A loading compartment for loading destructive devices

Abstract

This utility model discloses a loading compartment for loading damage devices, belonging to the technical field of damage device structural design, and solves the problems of bulky loading compartment structure and difficult operation during the limiting assembly process with the damage device. The loading compartment of this utility model includes a compartment body, a positioning component, a first support, and a second support. The compartment body has multiple bolt through holes along the radial direction for bolt connection between the compartment body and the first and second supports. The positioning component is threaded onto the outer periphery of the damage device. One end of the positioning component engages with the first support through a conical surface, and the other end is bolted to the second support, thereby limiting the damage device radially and in the flight direction within the compartment. The loading compartment of this utility model has a simple and convenient assembly process, and the limiting effect is reliable and stable.

Description

Technical Field

[0001] This utility model belongs to the technical field of damage device structure design, and relates to a loading compartment for loading damage devices. Background Technology

[0002] For large-caliber, heavy damaging devices, their installation and connection within the loading compartment are of great importance. It is necessary to consider both the strength and reliability of the connection structure, as well as the feasibility and ease of installation of the damaging device.

[0003] Currently, the commonly used installation structure for destructive devices within the loading compartment is as follows: Figure 1 As shown. The loading bay is equipped with three supports: front, middle, and rear. The damage device is fixed within the loading bay via these supports. The front support engages with the front end of the damage device, restricting its axial forward movement; the middle support engages with the cylindrical end of the damage device in the middle, providing support; and the rear support fits against the rear end of the damage device, restricting its axial backward movement. The supports are threadedly connected to the loading bay shell. This type of loading bay presents several problems: 1) It requires machining internal threads on the inner wall of the loading bay shell, necessitating a thicker shell blank during initial forming to allow for material allowance for subsequent machining of the internal threads. This significantly increases raw material consumption and the negative weight of the flight system, affecting its performance; 2) During loading bay assembly, threading the supports to the shell within the limited space of the loading bay shell is difficult and prone to damaging the threads, further increasing the assembly complexity of the loading bay. Utility Model Content

[0004] Based on the above analysis, this utility model aims to provide a spacecraft cabin for a controllable airburst diffusion vehicle, in order to solve the technical problems of the bulky structure of the loading cabin and the difficulty of operation in the process of limiting the assembly with the destruction device.

[0005] The purpose of this utility model is mainly achieved through the following technical solutions.

[0006] This utility model provides a loading compartment for loading a damage device, including a compartment body, a positioning component, a first bracket, and a second bracket; the compartment body has multiple bolt through holes along the radial direction, which are used to connect the compartment body to the first bracket and the second bracket via first bolts; the positioning component includes internal threads, and the positioning component is sleeved on the outer periphery of the damage device via the internal threads, one end of the positioning component is in contact with the first bracket via a conical surface, and the other end of the positioning component is connected to the second bracket via a second bolt, thereby achieving radial and flight direction limiting of the damage device within the compartment.

[0007] Furthermore, the positioning element also includes a first conical surface, with the smaller diameter end of the first conical surface located at the end of the positioning element.

[0008] Furthermore, the first support includes a second conical surface, which is disposed on the inner wall of the first support and has a taper that matches the first conical surface.

[0009] Furthermore, the positioning element also includes a first flange, which is arranged radially along the positioning element.

[0010] Furthermore, the second support includes a second flange, which is connected to the first flange by a second bolt and is located between the first flange and the first conical surface.

[0011] Furthermore, both the first and second supports include connecting rings, the outer diameter of which matches the inner diameter of the cabin at the assembly point of the first and second supports, respectively. Multiple threaded blind holes are formed on the outer surface of the connecting rings, and the positions of the threaded blind holes match the positions of the bolt through holes of the cabin at the assembly point of the first and second supports.

[0012] Furthermore, both the first and second supports also include a support ring, with the outer ring end of the support ring fixedly connected to the connecting ring.

[0013] Furthermore, the support ring has a tapered shape and a hollow structure.

[0014] Furthermore, the second conical surface is located at the inner ring end of the support ring of the first bracket; the second flange is located at the inner ring end of the support ring of the second bracket.

[0015] Furthermore, it also includes a third support and a baffle, which are used to limit the destructive device in the opposite direction of flight within the cabin.

[0016] Compared with the prior art, the present invention can achieve at least one of the following beneficial effects:

[0017] 1. The loading compartment of this utility model, due to the setting of a positioning component that is threaded onto the outer periphery of the damage device, can quickly realize the combination of the damage device and the loading compartment; by setting the conical contact and cooperation between the positioning component and the first bracket, the radial and flight direction limiting assembly of the damage device in the compartment can be quickly realized, and the limiting effect is reliable and stable, improving the structural stability during flight; by setting bolt through holes on the compartment, the first bracket and the second bracket can be fixedly assembled in the compartment from the outside of the compartment, and the assembly process is simple and convenient.

[0018] 2. The loading compartment of this utility model, because the ring of the support ring has a tapered shape and a hollow structure, can reduce the weight of the support on the one hand, and increase the support and connection rigidity of the support on the other hand, so as to ensure the stable positioning of the damage device in the compartment.

[0019] 3. In the loading compartment of this utility model, both the first flange and the second flange are arranged along the radial plane, and the second flange is located between the first flange and the first conical surface, so that the second flange can bear the forward impact force of the damage device, avoiding overload of the connecting bolts, thereby ensuring the stability and reliability of the overall connection structure between the loading compartment and the damage device.

[0020] In this invention, the above-described technical solutions can be combined with each other to achieve more preferred combinations. Other features and advantages of this invention will be set forth in the following description, and some advantages may become apparent from the description or be learned by practicing the invention. The objectives and other advantages of this invention can be realized and obtained through the embodiments described and the accompanying drawings, which are particularly pointed out. Attached Figure Description

[0021] Figure 1 This is a structural schematic diagram of the loading compartment for loading damage devices related to this embodiment;

[0022] Figure 2 This is a schematic diagram of the longitudinal section structure of the loading compartment according to an embodiment of the present utility model;

[0023] Figure 3 This is a schematic diagram of the cabin structure according to an embodiment of the present utility model;

[0024] Figure 4 This is a schematic diagram of the longitudinal section structure of the positioning component according to an embodiment of the present utility model;

[0025] Figure 5 This is a cross-sectional longitudinal view of the loading compartment according to an embodiment of the present utility model;

[0026] Figure 6 This is a schematic cross-sectional view of the first support structure according to an embodiment of the present utility model;

[0027] Figure 7 This is a schematic diagram of the structure of the second support in an embodiment of the present invention.

[0028] Figure label:

[0029] 1-Carrier; 11-Bolt through hole; 12-First bolt; 2-Positioning component; 21-Internal thread; 22-First conical surface; 23-First flange; 24-Second bolt; 3-First bracket; 31-Second conical surface; 4-Second bracket; 41-Second flange; 5-Third bracket; 6-Baffle; 7-Adjusting shim; 8-Destructive device;

[0030] 101-Connecting ring; 102-Supporting ring; 103-Threaded blind hole. Detailed Implementation

[0031] The preferred embodiments of the present invention will now be described in detail with reference to the accompanying drawings, which constitute a part of the present invention and are used together with the embodiments of the present invention to illustrate the principles of the present invention, but are not intended to limit the scope of the present invention.

[0032] Example 1

[0033] This embodiment provides a loading compartment for loading damaging devices, such as... Figure 2 , Figure 3 and Figure 4 As shown, the device includes a cabin 1, a positioning component 2, a first support 3, and a second support 4. The cabin 1 has multiple bolt through holes 11 along the radial direction, which are used to connect the cabin 1 to the first support 3 and the second support 4 via first bolts 12. The positioning component 2 includes an internal thread 21, which is fitted onto the outer periphery of the damage device. One end of the positioning component 2 is in contact with the first support 3 via a conical surface, and the other end of the positioning component 2 is connected to the second support 4 via a second bolt 24, thereby limiting the damage device in the radial and flight directions within the cabin 1.

[0034] When assembling the loading compartment of this embodiment outside the damage device, firstly, the positioning component 2 and the second bracket 4 are connected by the second bolt 24 and the nut. Then, the positioning component 2 and the second bracket 4 are fitted onto the outer periphery of the damage device, and the internal thread 21 is engaged with the external thread of the center of mass of the damage device to combine the positioning component 2, the second bracket 4 and the damage device into a single assembly. The first bracket 3 is placed inside the compartment 1, and the first bolt 12 is used to fix the first bracket 3 in a predetermined position inside the compartment 1 through the bolt through hole 11 on the compartment 1. Then, the damage device assembly is installed into the compartment 1 along the flight direction. When the front end of the positioning component 2 contacts the first bracket 3, the positioning component 2 and the first bracket 3 are engaged through conical contact. Then, the second bracket 4 is fixed to the compartment 1 by bolts through the bolt through hole 11, thereby completing the radial and flight direction limiting assembly of the damage device inside the compartment 1.

[0035] In this embodiment, the loading compartment is equipped with a positioning component that is threaded onto the outer periphery of the damage device, enabling rapid assembly of the damage device and the loading compartment. By setting the conical contact between the positioning component 2 and the first bracket 3, the radial and flight direction limiting assembly of the damage device within the compartment 1 can be achieved quickly, with reliable and stable limiting effect. By setting bolt through holes 11 on the compartment 1, the first bracket 3 and the second bracket 4 can be fixedly assembled within the compartment 1 from outside the compartment 1, making the operation simple and convenient.

[0036] The loading compartment in this embodiment also includes a third support 5 and a baffle 6. The third support 5 and the baffle 6 are used to limit the destruction device in the opposite direction of flight within the compartment 1.

[0037] Specifically, such as Figure 1 As shown, the cabin 1 has three sets of bolt through holes 11. Two sets are located in the middle section of the cabin 1, used to fix the first bracket 3 and the second bracket 4 with bolts, respectively. One set is located at the tail of the cabin 1, used to fix the third bracket 5 with bolts. The baffle 6 is connected to the third bracket 5 with bolts and nuts to press the tail end of the damage device, thereby limiting the damage device in the opposite direction of flight within the cabin 1. An adjusting shim 7 of appropriate thickness can be added between the baffle 6 and the tail end of the damage device according to the actual assembly clearance to ensure that the tail end of the damage device is pressed tightly.

[0038] In this embodiment, the loading compartment, by setting positioning component 2, first bracket 3, second bracket 4, third bracket 5 and baffle 6, realizes the limited assembly of the damage device in the compartment 1. The limiting effect is reliable and the assembly process is simple.

[0039] Preferred, such as Figure 4 As shown, the positioning component 2 also includes a first conical surface 22 and a first flange 23. The first conical surface 22 and the first flange 23 are located at both ends of the positioning component 2, respectively. The end of the first conical surface 22 with a smaller diameter is located at the end of the positioning component 2. The first flange 23 is arranged along the radial plane of the positioning component 2 and is used to connect with the second bracket 4 by bolts.

[0040] like Figure 5 As shown, the first bracket 3, the second bracket 4, and the third bracket 5 each include a connecting ring 101 and a support ring 102. The outer diameter of the connecting ring 101 matches the inner diameter of the cabin 1 at the assembly points of the first bracket 3, the second bracket 4, and the third bracket 5, respectively. A plurality of threaded blind holes 103 are uniformly formed on the outer surface of the connecting ring 101. The threaded blind holes 103 match the positions of the bolt through holes 11 at the assembly points of the cabin 1 of the first bracket 3 and the second bracket 4, so as to achieve the fixation of the first bracket 3, the second bracket 4, and the third bracket 5 inside the cabin 1 by using the first bolt 12 through the bolt through holes 11 and the threaded blind holes 103 outside the cabin 1.

[0041] Preferred, such as Figure 5 As shown, the outer ring end of the support ring 102 is fixedly connected to the connecting ring 101. The ring body of the support ring 102 has a tapered shape and a hollow structure, so that the first bracket 3, the second bracket 4 and the third bracket 5 are all hub-type structures. On the one hand, the weight of the bracket can be reduced, and on the other hand, the support and connection rigidity of the bracket can be increased to ensure the stable positioning of the damage device in the cabin 1.

[0042] To facilitate quick and easy assembly of limit positions, such as Figure 6As shown, the first support 3 includes a second conical surface 31, which is disposed on the inner wall of the first support 3 and its taper matches that of the first conical surface 22. Specifically, the second conical surface 31 is located at the inner ring end of the support ring 102 of the first support 3. During assembly, the taper of the support ring 102 convexes towards the tail end of the damaging device to increase the support rigidity of the support ring 102 on the positioning member 2 through the second conical surface 31, thereby ensuring the radial and flight direction limiting of the damaging device.

[0043] like Figure 7 As shown, the second support 4 includes a second flange 41, which is located at the inner ring end of the support ring 102 of the second support 4 and arranged along a radial plane. The second flange 41 is connected to the first flange 23 by a second bolt 24 and a nut. To avoid excessive load on the bolt assembly, after the bolt assembly is connected, the second flange 41 is located between the first flange 23 and the first conical surface 22. Since both the first flange 23 and the second flange 41 are arranged along a radial plane, the second flange 41 can withstand the forward impact force of the damaging device, avoiding overload of the connecting bolt assembly, thereby ensuring the stability and reliability of the overall connection structure between the loading compartment and the damaging device.

[0044] The above are merely preferred embodiments of this utility model, but the scope of protection of this utility model is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this utility model should be included within the scope of protection of this utility model.

Claims

1. A loading compartment for loading destructive devices, characterized in that, It includes a cabin (1), a positioning component (2), a first support (3), and a second support (4); The cabin (1) has a plurality of bolt through holes (11) in the radial direction. The bolt through holes (11) are used for the cabin (1) to be connected to the first bracket (3) and the second bracket (4) by the first bolt (12). The positioning element (2) includes an internal thread (21), and the positioning element (2) is sleeved on the outer periphery of the damaging device through the internal thread (21). One end of the positioning element (2) is engaged with the first bracket (3) through a conical contact, and the other end of the positioning element (2) is connected to the second bracket (4) through a second bolt (24), thereby enabling the damage device to be limited radially and in the flight direction within the cabin (1).

2. The loading compartment for loading damage devices according to claim 1, characterized in that, The positioning element (2) further includes a first conical surface (22), the smaller end of which is located at the end of the positioning element (2).

3. The loading compartment for loading damage devices according to claim 2, characterized in that, The first support (3) includes a second conical surface (31), which is disposed on the inner wall of the first support (3) and the taper matches that of the first conical surface (22).

4. The loading compartment for loading damage devices according to claim 3, characterized in that, The positioning element (2) further includes a first flange (23) which is arranged radially along the positioning element (2).

5. The loading compartment for loading a damage-causing device according to claim 4, characterized in that, The second bracket (4) includes a second flange (41), which is connected to the first flange (23) by a second bolt (24) and is located between the first flange (23) and the first conical surface (22).

6. The loading compartment for loading a damage-causing device according to claim 5, characterized in that, Both the first bracket (3) and the second bracket (4) include a connecting ring (101). The outer diameter of the connecting ring (101) matches the inner diameter of the cabin (1) at the assembly point of the first bracket (3) and the second bracket (4). Multiple threaded blind holes (103) are opened on the outer surface of the connecting ring (101). The threaded blind holes (103) match the positions of the bolt through holes (11) at the assembly point of the cabin (1) of the first bracket (3) and the second bracket (4).

7. The loading compartment for loading a damage-causing device according to claim 6, characterized in that, The first bracket (3) and the second bracket (4) also include a support ring (102), the outer ring end of which is fixedly connected to the connecting ring (101).

8. The loading compartment for loading a damage-causing device according to claim 7, characterized in that, The support ring (102) has a tapered shape and a hollow structure.

9. The loading compartment for loading a damage-causing device according to claim 8, characterized in that, The second conical surface (31) is located at the inner ring end of the support ring (102) of the first bracket (3); the second flange (41) is located at the inner ring end of the support ring (102) of the second bracket (4).

10. The loading compartment for loading damaging devices according to any one of claims 1 to 9, characterized in that, It also includes a third support (5) and a baffle (6), which are used to limit the destruction device in the opposite direction of flight within the cabin (1).

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