A cargo drone fuselage structure

Abstract

This utility model discloses a fuselage structure for a cargo drone, including a fuselage body, a tail cap, a nose cone, a hatch, a front cap, and a rear cap. The fuselage body consists of a fuselage frame and fuselage skin. Equipment mounting plates and floor panels are respectively installed at the top and bottom of the fuselage frame. The fuselage frame includes longitudinal members for bearing bending and tensile / compressive loads and circumferential members for bearing shear forces. The floor panel is mounted on floor beams and connected to the floor beams and the lower part of the frame of the circumferential members via fasteners. The equipment mounting plate is installed on the upper part of the fuselage and supported by the upper part of the frame of the circumferential members and the upper longitudinal beams. This fuselage structure is applicable to small and medium-sized electric vertical take-off and landing (eVTOL) compound wing cargo drones, featuring high space utilization, secure cargo fixation, convenient maintenance, high strength, and low cost.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) technology, specifically to a cargo UAV fuselage structure. Background Technology

[0002] The core value of small and medium-sized cargo drones lies in "solving the pain points of traditional logistics in short-distance, last-mile, and special scenarios in a flexible and efficient way." Especially against the backdrop of rising labor costs, increasing demand for low-carbon solutions, and the upgrading of logistics in remote areas, their application prospects continue to expand. Generally, the payload capacity (typically ≤50 kg) and flight time (typically ≤2 hours) of small and medium-sized cargo drones are limited. With future technological advancements, these parameters will gradually be improved, further unleashing their advantages.

[0003] The cargo drone's internal fuselage is designed with a cargo bay to primarily accommodate goods, meeting the transportation needs of various types of cargo. The design must maximize the utilization of the drone's internal space and enhance the reliability of the cargo. Simultaneously, the structural safety of the fuselage during drone flight must be considered to ensure safe and timely delivery of goods and facilitate loading and unloading.

[0004] Reference 1: Chinese patent document with publication number CN207697983U.

[0005] Reference 1 discloses a cargo drone fuselage structure, which includes a nose cargo door, a tail cargo door, or a side cargo door structure and corresponding mechanisms. The nose and tail cargo doors are assisted in opening and closing in various ways via electric servo mechanisms or manual mechanisms. The interior of the cargo compartment is equipped with an insulated structure made of heat-insulating material, and specialized equipment can provide a refrigerated or heated cargo environment. A labor-saving auxiliary movement mechanism is designed for the cargo compartment floor.

[0006] However, the above structure is applied to large cargo drones with a circular fuselage, which is suitable for internal pressurization structures. For general cargo drones without pressurization, which are mostly square, the circular fuselage structure has low space utilization. Utility Model Content

[0007] The purpose of this invention is to solve the aforementioned technical problems in the prior art and to provide a fuselage structure for a cargo drone.

[0008] To solve the above-mentioned technical problems, the technical solution adopted by this utility model is: a cargo drone fuselage structure, including a fuselage body, a tail cover, a head cover, a hatch, a front cover, and a rear cover;

[0009] The fuselage body consists of a fuselage frame and a fuselage skin. The fuselage frame supports the fuselage skin, and the top and bottom of the fuselage frame are respectively provided with equipment mounting plates and floor.

[0010] The fuselage frame includes longitudinal members for bearing bending and tensile / compressive loads and circumferential members for bearing shear forces;

[0011] The longitudinal component includes two floor beams, two upper longitudinal beams, and a vertical tail connecting rib. The vertical tail connecting rib is provided with a vertical tail beam insertion hole and a body frame connecting edge.

[0012] The circumferential component includes a first frame, a second frame, a support frame, a reinforcing frame, a door frame, a rear beam frame, a front beam frame, and an upper half frame arranged along the longitudinal direction;

[0013] The hinge of the front cover is connected to the upper half frame, the front beam frame is connected to the front beam of the wing, and the rear beam frame is connected to the rear beam of the wing.

[0014] The first frame and the second frame are connected to the vertical tail docking rib, and the webs of the first frame and the second frame are connected together with the front and rear fuselage frame connecting edges of the vertical tail docking rib.

[0015] The floor is mounted on the floor beam and is connected to the floor beam and the lower part of the frame in the circumferential member by fasteners.

[0016] The equipment mounting plate is installed on the upper part of the machine body and is supported by the upper part of the frame of the circumferential component and the upper longitudinal beam.

[0017] As a further optimization of the fuselage structure of a cargo drone according to this utility model: the frame of the circumferential component is made of carbon fiber composite material.

[0018] As a further optimization of the fuselage structure of a cargo drone according to this utility model: the head cover is composed of a hinge, a buckle and a head cover body. The two sides of the hinge are respectively connected to the head cover body and the fuselage body by fasteners, and the head cover can rotate around the hinge axis.

[0019] As a further optimization of the fuselage structure of the cargo drone of this utility model: the head cover also includes an airspeed tube support, which is provided with a hexagonal groove, a reinforcing rib and an airspeed tube through hole, the airspeed tube through hole for the airspeed tube to pass through, and an external hexagonal nut is provided in the hexagonal groove.

[0020] As a further optimization of the fuselage structure of the cargo drone of this utility model: the hatch is located on one side of the fuselage body, and the hatch is a detachable hatch.

[0021] As a further optimization of the fuselage structure of the cargo drone of this utility model: the door is composed of a door buckle, a latch and a door body. The door buckle is composed of a reinforcing plate, a locking hook and a latch. The reinforcing plate is connected to the door body, the locking hook is connected to the reinforcing plate and the latch is connected to the fuselage body. The door is fixed by the cooperation of the latch and the latch.

[0022] As a further optimization of the fuselage structure of a cargo drone of this utility model: the floor includes a floor body and a baffle disposed on the floor body, the baffle being fixed to the floor body through a first baffle joint and a second baffle joint.

[0023] As a further optimization of the fuselage structure of a cargo drone according to this utility model: a baffle groove is provided on the second baffle joint.

[0024] As a further optimization of the fuselage structure of the cargo drone of this utility model: a frame joint is provided on the back of the rear beam frame. One side of the frame joint is connected to the web plate of the rear beam frame by fasteners, and the other side is connected to the upper longitudinal beam and the lower beam support joint by fasteners. The beam support joint is first glued to the upper longitudinal beam, and then connected to the frame joint and the rear beam frame by fasteners.

[0025] As a further optimization of the fuselage structure of a cargo drone according to this utility model: the reinforcing frame includes a main frame and a bottom frame, which are respectively connected to the edge strip and web of the floor beam.

[0026] This utility model has the following beneficial effects:

[0027] 1. High space utilization: The fuselage is a square with straight sections in the middle area, which is suitable for transporting general square goods. The head cover is an integrally openable structure, which allows longer goods to be loaded into the fuselage through the head cover, resulting in high structural space utilization.

[0028] 2. The cargo is securely fixed. In the door area, a baffle is designed on the floor, and a retaining groove is designed on the joint of the second baffle. This can effectively fix the cargo inside the cargo hold and prevent the cargo from moving during transportation and affecting the center of gravity of the aircraft.

[0029] 3. Easy maintenance: The head cover, front port cover, and rear port cover all serve as maintenance access points and are quick and easy to open, facilitating maintenance of the equipment on the mounting plate. The tail port cover facilitates maintenance of the tail section equipment.

[0030] 4. High strength: The frame is a cage structure composed of circumferential and longitudinal members, with the longitudinal members remaining continuous. It can withstand the main loads of the fuselage, providing high strength and effectively loading cargo inside the fuselage structure to ensure safe cargo transportation. When the front beam frame, rear beam frame, and upper longitudinal beam are connected, locally reinforced frame joints and beam support joints are designed to increase the rigidity of the connection area, increase the number of connecting fasteners, and reduce stress in the connection area.

[0031] 5. Low cost: Circular parts within straight sections such as the body can be interchangeable, which helps reduce the number of molds and parts, and lowers molding and assembly costs. Attached Figure Description

[0032] Figure 1This is a diagram showing the location of the cargo drone's fuselage structure on the drone.

[0033] Figure 2 An isometric drawing of the fuselage structure of a cargo drone;

[0034] Figure 3 An exploded view of the fuselage structure of a cargo drone;

[0035] Figure 4 An exploded view of the fuselage.

[0036] Figure 5 An exploded view of the fuselage frame;

[0037] Figure 6 This is an axonometric drawing of the headgear;

[0038] Figure 7 This is an isometric view of the pitot tube support;

[0039] Figure 8 Axonometric drawing of the door;

[0040] Figure 9 An exploded view of the door latch;

[0041] Figure 10 Axonometric view of the vertical tail butt joint rib;

[0042] Figure 11 Axonometric view of the floor at the doorway;

[0043] Figure 12 This is an isometric view of the second baffle joint;

[0044] Figure 13 This is a partial view of the connection between the rear beam frame and the upper longitudinal beam.

[0045] Figure 14 This is a view showing the connection between the vertical tail rib and the first and second frames.

[0046] Figure 15 A partial view showing the connection between the reinforced frame and the floor beam;

[0047] Figure 16 Sectional view showing the connection between the reinforcing frame and the floor beam;

[0048] Numbered in the diagram: 1. Cargo UAV fuselage structure; 11. Fuselage body; 111. Fuselage frame; 11111. Floor beam; 11112. Upper longitudinal beam; 111121. Beam support joint; 11113. Vertical tail docking rib; 111131. Vertical tail beam insertion hole; 111132. Fuselage frame connecting edge; 11121. First frame; 11122. Second frame; 11123. Support frame; 11124. Reinforcing frame; 111241. Main frame; 111242. Bottom frame; 11125. Door frame; 11126. Rear beam frame; 111261. Frame joint; 11127. Front beam frame; 11128. Upper half frame; 1 1131. Equipment mounting plate; 11141. Floor; 111411. Floor body; 111412. Baffle; 111413. First baffle joint; 111414. Second baffle joint; 1114141. Baffle groove; 112. Fuselage skin; 12. Tail port cover; 13. Head cover; 131. Hinge; 132. Lock; 133. Piston tube support; 1331. Hexagonal groove; 1332. Reinforcing rib; 1333. Piston tube through hole; 14. Door; 141. Door latch; 1411. Reinforcing plate; 1412. Lock hook; 1413. Latch; 142. Door body; 15. Front port cover; 16. Rear port cover; 2. Unmanned aerial vehicle (UAV). Detailed Implementation

[0049] To better understand this utility model, the following embodiments further illustrate the content of this utility model, but the content of this utility model is not limited to the following embodiments.

[0050] like Figure 1 As shown, the fuselage structure 1 of the cargo drone of this utility model is arranged under the wing, and the landing gear is connected to the lower part of the fuselage to support the fuselage. The tail of the fuselage is connected to the horizontal tail and the vertical tail. The fuselage structure 1 provides space for cargo and equipment, fixes the cargo, and bears various loads during flight.

[0051] like Figure 2 and 3As shown, the cargo drone fuselage structure 1 consists of a fuselage body 11, a tail hatch 12, a nose cone 13, a hatch 14, a front hatch 15, and a rear hatch 16. The fuselage body 11 serves as the main load-bearing structure, bearing the main load of the fuselage. Internally, it provides space for accommodating cargo and equipment, and provides interfaces for securing cargo. The tail hatch 12 provides a maintenance channel for tail system equipment and a channel for inspecting the tail structure. Made of carbon fiber composite material, the tail hatch 12 is connected to the fuselage body 11 via detachable fasteners, allowing for removal and installation from the outside of the fuselage body 11. The fuselage body 11 has a square, straight section in the central area, providing high volume utilization. The uniform cross-section structure allows for the interchangeability of circumferential parts, and a single mold can form parts in multiple locations, reducing manufacturing costs.

[0052] The hood 13 is a head-opening structure connected to the fuselage body 11 via a hinge. It can be lifted upwards. When transporting large, slender objects that cannot pass through the hatch 14 into the fuselage body 11, they can be loaded into the fuselage body 11 through the hood 13. The hatch 14 is designed on one side of the fuselage body 11, providing a normal passage for transporting goods. The hatch 14 is a detachable structure, which avoids obstructing the opening of the hatch 14 after it is connected to the fuselage body 11, allowing the largest possible amount of goods to be loaded into the fuselage body 11 through the door. The front cover 15 and the rear cover 16 are designed on the upper part of the machine body, which facilitates the maintenance of the equipment mounted on the equipment mounting plate, improves maintenance convenience, and reduces maintenance costs. The front cover 15 and the rear cover 16 are connected to the machine body 11 by a latch, which can be easily opened and closed. The main body of the front cover 15 and the rear cover 16 is a carbon fiber composite foam sandwich structure, preferably PMI foam, with a preferred thickness of 5mm. This gives the covers high rigidity and prevents them from deforming due to aerodynamic forces. At the same time, fewer latches can be used to lock the covers.

[0053] like Figure 4As shown, the fuselage body 11 consists of a fuselage frame 111 and a fuselage skin 112. The fuselage frame 111 constitutes the main load-bearing structure and bears the main loads. At the same time, the fuselage frame 111 also bears concentrated internal forces in some areas. The fuselage frame 111 consists of circumferential members 1112 and longitudinal members 1111. The longitudinal members 1111 bear bending and tensile / compressive loads, while the circumferential members 1112 bear shear forces. The fuselage frame 111 provides support for the fuselage skin 112 and is bonded to the fuselage skin 112 with structural adhesive. In some areas with greater stress, fasteners and structural adhesive are used for a mixed connection to ensure load-bearing capacity and reliability. The fuselage skin 112 is an aerodynamic surface that maintains the shape of the fuselage structure and ensures it does not deform during flight. The fuselage skin 112 is divided into two parts, left and right, at the mid-surface of the fuselage, connected by a strip. The strip is first bonded to one side of the skin with structural adhesive. After the frame is assembled, the skin side bonded to the strip is first bonded to the frame. Fasteners are installed in areas of high stress. Then, the other side of the skin is bonded to the other side of the frame with structural adhesive, forming the complete fuselage body. The fuselage skin 112 is a carbon fiber composite foam sandwich structure. The foam area avoids overlapping with the frame and areas with high curvature. Avoiding overlapping with the frame ensures non-destructive testing of the adhesive layer after bonding the fuselage frame 111 and the fuselage skin 112. In areas with high curvature, the foam may crack during molding, leading to defects.

[0054] like Figure 5 As shown, the longitudinal members 1111 of the fuselage frame 111 mainly consist of two floor beams 11111, two upper longitudinal beams 11112, and a vertical tail connecting rib 11113. The floor beams 11111 and the upper longitudinal beams 11112 are symmetrical structures and are connected to the circumferential members 1112 from front to back. The area where they are arranged is the area of ​​the fuselage where the stress is greater. In the rear part of the fuselage where the stress is less, the stress is only borne by the skin and the circumferential frame, which can meet the requirements. Floor beam 11111 is a machined aluminum alloy part, made of aluminum alloy 7050, with a heat treatment state of T7451. Lightening holes are designed on the web, and vertical reinforcing ribs are designed between the upper and lower edge strips to support floor 11141. Floor 11141 is connected to floor beam 11111. The upper edge strips of the left and right floor beams are kept at the same height plane. After supporting the floor, floor 11141 is kept in a horizontal state. When goods are placed on floor 11141, the goods can remain horizontal.

[0055] The fuselage circumferential component 1112 consists of multiple frames, arranged from rear to front as follows: first frame 11121, second frame 11122, support frame 11123, reinforcing frame 11124, door frame 11125, rear beam frame 11126, front beam frame 11127, and upper frame 11128. There are two door frames 11125 and two reinforcing frames 11124, located at the front and rear respectively. All frames are carbon fiber composite laminate structures. The reinforcing frame 11124, connected to the landing gear, bears a significant load and is relatively thick. The door frame 11125 provides reinforcement for the door opening, preventing deformation of the fuselage skin around the door and maintaining structural strength. The upper frame 11128 supports the front hatch 15, and the hinges of the front hatch 15 are connected to the upper frame 11128, providing strong support and concentrated hinge force. The front spar frame 11127 is connected back-to-back to the front spar of the wing using a combination of structural adhesive and fasteners. The rear spar frame 11126 is connected to the rear spar of the wing in a similar manner to the front spar frame 11127, using a combination of structural adhesive and fasteners. This allows the fuselage load to be directly transferred to the front and rear spars of the wing. The front spar frame 11127 and the rear spar frame 11126 are subjected to greater stress and are therefore thicker.

[0056] Floor 11141 is installed on floor beam 11111 and is connected to floor beam 11111 and the lower part of the frame by detachable fasteners. Floor 11141 needs to support the weight of goods and is made of carbon fiber composite foam sandwich panel, preferably PMI foam with a thickness of 5mm.

[0057] The equipment mounting plate 11131 is installed on the upper part of the fuselage and is supported by the upper half of the frame and the upper longitudinal beam 11112. The equipment plate is equipped with batteries, flight control computers, navigation, image transmission, data transmission and other equipment. In order to avoid the vibration of the UAV being transmitted to the equipment, the equipment mounting plate 11131 has high rigidity. The equipment mounting plate 11131 and the floor 11141 are made of carbon fiber composite foam sandwich panels of the same thickness, which can be cut from the same large plate to reduce manufacturing costs.

[0058] like Figure 6As shown, the helmet shroud 13 consists of a hinge 131, a latch 132, an airspeed tube support 133, and the helmet shroud body. The hinge 131 is connected to the helmet shroud body and the fuselage body 11 on both sides via fasteners. The helmet shroud 13 can rotate around the hinge axis, allowing it to be opened and enabling the installation of cargo or equipment from the front. The latch 132 can be locked and unlocked, securing the helmet shroud 13 to the fuselage body 11. The latch 132 works in conjunction with the hinge 131 to ensure a secure fixation between the helmet shroud 13 and the fuselage body 11. The airspeed tube support 133 connects to the airspeed tube, providing support and ensuring the airspeed tube's axis is aligned with the flight direction. The hood body is a carbon fiber composite foam sandwich structure, with PMI foam preferred and a thickness of 10mm to ensure that the hood has a large rigidity and prevent deformation. Because the curvature of the hood is large, if the rigidity is low, the deformation will be large, which may cause the hood to not close properly, or the gap and surface difference between the hood and the fuselage skin after closing to be too large.

[0059] like Figure 7 As shown, the pitot tube support 133 is a machined aluminum alloy part, preferably made of 7050 aluminum alloy, and preferably heat-treated to T7451. It features a hexagonal groove 1331, a reinforcing rib 1332, and a pitot tube through-hole 1333. The through-hole 1333 allows the circular pitot tube to pass through. The outer side of the circular tube at the tail end of the pitot tube is threaded. After being inserted into the fuselage through the through-hole 1333, an external hexagonal nut is installed in the hexagonal groove 1331. The inner thread connects to the pitot tube. The hexagonal groove 1331 effectively prevents the nut from rotating and provides space for it. When the thread is tightened, the pitot tube is fixed. The reinforcing rib 1332 strengthens the pitot tube support 1333, improving structural rigidity and preventing deformation under stress that could affect the accuracy of the pitot tube axis.

[0060] like Figure 8 As shown, the hatch 14 is a detachable structure, allowing for the loading and unloading of larger cargo volumes without obstruction. The hatch 14 consists of a door latch 141, a latch 132, and a door body 142. The door latch 141 is a separable structure, and the latch is the same model as the latch used in the hood, maintaining the same latch model reduces procurement and subsequent replacement costs. The door body 142 is a carbon fiber composite foam sandwich structure with high rigidity; PMI foam is preferred, with a preferred thickness of 5mm.

[0061] like Figure 9As shown, the door latch 141 consists of a reinforcing plate 1411, a locking hook 1412, and a locking bolt 1413. The reinforcing plate 1411 is connected to the door body 142. Due to the need to reduce structural weight, the door body 142 is relatively thin. When connecting the locking hook 1412, it is easily damaged by the rivets of the latch. Therefore, a reinforcing plate 1411 is added to the connection area to connect with the door body 142, increasing the thickness at the connection with the locking hook 1412 and increasing strength. The locking hook 1412 is connected to the reinforcing plate 1411, and the locking bolt 1413 is connected to the fuselage body 11. The door 14 is fixed by the cooperation of the latch 132 and the locking bolt 1413. The installation method of the door 14 is as follows: the locking hook 1412 of the door 14 is put onto the locking bolt 1413, and then the lower latch is pressed. The latch 132 causes the door to deform downward, generating force to lock the door 14. The hatch 14 is opened by releasing the lower latch 132, lifting the hatch body 142 upwards by hand, thus separating the latch 1412 from the bolt 1413, and removing the hatch.

[0062] like Figure 10 As shown, the vertical tail connecting rib 11113 is a machined aluminum alloy part, preferably made of 7050 aluminum alloy, and preferably heat treated to T7451. It features a vertical tail beam insertion hole 111131 and a fuselage frame connecting edge 111132. The vertical tail tube beam is inserted into the vertical tail beam insertion hole 111131 to fix the vertical tail and bear its main load. Therefore, the area around the vertical tail beam insertion hole 111131 is reinforced with multiple reinforcing ribs. Since the vertical tail needs to be disassembled quickly, the vertical tail beam insertion hole 111131 and the vertical tail tube beam are in contact fit, and the axes of the two holes are in the same direction, thus meeting the insertion requirements of the vertical tail. The fuselage frame connecting edge connects to the first and second frames using structural adhesive.

[0063] like Figure 11 As shown, after the cargo is installed from the hatch 14 onto the fuselage floor 11141, front and rear baffles 111412 are designed to prevent the cargo from moving inside the fuselage. These baffles 111412 are fixed to the floor body 111411 using a first baffle connector and a second baffle connector. The baffles 111412 are made of carbon fiber composite laminate. The first baffle connector 111413 and the second baffle connector 111414 are both machined aluminum alloy parts, preferably made of 7050, and preferably heat-treated to T7451. The first baffle connector 111413 and the second baffle connector 111414 are connected to the floor body 111411 using detachable fasteners. When installing longer cargo, they can be disassembled to keep the floor 11141 flat from front to back.

[0064] like Figure 12As shown, the second baffle joint 111414 is designed with a retaining groove 1114141. When the goods are loaded between the two baffles 111412, in order to prevent the goods from swaying left and right during transportation, a hoop rope can be passed through the retaining groove 1114141 of the front and rear second baffle joints 111414 to tighten the goods and prevent them from swaying.

[0065] like Figure 13 As shown, the connection methods of the front beam frame 11127, the rear beam frame 11126, and the upper longitudinal beam 11112 are similar. This example only describes one connection. The rear beam frame 11126 has a frame joint 111261 on its back. One side is connected to the web of the rear beam frame 11126 by fasteners, and the other side is connected to the upper longitudinal beam 11112 and the lower beam support joint 111121 by fasteners. The design of the beam support joint 111121 and the frame joint 111261 can effectively improve the rigidity of the connection area, increase the number of fasteners, and improve the reliability of the connection. Both the beam support joint 111121 and the frame joint 111261 are machined aluminum alloy parts, preferably made of 7050, and preferably heat treated in T7451 condition. The beam support joint 111121 is first glued to the upper longitudinal beam 11112, and then fastened to the frame joint 111261 and the rear beam frame 11126. In this example, the fasteners are bolt and nut connections.

[0066] like Figure 14 As shown, the first frame 11121 and the second frame 11122 are connected to the vertical tail docking rib 11113, supporting the vertical tail docking rib 11113. The webs of the first frame 11121 and the second frame 11122 are connected to the front and rear fuselage frame connecting edges of the vertical tail docking rib 11113 using structural adhesive. After the vertical tail tube beam is connected to the vertical tail docking rib 11113, it bears the load transmitted by the vertical tail docking rib 11113. At the same time, the first frame 11121 and the second frame 11122 support the thickness of the fuselage skin and prevent the fuselage skin from buckling under stress.

[0067] like Figure 15 and 16 As shown, since the circumferential member 1112 and the longitudinal member 1111 intersect when connected, the longitudinal member 1111 remains a continuous structure, while the circumferential member 1112 is divided into parts at the intersection. This example takes the reinforcing frame 11124 as an example. The reinforcing frame 11124 is divided into two parts, namely the main frame 111241 and the bottom frame 111242, which are connected to the flange and web of the floor beam 11111 respectively. The floor beam 11111 has a "C" shaped cross section with the flange facing inward. Therefore, the flange of the bottom frame 111242 in the connection area with the floor beam 11111 is designed to be recessed and connected to the inner side of the flange of the floor beam 11111. The main frame 111241 is connected to the outer side of the web of the floor beam.

[0068] This utility model relates to a fuselage structure applied to small and medium-sized electric vertical takeoff and landing (VTOL) compound-wing cargo UAVs. The fuselage is a non-pressurized structure, designed in a square shape, and consists of a main fuselage body, a nose cone, a front hatch, a rear hatch, a door, and a tail hatch. The nose cone serves as both a maintenance access point and a cargo loading / unloading access point. The front, rear, and tail hatches serve as maintenance access points for equipment, facilitating maintenance and structural inspection of the internal equipment. The door serves as the cargo loading / unloading access point. The main fuselage body consists of a fuselage frame and fuselage skin. The fuselage frame comprises longitudinal members, circumferential members, a floor, and an equipment mounting plate. The fuselage frame supports the fuselage skin and bears the main load, while the fuselage skin maintains the aerodynamic shape and transmits aerodynamic forces to the fuselage frame. The floor and equipment mounting plate are connected to the longitudinal and circumferential members via fasteners. Cargo is placed on the floor, and baffles are installed in the door area to prevent cargo movement. The front beam frame, rear beam frame and upper longitudinal beam are connected by beam support joints and frame joints to improve the connection strength. It features high space utilization, reliable cargo fixing, convenient maintenance, high strength and low cost.

[0069] The fuselage frame of this invention is a three-dimensional cage structure composed of circumferential and longitudinal members, resulting in high strength. An openable hood is designed to accommodate longer cargo. The door is a removable structure, which does not occupy door opening space during loading and unloading, allowing for the side loading of larger items. Cargo baffles are designed on the floor to prevent cargo from shifting forward or backward. The second baffle joint features a groove for securing the hoop rope, preventing lateral movement of cargo. The pitot tube support on the hood has a hexagonal slot for securing the nut connecting to the pitot tube. The connection between the upper longitudinal beam and the rear beam frame utilizes localized metal beam support joints and frame joints for reinforcement, distributing stress at the connection and increasing the number of fasteners. The vertical tail butt rib is designed with vertical tail beam insertion holes for connection to the vertical tail tube beam, with all holes facing the same direction to meet vertical tail insertion requirements. The frame maintains continuity of longitudinal components, while circumferential components are connected separately from longitudinal components, ensuring the main load-bearing components at the front and rear of the fuselage remain integral and possess better strength performance.

[0070] The specific embodiments of this utility model have been described above. It should be understood that this utility model is not limited to the specific embodiments described above, and those skilled in the art can make various modifications or variations within the scope of the claims, which do not affect the substantive content of this utility model.

Claims

1. A cargo drone fuselage structure, characterized in that: It includes the fuselage body (11), tail hatch (12), nose cone (13), hatch (14), front hatch (15) and rear hatch (16); The fuselage body (11) is composed of a fuselage frame (111) and a fuselage skin (112). The fuselage frame (111) provides support for the fuselage skin (112). The top and bottom of the fuselage frame (111) are respectively provided with an equipment mounting plate (11131) and a floor (11141). The fuselage frame (111) includes a longitudinal member (1111) for bearing bending and tensile / compressive loads and a circumferential member (1112) for bearing shear forces; The longitudinal member (1111) includes two floor beams (11111), two upper longitudinal beams (11112), and a vertical tail connecting rib (11113). The vertical tail connecting rib (11113) is provided with a vertical tail beam insertion hole (111131) and a fuselage frame connecting edge (111132). The circumferential member (1112) includes a first frame (11121), a second frame (11122), a support frame (11123), a reinforcing frame (11124), a door frame (11125), a rear beam frame (11126), a front beam frame (11127), and an upper half frame (11128) arranged along the longitudinal member (1111); The hinge of the front cover (15) is connected to the upper half frame (11128), the front beam frame (11127) is connected to the front beam of the wing, and the rear beam frame (11126) is connected to the rear beam of the wing. The first frame (11121) and the second frame (11122) are connected to the vertical tail docking rib (11113), and the webs of the first frame (11121) and the second frame (11122) are connected together with the front and rear fuselage frame connecting edge (111132) of the vertical tail docking rib (11113). The floor (11141) is mounted on the floor beam (11111) and is connected to the floor beam (11111) and the lower part of the frame in the circumferential member (1112) by fasteners; The equipment mounting plate (11131) is installed on the upper part of the machine body and is supported by the upper part of the frame in the circumferential component (1112) and the upper longitudinal beam (11112).

2. The fuselage structure of a cargo drone as described in claim 1, characterized in that: The frame of the circumferential component (1112) is made of carbon fiber composite material.

3. The cargo drone fuselage structure as described in claim 2, characterized in that: The head cover (13) consists of a hinge (131), a buckle (132) and a head cover body. The two sides of the hinge (131) are connected to the head cover body and the fuselage body (11) respectively by fasteners. The head cover (13) can rotate around the hinge axis.

4. The fuselage structure of a cargo drone as described in claim 3, characterized in that: The headgear (13) also includes an airspeed tube support (133), which has a hexagonal groove (1331), a reinforcing rib (1332) and an airspeed tube through hole (1333). The airspeed tube through hole (1333) allows the airspeed tube to pass through, and an external hexagonal nut is provided in the hexagonal groove (1331).

5. The fuselage structure of a cargo drone as described in claim 1, characterized in that: The hatch (14) is located on one side of the fuselage body (11), and the hatch (14) is a detachable hatch.

6. The fuselage structure of a cargo drone as described in claim 1, characterized in that: The hatch (14) consists of a door latch (141), a lock, and a door body (142). The door latch (141) consists of a reinforcing plate (1411), a locking hook (1412), and a locking bolt (1413). The reinforcing plate (1411) is connected to the door body (142), the locking hook (1412) is connected to the reinforcing plate (1411), and the locking bolt (1413) is connected to the fuselage body (11). The hatch (14) is fixed by the cooperation of the latch and the locking bolt (1413).

7. The fuselage structure of a cargo drone as described in claim 1, characterized in that: The floor (11141) includes a floor body (111411) and a baffle (111412) disposed on the floor body (111411). The baffle (111412) is fixed to the floor body (111411) through a first baffle joint (111413) and a second baffle joint (111414).

8. The fuselage structure of a cargo drone as described in claim 1, characterized in that: The second baffle joint (111414) is provided with a baffle groove (1114141).

9. The fuselage structure of a cargo drone as described in claim 1, characterized in that: The rear beam frame (11126) is provided with a frame joint (111261) on the back. One side of the frame joint (111261) is connected to the web of the rear beam frame (11126) by fasteners, and the other side is connected to the upper longitudinal beam (11112) and the lower beam support joint (111121) by fasteners. The beam support joint (111121) is first glued to the upper longitudinal beam (11112), and then connected to the frame joint (111261) and the rear beam frame (11126) by fasteners.

10. The fuselage structure of a cargo drone as described in claim 1, characterized in that: The reinforcing frame (11124) includes a main frame (111241) and a bottom frame (111242), which are respectively connected to the edge strip and web of the floor beam (11111).

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