A detachable bundling support structure for a launch vehicle

Abstract

The present application relates to the technical field of launch vehicles, and relates to a detachable bundling support structure of a launch vehicle, a disassembly method thereof, and a launch vehicle. The detachable bundling support structure of a launch vehicle includes a booster connection part and an interface part; the booster connection part is configured to be connected to a booster; the interface part is connected to the booster connection part, and the interface part is configured to be detachably fixedly connected to a body shell segment. The disassembly and assembly method of the detachable bundling support structure of a launch vehicle includes detachably and fixedly connecting the first sub-part to the root joint of the main beam of the body shell segment; the secondary beam of the body shell segment, the middle frame of the body shell segment, the end frame of the body shell segment, and the reinforced joint of the body shell segment are respectively detachably and fixedly connected to the second sub-part of the detachable bundling support structure of the launch vehicle through fasteners. The present application meets the repeated disassembly and assembly requirements of the bundling structure to a certain extent, and improves the adaptability of various bundling structures such as transportation joints, lifting joints, and whole-rocket erection joints required under different operating conditions.

Description

Technical Field

[0001] The present application relates to the technical field of launch vehicles, and in particular, to a detachable bundling support structure for a launch vehicle and a disassembly method thereof, and a launch vehicle. Background Art

[0002] With the development of aerospace technology, in order to further improve the rocket carrying capacity, most of the current domestic and foreign launch vehicle models have adopted the solution of bundling boosters, such as the Ariane series, Atlas series, H-II and the US space shuttle, all of which use boosters to provide additional thrust. In these launch vehicle models, the core stage and the booster of the launch vehicle are mainly connected through a bundling structure. The bundling structure is located between the core stage and the booster of the launch vehicle, and it has two main functions: first, before the separation of the booster, the bundling structure bears and transmits a large booster concentrated load through the main bearing, and must meet the relative rotation and installation requirements of the booster and the core stage to ensure a reliable and firm connection; second, the bundling structure must ensure reliable unlocking according to the requirements of the control system to achieve successful separation of the booster and the core stage.

[0003] According to its use requirements, the bundling structure is actually a tension fastener; therefore, in order to ensure the reliable bearing and transmission of the concentrated load, the bundling structure and the core stage section are often designed as an integral structure, and beams, supports and other structures are used near the bundling structure to effectively diffuse the concentrated load. However, this integrated design scheme actually often requires higher structural assembly accuracy, and also increases the difficulty of assembly and disassembly of the bundling structure. Summary of the invention

[0004] The embodiments of the present application provide a detachable bundling support structure for a launch vehicle, a disassembly method thereof, and a launch vehicle to meet the needs of repeated disassembly and assembly of the bundling structure and to improve the adaptability to various bundling structures such as transport joints, lifting joints, and whole-rocket erection joints required under different operating conditions.

[0005] In order to achieve the above objectives, this application provides the following technical solutions:

[0006] The present application provides a detachable bundling support structure for a launch vehicle, which comprises:

[0007] a booster connection portion configured to connect to a booster; and

[0008] An interface portion is connected to the booster connection portion, and the interface portion is configured to be detachably fixedly connected to the rocket body and rocket shell segment.

[0009] Furthermore, the interface portion includes a first sub-portion and a second sub-portion, the first sub-portion is located on the top of the boosting connection portion, and the second sub-portion is connected to the left and right sides of the boosting connection portion respectively.

[0010] Furthermore, the interface portion and the boost connection portion are an integrated structure.

[0011] Furthermore, the interface portion is detachably fixedly connected to the arrow body shell via fasteners.

[0012] The present application also provides a launch vehicle, which includes: a booster, a rocket body shell segment and the detachable bundling support structure of the launch vehicle, the detachable bundling support structure of the launch vehicle and the rocket body shell segment are detachably fixedly connected, and the booster is connected to the booster connecting part.

[0013] Furthermore, the first sub-section is detachably fixedly connected to the main beam root joint of the rocket body shell section via a fastener;

[0014] The secondary beam of the body shell segment, the middle frame of the body shell segment, the end frame of the body shell segment and the reinforcement joint of the body shell segment are respectively detachably fixedly connected with the second sub-section through fasteners.

[0015] Furthermore, the fastener is a screw.

[0016] Furthermore, a spring washer is sleeved on the screw.

[0017] The present application also provides a method for disassembling and assembling a detachable bundling support structure of a launch vehicle, using any of the detachable bundling support structures of a launch vehicle, comprising:

[0018] The first sub-section of the detachable bundling support structure of the launch vehicle is detachably fixedly connected to the root joint of the main beam of the rocket body shell section by fasteners;

[0019] The auxiliary beam of the rocket body shell segment, the middle frame of the rocket body shell segment, the end frame of the rocket body shell segment and the reinforced joint of the rocket body shell segment are respectively detachably fixedly connected to the second sub-section of the detachable binding support structure of the launch vehicle through fasteners.

[0020] Optionally, the fastener is a screw.

[0021] The detachable bundling support structure for a launch vehicle and the disassembly method thereof, as well as the launch vehicle provided in the embodiments of the present application, mainly have the following technical effects:

[0022] The present application designs the detachable bundling support structure of the launch vehicle and the rocket body shell segment into a split structure, and adopts a booster connecting part to connect with the booster, and adopts an interface part to detachably and fixedly connect with the rocket body shell segment. This, to a certain extent, meets the needs of repeated disassembly and assembly of the bundling structure, and improves the adaptability of various bundling structures such as transportation joints, lifting joints and whole rocket erection joints required under different operating conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] The drawings described herein are used to provide a further understanding of the present application and constitute a part of the present application. The illustrative embodiments of the present application and their descriptions are used to explain the present application and do not constitute an improper limitation on the present application. In the drawings:

[0024] Figure 1 A schematic diagram of the structure of a launch vehicle in one or more embodiments of the present application;

[0025] Figure 2 for Figure 1 A local enlarged schematic diagram of the middle A;

[0026] Figure 3 A cross-sectional view of a launch vehicle in one or more embodiments of the present application;

[0027] Figure 4 A top view of a detachable bundling support structure of a launch vehicle in one or more embodiments of the present application;

[0028] Figure 5 A front view of a detachable bundling support structure for a launch vehicle in one or more embodiments of the present application.

[0029] The following are marked in the accompanying drawings:

[0030] 100. detachable bundling support structure of launch vehicle; 101. rocket body shell segment; 102. main beam; 103. secondary beam; 104. skin; 105. middle frame; 106. end frame; 107. reinforced joint; 108. main beam root joint; 109. screw; 110. support plate self-locking nut; 111. spring washer; 112. first mounting hole; 113. second mounting hole; 114. first sub-unit; 115. second sub-unit; 116. booster connection unit. DETAILED DESCRIPTION

[0031] In order to make the technical solutions and advantages in the embodiments of the present application more clearly understood, the exemplary embodiments of the present application are further described in detail below in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present application, rather than an exhaustive list of all the embodiments. It should be noted that the embodiments in the present application and the features in the embodiments can be combined with each other without conflict.

[0032] In view of the working conditions such as horizontal transportation, lifting and erection of the whole rocket proposed for the new generation of launch vehicles, it is necessary for specific sections to adopt different bundling connection structures during transportation, erection and connection with boosters. This requires that the bundling connection position can not only achieve basic functions such as reliable connection and separation, but also meet the functional requirements of repeated disassembly and assembly, and adaptation to different launch vehicles of the detachable bundling support structure 100. Against this background, the overall design of the detachable bundling support structure 100 for launch vehicles is no longer applicable. In order to meet the requirements of repeated disassembly and assembly, and adaptation to the functions of the detachable bundling support structure 100 for different launch vehicles, the present application provides a detachable launch vehicle detachable bundling support structure 100 design, which can meet the requirements of large concentrated force bearing function and repeated disassembly and assembly function.

[0033] See also Figure 1 As shown, in one or more embodiments, the present application provides a detachable bundling support structure 100 for a launch vehicle, which includes: a booster connection portion 116 and an interface portion; the booster connection portion is configured to be connected to the booster; the interface portion is connected to the booster connection portion 116, and the interface portion is configured to be detachably fixedly connected to the rocket body and rocket shell segment 101.

[0034] The present application designs the launch vehicle's detachable bundling support structure 100 and the rocket body shell segment 101 into a split structure, and adopts a booster connection part 116 to connect with the booster, and adopts an interface part to detachably and fixedly connect with the rocket body shell segment 101, which reduces the assembly accuracy to a certain extent, thereby facilitating the connection between the launch vehicle's detachable bundling support structure 100 and the booster.

[0035] See also Figure 4 As shown, in some embodiments, the interface portion includes a first sub-portion 114 and a second sub-portion 115, the first sub-portion 114 is located at the top of the booster connection portion 116, and the second sub-portion 115 is connected to the left and right sides of the booster connection portion 116. The booster connection portion 116 is substantially cylindrical, and the first sub-portion 114 and the second sub-portion 115 are respectively located at the top and the left and right sides of the booster connection portion 116 to be suitable for the cylindrical shape of the rocket body shell segment 101 and its internal space. The length of the second sub-portion 115 extends along the axial direction of the rocket body shell segment 101; a plurality of second mounting holes 113 are arranged along the length direction of the second sub-portion 115, and the second mounting holes 113 are light holes. A plurality of first mounting holes 112 are opened on the first sub-portion 114, and the first mounting holes 112 are threaded holes.

[0036] In some embodiments, the interface portion and the booster connection portion 116 are an integrated structure, which can improve the overall connection strength of the launch vehicle detachable binding support structure 100.

[0037] In some embodiments, the interface portion is detachably fixedly connected to the arrow body shell by a fastener. In one embodiment, the fastener is a screw 109; it should be noted that in some other embodiments, the fastener is not limited to the screw 109.

[0038] In one or more embodiments, the present application further provides a launch vehicle, comprising: a booster, a rocket body shell segment 101, and a launch vehicle detachable bundling support structure 100 provided by any embodiment, wherein the launch vehicle detachable bundling support structure 100 and the rocket body shell segment 101 are detachably fixedly connected, and the booster is connected to a booster connection portion 116. By making the launch vehicle detachable bundling support structure 100 and the concentrated force diffusion structures such as the main beam and the auxiliary beam 103 in the conventional rocket body shell segment 101 detachable, the launch vehicle detachable bundling support structure 100 can bear and transmit concentrated loads through the main beam, the auxiliary beam 103 and other structures, and can be directly separated from the remaining structures through simple operations when necessary, so as to meet the needs of rapid and repeated disassembly and assembly.

[0039] In one embodiment, four launch vehicle detachable binding support structures 100 are evenly installed around the circumference of the rocket body shell, and four boosters are connected to the corresponding side hangs.

[0040] See also Figure 2 and Figure 3 As shown, in some embodiments, the first sub-section 114 is detachably fixedly connected to the main beam root joint 108 of the rocket body shell segment 101 by a fastener, wherein the fastener is a screw 109, and a spring washer 111 is also sleeved on the screw 109 to prevent loosening. The axis of the screw 109 between the first sub-section 114 and the main beam 102 is parallel to the axis of the rocket body shell segment 101; the main beam of the rocket body shell segment 101 is connected to the skin 104 and the middle frame 105 of the rocket body shell segment 101 by screws 109 and spring washers 111 are used to prevent loosening; the main beam root joint 108 is also the root joint of the main beam; the first sub-section 114 located at the top of the booster connection 116 is connected to the main beam. In one embodiment, two threaded holes are opened on the first sub-section 114, and two screws 109 are used to achieve a detachable fixed connection between the first sub-section 114 and the main beam during installation.

[0041] In some embodiments, the secondary beam 103 of the body shell segment 101, the middle frame 105 of the body shell segment 101, the end frame 106 of the body shell segment 101 and the reinforced joint 107 of the body shell segment 101 are respectively detachably fixedly connected to the second sub-section 115 via fasteners.

[0042] In one embodiment, the secondary beam 103 of the rocket body shell segment 101 is fixed to the outside of the skin 104; the reinforcement joint 107 is fixed to the inside of the skin 104. The middle frame 105 is located on the inside of the skin 104. An end frame 106 is located below the second sub-section 115. The second sub-sections 115 on the left and right sides of the launch vehicle detachable bundling support structure 100 are connected to the secondary beam 103, the middle frame 105, the end frame 106 and the reinforcement joint 107 on the inside of the rocket body shell segment 101 by screws 109 and support plate self-locking nuts 110, and spring washers 111 are used to prevent loosening. Seven light holes are opened on the second sub-section 115, so that the second sub-sections 115 on the left and right sides of the launch vehicle detachable bundling support structure 100 are detachably fixedly connected to the rocket body shell segment 101 by 14 screws 109. It should be noted that the number of the first mounting holes 112 is not limited to 2; the number of the second mounting holes 113 is not limited to 7.

[0043] In at least one embodiment, the launch vehicle provided by the present application can diffuse the concentrated force on the detachable bundling support structure 100 of the launch vehicle through the main beam, the auxiliary beam 103 and the reinforced joint 107 to the middle frame 105 and the end frame 106, so as to meet the structural bearing requirements; it is only necessary to remove the screws 109 of the first sub-section 114 (connected to the main beam) and the left and right second sub-sections 115 (connected to the auxiliary beam 103), so as to realize the separation of the detachable bundling support structure 100 of the launch vehicle without removing other main load-bearing components; at the same time, the two second sub-sections 115 use screws 109 of the same specifications to realize quick replacement and installation. In addition, the launch vehicle's detachable bundling support structure 100, main beam, auxiliary beam 103, reinforced joint 107, middle frame 105 and end frame 106 are connected to form a whole. The axial concentrated load on the launch vehicle's detachable bundling support structure 100 can be diffused and transmitted to the upper and lower end frames 106 through the main beam, auxiliary beam 103 and other load-bearing components. At the same time, the lateral and radial concentrated loads on the launch vehicle's detachable bundling support structure 100 can also be diffused through the reinforced joint 107, middle frame 105, end frame 106 and the main beam, auxiliary beam 103 and other load-bearing components, ensuring that the structure can still achieve effective bearing under concentrated force loads.

[0044] In one or more embodiments, the present application provides a method for disassembling and assembling a launch vehicle detachable bundling support structure 100, using the launch vehicle detachable bundling support structure 100 provided by any embodiment, the method includes: an installation method and a disassembly method;

[0045] The installation method includes: detachably and fixedly connecting the first sub-section 114 of the detachable bundling support structure 100 of the launch vehicle to the main beam root joint 108 of the rocket body shell segment 101 through fasteners to achieve a detachable and fixed connection between the first sub-section 114 and the main beam; and detachably and fixedly connecting the secondary beam 103 of the rocket body shell segment 101, the middle frame 105 of the rocket body shell segment 101, the end frame 106 of the rocket body shell segment 101 and the reinforced joint 107 of the rocket body shell segment 101 to the second sub-section of the detachable bundling support structure 100 of the launch vehicle through fasteners.

[0046] The disassembly method comprises: removing the fasteners used to connect the first sub-section 114 of the detachable bundling support structure 100 of the launch vehicle and the joint 108 at the root of the main beam, and taking away the spring washer 111, and disconnecting the connection between the detachable bundling support structure 100 of the launch vehicle and the main beam; removing the fasteners and spring washers 111 used to connect the second sub-section 115 on the left and right sides of the detachable bundling support structure 100 of the launch vehicle and the reinforced joint 107 on the inner side of the auxiliary beam 103, the middle frame 105, the end frame 106 and the rocket body shell segment 101, disconnecting the connection between the detachable bundling support structure 100 of the launch vehicle and other components, and removing the detachable bundling support structure 100 of the launch vehicle.

[0047] In some embodiments, in the installation method and the removal method, the fastener is a screw 109 .

[0048] The present application also provides a specific application scenario of the detachable bundling support structure 100 for a launch vehicle in at least one embodiment:

[0049] (a) See Figure 4 As shown, the first sub-section 114 of the detachable bundling support structure 100 of the launch vehicle is designed with two M18 threaded holes, which are connected to the main beam root joint 108 by two M18×1.5 bolts, and QJ2963.2-97 spring washers 111 are used to prevent loosening. The threaded holes on the main beam root joint 108 need to be processed in coordination with the threaded holes on the detachable bundling support structure 100 of the launch vehicle;

[0050] (b) See Figure 5 As shown, the second sub-section 115 on the left and right sides of the detachable bundling support structure 100 of the launch vehicle is designed as 7 Φ17.8 light holes respectively, and a total of 14 M16×1.5 bolts are used to connect with the auxiliary beam 103, the middle frame 105, the end frame 106 and the reinforcement joint 107 on the inner side of the rocket body shell section 101, and QJ2963.2-97 spring washers 111 are used to prevent loosening. At the same time, the docking structure on the rocket needs to pre-set 14 support plate self-locking nuts 110, with threaded holes M16×1.5-7H and an effective thread depth of 12mm.

[0051] The design of the launch vehicle's detachable bundling support structure 100 for this application scenario has been verified through model ground static tests and multiple-launch flight tests, and can simultaneously meet the functional requirements of large concentrated force bearing and repeated disassembly and assembly.

[0052] In summary, the launch vehicle detachable bundling support structure 100 and its disassembly and assembly method, and the launch vehicle provided by the present application have the following advantages:

[0053] (a) The detachable bundling support structure 100 of the launch vehicle designed in the present application is connected with other main load-bearing structures (including the main beam, the secondary beam 103, the reinforced joint 107, the intermediate frame 105, the end frame 106, and the skin 104) of the rocket body shell section 101, thereby strengthening the structural stiffness around the detachable bundling support structure 100 of the launch vehicle, and at the same time realizing the effective diffusion of the concentrated force of the detachable bundling support structure 100 of the launch vehicle; the detachable bundling support structure 100 of the launch vehicle is connected with the other main load-bearing components to form a whole, which greatly improves the overall and local stiffness of the structure, and at the same time can fully diffuse the concentrated force at the detachable bundling support structure 100 of the launch vehicle, thereby avoiding large local deformation or failure of the structure, and ensuring the effective bearing of the structure.

[0054] (b) The detachable bundling support structure 100 of the launch vehicle designed in the present application and other main load-bearing structures of the rocket body shell segment 101 adopt a separate design concept, which can meet the repeated disassembly and assembly requirements put forward by the new generation of launch vehicles; when the specific section of the rocket is horizontally transported, lifted and erected, the detachable bundling support structure 100 of the launch vehicle can be repeatedly disassembled and assembled as needed, and the operation is simple, which greatly shortens the structural modification cycle; when the specific section of the rocket is horizontally transported, lifted and erected, the structural design scheme can realize the rapid disassembly and assembly of the detachable bundling support structure 100 of the launch vehicle without affecting the other structures on the section.

[0055] (c) When horizontally transporting, lifting and erecting specific sections of a rocket, different types of launch vehicle detachable bundling support structures 100, such as different transport joints, lifting joints and whole rocket erection joints, are often required. In the present application, the launch vehicle detachable bundling support structure 100 adopts a unified adapter interface (the second subsections 115 on the left and right sides adopt fasteners of the same specifications), which greatly improves the applicability of the structure and can simultaneously meet the use and modification requirements of various types of launch vehicle detachable bundling support structures 100, and can adapt to various types of launch vehicle detachable bundling support structures 100, such as transport joints, lifting joints and whole rocket erection joints required under different operating conditions.

[0056] Although the preferred embodiments of the present application have been described, those skilled in the art may make other changes and modifications to these embodiments once they have learned the basic creative concept. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments and all changes and modifications falling within the scope of the present application.

[0057] Obviously, those skilled in the art can make various changes and modifications to the present application without departing from the spirit and scope of the present application. Thus, if these modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is also intended to include these modifications and variations.

Claims

1. A launch vehicle, characterized in that: include: A booster, a rocket body shell segment and a detachable bundling support structure for a launch vehicle, wherein the detachable bundling support structure for the launch vehicle and the rocket body shell segment are detachably and fixedly connected, and the booster is connected to a booster connection portion; The launch vehicle detachable bundling support structure comprises: a booster connection portion, the booster connection portion being configured to be connected to the booster; as well as An interface portion, the interface portion being connected to the booster connection portion, and the interface portion being configured to be detachably fixedly connected to the rocket body shell segment; The interface portion includes a first sub-portion and a second sub-portion, the first sub-portion is located at the top of the boosting connection portion, and the second sub-portions are connected to the left and right sides of the boosting connection portion respectively; The secondary beam of the body shell segment is fixed to the outer side of the skin of the body shell segment; the reinforcement joint of the body shell segment is fixed to the inner side of the skin of the body shell segment, the middle frame of the body shell segment is located on the inner side of the skin of the body shell segment, and the end frame of the body shell segment is located below the second sub-section; the concentrated force received at the detachable binding support structure of the launch vehicle is diffused to the middle frame of the body shell segment and the end frame of the body shell segment through the main beam of the body shell segment, the secondary beam of the body shell segment and the reinforcement joint of the body shell segment; The first sub-section is detachably fixedly connected to the main beam root joint of the rocket body shell section via a fastener; The secondary beam of the body shell segment, the middle frame of the body shell segment, the end frame of the body shell segment and the reinforcement joint of the body shell segment are respectively detachably fixedly connected with the second sub-section through fasteners.

2. The launch vehicle according to claim 1, characterized in that: The fastener is a screw.

3. The launch vehicle according to claim 2, characterized in that: A spring washer is also sleeved on the screw.

4. The launch vehicle according to claim 1, characterized in that: The interface portion and the boost connection portion are an integrated structure.

5. The launch vehicle according to claim 1, characterized in that: The interface portion is detachably fixedly connected to the rocket body shell segment via fasteners.

6. A method for disassembling and assembling a detachable bundling support structure of a launch vehicle, using the detachable bundling support structure of a launch vehicle, wherein the detachable bundling support structure of the launch vehicle comprises: A booster connection part, the booster connection part is configured to be connected to a booster; and an interface part, the interface part is connected to the booster connection part, and the interface part is configured to be detachably fixedly connected to a rocket body shell segment; the interface part includes a first sub-part and a second sub-part, the first sub-part is located at the top of the booster connection part, and the second sub-part is respectively connected to the left and right sides of the booster connection part; the auxiliary beam of the rocket body shell segment is fixed to the outer side of the skin of the rocket body shell segment; the reinforcement joint of the rocket body shell segment is fixed to the inner side of the skin of the rocket body shell segment, the middle frame of the rocket body shell segment is located on the inner side of the skin of the rocket body shell segment, and the end frame of the rocket body shell segment is located below the second sub-part; the concentrated force received at the detachable bundling support structure of the launch vehicle is diffused to the middle frame of the rocket body shell segment and the end frame of the rocket body shell segment through the main beam of the rocket body shell segment, the auxiliary beam of the rocket body shell segment and the reinforcement joint of the rocket body shell segment; characterized in that the method comprises: The first sub-section of the detachable bundling support structure of the launch vehicle is detachably fixedly connected to the root joint of the main beam of the rocket body shell section by fasteners; The auxiliary beam of the rocket body shell segment, the middle frame of the rocket body shell segment, the end frame of the rocket body shell segment and the reinforced joint of the rocket body shell segment are respectively detachably fixedly connected to the second sub-section of the detachable binding support structure of the launch vehicle through fasteners.

7. The method for disassembling and assembling a detachable bundling support structure of a launch vehicle according to claim 6, characterized in that: The fastener is a screw.

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