Multi-assembly dense emission shock absorbing mechanism

Abstract

The application provides a multi-assembly dense launching shock damping mechanism in the technical field of missile launching device, which comprises a launching cylinder, a launching frame, a damper and a damping pad. The damper is arranged between the top of the launching cylinder and the top of the launching frame, and the launching frame is flexibly connected with the launching cylinder through the damper. The damping pad is arranged between the bottom of the launching frame and the bottom of the launching cylinder, and the launching frame is flexibly connected with the missile through the damping pad. A guide block is mounted on one side of the outer wall of the launching cylinder, a cross beam is arranged on the launching frame, and a guide pin is mounted on the cross beam. The launching cylinder and the launching frame are flexibly connected, so that the impact vibration of the missile launching is avoided from being transmitted to the adjacent missile through the launching frame, and the launching precision of the next missile is affected. The guide block and the guide pin are used in cooperation, so that the positioning precision of the missile in the horizontal direction is realized, and the up-and-down jumping of the missile in the shooting direction is not restricted.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of missile launching device, in particular to a multi-assembly dense launching shock damping mechanism. BACKGROUND

[0002] In a multi-assembly dense launching mode, two main shocks occur during the launching process. In the first stage, the boost engine at the tail of the missile body is started to push the missile body along the launching cylinder. The hot gas flow generated by the boost engine causes an impact on the launching cylinder base. The gas expands due to heating, causing the cylinder wall to elongate, and the launching cylinder base to move downward. In the second stage, the missile body climbs upward along the launching cylinder, breaks through the launching cylinder cover, and flies out of the launching cylinder. When the boost engine at the tail of the missile body rises to the launching cylinder port, it is blocked by the braking mechanism at the cylinder port and is separated from the missile body, and is trapped in the cylinder. The boost engine hits the braking mechanism, which causes an upward impact on the launching cylinder, causing the launching cylinder to jump upward.

[0003] It is a common practice to assemble multiple missiles on a launching rack for dense launching, which causes the shock and vibration of the previous missile launch to affect the launch of the next adjacent missile. To reduce the impact of the shock on the missile in the multi-assembly dense launching device, there are two common methods. One is to enhance the anti-shock capability of the launching rack and the launching cylinder, which resists the launching shock and quickly absorbs the shock and vibration caused by the launching. This results in a heavy structure of the launching rack and the launching cylinder. The other is to set a missile rack unlocking and switching mechanism. The missile rack is separated during launching and locked during transportation. This requires the launching device to be equipped with a missile rack unlocking and switching mechanism, resulting in a complex composition of the launching device and a decrease in reliability.

[0004] Through prior art retrieval, it is found that Chinese invention patent No. CN111426242B discloses a missile fixing mechanism, which comprises a base, a connecting rod structure, a reset structure and a starting device. A limiting block is arranged on the connecting rod structure. The missile is arranged on the base, and the axis of the missile is parallel to the base. The missile fixing mechanism comprises a locked state and an unlocked state. When the missile fixing mechanism is in the locked state, the limiting block is connected to the end face of the missile. When the missile fixing mechanism is in the unlocked state, the limiting block is separated from the end face of the missile, and in the radial direction of the missile, the limiting block is located outside the outer surface of the missile. The missile fixing mechanism can be switched from the locked state to the unlocked state under the action of the starting device, and the connecting rod structure can be reset under the action of the reset structure. The invention patent has the above-mentioned need to equip the launching device with a missile rack unlocking and switching mechanism, resulting in a complex composition of the launching device and a decrease in reliability. SUMMARY

[0005] In view of the defects in the prior art, the purpose of the present application is to provide a multi-assembly dense launching shock damping mechanism.

[0006] The application provides a multiple-launch dense launching shock-absorbing mechanism, which comprises a launching barrel, a launching frame, a shock absorber and a shock-absorbing pad.

[0007] The launching barrel is arranged in the launching frame, the shock absorber is arranged between the top of the launching barrel and the top of the launching frame, and the launching frame is flexibly connected to the launching barrel through the shock absorber.

[0008] The launching barrel stores missiles, and the shock absorber is used for buffering the shock of the missiles when the missiles are launched and the shock is transmitted to the adjacent missiles through the launching frame.

[0009] The shock-absorbing pad is arranged between the bottom of the launching frame and the bottom of the launching barrel, and the launching frame is flexibly connected to the missiles through the shock-absorbing pad.

[0010] The shock-absorbing pad is used for supporting the bottom of the launching barrel, and the shock-absorbing pad is used for buffering the expansion and elongation of the bottom of the launching barrel and the shock of the bottom of the launching frame.

[0011] One side of the outer wall of the launching barrel is provided with a guide block, the launching frame is provided with a cross beam, and the cross beam is provided with a guide pin.

[0012] The guide block and the guide pin are arranged in pairs and are used for positioning the horizontal direction of the launching barrel, and the guide block and the cross beam are arranged in pairs and do not limit the up-and-down jumping of the launching barrel in the direction of the launching.

[0013] In some embodiments, the shock absorber comprises a spring, and the spring is arranged around the outer wall of the top-end barrel of the launching barrel.

[0014] In some embodiments, the upper end of the shock absorber is provided with an upper flange, and the lower end of the shock absorber is provided with a lower flange.

[0015] In some embodiments, one end of the spring is connected to the bottom surface of the upper flange, and the other end of the spring is connected to the top surface of the lower flange.

[0016] In some embodiments, the upper flange is provided with an opening, the upper flange is gap-fitted with the top-end barrel of the launching barrel through the opening, and the upper flange reciprocates up and down with the spring.

[0017] In some embodiments, the outer wall of the launching barrel is provided with a flange, and the flange is connected to the upper flange through a screw.

[0018] In some embodiments, the lower flange is connected to the top of the launching frame through a screw.

[0019] In some embodiments, the guide pin is connected to the cross beam through a screw.

[0020] In some embodiments, the number of the launching tubes is multiple, and the launching tubes are arranged side by side in the launching frame.

[0021] In some embodiments, the damping pad is a polyurethane damping pad.

[0022] Compared with the prior art, the present application has the following beneficial effects:

[0023] 1. The flexible connection between the launching tube and the launching frame avoids the impact vibration of the missile launching from being transmitted to the adjacent missile through the launching frame, thereby affecting the launching precision of the next missile.

[0024] 2. The two flexible links of the damper and the damping pad are arranged to attenuate the impact in two stages during the launching process.

[0025] 3. The guide block and the guide pin are used in cooperation to realize the positioning precision of the missile in the horizontal direction without restricting the up-and-down jumping of the missile in the shooting direction under the condition of the flexible connection between the launching tube and the launching frame. BRIEF DESCRIPTION OF DRAWINGS

[0026] Other features, objects and advantages of the present application will become more apparent from the following detailed description of non-limiting embodiments with reference to the attached drawings:

[0027] Figure 1 It is a structure front view of the multi-assembly dense launching impact damping mechanism of the present application.

[0028] Figure 2 It is a structure side view of the multi-assembly dense launching impact damping mechanism of the present application.

[0029] Figure 3 It is a damper front view of the multi-assembly dense launching impact damping mechanism of the present application.

[0030] Figure 4 It is a damper top view of the multi-assembly dense launching impact damping mechanism of the present application.

[0031] Figure 5 It is a schematic top view of the cooperation of the guide block and the guide pin of the multi-assembly dense launching impact damping mechanism of the present application.

[0032] Figure 6 It is a schematic sectional view of the cooperation of the guide block and the guide pin of the multi-assembly dense launching impact damping mechanism of the present application.

[0033] Reference signs:

[0034] Launching tube 1 Spring 7

[0035] Launching frame 2 Lower flange 8

[0036] Damper 3 Guide block 9

[0037] 4 vibration damping pads and 10 guide pins

[0038] Flange 5, Beam 11

[0039] Upper flange 6, opening 12 Detailed Implementation

[0040] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0041] Example 1

[0042] like Figure 1 As shown, the present invention includes a launch tube 1, a launch frame 2, a vibration damper 3, and a vibration damping pad 4. The launch tube 1 is disposed inside the launch frame 2, and the vibration damper 3 is disposed between the top of the launch tube 1 and the top of the launch frame 2. The launch frame 2 is flexibly connected to the launch tube 1 through the vibration damper 3. The launch tube 1 stores missiles, and the vibration damper 3 is used to buffer the impact transmitted through the launch frame 2 to adjacent missiles during missile launch.

[0043] like Figure 1 As shown, the launch tube 1 is installed inside the launch frame 2, and the vibration damping pad 4 is installed between the bottom of the launch frame 2 and the bottom of the launch tube 1. The launch frame 2 is flexibly connected to the missile through the vibration damping pad 4. The vibration damping pad 4 is used to support the bottom of the launch tube 1 and to buffer the impact of the expansion and extension of the bottom of the launch tube 1 on the bottom of the launch frame 2.

[0044] like Figure 2 As shown, the launch tube 1 is installed inside the launch frame 2. A guide block 9 is installed on one side of the outer wall of the launch tube 1. A crossbeam 11 is installed on the launch frame 2, and a guide pin 10 is installed on the crossbeam 11. The guide block 9 and the guide pin 10 are paired and matched to ensure the horizontal accuracy of the launch tube 1, and the pairing of the guide block 9 and the crossbeam 11 does not restrict the vertical movement of the launch tube 1 in the firing direction.

[0045] Working principle:

[0046] During the intensive launch of multiple missiles, there are two main impacts in the launch process. In the first stage, the booster engine at the tail of the missile body starts, and the engine tail generates a downward hot airflow. The force of the hot airflow propels the missile body along the launch tube 1, and the reaction force impacts the base of the launch tube 1. In addition, the gas inside the tube expands due to heat, causing the tube wall to elongate and the base of the launch tube to displace downward. At this time, the vibration damping pad 4 is compressed to buffer the impact of this stage.

[0047] In the second stage, the missile body climbs along the launching barrel 1 upward and flies out of the launching barrel 1, but when the boost engine at the tail of the missile body rises to the barrel mouth of the launching barrel 1, the boost engine is blocked by the brake mechanism at the barrel mouth and is separated from the missile body and is trapped in the barrel, and the boost engine hits the brake mechanism, which causes an upward impact on the launching barrel 1 and drives the launching barrel 1 to produce an upward jumping displacement, at this time, the damper 3 is stretched and buffers the impact in this stage. In the impact process, the pin hole cooperation length needs to ensure that the missile bouncing caused by vibration meets the requirements.

[0048] In the description of the present application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application.

[0049] The specific embodiments of the present application are described above. It should be understood that the present application is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essential content of the present application. The embodiments of the present application and the features in the embodiments can be arbitrarily combined with each other without conflict.

Claims

1. A multiple-pack concentrated launch shock absorbing mechanism, characterized by, It comprises a launching barrel (1), a launching frame (2), a damper (3) and a damping pad (4); The launching barrel (1) is arranged in the launching frame (2), the damper (3) is arranged between the top of the launching barrel (1) and the top of the launching frame (2), and the launching frame (2) is flexibly connected to the launching barrel (1) through the damper (3); The launching barrel (1) stores a missile, and the damper (3) is used for buffering the impact of the missile transmission through the launching frame (2) to the adjacent missile during launching; The damping pad (4) is arranged between the bottom of the launching frame (2) and the bottom of the launching barrel (1), and the launching frame (2) is flexibly connected to the missile through the damping pad (4); The damping pad (4) is used for supporting the bottom of the launching barrel (1), and the damping pad (4) is used for buffering the impact of the bottom of the launching barrel (1) expanding and extending on the bottom of the launching frame (2); A guide block (9) is arranged on one side of the outer wall of the launching barrel (1), a cross beam (11) is arranged on the launching frame (2), and a guide pin (10) is arranged on the cross beam (11); The guide block (9) and the guide pin (10) are arranged in pairs to position the horizontal direction of the launching barrel (1) with high accuracy, and the guide block (9) and the cross beam (11) are arranged in pairs to limit the up-down bouncing of the launching barrel (1) in the direction of the launching barrel (1).

2. The multi-pack concentrated launch shock absorbing mechanism according to claim 1, characterized by, The damper (3) comprises a spring (7) arranged around the top end of the barrel (1).

3. The multiple-pack concentrated launch shock absorbing mechanism according to claim 2, characterized by, An upper flange (6) is arranged at the upper end of the damper (3), and a lower flange (8) is arranged at the lower end of the damper (3).

4. The multi-pack concentrated launch shock absorbing mechanism according to claim 3, characterized by, One end of the spring (7) is connected to the bottom surface of the upper flange (6), and the other end of the spring (7) is connected to the top surface of the lower flange (8).

5. The multiple-pack concentrated launch shock absorbing mechanism according to claim 4, characterized by, An opening (12) is arranged on the upper flange (6), the upper flange (6) is gap-fitted with the top end of the barrel (1) through the opening (12), and the upper flange (6) reciprocates with the spring (7) up and down.

6. The multiple-pack concentrated launch shock absorbing mechanism according to claim 3, wherein A flange (5) is arranged on the outer wall of the launching barrel (1), and the flange (5) is connected to the upper flange (6) through screws.

7. The multiple-pack concentrated launch shock absorbing mechanism according to claim 3, wherein The lower flange (8) is connected to the top of the launching frame (2) through screws.

8. The multi-pack compact launch shock mitigation mechanism of claim 1, wherein, The guide pin (10) is connected to the cross beam (11) through screws.

9. The multiple-pack concentrated launch shock absorbing mechanism according to claim 1, wherein The number of the launching barrels (1) is multiple, and they are arranged side by side in the launching frame (2).

10. The multi-pack concentrated launch shock absorbing mechanism according to claim 1, wherein, The damping pad (4) is a polyurethane damping pad.

Images