Sectional type unmanned aerial vehicle fuselage structure

Abstract

The sectional type unmanned aerial vehicle fuselage structure comprises a middle fuselage, a front fuselage and a rear fuselage, wherein the front fuselage and the rear fuselage are fixed to the two sides of the middle fuselage respectively. Connecting assemblies A, B and C are arranged on the two sides of the middle machine body and the opposite sides of the front machine body and the rear machine body respectively, and the connecting assemblies A, B and C comprise a plurality of connecting flanges A, B and C and a plurality of connecting lugs A, B and C; wherein the connecting flanges B and C and the connecting lugs B and C of the front fuselage and the rear fuselage correspond to the connecting flanges A and the connecting lugs A on the two sides of the middle fuselage respectively and are fixed through bolts. According to the sectional type unmanned aerial vehicle fuselage structure, the connecting assemblies A, B and C are designed, the connecting flanges and the connecting lugs are included, the fuselage parts are connected more simply and reliably in a bolt fixing mode, and the assembly precision and efficiency are improved. The standardized connection mode is convenient to realize automatic assembly, and the influence of human factors on the assembly quality is reduced.

Description

Technical Field

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

[0002] Against the backdrop of rapid development in modern technology, drone technology is making rapid progress, especially in the fields of transportation and rescue. The airframe structure design of unmanned helicopters is a key step in helicopter design. As the load-bearing center of the entire aircraft, the airframe structure must withstand the tensile, bending, and torsional loads generated by the rotor during flight, as well as the aerodynamic loads of the aircraft.

[0003] In the assembly process of traditional drone fuselages, the complex structure and high precision requirements of the connections between components make assembly difficult and prone to errors, affecting the overall performance and quality of the fuselage. Furthermore, the assembly process is time-consuming and has low production efficiency. Utility Model Content

[0004] This utility model proposes a segmented UAV fuselage structure, which solves the problems of complex fuselage structures, high precision requirements for the connection between components, high assembly difficulty, and easy assembly errors in the prior art.

[0005] The technical solution of this utility model is implemented as follows:

[0006] A segmented unmanned aerial vehicle (UAV) fuselage structure includes a middle fuselage and a front fuselage and a rear fuselage respectively fixed on both sides of the middle fuselage; connecting components A, B, and C are respectively provided on both sides of the middle fuselage and on the opposite sides of the front and rear fuselites. The connecting components A, B, and C include multiple connecting flanges A, B, and C and multiple connecting lugs A, B, and C; wherein the connecting flanges B and C and the connecting lugs B and C of the front and rear fuselites correspond to the connecting flanges A and connecting lugs A on both sides of the middle fuselage and are fixed with bolts.

[0007] Furthermore, the front fuselage includes two sets of symmetrically arranged front main beams, front sub-upper beams, and front sub-lower beams. The front sub-upper beams, front main beams, and front sub-lower beams on the same side are arranged from top to bottom and fixed by welding multiple reinforcing tubes. The front sub-upper beams, front main beams, and front sub-lower beams on adjacent sides are fixed by welding multiple reinforcing tubes.

[0008] Furthermore, the connecting flange B of the front fuselage and multiple connecting lugs B are respectively welded and fixed to the ends of the front main beam, the front sub-upper beam and the front sub-lower beam.

[0009] Furthermore, the middle fuselage includes two sets of symmetrically arranged middle main beams, middle auxiliary upper beams, and middle auxiliary lower beams. The middle auxiliary upper beams, middle main beams, and middle auxiliary lower beams on the same side are arranged from top to bottom and fixed by welding multiple reinforcing tubes. The middle auxiliary upper beams, middle main beams, and middle auxiliary lower beams on adjacent sides are fixed by welding multiple reinforcing tubes to a reducer frame. The reducer frame has an extension end on both sides of its bottom near the rear fuselage.

[0010] Furthermore, the connecting lugs A of the middle fuselage are respectively fixed to both ends of the middle main beam; multiple connecting lugs A of the middle fuselage are fixed to the middle auxiliary upper beam and the middle auxiliary lower beam near the front fuselage, and are also fixed to the extension ends on both sides of the bottom of the reducer frame.

[0011] Furthermore, the rear fuselage includes two sets of symmetrically arranged rear main beams and rear sub-lower beams. The rear main beams and rear sub-lower beams on the same side are arranged from top to bottom and fixed by welding with multiple reinforcing tubes. The rear main beams and rear sub-lower beams on adjacent sides are fixed by welding with multiple reinforcing tubes. The side of the rear sub-lower beam away from the middle fuselage is inclined upward and welded to the end of the rear main beam.

[0012] Furthermore, the connecting flange C and connecting lug C of the rear fuselage are respectively fixed to the rear main beam and the rear sub-lower beam at one end near the middle fuselage.

[0013] Furthermore, the connecting lug A of the middle fuselage is a double lug, while the connecting lugs B and C of the front and rear fuselage are single lugs, with the double lugs corresponding to the single lugs and clamping around the upper and lower sides of the single lugs.

[0014] The beneficial effects of the technical solution provided in this application are as follows:

[0015] This segmented UAV fuselage structure, with connecting components A, B, and C, includes multiple connecting flanges and lugs, secured by bolts. This simplifies and enhances the reliability of connections between the fuselage parts, improving assembly precision and efficiency. This standardized connection method facilitates automated assembly, reduces the impact of human error on assembly quality, and also simplifies quality control and inspection, ensuring the overall performance and reliability of the UAV fuselage. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in the embodiments 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 this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 This is a schematic diagram of the segmented unmanned aerial vehicle (UAV) fuselage structure of this utility model;

[0018] Figure 2 This is an exploded view of the segmented unmanned aerial vehicle (UAV) fuselage structure of this utility model;

[0019] Figure 3 This is a schematic diagram of the front fuselage of this utility model;

[0020] Figure 4 This is a schematic diagram of the fuselage of this utility model;

[0021] Figure 5 This is a schematic diagram of the rear fuselage of this utility model.

[0022] In the picture:

[0023] 10 Front fuselage, 11 Connecting assembly A, 12 Connecting flange B, 13 Connecting lug B, 14 Front main beam, 15 Front sub-upper beam, 16 Front sub-lower beam;

[0024] 20. Middle frame, 21. Connecting assembly A, 22. Connecting flange A, 23. Connecting lug A, 24. Middle main beam, 25. Middle secondary upper beam, 26. Middle secondary lower beam, 27. Reducer frame;

[0025] 30 Rear fuselage, 31 Connecting assembly A, 32 Connecting flange C, 33 Connecting lug C, 34 Rear main beam, 35 Rear sub-beam. Detailed Implementation

[0026] The technical solution of this utility model will be clearly and completely described below with reference to its embodiments. Obviously, the described embodiments are only some embodiments of this utility model, and not all embodiments. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of this utility model.

[0027] Reference Figure 1-5A segmented unmanned aerial vehicle (UAV) fuselage structure includes a middle fuselage 20 and a front fuselage 10 and a rear fuselage 30 fixed to its two sides. Connecting components A21, B11, and C31 are respectively provided on both sides of the middle fuselage 20 and on the opposite sides of the front fuselage 10 and the rear fuselage 30. Connecting components A21, B11, and C31 each include multiple connecting flanges A22, B12, and C32, and multiple connecting lugs A23, B13, and C33. The connecting flanges B12 and C32, and the connecting lugs B13 and C33 of the front fuselage 10 and the rear fuselage 30 correspond to the connecting flanges A22 and A23 on both sides of the middle fuselage 20 and are fixed with bolts. The connection between the front fuselage 10, the middle fuselage 20, and the rear fuselage 30 is achieved through the connecting flanges and connecting lugs in connecting components A21, B11, and C31. The design of the connecting flanges and connecting lugs allows for precise alignment of the components, which are then secured with bolts to ensure a robust and reliable connection. This segmented design not only simplifies the assembly process and improves production efficiency but also facilitates disassembly and maintenance when needed, further enhancing the practicality and flexibility of the drone.

[0028] In some embodiments, the front fuselage 10 includes two sets of symmetrically arranged front main beams 14, front auxiliary upper beams 15, and front auxiliary lower beams 16. The front auxiliary upper beams 15, front main beams 14, and front auxiliary lower beams 16 on the same side are arranged from top to bottom and welded together by multiple reinforcing pipes. The front auxiliary upper beams 15, front main beams 14, and front auxiliary lower beams 16 on adjacent sides are welded together by multiple reinforcing pipes. The middle fuselage 20 includes two sets of symmetrically arranged middle main beams 24, middle auxiliary upper beams 25, and middle auxiliary lower beams 26. The middle auxiliary upper beams 25, middle main beams 24, and middle auxiliary lower beams 26 on the same side are arranged from top to bottom and welded together by multiple reinforcing pipes. The middle auxiliary upper beams 25, middle main beams 24, and middle auxiliary lower beams 26 on adjacent sides are welded together by multiple reinforcing pipes. A reducer frame 27 is welded and fixed between the middle auxiliary upper beam 25, middle main beam 24, and middle auxiliary lower beam 26 on adjacent sides via multiple reinforcing pipes. The reducer frame 27 has extended ends on both sides of its bottom near the rear fuselage 30. The rear fuselage 30 includes two sets of symmetrically arranged rear main beams 34 and rear auxiliary lower beams 35. The rear main beams 34 and rear auxiliary lower beams 35 on the same side are arranged from top to bottom and fixed by welding multiple reinforcing pipes. The rear main beams 34 and rear auxiliary lower beams 35 on adjacent sides are fixed by welding multiple reinforcing pipes. The side of the rear auxiliary lower beam 35 away from the middle fuselage 20 is inclined upward and welded and fixed to the end of the rear main beam 34.

[0029] In the aforementioned technical solution, a robust frame structure is formed through the symmetrical arrangement of main beams, upper secondary beams, and lower secondary beams in the forward fuselage 10, mid-fuselage 20, and aft fuselage 30, along with the welding and fixing of reinforcing tubes. This structural design not only improves the strength and rigidity of each part but also ensures the balance of the fuselage through symmetrical arrangement. During flight, the forward fuselage 10 and mid-fuselage 20 can effectively withstand the rotor's thrust, bending moment, and torque loads while maintaining structural stability and reliability. The gearbox frame 27 of the mid-fuselage is welded and fixed between the upper secondary beam 25, the main secondary beam 24, and the lower secondary beam 26 of the mid-fuselage via reinforcing tubes, providing a stable mounting platform for key components such as the gearbox. The extended end design of the gearbox frame facilitates better connection with the aft fuselage 30, ensuring the continuity and stability of the entire fuselage structure. The rear sub-beam 35 of the rear fuselage 30 is inclined upwards on the side furthest from the mid-fuselage 20 and welded to the end of the rear main beam 34. This inclined design helps optimize aerodynamic performance, reduce flight drag, and enhance the connection strength between the rear fuselage and the mid-fuselage, ensuring the continuity and stability of the entire fuselage structure. This design improves assembly efficiency while ensuring the reliability and safety of the UAV under complex flight conditions, further enhancing the overall performance of the UAV.

[0030] In some embodiments, the connecting flange B12 and multiple connecting lugs B13 of the forward fuselage 10 are welded and fixed to the ends of the forward main beam 14, the forward upper sub-beam 15, and the forward lower sub-beam 16, respectively. By welding the connecting flange B12 and connecting lugs B13 to the ends of the forward main beam 14, the forward upper sub-beam 15, and the forward lower sub-beam 16, a robust connection node is formed. During assembly, these connection nodes are bolted to the connecting flange A22 and connecting lugs A23 of the mid-fuselage, ensuring a firm and reliable connection between the forward fuselage and the mid-fuselage. This welding method not only improves the strength of the connection points but also effectively transmits various loads during flight.

[0031] In some embodiments, the connecting lugs A23 of the middle fuselage 20 are respectively fixed to both ends of the middle main beam 24; the multiple connecting lugs A23 of the middle fuselage 20 are fixed to the middle auxiliary upper beam 25 and the middle auxiliary lower beam 26 near the front fuselage 10, and are also fixed to the extension ends on both sides of the bottom of the reducer frame 27.

[0032] Multiple robust connection nodes are formed by fixing connecting lugs A23 to both ends of the main beam 24, the upper and lower intermediate beams 25 and 26 near the front fuselage 10, and the extended ends on both sides of the bottom of the gearbox frame 27. During assembly, these connection nodes are bolted to the connecting flange B12 and connecting lugs B13 of the front fuselage, ensuring a firm and reliable connection between the middle fuselage and the front fuselage. This design not only improves the strength of the connection points but also effectively transmits various loads during flight, such as tension, bending moment, and torque, ensuring the stability and integrity of the entire fuselage structure during flight. The design of connecting lugs A23 on the extended ends on both sides of the bottom of the gearbox frame 27 further enhances the connection strength between the middle fuselage and the front fuselage, ensuring the continuity and stability of the entire fuselage structure, thereby improving the reliability and safety of the UAV under complex flight conditions.

[0033] In some embodiments, the connecting flange C32 and connecting lug C33 of the rear fuselage 30 are respectively fixed to the rear main beam 34 and the rear sub-lower beam 35 at one end near the middle fuselage 20.

[0034] A robust connection node is formed by fixing the connecting flange C32 and connecting lug C33 to one end of the rear main beam 34 and rear sub-lower beam 35 near the mid-fuselage 20. During assembly, these connection nodes are bolted to the connecting flange A22 and connecting lug A23 of the mid-fuselage, ensuring a firm and reliable connection between the rear fuselage and the mid-fuselage. This design not only improves the strength of the connection points but also effectively transmits various loads during flight, such as tension, bending moment, and torque, ensuring the stability and integrity of the entire fuselage structure during flight. In this way, the connection between the rear fuselage and the mid-fuselage is tighter, ensuring the continuity and stability of the entire fuselage structure, thereby improving the reliability and safety of the UAV under complex flight conditions.

[0035] In some embodiments, the connecting lug A23 of the mid-fuselage 20 is a double lug, while the connecting lugs B, C13, and C33 of the front fuselage 10 and rear fuselage 30 are single lugs. The double lugs correspond to the single lugs and clamp around the upper and lower sides of the single lugs. This clamping design of the double lugs not only enhances the strength of the connection points but also effectively disperses and transmits various loads during flight, reducing the risk of structural failure due to localized stress concentration, and further improving the reliability and safety of the UAV.

[0036] The double-ear connecting lug A23 of the mid-fuselage 20, in conjunction with the single-ear connecting lugs B13 and C33 of the front and rear fuselage 30, forms a more robust connection structure. During assembly, the double-ear lugs clamp onto the upper and lower sides of the single-ear lugs and are secured with bolts, ensuring a firm and reliable connection between the various fuselage parts. This design not only improves the strength of the connection points.

[0037] The above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.

Claims

1. A segmented unmanned aerial vehicle (UAV) fuselage structure, comprising a mid-fuselage (20) and a front fuselage (10) and a rear fuselage (30) respectively fixed on both sides thereof; characterized in that, The two sides of the middle fuselage (20) and the opposite sides of the front fuselage (10) and the rear fuselage (30) are respectively provided with connecting components A, B, C (21, 11, 31). The connecting components A, B, C (21, 11, 31) include multiple connecting flanges A, B, C (22, 12, 32) and multiple connecting lugs A, B, C (23, 13, 33). The connecting flanges B, C (12, 32) and connecting lugs B, C (13, 33) of the front fuselage (10) and the rear fuselage (30) correspond to the connecting flanges A (22) and connecting lugs A (23) on both sides of the middle fuselage (20) and are fixed with bolts.

2. The segmented UAV fuselage structure as described in claim 1, characterized in that, The front fuselage (10) includes two sets of symmetrically arranged front main beams (14), front sub-upper beams (15) and front sub-lower beams (16). The front sub-upper beams (15), front main beams (14) and front sub-lower beams (16) on the same side are arranged from top to bottom and fixed by welding with multiple reinforcing tubes. The front sub-upper beams (15), front main beams (14) and front sub-lower beams (16) on adjacent sides are fixed by welding with multiple reinforcing tubes.

3. The segmented UAV fuselage structure as described in claim 2, characterized in that, The connecting flange B (12) and multiple connecting lugs B (13) of the front fuselage (10) are respectively welded and fixed to the ends of the front main beam (14), the front sub-upper beam (15) and the front sub-lower beam (16).

4. The segmented UAV fuselage structure as described in claim 1, characterized in that, The middle fuselage (20) includes two sets of symmetrically arranged middle main beams (24), middle auxiliary upper beams (25) and middle auxiliary lower beams (26). The middle auxiliary upper beams (25), middle main beams (24) and middle auxiliary lower beams (26) on the same side are arranged from top to bottom and fixed by welding with multiple reinforcing pipes. The middle auxiliary upper beams (25), middle main beams (24) and middle auxiliary lower beams (26) on adjacent sides are fixed by welding with multiple reinforcing pipes to a reducer frame (27). The reducer frame (27) has an extension end on the side of its bottom closest to the rear fuselage (30).

5. The segmented UAV fuselage structure as described in claim 4, characterized in that, The connecting lugs A (23) of the middle fuselage (20) are respectively fixed at both ends of the middle main beam (24); the multiple connecting lugs A (23) of the middle fuselage (20) are fixed at one end of the middle auxiliary upper beam (25) and the middle auxiliary lower beam (26) near the front fuselage (10), and are also fixed at the extension ends on both sides of the bottom of the reducer frame (27).

6. The segmented UAV fuselage structure as described in claim 1, characterized in that, The rear fuselage (30) includes two sets of symmetrically arranged rear main beams (34) and rear sub-beams (35). The rear main beams (34) and rear sub-beams (35) on the same side are arranged from top to bottom and fixed by welding with multiple reinforcing tubes. The rear main beams (34) and rear sub-beams (35) on adjacent sides are fixed by welding with multiple reinforcing tubes. The rear sub-beams (35) on the side away from the middle fuselage (20) are inclined upward and welded to the end of the rear main beams (34).

7. The segmented UAV fuselage structure as described in claim 6, characterized in that, The connecting flange C (32) and connecting lug C (33) of the rear fuselage (30) are respectively fixed to the rear main beam (34) and the rear sub-beam (35) at one end near the middle fuselage (20).

8. The segmented UAV fuselage structure as described in claim 1, characterized in that, The connecting lug A (23) of the middle fuselage (20) is a double lug, and the connecting lugs B and C (13, 33) of the front fuselage (10) and the rear fuselage (30) are single lugs. The double lugs correspond to the single lugs and are clamped on the upper and lower sides of the single lugs.

Images