Rotary folding type unmanned aerial vehicle

Abstract

The invention provides a rotary folding type unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicles, the rotary folding type unmanned aerial vehicle comprises a fuselage, wings are arranged on the two sides of the fuselage, each wing comprises an inner wing section and an outer wing section, and the inner wing sections and the outer wing sections are connected through rotary folding mechanisms; the rotary folding mechanism comprises a first connecting part, a second connecting part, a pin shaft and a locking part, the first connecting part and the second connecting part are connected with the inner wing section and the outer wing section correspondingly, the second connecting part rotationally sleeves the outer side of the pin shaft and is rotationally connected with the first connecting part through the pin shaft, and the second connecting part can slide in the axial direction of the pin shaft; the outer wing section descends relative to the inner wing section, and the locking part can lock and position the first connecting part and the second connecting part when the wing is in an unfolded state; the problems that in the prior art, the wingspan of an unmanned aerial vehicle is large, and the requirement for the parking space of an airport hangar is high are solved.

Description

Technical Field

[0001] The present invention belongs to the technical field of unmanned aerial vehicles, and more specifically, relates to a rotating and folding unmanned aerial vehicle. Background Art

[0002] In order to meet the energy requirements of ultra-long flight, large solar drones generally adopt an ultra-large wingspan aerodynamic layout design. Large wingspan solar drones require much more ground hangar storage space than conventional aircraft. In particular, when multiple large solar drones are parked at the same time, ordinary airport hangars cannot meet the space requirements. Therefore, reducing the parking space requirements and improving the adaptability to airport hangars have become issues that need to be solved during the use of large solar drones. Summary of the invention

[0003] The purpose of the present invention is to provide a rotating foldable UAV to address the deficiencies in the prior art, thereby solving the problem that the UAVs in the prior art have a large wingspan and require a high parking space in an airport hangar.

[0004] In order to achieve the above object, the present invention provides a rotating foldable drone, comprising:

[0005] A fuselage, wherein wings are arranged on both sides of the fuselage, the wings comprising an inner wing section and an outer wing section, and the inner wing section is connected to the outer wing section via a rotating folding mechanism;

[0006] The rotary folding mechanism includes a first connecting part, a second connecting part, a pin shaft and a locking component. The first connecting part and the second connecting part are respectively connected to the inner wing section and the outer wing section. The second connecting part is rotatably sleeved on the outer side of the pin shaft and is rotatably connected to the first connecting part through the pin shaft. The second connecting part can slide along the axial direction of the pin shaft so that the outer wing section can descend relative to the inner wing section. The locking component can lock and position the first connecting part and the second connecting part when the wing is in an unfolded state.

[0007] Optionally, a sleeve portion is provided on the upper side of the second connecting portion, and the sleeve portion is movably sleeved on the outer side of the pin shaft.

[0008] Optionally, the locking component includes a nut, the outer periphery of the lower end of the pin shaft is provided with an external thread, and the nut is arranged below the second connecting portion and connected to the external thread.

[0009] Optionally, a limiting portion is provided at the upper end of the pin shaft, the limiting portion is provided on the upper side of the first connecting portion, and the pin shaft passes through the first connecting portion.

[0010] Optionally, the limiting portion is provided with a tool connecting portion, and the tool connecting portion is used to connect a rotating tool.

[0011] Optionally, a tail wing is provided at the rear end of the fuselage, and the tail wing includes a horizontal tail wing and a vertical tail wing, and the trailing edges of the horizontal tail wing and the vertical tail wing are respectively provided with an elevator and a rudder.

[0012] Optionally, a propeller is provided at the leading edge of the inner wing section.

[0013] Optionally, a landing gear is provided on the lower side of the inner wing section.

[0014] Optionally, an operating cover is further included, which is arranged at the connection between the inner wing section and the outer wing section, connected to the inner wing section and / or the outer wing section, and used to cover the rotating folding mechanism.

[0015] Optionally, a solar panel is provided on the upper surface of the wing.

[0016] The invention provides a rotary folding UAV, which has the following beneficial effects: the rotary folding UAV has folding wings, the wings include an inner wing section and an outer wing section, the two are connected by a rotary folding mechanism, a pin shaft passes through a first connection part and a second connection part respectively connected to the inner wing section and the outer wing section, when the wings need to be folded, the outer wing section together with the second connection part is first moved downward along the axial direction of the pin shaft, so that the outer wing section and the inner wing section are in different planes, and then the outer wing section is rotated to be able to be moved below the inner wing section, thereby reducing the size of the UAV, reducing the requirements for the size of the hangar, improving the adaptability to the hangar, saving the internal space of the hangar, and making better use of the internal space of the hangar; when the wings are unfolded, the outer wing section is rotated to make it come to the extension direction of the inner wing section, and the outer wing section is lifted upward, so that the second connection part is close to the first connection part, until the outer wing section and the inner wing section are in the same plane, and then locked by a locking component.

[0017] Other features and advantages of the present invention will be described in detail in the following detailed description. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The above and other objects, features and advantages of the present invention will become more apparent through a more detailed description of exemplary embodiments of the present invention in conjunction with the accompanying drawings, wherein like reference numerals generally represent like components throughout the exemplary embodiments of the present invention.

[0019] Figure 1 A schematic diagram of a wing unfolding state of a rotating and folding UAV according to an embodiment of the present invention is shown.

[0020] Figure 2 A schematic diagram of the rotation of an outer wing section of a rotating and folding UAV according to an embodiment of the present invention is shown.

[0021] Figure 3 A schematic diagram of a folded wing state of a rotating and folding UAV according to an embodiment of the present invention is shown.

[0022] Figure 4 Shows Figure 3 A partial enlarged schematic diagram of .

[0023] Description of reference numerals:

[0024] 1. Outer wing section; 2. Inner wing section; 3. Fuselage; 4. Horizontal tail; 5. Vertical tail; 6. Propeller; 7. Landing gear; 8. Aileron; 9. Elevator; 10. Rudder; 11. Rotating and folding mechanism; 12. First connecting part; 13. Second connecting part; 14. Nut; 15. Pin; 16. Sleeve part. DETAILED DESCRIPTION

[0025] The preferred embodiments of the present invention will be described in more detail below. Although the preferred embodiments of the present invention are described below, it should be understood that the present invention can be implemented in various forms and should not be limited by the embodiments set forth herein. On the contrary, these embodiments are provided to make the present invention more thorough and complete, and to fully convey the scope of the present invention to those skilled in the art.

[0026] like Figures 1 to 3 As shown, the present invention provides a rotating foldable drone, comprising:

[0027] A fuselage 3, with wings arranged on both sides of the fuselage 3, the wings comprising an inner wing section 2 and an outer wing section 1, the inner wing section 2 and the outer wing section 1 being connected via a rotating folding mechanism 11;

[0028] The rotary folding mechanism 11 includes a first connecting part 12, a second connecting part 13, a pin shaft 15 and a locking component. The first connecting part 12 and the second connecting part 13 are respectively connected to the inner wing section 2 and the outer wing section 1. The second connecting part 13 is rotatably sleeved on the outer side of the pin shaft 15 and is rotatably connected to the first connecting part 12 through the pin shaft 15. The second connecting part 13 can slide along the axial direction of the pin shaft 15 to make the outer wing section 1 descend relative to the inner wing section 2. The locking component can lock the first connecting part 12 and the second connecting part 13 in position when the wing is in the unfolded state.

[0029] Specifically, in order to solve the problem that the wingspan of the UAV in the prior art is large and the parking space requirement of the airport hangar is high; the rotating folding UAV provided by the present invention has folding wings, and the wings include an inner wing section 2 and an outer wing section 1, which are connected by a rotating folding mechanism 11, and a pin shaft 15 passes through a first connecting portion 12 and a second connecting portion 13 respectively connected to the inner wing section 2 and the outer wing section 1. When the wing needs to be folded, the outer wing section 1 together with the second connecting portion 13 is first moved downward along the axial direction of the pin shaft 15, so that the outer wing section 1 and the inner wing section 2 are folded. The outer wing section 1 is in different planes, and then the outer wing section 1 is rotated to be below the inner wing section 2, thereby reducing the size of the UAV, reducing the requirements for the size of the hangar, improving the adaptability to the hangar, and saving the internal space of the hangar, so as to make better use of the internal space of the hangar; when the wing is unfolded, the outer wing section 1 is rotated to the extension direction of the inner wing section 2, and the outer wing section 1 is lifted upward so that the second connecting part 13 is close to the first connecting part 12, until the outer wing section 1 and the inner wing section 2 are in the same plane, and then locked by the locking component.

[0030] Furthermore, the first connection portion 12 is arranged at a position of the inner wing section 2 close to the upper wing surface, and an avoidance opening is arranged at a position of the inner wing section 2 close to the lower wing surface. The avoidance opening is used to avoid the second connection portion 13 connected to the outer wing section 1. When the wing is unfolded, the outer end surface of the inner wing section 2 is butted against the inner end surface of the outer wing section 1. When the wing is folded, the second connection portion 13 follows the outer wing section 1 to move downward along the axial direction of the pin shaft 15, and the second connection portion 13 can pass through the avoidance opening.

[0031] In this embodiment, if Figure 4 As shown, the first connecting portion 12 and the second connecting portion 13 are two ear-piece structures.

[0032] The wings of the rotary folding UAV can be folded by rotating. After folding, the UAV's requirement for the hangar width is reduced by one third. Through the design of the rotary folding mechanism 11, the height of the outer wing section 1 of the wing can be lowered and rotated, and it can be rotated and folded under the inner wing section 2 of the wing; compared with the storage method of disassembling the outer wing section 1 of the wing, the rotary folding method simplifies the operation process, reduces the number of operators and operation time; compared with the method of folding the outer wing section 1 upward, for a large-wingspan solar UAV, the rotary folding design is more feasible due to the larger span of the outer wing section 1 of the wing; compared with the overlapping method of shortening the wing span, the mechanism of the rotary folding design is simpler to implement and is more suitable for the improvement of existing UAVs.

[0033] Optionally, a sleeve portion 16 is provided on the upper side of the second connecting portion 13 , and the sleeve portion 16 is movably sleeved on the outer side of the pin shaft 15 .

[0034] Specifically, the sleeve and the second connecting part 13 are an integrated structure. The sleeve can move along the axial direction of the pin 15 and can also rotate relative to the pin 15. When the locking component locks the outer wing section 1, the sleeve presses against the first connecting part 12. When the locking component is released, the sleeve follows the second connecting part 13 and moves downward relative to the pin 15, but always partially sleeves the pin 15.

[0035] Optionally, the locking component includes a nut 14 , an outer circumference of the lower end of the pin 15 is provided with an external thread, and the nut 14 is arranged below the second connecting portion 13 and connected to the external thread.

[0036] Specifically, by tightening the nut 14 on the external thread, the second connection portion 13 can be pushed upward until the sleeve portion 16 presses against the first connection portion 12, and at this time, the second connection portion 13 and the outer wing section 1 are in place.

[0037] In this embodiment, a gasket is disposed between the nut 14 and the second connecting portion 13 .

[0038] Optionally, a limiting portion is provided at the upper end of the pin shaft 15 , the limiting portion is provided on the upper side of the first connecting portion 12 , and the pin shaft 15 passes through the first connecting portion 12 .

[0039] Specifically, the limiting portion is connected to the first connecting portion 12 , and the upper end of the pin shaft 15 is movably inserted into the first connecting portion 12 .

[0040] Optionally, the limiting portion is provided with a tool connecting portion, and the tool connecting portion is used to connect a rotating tool.

[0041] Specifically, the tool connection portion is used to connect with a rotating tool such as a wrench or a screwdriver, so that the rotation of the pin 15 can be restricted during the process of tightening the nut 14, which facilitates operation.

[0042] In this embodiment, a tail is provided at the rear end of the fuselage 3. The tail includes a horizontal tail 4 and a vertical tail 5. The trailing edges of the horizontal tail 4 and the vertical tail 5 are provided with an elevator 9 and a rudder 10, respectively.

[0043] Specifically, the horizontal tail 4 is arranged at the rear end of the fuselage 3 , and the vertical tail 5 is arranged behind the horizontal tail 4 .

[0044] In this embodiment, a propeller 6 is provided at the leading edge of the inner wing section 2 .

[0045] In this embodiment, a landing gear 7 is provided on the lower side of the inner wing section 2 .

[0046] Optionally, an operating cover is also included, which is arranged at the connection between the inner wing section 2 and the outer wing section 1, connected to the inner wing section 2 and / or the outer wing section 1, and used to cover the rotating and folding mechanism 11.

[0047] Specifically, the operating cover covers the rotating folding mechanism 11 to achieve a rectifying effect; the operating cover can be installed by snap-fit ​​or screws.

[0048] Optionally, solar panels are provided on the upper surface of the wing.

[0049] Specifically, solar panels are arranged on the upper wing surfaces of the inner wing section 2 and the outer wing section 1; the UAV is a solar-powered UAV, which utilizes solar panels to convert solar energy into electrical energy to improve endurance.

[0050] In this embodiment, an aileron 8 is provided at the trailing edge of the outer wing section 1 .

[0051] In summary, when the rotating and folding UAV provided by the present invention is put into storage, it is first parked in a predetermined position and the operation cover is opened; the locking component for the first connecting part 12 and the second connecting part 13 is released; the height of the outer wing section 1 is lowered until the outer wing section 1 is lower than the inner wing section 2; the outer wing section 1 is rotated and folded around the pin shaft 15 to the bottom of the inner wing section 2 to complete the wing rotation and folding action; the rotating and folding UAV with folded wings is sent into the hangar and parking is completed. Before the next use, the rotating foldable drone is pushed out of the hangar to an open area, or the solar drone is parked in a predetermined position in the allowed space in the hangar; the outer wing section 1 is rotated around the pin shaft 15 until the outer wing section 1 is in the wingspan extension direction of the inner wing section 2, and a marking line can also be set, and the initial position marking line on the second connecting part 13 of the outer wing section 1 is aligned with the initial position marking line on the first connecting part 12 of the inner wing section 2; the outer wing section 1 is lifted upward by the locking component until the outer wing section 1 and the inner wing section 2 are in the same horizontal position and the first connecting part 12 and the second connecting part 13 are locked and positioned, so that the wing is in the unfolded state; the operating cover is installed again, the wing is unfolded and can be put into use.

[0052] The embodiments of the present invention have been described above, and the above description is exemplary, not exhaustive, and is not limited to the disclosed embodiments. Many modifications and changes will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments.

Claims

1. A rotating foldable drone, characterized in that: include: A fuselage, wherein wings are arranged on both sides of the fuselage, the wings comprising an inner wing section and an outer wing section, and the inner wing section is connected to the outer wing section via a rotating folding mechanism; The rotary folding mechanism includes a first connecting part, a second connecting part, a pin shaft and a locking component. The first connecting part and the second connecting part are respectively connected to the inner wing section and the outer wing section. The second connecting part is rotatably sleeved on the outer side of the pin shaft and is rotatably connected to the first connecting part through the pin shaft. The second connecting part can slide along the axial direction of the pin shaft so that the outer wing section can descend relative to the inner wing section. The locking component can lock and position the first connecting part and the second connecting part when the wing is in an unfolded state.

2. The rotating foldable drone according to claim 1, characterized in that: A sleeve portion is disposed on the upper side of the second connecting portion, and the sleeve portion is movably sleeved on the outer side of the pin shaft.

3. The rotating foldable drone according to claim 1, characterized in that: The locking component comprises a nut, an outer thread is arranged on the outer periphery of the lower end of the pin shaft, and the nut is arranged below the second connecting portion and connected with the outer thread.

4. The rotating foldable drone according to claim 1, characterized in that: A limiting portion is disposed at the upper end of the pin shaft, the limiting portion is disposed on the upper side of the first connecting portion, and the pin shaft passes through the first connecting portion.

5. The rotating foldable drone according to claim 4, characterized in that: The limiting portion is provided with a tool connecting portion, and the tool connecting portion is used to connect a rotating tool.

6. The rotating and folding drone according to claim 1, characterized in that: The rear end of the fuselage is provided with a tail wing, which includes a horizontal tail wing and a vertical tail wing. The trailing edges of the horizontal tail wing and the vertical tail wing are respectively provided with an elevator and a rudder.

7. The rotating and folding UAV according to claim 1, characterized in that: A propeller is arranged at the leading edge of the inner wing section.

8. The rotating and folding drone according to claim 1, characterized in that: A landing gear is arranged on the lower side of the inner wing section.

9. The rotating foldable drone according to claim 1, characterized in that: It also includes an operating cover, which is arranged at the connection between the inner wing section and the outer wing section, connected to the inner wing section and / or the outer wing section, and used to cover the rotating and folding mechanism.

10. The rotating and folding drone according to claim 1, characterized in that: The upper surface of the wing is provided with a solar cell panel.

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