A tail reduction gearbox case and method of manufacturing the same, a tail reduction gearbox and an aircraft

Abstract

This application discloses a tail reducer housing, its manufacturing method, the tail reducer itself, and an aircraft. The tail reducer housing includes a frame, a main body, and a liner. The frame is made of metal and includes a frame connector and a frame main body. The frame connector is a cavity structure with openings at both ends; the frame main body is an annular structure surrounding the frame connector, and includes a first surface and a second surface, forming a cavity between the first and second surfaces. Each of the first and second surfaces has at least two first through holes; the main body is made of composite material and fills the cavity through the first through holes; the liner is made of metal and is a cavity structure with openings at both ends, and is embedded in the inner circumference of the frame connector.

Description

Technical Field

[0001] This application relates to aviation, and more specifically, to a casing for a tail gear reducer, a method for manufacturing the same, the tail gear reducer, and an aircraft. Background Technology

[0002] Data shows that for every 1% reduction in helicopter structural weight, aircraft performance can improve by 3% to 5%, increasing corresponding payload and maneuverability. Therefore, lightweighting is not only an important indicator of aircraft design advancement but also a key focus of research in aeronautical science both domestically and internationally. The tail gearbox housing is part of the helicopter's transmission system. The tail gearbox housing has a complex shape and structure, is subjected to diverse excitation sources, and experiences a wide range of vibration frequencies, making dynamic issues quite prominent.

[0003] The inventors of this application have discovered that the casing of the tail reducer has a complex shape and is subject to loads, requiring fatigue resistance, high temperature resistance, and oil resistance. It is mainly made of high-strength magnesium-aluminum alloy material through precision casting, which makes the casing of the tail reducer heavy and difficult to process, which is not conducive to the design of a lightweight transmission system. Summary of the Invention

[0004] According to one aspect of this application, a casing for a tail reducer is provided. The casing of the tail reducer includes a frame, a body, and a liner. The frame is made of metal and includes a frame connector and a frame body. The frame connector is a cavity structure with openings at both ends; the frame body is an annular structure surrounding the frame connector, and the frame body includes a first surface and a second surface, forming a cavity between the first surface and the second surface, and each of the first surface and the second surface is provided with at least two first through holes; the body is made of composite material and fills the cavity through the first through holes; the liner is made of metal and is a cavity structure with openings at both ends, and the liner is embedded in the inner periphery of the frame connector.

[0005] According to some embodiments of this application, a support portion is provided inside the main frame body. The support portion is made of metal and includes at least one first support portion and at least one second support portion. At least one first support portion is disposed on the outside of the frame connector, with one end fixedly disposed on a first surface of the main frame body and the other end fixedly disposed on a second surface of the main frame body. At least one second support portion is disposed on the first surface of the main frame body, with one end connected to the inner periphery of the main frame body and the other end connected to the outer periphery of the main frame body.

[0006] According to some embodiments of this application, the first through hole is a pull stud structure.

[0007] According to some embodiments of this application, at least two second through holes are provided on the outer periphery edge side of the skeleton body.

[0008] According to some embodiments of this application, the skeleton further includes a first channel and a first interface. One end of the first channel is connected to the outer periphery of the skeleton body, and the other end of the first channel is connected to the inner periphery of the skeleton body. The first interface is disposed on the edge side of the skeleton body.

[0009] According to another aspect of this application, this application provides a method for manufacturing a casing for a tail reducer, the method being used to manufacture the casing of the tail reducer as described above. The manufacturing method includes: manufacturing a skeleton using metal material through printing technology, wherein the skeleton includes a skeleton connector and a skeleton body, the skeleton connector being a cavity structure open at both ends, the skeleton body being an annular structure surrounding the skeleton connector, the skeleton body including a first surface and a second surface, a cavity forming between the first surface and the second surface, and each of the first surface and the second surface having at least two first through holes; filling the cavity with a composite material body through the first through holes using thermoplastic molding technology; and embedding a liner into the inner periphery of the skeleton connector, wherein the liner is a cavity structure open at both ends.

[0010] According to some embodiments of this application, a support portion is provided inside the main frame body. The support portion is made of metal and includes at least one first support portion and at least one second support portion. At least one first support portion is disposed on the outside of the frame connector, with one end fixedly disposed on a first surface of the main frame body and the other end fixedly disposed on a second surface of the main frame body. At least one second support portion is disposed on the first surface of the main frame body, with one end connected to the inner periphery of the main frame body and the other end connected to the outer periphery of the main frame body.

[0011] According to some embodiments of this application, the first through hole is a pull stud structure.

[0012] According to some embodiments of this application, at least two second through holes are provided on the outer periphery edge side of the skeleton body.

[0013] According to some embodiments of this application, after the skeleton is manufactured by printing metal materials based on printing technology as described above, the manufacturing method may further include: performing post-printing processing on the manufactured skeleton to determine whether the skeleton meets a preset target.

[0014] According to some embodiments of this application, after the step of embedding the liner into the inner periphery of the skeleton connector, the manufacturing method further includes: machining a first channel and a first interface on the outer periphery of the skeleton body based on machining technology.

[0015] According to one aspect of this application, a tail reducer is provided, the tail reducer including a housing as described above.

[0016] According to one aspect of this application, an aircraft is provided, the aircraft including a tail decelerator as described above.

[0017] Through the above technical solution, this application forms a cavity-structured skeleton by creating a cavity between the first and second surfaces of the skeleton body. This application also forms a filling space for the skeleton body by providing first through holes on both the first and second surfaces of the skeleton body, with these through holes communicating with the cavity. By filling the cavity and first through holes of the skeleton body with a composite material, this application, compared to a solid metal casing of the same volume, can reduce the weight of the casing while still meeting the rigidity and strength requirements, thereby ensuring the flight performance of the aircraft. Attached Figure Description

[0018] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0019] Figure 1 A schematic diagram of the casing of a tail reducer according to an embodiment of this application is shown.

[0020] Figure 2 A schematic cross-sectional view of the casing of a tail reducer according to an embodiment of this application is shown;

[0021] Figure 3 Another cross-sectional schematic diagram of the casing of a tail reducer according to an embodiment of this application is shown;

[0022] Figure 4 A schematic flowchart illustrating a method for manufacturing a casing of a tail reducer according to an embodiment of this application is shown.

[0023] Figure 5 Another schematic flowchart illustrating a method for manufacturing a casing of a tail reducer according to an embodiment of this application is shown.

[0024] Figure label:

[0025] The housing 100 of the tail reducer.

[0026] 1. Skeleton; 2. Main body; 3. Liner.

[0027] Frame body 11; frame connector 12; support part 13; first channel 14; first interface 15.

[0028] First surface 111; second surface 112; first through hole 113; second through hole 114.

[0029] First support part 131; Second support part 132. Detailed Implementation

[0030] Exemplary embodiments will now be described more fully with reference to the accompanying drawings. However, these exemplary embodiments can be implemented in many forms and should not be construed as limited to the embodiments set forth herein; rather, they are provided so that this application will be thorough and complete, and will fully convey the concept of the exemplary embodiments to those skilled in the art. The same reference numerals in the drawings denote the same or similar parts, and therefore repeated descriptions of them will be omitted.

[0031] The described features, structures, or characteristics can be combined in any suitable manner in one or more embodiments. Numerous specific details are provided in the following description to give a full understanding of embodiments of this disclosure. However, those skilled in the art will recognize that the technical solutions of this disclosure can be practiced without one or more of these specific details, or other methods, components, materials, devices, etc. In these cases, well-known structures, methods, devices, implementations, materials, or operations will not be shown or described in detail.

[0032] Furthermore, the terms “comprising” and “having”, and any variations thereof, are intended to cover non-exclusive inclusion. For example, a process, method, system, product, or apparatus that includes a series of steps or units is not limited to the steps or units listed, but may optionally include steps or units not listed, or may optionally include other steps or units inherent to such process, method, product, or apparatus.

[0033] The terms "first," "second," etc., in the specification, claims, and accompanying drawings of this application are used to distinguish different objects, not to describe a specific order.

[0034] The technical solutions of this application will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some, not all, of the embodiments of this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application.

[0035] According to one aspect of this application, a housing 100 for a tail reducer is provided. See also... Figure 1 The tail reducer housing 100 includes a frame 1, a main body 2, and a liner 3.

[0036] According to the example embodiment, the skeleton 1 is made of metal.

[0037] For example, the skeleton 1 can be made of high-strength aluminum alloy or titanium alloy.

[0038] See Figure 1 and Figure 2 The skeleton 1 includes a skeleton connector 12 and a skeleton body 11. The skeleton connector 12 is a hollow structure with openings at both ends. For example, the skeleton connector 12 can be a cylindrical structure.

[0039] The main frame 11 is a ring structure, which surrounds the frame connector 12. The inner circumference of the main frame 11 fits against the outer circumference of the frame connector 12.

[0040] The skeleton body 11 includes a first surface 111 and a second surface 112. The first surface 111 can be an upper surface formed between the inner periphery and the outer periphery of the skeleton body 11. The second surface 112 can be a lower surface formed between the inner periphery and the outer periphery of the skeleton body 11. Both the first surface 111 and the second surface 112 can be curved surfaces.

[0041] A cavity is formed between the first surface 111 and the second surface 112, and both the first surface 111 and the second surface 112 are provided with at least two first through holes 113.

[0042] For example, see Figure 1 Both the first surface 111 and the second surface 112 are provided with a plurality of first through holes 113. Each first through hole 113 communicates with the cavity, so that the frame body 11 forms a honeycomb hollow structure. The casing 100 of the tail reducer can also dissipate heat through the first through holes 113.

[0043] According to the example embodiment, the main body 2 is a composite material.

[0044] For example, composite materials such as carbon fiber materials (polyphenylene sulfide (PPS), epoxy resin (EP), polyetheretherketone (PEEK), polytetrafluoroethylene (PTFE), poly(methyl methacrylate) (PMMA), carbon nanotubes (CNT), carbon materials, graphene fiber, graphite materials, etc.) have good designability and corrosion resistance, long fatigue life, and resistance to ballistic damage.

[0045] The main body 2 is filled into the cavity through the first through hole 113. Since the first through hole 113 is connected to the cavity, the main body 2 is also filled into each of the first through holes 113, and condenses on the surface of the first through hole 113 to form a condensed layer.

[0046] Since the density of composite materials is typically 0.5 to 0.3 times that of metal materials, using the composite material body 2 to fill the cavity of the skeleton 1 can reduce the weight of the tail reducer casing 100 compared to the solid structure of the tail reducer casing made of the same volume of metal materials.

[0047] According to the example embodiment, the liner 3 is made of a metallic material (such as bearing steel) and has a hollow structure with openings at both ends. The liner 3 is embedded in the inner circumference of the frame connector 12 so that the outer circumference of the liner 3 fits against the inner circumference of the frame connector 12. The liner 3 can be used to connect the frame 1 to the external bearing so that the housing 100 of the tail reducer can be mounted on external equipment (such as an engine).

[0048] According to the above embodiments, this application forms a cavity-structured skeleton 1 by creating a cavity between the first surface 111 and the second surface 112 of the skeleton body 11. This application provides first through holes 113 on both the first surface 111 and the second surface 112 of the skeleton body 11, and these first through holes 113 communicate with the cavity, forming a filling space for the skeleton body 11. By filling the cavity and first through holes 113 of the skeleton body 11 with the composite material body 2, this application, compared to a solid metal casing of the same volume, can reduce the weight of the tail gearbox casing 100 while still meeting the rigidity and strength requirements of the tail gearbox casing 100, thereby ensuring the flight performance of the aircraft.

[0049] Optionally, see Figure 2 The main body 11 of the skeleton is provided with a support part 13. The support part 13 is made of metal and includes at least one first support part 131 and at least one second support part 132.

[0050] According to the example embodiment, at least one first support portion 131 is disposed on the outside of the skeleton connector 12. One end of the first support portion 131 is fixedly disposed on the first surface 111 of the skeleton body 11, and the other end of the first support portion 131 is fixedly disposed on the second surface 112 of the skeleton body 11. Multiple first support portions 131 can be disposed around the outer periphery of the skeleton connector 12 to improve the vertical deformation resistance of the skeleton body 11.

[0051] At least one second support portion 132 is disposed on the first surface 111 of the frame body 11. One end of the second support portion 132 is connected to the inner periphery of the frame body 11, and the other end of the second support portion 132 is connected to the outer periphery of the frame body 11. Multiple second support portions 132 can be disposed around the outer periphery of the frame connector 12 to improve the horizontal deformation resistance of the frame body 11.

[0052] See Figure 3The support part 13 can be in the shape of "I". The "I" shape can not only improve the deformation resistance of the skeleton 1, but also take advantage of the high flexibility of 3D printing technology.

[0053] Through the above embodiments, by providing the first support portion 131 and the second support portion 132, this application can improve the deformation resistance of the frame 1, thereby improving the deformation resistance of the casing 100 of the tail reducer.

[0054] Optionally, the first through hole 113 can be a rivet structure. The rivet structure can improve the strength of the contact surface between the composite material and the metal material, prevent the two materials from separating, and make it less likely for the composite material body 2 to detach from the skeleton body 11.

[0055] Optionally, see Figure 1 At least two second through holes 114 are provided on the outer periphery edge side of the frame body 11. The second through holes 114 are connection holes between the frame body 11 and external equipment (such as an engine). The housing 100 of the tail reducer can be fixed to the external equipment by passing screws through the second through holes 114.

[0056] Optionally, see Figure 2 The frame 1 also includes a first channel 14 and a first interface 15. One end of the first channel 14 is connected to the outer periphery of the frame body 11, and the other end of the first channel 14 is connected to the inner periphery of the frame body 11. The first channel 14 can be a channel to guide the flow path and flow direction of lubricating oil in the casing 100 of the tail reducer, so that the lubricating oil can flow fully in the casing 100 of the tail reducer during use.

[0057] The first interface 15 can be the interface for connecting the housing 100 of the tail reducer to external equipment (such as an engine). The first interface 15 is located on the edge side of the frame body 11, and the cross-section of the first interface 15 can be L-shaped to better fit the connection with external equipment (such as an engine).

[0058] Through the above embodiments, the weight of the tail reducer casing provided in this application can be reduced by 10%-17% compared to the magnesium-aluminum alloy tail reducer casing 100.

[0059] According to another aspect of this application, this application also provides a method 2000 for manufacturing a housing of a tail reducer. The manufacturing method 2000 is used to manufacture the housing 100 of the tail reducer as described above.

[0060] According to the example embodiment, see Figure 4 The manufacturing method includes steps S210-S230.

[0061] In step S210, the skeleton 1 is manufactured using metal materials through printing technology. The skeleton 1 includes a skeleton connector 12 and a skeleton body 11.

[0062] According to the example embodiment, the printing technology can be 3D printing (Three Dimensions Printing). The skeleton 1 can be made of high-strength aluminum alloy.

[0063] The skeleton 1 includes a skeleton connector 12 and a skeleton body 11. The skeleton connector 12 is a hollow structure with openings at both ends. For example, the skeleton connector 12 can be a cylindrical structure.

[0064] The main frame 11 is a ring structure, which surrounds the frame connector 12. The inner circumference of the main frame 11 fits against the outer circumference of the frame connector 12.

[0065] The skeleton body 11 includes a first surface 111 and a second surface 112. The first surface 111 can be an upper surface formed between the inner periphery and the outer periphery of the skeleton body 11. The second surface 112 can be a lower surface formed between the inner periphery and the outer periphery of the skeleton body 11. Both the first surface 111 and the second surface 112 can be curved surfaces.

[0066] A cavity is formed between the first surface 111 and the second surface 112, and both the first surface 111 and the second surface 112 are provided with at least two first through holes 113.

[0067] For example, both the first surface 111 and the second surface 112 are provided with a plurality of first through holes 113. Each first through hole 113 communicates with the cavity, so that the frame body 11 forms a honeycomb hollow structure. The casing 100 of the tail reducer can also dissipate heat through the first through holes 113. By printing the frame 1 using 3D printing technology, the first through holes 113 and the cavity can be directly printed.

[0068] In step S220, the main body 2 of the composite material is filled into the cavity through the first through hole 113 based on thermoplastic molding technology.

[0069] For example, the composite material can be a thermoplastic composite material, such as carbon fiber, polyphenylene sulfide (PPS), epoxy resin (EP), polyetheretherketone (PEEK), polytetrafluoroethylene (PTFE), polymethyl methacrylate (PMMA), carbon nanotubes (CNT), carbon materials, graphene fiber, graphite, etc. Composite materials have advantages such as excellent designability and corrosion resistance, long fatigue life, and resistance to ballistic impact damage.

[0070] The main body 2 is filled into the cavity through the first through hole 113 using thermoplastic molding technology. Since the first through hole 113 is connected to the cavity, the main body 2 is also filled into each first through hole 113, and solidification occurs on the surface of the first through hole 113 to form a solidified layer.

[0071] Since the density of composite materials is typically 0.5 to 0.3 times that of metal materials, using the composite material body 2 to fill the cavity of the skeleton 1 can reduce the weight of the tail reducer casing 100 compared to a solid metal casing of the same volume.

[0072] In step S230, the liner 3 is embedded in the inner periphery of the skeleton connector 12, wherein the liner 3 is a cavity structure with openings at both ends.

[0073] According to the example embodiment, the liner 3 can be manufactured based on machining technology or 3D printing technology.

[0074] The liner 3 is made of a metallic material (such as bearing steel) and has a hollow structure with openings at both ends. The liner 3 is embedded in the inner circumference of the frame connector 12 so that the outer circumference of the liner 3 fits snugly against the inner circumference of the frame connector 12. The liner 3 can be used to connect the frame 1 to the external bearing so that the housing 100 of the tail reducer can be mounted on external equipment (such as an engine).

[0075] According to the above embodiments, this application forms a cavity-structured skeleton 1 by creating a cavity between the first surface 111 and the second surface 112 of the skeleton body 11. This application provides first through holes 113 on both the first surface 111 and the second surface 112 of the skeleton body 11, and these first through holes 113 communicate with the cavity, forming a filling space for the skeleton body 11. By filling the cavity and first through holes 113 of the skeleton body 11 with the composite material body 2, this application, compared to a solid metal casing of the same volume, can reduce the weight of the tail gearbox 100 while still meeting the rigidity and strength requirements of the tail gearbox casing 100, thereby ensuring the flight performance of the aircraft.

[0076] Optionally, in step S210, a support portion 13 can also be printed inside the skeleton body 11 using 3D printing technology. The support portion 13 is made of metal and is manufactured using 3D printing technology. The axial and radial parameters of the support portion 13 can be set according to the strength requirements of the tail reducer's casing 100.

[0077] The support portion 13 includes at least one first support portion 131 and at least one second support portion 132.

[0078] According to the example embodiment, at least one first support portion 131 is disposed on the outside of the skeleton connector 12. One end of the first support portion 131 is fixedly disposed on the first surface 111 of the skeleton body 11, and the other end of the first support portion 131 is fixedly disposed on the second surface 112 of the skeleton body 11. Multiple first support portions 131 can be disposed around the outer periphery of the skeleton connector 12 to improve the vertical deformation resistance of the skeleton body 11.

[0079] At least one second support portion 132 is disposed on the first surface 111 of the frame body 11. One end of the second support portion 132 is connected to the inner periphery of the frame body 11, and the other end of the second support portion 132 is connected to the outer periphery of the frame body 11. Multiple second support portions 132 can be disposed around the outer periphery of the frame connector 12 to improve the horizontal deformation resistance of the frame body 11.

[0080] Through the above embodiments, by providing the first support part 131 and the second support part 132, this application can improve the deformation resistance of the frame 1, thereby improving the rigidity of the casing 100 of the tail reducer.

[0081] Optionally, the first through hole 113 can be a rivet structure. The rivet structure can improve the strength of the contact surface between the composite material and the metal material, prevent the two materials from separating, and make it less likely for the composite material body 2 to detach from the skeleton body 11.

[0082] Optionally, see Figure 5The manufacturing method 2000 may also include steps S211 and S240.

[0083] In step S211, the printed skeleton 1 is subjected to post-printing processing to determine whether the skeleton 1 meets the preset target.

[0084] According to the example embodiment, the preset target can be the performance requirements of the frame 1 set to meet the flight specifications of the aircraft. For example, the preset target may include the performance requirements of the frame 1, appearance requirements, etc.

[0085] According to an example embodiment, post-printing processing may include heat treatment, support removal and sanding, appearance quality inspection (fluorescence detection) and internal quality inspection (X-ray or industrial CT).

[0086] For example, heat treatment can be stress-relieving annealing of the skeleton 1 at 300℃-350℃ for 2h-4h.

[0087] The removal and polishing can be performed using various fitter tools (such as rubber mallets, iron hammers, pneumatic impact drills, sanders, straight grinders, angle grinders, etc., which have a large removal capacity, and can be combined with saw blades, hand pliers, sandpaper, etc.) to remove the solid and block supports of the frame 1, until all supports of the frame 1 are removed. Polishing tools (such as white corundum grinding heads, paper belt wheels, and sandpaper wheels) can also be used to polish the remaining block support roots and solid support residues on the support surfaces of the frame 1 until the support surfaces of the frame 1 are smooth and consistent with the non-support surfaces.

[0088] Fluorescence testing can be used to perform 100% fluorescence penetrant testing on skeleton 1. Fluorescence penetrant testing can be performed according to GJB2367A-2005 to ensure that all surfaces of skeleton 1 are free from defects such as cracks, folds, inclusions, looseness, pores, cold shuts and oxide scars that are visible to the naked eye.

[0089] The internal quality of the parts can be inspected using X-rays or industrial computed tomography (CT) to examine the internal quality of the skeleton 1. The inspection standard for X-rays can be implemented according to GJB 1187A-2019, and the inspection standard for industrial CT can be implemented according to GJB 5312-2004.

[0090] Through the above post-printing processing, it can be determined that the printed skeleton 1 meets the preset target.

[0091] In step S240, the first channel 14 and the first interface 15 are machined on the outer periphery of the skeleton body 11 based on machining technology.

[0092] According to the example embodiment, one end of the first channel 14 is connected to the outer periphery of the frame body 11, and the other end of the first channel 14 is connected to the inner periphery of the frame body 11. The first channel 14 can be a channel that guides the flow path and flow direction of lubricating oil in the casing 100 of the tail reducer, so that the lubricating oil can flow fully in the casing 100 of the tail reducer during use.

[0093] The first interface 15 can be the interface for connecting the tail reducer housing 100 to external equipment (such as an engine). The first interface 15 is located on the edge side of the frame body 11, and the cross-section of the first interface 15 can be L-shaped to make the connection with external equipment (such as an engine) more secure.

[0094] Through the above embodiments, the tail reducer housing manufactured by the manufacturing method of the tail reducer housing provided in this application can reduce the weight of the tail reducer housing by 10%-17% compared to the housing of the magnesium-aluminum alloy tail reducer.

[0095] Optionally, manufacturing method 2000 can also be applied to the main structural and mechanical components of an aircraft, such as the fuselage, tail cone, rotor blades, drive shaft, and gears. The device can be...

[0096] According to one aspect of this application, a tail gear reducer is provided, which includes a housing 100 as described above. The tail gear reducer can be installed on helicopters, missile rudders, missile trailers, etc.

[0097] According to one aspect of this application, an aircraft is provided, which includes a tail gear reducer as described above. The aircraft may be a helicopter.

[0098] Finally, it should be noted that the above description is merely a preferred embodiment of this application and is not intended to limit this application. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions of the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this application should be included within the protection scope of this application.

Claims

1. A housing for a tail reducer, characterized in that, The casing includes: The skeleton, made of metal, includes: The skeleton connector is a hollow structure with openings at both ends; The main body of the skeleton is a ring structure, which surrounds the skeleton connector. The main body of the skeleton includes a first surface and a second surface, and a cavity is formed between the first surface and the second surface. Both the first surface and the second surface are provided with at least two first through holes. The main body is made of composite material, and the main body is filled into the cavity through the first through hole; The liner is made of metal and has a hollow structure with openings at both ends. The liner is embedded in the inner circumference of the skeleton connector.

2. The casing according to claim 1, characterized in that, The main frame body has an internal support section, which is made of metal and includes: At least one first support portion is disposed outside the skeleton connector, one end of the first support portion is fixedly disposed on the first surface of the skeleton body, and the other end of the first support portion is fixedly disposed on the second surface of the skeleton body; At least one second support portion is disposed on the first surface of the skeleton body, one end of the second support portion is connected to the inner periphery of the skeleton body, and the other end of the second support portion is connected to the outer periphery of the skeleton body.

3. The casing according to claim 1, characterized in that, The first through hole is a pull stud structure.

4. The casing according to claim 1, characterized in that, At least two second through holes are provided on the outer periphery edge side of the main skeleton body.

5. The casing according to claim 1, characterized in that, The skeleton also includes: The first channel is connected at one end to the outer periphery of the main skeleton body and at the other end to the inner periphery of the main skeleton body. The first interface is located on the edge side of the main skeleton body.

6. A method for manufacturing the casing of a tail reducer, characterized in that, The manufacturing method is used to manufacture the casing of the tail reducer as described in any one of claims 1-5, the manufacturing method comprising: A skeleton is manufactured using metal materials based on printing technology. The skeleton includes a skeleton connector and a skeleton body. The skeleton connector is a cavity structure with openings at both ends. The skeleton body is a ring structure that surrounds the skeleton connector. The skeleton body includes a first surface and a second surface, and a cavity is formed between the first surface and the second surface. Both the first surface and the second surface are provided with at least two first through holes. The composite material body is filled into the cavity through the first through hole using thermoplastic molding technology; The liner is embedded in the inner circumference of the skeleton connector, wherein the liner is a cavity structure with openings at both ends.

7. The manufacturing method according to claim 6, characterized in that, The main frame body has an internal support section, which is made of metal and includes: At least one first support portion is disposed outside the skeleton connector, one end of the first support portion is fixedly disposed on the first surface of the skeleton body, and the other end of the first support portion is fixedly disposed on the second surface of the skeleton body; At least one second support portion is disposed on the first surface of the skeleton body, one end of the second support portion is connected to the inner periphery of the skeleton body, and the other end of the second support portion is connected to the outer periphery of the skeleton body.

8. The manufacturing method according to claim 6, characterized in that, The first through hole is a pull stud structure.

9. The manufacturing method according to claim 6, characterized in that, At least two second through holes are provided on the outer periphery edge side of the main skeleton body.

10. The manufacturing method according to claim 6, characterized in that, After the skeleton is manufactured using metal materials based on printing technology, the manufacturing method further includes: The printed skeleton is then subjected to post-printing processing to determine whether it meets the preset target.

11. The manufacturing method according to claim 6, characterized in that, After the liner is fitted into the inner periphery of the skeleton connector, the manufacturing method further includes: The first channel and the first interface are machined on the outer periphery of the main skeleton body using machining technology.

12. A tail reducer, characterized in that, The tail reducer includes a housing as described in any one of claims 1-5.

13. An aircraft, characterized in that, The aircraft includes the tail decelerator as described in claim 11.

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