Rail type launching box body precision realization device and installation method

Abstract

The application provides a guide rail type launching box body precision realization device and mounting method in the technical field of missile launching, which comprises a jointed frame, a box body, guide rails, welding piles, a missile and anti-rotation blocks. The box body is connected to the inner wall of the jointed frame, the missile is connected in the box body, the anti-rotation blocks are arranged on the missile, the welding piles are connected in the gap between the anti-rotation blocks and the guide rails, and the guide rails are connected to the inner wall of the box body. The guide rails with small sections and small inner diameters are used, local surfacing is carried out at the two end parts of the guide rails adjacent to the anti-rotation blocks of the missile, the four guide rails and the welding piles are machined based on the bottom surface and the side surface of the outer jointed frame of the box body as the reference, so that the azimuth, pitch and roll error requirements of the box body and the missile are ensured. Meanwhile, the welding precision requirement of the guide rails in the box body is reduced, the welding process of the guide rails and the box body is improved, and the frictional resistance that needs to be overcome when the missile is loaded into the box body is reduced.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of missile launching, in particular to a guide rail type launching box body precision realization device and mounting method. BACKGROUND

[0002] In order to improve the weapon system integration level, under the premise of small size of the launching box body section, the missile wing and air rudder need to be folded in the same direction in the launching box body, but the adjacent gap is small after the wing and air rudder are radially enveloped, so the conventional guide rail hanging or sliding block sliding mode cannot be used to support the missile, and the adapter support mode is currently used at home and abroad, but the adapter splashing and falling during launching can easily pose a threat to the nearby equipment, which is not conducive to the safety of the nearby equipment. Therefore, a guide rail type launching box body is proposed in the industry to realize the support of the missile and the non-splashing launching mode, to ensure the safety of the nearby equipment and to improve the weapon system integration level.

[0003] Generally, when the weapon system precision is distributed, the azimuth, pitch and roll errors of the box body and the missile need to be controlled, wherein the azimuth and pitch errors relate to the missile shooting accuracy, and the missile needs to be controlled throughout the launching process, and the roll error only affects the initial phase of the missile, and the roll phase relative change can be obtained by self-solution during the missile launching process. Therefore, when using the guide rail type launching box body, in addition to supporting the missile by the inner envelope circle of the four guide rails, two anti-rotation blocks need to be additionally arranged on the surface of the missile, the anti-rotation blocks are located between the adjacent two guide rails of the box body, the contact limit between the outer side of the two anti-rotation blocks and the inner side of the two guide rails is used to realize the anti-rotation requirement of the missile. Generally, the four guide rails are fixed on the box body by welding, and since the guide rails are in the form of slender rods, the structure is not rigid enough, and after welding, the four guide rails can be deformed and cannot guarantee the straightness and relative position of the four guide rails, that is, the azimuth, pitch and roll errors of the box body and the missile cannot be guaranteed.

[0004] Therefore, the industry needs a guide rail type launching box body precision realization method to improve the welding process of the guide rail and the box body and to guarantee the cooperation precision requirement of the box body and the missile. SUMMARY

[0005] In view of the defects in the prior art, the purpose of the present application is to provide a guide rail type launching box body precision realization device and mounting method.

[0006] According to the guide rail type launching box body precision realization device provided by the present application, the inner wall of the unit frame is connected with the box body, the box body is connected with the missile in the inside, the missile is provided with the anti-rotation block, the welding pile is connected in the gap between the anti-rotation block and the guide rail, and the guide rail is connected to the inner wall of the box body.

[0007] Preferably, the box is octagonal, and the box comprises long sides and short sides, the long sides and the short sides are connected at intervals, and the guide rails are connected to the inner walls of the short sides of the box.

[0008] Preferably, the inner wheel gallery of the ganged frame is octagonal, and the outer wheel gallery of the ganged frame is rectangular.

[0009] The inner wheel gallery of the ganged frame is sleeved and fixed on the outer wheel gallery of the box.

[0010] Preferably, the diameters of the envelope circles formed by the plurality of guide rails are less than the outer diameters of the missiles.

[0011] Preferably, the guide rails comprise first guide rails and second guide rails, and the first guide rails and the second guide rails are respectively located on two sides of the box.

[0012] Preferably, the first guide rails and the anti-rotation blocks are connected one by one, and gaps are arranged between the inner side surfaces of the first guide rails and the anti-rotation blocks.

[0013] Preferably, during the process of loading the missiles into the box, the inner envelope circles of the plurality of guide rails support the missiles, and by adjusting the phases of the missiles, the anti-rotation blocks and the guide rails are kept at appropriate gaps.

[0014] Preferably, when the missiles are loaded into the box to the right positions, the inner side surfaces of the weld pads cooperate with the anti-rotation blocks, so as to realize the azimuth, pitch and roll error requirements of the box and the missiles.

[0015] Preferably, the anti-rotation blocks are connected to the surfaces of the tails of the missiles.

[0016] The application also provides an installation method of the box precision realization device of the guide rail type launch box, and the specific steps are as follows.

[0017] S1, the inner octagonal wheel gallery of the ganged frame is sleeved and fixed on the outer octagonal wheel gallery of the box, and the guide rails are respectively welded to the inner walls of the short sides of the box.

[0018] S2, after local surfacing is performed on the end of the first guide rail to form a weld pad, the inner envelope circles of the plurality of guide rails and the weld pad are machined based on the bottom surface and the side surface of the ganged frame, so as to ensure the diameter tolerance of the inner envelope circles of the plurality of guide rails, the azimuth and pitch shape tolerance of the ganged frame, the inner side surface angle tolerance of the weld pad and the angle tolerance of the bottom surface of the ganged frame.

[0019] S3, the anti-rotation blocks are located on the surfaces of the tails of the missiles, during the process of loading the missiles into the box, the inner envelope circles of the plurality of guide rails support the missiles, and by adjusting the phases of the missiles, the anti-rotation blocks and the guide rails are kept at appropriate gaps.

[0020] S4, when the missiles are loaded into the box to the right positions, the inner side surfaces of the weld pads cooperate with the anti-rotation blocks, so as to realize the azimuth, pitch and roll error requirements of the box and the missiles.

[0021] Compared with the prior art, the application has the following beneficial effects:

[0022] The present application uses small-section and small-diameter guide rails, and after local surfacing at the two rail ends adjacent to the missile anti-rotation block, the four rail inner envelope circles and the weld deposits are machined based on the box outer assembly frame bottom surface and side surface as the reference, so as to ensure the azimuth, pitch and roll error requirements of the box and the missile. Meanwhile, the guide rail welding precision requirement of the box is reduced, the guide rail and box welding process is improved, and the friction resistance to be overcome when the missile is loaded into the box is reduced. BRIEF DESCRIPTION OF DRAWINGS

[0023] Other features, objects and advantages of the present application will become more apparent from the following detailed description of non-limiting embodiments, which is to be read in conjunction with the accompanying drawings:

[0024] Figure 1 is a structural schematic view of the present application;

[0025] Figure 2 is a top view of the present application.

[0026] Reference numerals in the drawings:

[0027] Assembly frame 1, box 2, guide rail 3, weld deposit 4, missile 5, anti-rotation block 6. DETAILED DESCRIPTION

[0028] The present application will be described in detail below with specific embodiments. The following embodiments will help those skilled in the art to further understand the present application, but do not limit the present application in any form. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present application. These are within the scope of protection of the present application.

[0029] Example 1

[0030] According to the guide rail type launch box box precision realization device provided by the present application, as shown in Figures 1-2 , it comprises an assembly frame 1, a box 2, a guide rail 3, a weld deposit 4, a missile 5 and an anti-rotation block 6, the box 2 is connected to the inner wall of the assembly frame 1, the missile 5 is connected in the box 2, the anti-rotation block 6 is connected to the surface of the tail of the missile 5, the weld deposit 4 is connected to the gap between the anti-rotation block 6 and the guide rail 3, and the guide rail 3 is connected to the inner wall of the box 2. When the missile 5 is loaded into the box 2, the inner envelope circles of the plurality of guide rails 3 support the missile 5, and by adjusting the phase of the missile 5, the anti-rotation block 6 and the guide rail 3 maintain a proper gap. When the missile 5 is loaded into the box 2 to the position, the inner side surface of the weld deposit 4 cooperates with the anti-rotation block 6 to realize the azimuth, pitch and roll error requirements of the box 2 and the missile 5.

[0031] The inner wheel corridor of the joint frame 1 is octagonal, the outer wheel corridor of the joint frame 1 is rectangular, and the inner wheel corridor of the joint frame 1 is sleeved and fixed on the outer wheel corridor of the box body 2. The box body 2 is octagonal, the box body 2 comprises long edges and short edges, the long edges and the short edges are connected at intervals, four guide rails 3 are connected to the inner walls of the short edges of the box body 2, and the four guide rails 3 form an envelope circle with a diameter < the outer diameter of the missile 5. The four guide rails 3 comprise first guide rails and second guide rails, the first guide rails and the second guide rails are located on two sides of the box body 2 respectively, two first guide rails are located above, and two second guide rails are located below. The first guide rails and the anti-rotation blocks 6 are connected one by one, and a gap is arranged between the inner side surface of the first guide rail and the anti-rotation block 6.

[0032] Example 2

[0033] The application also provides a mounting method of the guide rail type launching box body precision realization device in embodiment 1, and the specific steps are as follows:

[0034] S1, the octagonal wheel corridor in the joint frame 1 is sleeved and fixed on the octagonal wheel contour outside the box body 2, and the guide rails 3 are welded on the inner walls of the short edges of the box body 2 respectively;

[0035] S2, after local surfacing is performed on the ends of the two first guide rails located above to form the welding stacks 4, the inner envelope circles of the plurality of guide rails 3 and the welding stacks 4 are machined with the bottom surface and the side surface of the joint frame 1 as the reference, so that the diameter tolerance of the inner envelope circles of the four guide rails 3, the orientation and pitch form tolerance of the joint frame 1, the inner side surface included angle tolerance of the welding stacks 4 and the bottom surface included angle tolerance of the joint frame 1 are ensured;

[0036] S3, the anti-rotation blocks 6 are located on the surface of the tail of the missile 5, when the missile 5 is loaded into the box body 2, the inner envelope circles of the four guide rails 3 support the missile 5, because the guide rails 3 are small in section, by adjusting the phase of the missile 5, the anti-rotation blocks 6 and the guide rails 3 are kept at a proper gap, and the frictional resistance that needs to be overcome when the missile 5 is loaded into the box body 2 is reduced;

[0037] S4, when the missile 5 is loaded into the box body 2 to the position, the inner side surfaces of the two welding stacks 4 cooperate with the anti-rotation blocks 6, so that the orientation, pitch and roll error requirements of the box body 2 and the missile 5 are realized.

[0038] More specifically, the application provides a mounting method of the guide rail type launching box body precision realization device, by using guide rails with small sections and small inner diameters, after local surfacing is performed on the ends of the two guide rails adjacent to the missile anti-rotation blocks, the inner envelope circles of the four guide rails and the welding stacks are machined with the bottom surface and the side surface of the outer joint frame of the box body as the reference, so that the orientation, pitch and roll error requirements of the box body and the missile are ensured. Meanwhile, the welding precision requirement of the guide rails in the box body is reduced, the welding process of the guide rails and the box body is improved, and the frictional resistance that needs to be overcome when the missile is loaded into the box body is reduced.

[0039] 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 refer to the orientation or positional relationship shown in the drawings, and are only intended to facilitate the description of the present application and simplify the description, and are not intended to 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.

[0040] The specific embodiments of the present application are described above. It should be understood that the present application is not limited to the above specific embodiments, and various changes or modifications can be made by those skilled in the art within the scope of the claims, which do 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, provided that they do not conflict.

Claims

1. An installation method for a rail-mounted launch box housing precision realization device, characterized in that, The guide rail type launch box body precision realization device includes a mounting frame (1), a box body (2), a guide rail (3), a welding stack (4), a missile (5), and an anti-spin block (6). The box body (2) is connected to the inner wall of the mounting frame (1), the missile (5) is connected inside the box body (2), the anti-spin block (6) is provided on the missile (5), the welding stack (4) is connected in the gap between the anti-spin block (6) and the guide rail (3), and the guide rail (3) is connected to the inner wall of the box body (2). The guide rail (3) includes a first guide rail and a second guide rail; The specific steps of the method are as follows: S1. The octagonal outline of the inner frame (1) is fitted and fixed on the outer octagonal outline of the box (2), and the guide rails (3) are welded to the inner wall of the short side of the box (2); S2. After forming the weld pile (4) by local welding at the end of the first guide rail, the inner envelope circles of the multiple guide rails (3) and the weld pile (4) are machined with reference to the bottom and side surfaces of the assembly frame (1) to ensure the diameter tolerance of the inner envelope circles of the multiple guide rails (3), the azimuth and pitch tolerance of the assembly frame (1), the inner side angle tolerance of the weld pile (4), and the angle tolerance of the bottom surface of the assembly frame (1). S3. The anti-spin block (6) is placed on the tail surface of the missile (5). When the missile (5) is loaded into the box (2), the inner envelope circles of the multiple guide rails (3) support the missile (5). By adjusting the phase of the missile (5), the anti-spin block (6) and the guide rails (3) maintain an appropriate gap. S4. When the missile (5) is installed into the box (2), the inner side of the weld pile (4) cooperates with the anti-spin block (6) to achieve the azimuth, pitch and roll error requirements of the box (2) and the missile (5).

2. The installation method of the guide rail type launch box housing accuracy realization device according to claim 1, characterized in that, The box (2) is octagonal in shape and includes a long side and a short side. The long side and the short side are connected at intervals. The guide rail (3) is connected to the inner wall of the short side of the box (2).

3. The installation method of the guide rail type launch box housing accuracy realization device according to claim 1, characterized in that, The inner contour of the assembly frame (1) is octagonal, and the outer contour of the assembly frame (1) is rectangular; The inner contour of the assembly frame (1) is fitted and fixed to the outer contour of the box body (2).

4. The installation method of the guide rail type launch box housing accuracy realization device according to claim 1, characterized in that, The diameter of the envelope circle formed by the multiple guide rails (3) is less than the outer diameter of the missile (5).

5. The installation method of the guide rail type launch box housing accuracy realization device according to claim 1, characterized in that, The first guide rail and the second guide rail are located on both sides of the housing (2).

6. The installation method of the guide rail type launch box housing accuracy realization device according to claim 5, characterized in that, The first guide rail and the anti-spin block (6) are connected in a one-to-one correspondence, and there is a gap between the inner side of the first guide rail and the anti-spin block (6).

7. The installation method of the guide rail type launch box housing accuracy realization device according to claim 1, characterized in that, During the process of the missile (5) being loaded into the housing (2), the inner envelope circles of the multiple guide rails (3) support the missile (5), and by adjusting the phase of the missile (5), the anti-spin block (6) and the guide rail (3) maintain an appropriate gap.

8. The installation method of the guide rail type launch box housing accuracy realization device according to claim 1, characterized in that, When the missile (5) is installed into the box (2), the inner side of the weld pile (4) cooperates with the anti-spin block (6) to achieve the azimuth, pitch and roll error requirements of the box (2) and the missile (5).

9. The installation method of the guide rail type launch box housing accuracy realization device according to claim 1, characterized in that, The anti-spin block (6) is connected to the tail surface of the missile (5).

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