Launch vehicle aft structure and launch vehicle

Abstract

The application provides a carrier rocket tail section structure and a carrier rocket, and the carrier rocket tail section structure comprises: an upper support frame, a middle frame and a lower support frame, the upper support frame, the middle frame and the lower support frame are used for bearing radial loads and are arranged at intervals along the axial direction of the carrier rocket tail section structure; longitudinal support members, two ends of at least one longitudinal support member in the plurality of longitudinal support members are connected with the upper support frame and the middle frame respectively, and two ends of at least one longitudinal support member are connected with the middle frame and the lower support frame respectively; a skin is arranged on the longitudinal support members, and the skin covers the upper support frame, the middle frame, the lower support frame and the longitudinal support members; and a connecting support is arranged on the longitudinal support members and located outside the accommodating cavity, and the connecting support is used for being connected with a landing support mechanism of the carrier rocket. Through the arrangement of the connecting support, the quick installation, convenient disassembly and maintenance of the landing support mechanism on the tail section are realized, and the installation efficiency and the maintenance efficiency of the carrier rocket are improved.

Description

Technical Field

[0001] This invention relates to the field of launch vehicle technology, and more specifically, to a launch vehicle tail section structure and a launch vehicle. Background Technology

[0002] Currently, with the rapid development of aerospace technology, global space exploration has entered a new stage characterized by large-scale internet constellations, space resource development and utilization, manned lunar exploration, and large-scale deep space exploration, leading to a rapid increase in human demand for space access. Using expendable launch vehicles for launch missions would pose a significant challenge to launch costs and launch vehicle production capacity. Reusability is a necessary choice to reduce launch costs and meet production capacity demands, representing a key development direction for launch vehicles and the foundation for future large-scale, low-cost access to space. Furthermore, the development of reusable launch vehicle technology can effectively support human missions involving landing, takeoff, and return to Earth.

[0003] Reusable launch vehicles are spacecraft that can travel between Earth and space multiple times, perform specific missions as needed, and return to Earth. Based on takeoff and landing methods, they can be categorized into vertical takeoff and landing (VTOL), vertical takeoff and horizontal landing (VTOL), and horizontal takeoff and landing (VTOL). VTOL typically employs a traditional launch vehicle configuration, adding landing support mechanisms, aerodynamic deceleration and control mechanisms, and related control system equipment for recovery. During the return process, aerodynamics and the main engine's reverse thrust are used for deceleration, and finally, the landing support mechanism provides cushioning for a vertical landing. This method inherits the configuration design of traditional launch vehicles, resulting in high overall rocket structural efficiency, lower requirements for landing sites, and a wide range of applications, making it particularly suitable for future landings and takeoffs from extraterrestrial bodies.

[0004] As a major section of reusable launch vehicles, the tail section is generally located at the rear of the launch vehicle and is used to connect the engine frame and propellant tanks. It not only needs to provide a good temperature and mechanical environment for the instruments and equipment inside the cabin, but it is also the main load-bearing location for the concentrated forces transmitted by the landing support mechanism. Currently, the tail section of launch vehicles is usually fixedly connected to the landing support mechanism by welding or other methods, without a separate structure that works in conjunction with the landing support mechanism. This makes the installation, disassembly, and maintenance of the landing support mechanism on the tail section inconvenient, thereby reducing the installation and maintenance efficiency of the launch vehicle. Summary of the Invention

[0005] This invention provides a tail section structure for a launch vehicle and a launch vehicle in order to solve the problem that the tail section of a launch vehicle in the prior art does not have a separate structure to cooperate with the landing support mechanism, which makes the installation, disassembly and maintenance of the landing support mechanism on the tail section inconvenient, thereby reducing the installation and maintenance efficiency of the launch vehicle.

[0006] To address the aforementioned problems, according to one aspect of the present invention, a launch vehicle tail section structure is provided, comprising: an upper support frame, a middle frame, and a lower support frame, wherein the upper support frame, middle frame, and lower support frame are used to bear radial loads and are arranged sequentially at intervals along the axial direction of the launch vehicle tail section structure; a plurality of longitudinal support members, wherein at least one of the longitudinal support members has its two ends connected to the upper support frame and the middle frame respectively, and at least one of the longitudinal support members has its two ends connected to the middle frame and the lower support frame respectively, and the plurality of longitudinal support members jointly bear axial loads; a skin disposed on the longitudinal support members, the skin covering the upper support frame, the middle frame, the lower support frame, and the longitudinal support members to form a receiving cavity; and a connecting support disposed on the longitudinal support members and located outside the receiving cavity; the connecting support is used to connect with the launch vehicle landing support mechanism.

[0007] Furthermore, there are at least two intermediate frames, including an upper middle frame and a lower middle frame, which are spaced apart along the axial direction of the tail section structure of the launch vehicle; wherein, the upper middle frame is connected and fixed to the upper support frame by longitudinal support members, and the lower middle frame is connected and fixed to the lower support frame by longitudinal support members.

[0008] Furthermore, the upper and middle frame has an "Ω" shaped cross-section and is composed of two half-frames. The half-frames are formed by rolling aluminum alloy plates, and the tensile strength of the aluminum alloy plates is not less than 420MPa.

[0009] Furthermore, the lower frame has a "C" shaped cross-section and is composed of four quarter frames. Each quarter frame is made of aluminum alloy sheet by rolling. The tensile strength of the aluminum alloy sheet is not less than 420MPa, and the thickness of the aluminum alloy sheet is 2-3mm.

[0010] Furthermore, at least one of the longitudinal support members is a support beam, which is connected to the upper support frame, the middle frame and the lower support frame in sequence; the connecting support is set on the support beam; the longitudinal support members include a plurality of support trusses, some of which have their ends connected to the upper support frame and the middle frame respectively, and some of which have their ends connected to the middle frame and the lower support frame respectively.

[0011] Furthermore, every three support beams form a main support section. The middle support beam is the main beam, and the two support beams on either side of the main beam are the first and second auxiliary beams. The centroids of the main beam, the first auxiliary beam, and the second auxiliary beam are coplanar, forming the first positioning surface. The intersection of the central axis of the launch vehicle tail section structure and the first positioning surface is taken as the center of a circle. The line connecting the centroid of the first auxiliary beam and the center of the circle is the first diameter, the line connecting the centroid of the main beam and the center of the circle is the main diameter, and the line connecting the centroid of the second auxiliary beam and the center of the circle is the second diameter. The angle between the first diameter and the main diameter and the angle between the second diameter and the main diameter are the same, with a degree range of 5-7 degrees.

[0012] Furthermore, every three support beams form a main support section, wherein the middle support beam is the main beam, and the two support beams located on both sides of the main beam are the first and second secondary beams, and the connecting supports are fixed to the main beam by key connection; there are multiple connecting supports, which are spaced apart along the circumference of the skin, and there are multiple main support sections, with multiple connecting supports corresponding to multiple main support sections one by one.

[0013] Furthermore, the projection of the centroid of the supporting stringer onto the first positioning surface is the projection point, the line connecting the projection point and the center of the circle is the projection line, and the angle between the first or second diameter and the adjacent projection line is 8-10 degrees.

[0014] Furthermore, there are multiple support trusses. Multiple support trusses connected to the upper support frame and the middle frame at both ends form one group, and multiple support trusses connected to the middle frame and the lower support frame at both ends form another group. Among them, the centroids of multiple support trusses in the same group are coplanar, forming a second positioning surface. With the intersection of the central axis of the tail section structure of the launch vehicle and the second positioning surface as the center, the lines connecting the centroids of two adjacent support trusses to the center are the first side and the second side, respectively, and the included angle between the first side and the second side is 9-11 degrees.

[0015] Furthermore, the longitudinal support is made of aluminum alloy forgings with a tensile strength of not less than 600 MPa.

[0016] Furthermore, the tail section structure of the launch vehicle also includes a hatch, with openings on the skin for connecting to the receiving cavity. The hatch is located at the hatch and is used to open and close the hatch.

[0017] Furthermore, there are multiple hatches, which are spaced apart on the skin, and multiple doors, which correspond one-to-one with the multiple hatches.

[0018] Furthermore, both the upper and lower support frames are made of extruded aluminum alloy profiles that are bent, and the tensile strength of the aluminum alloy is not less than 600 MPa.

[0019] Furthermore, the skin is formed by overlapping aluminum alloy plates with a thickness of 1.2-1.5mm; the connecting support is forged from TC4 titanium alloy material.

[0020] Furthermore, the connecting support includes: a support plate that abuts against the skin; a connecting key that is disposed on the side of the support plate facing the skin and passes through the skin; the connecting key cooperating with a longitudinal support member to fix the connecting support; and a connecting part disposed on the side of the support plate away from the skin, the connecting part being used to connect with the landing support mechanism of the launch vehicle.

[0021] According to another aspect of the present invention, a launch vehicle is provided, including the aforementioned launch vehicle tail section structure.

[0022] Applying the technical solution of this invention, this invention provides a tail section structure for a launch vehicle, comprising: an upper support frame, a middle frame, and a lower support frame, wherein the upper support frame, middle frame, and lower support frame are used to bear radial loads and are arranged sequentially at intervals along the axial direction of the tail section structure of the launch vehicle; a plurality of longitudinal support members, wherein at least one of the longitudinal support members has its two ends connected to the upper support frame and the middle frame respectively, and at least one of the longitudinal support members has its two ends connected to the middle frame and the lower support frame respectively, and the plurality of longitudinal support members jointly bear axial loads; a skin, disposed on the longitudinal support members, the skin covering the upper support frame, the middle frame, the lower support frame, and the longitudinal support members to form a receiving cavity; and a connecting support, disposed on the longitudinal support members and located outside the receiving cavity; the connecting support is used to connect with the landing support mechanism of the launch vehicle. This invention connects the launch vehicle's tail section to the landing support mechanism via a connecting support, creating a separate structure that works in conjunction with the landing support mechanism. This enables rapid installation, convenient disassembly, and maintenance of the landing support mechanism on the tail section, thereby improving the launch vehicle's installation and maintenance efficiency. The proposed launch vehicle tail section structure occupies little space, has high structural strength, and low section mass. By placing longitudinal support members within the accommodating cavity, the proposed launch vehicle tail section structure exhibits excellent aerodynamic shape and strong applicability. This invention can also provide tail section structural support for reusable launch vehicles. Attached Figure Description

[0023] The accompanying drawings, which form part of this application, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings:

[0024] Figure 1 A schematic diagram of the specific structure of the tail section of a launch vehicle provided in an embodiment of the present invention is shown;

[0025] Figure 2 This diagram illustrates the specific structure of the upper support frame, middle frame, and lower support frame provided in an embodiment of the present invention.

[0026] Figure 3 A schematic diagram of the specific structure of the support beam provided in an embodiment of the present invention is shown;

[0027] Figure 4 A schematic diagram of the specific structure of the skin provided in an embodiment of the present invention is shown;

[0028] Figure 5 A front structural schematic diagram of the hatch provided in an embodiment of the present invention is shown;

[0029] Figure 6A schematic diagram of the rear structure of the hatch provided in an embodiment of the present invention is shown;

[0030] Figure 7 A three-dimensional structural schematic diagram of the connecting support provided in an embodiment of the present invention is shown;

[0031] Figure 8 It shows Figure 7 A schematic diagram of the central connecting support from another angle.

[0032] The above figures include the following reference numerals:

[0033] 10. Upper support frame;

[0034] 20. Middle frame; 21. Top-middle frame; 22. Bottom-middle frame;

[0035] 30. Lower support frame;

[0036] 40. Longitudinal support member; 41. Support beam; 42. Support truss; 43. Main support section; 431. Main beam; 432. First secondary beam; 433. Second secondary beam;

[0037] 50. Skin; 51. Reception cavity; 52. Hatch;

[0038] 60. Connecting support; 61. Support plate; 62. Connecting key; 63. Connecting part;

[0039] 70. Cabin door. Detailed Implementation

[0040] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. The following description of at least one exemplary embodiment is merely illustrative and is in no way intended to limit the present invention or its application or use. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0041] like Figures 1 to 8 As shown, an embodiment of the present invention provides a tail section structure for a launch vehicle, including: an upper support frame 10, a middle frame 20, a lower support frame 30, a longitudinal support member 40, a skin 50, and a connecting support 60.

[0042] The upper support frame 10, the middle frame 20 and the lower support frame 30 are used to bear radial loads and are arranged sequentially at intervals along the axial direction of the tail section structure of the launch vehicle.

[0043] There are multiple longitudinal support members 40. At least one of the longitudinal support members 40 is connected at both ends to the upper support frame 10 and the middle frame 20, respectively. At least one of the longitudinal support members 40 is connected at both ends to the middle frame 20 and the lower support frame 30, respectively. The multiple longitudinal support members 40 jointly bear the axial load.

[0044] The skin 50 is disposed on the longitudinal support member 40, and the skin 50 covers the upper support frame 10, the middle frame 20, the lower support frame 30 and the longitudinal support member 40 to form a receiving cavity 51.

[0045] The connecting support 60 is mounted on the longitudinal support 40 and located outside the receiving cavity 51; the connecting support 60 is used to connect with the landing support mechanism of the launch vehicle.

[0046] This invention connects the connecting support 60 to the landing support mechanism of the launch vehicle, giving the launch vehicle's tail section a structure that works independently with the landing support mechanism. This enables rapid installation, convenient disassembly, and maintenance of the landing support mechanism on the tail section, thereby improving the installation and maintenance efficiency of the launch vehicle. The launch vehicle tail section structure proposed in this invention occupies little space, has high structural strength, and low section mass. By setting the longitudinal support member 40 within the receiving cavity 51, the proposed launch vehicle tail section structure has a good aerodynamic shape and strong applicability. This invention can also provide tail section structural support for reusable launch vehicles.

[0047] In one specific embodiment of the present invention, such as Figure 1 As shown, the upper support frame 10 and the lower support frame 30 each have docking interfaces for connecting with other sections of the launch vehicle. There are multiple docking interfaces, spaced apart on the upper support frame 10 and the lower support frame 30. By providing multiple docking interfaces, the subsequent docking and installation of the launch vehicle's tail section structure on the launch vehicle is facilitated. In another specific embodiment of the invention, the multiple docking interfaces include docking bolt holes and docking guide pin holes. Both the upper support frame 10 and the lower support frame 30 have 36 Φ13mm docking bolt holes and 4 Φ14.5mm docking guide pin holes.

[0048] In one specific embodiment of the present invention, the skin 50 is fixed to the upper support frame 10, the middle frame 20, the lower support frame 30 and the longitudinal support member 40 by riveting to ensure that the fixing strength of the skin 50 meets the actual aerospace requirements.

[0049] like Figure 2As shown, there are at least two intermediate frames 20, including an upper middle frame 21 and a lower middle frame 22, which are spaced apart along the axial direction of the launch vehicle's tail section structure. The upper middle frame 21 is connected and fixed to the upper support frame 10 via a longitudinal support member 40, and the lower middle frame 22 is connected and fixed to the lower support frame 30 via the same longitudinal support member 40. By providing the upper middle frame 21 and the lower middle frame 22, the radial strength and stiffness of the launch vehicle's tail section structure are further increased.

[0050] Specifically, such as Figure 2 As shown, the upper middle frame 21 has an "Ω" shaped cross-section and is composed of two half-frames. Each half-frame is formed by rolling aluminum alloy plates, and the tensile strength of the aluminum alloy plates is not less than 420MPa. This design facilitates the processing of the upper middle frame 21, thereby reducing costs, while ensuring that the strength of the upper middle frame 21 meets the actual usage requirements.

[0051] It should be noted that, in one specific embodiment of the present invention, the two half-frames are connected by a joint pad to ensure the connection strength of the two half-frames.

[0052] Specifically, such as Figure 2 As shown, the lower middle frame 22 has a "C" shaped cross-section and is composed of four quarter frames. Each quarter frame is made of aluminum alloy sheet by rolling. The tensile strength of the aluminum alloy sheet is not less than 420MPa, and the thickness of the aluminum alloy sheet is 2-3mm. This design facilitates the processing of the lower middle frame 22, thereby reducing costs, while ensuring that the strength of the lower middle frame 22 meets the actual use requirements.

[0053] like Figure 1 and Figure 3 As shown, at least one of the multiple longitudinal support members 40 is a support beam 41, which is sequentially connected to the upper support frame 10, the intermediate frame 20, and the lower support frame 30. A connecting support 60 is disposed on the support beam 41. The multiple longitudinal support members 40 include multiple support stringers 42, with some stringers 42 having their ends connected to the upper support frame 10 and the intermediate frame 20, and others having their ends connected to the intermediate frame 20 and the lower support frame 30, respectively. By providing the support beam 41, the axial load on the tail section structure of the launch vehicle can be effectively supported. By providing the support stringers 42, the axial strength and stiffness of the tail section structure of the launch vehicle are further improved, and the overall installation of the tail section structure of the launch vehicle is also facilitated.

[0054] In one specific embodiment of the present invention, such as Figure 1 As shown, the two ends of multiple support trusses 42 are respectively connected to the upper middle frame 21 and the lower middle frame 22. The multiple support trusses 42 are spaced apart to effectively connect and support the upper middle frame 21 and the lower middle frame 22.

[0055] It should be noted that the lengths of the supporting stringers 42 and the supporting beams 41 in this invention can be flexibly adjusted according to the size and length of the tail section, and their quantity and assembly angle can be varied; the quantity and position of the intermediate frames 20 can be varied, but at least one intermediate frame 20 must be provided to support the connecting support 60.

[0056] like Figure 1 As shown, every three support beams 41 form a main support section 43. The middle support beam 41 is the main beam 431, and the two support beams 41 located on either side of the main beam 431 are the first secondary beam 432 and the second secondary beam 433. The centroids of the main beam 431, the first secondary beam 432, and the second secondary beam 433 are coplanar, forming a first positioning surface. The intersection of the central axis of the launch vehicle tail section structure and the first positioning surface is taken as the center of a circle. The line connecting the centroid of the first secondary beam 432 and the center of the circle is the first diameter, the line connecting the centroid of the main beam 431 and the center of the circle is the main diameter, and the line connecting the centroid of the second secondary beam 433 and the center of the circle is the second diameter. The angle between the first diameter and the main diameter and the angle between the second diameter and the main diameter are the same, with a degree range of 5-7 degrees. By setting the main support part 43, the number of support beams 41 is minimized while ensuring effective bearing of the axial load on the tail section structure of the launch vehicle, thus facilitating the simplification and weight reduction of the overall tail section structure. By setting the angle between the first diameter and the main diameter to be the same as the angle between the second diameter and the main diameter, the auxiliary support effect of the first auxiliary beam 432 and the second auxiliary beam 433 is effectively guaranteed.

[0057] It should be noted that: such as Figure 1 As shown, the installation orientation of the first auxiliary beam 432 and the second auxiliary beam 433 as a whole points towards the intersection of the central axis of the tail section structure of the launch vehicle and the first positioning surface, that is, towards the center of the circle. This setting ensures the uniformity of the overall center of gravity distribution of the main support part 43.

[0058] like Figure 1 As shown, every three support beams 41 form a main support section 43. The middle support beam 41 is the main beam 431, and the two support beams 41 located on either side of the main beam 431 are the first secondary beam 432 and the second secondary beam 433. Connecting supports 60 are fixed to the main beam 431 in the main support section 43 via keys. Multiple connecting supports 60 are spaced apart circumferentially along the skin 50. Multiple main support sections 43 are also present, with each connecting support 60 corresponding to one of the main support sections 43. By using multiple connecting supports 60, flexible adaptation to multiple landing support mechanisms on the launch vehicle is achieved. By ensuring a one-to-one correspondence between multiple connecting supports 60 and multiple main support sections 43, effective support is provided for each connecting support 60, thereby increasing the cooperative working effect between the launch vehicle's tail section structure and multiple landing support mechanisms, and providing structural assurance for the subsequent reuse of the launch vehicle.

[0059] Specifically, the projection of the centroid of the support stringer 42 onto the first positioning surface is the projection point, and the line connecting the projection point and the center of the circle is the projection line. The angle between the first diameter or the second diameter and the adjacent projection line is 8-10 degrees. By setting the angle between the first diameter or the second diameter and the adjacent projection line, the position of the main support part 43 relative to the support stringer 42 is effectively defined while satisfying the support effect. This makes the distribution of the main support part 43 and the support stringer 42 more reasonable, and makes the overall weight distribution of the launch vehicle tail section structure more reasonable and uniform (e.g., the center of gravity is located on the central axis).

[0060] In one specific embodiment of the present invention, the angle between the first diameter or the second diameter and the adjacent projection line is preferably 9 degrees.

[0061] like Figure 1 As shown, there are multiple support stringers 42. One group consists of multiple support stringers 42 connected at both ends to the upper support frame 10 and the middle frame 20 respectively, while another group consists of multiple support stringers 42 connected at both ends to the middle frame 20 and the lower support frame 30 respectively. Within the same group, the centroids of the multiple support stringers 42 are coplanar, forming a second positioning surface. Centered on the intersection of the central axis of the launch vehicle's tail section structure and the second positioning surface, the lines connecting the centroids of two adjacent support stringers 42 to the center form the first and second sides, respectively, with an angle of 9-11 degrees between the first and second sides. This arrangement, while ensuring the support effect meets actual usage requirements, minimizes the number of support stringers 42, simplifying and lightweighting the overall launch vehicle tail section structure, and also makes the overall weight distribution of the launch vehicle tail section structure more rational.

[0062] In one specific embodiment of the present invention, the included angle between the first side and the second side is preferably 10 degrees.

[0063] In another specific embodiment of the present invention, such as Figure 1 As shown, multiple support trusses 42 that connect the upper frame 21 and the lower frame 22 at both ends are also a group. The installation positions of the three different groups of support trusses 42 are arranged collinearly to ensure the support effect of the support trusses 42.

[0064] Specifically, the longitudinal support 40 is an aluminum alloy forging with a tensile strength of not less than 600 MPa. By specifying the material of the longitudinal support 40, it is easier to process and form the longitudinal support 40, and the cost of the longitudinal support 40 is reduced.

[0065] like Figure 4 , Figure 5 and Figure 6As shown, the tail section structure of the launch vehicle also includes a hatch 70. A hatch 52 for connecting to the receiving cavity 51 is provided on the skin 50. The hatch 70 is located at the hatch 52 and is used to open and close the hatch 52. By providing the hatch 70, personnel or other instruments can directly enter the receiving cavity 51 from the tail section structure of the launch vehicle, facilitating subsequent instrument inspection and equipment installation.

[0066] Specifically, there are multiple hatches 52, spaced apart on the skin 50, and multiple hatches 70, each corresponding to one of the hatches 52. Different designs for the different hatches 52 are used to achieve different functions, providing structural support for the subsequent division of hatch functions.

[0067] In one specific embodiment of the present invention, there are three hatches 70, two of which have a specific size of 490mm×450mm (the size of hatch 52 is also adapted accordingly), and the above two hatches are passage hatches for personnel to enter and exit; the other hatch 70 has a specific size of 496mm×312mm (the size of hatch 52 is also adapted accordingly), and this hatch is used for the installation and inspection of related instruments.

[0068] It should be noted that, during assembly, the tail section structure of the launch vehicle provided by the present invention is based on the upper support frame 10 and the lower support frame 30. The support beam 41, the support stringer 42 and the intermediate frame 20 are installed in sequence, and then the skin 50 is installed. The upper support frame 10, the intermediate frame 20, the lower support frame 30 and the longitudinal support member 40 are fixed into one piece by screws and rivets. Finally, the hatch 70 is installed on the hatch 52 by screws, and the connecting support 60 is fixed to the main beam 431 by screws.

[0069] Specifically, both the upper support frame 10 and the lower support frame 30 are formed by bending extruded profiles of aluminum alloy, and the tensile strength of the aluminum alloy is not less than 600MPa. By setting the materials and processing technology of the upper support frame 10 and the lower support frame 30, it is not only convenient to process and form the upper support frame 10 and the lower support frame 30, but also to reduce the cost of the upper support frame 10 and the lower support frame 30.

[0070] In a specific embodiment of the present invention, the frame spacing between the upper support frame 10, the upper middle frame 21, the lower middle frame 22, and the lower support frame 30 is arranged as follows: starting from the lower support frame 30, the frame spacing from bottom to top is 640-460-460mm. This arrangement serves two purposes: first, to meet the assembly coordination requirements of the telescopic rod in the landing support mechanism, i.e., the distance between the lower middle frame 22, which is used to support the connecting support 60, and the lower support frame 30 is 640mm; second, to ensure the consistency of the frame spacing as much as possible, thereby saving on process preparation, the final frame spacing between the upper middle frame 21 and the lower middle frame 22, and between the upper support frame 10 and the upper middle frame 21, is determined to be 460mm.

[0071] like Figure 4 As shown, the skin 50 is formed by overlapping aluminum alloy plates with a thickness of 1.2-1.5mm; the connecting support 60 is forged from TC4 titanium alloy. By setting the material and processing technology of the connecting support 60, the connecting support 60 meets the actual use requirements while reducing its cost.

[0072] like Figure 7 and Figure 8 As shown, the connecting support 60 includes: a support plate 61 that abuts against the skin 50; a connecting key 62 disposed on the side of the support plate 61 facing the skin 50 and passing through the skin 50; the connecting key 62 cooperates with the longitudinal support member 40 to fix the connecting support 60; and a connecting part 63 disposed on the side of the support plate 61 facing away from the skin 50, which is used to connect with the landing support mechanism of the launch vehicle. By designing the structure of the connecting support 60, the overall structure of the connecting support 60 is simplified, facilitating subsequent processing and installation.

[0073] In a specific embodiment of the present invention, the key connection between the connecting support 60 and the main beam 431 in the connecting part 63 is as follows: the connecting key 62 passes through the skin 50 (at this time, a hole for the connecting key 62 needs to be pre-drilled on the skin 50), and is connected to the keyway (e.g., on the main beam 431) formed by the keyway. Figure 3 As shown, the key 62 is fitted to the support beam 41 through a keyway in the middle, and then fixed to the support beam 41 by riveting or welding, thus achieving a fixed fit between the connecting support 60 and the main beam 431.

[0074] It should be noted that; in one specific embodiment of the present invention, such as Figure 8 As shown, the connecting part 63 is a hinged connection; that is, the connecting support 60 is a common hinged support structure. The hinged support is hinged to the telescopic rod in the landing support mechanism to buffer the impact force during landing. There are 4 connecting supports 60, which are evenly distributed around the skin 50 to ensure the uniformity of load distribution.

[0075] The present invention also provides a launch vehicle including the aforementioned launch vehicle tail section structure. This launch vehicle is reusable, thus providing a solution for reducing launch costs and meeting production capacity demands, and offering a structural basis for large-scale, low-cost access to space in the future.

[0076] In summary, this invention provides a tail section structure for a launch vehicle and a launch vehicle in general. By providing a connecting support 60 that connects to the landing support mechanism of the launch vehicle, the tail section structure of the launch vehicle has a structure that can independently cooperate with the landing support mechanism. This enables the rapid installation, convenient disassembly, and maintenance of the landing support mechanism on the tail section, thereby improving the installation and maintenance efficiency of the launch vehicle. The tail section structure of the launch vehicle proposed in this invention occupies little space, has high structural strength, and low section mass. By setting the longitudinal support member 40 within the receiving cavity 51, the tail section structure of the launch vehicle proposed in this invention has a good aerodynamic shape and strong applicability. This invention can also provide tail section structural support for reusable launch vehicles.

[0077] It should be noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the exemplary embodiments according to this application. As used herein, the singular form is intended to include the plural form as well, unless the context clearly indicates otherwise. Furthermore, it should be understood that when the terms "comprising" and / or "including" are used in this specification, they indicate the presence of features, steps, operations, devices, components, and / or combinations thereof.

[0078] Unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps set forth in these embodiments do not limit the scope of the invention. It should also be understood that, for ease of description, the dimensions of the various parts shown in the drawings are not drawn to actual scale. Techniques, methods, and devices known to those skilled in the art may not be discussed in detail, but where appropriate, such techniques, methods, and devices should be considered part of the specification. In all examples shown and discussed herein, any specific values ​​should be interpreted as merely exemplary and not as limitations. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters in the following figures denote similar items; therefore, once an item is defined in one figure, it need not be further discussed in subsequent figures.

[0079] In the description of this invention, it should be understood that the orientation or positional relationship indicated by directional terms such as "front, back, up, down, left, right", "horizontal, vertical, horizontal" and "top, bottom" is generally based on the orientation or positional relationship shown in the accompanying drawings, and is only for the convenience of describing this invention and simplifying the description. Unless otherwise stated, these directional terms do not indicate or imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation on the scope of protection of this invention; the directional terms "inner" and "outer" refer to the inner and outer contours relative to the outline of each component itself.

[0080] For ease of description, spatial relative terms such as "above," "over," "on the surface above," "above," etc., are used herein to describe the spatial positional relationship of a device or feature as shown in the figures to other devices or features. It should be understood that spatial relative terms are intended to encompass different orientations in use or operation beyond the orientation of the device as described in the figures. For example, if the device in the figures were inverted, a device described as "above" or "above" other devices or structures would subsequently be positioned as "below" or "under" other devices or structures. Thus, the exemplary term "above" can include both "above" and "below." The device may also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatial relative descriptions used herein will be interpreted accordingly.

[0081] Furthermore, it should be noted that the use of terms such as "first" and "second" to define components is merely for the purpose of distinguishing the corresponding components. Unless otherwise stated, the above terms have no special meaning and therefore should not be construed as limiting the scope of protection of this invention.

[0082] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A tail section structure for a launch vehicle, characterized in that, include: The upper support frame (10), the middle frame (20) and the lower support frame (30) are used to bear radial loads and are arranged sequentially at intervals along the axial direction of the tail section structure of the launch vehicle. Longitudinal support member (40), there are multiple longitudinal support members (40), at least one of the longitudinal support members (40) is connected at both ends to the upper support frame (10) and the middle frame (20) respectively, at least one of the longitudinal support members (40) is connected at both ends to the middle frame (20) and the lower support frame (30) respectively, and the multiple longitudinal support members (40) jointly bear the axial load; A skin (50) is disposed on the longitudinal support (40), and the skin (50) covers the upper support frame (10), the middle frame (20), the lower support frame (30) and the longitudinal support (40) to form a receiving cavity (51). A connecting support (60) is disposed on the longitudinal support (40) and located outside the receiving cavity (51); the connecting support (60) is used to connect with the landing support mechanism of the launch vehicle; The intermediate frame (20) consists of at least two parts, including an upper middle frame (21) and a lower middle frame (22). The upper middle frame (21) and the lower middle frame (22) are spaced apart along the axial direction of the tail section structure of the launch vehicle. The upper middle frame (21) is connected and fixed to the upper support frame (10) through the longitudinal support member (40), and the lower middle frame (22) is connected and fixed to the lower support frame (30) through the longitudinal support member (40). The upper frame (21) has an "Ω" shaped cross section. The upper frame (21) is composed of two half-frames. The half-frames are formed by rolling aluminum alloy plates. The tensile strength of the aluminum alloy plates is not less than 420MPa. The lower frame (22) has a "C" shaped cross section. The lower frame (22) is composed of four quarter frames. The quarter frames are formed by rolling aluminum alloy plates. The tensile strength of the aluminum alloy plates is not less than 420MPa. The thickness of the aluminum alloy plates is 2-3mm. At least one of the longitudinal support members (40) is a support beam (41), which is connected in sequence to the upper support frame (10), the middle frame (20) and the lower support frame (30); the connecting support (60) is disposed on the support beam (41); the longitudinal support members (40) include a plurality of support stringers (42), the two ends of a portion of the support stringers (42) are respectively connected to the upper support frame (10) and the middle frame (20), and the two ends of a portion of the support stringers (42) are respectively connected to the middle frame (20) and the lower support frame (30); Every three of the support beams (41) form a main support section (43), wherein the support beam (41) located in the middle is the main beam (431), and the two support beams (41) located on both sides of the main beam (431) are the first secondary beam (432) and the second secondary beam (433). The centroids of the main beam (431), the first secondary beam (432), and the second secondary beam (433) are coplanar, forming a first positioning surface. The intersection of the central axis of the tail section structure of the launch vehicle and the first positioning surface is taken as the center of a circle. The line connecting the centroid of the first secondary beam (432) and the center of the circle is the first diameter. The line connecting the centroid of the main beam (431) and the center of the circle is the main diameter. The line connecting the centroid of the second secondary beam (433) and the center of the circle is the second diameter. The angle between the first diameter and the main diameter and the angle between the second diameter and the main diameter are the same, with a degree range of 5-7 degrees.

2. The launch vehicle tail section structure according to claim 1, characterized in that, Every three of the support beams (41) form a main support part (43), wherein the support beam (41) located in the middle is the main beam (431), and the two support beams (41) located on both sides of the main beam (431) are the first secondary beam (432) and the second secondary beam (433). The connecting support (60) is fixed to the main beam (431) by a key. There are multiple connecting supports (60), which are spaced apart along the circumference of the skin (50). There are multiple main support parts (43), and the multiple connecting supports (60) are arranged one-to-one with the multiple main support parts (43).

3. The launch vehicle tail section structure according to claim 1, characterized in that, The projection of the centroid of the support stringer (42) onto the first positioning surface is a projection point, and the line connecting the projection point and the center of the circle is a projection line. The angle between the first diameter or the second diameter and the adjacent projection line is 8-10 degrees.

4. The tail section structure of the launch vehicle according to claim 1, characterized in that, There are multiple support trusses (42). The multiple support trusses (42) connected to the upper support frame (10) and the middle frame (20) at both ends respectively form one group, and the multiple support trusses (42) connected to the middle frame (20) and the lower support frame (30) at both ends respectively form another group. Among them, the centroids of multiple support trusses (42) in the same group are coplanar, forming a second positioning surface. The intersection of the central axis of the tail section structure of the launch vehicle and the second positioning surface is taken as the center. The centroids of two adjacent support trusses (42) are respectively connected to the center as the first side and the second side. The included angle between the first side and the second side is 9-11 degrees.

5. The tail section structure of the launch vehicle according to claim 1, characterized in that, The longitudinal support (40) is an aluminum alloy forging with a tensile strength of not less than 600 MPa.

6. The tail section structure of the launch vehicle according to claim 1, characterized in that, The tail section structure of the launch vehicle also includes a hatch (70). The skin (50) has a hatch (52) for connecting the receiving cavity (51). The hatch (70) is located at the hatch (52) and is used to open and close the hatch (52).

7. The launch vehicle tail section structure according to claim 6, characterized in that, There are multiple hatches (52), which are spaced apart on the skin (50). There are multiple doors (70), which are arranged one-to-one with the multiple hatches (52).

8. The tail section structure of the launch vehicle according to claim 1, characterized in that, Both the upper support frame (10) and the lower support frame (30) are formed by bending extruded aluminum alloy profiles, and the tensile strength of the aluminum alloy is not less than 600MPa.

9. The tail section structure of a launch vehicle according to claim 1, characterized in that, The skin (50) is formed by overlapping aluminum alloy plates with a thickness of 1.2-1.5mm; the connecting support (60) is forged from TC4 titanium alloy material.

10. The tail section structure of a launch vehicle according to claim 1, characterized in that, The connecting support (60) includes: A support plate (61) abuts against the skin (50); A connecting key (62) is disposed on the side of the support plate (61) facing the skin (50) and passes through the skin (50); the connecting key (62) cooperates with the longitudinal support member (40) to fix the connecting support (60). A connecting part (63) is disposed on the side of the support plate (61) opposite to the skin (50), and the connecting part (63) is used to connect with the landing support mechanism of the launch vehicle.

11. A launch vehicle, characterized in that, Includes the launch vehicle tail section structure as described in any one of claims 1 to 10.

Images