Rocket fairing matched workpiece forming equipment

Abstract

The utility model relates to the technical field of rocket fairings, in particular to rocket fairing matched workpiece forming equipment which comprises a main body, the bottom of the main body is fixedly connected with a bottom end protection assembly, the interior of the main body is fixedly connected with an internal protection assembly, and the top of the internal protection assembly is fixedly connected with a top control assembly. The strength of the rocket fairing is improved through the inner grid sleeve, the dense stiffened plates and the high stiffened plates in the carbon fiber composite shell, the requirements for high performance and light weight of spaceflight in rocket upgrading and updating projects can be met, the requirements for different launching tasks can be met, the investment cost of protection materials can be greatly reduced, and the service life of the rocket fairing is prolonged. The loading time can be shortened, the launching success rate and recoverability can be improved, and the titanium alloy groove, the graphene plate and the inorganic non-metal plate are used for protecting the rocket from being affected by aerodynamic force and protecting the rocket from being affected by pneumatic heating.

Description

Technical Field

[0001] The utility model relates to the technical field of rocket fairings, in particular to a rocket fairing matching workpiece forming device. Background Art

[0002] The flow cover is used to protect the rocket and other payloads to prevent the rocket from being affected by harmful environments such as aerodynamics, aerodynamic heating and acoustic vibration. It is an important component of the launch vehicle. The rocket fairing is generally a clamshell structure, consisting of an end, a front cone section, a cylindrical section, an inverted cone section and longitudinal and transverse separation mechanisms.

[0003] Authorization announcement No. CN216308781 U discloses a fairing unlocking mechanism and a launch vehicle. Compared with the traditional rocket fairing that uses pyrotechnics and explosive bolts for radial separation and unlocking, the unlocking structure provided by the utility model has lower cost, lower requirements on installation personnel and installation environment, and no corresponding protective devices are required. While achieving the same function as pyrotechnics, it reduces product costs, transportation costs and installation requirements; however, in this scheme, when separating and unlocking the rocket, in order to consider the material problem of the fairing itself, whether it can be separated smoothly, the material use of the fairing needs to meet many adjustments before it can be separated smoothly, and this patent is used for the fairing structure form that matches the rocket, which cannot meet the high performance and lightweight requirements of aerospace in the rocket upgrade project. Therefore, a rocket fairing matching workpiece forming equipment is needed to improve the above problems. Utility Model Content

[0004] In order to solve the problem in the existing solution that when separating and unlocking the rocket, in order to consider the material problem of the fairing itself, whether the separation can be carried out smoothly, the material use of the fairing needs to meet many adjustments before it can be separated smoothly, and this patent is used for the fairing structure that matches the rocket, which cannot meet the high performance and lightweight requirements of aerospace in the rocket upgrade project. The purpose of this utility model is to provide a rocket fairing matching workpiece forming equipment to solve the problems raised in the above-mentioned background technology.

[0005] In order to achieve the above purpose, the utility model provides the following technical solutions:

[0006] A rocket fairing supporting workpiece forming device comprises a main body, a bottom end protection component is fixedly connected to the bottom of the main body, an internal protection component is fixedly connected to the inside of the main body, and a top control component is fixedly connected to the top of the internal protection component;

[0007] The main body comprises a carbon fiber composite shell, a side of the carbon fiber composite shell is fixedly connected to a petal mold, and a top of the carbon fiber composite shell is fixedly connected to an end head;

[0008] The internal protection component includes an inner grid sleeve, the interior of the inner grid sleeve is fixedly connected with a dense reinforced plate and a high reinforced plate, the top of the inner grid sleeve is fixedly connected with a titanium alloy groove, and the interior of the titanium alloy groove is fixedly connected with a graphene plate and an inorganic non-metallic plate.

[0009] As a preferred solution of the utility model, the inner grid sleeve and the titanium alloy groove are on the same vertical plane, and the inner grid sleeve and the titanium alloy groove are fixedly connected to the carbon fiber composite shell.

[0010] As a preferred solution of the utility model, the bottom protection assembly includes an external pressure frame, and the bottom of the external pressure frame is fixedly connected to a base mold.

[0011] As a preferred solution of the utility model, the top control assembly includes a supporting cross plate, the top of the supporting cross plate is fixedly connected to a supporting partition, and the side of the supporting partition is fixedly connected to a rocket mainboard.

[0012] As a preferred solution of the utility model, a control separation integrated board is fixedly connected to the side of the receiving partition, and a track module is fixedly connected to the side of the control separation integrated board.

[0013] As a preferred solution of the utility model, the top of the receiving partition is fixedly connected to a top plate, the top of the top plate is fixedly connected to a connecting groove, and the side of the receiving partition is provided with a fixing piece.

[0014] As a preferred solution of the utility model, a spray pipe is fixedly connected inside the connecting groove, a magnesium alloy cover is fixedly connected to the top of the connecting groove, and a loading end is fixedly connected to the top of the magnesium alloy cover.

[0015] As a preferred solution of the utility model, a label is fixedly connected to the side of the carbon fiber composite shell, a polymer transparent window is opened on the side of the carbon fiber composite shell, and aerospace glass is fixedly connected to the inside of the polymer transparent window.

[0016] Compared with the prior art, the beneficial effects of the utility model are:

[0017] 1. In the utility model, the inner grid sleeve, dense stiffened plate and high stiffened plate inside the carbon fiber composite shell are used to increase the strength of the rocket fairing, which can meet the high performance and lightweight requirements of aerospace in rocket upgrading projects, and can meet the needs of different launch missions. It can not only greatly reduce the cost of protective material investment, but also shorten the loading time, and improve the success rate and recyclability of the launch.

[0018] 2. In the utility model, titanium alloy grooves, graphene plates and inorganic non-metallic plates are used to protect the rocket from aerodynamic forces and aerodynamic heating. The rocket main board, control separation integrated board and trajectory module can unlock the separation system to ensure that the rocket fairing can be separated smoothly. When the carrier rocket is in a pre-launch state, the temperature and humidity in the fairing can be adjusted to ensure that the rocket is not affected by low temperature and environment. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is a schematic diagram of the overall structure of the utility model;

[0020] Figure 2 It is a schematic diagram of a partial decomposition structure of the utility model;

[0021] Figure 3 It is a schematic diagram of the exploded structure of the internal protection component of the utility model;

[0022] Figure 4 It is a schematic diagram of the exploded structure of the top control component of the utility model.

[0023] In the figure: 1. Main body; 101. Carbon fiber composite shell; 102. Label; 103. End; 104. Petal mold; 105. Polymer transparent window; 2. Bottom protection component; 201. External pressure frame; 202. Base mold; 3. Internal protection component; 301. Inner grid sleeve; 302. Densely reinforced plate; 303. Highly reinforced plate; 304. Titanium alloy groove; 305. Graphene plate; 306. Inorganic non-metallic plate; 4. Top control component; 401. Supporting cross plate; 402. Supporting partition; 403. Fixing part; 404. Rocket main board; 405. Control separation integrated board; 406. Trajectory module; 407. Top plate; 408. Connection groove; 409. Ejection tube; 410. Magnesium alloy cover; 411. Loading end. DETAILED DESCRIPTION

[0024] The technical solutions in the embodiments of the utility model will be clearly and completely described below in conjunction with the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, rather than all of the embodiments. Based on the embodiments of the utility model, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the utility model.

[0025] Example: See Figure 1-Figure 4 The rocket fairing supporting workpiece forming device shown in the figure comprises a main body 1, a bottom protection component 2 is fixedly connected to the bottom of the main body 1, an internal protection component 3 is fixedly connected to the inside of the main body 1, and a top control component 4 is fixedly connected to the top of the internal protection component 3;

[0026] In this embodiment, refer to Figure 1 , Figure 2 and Figure 3 As shown, the main body 1 includes a carbon fiber composite shell 101, the side of the carbon fiber composite shell 101 is fixedly connected with a petal mold 104, the top of the carbon fiber composite shell 101 is fixedly connected with an end head 103, the internal protection component 3 includes an inner grid sleeve 301, the inner part of the inner grid sleeve 301 is fixedly connected with a dense stiffened plate 302 and a high stiffened plate 303, the top of the inner grid sleeve 301 is fixedly connected with a titanium alloy groove 304, the inner part of the titanium alloy groove 304 is fixedly connected with a graphene plate 305 and an inorganic non-metallic plate 306, the inner grid sleeve 301, the dense stiffened plate 302 and the high stiffened plate 303 inside the carbon fiber composite shell 101 are used to increase the strength of the rocket fairing, which can meet the high performance and lightweight requirements of aerospace in the rocket upgrade project, can meet the needs of different launch missions, can not only greatly reduce the cost of protection material investment, but also shorten the loading time, and can improve the success rate and recyclability of the launch.

[0027] Among them, the inner grid sleeve 301 and the titanium alloy groove 304 are on the same vertical plane, the inner grid sleeve 301 and the titanium alloy groove 304 are fixedly connected to the carbon fiber composite shell 101, the bottom protection component 2 includes an external pressure frame 201, and the bottom of the external pressure frame 201 is fixedly connected to a base mold 202. The titanium alloy groove 304, the graphene plate 305 and the inorganic non-metallic plate 306 are used to protect the rocket from the effect of aerodynamic force and the effect of aerodynamic heating.

[0028] In this embodiment, refer to Figure 1 and Figure 4As shown, the top control assembly 4 includes a supporting horizontal plate 401, the top of the supporting horizontal plate 401 is fixedly connected to a supporting partition 402, the side of the supporting partition 402 is fixedly connected to a rocket mainboard 404, the side of the supporting partition 402 is fixedly connected to a control separation integrated board 405, the side of the control separation integrated board 405 is fixedly connected to a trajectory module 406, the top of the supporting partition 402 is fixedly connected to a top plate 407, the top of the top plate 407 is fixedly connected to a connecting groove 408, the side of the supporting partition 402 is provided with a fixing piece 403, the interior of the connecting groove 408 is fixedly connected to a spray pipe 409, and the connecting groove 4 08 is fixedly connected to the top with a magnesium alloy cover 410, and the top of the magnesium alloy cover 410 is fixedly connected to the loading end 411, and the side of the carbon fiber composite shell 101 is fixedly connected with a label 102, and the side of the carbon fiber composite shell 101 is provided with a polymer transparent window 105, and the inside of the polymer transparent window 105 is fixedly connected with aerospace glass. The separation system can be unlocked by using the rocket main board 404, the control separation integrated board 405 and the trajectory module 406 to ensure that the rocket fairing can be separated smoothly. When the carrier rocket is in a pre-launch state, the temperature and humidity in the fairing can be adjusted to ensure that the rocket is not affected by low temperature and environment.

[0029] In the present scheme, a rocket fairing supporting workpiece forming equipment is loaded with an inner grid sleeve 301, a dense stiffened plate 302 and a high stiffened plate 303 inside a carbon fiber composite shell 101 when in use, thereby increasing the strength of the rocket fairing, and utilizing a titanium alloy groove 304, a graphene plate 305 and an inorganic non-metallic plate 306 to protect the rocket from aerodynamic forces and aerodynamic heating. The rocket main board 404, the control separation integrated board 405 and the trajectory module 406 can unlock the separation system to ensure that the rocket fairing can be separated smoothly, thereby increasing its separation efficiency.

[0030] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A rocket fairing supporting workpiece forming device, comprising a main body (1), characterized in that: The bottom of the main body (1) is fixedly connected to a bottom protection component (2), the interior of the main body (1) is fixedly connected to an internal protection component (3), and the top of the internal protection component (3) is fixedly connected to a top control component (4); The main body (1) comprises a carbon fiber composite shell (101), a side of the carbon fiber composite shell (101) is fixedly connected to a split mold (104), and a top of the carbon fiber composite shell (101) is fixedly connected to an end head (103); The internal protection component (3) comprises an inner grid sleeve (301), the interior of the inner grid sleeve (301) being fixedly connected with a densely reinforced plate (302) and a highly reinforced plate (303), the top of the inner grid sleeve (301) being fixedly connected with a titanium alloy groove (304), and the interior of the titanium alloy groove (304) being fixedly connected with a graphene plate (305) and an inorganic non-metallic plate (306).

2. The rocket fairing supporting workpiece forming equipment according to claim 1 is characterized in that: The inner grid sleeve (301) and the titanium alloy groove (304) are on the same vertical plane, and the inner grid sleeve (301) and the titanium alloy groove (304) are fixedly connected to the carbon fiber composite shell (101).

3. The rocket fairing supporting workpiece forming equipment according to claim 1 is characterized in that: The bottom protection assembly (2) comprises an external pressure frame (201), and the bottom of the external pressure frame (201) is fixedly connected to a base mold (202).

4. The rocket fairing supporting workpiece forming equipment according to claim 1 is characterized in that: The top control assembly (4) comprises a supporting transverse plate (401), the top of the supporting transverse plate (401) is fixedly connected to a receiving partition (402), and the side of the receiving partition (402) is fixedly connected to a rocket mainboard (404).

5. The rocket fairing supporting workpiece forming equipment according to claim 4 is characterized in that: A control separation integrated board (405) is fixedly connected to the side of the receiving partition (402), and a track module (406) is fixedly connected to the side of the control separation integrated board (405).

6. The rocket fairing supporting workpiece forming equipment according to claim 4 is characterized in that: The top of the receiving partition (402) is fixedly connected to a top plate (407), the top of the top plate (407) is fixedly connected to a connecting groove (408), and a fixing piece (403) is provided on the side of the receiving partition (402).

7. The rocket fairing supporting workpiece forming equipment according to claim 6 is characterized by: The interior of the connection groove (408) is fixedly connected with a spray pipe (409), the top of the connection groove (408) is fixedly connected with a magnesium alloy cover (410), and the top of the magnesium alloy cover (410) is fixedly connected with a loading end (411).

8. The rocket fairing supporting workpiece forming equipment according to claim 1 is characterized in that: A label (102) is fixedly connected to the side of the carbon fiber composite shell (101), a polymer transparent window (105) is opened on the side of the carbon fiber composite shell (101), and aerospace glass is fixedly connected inside the polymer transparent window (105).

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