A cross-rotor unmanned helicopter and its fairing assembly

Abstract

This application relates to a cross-rotor unmanned helicopter and its fairing assembly. The cross-rotor unmanned helicopter includes a fuselage, and the fairing assembly includes a fairing body and a horizontal stabilizer and a vertical stabilizer separately disposed from the fairing body. The rear end and the rear bottom side of the fairing body are open structures, allowing the fairing body to cover the nose of the fuselage. The open structure allows the rear part of the fuselage to be exposed outside the fairing body. The horizontal stabilizer and the vertical stabilizer are respectively fixed to the exposed parts of the fuselage. The fairing body includes a first fairing body and a second fairing body, respectively fixed to the fuselage. The second fairing body is detachably connected to the upper rear end of the first fairing body via a connector. This fairing assembly can reduce the overall weight of the unmanned helicopter, facilitating lightweight design, while also improving the maintenance efficiency and simplifying operation.

Description

Technical Field

[0001] This application relates to the field of unmanned helicopter technology, and in particular to a cross-rotor unmanned helicopter and its fairing assembly. Background Technology

[0002] The fairing is an essential component of unmanned helicopters. It is installed on the outside of the fuselage and provides protection for the internal components. However, in the current technology, the overall weight of the fairing of unmanned helicopters is relatively large, which is not conducive to the lightweighting of unmanned helicopters. At the same time, when an unmanned helicopter malfunctions and needs to be repaired, the operation of disassembling the fairing is relatively complicated and the repair efficiency is low.

[0003] How to reduce the overall weight of unmanned helicopters to achieve lightweighting, while improving maintenance efficiency and simplifying operation, is a technical problem that needs to be solved by those skilled in the art. Summary of the Invention

[0004] The purpose of this application is to provide a cross-rotor unmanned helicopter and its fairing assembly, which can reduce the overall weight of the unmanned helicopter, facilitate lightweighting, improve the maintenance efficiency of the unmanned helicopter, and simplify operation.

[0005] To address the aforementioned technical problems, this application provides a fairing assembly for a cross-rotor unmanned helicopter. The cross-rotor unmanned helicopter includes a fuselage, and the fairing assembly includes a fairing body and a horizontal tail and a vertical tail separately disposed from the fairing body. The rear end and the rear bottom side of the fairing body are open structures, allowing the fairing body to cover the head of the fuselage. The open structure allows the rear part of the fuselage to be exposed outside the fairing body. The horizontal tail and the vertical tail are respectively fixed to the exposed parts of the fuselage. The fairing body includes a first fairing body and a second fairing body respectively fixed to the fuselage. The second fairing body is detachably connected to the upper rear end of the first fairing body via a connector. In the connected state, the outer surface of the rear end of the first fairing body and the outer surface of the front end of the second fairing body smoothly transition. A through hole can be formed between the rear edge of the first fairing body and the front edge of the second fairing body, and the through hole is used for the rotor shaft of the cross-rotor unmanned helicopter to pass through.

[0006] The canopy can be fixed to the fuselage and covers the outside of the nose of the fuselage to protect the engine and other components. The canopy does not completely cover the fuselage, but covers the front windward part and important components. The rear of the fuselage extends out of the canopy through an open structure and is exposed. The horizontal tail and vertical tail are fixed to the exposed parts of the fuselage. In this way, the overall volume of the canopy can be reduced, thereby effectively reducing the overall weight of the cross-rotor unmanned helicopter, which is conducive to achieving lightweighting, while also saving costs and improving economic efficiency.

[0007] The first and second covers are detachably connected, and each is individually fixed to the fuselage. Therefore, when a part of the fuselage malfunctions and requires repair, if the area to be repaired is at an open section of the cover, neither the first nor the second cover needs to be disassembled; repair can be performed directly through the open section. If the cover interferes with the repair location, either the first or second cover can be disassembled accordingly. After the repair is completed, the disassembled parts can be reinstalled. In other words, when repairing the fuselage, the need to remove the cover or only a portion of it can be removed depending on the specific location requiring repair, eliminating the need to disassemble the entire cover each time. This provides good flexibility, effectively improves repair efficiency, and simplifies operations.

[0008] The cover is separated from the flat tail and the vertical tail. Therefore, the disassembly and assembly of the cover, the flat tail, and the vertical tail do not affect each other. Thus, when the flat tail or the vertical tail needs to be disassembled and repaired, only the flat tail or the vertical tail needs to be disassembled and assembled separately, without disassembling the cover, which is very flexible.

[0009] Optionally, the rear end face of the first cover is further provided with a first positioning structure, and the front end face of the second cover is further provided with a second positioning structure. The first cover and the second cover can be positioned by the cooperation of the first positioning structure and the second positioning structure, and are connected by the connector.

[0010] Optionally, the first positioning structure is a positioning protrusion and the second positioning structure is a positioning hole; or, the first positioning structure is a positioning hole and the second positioning structure is a positioning protrusion.

[0011] Optionally, the rear edge of the first cover is provided with a first flange structure, and the first positioning structure is disposed on the first flange structure; the front edge of the second cover is provided with a second flange structure, and the second positioning structure is disposed on the second flange structure.

[0012] Optionally, the upper part of the first cover is also provided with a ventilation grille, through which air can enter the cover and flow out through the opening structure.

[0013] Optionally, the horizontal tail section includes a first fixing member and two horizontal tails symmetrically arranged about the first fixing member, the first fixing member being able to be fixed to the fuselage; the horizontal tail includes a horizontal tail frame and a horizontal tail panel, the horizontal tail panel being fixed to the outside of the horizontal tail frame, the horizontal tail frame being fixed to the first fixing member; the horizontal tail frame includes at least two parallel support beams and at least two parallel tubular beams, the support beams being fixed to each of the tubular beams respectively.

[0014] Optionally, the tube beam is a carbon fiber tube;

[0015] And / or, the supporting beam is an aluminum alloy beam;

[0016] And / or, the material of the flat-tail panel is glass fiber and aramid honeycomb core;

[0017] And / or, the gap between the tailstock frame and the tailstock panel is filled with foam.

[0018] Optionally, there are two tube beams, namely a first tube beam and a second tube beam, the diameter of the first tube beam is the same as the diameter of the second tube beam; the first tube beam is arranged at the maximum thickness of the airfoil of the horizontal stabilizer, and the second tube beam is arranged in the chord region of % to % of the chord.

[0019] Optionally, the vertical tail section includes an upper vertical tail and a lower vertical tail, and a second fixing member connecting the upper vertical tail and the lower vertical tail, the second fixing member being able to be fixed to the fuselage; the upper vertical tail includes an upper vertical tail frame and an upper vertical tail panel, the upper vertical tail frame including a first longitudinal beam and at least two first transverse ribs, the first longitudinal beam and the first transverse ribs being fixed, the upper vertical tail panel being disposed on the outside of the upper vertical tail frame; the lower vertical tail includes a lower vertical tail frame and a lower vertical tail panel, the lower vertical tail frame including a second longitudinal beam and at least two second transverse ribs, the second longitudinal beam and the second transverse ribs being fixed, the lower vertical tail panel being disposed on the outside of the lower vertical tail frame; the upper vertical tail frame and the lower vertical tail frame are respectively fixed to the second fixing member.

[0020] Optionally, the first longitudinal beam and / or the second longitudinal beam are aluminum square tube profiles.

[0021] This application also provides a cross-rotor unmanned helicopter, including a fuselage and a fairing assembly as described above.

[0022] The cross-rotor unmanned helicopter with the fairing assembly described above has similar technical effects to the fairing assembly described above, and will not be described in detail here for the sake of brevity. Attached Figure Description

[0023] Figure 1This is a schematic diagram of the fairing assembly of the cross-rotor unmanned helicopter provided in the embodiments of this application;

[0024] Figure 2 yes Figure 1 Schematic diagram of the structure of the inner cover;

[0025] Figure 3 yes Figure 2 Enlarged view of A in the middle;

[0026] Figure 4 yes Figure 1 A schematic diagram of the structure of the first enclosure;

[0027] Figure 5 yes Figure 4 A magnified view of the rear edge of the first enclosure.

[0028] Figure 6 yes Figure 1 A schematic diagram of the structure of the second cover;

[0029] Figure 7 yes Figure 1 A schematic diagram of the structure of the two flat tails at the mid-tail section;

[0030] Figure 8 yes Figure 1 Schematic diagram of the upper mid-tail structure;

[0031] Figure 9 yes Figure 1 A schematic diagram of the mid-to-lower drooping tail structure.

[0032] Appendix Figures 1-9 The reference numerals in the attached figures are explained as follows:

[0033] 1-Cover body, 11-First cover body, 111-First notch, 112-First positioning structure, 113-First flange structure, 114-Ventilation grille, 12-Second cover body, 121-Second notch, 122-Second positioning structure, 123-Second flange structure, 13-Connector, 14-Through hole, 15-Opening structure;

[0034] 2-Flat tail section, 21-First fixing component, 22-Flat tail, 23-Flat tail panel, 24-Support beam, 25-Pipe beam, 251-First pipe beam, 252-Second pipe beam, 26-Intermediate component;

[0035] 3-Vertical tail, 31-Second fixing member, 32-Upper vertical tail, 321-First longitudinal beam, 322-First transverse rib, 323-Upper vertical tail panel, 33-Lower vertical tail, 331-Second longitudinal beam, 332-Second transverse rib, 333-Lower vertical tail panel. Detailed Implementation

[0036] To enable those skilled in the art to better understand the technical solutions of this application, the application will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0037] This application provides a cross-rotor unmanned helicopter and its fairing assembly, wherein the cross-rotor unmanned helicopter includes a fuselage and a fairing assembly, such as... Figure 1 As shown, the fairing assembly includes a fairing body 1, a horizontal stabilizer 2, and a vertical stabilizer 3, as... Figure 2 As shown, the rear end and the rear bottom side of the cover 1 are open structures 15. The cover 1 can be fixed to the fuselage and cover the outside of the head of the fuselage, while the rear part of the fuselage can extend out of the open structure 15 and be exposed outside the cover 1. The horizontal tail 2 and the vertical tail 3 are fixed to the exposed part of the fuselage respectively. The horizontal tail 2 and the vertical tail 3 are located behind the cover 1 and are separately set from the cover 1, that is, the cover 1 covers the front end of the fuselage, and the horizontal tail 2 and the vertical tail 3 are fixed to the rear part of the fuselage.

[0038] The canopy 1 can be fixed to the fuselage and cover the outside of the fuselage head to protect the engine and other components of the fuselage. The canopy 1 does not completely cover the fuselage, but covers the front windward part and important components. The rear of the fuselage extends out of the canopy 1. In this way, the overall volume of the canopy 1 can be reduced, thereby effectively reducing the overall weight of the cross-rotor unmanned helicopter, which is conducive to achieving lightweighting, while also saving costs and improving economic efficiency.

[0039] like Figure 1 and Figure 2 As shown, the cover 1 includes two parts: a first cover 11 and a second cover 12. These two parts can be fixed to the fuselage (e.g., by bolts). Both the first cover 11 and the second cover 12 are symmetrical structures, specifically arranged symmetrically along the front-rear axis of the fuselage. The first cover 11 is located at the front, and the second cover 12 is located at the rear. Specifically, the front end of the second cover 12 is detachably connected to the upper rear end of the first cover 11 via a connector 13. Furthermore, when the first cover 11 and the second cover 12 are connected via the connector 13, the outer surface of the rear end of the first cover 11 and the outer surface of the front end of the second cover 12 smoothly transition (e.g., ...). Figure 3 As shown in the diagram, at the connection between the first cover 11 and the second cover 12, no end face of the cover 1 is exposed, so that when the wind flows along the outer surface of the first cover 11 to the outer surface of the second cover 12, the wind resistance will not be increased due to the obstruction of the exposed end face.

[0040] The fairing assembly has a streamlined curved surface structure, which can effectively reduce wind resistance during the flight of the unmanned helicopter. The sides of the fairing 1 need to have a streamlined shape, which is generated by lofting several trapezoids with rounded corners and narrower bottoms. At the same time, the rear end and the bottom rear side of the fairing 1 are set as open structures 15, and the fairing 1 is reasonably divided into a first fairing 11 and a second fairing 12 that can be detachably connected.

[0041] like Figure 4 As shown, the rear edge of the first cover 11 has a first notch 111, as... Figure 6 As shown, the front edge of the second cover 12 is provided with a second notch 121, such as... Figure 1 and Figure 2 As shown, when the first cover 11 and the second cover 12 are connected by the connector 13, the first notch 111 and the second notch 121 can be matched and enclosed to form a through hole 14, which is used for the rotor shaft of the cross-rotor unmanned helicopter to pass through. Specifically, there are two of each of the first notch 111 and the second notch 121. When the first cover 11 and the second cover 12 are connected, two through holes 14 can be formed between them to correspond to the two rotor shafts of the cross-rotor unmanned helicopter.

[0042] The first cover 11 and the second cover 12 are detachably connected, and each cover 11 and the second cover 12 are individually fixed to the fuselage. Therefore, when a part of the fuselage malfunctions and requires repair, if the repair location is at the open structure 15 of the cover 1, neither the first cover 11 nor the second cover 12 needs to be disassembled; the repair operation can be performed directly through the open structure 15. If the cover 1 affects the repair location, either the first cover 11 or the second cover 12 can be disassembled accordingly. After the repair operation is completed, the disassembled parts can be reinstalled. In other words, when performing repair operations on the fuselage, the need to remove the cover 1 or a part of the cover 1 can be selected based on the specific location to be repaired, without having to disassemble the entire cover 1 every time. This provides good flexibility, effectively improves repair efficiency, and simplifies the operation.

[0043] The first cover 11 and the second cover 12 are detachably connected by a connector 13. In this embodiment, the connector 13 is a buckle, which facilitates the disassembly and assembly of the first cover 11 and the second cover 12 and can effectively improve the disassembly and assembly efficiency. Of course, the connector 13 can also be set as a bolt or other component, and no specific limitation is made here.

[0044] like Figure 1As shown, the cover 1 is spaced apart from the flat tail 2 and the vertical tail 3. Therefore, the disassembly and assembly operations of the cover 1, the flat tail 2, and the vertical tail 3 do not affect each other. Thus, when the flat tail 2 or the vertical tail 3 needs to be disassembled and repaired, only the flat tail 2 or the vertical tail 3 needs to be disassembled and assembled separately, without disassembling the cover 1, which provides good flexibility.

[0045] The rear end face of the first cover 11 is provided with a first positioning structure 112, and the front end face of the second cover 12 is provided with a second positioning structure 122. When the first cover 11 and the second cover 12 are connected, they can be positioned by the cooperation of the first positioning structure 112 and the second positioning structure 122, and then connected by the connector 13. The positioning structure can ensure that the relative position between the first cover 11 and the second cover 12 is accurate, and ensure that the outer surface can achieve a smooth transition at the joint after the two are connected, so as to reduce wind resistance.

[0046] Furthermore, since the cover 1 is made of glass fiber and aramid honeycomb core, it is relatively lightweight. Therefore, when the first cover 11 and the second cover 12 are positioned by the positioning structure and then connected by the connector 13, it can be avoided that the rear edge of the first cover 11 or the front edge of the second cover 12 may become deformed and unable to be connected after long-term use.

[0047] In this embodiment, the specific structure of the first positioning structure 112 and the second positioning structure 122 is not limited. Specifically, multiple first positioning structures 112 are provided at intervals at the position where the rear end edge of the first cover 11 connects to the second cover 12. Similarly, multiple second positioning structures 122 are provided at intervals at the position where the front end edge of the second cover 12 connects to the first cover 11. The number of first positioning structures 112 and second positioning structures 122 are the same and they are arranged correspondingly to each other.

[0048] like Figure 5 and Figure 6 As shown, the first positioning structure 112 can be a positioning hole, and the second positioning structure 122 can be a positioning protrusion; alternatively, the first positioning structure 112 can be a positioning protrusion, and the second positioning structure 122 can be a positioning hole; or both the first positioning structure 112 and the second positioning structure 122 can be positioning holes. Positioning is then achieved by a positioning pin between the two correspondingly positioned holes. The positioning protrusion can be a carbon rod or a metal part.

[0049] like Figure 5 As shown, the rear edge of the first cover 11 is provided with a first flange structure 113, and the aforementioned first positioning structure 112 is disposed on the first flange structure 113, as shown. Figure 6As shown, the front edge of the second cover 12 has a second flange structure 123 facing inward, and the aforementioned second positioning structure 122 is disposed on the second flange structure 123. The flange structure facilitates the arrangement of the positioning structure, and since the flange structure is turned inward, this arrangement avoids obstructing external airflow and ensures a more regular overall external structure of the cover 1. Specifically, the flange structure can be continuously arranged or multiple flange structures spaced apart.

[0050] In this embodiment, the first flange structure 113 is continuously arranged along the rear end edge of the first cover 11, and the second flange structure 123 is continuously arranged along the front end edge of the second cover 12. The flange structure can increase the structural strength at the edges of the first cover 11 and the second cover 12 and reduce the occurrence of deformation.

[0051] like Figure 4 As shown, the upper part of the first cover 11 is also provided with a ventilation grille 114. During the flight of the cross-rotor unmanned helicopter, air can enter the cover 1 through the ventilation grille 114 and flow out through the open structure 15 of the cover 1, thus forming an airflow inside the cover 1, which is beneficial to the heat dissipation of the internal equipment and components of the unmanned helicopter.

[0052] In this embodiment, the specific structure of the ventilation grille 114 is not limited. For example, multiple grilles are arranged linearly on the ventilation grille 114, and the width of the grille is smaller than the interval between two adjacent grilles to increase the air intake.

[0053] like Figure 1 As shown, the horizontal stabilizer 2 includes a first fixing member 21 and two horizontal stabilizers 22, wherein the two horizontal stabilizers 22 are symmetrically arranged about the axis of the first fixing member 21, and the horizontal stabilizer 2 can be fixed to the fuselage by the first fixing member 21. Specifically, the structure of the horizontal stabilizer 22 is as follows: Figure 7 As shown, it includes a tailstock frame and a tailstock panel 23, wherein the tailstock frame is fixed to the first fixing member 21, and the tailstock panel 23 is located on the outside of the tailstock frame.

[0054] Specifically, the horizontal stabilizer frame includes at least two parallel support beams 24 and at least two parallel tubular beams 25. Each support beam 24 is fixed to each tubular beam 25, effectively improving the connection strength between the support beams 24 and the tubular beams 25 and ensuring the overall strength of the horizontal stabilizer frame. In this embodiment, there are four support beams 24, which are uniformly and linearly distributed along the axial direction of the tubular beams 25, and the support beams 24 and the tubular beams 25 are perpendicular to each other. The support beams 24 are mainly used to bear the aerodynamic loads and vibrations generated by the horizontal stabilizer 22 during flight; the horizontal stabilizer panel 23 serves to envelop the shape and provide aerodynamic smoothness; the horizontal stabilizer 22 adopts a cantilever beam structure with root support.

[0055] To reduce weight, carbon fiber tubes were chosen as the material for tube beam 25.

[0056] In this embodiment, the support beam 24 is made of aluminum alloy, which effectively reduces weight while ensuring support strength.

[0057] Furthermore, the flat-tail panel 23 is made of glass fiber and aramid honeycomb core, which effectively improves its strength.

[0058] To improve connection stability, foam is used to fill the gaps between the horizontal tail frame and the horizontal tail panel 23. Specifically, foam is used to fill the gaps between the support beam 24 and the horizontal tail panel 23, and also to fill the gaps between the tube beam 25 and the horizontal tail panel 23. This arrangement ensures connection strength while minimizing weight.

[0059] In this embodiment, there are two tube beams 25, namely a first tube beam 251 and a second tube beam 252. The diameter of the first tube beam 251 is the same as the diameter of the second tube beam 252. The first tube beam 251 is arranged at the maximum thickness of the airfoil of the horizontal stabilizer 22 to achieve a bending resistance effect. The second tube beam 252 is arranged in the 50% to 60% chord region of the horizontal stabilizer 22 to achieve a torsional resistance effect. The chord is the line connecting the leading edge and trailing edge of the airfoil, and the 50% to 60% chord region is the area between the middle position (50%) and the 60% position of the chord. In this embodiment, the chord length is 320 mm.

[0060] Furthermore, considering both improving support stability and reducing overall weight, the diameter of tube beam 25 is 60% of the maximum thickness of the airfoil. Of course, the diameter of tube beam 25 can also be set to other dimensions.

[0061] In this embodiment, the airfoil selected for the horizontal stabilizer 22 is NACA4412.

[0062] There are no restrictions on the method of fixing the tailstock frame and the first fixing component 21, such as... Figure 7 As shown, an intermediate member 26 can be fixed on the side of the horizontal tail frame facing the first fixing member 21. This intermediate member 26 is made of metal to ensure the overall structural strength. The intermediate member 26 is fixed to the horizontal tail frame and connected to the first fixing member 21 by bolts. Specifically, the intermediate member 26 can be fixed to the tube beam 25 of the horizontal tail frame, or it can be fixed to the support beam 24 of the horizontal tail frame.

[0063] like Figure 1 As shown, the vertical tail 3 includes an upper vertical tail 32, a lower vertical tail 33, and a second fixing member 31. The upper vertical tail 32 is connected above the second fixing member 31, and the lower vertical tail 33 is connected below the second fixing member 31. The vertical tail 3 can be fixed to the fuselage by the second fixing member 31.

[0064] Specifically, such as Figure 8 As shown, the upper tail 32 includes an upper tail frame and an upper tail panel 323. The upper tail frame is fixed to the second fixing member 31, and the upper tail panel 323 is located on the outside of the upper tail frame. Specifically, the upper tail frame includes a first longitudinal beam 321 and a first transverse rib 322. The number of first transverse ribs 322 is at least two and they are arranged along the extension direction of the first longitudinal beam. The first transverse ribs 322 are connected to the first longitudinal beam. It is understood that due to the structural limitations of the upper tail 32, the structures of at least the two first transverse ribs 322 are different, and their lengths decrease in the direction away from the fuselage of the unmanned helicopter. Through the above arrangement, the structural stability of the upper tail 32 is effectively improved. In this embodiment, the number of first longitudinal beams 321 is one. Since the length of at least the first transverse ribs 322 decreases in the direction away from the fuselage of the unmanned helicopter, two or three first longitudinal beams 321 can also be provided, etc., which will not be described in detail here and are all within the scope of protection.

[0065] To reduce weight, the first longitudinal beam 321 is made of aluminum square tubing. Alternatively, the first longitudinal beam 321 can be made of other profiles or other structures.

[0066] Furthermore, the first longitudinal beam 321 and the first transverse rib 322 are fixedly connected by bolts. They can also be connected by welding or gluing.

[0067] Furthermore, the upper tail frame can be bolted to the second fixing member 31, and then the second fixing member 31 is connected to the fuselage. As for the connection between the upper tail frame and the second fixing member 31, it can be that the first transverse rib 322 and the second fixing member 31 are directly connected by bolts, or it can be connected by a separately provided intermediate member, as with the structure of the horizontal tail 22.

[0068] In this embodiment, there are no restrictions on the specific structure of the first fixing member 21 and the second fixing member 31. For example, in this embodiment, both the first fixing member 21 and the second fixing member 31 are set as clamps, which can simplify the connection operation and facilitate the disassembly and assembly operation.

[0069] Of course, the upper vertical tail 32 can also be directly welded to the fuselage, and when connected to the fuselage by clamps, the disassembly and assembly operations can be simplified.

[0070] As shown in the figure, the drooping tail 33 includes a drooping tail frame and a drooping tail panel 333. The drooping tail frame is fixed to the second fixing member 31, and the drooping tail panel 333 is located on the outside of the drooping tail frame. Specifically, the drooping tail frame includes a second longitudinal beam 331 and a second transverse rib 332. There is one second longitudinal beam 331, and at least two second transverse ribs 332 arranged along the extension direction of the second longitudinal beam 331. This configuration effectively improves the structural strength.

[0071] Understandably, due to the structural limitations of the drooping tail 33, the structures of at least the two second transverse ribs 332 are different, and their lengths decrease in the direction away from the fuselage of the unmanned helicopter.

[0072] In this embodiment, the drooping tail frame is bolted to the second fixing member 31 (clamp). The connection between the drooping tail frame and the second fixing member 31 is the same as the connection between the upper drooping tail frame and the second fixing member 31. It can be that the second transverse rib 332 and the second fixing member 31 are directly connected by bolts, or they can be connected by an additional intermediate member.

[0073] For ease of installation, the second longitudinal beam 331 is made of aluminum square tube profile.

[0074] In this embodiment, the second longitudinal beam 331 and the second transverse rib 332 are fixedly connected by bolts. They can also be connected by welding or bonding.

[0075] The above are merely preferred embodiments of this application. It should be noted that those skilled in the art can make various improvements and modifications without departing from the principles of this application, and these improvements and modifications should also be considered within the scope of protection of this application.

Claims

1. A cowling assembly for a cross dual rotor unmanned helicopter, the cross dual rotor unmanned helicopter comprising a fuselage, characterised in that, The fairing assembly comprises a fairing body (1), a horizontal tail (2) and a vertical tail (3) which are separately arranged from the fairing body (1), the fairing body (1) is arranged separately from the horizontal tail (2) and the vertical tail (3), the rear end of the fairing body (1) and the rear side of the bottom of the fairing body (1) are both open structures (15), the fairing body (1) can wrap the head of the fuselage, the rear part of the fuselage can be exposed outside the fairing body (1) through the open structure (15), the rear part of the fuselage can be exposed outside the fairing body (1) through the open structure (15), the horizontal tail (2) and the vertical tail (3) are respectively fixed to the exposed part of the fuselage. The fairing body (1) comprises a first fairing body (11) and a second fairing body (12) which are respectively fixed to the fuselage, the second fairing body (12) is detachably connected with the upper rear end of the first fairing body (11) through a connecting piece (13), and in the connected state, the outer surface of the rear end of the first fairing body (11) and the outer surface of the front end of the second fairing body (12) are smoothly connected, the rear end edge of the first fairing body (11) and the front end edge of the second fairing body (12) can form a through hole (14) which is used for passing the rotor shaft of the cross dual-rotor unmanned helicopter.

2. The nacelle assembly of claim 1, wherein, The rear end face of the first fairing body (11) is further provided with a first positioning structure (112), the front end face of the second fairing body (12) is further provided with a second positioning structure (122), the first fairing body (11) and the second fairing body (12) can be positioned through cooperation of the first positioning structure (112) and the second positioning structure (122) and connected through the connecting piece (13).

3. The cowl assembly of a cross dual-rotor unmanned helicopter according to claim 2, characterized in that, The first positioning structure (112) is a positioning protrusion, and the second positioning structure (122) is a positioning hole. Alternatively, the first positioning structure (112) is a positioning hole, and the second positioning structure (122) is a positioning protrusion.

4. The cowl assembly of claim 2, wherein, The rear end edge of the first fairing body (11) is inwardly provided with a first flanging structure (113), and the first positioning structure (112) is arranged on the first flanging structure (113). The front end edge of the second fairing body (12) is inwardly provided with a second flanging structure (123), and the second positioning structure (122) is arranged on the second flanging structure (123).

5. The cowl assembly of a cross dual-rotor unmanned helicopter according to any one of claims 1-4, characterized in that, The upper part of the first fairing body (11) is further provided with a ventilation grille (114), air can enter the fairing body (1) through the ventilation grille (114) and flow out through the open structure (15).

6. The cowl assembly of a cross dual-rotor unmanned helicopter according to any one of claims 1-4, characterized in that, The horizontal tail (2) comprises a first fixing piece (21) and two horizontal tails (22) which are symmetrically arranged relative to the first fixing piece (21), and the first fixing piece (21) can be fixed to the fuselage. The horizontal tail (22) comprises a horizontal tail skeleton and a horizontal tail panel (23), the horizontal tail panel (23) is fixed to the outer side of the horizontal tail skeleton, and the horizontal tail skeleton is fixed to the first fixing piece (21). The flat tail skeleton comprises at least two parallel arranged support beams (24) and at least two parallel arranged tube beams (25), and each of the support beams (24) is fixed with each of the tube beams (25).

7. The cowl assembly of a cross dual-rotor unmanned helicopter according to claim 6, characterized in that, The tube beams (25) are carbon fiber tubes. And / or, the support beams (24) are aluminum alloy beams. And / or, the material of the flat tail panel (23) is glass fiber and aramid honeycomb core. And / or, the gap between the flat tail skeleton and the flat tail panel (23) is filled with foam.

8. The cowl assembly of claim 6, wherein, The number of the tube beams (25) is two, and each of the tube beams (25) is a first tube beam (251) and a second tube beam (252), and the diameter of the first tube beam (251) is the same as that of the second tube beam (252). The first tube beam (251) is arranged at the maximum thickness of the airfoil of the flat tail (22), and the second tube beam (252) is arranged within 50% to 60% of the chord region.

9. The cowl assembly of a cross dual-rotor unmanned helicopter according to any one of claims 1-4, characterized in that, The vertical tail part (3) comprises an upper vertical tail (32) and a lower vertical tail (33) and a second fixing member (31) connected between the upper vertical tail (32) and the lower vertical tail (33), and the second fixing member (31) is capable of being fixed with the fuselage; The upper vertical tail (32) comprises an upper vertical tail skeleton and an upper vertical tail panel (323), the upper vertical tail skeleton comprises a first longitudinal beam (321) and at least two first transverse ribs (322), the first longitudinal beam (321) and the first transverse ribs (322) are fixed, and the upper vertical tail panel (323) is arranged outside the upper vertical tail skeleton; The lower vertical tail (33) comprises a lower vertical tail skeleton and a lower vertical tail panel (333), the lower vertical tail skeleton comprises a second longitudinal beam (331) and at least two second transverse ribs (332), the second longitudinal beam (331) and the second transverse ribs (332) are fixed, and the lower vertical tail panel (333) is arranged outside the lower vertical tail skeleton; The upper vertical tail skeleton and the lower vertical tail skeleton are respectively fixed with the second fixing member (31).

10. The cowl assembly of a cross dual-rotor unmanned helicopter according to claim 9, characterized in that, The first longitudinal beam (321) and / or the second longitudinal beam (331) is an aluminum square tube profile.

11. A cross dual rotor unmanned helicopter, characterized in that, The whole aircraft comprises a fuselage and the fairing assembly according to any one of claims 1 to 10.

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