Distributed tilting ducted fan aircraft structure

Abstract

The utility model discloses a distributed tilting ducted fan aircraft structure which comprises an aircraft body, a front wing, a front tilting mechanism, a rear wing and a rear tilting mechanism, wherein the front wing and the front tilting mechanism are arranged in front of the aircraft body; a front beam mounting plate is arranged in front of the fuselage and connected with a front spar of the front wing, and a rear beam mounting plate is arranged behind the fuselage and connected with a rear spar of the rear wing; the front wing comprises a front carbon fiber truss, a foam shell and a front ducted fan; the front tilting mechanism is used for synchronously adjusting the tilting angles of the plurality of front ducted fans; the rear wing comprises a rear carbon fiber truss, a foam shell and a rear ducted fan; the rear tilting mechanism is used for synchronously adjusting the tilting angles of the rear ducted fans; after the structure is adopted, the problems in the existing small eVTOL structural design and tilting mechanism design can be solved.

Description

Technical Field

[0001] This utility model relates to the technical field of aircraft, and in particular to a distributed tilt ducted fan aircraft structure. Background Technology

[0002] Electric vertical takeoff and landing (eVTOL) aircraft are intelligent, low-noise, low-cost, environmentally friendly, and highly safe future urban airborne general-purpose aircraft. For small-scale eVTOL experimental prototypes, structural design presents significant challenges. Ensuring structural strength and stiffness while minimizing structural mass constraints is a major challenge in aircraft structural design. For VTOL aircraft, a reliable and efficient tilt mechanism design is crucial for successful flight. The tilting method, transmission method, and drive method of the tilt mechanism all present significant challenges. Therefore, overcoming these difficulties has become an urgent problem to be solved by those skilled in the art. Utility Model Content

[0003] The purpose of this invention is to provide a distributed tilting ducted fan aircraft structure to solve the problems in the design of existing small eVTOL structures and tilting mechanisms.

[0004] To address the aforementioned technical problems, this utility model provides a distributed tilt-ducted fan aircraft structure, including a fuselage, a front wing and a front tilt mechanism located at the front of the fuselage, and a rear wing and a rear tilt mechanism located at the rear of the fuselage; a front spar mounting plate is located at the front of the fuselage, and a rear spar mounting plate is located at the rear of the fuselage; the front spar mounting plate is connected to the front spar of the front wing near the central axis of the fuselage, and the rear spar mounting plate is connected to the rear spar of the rear wing; the front wing includes a front carbon fiber truss, a foam shell filling the front carbon fiber truss, and a [missing information - likely a component or structure]. The flaps of the front wing are connected to the front ducted fans, which are integrated with the front ducted fans in a synchronous tilting structure. The forward tilting mechanism is used to synchronously adjust the tilt angles of the multiple front ducted fans so that the multiple front ducted fans are capable of providing at least vertical lift and horizontal thrust. The rear wing includes a rear carbon fiber truss, a foam shell filled within the rear carbon fiber truss, and a rear ducted fan connected to the flaps of the rear wing in a synchronous tilting structure. The rear tilting mechanism is used to synchronously adjust the tilt angles of the multiple rear ducted fans so that the multiple rear ducted fans are capable of providing at least vertical lift and horizontal thrust.

[0005] In one embodiment, along the span direction of the front wing, the front carbon fiber truss includes a front wing root rib, a front wing mid-section rib, a front wing limiting rib, and a front wing tip rib arranged sequentially and opposite to each other; one end of the front wing spars passes sequentially through the front wing root rib, the front wing mid-section rib, the front wing limiting rib, and the front wing tip rib; the other end of the front wing spars extends to the wing root of the front wing, and this end of the front wing spars passes into the fuselage and connects to the front wing mounting plate; the front pivot of the front tilt mechanism passes sequentially through the front wing root rib, the front wing mid-section rib, and the front wing limiting rib to become a rotatable structure, and the rotation of the front pivot is used to drive the front ducted fan to tilt.

[0006] In one embodiment, multiple front beam mounting plates are arranged in parallel opposite directions, and each of the multiple front beam mounting plates is provided with a front beam mounting hole. The front wing beam is connected and fixed by passing through the multiple front beam mounting holes arranged in opposite directions.

[0007] In one embodiment, front bearings are provided on the root rib of the forewing, the middle rib of the forewing, and the limiting rib of the forewing, and multiple front bearings are sleeved on the outside of the front pivot.

[0008] In one embodiment, the forward tilting mechanism includes a front drive motor, a front gear set, and the front rotating shaft; the front drive motor is used to drive the front gear set to rotate; the rotation of the front gear set is used to drive the front rotating shaft to rotate; the front rotating shaft is provided with a plurality of front connecting members, the plurality of front connecting members are arranged separately along the axial direction of the front rotating shaft, and each of the plurality of front connecting members is respectively connected to the front ducted fan.

[0009] In one embodiment, along the span direction of the rear wing, the rear carbon fiber truss includes a rear wing root rib, a rear wing middle rib, a rear wing limiting rib, and a rear wing tip rib arranged sequentially and opposite to each other; one end of the rear wing spars passes sequentially through the rear wing root rib, the rear wing middle rib, the rear wing limiting rib, and the rear wing tip rib; the other end of the rear wing spars extends to the wing root of the rear wing, and this end of the rear wing spars passes into the fuselage and connects to the rear spars mounting plate; the rear pivot of the rear tilt mechanism passes sequentially through the rear wing root rib, the rear wing middle rib, and the rear wing limiting rib to become a rotatable structure, and the rotation of the rear pivot is used to drive the rear ducted fan to tilt.

[0010] In one embodiment, multiple rear beam mounting plates are arranged in parallel opposite directions, and each of the multiple rear beam mounting plates is provided with a rear beam mounting hole. The rear wing beam is connected and fixed by passing through the multiple rear beam mounting holes arranged in opposite directions.

[0011] In one embodiment, rear bearings are provided on the rear wing root rib, the rear wing middle rib, and the rear wing limiting rib, and multiple rear bearings are sleeved on the rear pivot.

[0012] In one embodiment, the rear tilt mechanism includes a rear drive motor, a rear gear set, and the rear rotating shaft; the rear drive motor is used to drive the rear gear set to rotate; the rotation of the rear gear set is used to drive the rear rotating shaft to rotate; the rear rotating shaft is provided with a plurality of rear connectors, the plurality of rear connectors are arranged separately along the axial direction of the rear rotating shaft, and each of the plurality of rear connectors is respectively connected to the rear ducted fan.

[0013] In one embodiment, the fuselage is a box-shaped and enclosed structure composed of a carbon fiber frame. The fuselage includes a base plate and a second-layer platform. At the nose of the fuselage, the base plate is provided with the forward tilt mechanism and the front beam mounting plate, so that the front wing is arranged near the bottom of the fuselage. At the tail of the fuselage, the base plate is provided with the second-layer platform, and the second-layer platform is provided with the rear tilt mechanism and the rear beam mounting plate, so that the rear wing is arranged near the top of the fuselage.

[0014] The beneficial effects of this utility model are as follows:

[0015] Since the front wing includes a front carbon fiber truss, a foam shell filling the front carbon fiber truss, and a front ducted fan connected to the flaps of the front wing in a synchronous tilting integrated structure, and the rear wing includes a rear carbon fiber truss, a foam shell filling the rear carbon fiber truss, and a rear ducted fan connected to the flaps of the rear wing in a synchronous tilting integrated structure, the wing of this utility model is a composite structure formed by carbon fiber truss and foam filling, which can resist the aerodynamic loads and torsional loads of the wing and overcome the wing's... Lateral bending and torsional deformation; the fuselage is a box-shaped and enclosed structure composed of carbon fiber frames, which bears most of the lateral and longitudinal bending moment loads and torsional loads of the main body of the fuselage. The outer shell of the fuselage can be composed of carbon fiber ribs and 3D printed thin shells to form a plate-rod thin-walled structure to resist the lateral bending load and torsional load of the fuselage and overcome the lateral and torsional deformation of the fuselage; furthermore, the forward tilt mechanism and the rear tilt mechanism are used to control the front ducted fan and the rear ducted fan to tilt more than 90°, thereby enabling the aircraft to have vertical take-off and landing capabilities. Attached Figure Description

[0016] To more clearly illustrate the technical solution of this utility model, the drawings used in the embodiments 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 from these drawings without creative effort.

[0017] Figure 1 This is a structural schematic diagram provided by an embodiment of the present utility model;

[0018] Figure 2 yes Figure 1 Enlarged schematic diagram of the forward tilting mechanism;

[0019] Figure 3 yes Figure 1 A magnified schematic diagram of the rear tilt mechanism.

[0020] The attached figures are labeled as follows:

[0021] 10. Fuselage; 11. Front beam mounting plate; 12. Rear beam mounting plate; 13. Base plate; 14. Second-layer platform;

[0022] 20. Forward wing; 21. Forward spars; 22. Forward wing root rib; 23. Forward wing mid-section rib; 24. Forward wing limiting rib; 25. Forward wing tip rib;

[0023] 30. Forward tilting mechanism; 31. Front drive motor; 32. Front gear set; 33. Front shaft; 34. Front connecting piece;

[0024] 40. Rear wing; 41. Rear wing spars; 42. Rear wing root rib; 43. Rear wing mid-section rib; 44. Rear wing limiting rib; 45. Rear wing tip rib;

[0025] 50. Rear tilting mechanism; 51. Rear drive motor; 52. Rear gear set; 53. Rear shaft; 54. Rear connecting piece;

[0026] 60. Front ducted fan;

[0027] 70. Rear duct fan. Detailed Implementation

[0028] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments.

[0029] This utility model provides a distributed tilt-ducted fan aircraft structure, the implementation of which is as follows: Figures 1 to 3As shown, the fuselage includes a fuselage 10, a front wing 20 and a forward tilt mechanism 30 located at the front of the fuselage 10, and a rear wing 40 and a rear tilt mechanism 50 located at the rear of the fuselage 10. A front spar mounting plate 11 is located at the front of the fuselage 10, and a rear spar mounting plate 1212 is located at the rear of the fuselage 10. The front spar mounting plate 11 is connected to the front spar 21 of the front wing 20 near the central axis of the fuselage 10, and the rear spar mounting plate 1212 is connected to the rear spar 41 of the rear wing 40. The front wing 20 includes a front carbon fiber truss, a foam shell filling the front carbon fiber truss, and flaps connected to the front wing 20. The front ducted fan 60 is a synchronous tilting integrated structure; the front tilting mechanism 30 is used to synchronously adjust the tilt angle of multiple front ducted fans 60 so that the multiple front ducted fans 60 have at least the working state of providing vertical lift and horizontal thrust; the rear wing 40 includes a rear carbon fiber truss, a foam shell filled in the rear carbon fiber truss, and a rear ducted fan 70 connected to the flaps of the rear wing 40 as a synchronous tilting integrated structure; the rear tilting mechanism 50 is used to synchronously adjust the tilt angle of multiple rear ducted fans 70 so that the multiple rear ducted fans 70 have at least the working state of providing vertical lift and horizontal thrust.

[0030] like Figure 1 and Figure 2 As shown, in this embodiment, along the span direction of the front wing 20, the front carbon fiber truss includes a front wing root rib 22, a front wing mid-section rib 23, a front wing limiting rib 24, and a front wing tip rib 25 arranged sequentially and opposite to each other. One end of the front wing spars 21 passes through the front wing root rib 22, the front wing mid-section rib 23, the front wing limiting rib 24, and the front wing tip rib 25 in sequence. The other end of the front wing spars 21 extends to the wing root of the front wing 20, and this end of the front wing spars 21 passes into the fuselage 10 and connects to the front spar mounting plate 11. The front pivot shaft 33 of the front tilt mechanism 30 passes through the front wing root rib 22, the front wing mid-section rib 23, and the front wing limiting rib 24 in sequence to become a rotatable structure. The rotation of the front pivot shaft 33 is used to drive the front ducted fan 60 to tilt.

[0031] Analysis reveals that the main loads borne by the forewing 20 are the axial bending moment and torsional moment generated by the wing's aerodynamic forces. The forewing sparb 21 of this invention primarily bears the axial bending moment load; therefore, the forewing sparb 21 is made of carbon fiber, possessing high structural strength. Since the root of the forewing 20 is the concentration point of the bending moment load, the root structure needs reinforcement. Furthermore, the root and tip of the forewing sparb 21 need to be positioned; therefore, the forewing root rib 22 and the forewing tip rib 25 are both made of carbon fiber plates. To enhance the forewing's spanwise torsional strength, reduce large deformations or flutter of the forewing 20, and suppress second-order modal oscillations, this invention uses foam material filled and installed between the forewing carbon fiber truss structures, forming a carbon fiber-foam wing composite structure. This structure not only reduces the overall weight of the forewing 20 and maintains its aerodynamic shape, but also possesses excellent structural strength and stiffness, effectively reducing structural deformation and vibration of the forewing 20.

[0032] Furthermore, due to the winglet design at the tip of the canard wing 20, the curved portion of the winglet has a complex geometry and aerodynamics. Therefore, a 3D printing process was used to create a single piece, utilizing foamed material to reduce structural mass. To minimize the risk of shear fracture between the curved portion of the winglet and the wingtip rib due to stress concentration, the canard sparb 21 extends outward at the wingtip, with the curved portion of the winglet connected and fixed to the carbon fiber tube of the sparb. The other end of the curved winglet component is connected and fixed to the winglet.

[0033] like Figure 2 As shown, in this embodiment, multiple front beam mounting plates 11 are arranged in parallel opposite directions. Each of the multiple front beam mounting plates 11 is provided with a front beam mounting hole. The front wing beam 21 passes through the multiple front beam mounting holes arranged in opposite directions and is connected and fixed.

[0034] At this time, the front wing spars 21 at the root of the front wing 20 extends beyond the wing root and serves as a connection structure for positioning and installing the front wing 20 and the fuselage 10. It is connected and fixed to the front wing mounting holes on the beam mounting plate. On the one hand, this facilitates the positioning and installation of the front wing 20 and improves the accuracy of the installation angle of the front wing 20. On the other hand, it can significantly enhance the structural rigidity of the root of the front wing 20, eliminate stress concentration, and distribute the concentrated load of the front wing 20 to the truss structure of the fuselage 10.

[0035] like Figure 1 and Figure 2 As shown, in this embodiment, front bearings are provided on the front wing root rib 22, the front wing middle rib 23 and the front wing limiting rib 24, and multiple front bearings are sleeved on the front rotating shaft 33.

[0036] At this point, the front bearing on the root rib 22 of the forewing reduces the frictional resistance between the pivot and the root rib 22, and also increases the constraint on the forward tilt mechanism 30, which helps to disperse the concentrated stress load at the root. A front bearing is also installed on the forewing limiting rib 24, which connects to the tip of the front pivot 33 to provide tip node constraint, thereby reducing tip deflection. A central rib 23 is also provided in the middle of the forewing 20, and a front bearing is also installed on it. Its function is also to increase the node constraint on the forward tilt mechanism 30, which helps to distribute the bending moment and torsional load of the forward tilt mechanism 30 to the load-bearing structure of the forewing 20, reducing the deformation of the forward tilt mechanism 30. Therefore, through the above design, the lateral bending moment and torsion of the forward tilt mechanism 30 can be distributed to the forewing 20, effectively reducing the deformation and vibration of the forward tilt mechanism 30 and improving the reliability of the tilt mechanism.

[0037] like Figure 1 and Figure 2 As shown, this embodiment provides a forward tilting mechanism 30 including a front drive motor 31, a front gear set 32, and a front rotating shaft 33; the front drive motor 31 is used to drive the front gear set 32 ​​to rotate; the rotation of the front gear set 32 ​​is used to drive the front rotating shaft 33 to rotate; the front rotating shaft 33 is provided with a plurality of front connecting members 34, which are arranged separately along the axial direction of the front rotating shaft 33, and each of the plurality of front connecting members 34 is connected to a front ducted fan 60.

[0038] like Figure 1 and Figure 3 As shown, in this embodiment, along the span direction of the rear wing 40, the rear carbon fiber truss includes a rear wing root rib 42, a rear wing middle rib 43, a rear wing limiting rib 44, and a rear wing tip rib 45 arranged sequentially and opposite to each other; one end of the rear wing spars 41 passes through the rear wing root rib 42, the rear wing middle rib 43, the rear wing limiting rib 44, and the rear wing tip rib 45 in sequence; the other end of the rear wing spars 41 extends to the wing root of the rear wing 40, and this end of the rear wing spars 41 passes into the fuselage 10 and connects to the rear spars mounting plate 12; the rear pivot shaft 53 of the rear tilt mechanism 50 passes through the rear wing root rib 42, the rear wing middle rib 43, and the rear wing limiting rib 44 in sequence to become a rotatable structure, and the rotation of the rear pivot shaft 53 is used to drive the rear ducted fan 70 to tilt.

[0039] Analysis shows that the main loads borne by the rear wing 40 are the axial bending moment and torsional moment generated by the wing's aerodynamic forces. The rear wing sparb 41 of the rear wing 40 of this invention is primarily responsible for bearing the axial bending moment load; therefore, the rear wing sparb 41 is made of carbon fiber material, possessing high structural strength. Since the root of the rear wing 40 is the location where the bending moment load is concentrated, the wing root structure needs to be strengthened. Furthermore, the wing root and wing tip of the rear wing sparb 41 need to be positioned; therefore, the wing root rib 42 and the wing tip rib 45 are both made of carbon fiber plates. To further enhance the wing's spanwise torsional strength, reduce large deformations or flutter of the rear wing 40, and suppress the second-order modal oscillations of the rear wing 40, this invention uses foam material filled and installed between the rear carbon fiber truss structures, forming a carbon fiber-foam wing composite structure. This structure not only reduces the overall weight of the rear wing 40 and maintains the geometry of the rear wing 40 to generate aerodynamic forces, but also has excellent structural strength and rigidity, effectively reducing the structural deformation and vibration of the rear wing 40.

[0040] Furthermore, due to the winglet design at the tip of the rear wing 40, the curved portion of the winglet has a complex geometry and aerodynamics. Therefore, a 3D printing process was used to create a single piece, utilizing foamed material to reduce structural mass. To minimize the risk of shear fracture between the curved portion of the winglet and the wingtip rib due to stress concentration, the rear wing sparb 41 extends outward at the wingtip, with the curved portion of the winglet connected and fixed to the carbon fiber tube of the sparb. The other end of the curved winglet component is connected and fixed to the winglet.

[0041] like Figure 1 and Figure 3 As shown, in this embodiment, multiple rear beam mounting plates 12 are arranged in parallel opposite directions. Each of the multiple rear beam mounting plates 12 is provided with a rear beam mounting hole. The rear wing beam 41 passes through the multiple rear beam mounting holes arranged in opposite directions and is connected and fixed.

[0042] At this time, the rear wing spars 41 at the root of the rear wing 40 extends beyond the wing root, serving as a connection structure for positioning and installing the rear wing 40 and the fuselage 10. It is connected and fixed to the rear wing mounting holes on the beam mounting plate. On the one hand, this facilitates the positioning and installation of the rear wing 40 and improves the accuracy of the installation angle of the rear wing 40; on the other hand, it can significantly enhance the structural rigidity of the root of the rear wing 40, eliminate stress concentration, and distribute the concentrated load of the rear wing 40 to the truss structure of the fuselage 10.

[0043] like Figure 1 and Figure 3 As shown, in this embodiment, rear bearings are provided on the rear wing root rib 42, the rear wing middle rib 43 and the rear wing limiting rib 44, and multiple rear bearings are sleeved on the rear rotating shaft 53; the fuselage 10 is provided with a rear axle platform, which is sleeved on the rear rotating shaft 53.

[0044] At this point, the rear axle platform is used to fix the rear rotating shaft 53, while the rear bearing on the rear wing root rib 42 reduces the frictional resistance between the rotating shaft and the rear wing root rib 42, and also increases the constraint on the rear tilt mechanism 50, which helps to disperse the concentrated stress load at the root. A rear bearing is also installed on the rear wing limiting rib 44, which is connected to the tip of the rear rotating shaft 53 to provide tip node constraint, thereby reducing tip deflection. A rear wing center rib 43 is also provided in the middle of the rear wing 40, and a rear bearing is also installed on the rear wing center rib 43. Its function is also to increase the node constraint on the rear tilt mechanism 50, which helps to distribute the bending moment load and torsional load of the rear tilt mechanism 50 to the load-bearing structure of the rear wing 40, reducing the deformation of the rear tilt mechanism 50. Therefore, through the above design, the lateral bending moment and torsion of the rear tilt mechanism 50 can be distributed to the rear wing 40, which can effectively reduce the deformation and vibration of the rear tilt mechanism 50 and improve the reliability of the tilt mechanism.

[0045] like Figure 1 and Figure 3 As shown, this embodiment provides a rear tilt mechanism 50 including a rear drive motor 51, a rear gear set 52, and a rear rotating shaft 53; the rear drive motor 51 is used to drive the rear gear set 52 to rotate; the rotation of the rear gear set 52 is used to drive the rear rotating shaft 53 to rotate; the rear rotating shaft 53 is provided with a plurality of rear connecting members 54, which are arranged separately along the axial direction of the rear rotating shaft 53, and each of the plurality of rear connecting members 54 is connected to a rear ducted fan 70.

[0046] like Figure 1 As shown, in this embodiment, the fuselage 10 is configured as a box-shaped and enclosed structure composed of a carbon fiber frame. The fuselage 10 includes a base plate 13 and a second-layer platform 14. Near the nose of the fuselage 10, the base plate 13 is provided with a forward tilting mechanism 30 and a front beam mounting plate 11, so that the front wing 20 is arranged near the bottom of the fuselage 10. Near the tail of the fuselage 10, the base plate 13 is provided with a second-layer platform 14, and the second-layer platform 14 is provided with a rear tilting mechanism 50 and a rear beam mounting plate 12, so that the rear wing 40 is arranged near the top of the fuselage 10, thereby achieving a staggered arrangement of the front wing 20 and the rear wing 40.

[0047] The above are preferred embodiments of this utility model. It should be noted that, for those skilled in the art, several improvements and modifications can be made without departing from the principle of this utility model, and these improvements and modifications are also considered to be within the protection scope of this utility model.

Claims

1. A distributed tilt-ducted fan aircraft structure, characterized in that, It includes a fuselage, a front wing and a forward tilt mechanism located at the front of the fuselage, and a rear wing and a rear tilt mechanism located at the rear of the fuselage; A front beam mounting plate is provided at the front of the fuselage, and a rear beam mounting plate is provided at the rear of the fuselage. The front beam mounting plate is connected to the front wing spars of the front wing and the rear beam mounting plate is connected to the rear wing spars of the rear wing near the central axis of the fuselage. The front wing includes a front carbon fiber truss, a foam shell filling the front carbon fiber truss, and a front ducted fan connected to the flaps of the front wing in a synchronous tilting integrated structure. The forward tilting mechanism is used to synchronously adjust the tilting angle of the multiple front duct fans so that the multiple front duct fans are at least in a working state that provides vertical lift and horizontal thrust. The rear wing includes a rear carbon fiber truss, a foam shell filled within the rear carbon fiber truss, and a rear ducted fan connected to the flaps of the rear wing in a synchronous tilting integrated structure. The rear tilting mechanism is used to synchronously adjust the tilting angle of the multiple rear duct fans so that the multiple rear duct fans are at least in a working state that provides vertical lift and horizontal thrust.

2. The distributed tilt-ducted fan aircraft structure according to claim 1, characterized in that, Along the span direction of the front wing, the front carbon fiber truss includes a front wing root rib, a front wing middle rib, a front wing limiting rib, and a front wing tip rib arranged in sequence and opposite to each other. One end of the front wing spall passes sequentially through the root wing rib of the front wing, the middle wing rib of the front wing, the limiting wing rib of the front wing, and the tip wing rib of the front wing; the other end of the front wing spall extends to the outside of the root of the front wing, and this end of the front wing spall passes into the fuselage and connects with the front wing mounting plate. The front pivot shaft of the forward tilting mechanism passes sequentially through the root rib of the front wing, the middle rib of the front wing, and the limiting rib of the front wing to become a rotatable structure. The rotation of the front pivot shaft is used to drive the front ducted fan to tilt.

3. The distributed tilt-ducted fan aircraft structure according to claim 2, characterized in that, Multiple front beam mounting plates are parallel to each other, and each of the multiple front beam mounting plates is provided with front beam mounting holes. The front wing beam is connected and fixed by passing through the multiple front beam mounting holes arranged in opposite directions.

4. The distributed tilt-ducted fan aircraft structure according to claim 2, characterized in that, The forewing root rib, the forewing middle rib, and the forewing limiting rib are all provided with front bearings, and multiple front bearings are sleeved on the outside of the front pivot.

5. The distributed tilt-ducted fan aircraft structure according to claim 2, characterized in that, The forward tilting mechanism includes a front drive motor, a front gear set, and the front rotating shaft; The front drive motor is used to drive the front gear set to rotate; The rotation of the front gear set is used to drive the front shaft to rotate. The front shaft is provided with a plurality of front connectors, which are arranged separately along the axial direction of the front shaft, and each of the plurality of front connectors is connected to the front duct fan.

6. The distributed tilt-ducted fan aircraft structure according to claim 1, characterized in that, Along the span direction of the rear wing, the rear carbon fiber truss includes a rear wing root rib, a rear wing middle rib, a rear wing limiting rib, and a rear wing tip rib that are sequentially separated and arranged opposite to each other. One end of the rear wing spall passes sequentially through the rear wing root rib, the rear wing middle rib, the rear wing limiting rib, and the rear wing tip rib; the other end of the rear wing spall extends to the outside of the wing root of the rear wing, and this end of the rear wing spall passes into the fuselage and connects with the rear wing mounting plate. The rear tilt mechanism's rear rotating shaft passes sequentially through the rear wing root rib, the rear wing middle rib, and the rear wing limiting rib to become a rotatable structure. The rotation of the rear rotating shaft is used to drive the rear ducted fan to tilt.

7. The distributed tilt-ducted fan aircraft structure according to claim 6, characterized in that, Multiple rear beam mounting plates are parallel to each other, and each of the multiple rear beam mounting plates is provided with rear beam mounting holes. The rear wing beam is connected and fixed by passing through the multiple rear beam mounting holes arranged in opposite directions.

8. The distributed tilt-ducted fan aircraft structure according to claim 6, characterized in that, The rear wing root rib, the rear wing middle rib, and the rear wing limiting rib are all provided with rear bearings, and multiple rear bearings are sleeved on the rear pivot.

9. The distributed tilt-ducted fan aircraft structure according to claim 6, characterized in that, The rear tilting mechanism includes a rear drive motor, a rear gear set, and the rear rotating shaft; The rear drive motor is used to drive the rear gear set to rotate; The rotation of the rear gear set is used to drive the rear rotating shaft to rotate. The rear shaft is provided with a plurality of rear connectors, which are arranged separately along the axial direction of the rear shaft, and each of the plurality of rear connectors is connected to the rear duct fan.

10. The distributed tilt-ducted fan aircraft structure according to claim 1, characterized in that, The fuselage is a box-shaped and enclosed structure composed of a carbon fiber frame, and the fuselage includes a base plate and a two-layer platform. At the nose of the fuselage, the base plate is provided with the forward tilting mechanism and the front beam mounting plate so that the front wing is arranged near the bottom of the fuselage; At the tail of the fuselage, a second-layer platform is provided on the base plate, and the rear tilt mechanism and the rear beam mounting plate are provided on the second-layer platform so that the rear wing is arranged near the top of the fuselage.

Images