Cage type exoskeleton light-weight fuselage structure of tandem double-rotor unmanned helicopter
The cage-like exoskeleton structure with carbon fiber tubular main beams and hollowed-out clamps solves the problems of dead weight and difficult maintenance of drone fuselages, achieving improvements in lightweighting, maintainability, and structural strength, thereby increasing payload and endurance, while simplifying the maintenance process.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- XINGFAN (GUANGZHOU) AVIATION TECHNOLOGY CO LTD
- Filing Date
- 2025-06-16
- Publication Date
- 2026-04-24
AI Technical Summary
Existing tandem dual-rotor UAVs suffer from excessive dead weight and difficult maintenance. The separation of the triangular support frame from the decorative shell increases the ineffective dead weight, and maintenance requires destructive disassembly and assembly, resulting in high maintenance costs.
The main beam, which adopts a carbon fiber tube structure, forms a cage-like exoskeleton structure with an integrated hollowed-out clamp. The clamp serves both decorative and load-bearing functions. It is connected by bolts to achieve non-destructive assembly and disassembly. The main beam and clamp fit together precisely to avoid damage from drilling. It is combined with the transmission longitudinal shaft to drive the rotor.
It achieves lightweight fuselage, improves payload and range, simplifies maintenance procedures, reduces maintenance costs, and enhances torsional rigidity and flight stability.
Smart Images
Figure CN224159442U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of unmanned aerial vehicles (UAVs), and in particular to a cage-type exoskeleton lightweight fuselage structure for a tandem dual-rotor helicopter UAV. Background Technology
[0002] Existing tandem rotor drones generally use a triangular support structure as the main fuselage frame, covered with non-load-bearing decorative shell parts. This structure has significant drawbacks. On the one hand, the shell parts are only for decoration and cannot provide structural reinforcement, resulting in an excessively high proportion of ineffective dead weight, increasing the overall weight and affecting payload and range. On the other hand, the main fuselage relies on welding or riveting for fixation, requiring destructive disassembly and assembly during maintenance, leading to high maintenance costs and low efficiency.
[0003] In view of this, this technical solution proposes a cage-like exoskeleton lightweight fuselage structure for a tandem dual-rotor helicopter-UAV. It uses four carbon fiber tubes as main beams, connected by bolts to form three modular sections (composed of upper, lower, left, and right clamping plates forming a cage structure). The clamping plates serve both as decorative elements and structural load-bearing components, achieving integration of the shell and structure and completely eliminating dead weight. Furthermore, the clamping plate connections feature stoppers to improve assembly precision, avoiding the need for drilling holes in the carbon fiber tubes to protect the main beam strength, directly reducing the proportion of ineffective structure, and improving load capacity and endurance. The three modular sections, secured with bolts, allow for non-destructive assembly and disassembly, significantly simplifying maintenance and reducing costs. Utility Model Content
[0004] The present invention aims to at least partially solve one of the technical problems in the related technologies. Therefore, the main objective of this invention is to provide a lightweight, cage-like exoskeleton fuselage structure for a tandem dual-rotor helicopter-type UAV, aiming to address the problems of excessive dead weight and ineffective structure in existing UAV fuselage structures, as well as the inconvenience of maintenance and disassembly.
[0005] To achieve the above objectives, this utility model provides a cage-type exoskeleton lightweight fuselage structure for a tandem dual-rotor helicopter drone, comprising a drone body composed of a main beam, a first clamping plate, a second clamping plate, a third clamping plate, a fourth clamping plate, a first rotor body, and a second rotor body.
[0006] The first and second clamping plates are respectively disposed on both sides, and the third and fourth clamping plates are respectively engaged with the bottom and top of the first and second clamping plates. Each main beam member is disposed between the joints of the clamping plates.
[0007] The clamping plates and the main beam components work together to form a cage structure, with the first rotor body and the second rotor body respectively located on the top two sides of the cage structure.
[0008] As a further embodiment of this utility model, the main beam is a carbon fiber tube structure, and the number of main beams is at least 4 sets.
[0009] As a further embodiment of this utility model, the first clamping plate, the second clamping plate, the third clamping plate, and the fourth clamping plate are all integral perforated hollow clamping plate structures.
[0010] As a further embodiment of this utility model, the first clamping plate, the second clamping plate, the third clamping plate, and the fourth clamping plate are provided with recesses on both sides that match the outer contour of the main beam, and a through hole for fastening the fastener is provided on one side of the recess.
[0011] As a further embodiment of this utility model, the third and fourth clamping plates are provided with buckles on both sides to cooperate with the first and second clamping plates to fix the main beam. The buckles are claw-shaped structures with frames, and the buckles are provided with fixing holes on both sides to cooperate with the through holes.
[0012] As a further improvement of this utility model, the fixing element is a screw.
[0013] As a further embodiment of this invention, the first rotor body and the second rotor body are connected by a transmission longitudinal shaft.
[0014] The beneficial effects of this utility model are as follows:
[0015] This technical solution completely solves the problems of excessive dead weight and difficult maintenance caused by the separation of the triangular support frame and decorative shell in existing tandem dual-rotor UAVs. The skeleton is formed by at least four sets of carbon fiber tube main beams, combined with the integrated hollow design of the first, second, third, and fourth clamping plates. The clamping plates have both shell decoration and structural load-bearing functions, directly eliminating ineffective dead weight and improving payload and endurance. At the same time, the recesses on both sides of the clamping plates are used to precisely fit the contour of the main beams. Combined with the claw-shaped buckles of the third and fourth clamping plates and the through holes of the first and second clamping plates, the fasteners lock together to form a non-destructive connection, enabling quick assembly and disassembly and improving maintenance efficiency. In addition, the cage-like skeleton evenly distributes the load. With the integrated design of the first and second rotor bodies driven by the transmission longitudinal shaft, the torsional resistance and flight stability of the whole aircraft are significantly enhanced, systematically achieving lightweight, maintainability, and structural strength. Attached Figure Description
[0016] To more clearly illustrate the technical solutions of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the technical solutions of this utility model. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without creative effort.
[0017] Figure 1 This is a perspective view of the assembly of the various clamps and main beams of the drone body in this utility model.
[0018] Figure 2 This is a schematic diagram of the connection between the clamping plate and the main beam in this utility model.
[0019] Figure 3 This is an enlarged schematic diagram of the snap-fit structure in this utility model.
[0020] Figure 4 This is a top-view schematic diagram of the main body of the drone in this utility model.
[0021] Figure 5 This is a horizontal view of the main body of the drone in this utility model.
[0022] Figure 6 This is a schematic diagram of one side view of the main body of the drone in this utility model.
[0023] Figure 7 This is a schematic diagram of the overall structure of the drone body after assembly according to this utility model.
[0024] label name label name 1 drone body 110 Through hole 10 Main beam component 111 concave 11 First plywood 17 Fasteners 12 Second plywood 18 Buckle 13 Third plywood 19 Drive shaft 14 Fourth plywood 15 First rotor body 16 Second rotor body Detailed Implementation
[0025] as follows:
[0026] Please see the appendix Figure 1-7 ,
[0027] The main structure includes a UAV body (1) consisting of a main beam (10), a first clamping plate (11), a second clamping plate (12), a third clamping plate (13), a fourth clamping plate (14), a first rotor body (15), and a second rotor body (16). The first clamping plate (11) and the second clamping plate (12) are respectively located on both sides. The third clamping plate (13) and the fourth clamping plate (14) are respectively connected to the bottom and top of the first clamping plate (11) and the second clamping plate (12). Each main beam (10) is located between the clamping plates. Each clamping plate and the main beam (10) cooperate to form a cage structure. The first rotor body (15) and the second rotor body (16) are respectively located on the top sides of the cage structure.
[0028] The working principle is as follows:
[0029] Existing tandem rotor drones generally adopt a combination structure of triangular support frame and decorative shell, which results in two major defects in the fuselage. First, the shell only serves a decorative purpose and cannot provide structural support, resulting in an excessively high proportion of ineffective dead weight, which increases the overall weight of the aircraft and restricts its payload and endurance. Second, the main body of the fuselage relies on welding or riveting for fixation, which requires destructive disassembly and assembly during maintenance, resulting in low maintenance efficiency and high costs.
[0030] This technical solution uses at least four sets of carbon fiber tube structure main beams (10), with first clamps (11), second clamps (12) (located on both sides), and third clamps (13) and fourth clamps (14) (connecting the top and bottom), to form a cage structure through the precise fit of recesses (111) and buckles (18). The clamps are all one-piece perforated hollow design, which serves both as shell decoration and structural load-bearing function, realizing the integration of shell and structure, directly eliminating ineffective dead weight. At the same time, recesses (111) matching the contour of the main beam (10) are opened on both sides of the clamps, and are locked by claw buckles (18) (frame structure) and through holes (110) with fasteners (17) (screws (17)), which avoids damaging the strength by drilling holes in the main beam (10) and realizes non-destructive assembly and disassembly.
[0031] The assembly and disassembly process can be,
[0032] During assembly, the main beam (10) of the four sets of carbon fiber tube structures is embedded into the pre-set recesses (111) on both sides of the third clamping plate (13) and the fourth clamping plate (14). It is initially locked by the fastener (17). The recesses (111) of the first clamping plate (11) and the second clamping plate (12) are aligned with the main beam (10) so that it engages with the claw-shaped buckles (18) of the third clamping plate (13) and the fourth clamping plate (14). Then, screws (17) are inserted through the through holes (110) to lock and fix it. The first rotor body (15) and the second rotor body (16) are installed on both sides of the top of the cage structure and connected to the power system of the two through the transmission longitudinal shaft (19).
[0033] During disassembly, first remove the transmission longitudinal shaft (19), remove the first rotor body (15) and the second rotor body (16), loosen the fasteners (17) of the first clamping plate (11) and the second clamping plate (12), release the claw-shaped buckle (18) from engagement, lift the side plate upward, remove the screws (17) of the third clamping plate (13) and the fourth clamping plate (14), pull out the main beam (10) from the recess (111), and complete the disassembly.
[0034] Reference Appendix Figure 1 In a preferred embodiment of this utility model, the main beam (10) is a carbon fiber tube structure, and the number of main beams (10) is at least 4 sets.
[0035] In this technical solution, the main beam (10) adopts carbon fiber tube to achieve a balance between lightweight and high strength load bearing. The carbon fiber material significantly reduces the self-weight and provides excellent tensile and torsional performance. The four main beams (10) form a stable spatial cage frame, so that the load is evenly distributed through the recesses (111) and buckles (18) of the first clamping plate (11), the second clamping plate (12), the third clamping plate (13) and the fourth clamping plate (14), avoiding local stress concentration and ensuring that the whole machine maintains structural rigidity during flight.
[0036] Reference Appendix Figure 1 , 2 In a preferred embodiment of this utility model, the first clamping plate (11), the second clamping plate (12), the third clamping plate (13), and the fourth clamping plate (14) are all integral perforated hollow clamping plate structures.
[0037] In this design, the first clamping plate (11), the second clamping plate (12), the third clamping plate (13), and the fourth clamping plate (14) adopt an integrated perforated hollow design. By removing excess material, lightweighting is achieved while maintaining the structural strength of the clamping plate. The hollow structure enables the clamping plate to have both decorative and load-bearing functions, reducing ineffective dead weight and improving overall torsional resistance. The one-piece molding process avoids the weaknesses of welding or riveting, ensuring structural stability and simplifying the production process.
[0038] Reference Appendix Figure 2 , 3 In a preferred embodiment of the present invention, the first clamping plate (11), the second clamping plate (12), the third clamping plate (13), and the fourth clamping plate (14) are provided with recesses (111) on both sides that match the outer contour of the main beam (10), and a through hole (110) for fastening the fastener (17) is provided on one side of the recess (111).
[0039] Specifically, the recesses (111) on both sides of the first clamping plate (11), the second clamping plate (12), the third clamping plate (13), and the fourth clamping plate (14) are closely fitted to the outer contour of the main beam (10) to form a semi-enclosed snap-fit structure, which prevents the main beam (10) from shifting when under stress. The through hole (110) on one side of the recess (111) allows the fixing part (17) (screw (17)) to pass through and lock, rigidly connecting the clamping plate to the main beam (10). There is no need to drill holes in the main beam (10) to damage its strength. The precise positioning of the recess (111) enables rapid assembly.
[0040] Reference Appendix Figure 2 , 3In a preferred embodiment of this utility model, the third clamping plate (13) and the fourth clamping plate (14) are provided with buckles (18) on both sides to fix the main beam (10) in conjunction with the first clamping plate (11) and the second clamping plate (12). The buckles (18) are claw-shaped structures with frames, and the buckles (18) are provided with fixing holes on both sides to cooperate with the through holes (110).
[0041] Specifically, the frame-locking claw-shaped buckles (18) on both sides of the third clamping plate (13) and the fourth clamping plate (14) form a cylindrical space by combining the recesses (111) on both sides, which wraps around the outer wall of the main beam (10) to achieve quick positioning. The fixing holes on both sides of the buckle (18) are aligned with the through holes (110) of the first clamping plate (11) and the second clamping plate (12). After the fixing part (17) (screw (17)) is inserted, a three-point fixing is formed to prevent the main beam (10) from being rotated or displaced under force, and to achieve non-destructive disassembly and assembly between the clamping plates.
[0042] Reference Appendix Figure 2 In a preferred embodiment of this utility model, the fixing member (17) is a screw (17).
[0043] Specifically, screws (17) are general standard parts. Screws (17) are easy to purchase and replace and are inexpensive. Only a regular wrench is needed to lock or disassemble the clamp recess (111) and the buckle (18), so as to achieve non-destructive assembly and disassembly.
[0044] Reference Appendix Figure 1 In a preferred embodiment of the present invention, the first rotor body (15) and the second rotor body (16) are connected by a transmission longitudinal shaft (19).
[0045] In this scheme, the first rotor body (15) and the second rotor body (16) are connected by a transmission shaft (19) to achieve synchronous rotation of the two rotors driven by a single power source, avoiding the energy consumption and cost waste of independent dual motor drive, and enhancing the overall lift output through mechanical linkage. The transmission shaft (19) is directly integrated into the cage structure (or externally), simplifying power transmission, reducing system complexity, and improving wind resistance stability and load capacity.
[0046] The above are merely preferred embodiments of the present utility model and do not limit the patent scope of the present utility model. Any equivalent structural transformations made using the contents of the present utility model specification and drawings under the concept of the present utility model, or direct / indirect applications in other related technical fields, are included within the patent protection scope of the present utility model.
Claims
1. A lightweight airframe structure with a cage-like exoskeleton for a tandem dual-rotor helicopter-type unmanned aerial vehicle, characterized in that, include The main body of the UAV consists of a main beam, a first clamping plate, a second clamping plate, a third clamping plate, a fourth clamping plate, a first rotor body, and a second rotor body. The first and second clamping plates are respectively disposed on both sides, and the third and fourth clamping plates are respectively engaged with the bottom and top of the first and second clamping plates. Each main beam member is disposed between the joints of the clamping plates. The clamping plates and the main beam components work together to form a cage structure, with the first rotor body and the second rotor body respectively located on the top two sides of the cage structure.
2. The cage-type exoskeleton lightweight fuselage structure of the tandem dual-rotor helicopter UAV according to claim 1, characterized in that, The main beam is a carbon fiber tube structure, and the number of main beams is at least 4 sets.
3. The cage-type exoskeleton lightweight fuselage structure of the tandem dual-rotor helicopter UAV according to claim 1, characterized in that, The first, second, third, and fourth clamping plates are all one-piece perforated hollow clamping plate structures.
4. The cage-type exoskeleton lightweight fuselage structure of the tandem dual-rotor helicopter UAV according to claim 1, characterized in that, The first clamping plate, the second clamping plate, the third clamping plate, and the fourth clamping plate all have recesses on both sides that match the outer contour of the main beam, and a through hole for fastening the fastener is provided on one side of the recess.
5. The cage-type exoskeleton lightweight fuselage structure of the tandem dual-rotor helicopter UAV according to claim 4, characterized in that, The third and fourth clamping plates are provided with buckles on both sides to cooperate with the first and second clamping plates to fix the main beam. The buckles are claw-shaped structures with frames, and fixing holes that cooperate with the through holes are provided on both sides of the buckles.
6. The cage-type exoskeleton lightweight fuselage structure of the tandem dual-rotor helicopter UAV according to claim 4, characterized in that, The fastener is a screw.
7. The cage-type exoskeleton lightweight fuselage structure of the tandem dual-rotor helicopter UAV according to claim 1, characterized in that, The first rotor body and the second rotor body are connected by a transmission longitudinal shaft.