A missile transport and clamping mechanism

Abstract

The present invention discloses a missile transport clamping mechanism, which belongs to the field of missile transport equipment and solves the technical problem that existing missile transfer vehicles have limited axial fixing capabilities for large missiles when transporting missiles. It includes a pressure plate and a support arm structure conveniently connected to the pressure plate, wherein the support arm structure includes an adjusting rod, a support arm, and a strut, wherein the strut is a hollow rod, one end of the adjusting rod is inserted into a hole in the middle of the strut, and the other end is connected to the support arm; the strut, the support arm, and the support seat are conveniently connected; the support seat structure includes a support seat, a shaft sleeve fastened to the support seat, and a pin connected to the shaft sleeve through a bearing system; by flexibly adjusting the support arm structure and the support seat structure, reliable fixing of the missile during transportation is achieved. The missile transport clamping mechanism of the present invention can be better used for the transportation and loading and unloading of missiles, has a wide range of applications, high transportation efficiency, and is easy to use.

Description

Technical Field

[0001] The invention relates to a pressing mechanism, in particular to a missile transport pressing mechanism, and belongs to the field of missile transport equipment. Background Art

[0002] The applicant has discovered that the prior art has at least the following technical problems:

[0003] A missile is an aircraft that carries a warhead, is propelled by its own power plant, and is guided and controlled by a guidance system to navigate and destroy its target. In military missile manufacturing, finished missiles are typically stored in missile packaging boxes and then transported by missile transport vehicles. To ensure safety during missile transportation, high stability requirements are imposed on the missiles during transport.

[0004] Currently, existing missile transport vehicles typically use compression straps to secure missiles to the transporter. However, when transporting large missiles, the compression straps have limited axial securing capabilities, requiring mechanical compression to reliably secure the missiles in both the axial and radial directions. Given the wide variety of missiles available, transporting different missile models requires replacing different compression devices, increasing transportation costs and creating significant inconvenience. Summary of the Invention

[0005] The purpose of the present invention is to provide a missile transport compacting mechanism to solve the technical problem in the prior art of inconvenience in transporting missiles of different models.

[0006] To achieve the above-mentioned objectives, the present invention provides the following technical solutions: a missile transport clamping mechanism, comprising a pressure plate, a support arm mechanism connected to the pressure plate, and a support seat structure for supporting and fixing; the support arm structure comprises a support arm that plays a main supporting role and an adjustment rod and a support rod for auxiliary adjustment; one end of the support arm is movably connected to the pressure plate, and an extension section for interacting with the adjustment rod is also provided on the pressure plate; the adjustment rod is movably connected to the support rod; the support seat structure comprises a support seat and a rotating structure connected to the support seat.

[0007] Optionally or preferably, the pressure plate is wrapped with a soft material layer for protecting the contact position with the missile.

[0008] Optionally or preferably, there is a accommodating cavity inside the support rod, one end of the adjusting rod is movably connected to the pressure plate extension section, and the other end is nested inside the support rod, and a locking device is provided at the contact position between the support rod and the adjusting rod.

[0009] Optionally or preferably, the locking device is a locking nut.

[0010] Optionally or preferably, the rotating structure is a rotating bearing that enables the device body to rotate along the vertical plane direction and a pin that enables the support seat and the structure above the support seat to rotate in the horizontal plane direction, and a No. 2 bearing cover is provided at the upper end of the pin; a No. 1 bearing cover is provided on one side of the rotating bearing, and a fixing device is connected to the other side, and a shaft sleeve is provided on the outside.

[0011] Optionally or preferably, a sealing ring is radially installed between the second bearing cover and the shaft sleeve.

[0012] Optionally or preferably, the shaft sleeve is movably connected via a No. 1 tapered roller bearing and a No. 2 tapered roller bearing.

[0013] The missile transport and clamping mechanism of the present invention can be better used for the transportation and loading and unloading of missiles, has a wide range of applications, high transport efficiency, is easy to use, and effectively reduces the transportation cost of missiles.

[0014] Based on the above technical solution, the embodiments of the present invention can produce at least the following technical effects:

[0015] The missile transport clamping mechanism provided by the present invention securely presses a pressure plate against the curved surface of a missile by adjusting the position of the support arm and the locking nut, thereby reliably securing the missile. This mechanism can also accommodate the transport of different missile models, improving transportation efficiency and reducing transportation costs. The contact portion between the mechanical arm and the missile utilizes a pressure plate made of soft rubber, enhancing the safety and stability of the missile during transport. During missile installation, the clamping mechanism is secured to the missile support beam with screws. During missile hoisting, the entire clamping mechanism can be rotated between a horizontal and vertical position by rotating the support base structure to prevent collision between the clamping mechanism and the missile, facilitating missile loading and unloading and improving transportation efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Attachment Figure 1 It is the axial side view of the clamping mechanism;

[0017] Attachment Figure 2 This is the main view of the clamping mechanism;

[0018] Attachment Figure 3 It is the AA cross-sectional view of the pressing mechanism;

[0019] Attachment Figure 4 It is the working condition 1 of the clamping mechanism;

[0020] Attachment Figure 5 This is working condition 2 of the clamping mechanism.

[0021] In the figure: 1. Pressure plate; 2. Quick release pin No. 1; 3. Quick release pin No. 2; 4. Adjusting rod; 5. Locking device; 6. Support arm; 7. Strut; 8. Quick release pin No. 3; 9. Quick release pin No. 4; 10. Support seat; 11. Quick release pin No. 5; 12. Pin shaft; 13. Bushing; 14. Bearing cover No. 1; 15. Bearing cover No. 2; 16. Tapered roller bearing No. 1; 17. Tapered roller bearing No. 2; 18. Small round nut. DETAILED DESCRIPTION

[0022] The present invention will be further described below with reference to the accompanying drawings.

[0023] See also Figures 1 to 5 , the pressure plate 1 is conveniently connected to the support arm structure. The support arm structure includes an adjusting rod 4, a support arm 6 and a strut 7, wherein the strut 7 is in the form of a hollow rod. One end of the adjusting rod 4 is inserted into the hole in the middle of the strut 7, and the other end is connected to the support arm 6 through a No. 2 quick-release pin 3; the locking device 5 adopts a locking nut to achieve reliable locking, and the adjusting rod 4 can be reliably locked on the strut 7 through the locking nut. The strut 7 is connected to the support base 10 through a No. 4 quick-release pin 9; the support arm 6 and the support base 10 are connected through a No. 3 quick-release pin 8;

[0024] The support seat 10 is fastened to the sleeve 13 by screws, and the sleeve 13 is connected to the pin 12 through the No. 1 tapered roller bearing 16, the No. 2 tapered roller bearing 17 and the small round nut 18. The sleeve 13 can rotate freely around the pin 12 through the No. 1 tapered roller bearing 16 and the No. 2 tapered roller bearing 17. In order to limit the rotation of the sleeve 13 around the pin 12 in the horizontal and vertical positions, holes for installing fixed components are provided on the sleeve 13 and the periphery of the pin 12, which can also be quickly fixed by quick-release pins; the No. 1 bearing cover 14 is fastened to the sleeve 13 by screws; the No. 2 bearing cover 15 is fixed to the pin 12 by screws.

[0025] As an optional embodiment, the pressure plate 1 can rotate freely around the connection point with the support arm structure, and the contact portion between the pressure plate 1 and the missile is made of soft material.

[0026] In this embodiment, the pressure plate 1 is conveniently connected to the support arm 6 through the No. 1 quick-release pin 2, and the pressure plate 1 can be rotated a certain angle around the hinge point connected to the No. 1 quick-release pin 2 to adapt to the fixation of different types of missiles; the contact part between the pressure plate 1 and the missile is made of soft rubber material, which plays an effective fixing and protection role during the transportation of the missile.

[0027] As an optional embodiment, the adjusting rod 4 is securely locked on the strut 7 by the locking device 5 or is free to slide in the strut 7 .

[0028] In this embodiment, the adjusting rod 4 is reliably locked on the strut 7 or slides freely in the strut 7 through the locking device 5. The adjusting rod 4 is in the form of a screw and the locking device 5 is two locking nuts. When the locking nuts are not tightened, the adjusting rod 4 can slide freely on the strut. At this time, the pressure plate 1 is not affected by the adjusting rod 4 and can still rotate freely around the hinge point connected to the No. 1 quick-release pin 2; after the locking nut is tightened, the adjusting rod 4 is reliably locked on the strut 7, and the pressure plate 1 will be partially affected by the adjusting rod 4. After the inner arc surface of the pressure plate 1 completely contacts the missile, the pressure plate 1 will be reliably pressed on the arc surface of the missile under the action of the force arm, thereby achieving reliable fixation of the missile.

[0029] As an optional embodiment, the upper portion of the support base 10 can swing freely.

[0030] In this embodiment, the portion above the support base 10 can swing freely. During the loading and unloading process of the missile, the support arm 6 can be adjusted to a horizontal or vertical position as the support base 10 rotates, which facilitates the loading and unloading of the missile and avoids unnecessary bumps.

[0031] As an optional embodiment, the sleeve 13 can rotate freely around the pin 12 through a bearing system, and the sleeve 13 can be fixed by providing a fixing device around the sleeve 13 and the pin 12.

[0032] In this embodiment, the sleeve 13 is connected to the pin 12 through the No. 1 tapered roller bearing 16, the No. 2 tapered roller bearing 17 and the small round nut 18. The sleeve 13 can rotate freely around the pin 12 through the No. 1 tapered roller bearing 16 and the No. 2 tapered roller bearing 17. In order to limit the rotation of the sleeve 13 around the pin 12 in the horizontal position and the vertical position, holes for installing and fixing components are provided on the sleeve 13 and around the pin 12, which can be quickly and conveniently fixed by quick-release pins.

[0033] As an optional embodiment, a No. 1 bearing cap 14 is provided on the shaft sleeve 13 ; and a No. 2 bearing cap 15 is provided on the pin shaft 12 .

[0034] In this embodiment, a No. 1 bearing cover 14 is provided on the shaft sleeve 13; a No. 2 bearing cover 15 is provided on the pin shaft 12; the bearing cover prevents foreign matter such as dust from invading the raceway of the rolling element, ensures that the lubricant only acts on the rolling element and the raceway without overflowing, and to a certain extent prevents the rolling element retainer and other wearing parts from being damaged by external forces, thereby improving the service life of the shaft structure as a whole.

[0035] As an optional embodiment, a sealing ring is radially installed between the bearing cover 15 and the shaft sleeve 13 .

[0036] In this embodiment, a sealing ring is radially installed between the bearing cover 15 and the shaft sleeve 13, and the sealing ring has the effect of preventing foreign matter from intruding and lubricant from leaking.

[0037] As an optional embodiment, a step is provided at one end of the pin shaft 12 .

[0038] In this embodiment, a flat step is provided at one end of the pin shaft 12. Through the flat step, one end of the pin shaft 12 can be flatly fitted on the loading beam to facilitate the installation of the missile transport clamping device and the stability in the working state.

[0039] Typical working conditions are shown in Figure 4 、 Figure 5 Attach the stepped end of the pin 12 to the missile support beam, align the fixing hole of the pin 12 with the hole in the missile support beam, and then install the clamping mechanism to the missile support beam using the screws. To clamp the missile, first loosen the locking nut in the locking device 5, allowing the adjustment rod 4 to slide freely within the strut 7. Then, move the support arm 6 so that it rotates around the No. 3 quick-release pin 8. Adjust the support arm 6 to an angle appropriate for the missile size, allowing the soft inner curved surface of the pressure plate 1 to contact the missile. Then, adjust the locking nut in the locking device 5 to tighten. At this point, the screw-structured adjustment rod 4 moves toward the support arm 6. Because the locking device 5 is restrained by the strut 7, the force arm allows the pressure plate 1 to reliably clamp against the missile, ultimately achieving reliable missile fixation. It should be noted that at least two of these clamping mechanisms are required on one end of the missile to achieve reliable missile fixation.

[0040] When hoisting the missile, in order to prevent the impact and inconvenience caused by the clamping mechanism on the hoisting process, the support arm 6 can be lifted up around the No. 3 quick-release pin 8, and the support seat 10 can be rotated outward by a certain angle, and finally the entire clamping mechanism is rotated to a horizontal position or a vertical position, and locked in this working state by the No. 5 quick-release pin 11 to facilitate the loading and unloading of the missile.

[0041] In the description of the present invention, it should be noted that, unless otherwise specified and defined, the terms "installation", "installation" and "installation" shall not be construed as

[0042] The terms "installed", "sheathed / connected", "connected", etc. should be understood in a broad sense. For example, "connected" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, and it can be the internal communication of two components. For those skilled in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0043] Obviously, the above embodiments of the present invention are merely examples for the purpose of clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention. Those skilled in the art will appreciate that other variations and modifications can be made based on the above description. It is not necessary and impossible to enumerate all embodiments here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention shall be included within the scope of protection of the claims of the present invention.

Claims

1. A missile transport and clamping mechanism, characterized in that: It comprises a pressing plate (1), a support arm structure connected to the pressing plate (1), and a support seat structure for supporting and fixing; the support arm structure comprises a support arm (6) that plays a main supporting role and an adjustment rod (4) and a support rod (7) for auxiliary adjustment; one end of the support arm (6) is movably connected to the pressing plate (1), and the pressing plate (1) is also provided with an extension section for interacting with the adjustment rod (4); the adjustment rod (4) is movably connected to the support rod (7); the support seat structure comprises a support seat (10) and a rotating structure connected to the support seat (10); The pressure plate (1) is wrapped with a soft material layer for protecting the contact position with the missile; the support rod (7) has an accommodating cavity inside, one end of the adjustment rod (4) is movably connected to the extension section of the pressure plate (1), and the other end is nested in the support rod (7), and a locking device (5) is provided at the contact position between the support rod (7) and the adjustment rod (4); the locking device (5) is a locking nut; the rotating structure is a rotating bearing for rotating the device body along the vertical plane direction and a pin (12) for rotating the support seat (10) and the structure above the support seat (10) in the horizontal plane direction, and the upper end of the pin (12) is provided with a No. 2 bearing cover (15); one side of the rotating bearing is provided with a No. 1 bearing cover (14), the other side is connected to a fixing device, and the outer side is provided with a shaft sleeve (13).

2. A missile transport and clamping mechanism according to claim 1, characterized in that: A sealing ring is radially installed between the second bearing cover (15) and the shaft sleeve (13).

3. A missile transport and clamping mechanism according to claim 1, characterized in that: The shaft sleeve (13) is movably connected via a No. 1 tapered roller bearing (16) and a No. 2 tapered roller bearing (17).

Images