpose of setting the first fixing blocks 20 is to allow the positioning member 21 to be embedded inside the first fixing blocks 20 for fixed placement during adjustment, preventing the positioning member 21 from falling off after use.

[0033] To adapt to more scenarios, the height of support frame 1 can be increased, for example, by setting a second adjusting sleeve, as follows.

[0034] The first adjusting sleeve also includes a second sliding block 16 connected to the bottom of the first sleeve 18. The second sliding block 16 is provided with a second positioning hole. The support frame 1 also includes a second adjusting sleeve and a support platform. The structure of the second adjusting sleeve is the same as that of the first adjusting sleeve. The second sliding block 16 is located inside the first sleeve 18 of the second adjusting sleeve. One end of the positioning member 21 of the second adjusting sleeve extends into the second positioning hole through a corresponding through hole. The support platform is connected to the bottom of the second adjusting sleeve.

[0035] Specifically, the second adjusting sleeve includes a second sleeve 23 and a corresponding positioning element 21. A spring 19 is installed inside the second sleeve 23. One end of the spring 19 is connected to the second sliding block 16, and the other end is connected to the bottom of the second sleeve 23. Through holes are provided on both sides of the second sleeve 23, and second fixing blocks are connected to the through holes. The positioning element 21 passes through the second fixing block and the through hole, and enters the second positioning hole to achieve positioning of the second adjusting sleeve and the first adjusting sleeve. Rotating the positioning element 21 can disengage the positioning element 21 from the second sliding block 16, allowing the first adjusting sleeve to be housed inside the second adjusting sleeve.

[0036] Working principle: In use, first rotate the positioning piece 21 on the first sleeve 18 to disengage it from the first fixed block 20 and the second sliding block 16. Then, pull the movable rod 14 to make the second sliding block 16 slide inside the second sliding groove 17, thereby adjusting the height of the movable rod 14. After adjustment, rotate the positioning piece 21 to gradually embed it into the positioning groove 15 to fix the movable rod 14 and prevent it from falling off. The protective layer 2 supports the aircraft tail. When it needs to be stored after use, rotate the positioning piece 21 on the first sleeve 18 and the second sleeve 23 to disassemble it. Then, under the action of the second sliding block 16 and the second sliding groove 17, the first sleeve 18 is stored inside the second sleeve 23. Similarly, the movable rod 14 is stored inside the first sleeve 18. Finally, the positioning piece 21 is inserted into the positioning groove 15 at the top of the movable rod 14 for fixation. This makes it convenient to use and improves the practicality of the device. When not in use, it can be stored away for easy placement without taking up too much space.

[0037] When it is necessary to install and fix the force-bearing block 22, firstly, the force-bearing block 22 is embedded into the inside of the fixing groove 13. Then, by rotating the force-bearing block 22 under the action of the first thread and the second thread, the force-bearing block 22 is initially fixed to the fixing groove 13. By rotating the handle 12, the lead screw 11 is rotated, thereby driving the movable sleeve 10 to move to the left. At this time, the two second hinge shafts 9 move to the left, driving one connecting rod 8 to rotate clockwise around the second hinge shaft 9, and the other connecting rod 8 to rotate counterclockwise around the second hinge shaft 9, thereby pushing one first hinge shaft 7 to move upward and the other first hinge shaft 7 to move downward. This causes the two first sliding blocks 5 to move upward and downward respectively under the action of the first sliding groove 4, thereby gradually embedding into the inside of the first slot 3 and the second slot 24, which can strengthen the fixation. The above can enhance the stability of the device, and the installation is simple and firm. When the force-bearing block 22 is damaged, it can be easily replaced.

[0038] The above are merely preferred embodiments of this application and do not limit the patent scope of this application. Any equivalent structural or procedural transformations made using the content of this application's specification and drawings, or direct or indirect applications in other related technical fields, are similarly included within the patent protection scope of this application.

Claims

1. A support device for easy installation on an aircraft tail fin, characterized in that, The utility model relates to a support device for the installation of aircraft tail wing, comprising: A fixed groove is vertically provided with a baffle inside; A force block is located above the fixed groove, and a first clamping groove is opened on the bottom surface of the force block; A support frame is connected at the bottom of the fixed groove, and a second clamping groove is provided on the support frame and communicates with the fixed groove; wherein the first clamping groove and the second clamping groove are located on the same side of the baffle, and the side walls of the first clamping groove and the second clamping groove are located on the same plane as the side walls of the baffle; A driving mechanism is located inside the fixed groove; Two first sliding blocks are slidingly connected to the baffle and are respectively connected to the driving mechanism, and under the action of the driving mechanism, the two first sliding blocks are respectively embedded into the first clamping groove and the second clamping groove along the baffle.

2. The support device for facilitating installation of an aircraft tail wing according to claim 1, wherein, The driving mechanism comprises: A lead screw, one end of which extends into the fixed groove along the side wall of the fixed groove and is rotatably connected to the fixed groove; A movable sleeve is sleeved on the lead screw and is threadedly connected to the lead screw; Two connecting rods, one end of each connecting rod is hingedly connected to the movable sleeve, and the other end is hingedly connected to the corresponding first sliding block.

3. The support device for facilitating installation of an aircraft tail wing of claim 1, wherein, First sliding grooves adapted to the first sliding blocks are provided on the baffle, the first clamping groove and the second clamping groove.

4. The support device for the installation of aircraft tail wing according to claim 1, wherein the driving mechanism and the two first sliding blocks are taken as locking mechanisms, and the two locking mechanisms are provided on both sides of the baffle; Two first clamping grooves are correspondingly provided on the force block, and two second clamping grooves are correspondingly provided on the support frame. The shape of the force block is arc-shaped, and a protective layer is provided on the surface of the force block that contacts the aircraft tail wing.

5. The support device for facilitating installation of an aircraft tailplane according to claim 1, wherein, 6. The support device for the installation of aircraft tail wing according to claim 1, wherein the support frame comprises: A first adjusting sleeve rod; An active rod is connected to the bottom of the fixed groove, and one end of the active rod extends into the first adjusting sleeve rod; the second clamping groove is opened on the active rod; The first adjusting sleeve rod comprises: A first sleeve is sleeved on the bottom of the active rod, and a through hole is provided on the side wall of the first sleeve; A positioning member passes through the through hole and is movably connected to the active rod.

7. The support device for the installation of aircraft tail wing according to claim 6, wherein the first adjusting sleeve rod further comprises: A spring is located in the first sleeve, one end of the spring is connected to the bottom of the active rod, and the other end of the spring is connected to the bottom of the first sleeve.

8. The support device for the installation of aircraft tail wing according to claim 6, wherein a positioning groove is provided on the active rod, and one end of the positioning member passes through the through hole and is located in the positioning groove. The support frame further comprises: A second sliding block is connected to the bottom of the active rod and is located in the first sleeve, and a first positioning hole adapted to the positioning member is provided on the second sliding block; A second sliding groove adapted to the second sliding block is provided on the inner wall of the first sleeve. The first adjusting sleeve rod further comprises:

9. The support device for facilitating installation of an aircraft tailplane according to claim 6, wherein, A second sliding block is connected to the bottom of the first sleeve, and a second positioning hole is provided on the second sliding block; The support frame further comprises: ​ 10. The support device for facilitating installation of an aircraft tailplane according to claim 6, wherein, ​ ​ ​ A second adjusting sleeve rod, which has the same structure as the first adjusting sleeve rod, and a second sliding block is located in the first sleeve of the second adjusting sleeve rod; A positioning member of the second adjusting sleeve rod, one end of which extends into the second positioning hole through the corresponding through hole; A supporting platform connected to the bottom of the second adjusting sleeve rod.

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