Preparation method of integrated light-weight tail section of carrier rocket

Abstract

The invention relates to a preparation method of an integrated light-weight launch vehicle tail section, and belongs to the technical field of launch vehicles, and the preparation method comprises the following steps: S100, carrying out forward and reverse bidirectional profiling on an aluminum honeycomb panel to obtain a first arc plate which adopts a three-section arc structure, and taking an arc positioned in the middle as a first arc part, the arcs located at the two ends serve as second arc parts, and the first arc parts and the second arc parts are tangent and opposite in direction. S200, performing one-way compression on the aluminum honeycomb panel to obtain a second arc plate; s300, the second arc plates are welded to the two ends of the first arc plate correspondingly to obtain semicircular wall plates, and the circle centers of the second arc parts coincide with the circle centers of the second arc plates; and S400, the step S100 to the step S300 are repeated, the two wall plates are in butt joint and then welded, and the annular carrier rocket tail section is obtained.The technical problem that in the prior art, the development requirements of light weight, modularization and low cost cannot be met can be solved.

Description

Technical Field

[0001] The invention belongs to the technical field of launch vehicles, and in particular relates to a method for preparing an integrated lightweight launch vehicle tail section. Background Art

[0002] The tail section, as the main section of a reusable launch vehicle, is generally located at the rear end of the launch vehicle and is used to connect the engine frame and the propellant tank. It not only needs to provide a good temperature and mechanical environment for the instruments and equipment in the cabin, but is also the main bearing position of the concentrated force transmitted by the landing support mechanism.

[0003] CN116399184A discloses a carrier rocket tail section structure and a carrier rocket, comprising: an upper support frame, an intermediate frame and a lower support frame, wherein the upper support frame, the intermediate frame and the lower support frame are used to bear radial loads and are arranged at intervals along the axial direction of the carrier rocket tail section structure; the two ends of at least one longitudinal support member among a plurality of longitudinal support members are respectively connected to the upper support frame and the intermediate frame, and the two ends of at least one longitudinal support member are respectively connected to the intermediate frame and the lower support frame; a skin is arranged on the longitudinal support member, and the skin covers the upper support frame, the intermediate frame, the lower support frame and the longitudinal support member. The tail section structure has a heavy overall weight, numerous process steps and complex assembly, a large amount of welding, large welding deformation and stress, and low production efficiency, and cannot meet the development needs of lightweight, modularization and low cost. Summary of the invention

[0004] In view of the various shortcomings of the existing technology, a method for preparing an integrated lightweight launch vehicle tail section is proposed to solve the technical problem that the existing technology cannot meet the development needs of lightweight, modularization and low cost.

[0005] To achieve the above object, the present invention provides the following technical solutions: A method for preparing an integrated lightweight launch vehicle tail section comprises the following steps: S100, performing positive and negative bidirectional pressing on the aluminum honeycomb panel to obtain a first arc panel, wherein the first arc panel adopts a three-segment arc structure, wherein the arc located in the middle is used as the first arc portion, and the arcs located at both ends are used as the second arc portions, and the first arc portion is tangent to the second arc portion and faces in opposite directions; S200, performing unidirectional pressing on the aluminum honeycomb panel to obtain a second arc panel; S300, welding the second arc plates at both ends of the first arc plate to obtain a semicircular wall plate, wherein the center of the second arc portion coincides with the center of the second arc plate; S400, repeating steps S100 to S300, first butting the two wall panels and then welding them to obtain a ring-shaped launch vehicle tail section.

[0006] The technical solution is further configured as follows: the manufacturing method of the aluminum honeycomb panel is: Along the length direction of the main honeycomb core, a first reinforcement plate is welded at the end of the main honeycomb core to form a first reinforcement end; Along the width direction of the main honeycomb core, a second reinforcement plate is welded at the end of the main honeycomb core to form a second reinforcement end; Panels are welded above and below the main honeycomb core, the first reinforcement plate, and the second reinforcement plate, respectively, to obtain the aluminum honeycomb panel.

[0007] The technical solution is further configured such that both the first reinforcement plate and the second reinforcement plate are reinforced aluminum honeycomb panels, and the honeycomb core arrangement of the reinforced aluminum honeycomb panels is the same as the main honeycomb core arrangement.

[0008] The technical solution is further configured that, in step S100, the aluminum honeycomb panel is subjected to positive and negative bidirectional profiling to obtain a first arc panel, specifically comprising: S101, placing the aluminum honeycomb panel in a first pressing mold for pre-pressing, first pre-pressing the first arc portion, then turning the aluminum honeycomb panel 180 degrees, and pre-pressing the second arc portion at the end of the first arc portion; S102, placing the pre-pressed aluminum honeycomb panel in a second pressing mold for secondary pressing to obtain the first arc panel.

[0009] The technical solution is further configured as follows: the first pressing mold is a wooden mold, and the second pressing mold is a steel mold.

[0010] The technical solution is further configured that the thickness of the first arc plate is , the radius of the first arc portion is , the radius of the second arc portion is ,but , and Should meet: ,and .

[0011] The technical solution is further configured to, before step S300, also include welding an edge beam to one of the second reinforcement ends of the second arc plate, and welding an edge plate to the first reinforcement ends of the first arc plate and the second arc plate respectively.

[0012] The technical solution is further configured that the welding method of the edge beam is: A groove is formed inside the second reinforcing plate, the first end of the edge beam is embedded in the groove and welded, and the second end of the edge beam is thinned in the thickness direction to form an overlapping edge.

[0013] The technical solution is further configured such that, in step S300, the two second reinforcement ends of the first arc plate are respectively welded to the second reinforcement ends of the unwelded edge beams of the second arc plate to obtain a semicircular wall panel.

[0014] The technical solution is further configured as follows: in step S400, the edge beams of the two wall panels are butt-jointed in an overlapping manner and then welded to obtain a ring-shaped carrier rocket tail section. The beneficial effects of the present invention are: Aluminum honeycomb panels are used as the main material, fully utilizing the characteristics of aluminum honeycomb panels such as high load-bearing capacity, light weight, impact resistance, temperature resistance, weldability and good formability to meet the development needs of the tail section of the launch vehicle, such as thermal insulation, long life, low cost and lightweight; the first arc plate and the second arc plate can be processed separately to improve the convenience of manufacturing the tail section of the launch vehicle, meet the modular production needs, and improve production efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a flowchart of a method for preparing an integrated lightweight launch vehicle tail section in an embodiment of the present invention; Figure 2 Schematic diagram of an integrated lightweight launch vehicle tail section in an embodiment of the present invention; Figure 3 is a schematic diagram of a wall panel according to an embodiment of the present invention; Figure 4 is a side view of a second arc plate in an embodiment of the present invention; Figure 5 yes Figure 4 Middle AA section view; Figure 6 yes Figure 4 Middle BB section view; Figure 7 yes Figure 4 Middle CC section view; Figure 8 is a top view of a first arc plate in an embodiment of the present invention; Fig. 9 is a schematic diagram of a first pressing mold in an embodiment of the present invention; Fig.10 Schematic diagram of the second pressing mold in an embodiment of the present invention.

[0016] In the accompanying drawings: 100, wall panel; 200, first arc plate; 201, first circular arc portion; 202, second circular arc portion; 300, second arc plate; 400, edge plate; 500, edge beam; 501, overlapping edge; 600, aluminum honeycomb panel; 700, first reinforcement plate; 800, second reinforcement plate; 110, first upper mold; 120, first lower mold; 130, second upper mold; 140, second lower mold. DETAILED DESCRIPTION

[0017] In order to enable those skilled in the art to better understand the technical solution of the present invention, the technical solution of the present invention is clearly and completely described below in conjunction with the accompanying drawings of the present invention. Based on the embodiments in this application, other similar embodiments obtained by ordinary technicians in this field without making creative work should all fall within the scope of protection of this application. In addition, the directional words mentioned in the following embodiments, such as "up", "down", "left", "right", etc., are only reference to the directions of the accompanying drawings. Therefore, the directional words used are used to illustrate rather than limit the invention.

[0018] According to an embodiment of the present invention, a method for preparing an integrated lightweight launch vehicle tail section is provided. Figures 1 to 3 , including the following steps: S100, performing positive and negative bidirectional pressing on the aluminum honeycomb panel to obtain a first arc panel 200, wherein the first arc panel 200 adopts a three-segment arc structure, wherein the arc at the middle position is used as a first arc portion 201, and the arcs at both ends are used as second arc portions 202, and the first arc portion 201 is tangent to the second arc portion 202 and faces in opposite directions; S200, performing unidirectional pressing on the aluminum honeycomb panel to obtain a second arc panel 300; S300, welding the second arc plates 300 at both ends of the first arc plate 200 to obtain a semicircular wall plate 100, wherein the center of the second arc portion 202 coincides with the center of the second arc plate 300; S400, repeating steps S100 to S300, first butting the two wall panels 100 and then welding them to obtain a ring-shaped launch vehicle tail section.

[0019] It should be noted that the aluminum honeycomb panel is used as the main material, and the characteristics of the aluminum honeycomb panel such as high load-bearing capacity, light weight, impact resistance, temperature resistance, weldability and good formability are fully utilized to meet the development needs of the tail section of the launch vehicle such as heat insulation, long life, low cost and light weight; the first arc plate 200 and the second arc plate 300 can be processed separately, which improves the convenience of manufacturing the tail section of the launch vehicle, meets the modular production needs, and improves production efficiency.

[0020] In the method for preparing the integrated lightweight launch vehicle tail section of this embodiment, please refer to Figures 1 to 7 The manufacturing method of the aluminum honeycomb panel 600 is as follows: Along the length direction of the main honeycomb core, a first reinforcement plate 700 is welded at the end of the main honeycomb core to form a first reinforcement end; A second reinforcement plate 800 is welded at the end of the main honeycomb core along the width direction of the main honeycomb core to form a second reinforcement end; Panels are welded above and below the main honeycomb core, the first reinforcement plate 700 and the second reinforcement plate 800, respectively, to obtain the aluminum honeycomb panel.

[0021] Specifically, the first reinforcing plate 700 and the second reinforcing plate 800 are both reinforced aluminum honeycomb plates, and the honeycomb core arrangement of the reinforced aluminum honeycomb plates is the same as the main honeycomb core arrangement. The upper surface of the upper panel of the reinforced aluminum honeycomb plate is connected to the lower surface of the upper panel of the aluminum honeycomb plate 600 by welding, and the lower surface of the lower panel of the reinforced aluminum honeycomb plate is connected to the upper surface of the lower panel of the aluminum honeycomb plate 600 by welding.

[0022] It should be noted that by pre-embedding the first reinforcing plate 700 and the second reinforcing plate 800 at the ends of the aluminum honeycomb panel 600 , the welding strength of the aluminum honeycomb panel 600 is improved.

[0023] In the method for preparing the integrated lightweight launch vehicle tail section of this embodiment, please refer to Figures 1 to 10 In step S100, the aluminum honeycomb panel is subjected to positive and negative bidirectional pressing to obtain the first arc panel 200, which specifically includes: S101, placing the aluminum honeycomb panel in a first pressing mold for pre-pressing, first pre-pressing the first arc portion 201, then turning the aluminum honeycomb panel 180 degrees, and pre-pressing the second arc portion 202 at the end of the first arc portion 201; S102, placing the pre-pressed aluminum honeycomb panel in a second pressing mold for secondary pressing to obtain the first arc panel.

[0024] Specifically, the first pressing mold is a wooden mold, which includes a first upper mold 110 and a first lower mold 120, wherein the top of the first lower mold 120 is set to have the same shape as the first arc plate 200, and each arc radius of the first lower mold 120 is greater than each arc radius of the first arc plate 200, and the bottom of the first upper mold 110 is set to have the same shape as the first arc portion 201, and the arc radius of the first upper mold 110 is greater than the radius of the first arc portion 201. First, the first arc portion 201 is pre-pressed with the first upper mold 110 and the first lower mold 120, and then the aluminum honeycomb panel is turned 180°, and then the end of the aluminum honeycomb panel is reversely pre-pressed to the second arc portion 202.

[0025] Specifically, the second pressing mold is a steel mold, which includes a second upper mold 130 and a second lower mold 140, wherein the bottom of the second upper mold 130 and the top of the second lower mold 140 are both configured to have the same shape and size as the first arc plate 200. The aluminum honeycomb panel after pre-pressing is placed in the second pressing mold, and the pressing process can be completed in one step without repeated steps.

[0026] That is to say, since the first arc plate 200 is composed of a large diameter arc in the middle and small arcs in opposite directions at both ends, it is easy to cause the aluminum honeycomb panel to collapse during the pressing process, and the forming is difficult, so two sets of molds are selected to press the plate multiple times. The second arc plate 300 is a standard arc with a simple structure, and can be pressed into place once using a pressing mold.

[0027] In the method for preparing the integrated lightweight launch vehicle tail section of this embodiment, please refer to Figures 1 to 10 , the thickness of the first arc plate 200 is , the radius of the first arc portion 201 is , the radius of the second arc portion 202 is ,but , and Should meet: ,and .

[0028] It should be noted that the aluminum honeycomb panel with a thickness of T is formed by step-by-step pressing to a radius of , The two positive and negative arcs are formed in one piece, replacing the original welded structure; When the aluminum honeycomb panel is under pressure, the integrity of the honeycomb core will be destroyed and it cannot be formed.

[0029] In the method for preparing the integrated lightweight launch vehicle tail section of this embodiment, please refer to Figures 1 to 8 Before step S300, the method further includes welding an edge beam 500 to one of the second reinforcement ends of the second arc plate 300, and welding an edge plate 400 to the first reinforcement ends of the first arc plate 200 and the second arc plate 300, respectively.

[0030] Specifically, the welding method of the edge beam 500 is: A groove is formed inside the second reinforcing plate 800 , and the first end of the edge beam 500 is embedded in the groove and welded. The second end of the edge beam 500 is thinned in the thickness direction to form an overlapped edge 501 .

[0031] It should be noted that when welding the aluminum honeycomb panel after pressing, the workpiece needs to be fixed on the processing tooling and clamped with F clamps to ensure that it will not move during the welding process.

[0032] In the method for preparing the integrated lightweight launch vehicle tail section of this embodiment, please refer to Figures 1 to 10In step S300, the two second reinforcement ends of the first arc plate 200 are respectively welded to the second reinforcement ends of the unwelded edge beams of the second arc plate 300 to obtain a semicircular wall panel 100. It should be noted that the first arc plate 200 and the second arc plate 300 are connected at the second reinforcement ends by welding to improve the connection stability.

[0033] Specifically, the second arc plate 300 is welded from a plurality of aluminum honeycomb panels 600, and a groove is provided on the second reinforcement plate 800 located at the junction of adjacent aluminum honeycomb panels 600. It should be noted that adjacent aluminum honeycomb panels 600 are connected by welding at the second reinforcement end to improve the connection stability.

[0034] In the method for preparing the integrated lightweight launch vehicle tail section of this embodiment, please refer to Figures 1 to 10 In step S400, the edge beams 500 of the two wall panels 100 are butt-jointed by overlapping and then welded to obtain a circular launch vehicle tail section.

[0035] The integrated lightweight launch vehicle tail section prepared by the present application has the following advantages: 1. Aluminum honeycomb panels have low density, high specific strength, high specific stiffness, and material specifications (panel thickness, honeycomb core form) can be flexibly designed according to demand, which can achieve high bearing performance, light weight, impact resistance, heat resistance and other functional requirements, and can achieve flexible design; 2. The welding aluminum honeycomb panel splicing technology and step-by-step molding technology are adopted, which has good process stability, facilitates the modular production of products, and is conducive to improving production efficiency and shortening production cycle; 3. The design concept of local brazing pre-embedded and local brazing reinforcement realizes precise design, which saves material cost and labor cost to a great extent; 4. On the basis of meeting the load-bearing requirements, the overall weight is greatly reduced, achieving lightweight design indicators; 5. Since the welding volume, welding deformation and stress of the product are reduced, the production efficiency is improved, the manufacturing cycle is shortened, the yield rate is guaranteed, the product scrap rate is greatly reduced, and it is beneficial to control costs.

[0036] The present invention has been described in detail above. The above description is only a preferred embodiment of the present invention and should not limit the scope of implementation of the present invention. That is, all equivalent changes and modifications made within the scope of this application should still fall within the scope of the present invention.

Claims

1. A method for preparing an integrated lightweight launch vehicle tail section, characterized in that: The following steps are involved: S100, performing positive and negative bidirectional pressing on the aluminum honeycomb panel to obtain a first arc panel, wherein the first arc panel adopts a three-segment arc structure, wherein the arc located in the middle is used as the first arc portion, and the arcs located at both ends are used as the second arc portions, and the first arc portion is tangent to the second arc portion and faces in opposite directions; S200, performing unidirectional pressing on the aluminum honeycomb panel to obtain a second arc panel; S300, welding the second arc plates at both ends of the first arc plate to obtain a semicircular wall plate, wherein the center of the second arc portion coincides with the center of the second arc plate; S400, repeating steps S100 to S300, first butting the two wall panels and then welding them to obtain a ring-shaped launch vehicle tail section.

2. The method for preparing an integrated lightweight launch vehicle tail section according to claim 1, characterized in that: The manufacturing method of the aluminum honeycomb panel is as follows: Along the length direction of the main honeycomb core, a first reinforcement plate is welded at the end of the main honeycomb core to form a first reinforcement end; Along the width direction of the main honeycomb core, a second reinforcement plate is welded at the end of the main honeycomb core to form a second reinforcement end; Panels are welded above and below the main honeycomb core, the first reinforcement plate, and the second reinforcement plate, respectively, to obtain the aluminum honeycomb panel.

3. The method for preparing an integrated lightweight launch vehicle tail section according to claim 2, characterized in that: The first reinforcement plate and the second reinforcement plate are both reinforced aluminum honeycomb panels, and the honeycomb core arrangement of the reinforced aluminum honeycomb panels is the same as the main honeycomb core arrangement.

4. The method for preparing an integrated lightweight launch vehicle tail section according to claim 1, characterized in that: In step S100, the aluminum honeycomb panel is subjected to positive and negative bidirectional profiling to obtain a first curved panel, which specifically includes: S101, placing the aluminum honeycomb panel in a first pressing mold for pre-pressing, first pre-pressing the first arc portion, then turning the aluminum honeycomb panel 180 degrees, and pre-pressing the second arc portion at the end of the first arc portion; S102, placing the pre-pressed aluminum honeycomb panel in a second pressing mold for secondary pressing to obtain the first arc panel.

5. The method for preparing an integrated lightweight launch vehicle tail section according to claim 4, characterized in that: The first pressing mold is a wooden mold, and the second pressing mold is a steel mold.

6. The method for preparing an integrated lightweight launch vehicle tail section according to claim 1, characterized in that: The thickness of the first arc plate is , the radius of the first arc portion is , the radius of the second arc portion is ,but , and Should meet: ,and .

7. The method for preparing an integrated lightweight launch vehicle tail section according to claim 2 or 3, characterized in that: Before step S300, the method further includes welding an edge beam to one of the second reinforcement ends of the second arc plate, and welding an edge plate to the first reinforcement ends of the first arc plate and the second arc plate, respectively.

8. The method for preparing an integrated lightweight launch vehicle tail section according to claim 7, characterized in that: The welding method of the edge beam is as follows: A groove is formed inside the second reinforcing plate, the first end of the edge beam is embedded in the groove and welded, and the second end of the edge beam is thinned in the thickness direction to form an overlapping edge.

9. The method for preparing an integrated lightweight launch vehicle tail section according to claim 8, characterized in that: In step S300, the two second reinforcement ends of the first arc plate are respectively welded to the second reinforcement ends of the unwelded edge beams of the second arc plate to obtain a semicircular wall panel.

10. The method for preparing an integrated lightweight launch vehicle tail section according to claim 9, characterized in that: In step S400, the edge beams of the two wall panels are butt-jointed in an overlapping manner and then welded to obtain a ring-shaped launch vehicle tail section.

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