Device for testing friction force of launch canister

Abstract

The utility model discloses a launch canister friction test device, which comprises a launch canister simulation piece, a launcher, a blocking frame and a launch driving assembly, and is characterized in that the launch canister simulation piece is arranged on the launcher; the launch canister simulation piece comprises a canister simulation piece and an ammunition simulation piece located in the canister simulation piece. The blocking frame is provided with a blocking net used for blocking the launched ammunition simulation piece and a horizontally-arranged spring washer, the launch canister simulation piece, the launch driving assembly and the spring washer are located on the same side of the blocking net, the blocking frame located on the other side of the blocking net is provided with a pulley block, one end of the traction rope is connected with the ammunition simulation piece, and the other end of the traction rope is connected with the launch canister simulation piece. And the other end penetrates through the blocking net and is connected with the launching driving assembly after being transferred by the pulley block. When the device is used for testing, the driving part and the launched ammunition simulation piece only move on one side of the blocking net, and the other side of the blocking net is a safe area which can be used as a working area of workers, so that the safety is higher.

Description

Technical Field

[0001] The utility model relates to the technical field of launch test, in particular to a friction force test device for a launch tube. Background Technique

[0002] In the design of a launch tube, multiple tests need to be carried out to enable the missile launch to meet the specified launch requirements. For an inclined launch type launch tube, the friction force between the ammunition and the tube body during launch needs to be precisely controlled so as to ensure that the exit speed of the ammunition reaches the specified requirements. The value of this friction force is mainly related to factors such as the launch angle of the launch tube, the materials of the ammunition and the tube body, etc. When the materials of the ammunition and the tube body are certain, it is mainly related to the launch angle. Therefore, usually after the launch tube is produced, tests need to be carried out for different launch angles, and the data to be collected is the speed at which the missile flies out of the launch port of the tube body.

[0003] If a real launch tube is used for testing, it will cause a great waste of cost and there are also safety hazards. Therefore, the prior art usually uses a launch tube simulation part and corresponding test devices to complete the test work. However, there are few test device designs in this field at present. For example, the test system described in the invention patent "A Missile Simulation Launch Test System" with the application number CN201710658247.6 can measure the speed at which a missile flies out of the launch port of a missile launch tube under the action of different magnitudes of thrust of a missile engine. First, it can be seen from the attached drawings of this test system that its power components and launch tubes are distributed on both sides of a sponge pad, and the whole system is completely open. For operators, there is no relatively safe area and the operation risk is relatively high. Second, this test system provides the release impact force by the compression elastic force of a compression spring. For missile launch, the elastic force of the spring is obviously not equivalent to it. Therefore, this system cannot implement most of the launch tube performance tests.

[0004] Therefore, it is necessary to design a launch tube friction force test device with higher safety and higher reference value of test results. Content of the Utility Model

[0005] In order to solve the technical problems in the prior art that the safety factor of the launch tube test device is relatively low and the launch test with a large impact force cannot be carried out, resulting in poor practicability of the simulation results, the utility model provides a launch tube friction force test device to solve the above problems.

[0006] The technical solution adopted by the utility model to solve its technical problems is: a launch tube friction force test device, including a launch tube simulation part, a launch rack, a blocking rack, and a launch driving component. The launch tube simulation part is placed on the launch rack; the launch tube simulation part includes a tube body simulation part and an ammunition simulation part located inside it.

[0007] A blocking net for intercepting the launched ammunition simulator and a horizontally arranged cushion are installed on the blocking frame. The launcher simulator, the launch driving assembly, and the cushion are located on the same side of the blocking net. A pulley block is arranged on the blocking frame on the other side of the blocking net. One end of the towing rope is connected to the ammunition simulator, and the other end passes through the blocking net and is connected to the launch driving assembly after being transferred through the pulley block.

[0008] Furthermore, a photoelectric switch sensor for measuring the exit velocity is installed on the inner wall of the barrel simulator near the exit of the barrel simulator.

[0009] Furthermore, the launch driving assembly includes a driving cylinder and a cut-off cylinder. The driving cylinder is connected to a gas cylinder, and the piston rod of the driving cylinder is connected to the towing rope. There is a pin hole on the piston rod of the driving cylinder for the piston rod of the cut-off cylinder to pass through. When the driving cylinder is in a fully extended state, the piston rod of the cut-off cylinder is inserted into the pin hole; the piston rod of the cut-off cylinder releases the piston rod of the driving cylinder when the driving cylinder reaches the specified driving force.

[0010] Furthermore, a support seat is arranged in front of the cut-off cylinder. There are two lifting lugs on the support seat for the piston rod of the cut-off cylinder to pass through, and the piston rod of the driving cylinder is located between the two lifting lugs.

[0011] Furthermore, the pulley block includes a first fixed pulley installed on the blocking frame and a second fixed pulley located below the first fixed pulley. The towing rope is connected to the launch driving assembly after passing through the first fixed pulley and the second fixed pulley in sequence. The height of the second fixed pulley is lower than the lowest height of the launcher simulator, and the towing rope between the first fixed pulley and the ammunition simulator is on the same straight line as the central axis of the launcher simulator.

[0012] Furthermore, the blocking frame includes a vertical frame and a horizontal frame on one side of the vertical frame. A column is arranged on the other side of the vertical frame. The blocking net is installed on the vertical frame, the cushion is installed on the horizontal frame, and the pulley block is installed on the column.

[0013] Furthermore, baffles corresponding to the first fixed pulley and the second fixed pulley one by one are fixed on the column, and the baffles are located on the side of each fixed pulley away from the vertical frame.

[0014] Furthermore, the launch rack is located between the launch driving member and the blocking frame.

[0015] Furthermore, fences are arranged on both sides of the horizontal frame.

[0016] Furthermore, a triangular support is also installed on the side of the vertical frame where the column is installed.

[0017] The beneficial effects of the utility model are:

[0018] (1) In this utility model, the simulated launcher tube, the launch drive assembly, and the projectile pad are all arranged on the same side of the interception net. During the test work, both the drive component and the simulated ammunition launched only move on one side of the interception net, and the other side of the interception net is a safe area, which can be used as the working area for the staff, with relatively high safety.

[0019] (2) In the launch drive assembly of this utility model, the launch driving force is provided by a cylinder, and a cut-off cylinder is used to control the movement timing of the piston rod of the drive cylinder, so that the corresponding pressure can be adjusted according to the specific launch requirements, which matches the actual launch. The test accuracy is higher, and it can be used for the launch tube test with higher impact force. Description of the Drawings

[0020] The following further describes this utility model in conjunction with the drawings and embodiments.

[0021] Figure 1 is a perspective view of the specific implementation manner of the launcher tube friction test device described in this utility model;

[0022] Figure 2 is Figure 1 the top view of

[0023] Figure 3 is Figure 2 the enlarged view at position a of

[0024] Figure 4 is Figure 2 the sectional view taken along the A-A direction of

[0025] Figure 5 is Figure 4 the enlarged view at position b of

[0026] In the figure, 1. Simulated launcher tube, 101. Simulated barrel, 102. Simulated ammunition, 2. Launch rack, 3. Interception rack, 301. Vertical frame, 302. Horizontal frame, 303. Column, 304. Fence, 305. Triangular support, 4. Launch drive assembly, 401. Drive cylinder, 402. Cut-off cylinder, 403. Gas cylinder, 404. Piston rod, 405. Support seat, 406. Lifting lug, 5. Interception net, 6. Projectile pad, 7. Pulley block, 701. First fixed pulley, 702. Second fixed pulley, 8. Ejection port, 9. Towing rope, 10. Baffle. Specific Implementation Manner

[0027] The embodiments of the present invention are described in detail below, and examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and cannot be understood as limiting the present invention.

[0028] Embodiment 1

[0029] like Figures 1-4 As shown, a launch tube friction force test device includes a launch tube simulation 1, a launch rack 2, an arresting rack 3, and a launch drive assembly 4. The launch tube simulation 1 is placed on the launch rack 2; the launch tube simulation 1 includes a barrel simulation 101 and an ammunition simulation 102 located inside the barrel simulation 101. The launch rack 2 is used to support and fix the launch tube simulation 1 so that the launch tube simulation 1 is at a certain launch angle. The launch drive assembly 4 is used to provide launch power for the ammunition simulation 102.

[0030] It should be noted that, in order to ensure the authenticity of the test results, the shape, size, and weight of the ammunition simulation part 102 should be consistent with the shape, size, and weight of the real ammunition to be simulated, and especially the center of gravity distribution should be consistent. The barrel simulation part 101 should be consistent with the shape and size of the real barrel to be simulated, and especially the shape and size of the inner cavity of the real barrel should be consistent.

[0031] The blocking frame 3 is equipped with a blocking net 5 and a horizontally arranged spring pad 6 for intercepting the fired ammunition simulation 102. After being fired, the ammunition simulation 102 collides with the blocking net 5 and finally falls onto the spring pad 6. The launch tube simulation 1, the launch drive assembly 4 and the spring pad 6 are located on the same side of the blocking net 5. The blocking frame 3 located on the other side of the blocking net 5 is provided with a pulley block 7. One end of the traction rope 9 is connected to the ammunition simulation 102, and the other end passes through the blocking net 5 and is connected to the launch drive assembly 4 after being transferred by the pulley block 7. The blocking net 5 is a mesh structure (the mesh structure is not shown in the attached figure), which can intercept the ammunition simulation 102, but can allow the traction rope 9 to pass through. The launch tube simulation 1 and the launch drive assembly 4 are the main moving parts and have large kinetic energy. Therefore, there are safety hazards in the area where they are located. The utility model arranges the launch tube simulation 1, the launch drive assembly 4 and the spring pad 6 on the same side of the blocking frame 3, that is, Figure 4 The left side area of the barrier frame 3 in the middle, and the other side of the barrier frame 3 (i.e. Figure 4 The right side area of the barrier frame 3 in the figure has no moving parts, only a sliding group for transmission, so this area is a safe area, and the staff can perform testing work in this area with higher safety.

[0032] For convenience of description, in the present utility model, the horizontal sub-direction of the ejection direction of the ammunition simulation part 102 is taken as the front, the direction opposite thereto is taken as the rear, and the direction perpendicular to the front-rear direction and extending along the plane is taken as the left-right direction.

[0033] For obtaining test data, the present utility model can adopt the same method as that in the application No. CN201710658247.6, that is, a plurality of groups of photoelectric switch sensors are used to collect the time when the ammunition simulation part 102 passes through different points, so as to calculate the ejection speed of the ammunition simulation part 102. The present utility model can arrange the photoelectric switch sensors on the inner wall of the barrel simulation part 101 close to the ejection port 8 of the barrel simulation part 101, so that the detected result can better reflect the ejection speed of the ammunition simulation part 102.

[0034] In order to make the launch impact force match more real missile launch situations, the present utility model changes the driving part that traditionally provides instantaneous impact force by means of elastic force into a driving part that can directly provide instantaneous impact force. Specifically, the following structure can be adopted: as Figures 1-3 shown, the launch driving assembly 4 includes a driving cylinder 401 and a cut-off cylinder 402. The driving cylinder 401 is connected with a gas cylinder 403. The piston rod 404 of the driving cylinder 401 is connected with a traction rope 9. A pin hole for the piston rod 404 of the cut-off cylinder 402 to pass through is provided on the piston rod 404 of the driving cylinder 401. When the driving cylinder 401 is in a fully extended state, the piston rod 404 of the cut-off cylinder 402 is inserted into the pin hole; the piston rod 404 of the cut-off cylinder 402 releases the piston rod 404 of the driving cylinder 401 when the driving cylinder 401 reaches the specified driving force.

[0035] The driving cylinder 401 provides power for the launch of the launch tube simulation part 1. The cut-off cylinder 402 is used to fix the piston rod 404 of the driving cylinder 401 when not launched. The piston rod 404 of the driving cylinder 401 is in an extended state in the initial state. The gas cylinder 403 is used to inflate the rod chamber in the driving cylinder 401. Appropriate high-pressure gas can be filled into the driving cylinder 401 according to the launch impact force requirement. After the inflation is completed, the piston rod 404 of the cut-off cylinder 402 is retracted to be separated from the piston rod 404 of the driving cylinder 401, and the piston rod 404 of the driving cylinder 401 instantaneously retracts, thereby driving the traction rope 9 to move quickly and providing ejection power for the ammunition simulation part 102.

[0036] As Figure 2 and Figure 3 shown, the cut-off cylinder 402 is located in front of the driving cylinder 401. The piston rod 404 of the driving cylinder 401 extends along the front-rear direction, and the piston rod 404 of the cut-off cylinder 402 extends along the left-right direction. Connecting the piston rods 404 of the cut-off cylinder 402 and the driving cylinder 401 through the pin hole can ensure the connection strength and can resist the retraction power of the piston rod 404 of the larger driving cylinder 401.

[0037] The pulley block 7 includes at least two pulleys. For example, Figure 4 as shown, the simplest form includes a first fixed pulley 701 installed on the blocking frame 3 and a second fixed pulley 702 located below the first fixed pulley 701. The traction rope 9 passes through the first fixed pulley 701 and the second fixed pulley 702 in sequence and then is connected to the launch drive assembly 4. The height where the second fixed pulley 702 is located is lower than the lowest height of the launch tube simulator 1. The traction rope 9 between the first fixed pulley 701 and the ammunition simulator 102 is on the same straight line as the central axis of the launch tube simulator 1. The first fixed pulley 701 is used to axially pull out the ammunition simulator 102, and the second fixed pulley 702 guides the traction rope 9 to the height where the driving cylinder 401 is located. The traction rope 9 between the second fixed pulley 702 and the driving cylinder 401 is at the lowest position of the entire device and will not interfere with the installation of other components and the movement of the ammunition simulator 102. In other alternative embodiments, other pulleys for transfer can also be provided between the first fixed pulley 701 and the second fixed pulley 702 to meet different transmission requirements.

[0038] The blocking frame 3, as the installation component of the blocking net 5, the cushion 6, and the pulley block 7, can specifically adopt the following structure, including a vertical frame 301 and a horizontal frame 302 located on one side of the vertical frame 301. A column 303 is provided on the other side of the vertical frame 301. The blocking net 5 is installed on the vertical frame 301, the cushion 6 is installed on the horizontal frame 302, and the pulley block 7 is installed on the column 303. For example, Figure 1 and Figure 2 as shown, there are two columns 303. The first fixed pulley 701 is located above, and the second fixed pulley 702 is directly below the first fixed pulley 701. Both ends of the connecting shaft of the two fixed pulleys are connected to the two columns 303. The two columns 303 are arranged in mirror symmetry, and the symmetry plane is in the same plane as the central axis of the launch tube simulator 1 and the launch drive assembly 4. The connection path of the traction rope 9 is located in this plane, which can prevent the traction rope 9 from being pulled by a lateral force when being pulled, resulting in the traction rope 9 detaching from the fixed pulley or causing the movement direction of the ammunition simulator 102 to deviate.

[0039] To prevent the ammunition simulator 102 from popping out to the left and right after falling onto the cushion 6, preferably, fences 304 are provided on both sides of the horizontal frame 302.

[0040] Embodiment 2

[0041] In order to further improve the strength of the piston rod 404 of the cut-off cylinder 402 and prevent the piston rod 404 of the cut-off cylinder 402 from being bent by the force, the following improvements are made in this embodiment on the basis of Embodiment 1: For example, Figure 3As shown in the figure, a support base 405 is provided in front of the cut-off cylinder 402. There are two lugs 406 on the support base 405 through which the piston rod 404 of the cut-off cylinder 402 passes. The piston rod 404 of the driving cylinder 401 is located between the two lugs 406. Here, the front of the cut-off cylinder 402 refers to the direction in which the piston rod 404 of the cut-off cylinder 402 extends. The lugs 406 play a role in supporting and positioning the piston rod 404 of the cut-off cylinder 402, preventing the piston rod 404 of the cut-off cylinder 402 from bending or even breaking.

[0042] Embodiment III

[0043] On the basis of the above embodiments, in order to further improve the safety of the area in front of the blocking frame 3, in this embodiment, a baffle 10 corresponding to the first fixed pulley 701 and the second fixed pulley 702 is fixed on the upright column 303. The baffle 10 is located on the side of each fixed pulley away from the vertical frame 301. As Figure 5 shown in the figure, baffles 10 are provided in front of both the first fixed pulley 701 and the second fixed pulley 702 to prevent the first fixed pulley 701 or the second fixed pulley 702 from falling off and flying out, causing injury to the staff.

[0044] Embodiment IV

[0045] In the above embodiments, there are many structures and relatively large mass behind the vertical frame 301 of the blocking frame 3. After the blocking frame 3 is impacted by the ammunition simulation part 102, it is easy to collapse. Therefore, in this embodiment, a triangular support 305 is also installed on the side of the vertical frame 301 where the upright column 303 is installed. The triangular support 305 can coordinate with the horizontal frame 302 to make the structure of the blocking frame 3 more stable and have stronger impact resistance.

[0046] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "center", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "inner", "outer", "axial", etc. is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present invention.

[0047] In addition, the terms "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0048] In this specification, the schematic description of the terms does not necessarily refer to the same embodiment. Moreover, the specific features, structures, materials or characteristics described can be combined in a suitable manner in any one or more embodiments.

[0049] Based on the above-mentioned ideal embodiments of the present utility model as inspiration, through the above description, relevant staff can completely make various changes and modifications without departing from the technical idea of this utility model. The technical scope of this utility model is not limited to the content in the specification, and its technical scope must be determined according to the scope of the claims.

Claims

1. A friction force test device for a launcher tube, characterized in that: It includes a launch tube simulation, a launch stand, an arresting stand, and a launch drive assembly, wherein the launch tube simulation is placed on the launch stand; the launch tube simulation includes a tube body simulation and an ammunition simulation located inside the tube body simulation; The blocking frame is equipped with a blocking net and a horizontally arranged spring pad for intercepting the fired ammunition simulation. The launch tube simulation, the launch drive assembly and the spring pad are located on the same side of the blocking net. A pulley block is provided on the blocking frame on the other side of the blocking net. One end of the traction rope is connected to the ammunition simulation, and the other end passes through the blocking net and is connected to the launch drive assembly after being transferred by the pulley block.

2. The friction force test device for the launcher tube according to claim 1, wherein: A photoelectric switch sensor for measuring the ejection speed is installed on the inner wall of the cylinder simulation part near the ejection port of the cylinder simulation part.

3. The friction force test device for the launcher tube according to claim 1, wherein: The launch drive assembly includes a driving cylinder and a cut-off cylinder, the driving cylinder is connected to a gas cylinder, the piston rod of the driving cylinder is connected to a traction rope, the piston rod of the driving cylinder is provided with a pin hole for the piston rod of the cut-off cylinder to pass through, when the driving cylinder is in a fully extended state, the piston rod of the cut-off cylinder is inserted into the pin hole; the piston rod of the cut-off cylinder releases the piston rod of the driving cylinder when the driving cylinder reaches a specified driving force.

4. The friction force test device for the launcher tube according to claim 3, wherein: A support seat is arranged in front of the cut-off cylinder. The support seat is provided with two lifting ears for the piston rod of the cut-off cylinder to pass through. The piston rod of the driving cylinder is located between the two lifting ears.

5. The friction force test device for the launcher tube according to claim 1, characterized in that: The pulley group includes a first fixed pulley installed on the blocking frame and a second fixed pulley located below the first fixed pulley. The traction rope is connected to the launch drive assembly after passing through the first fixed pulley and the second fixed pulley in sequence. The height of the second fixed pulley is lower than the lowest height of the launch tube simulation. The traction rope between the first fixed pulley and the ammunition simulation is in the same straight line as the central axis of the launch tube simulation.

6. The launcher friction test device according to claim 5, characterized in that: The blocking frame includes a vertical frame and a horizontal frame located on one side of the vertical frame, a column is arranged on the other side of the vertical frame, the blocking net is installed on the vertical frame, the spring pad is installed on the horizontal frame, and the pulley block is installed on the column.

7. The launcher friction test device according to claim 6, wherein: Baffles corresponding to the first fixed pulley and the second fixed pulley are fixed on the column, and the baffles are located on a side of each fixed pulley away from the vertical frame.

8. The test device for the friction force of the launcher tube according to claim 1, wherein: The launching frame is located between the launching drive component and the blocking frame.

9. The launcher friction test device according to claim 6, characterized in that: Fences are arranged on both sides of the horizontal frame.

10. The launcher friction test device according to claim 6, wherein: A triangular support is also installed on one side of the vertical frame installation column.

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