A new self-separating fairing

Abstract

The utility model provides a novel self -separation fairing, include: fairing piece, magnetic attraction type pre -fixed structure and composite drive separation mechanism, fairing piece at least includes first half fairing piece and second half fairing piece, magnetic attraction type pre -fixed structure includes permanent magnet strip and electromagnetic adsorption block, permanent magnet strip fixed setting is in the butt joint of first half fairing piece and second half fairing piece, electromagnetic adsorption block fixed setting is in the butt joint of second half fairing piece and first half fairing piece, electromagnetic adsorption block energization passes through magnetic force and permanent magnet strip fixed connection, makes first half fairing piece and second half fairing piece fixed butt joint, composite drive separation mechanism sets up between first half fairing piece and second half fairing piece, and composite drive separation mechanism is used to provide driving force to make first half fairing piece and second half fairing piece separate. The fairing can effectively promote the reliability of fairing piece connection under low temperature environment.

Description

Technical Field

[0001] This utility model relates to the field of fairings, specifically to a novel self-separating fairing. Background Technology

[0002] As a key component of launch vehicles and spacecraft, the fairing's primary function is to protect the payload from aerodynamic heating, airflow erosion, and noise and vibration during launch and the initial stages of flight. The fairing needs to reliably separate from the rocket body during specific flight phases (such as at the atmospheric edge) to reduce rocket weight and prevent interference with the payload. The existing fairing self-separation structure has the following technical problems: (1) The docking structure mostly adopts rigid bolt connection or simple overlap. High-speed airflow can easily enter from the gap of the joint, causing local turbulence, which affects the aerodynamic stability of the rocket body. In addition, in extreme temperature environment (-50℃ to 150℃), the thermal expansion and contraction of the joint material can easily lead to sealing failure. (2) The mainstream separation method relies on pyrotechnics such as detonating bolts, which poses a risk of accidental triggering. The explosion process can easily generate fragments, which may damage the rocket body or payload. (3) Some separation mechanisms are driven by hydraulic / pneumatic pressure. The structure is complex and the maintenance cost is high. It is easy to jam at low temperature. When assembling the separation mechanism, it is necessary to ensure that the joint is tightly fitted. When separating, it is necessary to quickly release the constraint and provide stable thrust. The existing structure is difficult to meet the requirements of "strong connection" and "fast separation". It is easy to have separation attitude deviation or incomplete separation. In addition, the joint lacks effective protection and buffer structure. It is easy to generate fatigue damage under aerodynamic heating and vibration impact, which shortens the service life. The residual parts after separation may become space debris, which does not conform to the development trend of green aerospace.

[0003] To achieve effective docking and separation of the fairing, designing a novel self-separating fairing is of particular importance. Utility Model Content

[0004] The purpose of this invention is to overcome the shortcomings of the prior art and provide a novel self-separating fairing.

[0005] This utility model provides a novel self-separating rectifier, comprising: a rectifier sheet, a magnetic pre-fixing structure, and a composite drive separation mechanism; the rectifier sheet includes at least a first half-rectifier sheet and a second half-rectifier sheet, which are assembled to form a complete rectifier; the magnetic pre-fixing structure includes a permanent magnet strip and an electromagnetic adsorption block; the permanent magnet strip is fixedly disposed at the joint between the first half-rectifier sheet and the second half-rectifier sheet, and the electromagnetic adsorption block is fixedly disposed at the joint between the second half-rectifier sheet and the first half-rectifier sheet; the electromagnetic adsorption block is energized and magnetically connected to the permanent magnet strip, thereby fixing the first half-rectifier sheet and the second half-rectifier sheet together; the composite drive separation mechanism is disposed between the first half-rectifier sheet and the second half-rectifier sheet, and is used to provide driving force to separate the first half-rectifier sheet and the second half-rectifier sheet.

[0006] According to one embodiment of the present invention, a split-type seam mechanism is further included; the split-type seam mechanism includes a female seam assembly and a female seam assembly; the female seam assembly includes a support plate disposed at the joint between the first half-rectifier fairing and the second half-rectifier fairing; the female seam assembly includes an abutment plate disposed at the joint between the second half-rectifier fairing and the first half-rectifier fairing; the support plate is used to abut the end face of the abutment plate having a connecting groove, and the abutment plate is embedded in the connecting groove so that the female seam assembly and the female seam assembly are connected.

[0007] According to one embodiment of the present invention, the support plate has an L-shaped cross-section in the direction perpendicular to the axial direction of the fairing, and the abutment plate has a shape adapted to the support plate.

[0008] According to one embodiment of the present invention, an elastic sealing skirt is provided at the joint between the abutment plate and the support plate near the outer side of the fairing; the elastic sealing skirt is interference-fitted with the support plate to seal the joint between the abutment plate and the support plate.

[0009] According to one embodiment of the present invention, the composite drive separation mechanism includes at least one set of ejection units; the ejection unit includes a fixed sleeve, a compression spring, and a guide push rod; the fixed sleeve is disposed on the first half-rectifier plate, and the opening of the fixed sleeve faces the second half-rectifier plate; one end of the guide push rod is disposed on the second half-rectifier plate, and the other end extends toward the fixed sleeve; the guide push rod is provided with a spring limiting plate; the compression spring is disposed in the fixed sleeve, and both ends of the compression spring are limited by the fixed sleeve and the spring limiting plate, respectively.

[0010] According to one embodiment of the present invention, multiple sets of the ejection units are arranged along the length direction of the joint between the first half-rectifier sheet and the second half-rectifier sheet.

[0011] According to one embodiment of the present invention, it further includes a fusible constraint component; the fusible constraint component is a rod-shaped structure; one end of the fusible constraint component is connected to the first semi-rectifier cover plate, and the other end is connected to the spring limiting plate.

[0012] According to one embodiment of the present invention, a strain buffer layer is provided between the first semi-rectifier shroud and the mother joint assembly; the strain buffer layer is honeycomb-shaped to buffer the compressive force between the first semi-rectifier shroud and the second semi-rectifier shroud.

[0013] According to one embodiment of the present invention, along the joint between the first half-rectifier shroud and the second half-rectifier shroud, rigid reinforcing blocks are provided at intervals between the first half-rectifier shroud and the female joint assembly to enhance its rigidity.

[0014] According to one embodiment of the present invention, the portion of the split-type seam mechanism facing the outside of the fairing is provided with a degradable protective layer.

[0015] According to this utility model, the novel self-separating rectifier can effectively improve the reliability of the connection of the rectifier plates in low-temperature environments through the non-rigid connection of the magnetic pre-fixed structure.

[0016] It should be understood that the above general description and the following specific embodiments are merely exemplary and illustrative, and do not limit the scope of the present invention. Attached Figure Description

[0017] The accompanying drawings are part of the specification of this utility model and illustrate exemplary embodiments of the utility model. The drawings, together with the description in the specification, are used to illustrate the principles of the utility model.

[0018] Figure 1 This is a schematic diagram of a novel self-separating fairing according to an embodiment of the present invention;

[0019] Figure 2 This is a cross-sectional view of a novel self-separating fairing according to an embodiment of the present invention;

[0020] Figure 3 yes Figure 2 Enlarged view of 'a' in the middle;

[0021] Figure 4 This is a schematic diagram of a split-type seam mechanism according to an embodiment of the present invention.

[0022] Explanation of reference numerals in the attached figures:

[0023] 1. Fairing plate; 2. Split-type seam mechanism; 3. Magnetic pre-fixing mechanism; 4. Composite drive separation mechanism; 5. Fusible constraint assembly; 11. First half-fairing plate; 12. Second half-fairing plate; 21. Female seam assembly; 22. Female seam assembly; 31. Permanent magnet strip; 32. Electromagnetic adsorption block; 41. Ejection unit; 211. Support plate; 212. Connecting groove; 221. Abutment plate; 222. Elastic sealing skirt; 411. Fixing sleeve; 412. Compression spring; 413. Guide push rod; 414. Spring limit plate. Detailed Implementation

[0024] The features and exemplary embodiments of various aspects of this utility model will be described in detail below. To make the objectives, technical solutions, and advantages of this utility model clearer, the following detailed description is provided in conjunction with the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only configured to explain this utility model and to exemplarily illustrate the principles of this utility model, and are not configured to limit this utility model. In addition, the structural components in the drawings are not necessarily drawn to scale. For example, the dimensions of some structural components or regions in the drawings may be enlarged for other structural components or regions to aid in the understanding of the embodiments of this utility model.

[0025] The directional terms used in the following description refer to the directions shown in the figures and are not intended to limit the specific structure of the embodiments of this utility model. In the description of this utility model, it should be noted that, unless otherwise stated, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0026] Furthermore, the terms "comprising," "including," "having," or any other variations thereof are intended to cover non-exclusive inclusion, such that a structure or component that includes a list of elements includes not only those elements but also other structural elements that are not expressly listed or inherent to the structure or component. Without further limitations, an element defined by the phrase "comprising..." does not exclude the presence of other identical elements in the article or apparatus that includes the element.

[0027] Spatial relation terms such as "below," "under," "under," "low," "above," "on," and "high" are used for descriptive convenience to explain the positioning of one element relative to a second element, indicating that these terms are intended to cover different orientations of the device, in addition to those different from those shown in the figure. Furthermore, phrases such as "one element on / below another element" can indicate that two elements are in direct contact, or that there are other elements between the two elements. In addition, terms such as "first" and "second" are also used to describe individual elements, areas, parts, etc., without specifically indicating order or sequence, and should not be considered restrictive. Similar terms are used throughout the description to represent similar elements.

[0028] In the following description of this utility model, the terms "rocket," "launch vehicle," "spacecraft," "space launch vehicle," or "missile" may be used in certain scenarios for ease of description only, and their connotations are not limited to the specific terms used. Generally, the rocket in this utility model includes space launch vehicles or launch vehicles used to launch satellites, spacecraft, or other probes, as well as various missiles, rockets, and other weapons used to carry payloads, and similar products capable of sending payloads into the air. Those skilled in the art, when interpreting the above specific terms, should not limit the rocket to only launch vehicles or missiles based on the specific terms used in the description, thereby narrowing the scope of protection of this utility model.

[0029] For those skilled in the art, this invention can be implemented without some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of the invention by illustrating examples.

[0030] Figure 1 This is a schematic diagram of a novel self-separating fairing according to an embodiment of the present invention; Figure 2 This is a cross-sectional view of a novel self-separating fairing according to an embodiment of the present invention; Figure 3 yes Figure 2 Enlarged view of 'a' in the middle; Figure 4 This is a schematic diagram of a split-type seam mechanism according to an embodiment of the present invention.

[0031] like Figures 1-3As shown, this utility model provides a novel self-separating rectifier, comprising: a rectifier plate 1, a magnetic pre-fixing structure 3, and a composite drive separation mechanism 4. The rectifier plate 1 includes at least a first half-rectifier plate 11 and a second half-rectifier plate 12, which are assembled to form a complete rectifier. The magnetic pre-fixing structure 3 includes a permanent magnet strip 31 and an electromagnetic adsorption block 32. The permanent magnet strip 31 is fixedly disposed at the junction of the first half-rectifier plate 11 and the second half-rectifier plate 12, and the electromagnetic adsorption block 32 is fixedly disposed at the junction of the second half-rectifier plate 12 and the first half-rectifier plate 11. When the electromagnetic adsorption block 32 is energized, it is fixedly connected to the permanent magnet strip 31 by magnetic force, thereby fixing the first half-rectifier plate 11 and the second half-rectifier plate 12 together. The composite drive separation mechanism 4 is disposed between the first half-rectifier shroud 11 and the second half-rectifier shroud 12. The composite drive separation mechanism 4 is used to provide driving force to separate the first half-rectifier shroud 11 and the second half-rectifier shroud 12.

[0032] The fairing provided in this embodiment achieves the connection between the first half-fairing plate 11 and the second half-fairing plate 12 through a non-rigid connection of a permanent magnet strip 31 with a magnetic pre-fixed structure and an electromagnetic adsorption block 32. This not only avoids stress concentration in traditional bolted connections but also compensates for thermal expansion and contraction through slight deformation during temperature changes, effectively improving the reliability of the connection in low-temperature environments. Furthermore, the fairing can reliably separate the two half-fairing plates by providing driving force through a composite drive separation mechanism 4. For example, the fairing plate 1 may include three or more fairing plates. For example, the first half-fairing plate 11 and the second half-fairing plate 12 may be symmetrically arranged. For example, the electromagnetic adsorption block 32 can be connected to the rocket's power system via wires.

[0033] like Figures 1-4 As shown, according to one embodiment of the present invention, in addition to the fairing plate 1, the magnetic pre-fixing structure 3, and the composite drive separation mechanism 4, the fairing also includes a split-type seam mechanism 2. The female seam assembly 21 includes a support plate 211. The support plate 211 is disposed at the joint between the first half-fairing plate 11 and the second half-fairing plate 12. The female seam assembly 22 includes an abutment plate 221. The abutment plate 221 is disposed at the joint between the second half-fairing plate 12 and the first half-fairing plate 11. The support plate 211 has a connecting groove 212 on its end face for engaging with the abutment plate 221. The abutment plate 221 is embedded in the connecting groove 212 to allow the female seam assembly 21 and the female seam assembly 22 to engage.

[0034] In this embodiment, the abutment plate 221 matches the connecting groove 212, ensuring a sealed connection between the female joint assembly 21 and the female joint assembly 22. The support plate 211 of the female joint assembly 21 of the fairing and the abutment plate 221 of the female joint assembly 22 form a nested guide structure, achieving a sealed connection between the female joint assembly 21 and the female joint assembly 22. For example, a permanent magnet strip 31 can be embedded in the support plate 211, and an electromagnetic adsorption block 32 can be embedded in the abutment plate 221.

[0035] According to one embodiment of the present invention, the support plate 211 has an L-shaped cross section perpendicular to the axial direction of the fairing, and the abutment plate 221 has a shape adapted to the support plate 211.

[0036] According to one embodiment of the present invention, an elastic sealing skirt 222 is provided at the joint between the abutment plate 221 and the support plate 211 near the outer side of the fairing. The elastic sealing skirt 222 is interference-fitted with the support plate 211 to seal the joint between the abutment plate 221 and the support plate 211.

[0037] In this embodiment, the interference fit between the elastic sealing skirt 222 and the support plate 211 can further improve the airtightness of the fairing joint and effectively block the intrusion of high-speed airflow into the interior of the fairing.

[0038] like Figure 2 As shown, according to one embodiment of the present invention, the composite drive separation mechanism 4 includes at least one set of ejection units 41. Each ejection unit 41 includes a fixed sleeve 411, a compression spring 412, and a guide push rod 413. The fixed sleeve 411 is disposed on the first semi-rectifier shroud 11, with its opening facing the second semi-rectifier shroud 12. One end of the guide push rod 413 is disposed on the second semi-rectifier shroud 12, and the other end extends into the fixed sleeve 411. The guide push rod 413 is provided with a spring limiting plate 414. The compression spring 412 is disposed in the fixed sleeve 411, and both ends of the compression spring 412 are limited by the fixed sleeve 411 and the spring limiting plate 414, respectively.

[0039] In this embodiment, for example, one end of the guide push rod 413 can be hinged to the second half-fairing plate 12. For example, the ejection unit 41 can be located near the top of the fairing plate 1 (i.e., away from the junction of the fairing and the rocket body). The ejection unit 41 can be located inside the fairing. For example, a set of ejection units 41 can be respectively located near the two joints of the first half-fairing plate 11 and the second half-fairing plate 12. For example, the compression spring 412 can be a high-strength compression spring. The length of the compression spring 412 in its natural state can be 1.8-2.2 times the length of the fixed sleeve 411, and its pre-compression amount is 1 / 2-2 / 3 of its free length.

[0040] The fairing's operation process is divided into two stages: the waiting-to-separate locked state and the active separation of the fairing.

[0041] When the first half-rectifier cover 11 and the second half-rectifier cover 12 are in the state of waiting to be separated and locked, the first half-rectifier cover 11 and the second half-rectifier cover 12 are connected through the female joint assembly 21 and the female joint assembly 22 of the split joint mechanism 2 (the abutment plate 221 of the female joint assembly 22 is embedded in the connecting groove 212 of the female joint assembly 21). The elastic sealing skirt 222 of the abutment plate 221 forms an interference fit with the support plate 211, realizing the sealing and preliminary mechanical positioning of the joint between the first half-rectifier cover 11 and the second half-rectifier cover 12. At the same time, the permanent magnet strip 31 embedded in the support plate 211 and the electromagnetic adsorption block 32 of the abutment plate 221 attract each other (the electromagnetic adsorption block 32 generates a strong magnetic force when energized, forming a stable magnetic attraction constraint with the permanent magnet strip 31), further strengthening the connection between the first half-rectifier cover 11 and the second half-rectifier cover 12. At this time, the high-strength compression spring 412 inside the fixed sleeve 411 is pre-compressed by the fixed sleeve 411 and the spring limiting plate 414 (for example, the pre-compression amount can be 1 / 2 to 2 / 3 of the free length), and the guide push rod 413 extends into the compression spring 412. In this state, the fairing remains closed and sealed, which can meet the aerodynamic protection requirements during flight.

[0042] Active execution of fairing separation: Upon receiving the fairing separation command, the electromagnetic adsorption block 32 is de-energized. For example, the residual magnetic force of the electromagnetic adsorption block 32 can drop to less than 1 / 5 of the magnetic force of the permanent magnet strip 31, at which point the constraint effect of the magnetic pre-fixed structure 3 is greatly weakened. The compression spring 412 of the ejection unit 41 releases the pre-compression force, pushing the guide push rod 413 away from the fixed sleeve 411. The guide push rod 413 applies a separation thrust to the second half-fairing plate 12 through the hinge point with the second half-fairing plate 12. Under the action of the thrust, the abutment plate 221 of the sub-joint assembly 22 slides along the connecting groove 212 of the female joint assembly 21, the elastic sealing skirt 222 disengages from the interference fit state, and the first half-fairing plate 11 separates from the second half-fairing plate 12.

[0043] The fairing's drive separation mechanism has a simple structure. By replacing traditional pyrotechnic components with a composite drive separation mechanism 4, material costs can be reduced, and there is no risk of explosive fragments, thus improving operational and separation safety.

[0044] According to one embodiment of the present invention, two or more sets of ejection units 41 can be provided along the length direction of the joint between the first half-rectifier 11 and the second half-rectifier 12.

[0045] like Figure 2As shown, according to one embodiment of the present invention, in addition to the fairing plate 1, the split-type seam mechanism 2, and the composite drive separation mechanism 4, the fairing also includes a fusible constraint assembly 5. The fusible constraint assembly 5 has a rod-shaped structure. One end of the fusible constraint assembly 5 is connected to the first half-fairing plate, and the other end is connected to the spring limiting plate 414.

[0046] In this embodiment, the ejection unit 41 is locked to the split-type seam mechanism 2 via the fusible constraint component 5.

[0047] For example, the fusible restraint assembly 5 can be a low-melting-point metal fusible wire (e.g., a lead-tin alloy wire). One end of the energized wire is wound around the metal fusible wire of the fusible restraint assembly 5, and the other end is connected to the rocket power system. When a separation command is received, the rocket power system supplies power to the energized wire, which in turn heats and melts the metal fusible wire of the fusible restraint assembly 5 to achieve unlocking. For example, the energized wire can be a thin copper core wire. In this embodiment, for example, the lead-tin alloy wire of the fusible restraint assembly 5 can reach its melting point and melt within 1-2 seconds. For example, the fusible restraint assembly 5 shares the same control circuit with the electromagnetic adsorption block 32 of the magnetic pre-fixed structure 3 to simplify the circuit.

[0048] According to one embodiment of the present invention, a strain buffer layer is provided between the first semi-rectifier shroud 11 and the female joint assembly 21. The strain buffer layer is honeycomb-shaped to buffer the compressive force between the first semi-rectifier shroud 11 and the second semi-rectifier shroud 12.

[0049] In this embodiment, for example, the strain buffer layer can be a honeycomb aluminum foil core material with a thickness of 5-8 mm. This strain buffer layer has the ability to absorb vibrations through the honeycomb structure.

[0050] According to one embodiment of the present invention, rigid reinforcing blocks are provided at intervals between the first half-rectifier 11 and the female joint assembly 21 along the butt joint of the first half-rectifier 11 and the second half-rectifier 12 to enhance its rigidity.

[0051] In this embodiment, the rigid reinforcing block can be set inside the strain buffer layer to ensure the strength of the joint, avoid excessive deformation of the strain buffer layer, improve the fatigue resistance of the overall structure, and extend the service life.

[0052] According to one embodiment of the present invention, the portion of the split-type seam mechanism 2 facing the outside of the fairing is provided with a degradable protective layer.

[0053] In this embodiment, the biodegradable protective layer can resist aerodynamic heating and particle erosion before the fairing separates during the initial stage of flight, protecting the split-type seam mechanism 2. After the fairing separates, the biodegradable protective layer can naturally degrade as it falls into the atmosphere, avoiding the generation of space debris.

[0054] For example, the biodegradable protective layer can be made of polycaprolactone-based composite material with a thickness of 2-4 mm, and can withstand temperatures from -50°C to 150°C, ensuring structural integrity in extreme environments.

[0055] The above embodiments of this utility model can be combined with each other and have corresponding technical effects.

[0056] The above are merely preferred embodiments of the present utility model and are not intended to limit the present utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model shall be included within the protection scope of the present utility model.

Claims

1. A novel self-separating fairing, characterized in that, include: fairing, magnetic pre-fixed structure and composite drive separation mechanism; The fairing includes at least a first half-fairing and a second half-fairing, and the first half-fairing and the second half-fairing are assembled to form a complete fairing. The magnetic pre-fixed structure includes a permanent magnet strip and an electromagnetic adsorption block; the permanent magnet strip is fixedly disposed at the joint between the first half-rectifier shroud and the second half-rectifier shroud, and the electromagnetic adsorption block is fixedly disposed at the joint between the second half-rectifier shroud and the first half-rectifier shroud; when the electromagnetic adsorption block is energized, it is fixedly connected to the permanent magnet strip by magnetic force, so that the first half-rectifier shroud and the second half-rectifier shroud are fixedly joined. The composite drive separation mechanism is disposed between the first half-rectifier shroud and the second half-rectifier shroud, and the composite drive separation mechanism is used to provide driving force to separate the first half-rectifier shroud and the second half-rectifier shroud.

2. The fairing according to claim 1, characterized in that, It also includes a split-type seam mechanism; the split-type seam mechanism includes a female seam assembly and a female seam assembly; the female seam assembly includes a support plate, which is disposed at the joint between the first half-rectifier fairing and the second half-rectifier fairing; the female seam assembly includes an abutment plate, which is disposed at the joint between the second half-rectifier fairing and the first half-rectifier fairing; the support plate is used to abut the end face of the abutment plate to form a connecting groove, and the abutment plate is embedded in the connecting groove so that the female seam assembly and the female seam assembly are connected.

3. The fairing according to claim 2, characterized in that, The support plate has an L-shaped cross-section perpendicular to the axial direction of the fairing, and the abutment plate has a shape adapted to the support plate.

4. The fairing according to claim 2, characterized in that, An elastic sealing skirt is provided at the joint between the abutment plate and the support plate near the outer side of the fairing; the elastic sealing skirt is interference-fitted with the support plate to seal the joint between the abutment plate and the support plate.

5. The fairing according to claim 1, characterized in that, The composite drive separation mechanism includes at least one set of ejection units; each ejection unit includes a fixed sleeve, a compression spring, and a guide push rod; the fixed sleeve is disposed on the first half-rectifier plate, and the opening of the fixed sleeve faces the second half-rectifier plate; one end of the guide push rod is disposed on the second half-rectifier plate, and the other end extends toward the fixed sleeve; the guide push rod is provided with a spring limiting plate; the compression spring is disposed in the fixed sleeve, and both ends of the compression spring are limited by the fixed sleeve and the spring limiting plate, respectively.

6. The fairing according to claim 5, characterized in that, Multiple sets of the ejection units are arranged along the length of the joint between the first half-rectifier and the second half-rectifier.

7. The fairing according to claim 5, characterized in that, It also includes a fusible constraint assembly; the fusible constraint assembly is a rod-shaped structure; one end of the fusible constraint assembly is connected to the first half-rectifier plate, and the other end is connected to the spring limiting plate.

8. The fairing of claim 2, wherein, A strain buffer layer is provided between the first half-rectifier shroud and the mother joint assembly; the strain buffer layer is honeycomb-shaped to buffer the compressive force between the first half-rectifier shroud and the second half-rectifier shroud.

9. The fairing of claim 2, wherein, Rigid reinforcing blocks are provided at intervals between the first half-rectifier shroud and the mother joint assembly along the joint between the first half-rectifier shroud and the second half-rectifier shroud to enhance its rigidity.

10. The fairing according to claim 2, characterized in that, The split-type seam mechanism has a biodegradable protective layer on the portion facing the outside of the fairing.

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