Missile launching cylinder cover driving device load debugging tool

Abstract

The utility model discloses a missile launching cylinder cover driving device load debugging tool which comprises a debugging workbench, a driving device is arranged at one end of the debugging workbench, a load support is arranged at the other end of the debugging workbench, a driving device swing arm is arranged on one side of the driving device, and a crank is fixedly connected to the side, close to the load support, of the driving device swing arm. A bearing supporting seat is arranged in the end, away from the driving device swing arm, of the crank, a switching clamp is arranged at one end of the crank and provided with a load chuck, a load twisting strip is arranged at the end, away from the switching clamp, of the load chuck, and the other end of the load twisting strip is fixedly connected with a load support. Compared with the prior art, the utility model has the advantages that the launch canister cover of the corresponding model can be tested by adjusting the size of the load torsion bar, the working condition of the driving device is quickly simulated, the operation of repeatedly disassembling and assembling the launch canister cover in the test stage is reduced, and the damage to the driving device caused by the test is greatly avoided.

Description

Technical Field

[0001] The utility model relates to the technical field of missile launch tube debugging tooling, in particular to a missile launch tube cover driving device load debugging tooling. Background Art

[0002] The utility model relates to the field of missile launch tube debugging tooling, in particular to the design of a missile launch tube cover driving device load debugging tooling, belonging to the technical field of debugging tooling design and manufacturing.

[0003] A missile launch tube is a specialized cylindrical device used to hold and launch missiles. It primarily consists of a hatch and inner tube. It supports, stores, and launches missiles. When a missile is ready for launch, the hatch must be able to be quickly opened to clear the missile's flight path. Currently, the main hatch opening solutions for missile launch tubes include mechanical, ejectable, and frangible lid technologies. Mechanical hatch opening utilizes manual or electric actuation, using a transmission mechanism to open the hatch. These methods offer repeatability and maintainability.

[0004] With the continuous advancement of technology and the increasing demand for missiles and rockets of varying sizes in military operations, the size of missile launch tubes is also evolving. Therefore, it is particularly important to test the performance of the missile launch tube cover drive mechanism in advance during the design and development phase.

[0005] The information disclosed in this background technology section is only intended to enhance understanding of the overall background of the invention and should not be regarded as an admission or any form of suggestion that the information constitutes the prior art already known to a person skilled in the art. Utility Model Content

[0006] The technical problem to be solved by the utility model is to overcome the above technical defects and provide a load debugging tool for a missile launch tube cover drive device.

[0007] In order to solve the above problems, the technical solution of the present invention is: a load debugging tooling for a missile launch tube cover drive device, comprising a debugging workbench, a drive device is provided at one end of the debugging workbench, and a load bracket is provided at the other end; a drive device swing arm is provided on one side of the drive device, and a crank is fixedly connected to the side of the drive device swing arm close to the load bracket; a bearing support seat is provided in the end of the crank away from the drive device swing arm; an adapter clamp is provided at one end of the crank, and the adapter clamp is provided with a load chuck; a load twist bar is provided at the end of the load chuck away from the adapter clamp, and the other end of the load twist bar is fixedly connected to the load bracket.

[0008] Furthermore, a bearing hole is provided in the bearing support seat, and one end of the crank is inserted into the bearing hole and connected to the adapter fixture.

[0009] Furthermore, a fixing hole is provided at one end of the crank away from the swing arm of the driving device, and a bearing is provided on the outer ring of the end.

[0010] Furthermore, the adapter clamp is provided with a plug-in fastener at one end away from the load clamp, and the plug-in fastener is plugged into the fixing hole.

[0011] The advantages of this utility model compared with the existing technology are:

[0012] (1) The utility model has the advantages of simple structure, low difficulty in processing and assembling parts, convenient and quick operation, and more accurate data.

[0013] (2) By adjusting the size of the load twist bar, the corresponding model of the launch tube cover can be tested, and the working conditions of the drive device can be quickly simulated, which reduces the repeated disassembly and assembly of the launch tube cover during the test phase and greatly avoids damage to the drive device caused by the test.

[0014] (3) With the adjustment of the load torsion bar parameters, the operation of large or extra-large launch tube covers can be seamlessly simulated. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 This is an assembly diagram of the present utility model.

[0016] Figure 2 It is a schematic diagram of the crank of the present utility model.

[0017] Figure 3 This is a schematic diagram of the transfer fixture of the present utility model.

[0018] As shown in the figure: 1. Debugging workbench; 2. Drive unit; 3. Drive unit swing arm; 4. Crank; 5. Bearing support seat; 6. Adapter fixture; 7. Load chuck; 8. Load twist bar; 9. Load bracket. DETAILED DESCRIPTION

[0019] The specific embodiments of the present invention will be further described below with reference to the accompanying drawings, wherein the same components are represented by the same reference numerals.

[0020] It should be noted that the words "front", "rear", "left", "right", "up" and "down" used in the following description refer to directions in the accompanying drawings, and the words "inside" and "outside" refer to directions toward or away from the geometric center of a specific component, respectively.

[0021] In order to make the contents of the present invention more clearly understood, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention.

[0022] like Figures 1 to 3As shown, a load debugging tool for a missile launch tube cover drive device includes a debugging workbench 1, a drive device 2 is provided at one end of the debugging workbench 1, and a load bracket 9 is provided at the other end. A drive device swing arm 3 is provided on one side of the drive device 2, and a crank 4 is fixedly connected to the drive device swing arm 3 on the side close to the load bracket 9. A fixing hole is provided at the end of the crank 4 away from the drive device swing arm 3, and a bearing is provided on the outer ring of the end. A bearing support seat 5 is provided in the end of the crank 4 away from the drive device swing arm 3. The design of the crank 4 is to convert the circular motion of the drive device swing arm 3 into the central rotation motion of the circular axis extension end of the crank 4. A transfer fixture 6 is provided at one end of the crank 4, and a bearing hole is provided in the bearing support seat 5. One end of the crank 4 is inserted into the bearing hole and connected to the transfer fixture 6. The transfer fixture 6 is provided with a load clamp 7, and a plug-in fastener is provided at the end of the transfer fixture 6 away from the load clamp 7. The plug-in fastener is plugged into In the fixing hole, a load twist bar 8 is provided at one end of the load clamp 7 away from the adapter clamp 6, and the other end of the load twist bar 8 is fixedly connected to the load bracket 9. The driving device swing arm 3 is fixed to the debugging workbench 1, and its cover opening swing arm is transferred to the bearing support seat 5 through a set of cranks 4 with bearings and fixed, and then the load twist bar 8 fixed at one end is connected to the crank 4 through the adapter clamp 6. At this time, the operating data of the driving device 2 and the torsion angle of the load twist bar 8 can be used to judge whether the driving device meets the design requirements. The applied load strength can be calculated through the torque parameters of the load twist bar 8 itself and the rotation angle of the twist bar. The load strength of the load twist bar 8 is equivalent to the load strength of the missile launch tube cover acting on the driving device 2. The load twist bar 8 can replace some large or extra-large launch tube covers, thereby simulating the operating parameters of the driving device to check whether its design strength meets the use requirements.

[0023] according to Figures 1 to 3 In a specific application of the load debugging tooling for a missile launch tube cover drive device shown in FIG. 1 , the drive device 2 and the load bracket 9 are mounted on the same debugging workbench 1. The drive device's swing arm 3 is fixed to the connection end of the crank 4. The crank 4's axial extension is inserted into the inner bearing hole of the bearing support 5, completing the assembly of the drive device end. A load twist bar 8 is fixed to the load bracket 9 at one end, and connected to the load chuck 7 at the other end. The connected load chuck 7 is then connected and fixed to the crank 4's axial extension mounted on the bearing support 5 via an adapter fixture 6, completing the assembly of the load end. At the beginning of the test, the drive device 2 is operated, and its swing arm 3 drives the crank 4 in a circular motion. The crank 4's axial extension cooperates with the adapter fixture 6 to force the twist bar 8 to rotate axially. The applied load intensity can be calculated based on the rotation angle of the twist bar 8 and its own torque parameters. At this point, the drive device's operating data is read to simulate and determine the operation of the drive device when driving the missile launch tube cover.

[0024] It should be noted that, in this document, relational terms such as first and second, etc., are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the terms "comprises," "comprising," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that includes a list of elements includes not only those elements but also other elements not explicitly listed, or elements inherent to such process, method, article, or apparatus.

[0025] Although the embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and variations may be made to these embodiments without departing from the principles and spirit of the present invention, and the scope of the present invention is defined by the appended claims and their equivalents.

[0026] The above description of the present invention and its embodiments is non-limiting. The drawings show only one embodiment of the present invention, and the actual structure is not limited thereto. In short, if a person skilled in the art is inspired by the above, and does not deviate from the purpose of the present invention, without inventive design, a structure and embodiment similar to the technical solution should fall within the scope of protection of the present invention.

Claims

1. A load debugging tool for a missile launch tube cover drive device, characterized by: The invention comprises a debugging workbench (1), wherein one end of the debugging workbench (1) is provided with a driving device (2), and the other end is provided with a load bracket (9), one side of the driving device (2) is provided with a driving device swing arm (3), the side of the driving device swing arm (3) close to the load bracket (9) is fixedly connected to a crank (4), the end of the crank (4) away from the driving device swing arm (3) is provided with a bearing support seat (5), one end of the crank (4) is provided with a transfer fixture (6), the transfer fixture (6) is provided with a load clamp (7), the end of the load clamp (7) away from the transfer fixture (6) is provided with a load twist bar (8), and the other end of the load twist bar (8) is fixedly connected to the load bracket (9).

2. A missile launch tube cover drive device load debugging tool according to claim 1, characterized in that: A bearing hole is provided in the bearing support seat (5), and one end of the crank (4) is inserted into the bearing hole and connected to the adapter clamp (6).

3. The load debugging tool for a missile launch tube cover drive device according to claim 1, characterized in that: A fixing hole is provided at one end of the crank (4) away from the driving device swing arm (3), and a bearing is provided on the outer ring of the end.

4. The load debugging tool for a missile launch tube cover drive device according to claim 1, characterized in that: The adapter clamp (6) is provided with a plug-in fastener at one end away from the load clamp (7), and the plug-in fastener is plugged into the fixing hole.

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