Modular fairing

Abstract

The embodiment of the application provides a modular fairing, comprising two separable half fairings connected through a separation structure on a middle separation surface, a middle axis of the fairing is located in a plane where the separation surface of the two half fairings is located, and the two half fairings combine to form an internal envelope space; the half fairing is sequentially provided with a head, a front cone, a column section and a transition section along the middle axis direction from top to bottom, the head and the front cone are connected through a first connecting assembly; the front cone and the column section are connected through a second connecting assembly; and the column section and the transition section are connected through a third connecting assembly. The embodiment of the application provides different basic types of fairings, each basic type is split into independent modules such as a head, a front cone, a column section and a transition section, and different payload envelope requirements of the fairing are realized through a free combination form. The embodiment solves the problem that a model is flexibly and quickly adapted to different space envelope requirements of a payload, and improves the adaptability of the fairing when a space vehicle launches different payloads.

Description

Technical Field

[0001] This application relates to the field of space launch vehicle structural design and manufacturing technology, specifically to a fairing structure for the development of fairings for medium, large and heavy launch vehicles, which adopts a modular design to adapt to the space envelope requirements of different payloads. Background Technology

[0002] The function of a launch vehicle's payload fairing is to provide the payload with a suitable environment, protecting it from aerodynamic forces and aerothermal effects. In recent years, launch vehicles have become increasingly larger, ranging from 3-meter-class medium-lift launch vehicles to 5-meter-class heavy-lift launch vehicles. The structure of the fairing has also become larger, with some domestic and international companies even beginning to develop 10-meter-class heavy-lift launch vehicle fairings. The fairing has a longitudinal separation surface, typically dividing it into two halves. Separation structures, such as explosive bolts, hook-and-lock mechanisms, airbag-push-type mechanisms, and notched bolt mechanisms, are installed on the separation surface. Once the launch vehicle exits the atmosphere, the longitudinal separation surface unlocks, and the two halves separate from the rocket.

[0003] Currently, each half of the fairing is mostly molded as a single piece, with a structure that can be either a semi-monocoque structure or a composite sandwich structure. However, as fairing structures become larger, the single-piece molding process becomes more difficult, especially for composite sandwich structures, which are limited by the size of existing autoclaves and cannot be increased arbitrarily, while the cost of installing new autoclaves is high. In addition, single-piece molding cannot meet the envelope requirements of different payloads, and changing the fairing size requires redesign, which restricts the launch vehicle's ability to adapt to different launch missions. Summary of the Invention

[0004] This application provides a modular fairing to address one of the aforementioned deficiencies.

[0005] This application provides the following technical solution:

[0006] A modular fairing includes two separable half-fairings connected by a separation structure on a middle separation surface. The central axis of the fairing lies in the plane containing the separation surface of the two half-fairings, and the two half-fairings combine to form an internal envelope space.

[0007] The semi-enclosed structure is provided sequentially from top to bottom along the central axis, consisting of an end cap, a front cone, at least one column segment, and a transition segment. The front cone and column segment are sandwich structures.

[0008] The end cap and the front cone are connected by a first connecting component; the front cone and the column segment are connected by a second connecting component; the column segments are connected by a third connecting component; and the column segment and the transition segment are connected by a fourth connecting component.

[0009] As a preferred embodiment of this application, the bottom end of the transition section is connected to the final stage of the rocket body.

[0010] As a preferred embodiment of this application, the front cone has an inner wall surface near the central axis and an outer wall surface away from the central axis, with a sandwich layer between the inner and outer wall surfaces; the top of the front cone is inserted into a first frame towards the middle of the front cone, and the first frame extends circumferentially along the half-cover.

[0011] The longitudinal section of the first frame is a U-shaped structure, including two parallel first frame sides and first frame sides. One side of the first frame is closely connected to the outer wall of the front cone, and the two sides of the first frame are closely connected to the inner wall of the front cone.

[0012] As a preferred embodiment of this application, the first connecting component includes: a first reinforcing frame extending circumferentially along the half-cover, including one side of the first reinforcing frame integrally formed with an obtuse angle and two sides of the first reinforcing frame, wherein one side of the first reinforcing frame is closely connected to the inner wall surface of the front cone;

[0013] The first end frame extends circumferentially along the half-cover and includes one side of the first end frame and two sides of the first end frame integrally formed with an obtuse angle. One side of the first end frame is closely connected to one side of the first frame.

[0014] The lower frame extends circumferentially along the half-cover and includes one side of the lower frame and two sides of the lower frame integrally formed with an acute angle. One side of the lower frame is closely connected to the inner wall surface of the lower part of the end.

[0015] The first end frame is located below the two sides of the lower end frame and above the two sides of the first reinforcing frame;

[0016] The two sides of the lower end frame, the two sides of the first end frame, and the two sides of the first reinforcing frame are connected by multiple bolt assemblies.

[0017] As a preferred embodiment of this application, the column segment includes an inner wall surface near the central axis and an outer wall surface away from the central axis. The top and bottom ends of the column segment are connected to a third frame in the direction of the middle of the column segment. The longitudinal section of the third frame is U-shaped, including two parallel sides, one side of the third frame near the central axis and two sides of the third frame away from the central axis.

[0018] As a preferred embodiment of this application, the bottom end of the front cone is inserted into the middle of the front cone, and the longitudinal section of the second frame is U-shaped, including two parallel sides, one side of the second frame close to the central axis and two sides of the second frame away from the central axis.

[0019] The second connecting component includes: a second end frame extending circumferentially along the front cone, having one side of the second end frame and two sides of the second end frame, wherein the side of the second end frame facing away from the central axis is closely connected to the side of the two sides of the second end frame close to the central axis, and the two sides of the second end frame extend horizontally in the direction close to the central axis;

[0020] The third end frame extends circumferentially along the front cone and has one side and two sides. The longitudinal section of the third end frame is an L-shaped structure. The side of the third end frame facing away from the central axis is closely connected to the side of the two sides of the third end frame that is close to the central axis. The two sides of the third end frame extend horizontally towards the central axis.

[0021] The two sides of the second end frame are close to the two sides of the third end frame and are connected by multiple large bolt assemblies. The large bolt assemblies are located close to one side of the second end frame and one side of the third end frame.

[0022] As a preferred embodiment of this application, the second connecting component further includes:

[0023] The second reinforcing frame includes one side of the second reinforcing frame and two sides of the second reinforcing frame. One side of the second reinforcing frame is closely connected to the inner wall of the front cone. The two sides of the second reinforcing frame extend horizontally towards the central axis. The two sides of the second reinforcing frame are located above the two sides of the second end frame.

[0024] The third reinforcing frame includes one side and two sides of the third reinforcing frame. One side of the third reinforcing frame is closely connected to the inner wall of the column segment. The two sides of the third reinforcing frame extend horizontally towards the central axis and are located below the two sides of the third end frame.

[0025] The two sides of the second reinforcing frame, the two sides of the second end frame, the two sides of the third end frame, and the two sides of the third reinforcing frame are connected by multiple small bolt assemblies.

[0026] As a preferred embodiment of this application, the third connecting component includes two sets of third end frames and third reinforcing frames symmetrically connected to the top and bottom of adjacent column segments. The two sides of adjacent third end frames are connected through multiple large bolt assemblies; the two sides of adjacent third reinforcing frames and the two sides of adjacent third end frames are connected through multiple small bolt assemblies.

[0027] As a preferred embodiment of this application, the fourth connecting component includes a front end frame that extends circumferentially along the transition section. The front end frame includes one front end frame side and two front end frame sides, with one front end frame side being fixed close to the inner wall surface of the transition section.

[0028] The two front ends are located below the two adjacent third end frames, and the two front ends and the two third end frames are connected by a series of large bolt assemblies.

[0029] The two sides of the adjacent third reinforcing frame, the two sides of the third end frame, and the two sides of the front frame are connected by multiple small bolt assemblies.

[0030] As a preferred embodiment of this application, a honeycomb layer is provided between the inner wall surface and the outer wall surface of the column segment.

[0031] The modular fairing provided in this application embodiment has the following technical advantages compared to the prior art:

[0032] This application provides a modular fairing, which connects two symmetrical half-fairings via a central separation structure. The two half-fairings combine to form an internal envelope space. Each half-fairing, from top to bottom along its central axis, sequentially comprises an end cap, a front cone, a cylindrical section, and a transition section. Adjacent structural components are connected by corresponding connecting components. This application provides different basic fairing models, each of which is divided into independent modules such as an end cap, a front cone, a cylindrical section, and a transition section. These modules can be freely combined to meet different payload envelope requirements. This solves the need for flexible and rapid adaptation to different payload spatial envelopes, improving the fairing's adaptability when launching different payloads from spacecraft. Attached Figure Description

[0033] The accompanying drawings, which are included to provide a further understanding of this application and form part of this application, illustrate exemplary embodiments and are used to explain this application, but do not constitute an undue limitation of this application. In the drawings:

[0034] Figure 1 A schematic diagram of the modular fairing structure provided in the embodiments of this application;

[0035] Figure 2 This is a schematic diagram of the connection form between the end cap and the front cone provided in an embodiment of this application;

[0036] Figure 3 This is a schematic diagram of the connection between the front cone and the column segment provided in an embodiment of this application;

[0037] Figure 4 This is a schematic diagram of the connection form between column segments provided in the embodiments of this application;

[0038] Figure 5 This is a schematic diagram illustrating the connection form between the column segment and the transition segment provided in an embodiment of this application;

[0039] Figure 6 This is a schematic diagram of another embodiment of the structure of this application.

[0040] The following labels are shown in the attached diagram:

[0041] End cap 100, front cone 200, column section 300, transition section 400.

[0042] Bottom frame 1, interlayer 2, first border 3, first end frame 4, first reinforcing frame 5, second border 6, second end frame 7, second reinforcing frame 8, honeycomb layer 9, third border 10, third end frame 11, third reinforcing frame 12, front frame 13. Detailed Implementation

[0043] This invention discloses an energy-absorbing device to solve the problems of poor and unstable energy absorption effect and easy rebound after compression of existing spring anti-climb energy-absorbing devices.

[0044] To make the technical solutions and advantages of the embodiments of this application clearer, the exemplary embodiments of this application will be described in further detail below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this application, and not an exhaustive list of all embodiments. It should be noted that, unless otherwise specified, the embodiments and features in the embodiments of this application can be combined with each other.

[0045] Please see Figures 1-5 As shown, to address the variable space requirements of the fairing, this invention employs a modular design approach, dividing the fairing half into different functional units. These units can be freely combined to achieve different spatial envelope requirements. The payload envelope requirements are determined based on mission needs. A combination form is selected from the basic model based on the envelope, with all modules being standard-sized products and interfaces remaining constant. All modules are connected via screw connections, allowing the assembly sequence to be determined after the mission is defined.

[0046] In one specific implementation, a complete modular fairing comprises two separable halves. Figure 1 This is a schematic diagram of a modular fairing structure provided in an embodiment of this application. Figure 1 As shown, the two half-covers are connected by a separation structure on the middle separation surface. The central axis of the fairing is located in the plane where the separation surfaces of the two half-covers are located. The two half-covers are combined to form the internal envelope space.

[0047] The semi-enclosed structure consists of an end cap 100, a front cone 200, one or more column segments 300, and a transition section 400 arranged sequentially from top to bottom along the central axis. The front cone 200 and column segments 300 are sandwich structures. A honeycomb layer 9 is filled between the inner and outer walls of the column segments.

[0048] The end section (100mm) is typically a spherical cap molded from a heat-resistant material, such as fiberglass, with a metal frame connecting the lower end for docking. The forward cone section generally adopts a von Kármán shape, a single cone shape, or a double cone shape, and the structural form is a sandwich structure with good rigidity. The column section is generally divided into two different heights for combining into fairings of different heights, and the structural form is also a sandwich structure with good rigidity. The transition section connects the column section and the rocket's final stage body, serving as a transition between the two. Its shape can be cylindrical or inverted conical, and it can also accommodate separation spring supports, hinge supports, instrument supports, and other structures.

[0049] End cap 100 and front cone 200 are connected by a first connecting assembly. Front cone 200 and column section 300 are connected by a second connecting assembly. Column sections 300 and 300 are connected by a third connecting assembly. Column section 300 and transition section 400 are connected by a fourth connecting assembly. By designing detachable connection methods between different modules, rapid combination of different modules is achieved, improving the fairing's ability to be freely combined.

[0050] Figure 2 This is a schematic diagram illustrating the connection form between the end cap and the front cone provided in an embodiment of this application. Figure 2 As shown, the lower end frame 1 of the end head is connected to the front cone 200 by a ring of bolts. The front cone 200 adopts a sandwich structure, with the first frame 3 embedded in the end face of the top.

[0051] Specifically, the front cone 200, as a sandwich structure, has an inner wall surface near the central axis and an outer wall surface away from the central axis. A sandwich layer 2 is filled between the inner and outer walls of the front cone. A first frame 3 is inserted at the top of the front cone 200 towards the center of the front cone 200. The first frame 3 has an opening away from the center of the front cone. The first frame 3 extends circumferentially along the semi-enclosed structure and can be a closed ring structure or an intermittent arc-shaped structure.

[0052] The longitudinal section of the first frame 3 is a U-shaped structure, including two parallel first frame sides. One side of the first frame is closely connected to the outer wall of the front cone, and the two sides of the first frame are closely connected to the inner wall of the front cone. The first frame 3 serves as an auxiliary connecting structure for the connecting assembly, used to connect with the first connecting assembly.

[0053] Specifically, the lower end frame 1 of the end head 100 is connected to the first end frame 4 and the first reinforcing frame 5.

[0054] The first reinforcing frame 5 extends circumferentially along the half-cover and includes one side of the first reinforcing frame and two sides of the first reinforcing frame integrally formed with an obtuse angle. One side of the first reinforcing frame is closely connected to the inner wall surface of the front cone.

[0055] The first end frame 4 extends circumferentially along the half-cover and includes one side of the first end frame and two sides of the first end frame integrally formed with an obtuse angle. One side of the first end frame is closely connected to one side of the first frame.

[0056] The lower frame 1 extends circumferentially along the semi-enclosed structure and includes one side and two sides of the lower frame integrally formed with an acute angle. One side of the lower frame is closely connected to the lower inner wall of the end head 100. Since the end head, when assembled, is a pointed structure with a dome that is approximately an isosceles triangle in the main view projection, the lower frame here has two sides with an acute angle, one side being parallel to the side slope of the end head, and the other side extending horizontally towards the central axis.

[0057] The first end frame is located below the two sides of the lower end frame and above the two sides of the first reinforcing frame;

[0058] The two sides of the lower frame, the two sides of the first end frame, and the two sides of the first reinforcing frame are connected by multiple bolt assemblies. The bolt assemblies form a dense circular array to achieve a firm connection.

[0059] The bottom of the front cone 200 is inserted into the middle of the front cone 200 via a second frame 6. The longitudinal section of the second frame 6 is U-shaped, consisting of two parallel sides, one side close to the central axis and the other two sides away from the central axis. As the top structure of the fairing, the end cap, being the smallest in volume than other parts, can be stabilized with just one bolt.

[0060] Figure 3 This is a schematic diagram illustrating the connection between the front cone and the column segment according to an embodiment of this application. The rear end face of the front cone is embedded with a second frame 6, and the front end face of the column segment is also embedded with a third frame 10. The front cone is connected to the third end frame 11 and the third reinforcing frame 12 of the column segment via a second end frame 7 and a second reinforcing frame 8.

[0061] Specifically, column segment 300 includes an inner wall surface near the central axis and an outer wall surface away from the central axis. A third frame 10 is inserted into the top and bottom of column segment 300 towards the center. The third frame 10 has a U-shaped longitudinal section, including two parallel sides, one side near the central axis and two sides away from the central axis. The third frame 10 has an opening away from the center of the column segment. The third frame 10 is provided at both the top and bottom of the column segment for better connection of corresponding connecting components, achieving modular and flexible connection.

[0062] When connected to column segment 300, the second end frame 7 extends circumferentially along the front cone 200, having one side of the second end frame and two sides of the second end frame. The side of the second end frame facing away from the central axis is closely connected to the side of the two sides of the second end frame that is close to the central axis. The two sides of the second end frame extend horizontally in the direction close to the central axis.

[0063] The third end frame 11 extends circumferentially along the front cone 200 and has one side and two sides. The longitudinal section of the third end frame 11 is an L-shaped structure. The side of the third end frame facing away from the central axis is closely connected to the side of the two sides of the third end frame that is close to the central axis. The two sides of the third end frame extend horizontally in the direction close to the central axis.

[0064] The two sides of the second end frame are close to the two sides of the third end frame and are connected by multiple large bolt assemblies. The large bolt assemblies are located close to one side of the second end frame and one side of the third end frame.

[0065] The second connection component also includes:

[0066] The second reinforcing frame 8 includes one side and two sides of the second reinforcing frame. The one side of the second reinforcing frame is closely connected to the inner wall of the front cone. The two sides of the second reinforcing frame extend horizontally towards the central axis and are positioned above the two sides of the second end frame.

[0067] The third reinforcing frame 12 includes one side and two sides of the third reinforcing frame. One side of the third reinforcing frame is closely connected to the inner wall of the column segment 300. The two sides of the third reinforcing frame extend horizontally towards the central axis and are located below the two sides of the third end frame.

[0068] The two sides of the second reinforcing frame, the two sides of the second end frame, the two sides of the third end frame, and the two sides of the third reinforcing frame are connected by multiple small bolt assemblies.

[0069] like Figure 3 As shown, the front cone and column section are connected by two rings of bolts, with the outer ring of large bolts being the main load-bearing connectors, used to bear most of the axial tensile load on the wall panel. The inner ring of small bolts are auxiliary connectors, used to counteract local bending moments and improve the stress condition of the honeycomb panel.

[0070] Figure 4 This is a schematic diagram illustrating the connection method between column segments provided in an embodiment of this application. Figure 4 As shown, the front and rear end faces of the column segment are embedded with a third frame 10, which is connected by a third end frame 11 and a third reinforcing frame 12.

[0071] Specifically, the third connecting component includes two sets of third end frames 11 and third reinforcing frames 12 symmetrically connected at the top and bottom of adjacent column segments 300. The two sides of adjacent third end frames are connected through multiple large bolt assemblies; the two sides of adjacent third reinforcing frames and the two sides of third end frames are connected through multiple small bolt assemblies.

[0072] The column segments are connected by two rings of bolts, with the outer ring of large bolts being the main load-bearing connectors, responsible for bearing most of the axial tensile loads on the wall panels. The inner ring of small bolts are auxiliary connectors, used to counteract local bending moments and improve the stress distribution of the honeycomb panels.

[0073] Figure 5 This is a schematic diagram illustrating the connection form between the column segment and the transition segment provided in an embodiment of this application. Figure 5 As shown, the rear end face of the column segment is embedded with a third frame 10. The column segment is connected to the front end frame 13 of the transition segment through a third end frame 11 and a third reinforcing frame 12.

[0074] The fourth connecting component includes a front frame 13, which extends circumferentially along the transition section 400. The front frame 13 includes one front frame side and two front frame sides, with one front frame side being close to and fixed to the inner wall of the transition section.

[0075] The two front ends are located below the two adjacent third end frames, and the two front ends and the two third end frames are connected through multiple large bolt assemblies.

[0076] The two sides of the adjacent third reinforcing frame, the two sides of the third end frame, and the two sides of the front frame are connected by multiple small bolt assemblies.

[0077] The column section and transition section are connected by two rings of bolts, with the outer ring of large bolts being the main load-bearing connectors, used to bear most of the axial tensile load of the wall panel. The inner ring of small bolts are auxiliary connectors, used to counteract local bending moments and improve the stress condition of the honeycomb panel.

[0078] Figure 1 This is a schematic diagram of the modular fairing structure provided in the embodiments of this application. Figure 6 This is a schematic diagram of another embodiment of the structure of this application. The bottom end of the transition section 400 is connected to the rocket's final stage body.

[0079] The diameter of the fairing section is determined based on the diameter of the final stage of the launch vehicle. Generally, two specifications are chosen: the same as the final stage diameter and a larger diameter. Then, the overall launch vehicle designers conduct aerodynamic shape analysis of the launch vehicle based on the two fairing diameters and carry out wind tunnel tests as needed. After the tests are passed, thermal environment and load analyses are conducted, and the design specifications for the fairing are given. Structural designers then design the basic fairing model based on the design specifications.

[0080] like Figure 1 , Figure 6 As shown, the basic fairing type generally includes two diameters: the basic type with the same diameter of the column section as the final stage rocket body and the basic type with an expanded column section. Each basic type achieves different envelopes in the height direction of the fairing through different combinations of column sections. At the same time, each basic type can be divided into the tip, the front cone, the column section and the transition section.

[0081] This disclosure presents different basic fairing designs, each of which is divided into independent modules such as the end cap 100, the front cone 200, the cylindrical section 300, and the transition section 400. These modules can be freely combined to meet the different payload envelope requirements of the fairing. This solves the problem of the need for flexible and rapid adaptation to different payload space envelopes and improves the adaptability of the fairing when launching different payloads from spacecraft.

[0082] This disclosure can be widely applied to the design of launch vehicles and missiles in my country, and can be applied to the design of large fairing structures in the future, with significant application value and social benefits.

[0083] Although preferred embodiments of this application have been described, those skilled in the art, upon learning the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments as well as all changes and modifications falling within the scope of this application.

[0084] Obviously, those skilled in the art can make various modifications and variations to this application without departing from the spirit and scope of this application. Therefore, if such modifications and variations fall within the scope of the claims of this application and their equivalents, this application also intends to include such modifications and variations.

Claims

1. A modular fairing, characterized by, The fairing comprises two separable half fairings connected by a separation structure on a middle separation surface, a middle axis of the fairing is located in a plane of the separation surface of the two half fairings, and the two half fairings combine to form an internal envelope space. The half fairing is sequentially provided with a head, a front cone, at least one column segment and a transition segment along the middle axis from top to bottom, and the front cone and the column segment are sandwiched structures. The head and the front cone are connected by a first connecting assembly, the front cone and the column segment are connected by a second connecting assembly, the column segments are connected by a third connecting assembly, and the column segment and the transition segment are connected by a fourth connecting assembly. The front cone has a front cone inner wall surface close to the middle axis and a front cone outer wall surface away from the middle axis, and a sandwich layer is filled between the front cone inner wall surface and the front cone outer wall surface. The first edge frame is in a U-shaped structure in a longitudinal section, and comprises two parallel first edge frame one sides and first edge frame two sides. The first connecting assembly comprises a first reinforcing frame extending along the circumference of the half fairing and comprising a first reinforcing frame one side and a first reinforcing frame two side integrally formed and having an obtuse angle, and the first reinforcing frame one side is connected to the front cone inner wall surface. The first end frame extends along the circumference of the half fairing and comprises a first end frame one side and a first end frame two side integrally formed and having an obtuse angle, and the first end frame one side is connected to the first edge frame one side. The lower end frame extends along the circumference of the half fairing and comprises a lower end frame one side and a lower end frame two side integrally formed and having an acute angle, and the lower end frame one side is connected to the inner wall surface of the lower part of the head. The first end frame two side is arranged below the lower end frame two side and above the first reinforcing frame two side. The lower end frame two side, the first end frame two side and the first reinforcing frame two side are connected by a plurality of bolt assemblies.

2. The modular fairing of claim 1, wherein, The transition segment bottom end is connected to the rocket final stage body.

3. The modular fairing of claim 1, wherein, The column segment comprises a column segment inner wall surface close to the middle axis and a column segment outer wall surface away from the middle axis, and a third edge frame is inserted into the middle part of the column segment from the top end and the bottom end of the column segment.

4. The modular fairing of claim 3, wherein, The front cone bottom end is inserted into the middle part of the front cone from the bottom end to the top end of the front cone. The second connecting assembly comprises a second end frame extending along the circumference of the front cone and having a second end frame one side and a second end frame two side, the second end frame one side is connected to the second edge frame two side close to the middle axis, and the second end frame two side extends horizontally towards the middle axis. The third end frame extends along the circumference of the front cone and has a third end frame one side and a third end frame two side, the third end frame one side is connected to the third edge frame two side close to the middle axis, and the third end frame two side extends horizontally towards the middle axis. The second end frame two sides are close to the third end frame two sides and are connected by a plurality of large bolt assemblies, and the large bolt assemblies are located close to the second end frame one side and the third end frame one side.

5. The modular fairing of claim 4, wherein, The second connecting assembly further comprises: The second reinforcing frame comprises a second reinforcing frame one side and a second reinforcing frame two side, the second reinforcing frame one side is close to the inner wall of the front cone, and the second reinforcing frame two side extends horizontally towards the direction close to the central axis, and the second reinforcing frame two side is arranged above the second end frame two side; The third reinforcing frame comprises a third reinforcing frame one side and a third reinforcing frame two side, the third reinforcing frame one side is close to the inner wall of the column segment, and the third reinforcing frame two side extends horizontally towards the direction close to the central axis, and the third reinforcing frame two side is arranged below the third end frame two side; The second reinforcing frame two side, the second end frame two side, the third end frame two side and the third reinforcing frame two side are connected by a plurality of small bolt assemblies.

6. The modular fairing of claim 5, wherein, The third connecting assembly comprises two groups of third end frames and third reinforcing frames which are symmetrically connected to the top end and the bottom end of the adjacent column segments, the adjacent third end frame two sides are connected by a plurality of large bolt assemblies, and the adjacent third reinforcing frame two sides and the third end frame two sides are connected by a plurality of small bolt assemblies.

7. The modular fairing of claim 6, wherein, The fourth connecting assembly comprises a front end frame, the front end frame extends along the transition segment in the circumferential direction, the front end frame comprises a front end frame one side and a front end frame two side, and the front end frame one side is close to the inner wall of the transition segment; The front end frame two side is arranged below the adjacent third end frame two side, and the front end frame two side and the third end frame two side are connected by a plurality of large bolt assemblies; The adjacent third reinforcing frame two side, the third end frame two side and the front end frame two side are connected by a plurality of small bolt assemblies.

8. The modular fairing of claim 1, wherein, The honeycomb layer is arranged between the inner wall of the column segment and the outer wall of the column segment.

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