Rocket composite shell section interstage connecting structure

Abstract

The utility model relates to a rocket composite shell section interstage connecting structure, which belongs to the technical field of bolt connection, and comprises a bolt seat and a nut seat, a bolt is placed in the bolt seat, the bolt seat is arranged on an upper shell section of a shell to be connected, the nut seat is arranged on a lower shell section of the shell to be connected, the nut seat is provided with a mounting port, and the mounting port is connected with the bolt seat. The tail end of the bolt tooth portion extends out of the installation opening, and a nut is arranged in the installation opening and meshed with the bolt. According to the rocket composite shell section interstage connecting structure, the bolt seat and the nut seat are designed in a split mode, the weight can be reduced, the carrying efficiency of a carrier rocket is improved, installation is easy and convenient, meanwhile, each support can be independently installed, replaced and maintained, and the rocket composite shell section interstage connecting structure has the advantages of being simple in structure, light in weight, good in maintainability and the like.

Description

Technical Field

[0001] The present invention relates to the technical field of bolt connection, and in particular to a rocket composite shell segment interstage connection structure. Background Art

[0002] Liquid launch vehicles are mainly used to send artificial satellites, biological payloads or interplanetary probes into predetermined orbits in space. In other related technologies, the shell of a launch vehicle is usually made of aluminum alloy, which is heavier than composite materials, greatly limiting the overall carrying efficiency of the rocket. Since the rocket shell is usually connected by an outward flange or an inward flange, the outward flange will affect the aerodynamic flow field of the entire rocket, increase the aerodynamic force, affect the strength of the entire rocket, and thus reduce the carrying capacity. The inward flange is difficult to process and form for composite materials, and the manufacturing cost is high. Summary of the invention

[0003] The present invention proposes a rocket composite shell segment interstage connection structure, which can solve the problem of high resistance of the outward-turned flange during rocket flight. The application of this application can reduce weight, reduce the aerodynamic force of the entire rocket, improve carrying capacity, simplify installation and maintenance, and save costs.

[0004] The technical solution of the present invention is as follows:

[0005] A rocket composite shell segment interstage connection structure, characterized in that it includes a bolt seat and a nut seat, a bolt is placed inside the bolt seat, the bolt seat is arranged on the upper shell segment of the shell to be connected, and the nut seat is arranged on the lower shell segment of the shell to be connected, the nut seat is provided with an installation opening, the tail end of the bolt tooth portion extends out of the installation opening, and a nut is present in the installation opening to engage with the bolt.

[0006] As a further optimization of this solution, the bolt seat includes a seat sleeve, a screw head cavity is arranged in the seat sleeve, a screw rod opening is arranged at the bottom of the seat sleeve, the inner diameter of the screw rod opening is adapted to the screw rod diameter of the bolt, the seat sleeve includes an upper seat sleeve and a lower seat sleeve to form a detachable structure of upper and lower pieces, the screw head cavity is adapted to the shape of the screw head of the applied bolt, the screw head of the bolt is placed in the screw head cavity, and the screw rod of the bolt extends from the screw mouth.

[0007] As a further optimization of this solution, the cross-section of the inner wall of the screw head cavity is a polygon.

[0008] As a further optimization of this solution, the edges of the bolt seat and the nut seat are both provided with fixed edges, and the fixed edges of the bolt seat and the nut seat are distributed around the bolt seat and the nut seat in the assembled state, and a plurality of through holes are distributed on the fixed edges, and the bolt seat is fixed to the upper shell segment by means of the through holes on the fixed edges and rivets, and the nut seat is fixedly connected to the lower shell segment by means of the through holes on the fixed edges.

[0009] As a further optimization of this solution, the upper shell section is provided with a groove for accommodating the lower half of the bolt seat, and the lower shell section is provided with a groove for accommodating the lower half of the nut seat.

[0010] As a further optimization of this solution, the nut seat includes a retaining ring, the mounting port is arranged on the lower side of the retaining ring, the outer diameter of the retaining ring is the same as the outer diameter of the seat sleeve, and the inner diameter of the retaining ring is the same as the inner diameter of the screw port.

[0011] As a further optimization of this solution, the external shape of the bolt seat and the nut seat after being spliced ​​is a von Karman streamline shape.

[0012] As a further optimization of the present solution, the internal cross-section of the bolt seat is hexagonal, and the head of the bolt adapted thereto is hexagonal.

[0013] The working principle and beneficial effects of the present invention are:

[0014] In this solution, the joints of the two rocket shells that need to be docked only need to have corresponding grooves in advance. When docking, the bolt seat with bolts installed is placed in the groove of the upper shell section and fixed to the upper shell section, and then the nut seat is fixed to the lower shell section, and the nut seat is docked with the protruding part of the corresponding bolt seat, and then the bolt is fixed by connecting the nut through the installation port. The application of this structure can reduce the resistance of the rocket during operation and ensure the controllability of costs.

[0015] The present application provides a rocket composite shell stage connection structure, which adopts a separate design of bolt seat and nut seat, can reduce weight, improve the carrying efficiency of the launch vehicle, and is easy to install. At the same time, each support can be replaced and maintained individually, and has the characteristics of simple structure, light weight, and good maintainability. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] The present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0017] Figure 1 This is a schematic diagram of the structure of this application;

[0018] Figure 2 It is a structural schematic diagram of the bolt seat in this application;

[0019] Figure 3 is a cross-sectional view of the bolt seat in this application;

[0020] Figure 4 It is a structural schematic diagram of the nut seat in this application;

[0021] Figure 5 It is a schematic diagram of the structure of the present application acting on the upper and lower shell sections;

[0022] Figure 6 It is a structural schematic diagram of an embedded flange in the prior art.

[0023] In the figure: 100. bolt seat, 101. upper seat sleeve, 102. lower seat sleeve, 103, fixed edge, 104, screw head cavity, 105. screw mouth, 200. nut seat, 201. retaining ring, 202. installation mouth, 300. bolt, 400. nut, 500. upper shell section, 600. lower shell section. DETAILED DESCRIPTION

[0024] The following will be combined with the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0025] As the instruction manual Figure 5 As shown, a rocket composite shell segment interstage connection structure includes a bolt seat and a nut seat, a bolt is placed inside the bolt seat, the bolt seat is arranged on the upper shell segment of the shell to be connected, and the nut seat is arranged on the lower shell segment of the shell to be connected, the nut seat is provided with a mounting opening, the tail end of the bolt tooth portion extends from the mounting opening, and a nut is present in the mounting opening to engage with the bolt.

[0026] In the traditional connection structure, the upper shell section and the lower shell section are connected by means of flanges. Generally, the flange is an outward-turned flange. If this is configured, the outward-turned edge will affect the aerodynamic flow field of the entire rocket during the high-speed flight of the rocket, affecting the flight of the rocket. For the embedded flange, the rocket shell needs to be processed and installed, and the manufacturing cost is relatively high.

[0027] The bolt seat includes a seat sleeve, a screw head cavity is provided in the seat sleeve, a screw rod opening is provided at the bottom of the seat sleeve, the inner diameter of the screw rod opening is adapted to the screw rod diameter of the bolt, the seat sleeve includes an upper seat sleeve and a lower seat sleeve to form a detachable structure of upper and lower pieces, the screw head cavity is adapted to the shape of the screw head of the applied bolt, the screw head of the bolt is placed in the screw head cavity, and the screw rod of the bolt extends out of the screw mouth. The inner wall section of the screw head cavity is polygonal. As shown in the attached manual Figure 2-3 As shown in the figure, the internal cross-section of the bolt seat is hexagonal, and the head of the bolt that matches it is hexagonal. Figure 1-4As shown, the edges of the bolt seat and the nut seat are both provided with fixed edges, which are distributed around the bolt seat and the nut seat in the assembled state, and the fixed edges are distributed with multiple through holes. The bolt seat is fixed to the upper shell section by means of the through holes on the fixed edges and rivets, and the nut seat is fixedly connected to the lower shell section by means of the through holes on the fixed edges. Figure 4 As shown, the nut seat includes a snap ring, the mounting opening is arranged at the lower side of the snap ring, the outer diameter of the snap ring is the same as the outer diameter of the seat sleeve, and the inner diameter of the snap ring is the same as the inner diameter of the screw rod opening. The upper shell section is provided with a groove for accommodating the lower half of the bolt seat, and the lower shell section is provided with a groove for accommodating the lower half of the nut seat.

[0028] When installing, first separate the upper and lower seat sleeves, put the bolt head into the screw head cavity, combine the upper seat sleeve and the lower seat sleeve, and clamp the bolt in it, then place the bolt seat in the corresponding groove outside the upper shell segment, fix the upper seat sleeve to the upper shell segment, and install all the bolt seats that need to be installed in the upper shell segment in this way, then place the nut seat in the groove of the lower shell segment, fix the nut seat to the surface of the lower shell segment through the fixed edge, butt the upper and lower shell segments, pass the screw through the nut seat, put the nut in the installation port, and tighten the bolt. The through holes distributed on the fixed edge can be used to install rivets to fix the bolt seat and nut seat. The hexagonal design of the screw head cavity can prevent the bolt from rotating axially.

[0029] The external shape of the bolt seat and the nut seat after being spliced ​​is a von Karman streamline shape, which can reduce aerodynamic resistance.

[0030] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A rocket composite shell interstage connection structure, characterized in that: It includes a bolt seat and a nut seat, a bolt is placed inside the bolt seat, the bolt seat is arranged on the upper shell section of the shell to be connected, and the nut seat is arranged on the lower shell section of the shell to be connected. The nut seat is provided with an installation opening, the tail end of the bolt tooth extends from the installation opening, and a nut is present in the installation opening to engage with the bolt.

2. A rocket composite shell segment interstage connection structure according to claim 1, characterized in that: The bolt seat includes a seat sleeve, a screw head cavity is arranged in the seat sleeve, a screw rod opening is arranged at the bottom of the seat sleeve, the inner diameter of the screw rod opening is adapted to the screw rod diameter of the bolt, the seat sleeve includes an upper seat sleeve and a lower seat sleeve to form a detachable structure of upper and lower pieces, the screw head cavity is adapted to the shape of the screw head of the applied bolt, the screw head of the bolt is placed in the screw head cavity, and the screw rod of the bolt extends out of the screw mouth.

3. A rocket composite shell segment interstage connection structure according to claim 2, characterized in that: The inner wall section of the screw head cavity is polygonal.

4. A rocket composite shell segment interstage connection structure according to claim 1, characterized in that: The edges of the bolt seat and the nut seat are both provided with fixed edges, and the fixed edges of the bolt seat and the nut seat are distributed around the bolt seat and the nut seat in the assembled state, and a plurality of through holes are distributed on the fixed edges. The bolt seat is fixed to the upper shell section by means of the through holes on the fixed edges and rivets, and the nut seat is fixedly connected to the lower shell section by means of the through holes on the fixed edges.

5. A rocket composite shell segment interstage connection structure according to claim 4, characterized in that: The upper shell section is provided with a groove for accommodating the lower half of the bolt seat, and the lower shell section is provided with a groove for accommodating the lower half of the nut seat.

6. A rocket composite shell segment interstage connection structure according to claim 2, characterized in that: The nut seat comprises a snap ring, the mounting opening is arranged at the lower side of the snap ring, the outer diameter of the snap ring is the same as the outer diameter of the seat sleeve, and the inner diameter of the snap ring is the same as the inner diameter of the screw rod opening.

7. A rocket composite shell segment interstage connection structure according to claim 2, characterized in that: The external shape of the bolt seat and the nut seat after being spliced ​​is a von Karman streamline shape.

8. A rocket composite shell segment interstage connection structure according to claim 2, characterized in that: The internal cross-section of the bolt seat is hexagonal, and the head of the bolt adapted to it is hexagonal.

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