Integrated light-weight carrier rocket tail section and carrier rocket

Abstract

The utility model relates to an integrated light-weight launch vehicle tail section and launch vehicle, the integrated light-weight launch vehicle tail section is formed by welding two semicircular wall plates, the wall plates comprise a first arc plate and second arc plates located on the two sides of the first arc plate, the first arc plate and the second arc plates are both aluminum honeycomb plates, and the first arc plate and the second arc plates are arranged in parallel. The first arc plate comprises a first arc part and second arc parts located on the two sides of the first arc part, the first arc part and the second arc parts are tangent and opposite in direction, and the circle center of the second arc parts coincides with the circle center of the second arc plate. According to the utility model, the technical problem that the development requirements of light weight, modularization and low cost cannot be met in the prior art can be solved.

Description

Technical Field

[0001] The utility model belongs to the technical field of carrier rockets, and in particular relates to an integrated lightweight carrier rocket tail section and a carrier rocket. 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 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, the upper, intermediate, and lower support frames being used to bear radial loads and spaced apart along the axial direction of the carrier rocket tail section structure; at least one of a plurality of longitudinal support members having its ends connected to the upper support frame and the intermediate frame, respectively, and at least one of the longitudinal support members having its ends connected to the intermediate frame and the lower support frame, respectively; and a skin disposed on the longitudinal support members, the skin covering the upper, intermediate, lower support frame, and longitudinal support members. This tail section structure is relatively heavy overall, has numerous processes and complex assembly, requires extensive welding, results in significant welding deformation and stress, and has low production efficiency, failing to meet the development needs of lightweighting, modularization, and low cost. Utility Model Content

[0004] In view of the various deficiencies of the existing technology, an integrated lightweight launch vehicle tail section and launch vehicle are proposed to solve the technical problem that the existing technology cannot meet the development requirements of lightweight, modular and low cost.

[0005] To achieve the above objectives, the present invention provides the following technical solutions:

[0006] In the first aspect, the utility model provides an integrated lightweight launch vehicle tail section, which is welded from two semicircular wall panels, wherein the wall panels include a first arc plate and a second arc plate located on both sides of the first arc plate, the first arc plate and the second arc plate are both configured as aluminum honeycomb panels, the first arc plate includes a first arc portion and a second arc portion located on both sides of the first arc portion, the first arc portion is tangent to the second arc portion and faces opposite directions, and the center of the second arc portion coincides with the center of the second arc plate.

[0007] The technical solution is further configured such 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 the following requirements: ,and .

[0008] The technical solution is further configured such that edge panels are provided at the upper and lower ends of the wall panel, and edge beams are provided at the left and right ends of the wall panel.

[0009] The technical solution is further configured such that the upper and lower ends of the aluminum honeycomb panel are both provided with first reinforcing plates, the left and right ends of the aluminum honeycomb panel are both provided with second reinforcing plates, and the first reinforcing plates are connected to the edge sealing plates by welding.

[0010] 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 reinforced aluminum honeycomb panels have the same arrangement of honeycomb cores as the aluminum honeycomb panels.

[0011] The technical solution is further configured such that a groove is provided inside the second reinforcing plate connected to the edge beam, the first end of the edge beam is embedded in the groove, and the second end of the edge beam is provided with a lap edge for lap connection with an adjacent edge beam.

[0012] The technical solution is further configured such that the second arc plate is formed by welding a plurality of aluminum honeycomb panels, and a groove is provided on the second reinforcing plate located at the junction of adjacent aluminum honeycomb panels.

[0013] The technical solution is further configured such that a mounting hole is provided on the second arc plate, and a mounting seat is provided inside the mounting hole.

[0014] In a second aspect, the utility model provides a carrier rocket comprising the above-mentioned integrated lightweight carrier rocket tail section.

[0015] The beneficial effects of the utility model are:

[0016] 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, which improves the convenience of manufacturing the tail section of the launch vehicle, meets the needs of modular production, and improves production efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 Schematic diagram of an integrated lightweight carrier rocket tail section in an embodiment of the present invention;

[0018] Figure 2 is a schematic diagram of a wall panel in an embodiment of the present utility model;

[0019] Figure 3It is a side view of the second arc plate in the embodiment of the present utility model;

[0020] Figure 4 yes Figure 3 Middle AA section view;

[0021] Figure 5 yes Figure 3 Middle BB cross-section;

[0022] Figure 6 yes Figure 3 Middle CC section view;

[0023] Figure 7 It is a top view of the first arc plate in the embodiment of the present utility model.

[0024] In the accompanying drawings: 100, wall panel; 200, first arc panel; 201, first circular arc portion; 202, second circular arc portion; 300, second arc panel; 400, edge banding panel; 500, edge banding beam; 501, overlapping edge; 600, aluminum honeycomb panel; 700, first reinforcing plate; 800, second reinforcing plate. DETAILED DESCRIPTION

[0025] In order to enable those skilled in the art to better understand the technical solution of the present invention, the following is a clear and complete description of the technical solution of the present invention in conjunction with the 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 fall within the scope of protection of this application. In addition, the directional terms mentioned in the following embodiments, such as "up", "down", "left", "right", etc., are only referenced to the directions of the drawings. Therefore, the directional terms used are used to illustrate rather than limit the invention.

[0026] The present invention will be further described below with reference to the accompanying drawings and preferred embodiments.

[0027] According to the embodiment of the present invention, an integrated lightweight carrier rocket tail section is provided. Figures 1 to 3 ,as well as Figure 7 It is welded by two semicircular wall panels 100, the wall panel 100 includes a first arc plate 200 and a second arc plate 300 located on both sides of the first arc plate 200, the first arc plate 200 and the second arc plate 300 are both set as aluminum honeycomb panels 600, the first arc plate 200 includes a first arc portion 201 and a second arc portion 202 located on both sides of the first arc portion 201, the first arc portion 201 is tangent to the second arc portion 202 and faces oppositely, and the center of the second arc portion 202 coincides with the center of the second arc plate 300.

[0028] It should be noted that the aluminum honeycomb panel 600 is used as the main material, and the characteristics of the aluminum honeycomb panel 600 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 carrier rocket, such as thermal insulation, long life, low cost and lightweight; 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 carrier rocket, meets the modular production needs, and improves production efficiency.

[0029] In the integrated lightweight carrier rocket tail section of this embodiment, please refer to Figure 1 、 Figure 2 as well as Figure 7 , 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 the following requirements: ,and .

[0030] It should be noted that the aluminum honeycomb panel with a thickness of T is formed into 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 will not be able to be formed.

[0031] In the integrated lightweight carrier rocket tail section of this embodiment, please refer to Figure 1 as well as Figure 2 The upper and lower ends of the wall panel 100 are both provided with edge sealing plates 400 , and the left and right ends of the wall panel 100 are both provided with edge sealing beams 500 .

[0032] It should be noted that the edge beams 500 on the two wall panels 100 overlap each other to assemble the two wall panels 100 into one body.

[0033] In the integrated lightweight carrier rocket tail section of this embodiment, please refer to Figures 1 to 6 The upper and lower ends of the aluminum honeycomb panel 600 are both provided with a first reinforcing plate 700, and the left and right ends of the aluminum honeycomb panel 600 are both provided with a second reinforcing plate 800. The first reinforcing plate 700 is connected to the edge sealing plate 400 by welding.

[0034] It should be noted that by pre-embedding the first reinforcement plate 700 and the second reinforcement plate 800 at the ends of the aluminum honeycomb panel 600 , the welding strength of the aluminum honeycomb panel 600 is improved.

[0035] Specifically, the first reinforcing plate 700 and the second reinforcing plate 800 are both reinforced aluminum honeycomb panels, and the honeycomb core arrangement of the reinforced aluminum honeycomb panels is the same as that of the aluminum honeycomb panel 600. The upper surface of the upper panel of the reinforced aluminum honeycomb panel is welded to the lower surface of the upper panel of the aluminum honeycomb panel 600, and the lower surface of the lower panel of the reinforced aluminum honeycomb panel is also welded to the upper surface of the lower panel of the aluminum honeycomb panel 600.

[0036] In the integrated lightweight carrier rocket tail section of this embodiment, please refer to Figures 1 to 4 A groove is provided inside the second reinforcing plate 800 connected to the edge beam 500, the first end of the edge beam 500 is embedded in the groove, and the second end of the edge beam 500 is provided with a lap edge 501 for lap connection with the adjacent edge beam.

[0037] It should be noted that the first end of the edge beam 500 is embedded in the groove and connected by welding to improve the connection stability; adjacent edge beams are overlapped by overlapping edges 501 for easy docking and are connected by welding.

[0038] In the integrated lightweight carrier rocket tail section of this embodiment, please refer to Figures 1 to 5 The second arc plate 300 is formed by welding a plurality of aluminum honeycomb panels 600 , and a groove is provided on the second reinforcing plate 800 located at the junction of adjacent aluminum honeycomb panels 600 .

[0039] It should be noted that the adjacent aluminum honeycomb panels 600 are connected by welding at the second reinforcing plate 800 to improve the connection stability.

[0040] In the integrated lightweight carrier rocket tail section of this embodiment, please refer to Figure 1 、 Figure 2 The second arc plate 300 is provided with a mounting hole, and a mounting seat is provided inside the mounting hole.

[0041] It should be noted that the mounting hole and the mounting seat are connected by welding, and the mounting seat is used to install structural parts such as panels.

[0042] A carrier rocket includes the integrated lightweight carrier rocket tail section. The integrated lightweight carrier rocket tail section has the following advantages:

[0043] 1. Aluminum honeycomb panels have low density, high specific strength and high specific stiffness, and the material specifications (panel thickness, honeycomb core form) can be flexibly designed according to demand, which can achieve functional requirements such as high load-bearing performance, light weight, impact resistance, and heat resistance, and can realize flexible design;

[0044] 2. The use of welded aluminum honeycomb panel splicing technology and step-by-step molding technology has good process stability, which facilitates the realization of modular production of products, improves production efficiency and shortens production cycle;

[0045] 3. The design concept of local brazing pre-embedded and local brazing reinforcement realizes precise design, which greatly saves material and labor costs;

[0046] 4. On the basis of meeting the load-bearing requirements, the overall weight is greatly reduced, achieving lightweight design indicators;

[0047] 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.

[0048] 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. All equivalent changes and modifications made within the scope of this application should still fall within the scope of the present invention.

Claims

1. An integrated lightweight carrier rocket tail section, characterized in that: It is welded from two semicircular wall panels, the wall panels including a first arc panel and a second arc panel located on both sides of the first arc panel, the first arc panel and the second arc panel are both configured as aluminum honeycomb panels, the first arc panel including a first arc portion and a second arc portion located on both sides of the first arc portion, the first arc portion is tangent to the second arc portion and faces in opposite directions, and the center of the second arc portion coincides with the center of the second arc panel.

2. The integrated lightweight carrier rocket 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 the following requirements: ,and .

3. The integrated lightweight carrier rocket tail section according to claim 1, characterized in that: The upper and lower ends of the wall panel are both provided with edge sealing plates, and the left and right ends of the wall panel are both provided with edge sealing beams.

4. The integrated lightweight carrier rocket tail section according to claim 3, characterized in that: The upper and lower ends of the aluminum honeycomb panel are both provided with a first reinforcing plate, the left and right ends of the aluminum honeycomb panel are both provided with a second reinforcing plate, and the first reinforcing plate is connected to the edge sealing plate by welding.

5. The integrated lightweight carrier rocket tail section according to claim 4, characterized in that: The first reinforcement plate and the second reinforcement plate are both reinforced aluminum honeycomb panels, and the arrangement of the honeycomb cores in the reinforced aluminum honeycomb panels is the same as that in the aluminum honeycomb panels.

6. The integrated lightweight carrier rocket tail section according to claim 4, characterized in that: A groove is provided inside the second reinforcing plate connected to the edge beam, the first end of the edge beam is embedded in the groove, and the second end of the edge beam is provided with an overlapping edge for overlapping with the adjacent edge beam.

7. The integrated lightweight carrier rocket tail section according to any one of claims 4 to 6, characterized in that: The second arc plate is formed by welding a plurality of aluminum honeycomb panels, and a groove is provided on the second reinforcing plate located at the junction of adjacent aluminum honeycomb panels.

8. The integrated lightweight carrier rocket tail section according to claim 1, characterized in that: A mounting hole is provided on the second arc plate, and a mounting seat is provided inside the mounting hole.

9. A carrier rocket comprising the integrated lightweight carrier rocket tail section according to any one of claims 1 to 8.

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