An adaptive flexible mount assembly and missile launching device

Abstract

The application relates to the field of missile launching equipment, in particular to a self-adaptive flexible base assembly and a missile launching equipment; the self-adaptive flexible base assembly comprises: a flexible base and a supporting seat; the flexible base and the supporting seat are connected with a launching barrel frame through bolts and are used for bearing and transmitting launching loads during missile launching; a screw tightening torque compression basin is tightly attached to the bottom of the launching barrel frame to achieve sealed connection and effectively prevent the external leakage of internal high-pressure gas during launching; the flexible base is made of rubber material containing a cord layer and has good flexibility and friction, and can have strong ground holding capacity when being in contact with the ground; the supporting seat can provide vertical support before launching, supports the weight of the launching barrel frame, the ring seat body of the supporting seat can bear transverse shear force and keep the transverse stability of launching; the assembly structure scheme of the flexible base and the supporting seat effectively reduces the sliding during missile launching, and guarantees the accurate launching direction and launching precision of the missile.

Description

Technical Field

[0001] This application relates to the field of missile launching equipment, specifically an adaptive flexible base assembly and a missile launching device. Background Technology

[0002] Existing missile ejection schemes are basically flexible base schemes. The flexible base can effectively transfer the ejection load to the ground through its own large deformation capacity. Although the existing flexible base ejection scheme can achieve missile ejection, it has the problems of weak support for the ejection tube frame, serious lateral slippage of the ejection tube frame during missile ejection, resulting in large deviations in the missile ejection direction and ejection accuracy. Summary of the Invention

[0003] This application provides an adaptive flexible base assembly to compensate for the problem of large deviations in missile launch direction and launch accuracy.

[0004] This application provides the following technical solution: An adaptive flexible base assembly includes: a flexible base and a support base; The flexible base includes a base plate and side walls, which together form a basin structure. Both the base plate and side walls are made of rubber with built-in cord layers. The side wall at the open end of the basin extends outward to form a basin rim for connection. The support includes a ring seat body, and the basin rim of the flexible base is connected to the ring seat body. The basin structure is placed in the ring seat body.

[0005] Furthermore, the basin edge is connected to the top of the ring seat body; or, the inner peripheral wall of the ring seat body is provided with a support edge, the basin edge is located on the support edge, and an annular rubber seat is provided at the lower part of the support edge.

[0006] Furthermore, the inner surface of the annular rubber seat is set as an inclined surface, forming an annular seat structure that is wide at the top and narrow at the bottom.

[0007] Furthermore, multiple annular sealing ribs are distributed circumferentially around the annular rubber seat.

[0008] Furthermore, the basin is provided with a first through hole for connection along its circumference, and a second through hole is provided on the main body of the ring seat, with bolts connecting the two through holes.

[0009] Furthermore, a metal ring is wrapped inside the basin rim structure. The metal ring serves as a skeleton to enhance strength, and the metal ring is preferably a steel ring.

[0010] Furthermore, the ratio of the height of the ring seat body at the bottom to the height of the ring rubber seat is 1 / 4-2.

[0011] Furthermore, the basin is provided with first through holes for connection distributed circumferentially, and there are multiple first through holes, which are located in multiple strip-shaped inner holes respectively.

[0012] Furthermore, both the base plate and side walls are made of rubber airbag material with built-in cord layers. Preferably, the rubber airbag has two built-in cord layers.

[0013] This application also provides a missile launching device, including the aforementioned adaptive flexible base assembly.

[0014] Beneficial effects: This application discloses an adaptive flexible base assembly, including a flexible base and a support base. The flexible base includes a bottom plate and side walls, which together form a basin structure. Both the bottom plate and side walls are made of rubber with built-in cord layers. The side wall at the open end of the basin extends outward to form a basin rim for connection. The support base includes a ring seat body, and the basin rim of the flexible base is connected to the ring seat body. The basin structure is placed in the ring seat body. The adaptive flexible base assembly of this application connects the flexible base and the support seat to the ejection tube frame via bolts, serving to bear and transfer the ejection load during missile launch. The tightening torque of the screws compresses the rim to ensure a tight fit against the bottom of the ejection tube frame, achieving a sealed connection and effectively preventing the leakage of internal high-pressure gas during ejection. The flexible base is made of rubber material containing a cord layer, possessing good flexibility and friction, and exhibiting strong grip when in contact with the ground. The support seat provides vertical support before ejection, bearing the weight of the ejection tube frame. During ejection, the ring seat body of the support seat can withstand lateral shear force, maintaining lateral stability during ejection. The component structure of the flexible base and support seat in this application effectively reduces missile slippage during ejection, ensuring accurate missile ejection direction and ejection precision. Attached Figure Description

[0015] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0016] Figure 1 This is a schematic diagram of the adaptive flexible base assembly structure of this application; Figure 2 for Figure 1 A schematic diagram of the first type of structure for the central support base; Figure 3 for Figure 1 Schematic diagram of the second structure of the central support base; Figure 4 for Figure 1 A cross-sectional view (3D) of the main body of the ring seat and the annular rubber seat in the support base; In the diagram: 10. Flexible base; 11. Base plate; 12. Side wall; 13. Basin edge; 14. Rubber; 15. Cord layer; 16. Metal ring; 20. Support seat; 21. Ring seat body; 22. Support edge; 23. Annular rubber seat. Detailed Implementation

[0017] To enable those skilled in the art to better understand the technical solutions in this application, the technical solutions in the embodiments of this application will be clearly and completely described below. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of the embodiments. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0018] It should be noted that when a component is referred to as being "fixed to" or "set on" another component, it can be directly on or indirectly set on the other component; when a component is referred to as being "connected to" another component, it can be directly connected to or indirectly connected to the other component.

[0019] It should be understood that the terms "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", and "outer" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0020] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this application, "multiple" or "several" means two or more, unless otherwise explicitly specified.

[0021] It should be noted that the structures, proportions, sizes, etc., shown in the accompanying drawings of this specification are only for the purpose of assisting those skilled in the art in understanding and reading the content disclosed in the specification, and are not intended to limit the conditions under which this application can be implemented. Therefore, they have no substantial technical significance. Any modifications to the structure, changes in the proportions, or adjustments to the size should still fall within the scope of the technical content disclosed in this application, provided that they do not affect the effects and purposes that this application can produce.

[0022] The embodiments in this application are written in a progressive manner.

[0023] Please see Figures 1 to 4 An adaptive flexible base assembly includes: a flexible base 10 and a support 20; The flexible base includes a base plate 11 and a side wall 12, which together form a basin structure. Both the base plate and the side wall are made of rubber 14 with a built-in cord layer 15. The side wall at the open end of the basin extends outward to form a basin rim 13 for connection. The support includes a ring seat body 21, and the basin rim of the flexible base is connected to the ring seat body. The basin structure is placed in the ring seat body.

[0024] The adaptive flexible base assembly of this application connects the flexible base and the support seat to the ejection tube frame via bolts, serving to bear and transfer the ejection load during missile launch. The tightening torque of the screws compresses the rim to ensure a tight fit against the bottom of the ejection tube frame, achieving a sealed connection and effectively preventing the leakage of internal high-pressure gas during ejection. The flexible base is made of rubber material containing a cord layer, possessing good flexibility and friction, and exhibiting strong grip when in contact with the ground. The support seat provides vertical support before ejection, bearing the weight of the ejection tube frame. During ejection, the ring seat body of the support seat can withstand lateral shear force, maintaining lateral stability during ejection. The component structure of the flexible base and support seat in this application effectively reduces missile slippage during ejection, ensuring accurate missile ejection direction and ejection precision.

[0025] The main body of the ring seat is made of metal, preferably aluminum alloy. Aluminum alloy ring seat has high strength and rigidity and is lightweight, which can meet the requirements of providing large vertical and lateral support and achieve lightweight base.

[0026] As an optional implementation, the basin rim is connected to the top of the ring seat body; specifically, the basin rim is provided with a first through hole for connection in a circumferential manner, and the ring seat body is provided with a corresponding second through hole, and bolts are provided in the two through holes to connect them.

[0027] Preferably, a support edge 22 is provided on the inner peripheral wall of the ring seat body, the basin edge is located on the support edge, and an annular rubber seat 23 is provided at the lower part of the support edge. Through holes for connecting the flexible base and the ring seat body are provided in the basin edge and the support edge, and bolts are installed in the through holes for connection.

[0028] The support base consists of a metal ring seat body and an annular rubber seat. The metal ring seat body is sufficient to bear the weight of the ejection tube frame before ejection, and due to the presence of the annular rubber seat, it has a certain degree of deformation and vertical displacement deformation, which can adapt to certain uneven ground. The side wall of the annular rubber seat is wrapped by the ring seat body to enhance the lateral stiffness, which is conducive to maintaining the lateral stability of the ejection tube frame during missile ejection and improving ejection accuracy.

[0029] In a preferred embodiment, the inner surface of the annular rubber seat is set as an inclined surface, forming an annular seat structure that is wider at the top and narrower at the bottom. The advantage of this structure is that, under the weight of the ejection tube frame, the annular rubber seat deforms, increasing the contact area with the ground, while also having a certain deformation displacement to adapt to certain uneven ground conditions; in addition, the sidewalls of the annular rubber seat are stopped by the metal annular seat body, effectively preventing lateral instability.

[0030] Furthermore, the ratio of the height of the ring seat body at the bottom to the height of the ring rubber seat is 1 / 4-2; this proportion structure is conducive to the comprehensive protection of vertical deformation, vertical support and lateral support.

[0031] As another preferred embodiment, the annular rubber seat is provided with multiple annular sealing ribs distributed circumferentially, and the inner hole of the strip is a waist-shaped hole, or the two sides of the waist-shaped hole are diamond-shaped structures. This structural scheme reduces the vertical stiffness of the main body of the annular seat to a certain extent, while satisfying the self-weight bearing support of the catapult frame and having a certain degree of deformation to increase the contact area with the ground and adapt to certain ground unevenness. In addition, the side wall of the annular rubber seat is stopped by the metal main body of the annular seat, which effectively prevents lateral instability.

[0032] Preferably, the connecting through holes arranged circumferentially along the basin edge are preferably located in the inner hole of the strip, with each through hole corresponding to one inner hole of the strip, and the through holes located in the middle section of the inner hole of the strip.

[0033] As a preferred embodiment, a metal ring 16 is wrapped inside the basin rim structure. The metal ring serves as a skeleton for enhancing strength. The metal ring is preferably a steel ring. The flexible base of the cord layer rubber can share the ejection load with the help of the metal ring, thereby improving the load-bearing capacity of the base.

[0034] Alternatively, both the base plate and side walls are made of rubber airbag material with built-in cord layers. Preferably, the rubber airbag has two built-in cord layers.

[0035] This application also provides a missile launching device, including the aforementioned adaptive flexible base assembly. The beneficial effects of the missile launching device provided in this application are the same as those of the provided flexible base system, and will not be repeated here.

[0036] The above description of the disclosed embodiments enables those skilled in the art to make or use this application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of this application. Therefore, this application is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. An adaptive flexible base assembly for launching missiles, characterized in that, include: Flexible base and support; The flexible base includes a base plate and side walls, which form a basin structure. Both the base plate and side walls are made of rubber with built-in cord layers. The open end sidewall of the basin extends outward to form a basin rim for connection; the support base includes a ring seat body, the basin rim of the flexible base is connected to the ring seat body, and the basin structure is placed in the ring seat body; The basin rim is connected to the top of the ring seat body; or, the inner peripheral wall of the ring seat body is provided with a support edge, the basin rim is located on the support edge, and an annular rubber seat is provided at the bottom of the support edge. The inner surface of the annular rubber seat is set as an inclined surface, forming an annular seat structure that is wider at the top and narrower at the bottom.

2. The adaptive flexible base assembly according to claim 1, characterized in that, The annular rubber seat has multiple annular sealing ribs distributed around its circumference.

3. The adaptive flexible base assembly according to any one of claims 1-2, characterized in that, The basin is provided with a first through hole for connection along its circumference, and a second through hole is provided on the main body of the ring seat. The two through holes are connected by bolts.

4. The adaptive flexible base assembly according to claim 3, characterized in that, The basin rim structure is enclosed with metal rings, which serve as a framework to enhance strength.

5. The adaptive flexible base assembly according to any one of claims 1-2, characterized in that, The ratio of the height of the ring seat body at the bottom to the height of the ring rubber seat is 1 / 4-2.

6. The adaptive flexible base assembly according to claim 2, characterized in that, The basin is provided with multiple first through holes for connection along its circumference. These multiple first through holes are located in multiple annular sealing ribs.

7. The adaptive flexible base assembly according to claim 1, characterized in that, The base plate and side walls are made of rubber airbag material with built-in cord layers.

8. A missile launching device, characterized in that, Includes the adaptive flexible base assembly as described in any one of claims 1-7.

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