Fuselage framework and fuselage structure of light solar unmanned aerial vehicle

Abstract

The utility model relates to the technical field of aircrafts, in particular to a fuselage framework and a fuselage structure of a light solar unmanned aerial vehicle. The fuselage framework comprises an annular part and a connecting part which are made of a composite material, and the annular part comprises an outer annular frame and an inner annular frame; the connecting part comprises a front-section longitudinal beam and a rear-section longitudinal beam; the multiple outer annular frames and the multiple inner annular frames are sequentially arranged in the length direction of the fuselage, the multiple front-section longitudinal beams and the multiple rear-section longitudinal beams are annularly arranged in the fuselage, the front-section longitudinal beams are connected with the outer annular frames of the outer ring to form a front functional cabin section, and the rear-section longitudinal beams are connected with the inner annular frames of the inner ring to form a rear machine tail cabin section; the outer annular frame at the tail end of the front functional cabin section is connected with the inner annular frame at the head end of the rear tail cabin section, and the front functional cabin section and the rear tail cabin section are connected together. According to the fuselage skeleton and the fuselage structure comprising the fuselage skeleton disclosed by the utility model, the weight is obviously reduced, the fuselage strength is enhanced, and the flight stability is improved.

Description

Technical Field

[0001] This utility model relates to the field of aircraft technology, specifically to a lightweight solar-powered unmanned aerial vehicle (UAV) fuselage frame and fuselage structure. Background Technology

[0002] Solar-powered drones have broad application prospects in numerous fields. For example, drones carrying communication payloads can provide routine, long-distance, high-bandwidth communication services to mobile users on the ground, at sea, and in the air. By providing communication relay and broadband access functions, they can compensate for the shortcomings of land-based and satellite-based communication networks, offering a new approach to building a three-dimensional communication network. For instance, drones equipped with optoelectronic imaging, radar, and stereo mapping cameras can conduct wide-area, continuous detection and surveillance of fixed and moving targets on the ground, used for land resource surveys and environmental monitoring, agricultural surveillance, and marine management. Furthermore, drones equipped with atmospheric environmental monitoring sensors can excel in macroscopic observation of typhoons and hurricanes, acquiring information such as wind field distribution, turbulence intensity, and ozone distribution in the near-space layer, providing first-hand data for near-space atmospheric research and filling current gaps in space knowledge.

[0003] Several lightweight airframe technologies have been proposed in the prior art. For example, Chinese invention patent CN107972843A provides a lightweight, highly maintainable composite material structure system for unmanned aerial vehicles (UAVs). Except for a very few structures subjected to impact loads, all main load-bearing structures are made of composite materials. Compared with previous UAV structural technologies of this type, it cleverly utilizes the material properties of composite materials to meet the load-bearing and functional requirements of a small, high-speed UAV's all-composite material structure, achieving low cost and high maintainability. Another example is Chinese utility model patent CN207791131U, which provides a solar-powered UAV. Solar panels are installed in a receiving groove of a flexible filler. The flexible filler is made of foam material, which is lightweight, flexible, easy to process, and has a certain tensile and compressive strength. Utility Model Content

[0004] To circumvent the barriers of existing technologies, this utility model proposes a lightweight solar-powered drone's fuselage frame and structure. The fuselage frame is mainly composed of ring-shaped components and connecting components that are connected longitudinally and transversely to form a whole. Both the ring-shaped components and connecting components are made of composite materials. The overall structure is simple, significantly reducing weight while enhancing the body strength and improving flight stability.

[0005] First, this utility model provides a lightweight solar-powered drone fuselage frame.

[0006] The fuselage framework includes an annular component and a connecting component made of composite materials. The annular component includes an outer annular frame and an inner annular frame. The connecting component includes a front longitudinal beam and a rear longitudinal beam. A plurality of outer annular frames are arranged in sequence along the length direction of the fuselage. A plurality of front longitudinal beams are arranged circumferentially along the fuselage. After the front longitudinal beams are connected to the outer annular frames of the outer ring, they form a front functional cabin section. A plurality of inner annular frames are arranged in sequence along the length direction of the fuselage. A plurality of rear longitudinal beams are arranged circumferentially along the fuselage. After the rear longitudinal beams are connected to the inner annular frames of the inner ring, they form a rear tail cabin section. The outer annular frame at the end of the front functional cabin section is connected to the inner annular frame at the head of the rear tail cabin section, connecting the front functional cabin section and the rear tail cabin section together to form an entire fuselage framework.

[0007] Further, to better implement the present utility model, both the outer annular frame and the inner annular frame are square frames. Four front longitudinal beams are respectively connected to the four corners of the outer annular frame. Four rear longitudinal beams are respectively connected to the centers of the four side frames of the inner annular frame.

[0008] Further, to better implement the present utility model, a cross beam is added between the two lower front longitudinal beams among the four front longitudinal beams.

[0009] Further, to better implement the present utility model, the front functional cabin section is further provided with partitions connected to the outer annular frame and / or the front longitudinal beams, for forming accommodation spaces inside the front functional cabin section.

[0010] Further, to better implement the present utility model, the cross section of the outer annular frame is in a "T" shape.

[0011] Further, to better implement the present utility model, the cross section of the inner annular frame is in a "匚" shape.

[0012] Further, to better implement the present utility model, reinforcing ribs are provided on the inner wall of the outer annular frame.

[0013] Secondly, the present utility model provides a fuselage structure of a lightweight solar unmanned aerial vehicle.

[0014] The fuselage structure includes a framework, a nose cone front cover installed at the head of the framework, a fuselage skin covering the framework, and an equipment bracket for installing airborne equipment. The framework adopts the above-mentioned fuselage framework. The equipment bracket is installed inside the nose cone front cover and inside the front functional cabin section of the fuselage framework.

[0015] Further, to better implement the present utility model, the inside of the nose cone front cover is a nose cone cabin. Inside the front functional cabin section, a power supply cabin, an electrical cabin, and an equipment cabin are sequentially arranged from the nose to the tail. The inside of the rear tail cabin section is a rear fuselage cabin.

[0016] The nose cone cabin is used to install an omnidirectional antenna, a GNSS antenna, and an atmospheric environment sensor;

[0017] The power supply cabin is used to install an energy storage battery and a power controller;

[0018] The electrical appliance cabin is used to install an attitude and heading reference system (AHRS);

[0019] The equipment cabin is used to install an aircraft management computer;

[0020] The rear fuselage cabin is used to lay cables connecting to the tail fin.

[0021] Furthermore, in order to better implement the present utility model, an atmospheric machine support and a pressure-bearing platform are also provided; the atmospheric machine support, the pressure-bearing platform, and the equipment support, which are integrally in a "U" shape, are connected together and then installed in the nose cone cabin through connectors to fix the atmospheric environment sensor.

[0022] The present utility model has the following beneficial effects.

[0023] (1) The fuselage skeleton provided by the present utility model can solve the problems of complex fuselage skeleton structure, large fuselage weight, and cumbersome processing steps, and the skeleton structure is easy to disassemble and assemble.

[0024] (2) For the fuselage skeleton provided by the present utility model, both the outer ring frame and the inner ring frame are square frames, and the cross-section of the fuselage formed after covering the skin is square, which is convenient for parking on the ground usually and better fixing in the transport packaging box during transfer transportation; it is convenient to set access panels on the fuselage.

[0025] (3) The fuselage structure provided by the present utility model has a relatively large internal volume and is easy to carry multiple devices. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 It is a schematic diagram of the overall structure of the fuselage skeleton structure of the present utility model.

[0027] Figure 2 It is a schematic diagram of the assembly method of the outer ring frame, the front longitudinal beam, and the partition of the present utility model.

[0028] Figure 3 It is a schematic diagram of the assembly method of the inner ring frame and the rear longitudinal beam of the present utility model.

[0029] Figure 4 It is a schematic diagram of the state of the front functional cabin section of the fuselage skeleton of the present utility model with the fuselage skin wrapped outside and the equipment support built inside.

[0030] Figure 5 It is a schematic diagram of the state of installing the equipment support in the nose cone cabin of the present utility model.

[0031] Figure 6 This is a schematic diagram illustrating the assembly method of the equipment support, air compressor support, and pressure platform described in this utility model.

[0032] Figure 7 This is a schematic diagram of the assembly method of the outer annular frame, the front longitudinal beam, and the cross beam of this utility model.

[0033] Figure 8 This is a schematic diagram of the outer ring frame structure in this utility model.

[0034] Figure 9 This is a schematic diagram of the inner annular frame described in this utility model.

[0035] Figure 10 The present utility model Figure 9 Detailed view A of a partial cross-section of the inner annular frame.

[0036] Figure 11 This is a schematic diagram of the specific structure of the front longitudinal beam described in this utility model.

[0037] Figure 12 The present utility model Figure 11 Detailed view B of a partial cross-section of the front section of the longitudinal beam.

[0038] Figure 13 This is a schematic diagram showing the assembly position of the wing connected to the fuselage.

[0039] Among them, 110 is the outer ring frame; 120 is the front longitudinal beam; 130 is the crossbeam; 140 is the partition; 150 is the inner ring frame; 160 is the rear longitudinal beam; and 170 is the fuselage skin.

[0040] 100. Front cover of the nose cone; 200. Nose cone compartment; 300. Power supply compartment; 400. Electrical compartment; 500. Equipment compartment; 600. Aft fuselage compartment;

[0041] 4. Equipment support frame; 5. Air compressor support frame; 6. Pressure plate. Detailed Implementation

[0042] To more clearly illustrate the technical solutions of the embodiments of this utility model, the technical solutions of the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings. It should be understood that the described embodiments are only some embodiments of this utility model, not all embodiments, and therefore should not be regarded as a limitation on the scope of protection. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this utility model.

[0043] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "set up," "connected," and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.

[0044] Example 1:

[0045] This embodiment provides a lightweight solar-powered drone fuselage frame, such as... Figure 1 As shown, the fuselage frame includes annular components and connecting components made of composite materials. The annular components include an outer annular frame 110 and an inner annular frame 150. The connecting components include a front longitudinal beam 120 and a rear longitudinal beam 160. Multiple outer annular frames 110 and multiple inner annular frames 150 are arranged sequentially along the length of the fuselage. Multiple front longitudinal beams 120 and multiple rear longitudinal beams 160 are arranged circumferentially along the fuselage. The front longitudinal beam 120 connects with the outer annular frame 110 to form the forward functional compartment. The rear longitudinal beam 160 connects with the inner annular frame 150 to form the rear tail compartment. The outer annular frame 110 at the end of the forward functional compartment connects with the inner annular frame 150 at the beginning of the rear tail compartment, thus connecting the forward functional compartment and the rear tail compartment together.

[0046] In this embodiment, all annular components and connecting components are made of composite materials; that is, all annular components and connecting components are composite parts. During assembly, the forward functional section and the aft tail section are assembled first. The forward functional section is mainly composed of multiple outer annular frames 110 and multiple forward longitudinal beams 120 connected together using a film mixture. The multiple outer annular frames 110 are arranged sequentially along the length of the fuselage, and the multiple forward longitudinal beams 120 are arranged circumferentially along the fuselage. Figure 2 As shown, multiple outer annular frames 110 and multiple front longitudinal beams 120 are connected to form a cage structure, creating an internal storage space. Similarly, the aft tail section is mainly composed of multiple inner annular frames 150 and multiple rear longitudinal beams 160 connected together with a film. The inner annular frames 150 are arranged sequentially along the length of the fuselage, and the rear longitudinal beams 160 are arranged circumferentially along the fuselage. Figure 3 As shown, multiple inner annular frames 150 and multiple rear longitudinal beams 160 are connected to form a cage structure, creating an internal storage space. After the forward functional section and the rear tail section are assembled separately, they are then assembled into a single unit to form a complete fuselage frame.

[0047] The main components of the aforementioned fuselage frame are ring-shaped parts and connecting parts made of composite materials. These ring-shaped parts and connecting parts largely utilize a combination of room-temperature adhesive bonding and bolt connections, reducing or even eliminating the use of rivets and bolts commonly found in composite components. The extensive use of composite materials serves two purposes: firstly, leveraging their superior load-bearing capacity to reduce material usage; and secondly, utilizing their lightweight properties to ensure lift during flight in the thin air at high altitudes. The fewer types of components and simpler connection structure of the fuselage frame significantly reduce weight while enhancing airframe strength and improving flight stability. In another specific embodiment, such as... Figure 2 , Figure 3 As shown, both the outer annular frame 110 and the inner annular frame 150 are square frames. Four front longitudinal beams 120 are connected to the four corners of the outer annular frame 110, and four rear longitudinal beams 160 are connected to the center of the four sides of the inner annular frame 150. The shapes of the outer annular frame 110 and the inner annular frame 150 determine the contour of the key cross-section of the fuselage frame.

[0048] If the outer annular frame 110 and the inner annular frame 150 are circular frames, then the cross-sectional profile of the assembled fuselage frame will be circular or near-circular. In this embodiment, for example... Figure 2 , Figure 3 , Figure 9 , Figure 10 As shown, the outer annular frame 110 and the inner annular frame 150 are designed as square annular frames, and the assembled fuselage frame has a square or near-square cross-section, with the four side walls of the fuselage being planar structures. Therefore, the square cross-section fuselage has the following advantages over the circular cross-section fuselage: 1. It is easier to park on the ground during normal operation; 2. It is easier to secure the fuselage in the transport packaging box during relocation and transportation; 3. It is easier to install a cover; 4. It is easier to install a flat equipment bracket 4.

[0049] It should be noted that perfect circles and perfect squares are ideal states. Deviations are common in actual processing, and it is difficult to process perfect circles and squares. Therefore, it is more accurate to describe the horizontal outlines of the outer ring frame 110 and the inner ring frame 150 as quasi-circular and quasi-square.

[0050] Furthermore, taking any cross-section of the fuselage frame as a reference plane, the installation positions of the four forward longitudinal beams 120 differ from the installation positions of the four aft longitudinal beams 160 by 45 degrees. This design can balance the weight of the fuselage frame and meets the design requirements that the forward functional section is mainly used for installing airborne equipment and the aft tail section is mainly used for installing the tail fin.

[0051] In another specific implementation, such as Figure 7As shown, a crossbeam 130 is added between the two lower front longitudinal beams 120 among the four front longitudinal beams 120. The strength and stiffness of the fuselage skeleton are enhanced by adding an "I"-shaped crossbeam or a "C"-shaped crossbeam.

[0052] In another specific embodiment, the front functional cabin section is further provided with a partition 140 connected to the outer annular frame 110 and / or the front longitudinal beam 120, for forming an accommodation space inside the front functional cabin section. From the nose to the tail, the multiple functional cabins are respectively: the nose cone cabin 200, the power cabin 300, the electrical cabin 400, and the equipment cabin 500.

[0053] In another specific embodiment, as Figure 8 shown, the cross-section of the outer annular frame 110 is "T"-shaped. A circular boss is formed in the middle of the inner wall of the outer annular frame 110, facilitating positioning when assembling the front longitudinal beam 120 or the rear longitudinal beam 160. As Figure 11 、 Figure 12 shown, a limiting platform is provided at the end of the front longitudinal beam 120, facilitating positioning and installation. The outer annular frame 110 is sleeved on the outer circles of the four front longitudinal beams 120.

[0054] In another specific embodiment, as Figure 9 、 Figure 10 shown, the cross-section of the inner annular frame 150 is "匚"-shaped. The inner annular frame 150 is installed on the inner circles of the four rear longitudinal beams 160.

[0055] In another specific embodiment, the inner wall of the outer annular frame 110 is provided with reinforcing ribs.

[0056] In another specific embodiment, for the annular component at the end of the rear tail cabin section, the inner annular frame 150 can be used alone, the outer annular frame 110 can be used alone, or the outer annular frame 110 and the inner annular frame 150 can be stacked and used together.

[0057] Any of the above specific embodiments can solve the problems of complex fuselage skeleton structure, resulting in a relatively large fuselage weight and cumbersome processing steps, and also reduce the fuselage weight by simplifying the fuselage skeleton.

[0058] Embodiment 2:

[0059] Based on Embodiment 1, this embodiment provides a fuselage structure of a lightweight solar unmanned aerial vehicle.

[0060] The fuselage structure, as Figure 4As shown in the figure, it includes a framework, a nose cone front cover 100 installed at the front end of the framework, a fuselage skin 170 wrapped around the framework, and an equipment support 4 for installing airborne equipment. The framework adopts the fuselage framework described in Embodiment 1. The equipment support 4 is installed inside the nose cone front cover 100 and inside the front functional cabin section of the fuselage framework.

[0061] When the outer annular frame 110 and the inner annular frame 150 adopt square annular frames, the fuselage skin 170 wraps around the fuselage framework to form a square tube-shaped composite thin shell structure. During assembly, the annular components and connecting components are first connected into a whole by adhesive film mixing, and then secondarily connected to the fuselage skin 170 by adhesive film mixing.

[0062] As Figure 4 shown, the interior of the nose cone front cover 100 is the nose cone cabin 200; as Figure 13 shown, inside the front functional cabin section, there are successively arranged a power supply cabin 300, an electrical equipment cabin 400, and an equipment cabin 500 from the nose to the tail; the interior of the rear tail cabin section is the rear fuselage cabin 600.

[0063] The nose cone cabin 200 is used for installing omnidirectional antennas, GNSS antennas, and atmospheric environment sensors;

[0064] The power supply cabin 300 is used for installing energy storage batteries and power controllers;

[0065] The electrical equipment cabin 400 is used for installing an attitude and heading reference system;

[0066] The equipment cabin 500 is used for installing an aircraft management computer;

[0067] The rear fuselage cabin 600 is used for laying cables connecting to the tail fin.

[0068] As Figure 4 、 Figure 5 shown, flat frame-type equipment supports 4 are provided in the nose cone cabin 200, the power supply cabin 300, the electrical equipment cabin 400, and the equipment cabin 500. The airborne equipment configured in each functional cabin is fixedly installed through the equipment support 4.

[0069] In another specific embodiment, as Figure 6 shown, an atmospheric machine support 5 and a pressure-bearing platform 6 are further provided inside the nose cone cabin 200. The atmospheric machine support 5, the pressure-bearing platform 6, and the equipment support 4, which are integrally in a "U" shape, are connected into a whole and then installed in the nose cone cabin 200 through connecting parts for fixing the atmospheric environment sensor. The connecting parts here usually adopt commercially available bolt and nut assemblies. The bolts, nuts, and gaskets in the bolt and nut assemblies are usually directly purchased as standard parts, while the annular components and connecting components are made of composite materials, with light self-weight but high structural strength and high production and assembly efficiency.

[0070] The fuselage structure described in this embodiment can serve as an ideal airborne platform for performing tasks such as reconnaissance and surveillance, atmospheric monitoring, and communication relay.

[0071] Example 3:

[0072] Near-space solar-powered unmanned aerial vehicles (UAVs) experience significant deformation of their flexible wings under normal flight conditions, leading to a redistribution of aerodynamic loads. This aerodynamic / structural coupling significantly impacts flight speed and performance, placing higher demands on the strength and rigidity of the airframe. Furthermore, near-space solar-powered UAVs require a high payload capacity.

[0073] This embodiment, based on Embodiment 1 or Embodiment 2, provides a near-space solar-powered unmanned aerial vehicle (UAV) with a total length of approximately 10 meters. The UAV adopts the fuselage structure described in Embodiment 2, with wings and a tail mounted on the fuselage. The solar energy conversion components are mounted on the wings. The fuselage houses an omnidirectional antenna, a GNSS antenna, an atmospheric environment sensor, an energy storage battery, a power controller, an attitude measurement system, and a flight management computer. The solar energy conversion components are connected to the energy storage battery and the power controller, and the converted electrical energy can power other electrical devices.

[0074] The aforementioned equipment weighs a total of over ten kilograms and is concentrated in the forward functional section; while the aft tail section is mainly for connecting the tail section's cantilever. The aft fuselage compartment, aside from cables, typically does not house other equipment and does not carry excessive concentrated loads. Therefore, the aft tail section is structurally simpler than the forward functional section.

[0075] Specifically: the omnidirectional antenna, GNSS antenna, and atmospheric environment sensor are installed in the nose cone 200; the energy storage battery and power controller are installed in the power supply compartment 300; the attitude measurement instrument is installed in the electronics compartment 400; and the aircraft management computer is installed in the equipment compartment 500. The atmospheric environment sensor can be a temperature sensor, or a humidity sensor, smoke sensor, or other environmental element sensors. This is not a major improvement point in this embodiment, and can be configured according to actual needs, so it will not be described in detail.

[0076] Furthermore, the tail fin is mounted to the rear aft section of the aircraft via wing-body connecting bolts, and the tail fin mounting position is as follows: Figure 13 As shown. Figure 13 The boxed area indicates the location of the tail wing. Figure 13 The ellipse in the middle indicates the location of the wing-body connecting bolts.

[0077] Furthermore, the annular component at the end of the forward functional section and the annular component at the beginning of the aft tail section are the connecting parts, used to connect the forward functional section and the aft tail section into a whole.

[0078] Based on the fuselage structure described in Example 2, the near-space solar-powered UAV designed and manufactured in this embodiment can meet the basic performance requirements, and has a long flight time and high flight altitude.

[0079] The other parts of this embodiment are the same as those in Embodiment 1 or Embodiment 2, so they will not be described again.

[0080] The above description is merely a preferred embodiment of this application and is not intended to limit this application. Various modifications and variations can be made to this application by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this application should be included within the protection scope of this application.

[0081] It will be apparent to those skilled in the art that this application is not limited to the details of the exemplary embodiments described above, and that this application can be implemented in other specific forms without departing from the spirit or essential characteristics of this application. Therefore, the embodiments should be considered illustrative and non-limiting in all respects, and the scope of this application is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of equivalents of the claims are intended to be included within this application. No reference numerals in the claims should be construed as limiting the scope of the claims.

Claims

1. A lightweight solar-powered unmanned aerial vehicle (UAV) fuselage frame, comprising a ring-shaped component and connecting components made of composite materials, characterized in that, The annular component includes an outer annular frame (110) and an inner annular frame (150); the connecting component includes a front longitudinal beam (120) and a rear longitudinal beam (160); a plurality of outer annular frames (110) are arranged in sequence along the length direction of the fuselage, a plurality of front longitudinal beams (120) are arranged circumferentially along the fuselage, and after the front longitudinal beams (120) are connected to the outer annular frames (110) on the outer circle, a front functional cabin section is formed; a plurality of inner annular frames (150) are arranged in sequence along the length direction of the fuselage, a plurality of rear longitudinal beams (160) are arranged circumferentially along the fuselage, and after the rear longitudinal beams (160) are connected to the inner annular frames (150) on the inner circle, a rear tail cabin section is formed; the outer annular frame (110) at the end of the front functional cabin section is connected to the inner annular frame (150) at the head of the rear tail cabin section, connecting the front functional cabin section and the rear tail cabin section together to form an entire fuselage skeleton.

2. The fuselage frame of a lightweight solar-powered unmanned aerial vehicle according to claim 1, characterized in that, The outer annular frame (110) and the inner annular frame (150) are both square frames, and four front longitudinal beams (120) are respectively connected to the four corners of the outer annular frame (110), and four rear longitudinal beams (160) are respectively connected to the centers of the four side frames of the inner annular frame (150).

3. The fuselage frame of a lightweight solar-powered unmanned aerial vehicle according to claim 2, characterized in that, A cross beam (130) is added between the two lower front longitudinal beams (120) among the four front longitudinal beams (120).

4. The fuselage frame of a lightweight solar-powered drone according to claim 1, characterized in that, The front functional cabin section is further provided with a partition (140) connected to the outer annular frame (110) and / or the front longitudinal beam (120), for forming an accommodation space inside the front functional cabin section.

5. The fuselage frame of a lightweight solar-powered unmanned aerial vehicle according to claim 1, characterized in that, The cross section of the outer annular frame (110) is in a "T" shape.

6. The fuselage frame of a lightweight solar-powered unmanned aerial vehicle according to claim 1, characterized in that, The cross section of the inner annular frame (150) is in a "匚" shape.

7. The fuselage frame of a lightweight solar-powered unmanned aerial vehicle according to claim 1, characterized in that, Reinforcing ribs are provided on the inner wall of the outer annular frame (110).

8. A lightweight solar-powered unmanned aerial vehicle (UAV) fuselage structure, comprising a frame, a nose cone front cover (100) mounted at the front end of the frame, a fuselage skin (170) covering the frame, and an equipment bracket (4) for mounting onboard equipment, characterized in that, The skeleton adopts the fuselage skeleton as described in any one of claims 1-7; the equipment support (4) is installed inside the nose cone front cover (100) and inside the front functional cabin section of the fuselage skeleton.

9. The fuselage structure of a lightweight solar-powered unmanned aerial vehicle according to claim 8, characterized in that, The inside of the nose cone front cover (100) is a nose cone cabin (200); inside the front functional cabin section, a power cabin (300), an electrical cabin (400), and an equipment cabin (500) are sequentially arranged from the nose to the tail; the inside of the rear tail cabin section is a rear fuselage cabin (600); The nose cone cabin (200) is used for installing an omnidirectional antenna, a GNSS antenna, and an atmospheric environment sensor; The power cabin (300) is used for installing an energy storage battery and a power controller; The electrical cabin (400) is used for installing an attitude and heading reference system; The equipment cabin (500) is used for installing an aircraft management computer; The rear fuselage cabin (600) is used for laying cables connecting to the tail wing.

10. The fuselage structure of a lightweight solar-powered unmanned aerial vehicle according to claim 9, characterized in that, An atmospheric machine support (5) and a pressure-bearing platform (6) are further provided; the atmospheric machine support (5), the pressure-bearing platform (6), and the equipment support (4) which are integrally in a "几" shape are connected together and then installed in the nose cone cabin (200) through a connecting member, for fixing the atmospheric environment sensor.

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