A structure for a recoverable launch vehicle cabin section

Abstract

The application relates to the field of aerospace technology and discloses a cabin section structure suitable for a recoverable carrier rocket, which comprises a cabin section structure main body, the cabin section structure main body is mainly composed of a thin wall, a high rib and a grid, and the thin wall and the high rib are integrated through the spinning, milling and turning modes to process an aluminum alloy cylinder ingot, so that the design time of the rivet structure is reduced, and the design efficiency is improved. A large number of part assembly designs are needed for a traditional semi-hard shell structure, including rivet design. The rivet design is related to hole making requirements, positioning size and rivet specifications and the like. The design work usually accounts for 30-40% of the workload of a designer. However, the unit wall plate structure of the application cancels the rivet structure, realizes rivet avoidance design, and greatly improves the design efficiency of the structure product.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aerospace technology, in particular to a cabin section structure suitable for a recoverable launch vehicle. BACKGROUND

[0002] As the main tool for space exploration, rockets have traditionally been used only once, but the high cost has limited the development of space engineering. Recoverable rocket cabin sections are of great significance. First, they reduce costs by being reused after proper maintenance and inspection, achieving significant cost savings. Second, recoverable cabin sections shorten the development cycle, avoiding the need to redesign and manufacture new cabin sections, speeding up project progress. In addition, recoverable cabin sections improve reliability through multiple uses and improvements, reducing the risk of launch mission failure. Most importantly, recoverability meets the goal of sustainable development, reducing the generation of space debris. Currently, the cabin section uses a skin-stringer-ring frame structure, which requires a large number of rivets to connect between the skin and the stringer. The assembly strength and complexity of this structure accounts for more than 70% of the entire cabin section production and manufacturing. Therefore, a cabin section structure that can meet the strength requirements of the rocket recovery cabin section and reduce the complexity of design and assembly has become one of the key technologies.

[0003] The skin-stringer structure is usually connected using rivets. However, the holes of the rivets introduce stress concentration points, leading to structural weaknesses and the generation of fatigue cracks. Stress concentration also increases the weight of the structure and the risk of material fatigue. The assembly of the skin-stringer structure usually requires welding or sealing treatment at the joints to ensure the sealing of the structure. However, the quality control requirements of welding and sealing treatment are high, and there is a risk of leakage, especially in high-pressure or low-temperature environments. The rivet assembly of the skin-stringer structure accounts for about 70% of the total cabin section manufacturing time, with high labor intensity and high skill requirements for operators.

[0004] The traditional semi-hard shell structure includes a skin and a stringer structure, which are connected together by rivet fasteners. The present application realizes the integrated formation of the skin structure and the stringer structure by equating the thin wall to the skin structure and equating the high rib part to the stringer structure, thereby eliminating the rivet fastener structure, as shown in Figure 1 This innovative design not only realizes an integrated structure form, but also optimizes the combination of thin walls and high rib parts to achieve the goals of general productization and reducing product configurations. SUMMARY

[0005] (I) Technical problems solved

[0006] In view of the deficiencies of the prior art, the present application provides a cabin section structure suitable for a recoverable launch vehicle.

[0007] (II) Technical solutions

[0008] To achieve the above object, the application provides the following technical scheme: a recyclable launch vehicle cabin section structure, comprising a cabin section structure main body, which is mainly composed of a thin wall, a high rib and a grid, and is obtained by processing an aluminum alloy cylinder ingot through spinning, milling and turning.

[0009] Preferably, the preparation method is:

[0010] S1: obtaining an aluminum alloy cylinder ingot through rolling / roll bending / isometric bending and the like;

[0011] S2: heat treatment after aluminum alloy cylinder ingot interface welding;

[0012] S31: forming a grid thin wall high rib structure of the aluminum alloy cylinder ingot through a spinning process;

[0013] S32: forming a grid thin wall high rib structure of the aluminum alloy cylinder ingot through a milling process;

[0014] S4: solid solution aging of the formed grid thin wall high rib structure cabin section to achieve T6 state.

[0015] The internal structure is uniform;

[0016] S5: turning processing of the cabin section to process the aluminum alloy cylinder ingot allowance.

[0017] Preferably, the S31 specifically comprises: manufacturing an original aluminum cylinder blank, installing the cylinder blank in a rolling tool equipment, the rolling tool equipment comprising an external mold, a rotating shaft and a spinning roller, the internal shape of the external mold being adapted to the shape of the grid, the rotating shaft and the spinning roller being threadedly connected, the spinning roller being wedge-shaped and placed from small to large and from top to bottom, and the spinning roller being gradually spun to the top end of the external mold.

[0018] Preferably, the specific steps of the S31 are: the outer surface of the cylinder blank is in contact with the external mold, the spinning roller placed at the bottom of the cylinder blank is attached to the rotating shaft to spin the cylinder blank from bottom to top until the cylinder blank is attached to the external mold to form a grid high rib structure, and the cylinder blank is finally placed at the top end of the spinning equipment.

[0019] Preferably, the diameter of the cylinder blank is r and the height is h, the diameter r is smaller than the final cabin section diameter R, the height of the cylinder blank is greater than the height H of the cabin section, the cylinder blank is finally placed at the top end of the spinning equipment, at this time, the height of the cylinder blank is greater than the initial height h of the cylinder blank, and the overall solid solution aging is adopted to improve the material performance of the cylinder blank to T6 state.

[0020] Preferably, the S32 is specifically that the cylinder embryo is formed by milling through a cylindrical inner support positioning tool machine, and is fixed on a machining platform through a positioning machine, then a milling operation is performed by using a machining equipment, and thin walls and high rib parts are gradually machined and formed according to design requirements.

[0021] Preferably, the cabin section structure body is made by segmenting thin-walled high-rib unit plates one by one, and is formed into an integral cabin section by segmental welding and assembly, the thin-walled high-rib unit plates need to be heat treated first, the integral cabin section after welding and assembly is subjected to solid solution and aging treatment as a whole, and the cabin section is subjected to X-ray detection of welds.

[0022] Preferably, through the electric arc additive manufacturing 3D printing technology, the thin-walled grid high-rib structure is gradually formed from a line-surface body according to three-dimensional digital modeling by continuously adding wire materials through layer-by-layer surfacing.

[0023] (Three) beneficial effects

[0024] Compared with the prior art, the application provides a cabin section structure suitable for a recoverable launch vehicle, which has the following beneficial effects:

[0025] 1. The cabin section structure suitable for a recoverable launch vehicle reduces the design time of rivet structures and improves the design efficiency. The traditional semi-hard shell structure needs a large amount of part assembly design, which includes rivet design. Rivet design involves hole making requirements, positioning size and rivet specifications. This design work usually accounts for 30-40% of the workload of designers. However, the unit wall plate structure of the application cancels the rivet structure, realizes the avoidance design of rivets, and greatly improves the design efficiency of the structure product.

[0026] 2. The cabin section structure suitable for a recoverable launch vehicle cancels the rivet riveting assembly time and improves the production efficiency. In the traditional assembly process, tens of thousands of rivets are usually used for a cabin section. The time required for the riveting process accounts for more than 80% of the entire missile body cabin section assembly time. However, the unit wall plate structure of the application cancels the rivet structure, so a large amount of time is saved in the structure assembly of the missile body cabin section, and the production efficiency is finally significantly improved. BRIEF DESCRIPTION OF DRAWINGS

[0027] Figure 1 is a thin-walled and high-rib integrated structure of a recoverable cabin section of the application;

[0028] Figure 2 is a spinning method of a thin-walled and high-rib integrated structure of a recoverable cabin section of the application;

[0029] Figure 3 is a milling processing method of a thin-walled and high-rib integrated structure of a recoverable cabin section of the application.

[0030] In the figure: 1, outer mold; 2, rotating shaft; 3, spinning roller; 4, cabin section structure main body; 5, positioning tool; 41, thin wall; 42, high rib; 43, grid. DETAILED DESCRIPTION

[0031] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the scope of protection of the present application.

[0032] Please refer to Figures 1-3 A cabin section structure suitable for a recoverable launch vehicle, comprising a cabin section structure main body 4, which is mainly composed of a thin wall 41, a high rib 42 and a grid 43, and is obtained by processing an aluminum alloy cylinder ingot through spinning, milling and turning to form an integrated structure of the thin wall and the high rib.

[0033] The preparation method is as follows:

[0034] S1: obtaining an aluminum alloy cylinder ingot through rolling / bending / isometric bending and other processes;

[0035] S2: heat treatment after interface welding of the aluminum alloy cylinder ingot;

[0036] S31: forming a grid thin wall high rib structure through a spinning process of the aluminum alloy cylinder ingot;

[0037] S32: forming a grid thin wall high rib structure through a milling process of the aluminum alloy cylinder ingot;

[0038] S4: solid solution aging of the formed grid thin wall high rib structure cabin section to achieve T6 state;

[0039] Uniform internal structure;

[0040] S5: turning processing of the cabin section to process the aluminum alloy cylinder ingot allowance;

[0041] The S31 specifically comprises the following steps: manufacturing an original aluminum cylinder blank, installing the cylinder blank in a rolling tool equipment, the rolling tool equipment comprising an outer mold 1, a rotating shaft 2 and a spinning roller 3, the inner shape of the outer mold 1 being matched with the shape of the grid, the rotating shaft 2 and the spinning roller 3 being threadedly connected, the spinning roller 3 being wedge-shaped and placed from small to large and from top to bottom, and spinning layer by layer to the top end of the outer mold 1,

[0042] The specific step of S31 is that the outer surface of the cylinder embryo contacts the outer mold 1, the spinning roller 3 at the bottom of the cylinder embryo adheres to the rotating shaft 2 to spin the cylinder embryo from bottom to top until the cylinder embryo is attached to the outer mold 1 to form a grid high rib structure, and the cylinder embryo is extruded and finally placed at the top end of the spinning equipment.

[0043] The diameter of the cylinder embryo is r and the height is h, the diameter r is smaller than the final cabin section diameter R, the height of the cylinder embryo is greater than the height of the cabin section H, the cylinder embryo is extruded and finally placed at the top end of the spinning equipment, at this time the height of the cylinder embryo is greater than the initial cylinder embryo height h, and the overall solid solution aging is adopted to improve the material performance of the cylinder embryo to T6 state.

[0044] S32 is specifically that the cylinder embryo is machined and milled by the cylinder inner support positioning tool 5, and is fixed on the machining platform by the positioning machine, then the milling operation is performed by using the machining equipment, and the thin-walled and high-rib parts are gradually machined and formed according to the design requirements.

[0045] The cabin section structure body 4 is made by segmenting thin-walled high-rib unit plates one by one, and is assembled by segmenting welding to form an overall cabin section, the thin-walled high-rib unit plate needs to be heat treated first, the overall cabin section after welding assembly is treated by solid solution aging, and the cabin section is detected by X-ray for weld.

[0046] By the 3D printing technology of electric arc additive manufacturing, the wire material is continuously added by the principle of layer-by-layer surfacing cladding, the thin-walled grid high-rib structure is gradually formed from the line surface body according to the three-dimensional digital modeling.

[0047] Although the embodiments of the present application have been shown and described, it can be understood by those skilled in the art that various changes, modifications, replacements and variations can be made to the embodiments without departing from the principles and spirits of the present application, the scope of the present application is defined by the appended claims and their equivalents.

Claims

1. A method for preparing a recoverable launch vehicle compartment structure, comprising a compartment structure body (4), characterized in that: The cabin structure body (4) is mainly composed of a thin wall (41), high ribs (42) and a grid (43), and the thin wall and high rib integrated structure is obtained by processing the aluminum alloy cylindrical ingot by spinning, milling and turning; Its preparation method is: S1: Aluminum alloy cylindrical ingots are obtained by rolling / rolling / equidistant bending processes; S2: Heat treatment after welding of aluminum alloy barrel ingot interface; S31: Aluminum alloy cylindrical ingot is formed into a grid thin-wall high-rib structure through a spinning process; S32: Aluminum alloy cylindrical ingot is milled to form a grid thin-wall high-rib structure; S4: The formed thin-walled gridded high-ribbed structure cabin is subjected to solid solution aging to achieve T6 state, and the internal structure is uniform; S5: Turn the cabin section to process the excess of the aluminum alloy barrel ingot; The S31 specifically comprises: making an original aluminum tube blank, installing the tube blank in a rolling tooling device, wherein the rolling tooling device comprises an external mold (1), a rotating shaft (2) and a spinning roller (3), wherein the internal shape of the external mold (1) is adapted to the grid shape, the rotating shaft (2) and the spinning roller (3) are threadedly connected, and the spinning roller (3) is wedge-shaped and arranged from small to large and from top to bottom, and is spun layer by layer to the top of the external mold (1); The specific steps of S31 are as follows: the outer surface of the tube blank contacts the external mold (1), the spinning roller (3) placed at the bottom of the tube blank is attached to the rotating shaft (2) and spins the tube blank from bottom to top until the tube blank fits with the external mold (1) to form a grid high-rib structure, and the tube blank is extruded and finally placed on the top of the spinning equipment; The barrel blank has a diameter of r and a height of h, wherein the diameter r is smaller than the final compartment diameter R, and the barrel blank height is larger than the compartment height H. The barrel blank is expected to be finally placed on the top of the spinning equipment after extrusion, and the barrel blank height is larger than the initial barrel blank height h. The overall solid solution aging is used to improve the barrel blank material performance to the T6 state; The S32 is specifically as follows: the barrel blank is machined and milled by the cylindrical inner support positioning fixture (5), and is fixed on the processing platform by a positioning machine, and then the milling operation is performed by machining equipment to gradually process and shape the thin-walled and high-ribbed parts according to the design requirements.

2. The method for preparing a recoverable launch vehicle compartment structure according to claim 1, characterized in that: The cabin structure body (4) is made of thin-walled high-rib unit plates one by one, and the sections are welded and assembled to form an integral cabin. The thin-walled high-rib unit plates need to be heat treated first, and the integral cabin after welding and assembly is subjected to solid solution aging treatment as a whole, and the cabin welds are X-ray inspected.

3. The method for preparing a recoverable launch vehicle compartment structure according to claim 1, characterized in that: Through arc additive manufacturing 3D printing technology, wire is continuously added through the principle of layer-by-layer welding and cladding, and according to three-dimensional digital modeling, a thin-walled grid high-rib structure is gradually formed from the line-surface body.

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