Unmanned aerial vehicle and fuselage fairing structure thereof

Abstract

The invention belongs to the field of unmanned aerial vehicle structures, and discloses an unmanned aerial vehicle and a fuselage fairing structure thereof, the unmanned aerial vehicle comprises a cover body, the top of the cover body is provided with a hinge joint connected with a fuselage of the unmanned aerial vehicle, the cover body is also provided with a quick release lock connected with the fuselage of the unmanned aerial vehicle, and the cover body is internally provided with an air support rod connected with the fuselage of the unmanned aerial vehicle; when the quick-release lock releases the connection between the cover body and the fuselage of the unmanned aerial vehicle, the air supporting rod can upwards support the cover body, and when the air supporting rod upwards supports the cover body, the cover body rotates around the hinge joint. The fuselage fairing structure of the unmanned aerial vehicle is convenient to open, and then maintenance of the large freight unmanned aerial vehicle is facilitated.

Description

Technical Field

[0001] The invention belongs to the field of unmanned aerial vehicle structures, and in particular relates to an unmanned aerial vehicle and a fuselage fairing structure thereof. Background Art

[0002] The fairing design of large cargo drones is different from that of manned aircraft. Generally, it is required to have a simple structure, easy maintenance, low cost and reliable performance. The nose fairing needs to have a good aerodynamic shape and provide an installation interface and platform for internal system equipment. Considering the economic needs of cargo drones, the nose fairing must also have excellent weight indicators. Traditional nose fairings cannot be opened quickly or are inconvenient to open, resulting in time-consuming and labor-intensive equipment maintenance. Summary of the invention

[0003] In order to solve the problems existing in the prior art, the purpose of the present invention is to provide a UAV and its fuselage fairing structure. The fuselage fairing structure of the UAV of the present invention is easy to open, which is beneficial to the maintenance of large cargo UAVs.

[0004] To achieve the above purpose, the technical solution adopted by the present invention is as follows: A fuselage fairing structure for an unmanned aerial vehicle comprises a cover body, a hinge joint connected to the fuselage of the unmanned aerial vehicle is provided on the top of the cover body, a quick-release lock connected to the fuselage of the unmanned aerial vehicle is also provided on the cover body, and a gas strut connected to the fuselage of the unmanned aerial vehicle is provided inside the cover body; when the quick-release lock releases the connection between the cover body and the fuselage of the unmanned aerial vehicle, the gas strut can prop up the cover body upwards, and when the gas strut props up the cover body, the cover body rotates around the hinge joint.

[0005] Preferably, the quick-release locks are provided on both sides of the cover body, and positioning pins are provided at the bottom of the cover body, and the positioning pins are used for positioning between the cover body and the fuselage of the drone.

[0006] Preferably, the gas struts are symmetrically arranged inside the cover along the width direction of the fuselage of the drone.

[0007] Preferably, the cover body includes a frame and a cover body wall panel arranged on the frame.

[0008] Preferably, the cover body wall panel comprises a front cover body wall panel and a rear cover body wall panel; The skeleton includes a frame and a longitudinal beam. Along the heading direction, the frame includes a front frame, a middle frame and a rear end frame. The longitudinal beam is connected to the front frame, the middle frame and the rear end frame. The front cover body wall panel and the rear cover body wall panel are butted at the front frame. The rear cover body wall panel is covered outside the middle frame and the rear end frame. The rear cover body wall panel is sealed and butted with the fuselage of the UAV through the rear end frame. The hinge joint and quick release lock are both connected to the rear end frame; One end of the gas strut is installed at the connection between the middle frame and the longitudinal beam through a strut support, and the other end of the gas strut is connected to the fuselage of the UAV.

[0009] Preferably, the top of the rear cover body wall panel and the rear end frame is provided with a first notch for avoiding the fuselage fairing of the drone, and the bottom of the rear end frame is provided with a second notch for avoiding the front landing gear of the drone.

[0010] Preferably, a top fairing package is provided at the top of the rear cover body wall panel in front of the first notch, and a lower fairing is provided at the bottom of the rear cover body wall panel in front of the second notch.

[0011] Preferably, the rear cover body wall panel adopts a composite sandwich structure, and the top fairing package and the lower fairing adopt a laminate structure.

[0012] Preferably, the material of the front cover body wall panel is a composite material with a sandwich structure, and the front cover body wall panel adopts a laminate structure in the connection area and the equipment installation area.

[0013] The present invention also provides an unmanned aerial vehicle, wherein the fuselage fairing of the unmanned aerial vehicle adopts the fuselage fairing structure of the unmanned aerial vehicle described above in the present invention.

[0014] The present invention has the following beneficial effects: In the fuselage fairing structure of the UAV of the present invention, considering that the height of the UAV is generally low, the cover body is lower from the ground, so the top of the cover body of the present invention is provided with a hinge joint connected to the fuselage of the UAV, and the hinge joint can be used to realize the cover body to flip upward, so as to facilitate maintenance personnel to perform maintenance and inspection; the cover body is also provided with a quick release lock connected to the fuselage of the UAV, so the quick release lock can be used to realize the cover body and the fuselage of the UAV to be quickly locked or unlocked without tools; the inside of the cover body is provided with a gas strut connected to the fuselage of the UAV, so when the cover body is flipped upward, the gas strut can be used to keep the cover body in the flipped-up position, and then the maintenance personnel can perform maintenance and inspection operations. In summary, the fuselage fairing structure of the UAV of the present invention is easy to open, which is conducive to the maintenance of large cargo UAVs. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] The present application is further described in detail below in conjunction with the accompanying drawings of the embodiments.

[0016] Figure 1 This is a schematic diagram of the overall structure of the fuselage fairing structure of the UAV.

[0017] Figure 2 Schematic diagram of the structure of the nose cover frame in an embodiment of the present invention.

[0018] Figure 3 It is a schematic diagram of the structure after the nose cover is closed in an embodiment of the present invention.

[0019] Figure 4 It is a schematic diagram of the structure after the nose cover is opened 120 degrees in an embodiment of the present invention.

[0020] Among them: 1-front cover body wall panel, 2-rear cover body wall panel, 3-top fairing package, 4-lower fairing, 5-1-first front frame, 5-2-second front frame, 6-1-first middle frame, 6-2-second middle frame, 7-1-first rear end frame, 7-2-second rear end frame, 7-3-third rear end frame, 8-1-first left longitudinal beam, 8-2-second right longitudinal beam, 9-1-first gas strut, 9-2-second gas strut, 10-1-first top longitudinal beam, 10-2-second top longitudinal beam Beam, 11-connecting joint, 12-quick release lock, 13-lower camera mounting bracket, 14-upper camera mounting bracket, 15-sensor mounting bracket, 16-1-first hinge joint, 16-2-second hinge joint, 17-1-first locating pin, 17-2-second locating pin, 18-1-first strut support, 18-2-second strut support, 19-UAV fuselage, 20-fuselage fairing, 21-front landing gear, 22-first notch, 23-second notch. DETAILED DESCRIPTION

[0021] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all of the embodiments. The components of the embodiments of the present invention described and shown in the drawings here can usually be arranged and designed in various different configurations. Therefore, the following detailed description of the embodiments of the present invention provided in the drawings is not intended to limit the scope of the claimed invention, but merely represents selected embodiments of the present invention. Based on the embodiments in the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0022] See also Figure 1-Figure 4 The fuselage fairing structure of the drone of this embodiment includes a cover body, a hinge joint connected to the fuselage of the drone is provided on the top of the cover body, a quick-release lock connected to the fuselage of the drone is also provided on the cover body, and a gas strut connected to the fuselage of the drone is provided inside the cover body; when the quick-release lock releases the connection between the cover body and the fuselage of the drone, the gas strut can prop up the cover body upward, and when the gas strut props up the cover body, the cover body rotates around the hinge joint.

[0023] The fuselage fairing structure of the UAV in the above embodiment includes the following steps during use: Closing process: Figure 3 to Figure 4 Taking the process shown in the figure as an example, the cover body is rotated counterclockwise around the hinge joint to turn the cover body downward. Figure 3In the state shown, during the flipping process, the gas struts are retracted, and then the cover body and the UAV fuselage are locked relative to each other through the quick release lock, thereby realizing the closing of the UAV nose cover; Opening process: Figure 4 to Figure 3 Take the process shown in the figure as an example, first open the quick release lock to release the locking state between the cover and the drone body, and then rotate the cover clockwise around the hinge joint to turn the cover down. Figure 3 In the state shown, during the flipping process, the gas struts extend until the cover is flipped to the point where the gas struts can no longer extend. At this time, the cover is at a certain angle to the drone body. At this angle, maintenance personnel can perform maintenance operations. The specific angle can be determined based on actual conditions, and the present invention does not make any specific limitations.

[0024] As a preferred embodiment of the present invention, see Figure 1-Figure 4 In this embodiment, the quick-release locks are provided on both sides of the cover (referring to the width direction of the drone (also the wingspan direction)), and more than two can be provided on each side to ensure the stability of the locking between the cover and the drone fuselage; and a positioning pin is provided at the bottom of the cover, and the positioning pin is used for positioning between the cover and the drone fuselage. Specifically, the positioning pin can be provided on the cover, and in this case, a positioning hole adapted to the positioning pin is provided on the drone fuselage 19; or, the positioning pin is provided on the drone fuselage 19, and in this case, a positioning hole adapted to the positioning pin is provided on the cover. The positioning pin is provided to accurately position the drone fuselage 19 and the cover, and to prevent the drone fuselage 19 and the cover from being misaligned and affecting the overall aerodynamic performance of the aircraft.

[0025] As a preferred embodiment of the present invention, see Figure 2 In this embodiment, the gas struts are symmetrically arranged inside the cover along the width direction of the UAV fuselage. The two symmetrical gas struts can ensure that the cover is subjected to balanced force in the width direction of the fuselage, thereby avoiding deformation of the cover due to the cover being supported for too long during maintenance.

[0026] As a preferred embodiment of the present invention, see Figure 1-Figure 4 In this embodiment, the cover body includes a frame and a cover body wall plate arranged on the frame. The frame can play the main role of bearing force and ensure the rigidity of the cover body as a whole. The cover body wall plate mainly plays the role of heat preservation, sound insulation, noise reduction and protection of parts in the cover body, and can be made of lightweight materials. Therefore, the cover body of this embodiment has the characteristics of good structural rigidity and light weight.

[0027] As a preferred embodiment of the present invention, see Figure 1-Figure 4 In this embodiment, the cover body wall panel includes a front cover body wall panel 1 and a rear cover body wall panel 2; the skeleton includes a frame and a longitudinal beam, along the heading direction (ie Figure 3In the direction from left to right in the figure), the frame includes a front frame, a middle frame and a rear end frame, and the longitudinal beam is connected to the front frame, the middle frame and the rear end frame. The longitudinal beam mainly serves to connect the front frame, the middle frame and the rear end frame longitudinally to ensure the relative positions of the front frame, the middle frame and the rear end frame in the heading direction. The front cover body wall panel 1 and the rear cover body wall panel 2 are butted at the front frame, and the rear cover body wall panel 2 is covered outside the middle frame and the rear end frame. The rear cover body wall panel 2 is sealed and butted with the fuselage of the UAV through the rear end frame; the hinge joint and the quick release lock are both connected to the rear end frame; one end of the gas strut is installed at the connection between the middle frame and the longitudinal beam through a strut support, and the other end of the gas strut is connected to the fuselage of the UAV.

[0028] As a preferred embodiment of the present invention, see Figure 2 , combined with Figure 3 and Figure 4 In this embodiment, the top of the rear cover wall plate 2 and the rear end frame is provided with a first notch 22 for avoiding the fuselage fairing 20 of the UAV, and the bottom of the rear end frame is provided with a second notch 23 for avoiding the front landing gear 21 of the UAV. When the cover is turned up, due to the presence of the first notch 22, the position interference between the top of the fuselage fairing 20 and the top of the cover wall plate is avoided; when the cover is turned down, due to the presence of the second notch 23, the front landing gear 21 of the UAV just extends into the second notch 23, thereby avoiding the position interference between the bottom of the second notch 23 and the bottom of the cover wall plate, and at the same time providing corresponding space for the front landing gear 21 to be retracted.

[0029] As a preferred embodiment of the present invention, see Figure 1 , Figure 3 and Figure 4 In this embodiment, a top fairing package 3 is provided at the top of the rear cover body wall panel 2 in front of the first notch 22, and a lower fairing 4 is provided at the bottom of the rear cover body wall panel 2 in front of the second notch 23. The top fairing package 3 can be used together with the fuselage fairing 20 to perform fairing, thereby avoiding the influence of the opening of the first notch 22 on the aerodynamic performance of the aircraft and improving the aerodynamic performance of the UAV; the lower fairing 4 can perform fairing on the aircraft, thereby avoiding the influence of the opening of the second notch 23 on the aerodynamic performance of the aircraft and improving the aerodynamic performance of the UAV.

[0030] As a preferred implementation scheme of the present invention, in this embodiment, the rear cover body wall panel 2 adopts a composite material sandwich structure, so that the rear cover body wall panel 2 has the characteristics of light weight, stable structure, good heat preservation, noise reduction and other effects, and the top fairing package 3 and the lower fairing 4 adopt a laminate structure, which ensures that the top fairing package 3 and the lower fairing 4 have a certain fairing ability while also having a certain anti-deformation ability, thereby ensuring the overall fairing and aerodynamics of the aircraft.

[0031] As a preferred embodiment of the present invention, in this embodiment, the material of the front cover body wall panel 1 adopts a composite material with a sandwich structure, so that the front cover body wall panel 1 has the characteristics of light weight, stable structure, good heat preservation, noise reduction and other effects. The front cover body wall panel 1 adopts a laminate structure in the connection area and the equipment installation area to ensure the strength of the front cover body wall panel 1 in the connection area and the equipment installation area.

[0032] Example The fuselage fairing structure of the UAV in this embodiment includes a cover wall panel, a frame, a hinge joint, a gas strut, a strut support, and a quick release lock. The fuselage fairing structure can provide aerodynamic fairing, an installation platform, and a maintenance path for the internal equipment of the UAV's nose cover. The overall material of the cover wall panel is a honeycomb sandwich composite material structure, and the frame adopts a metal frame beam composite structure. The cover wall panel consists of two parts, front and back, including a cover wall panel 1 and a rear cover wall panel 2. The top of the rear cover wall panel 2 is provided with a top fairing package 3 and the bottom is provided with a lower fairing 4. The frame of the nose cover consists of a frame and a longitudinal beam. Three frames are arranged along the heading, namely the front frame, the middle frame, and the rear end frame. The front frame is used for the docking of the cover wall panel 1 and the rear cover wall panel 2; the middle frame is used to increase the rigidity of the cover skin, and the rear end frame is used to strengthen the opening of the rear cover wall panel 2 and ensure its sealing with the front end frame of the cargo compartment of the UAV fuselage when the cover is closed. Four longitudinal beams are arranged along the circumferential direction of the rear cover wall panel 2 for load transmission and strengthening of the skin opening. A pitot tube connection joint and a reinforcement structure are also arranged between the upper left and right longitudinal beams. Two sets of hinge joints are arranged on the upper part of the rear cover wall panel 2, and a set of gas struts are arranged on both sides to achieve power assistance. A positioning pin is arranged at the lower part of the rear cover wall panel 2. When the cover is in the closed state, the positioning pin is locked with a hook lock, and the entire cover is opened in an upward flip-up manner.

[0033] Specifically, the present embodiment is further described below in conjunction with the accompanying drawings: The front cover body wall panel 1 adopts a composite sandwich structure, and the front cover body wall panel 1 is a laminated plate structure in the connection area and the equipment installation area. The top of the rear cover body wall panel 2 is provided with a top fairing package 3, and the lower fairing 4 is provided at the bottom. The rear cover body wall panel 2 adopts a composite sandwich structure, and the top fairing package 3 and the lower fairing 4 are laminated plate structures; specifically, the rear cover body wall panel 2 adopts a honeycomb sandwich composite structure, and the lower part of the rear cover body wall panel 2 and the front landing gear compartment are integrally formed.

[0034] The nose cover skeleton is arranged with three frames along the heading direction; along the axis direction of the aircraft, the front frame includes two sections, namely, the first front frame 5-1 on the right and the second front frame 5-2 on the left; the connection between the first front frame 5-1 and the second front frame 5-2 is butt-jointed with a connecting angle piece; the first front frame 5-1 and the second front frame 5-2 are riveted to the cover skin (i.e., the cover wall panel); the front cover wall panel 1 and the rear cover wall panel 2 are butt-jointed together; the first front frame 5-1 and the second front frame 5-2 provide joints for the installation of the lower camera mounting bracket 13, the upper camera mounting bracket 14, and the sensor mounting bracket 15, wherein the lower camera mounting bracket 13 and the upper camera mounting bracket 14 are both used to install cameras, and the sensor mounting bracket 15 is used to install sensors (such as atmospheric data sensors); The intermediate frame is divided into four sections: including the first middle frame 6-1 on the right and the second middle frame 6-2 on the left. The first middle frame 6-1 and the second middle frame 6-2 can be used as an integral structure or fixed as a whole by a fixed structure. The first middle frame 6-1 and the second middle frame 6-2 are riveted to the rear cover wall panel 2 to improve the rigidity of the rear cover skin wall panel 2; the rear end frame includes the first rear end frame 7-1 on the right, the second rear end frame 7-3 in the middle and the third rear end frame 7-2 on the left. The second rear end frame 7-3 is provided with a second notch 23, and the second notch 23 is used to provide an avoidance space for the front landing gear 21. The first rear end frame 7-1, the second rear end frame 7-3 in the middle and the third rear end frame 7-2 on the left are designed as an integral structure or fixed as a whole. The fixed structure fixes the two together, and the entire rear end frame is used to increase the strength of the cover opening and the front landing gear compartment opening and to ensure the sealing between the cover and the cargo compartment when the cover is closed; two locating pins are arranged at the lower part of the rear end frame, namely the first locating pin 17-1 and the second locating pin 17-2, which are respectively arranged at the bottom of the first rear end frame 7-1 and the third rear end frame 7-2, and the two locating pins are used for positioning between the cover and the UAV fuselage 19 in the locked state; four right longitudinal beams are arranged along the circumferential direction of the entire cover, namely the first top longitudinal beam 10-1, the second top longitudinal beam 10-2, the first left longitudinal beam 8-1 and the second right longitudinal beam 8-2, among which the first top longitudinal beam 10-1 and the second top longitudinal beam 10-2 are opposite to each other. It is located on the right and left sides of the top of the skeleton, the first left longitudinal beam 8-1 and the second right longitudinal beam 8-2 are symmetrically located on the left and right sides of the side of the skeleton, the two ends of all the longitudinal beams are fixedly connected to the front frame and the rear end frame respectively, and the middle is fixedly connected to the middle frame. The longitudinal beams are used to transfer the longitudinal load of the gas struts, as well as to fix and limit the front frame, the middle frame and the rear end frame in the longitudinal direction, so that the front frame, the middle frame and the rear end frame are connected to form an integral structure with a certain rigidity; a connecting joint 11 is arranged between the two upper longitudinal beams (i.e., the first top longitudinal beam 10-1 and the second top longitudinal beam 10-2), and the connecting joint 11 can be set at the top of the middle frame and is also connected to the middle frame, thereby ensuring the stability of the installation of the connecting joint 11, and the connecting joint 11 can provide an installation interface and platform for the system equipment.

[0035] There are two hinge joints, namely the first hinge joint 16-1 and the second hinge joint 16-2. The first hinge joint 16-1 and the second hinge joint 16-2 are both single-ear joints. The first hinge joint 16-1 and the second hinge joint 16-2 are symmetrically distributed on the upper rear side of the nose cover, and are riveted to the first rear end frame 7-1 and the second rear end frame 7-2 respectively; the hinge joint is docked with the double-ear joint of the fuselage to provide a rotation axis for opening the nose cover.

[0036] Two gas struts are provided, namely the first gas strut 9-1 and the second gas strut 9-2. A first strut support 18-1 is provided at the intersection of the first middle frame 6-1 and the second right longitudinal beam 8-2, and a second strut support 18-2 is provided at the intersection of the second middle frame 6-2 and the first left longitudinal beam 8-1. One end of the first gas strut 9-1 is connected to the first strut support 18-1, and the other end is connected to the fuselage. One end of the second gas strut 9-2 is connected to the second strut support 18-2, and the other end is connected to the fuselage. The first strut support 18-1 and the second strut support 18-2 are bolted to the intersection of the middle frame (the first middle frame 6-1, the second middle frame 6-2) and the longitudinal beams on both sides (the first left longitudinal beam 8-1, the second right longitudinal beam 8-2), and the heading and circumferential loads are transmitted by the middle frame and the longitudinal beams on both sides respectively. The strut support is a double-ear structure, which is connected to the single ear of the gas strut to provide a rotation axis for the gas strut. In this embodiment, four quick-release locks 12 are arranged in total, and two quick-release locks 12 are symmetrically arranged on the left and right sides of the cover body; the lock seat of the quick-release lock 12 is riveted on the nose cover, the lock body of the quick-release lock 12 is installed on the lock seat, the opening button is located on the outside of the fuselage, and the hook is installed on the front end surface of the fuselage.

[0037] The fuselage fairing structure of the UAV of the present invention can provide aerodynamic fairing for the equipment installed inside the nose and the front landing gear structure, provide installation space and maintenance channels for system equipment, and provide an installation platform or structural interface for internal equipment or accessories, with good maintainability and convenient opening / closing operation; the cover body has excellent structural strength and weight index, is not easy to deform, and has good anti-bird strike performance.

[0038] Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work should fall within the scope of protection of the present invention.

[0039] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention rather than to limit it. Although the present invention has been described in detail with reference to the above embodiments, ordinary technicians in the relevant field should understand that the specific implementation methods of the present invention can still be modified or replaced by equivalents. Any modification or equivalent replacement that does not depart from the spirit and scope of the present invention should be covered within the scope of protection of the claims of the present invention.

Claims

1. A fuselage fairing structure of an unmanned aerial vehicle, characterized in that: The invention comprises a cover body, the top of which is provided with a hinge joint connected to the fuselage of the UAV, the cover body is also provided with a quick-release lock connected to the fuselage of the UAV, and the inside of the cover body is provided with a gas strut connected to the fuselage of the UAV; when the quick-release lock releases the connection between the cover body and the fuselage of the UAV, the gas strut can prop up the cover body upwards, and when the gas strut props up the cover body, the cover body rotates around the hinge joint.

2. The fuselage fairing structure of an unmanned aerial vehicle according to claim 1, characterized in that: The quick-release locks are arranged on both sides of the cover body, and positioning pins are arranged at the bottom of the cover body, and the positioning pins are used for positioning between the cover body and the fuselage of the drone.

3. The fuselage fairing structure of an unmanned aerial vehicle according to claim 1, characterized in that: The gas struts are symmetrically arranged inside the cover along the width direction of the fuselage of the drone.

4. The fuselage fairing structure of an unmanned aerial vehicle according to claim 1, characterized in that: The cover body comprises a frame and a cover body wall plate arranged on the frame.

5. The fuselage fairing structure of an unmanned aerial vehicle according to claim 4, characterized in that: The cover body wall panel comprises a front cover body wall panel (1) and a rear cover body wall panel (2); The frame comprises a frame and a longitudinal beam. Along the heading direction, the frame comprises a front frame, a middle frame and a rear end frame. The longitudinal beam is connected to the front frame, the middle frame and the rear end frame. The front cover body wall panel (1) and the rear cover body wall panel (2) are butted at the front frame. The rear cover body wall panel (2) is covered outside the middle frame and the rear end frame. The rear cover body wall panel (2) is sealed and butted with the fuselage of the drone through the rear end frame. The hinge joint and quick release lock are both connected to the rear end frame; One end of the gas strut is installed at the connection between the middle frame and the longitudinal beam through a strut support, and the other end of the gas strut is connected to the fuselage of the UAV.

6. The fuselage fairing structure of an unmanned aerial vehicle according to claim 5, characterized in that: The rear cover body wall plate (2) and the top of the rear end frame are provided with a first notch (22) for avoiding the fuselage fairing (20) of the drone, and the bottom of the rear end frame is provided with a second notch (23) for avoiding the front landing gear (21) of the drone.

7. The fuselage fairing structure of an unmanned aerial vehicle according to claim 6, characterized in that: A top fairing package (3) is provided at the top of the rear cover body wall plate (2) in front of the first notch (22), and a lower fairing (4) is provided at the bottom of the rear cover body wall plate (2) in front of the second notch (23).

8. The fuselage fairing structure of an unmanned aerial vehicle according to claim 7, characterized in that: The rear cowl body wall panel (2) adopts a composite material sandwich structure, and the top fairing package (3) and the lower fairing (4) adopt a laminated plate structure.

9. The fuselage fairing structure of an unmanned aerial vehicle according to claim 6, characterized in that: The material of the front cover body wall panel (1) is a composite material with a sandwich structure, and the front cover body wall panel (1) has a laminate structure in the connection area and the equipment installation area.

10. A drone, characterized in that: The fuselage fairing of the UAV adopts the fuselage fairing structure of the UAV described in any one of claims 1-9.

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