An unmanned aerial vehicle

Abstract

The present invention relates to the field of aircraft, and discloses an unmanned aerial vehicle, comprising a fuselage and a landing gear assembly mounted on the fuselage, wherein the landing gear assembly comprises a mounting plate, a landing gear, and a clamping structure. The mounting plate is connected to the fuselage, and the landing gear is mounted on the mounting plate. The landing gear can rotate around a center line relative to the mounting plate, and one of the mounting plate and the landing gear is provided with at least two locking holes, and the other is provided with a locking pin, wherein the at least two locking holes are distributed in a circle around the center line, and the clamping structure connects the mounting plate and the landing gear, and is used to provide a clamping force that brings the mounting plate and the landing gear closer to each other along the center line. The unmanned aerial vehicle is equipped with a landing gear assembly, and the landing gear in the landing gear assembly can be unfolded or folded relative to the fuselage, so that the unmanned aerial vehicle can be easily carried.

Description

[Technical field]

[0001] The present invention relates to the field of aircraft, and in particular to an unmanned aircraft. [Background technology]

[0002] The landing gear is an accessory device of the unmanned aerial vehicle that has both load-bearing and maneuverability. It plays an extremely important mission in the safe take-off and landing process of the unmanned aerial vehicle and is one of the important components of the unmanned aerial vehicle.

[0003] Currently, the landing gear is generally fixed.

[0004] However, the inventor found in the process of implementing the present invention that the fixed landing gear is inconvenient to carry. Therefore, the prior art needs to be improved. [Summary of the invention]

[0005] In order to solve the above technical problems, an embodiment of the present invention provides an unmanned aerial vehicle equipped with a landing gear, which is easy to carry.

[0006] In order to solve the above technical problems, the embodiments of the present invention provide the following technical solutions:

[0007] An unmanned aerial vehicle is provided, characterized in that it includes a fuselage and a landing gear assembly installed on the fuselage, the landing gear assembly including: a landing gear, which can rotate relative to the fuselage around a center line; a clamping structure, one end of the clamping structure is connected to the rotating shaft, and the other end is connected to the fuselage, the clamping structure is used to provide a clamping force to make the landing gear approach the fuselage along the center line; one of the fuselage and the landing gear is provided with a locking hole, and the other of the fuselage and the landing gear is provided with a locking pin; the locking pin cooperates with the locking hole so that the position of the landing gear relative to the fuselage is locked; the locking pin can be separated from the locking hole so that the landing gear can rotate relative to the fuselage around the center line.

[0008] In some embodiments, the fuselage is further provided with a mounting plate, one of the mounting plate and the landing gear is provided with the locking hole, and the other of the mounting plate and the landing gear is provided with the locking pin.

[0009] In some embodiments, the locking pin is disposed on the landing gear, and the locking hole is disposed on the mounting plate.

[0010] In some embodiments, the mounting plate has a first contact surface, and the landing gear has a second contact surface facing the first contact surface and in contact with the first contact surface; the locking pin is arranged on the first contact surface, and the locking pin extends along the center line toward the second contact surface, and the locking hole is correspondingly formed on the second contact surface.

[0011] In some embodiments, the locking hole is disposed on the landing gear, and the locking pin is disposed on the mounting plate.

[0012] In some embodiments, the mounting plate has a first contact surface, and the landing gear has a second contact surface facing the first contact surface and in contact with the first contact surface; the locking pin is arranged on the second contact surface, and the locking pin extends along the center line toward the first contact surface, and the locking hole is correspondingly formed on the first contact surface.

[0013] In some embodiments, the mounting plate is provided with a mounting groove, and the second contact surface is the bottom of the mounting groove; the landing gear is provided with one end of the first contact surface accommodated in the mounting groove.

[0014] In some embodiments, one of the landing gear and the fuselage is provided with a rotating shaft arranged along the center line, and the other is provided with an axial hole, and the rotating shaft is inserted into the axial hole.

[0015] In some embodiments, the rotating shaft is disposed on the landing gear, the shaft hole is disposed on the mounting plate, and the shaft hole passes through the mounting plate and communicates with the interior of the fuselage.

[0016] In some embodiments, the clamping structure includes a pressing plate and an elastic member; the pressing plate is arranged at one end of the rotating shaft passing through the axial hole, the elastic member is sleeved on the rotating shaft, and the elastic member abuts between the pressing plate and the mounting plate.

[0017] In some embodiments, the elastic member is a compression spring.

[0018] In some embodiments, the pressing plate is threadedly connected to the rotating shaft.

[0019] Compared with the prior art, in an unmanned aerial vehicle of an embodiment of the present invention, the unmanned aerial vehicle is equipped with a landing gear assembly, and the landing gear in the landing gear assembly can be unfolded or folded relative to the fuselage, so that the unmanned aerial vehicle can be easy to carry.

Brief Description of the Drawings

[0020] One or more embodiments are exemplarily described by corresponding drawings, which do not constitute limitations on the embodiments. Elements with the same reference numerals in the drawings represent similar elements, and the figures in the drawings do not constitute proportional limitations unless otherwise stated.

[0021] Figure 1 A three-dimensional diagram of an unmanned aerial vehicle provided by one embodiment of the present invention;

[0022] Figure 2 for Figure 1A cross-sectional view of a landing gear assembly of an unmanned aerial vehicle is shown, wherein a landing gear of the landing gear assembly is partially omitted;

[0023] Figure 3 for Figure 1 A top view of the UAV is shown, wherein some parts of the UAV are omitted;

[0024] Figure 4 for Figure 1 A front view of the UAV is shown with the length of the two wings omitted;

[0025] Figure 5 for Figure 2 A cross-sectional view of the landing gear assembly shown in another embodiment, wherein the landing gear is partially omitted;

[0026] Figure 6 for Figure 2 A cross-sectional schematic diagram of the landing gear assembly shown in a first state;

[0027] Figure 7 for Figure 2 A cross-sectional schematic diagram of the landing gear assembly shown in a second state;

[0028] Figure 8 for Figure 2 The schematic cross-sectional view of the landing gear assembly shown is in a third state;

[0029] Fig. 9 for Figure 2 The schematic cross-sectional view of the landing gear assembly shown is in a fourth state. [Specific implementation method]

[0030] For ease of understanding of the present invention, the present invention is described in more detail below in conjunction with the accompanying drawings and specific embodiments. It should be noted that when an element is described as "fixed to" another element, it can be directly on another element, or there can be one or more centered elements therebetween. When an element is described as "connected to" another element, it can be directly connected to another element, or there can be one or more centered elements therebetween. The terms "vertical", "horizontal", "left", "right", "inside", "outside" and similar expressions used in this specification are for illustrative purposes only.

[0031] Unless otherwise defined, all technical and scientific terms used in this specification have the same meaning as those commonly understood by those skilled in the art of the present invention. The terms used in the specification of the present invention are only for the purpose of describing specific embodiments and are not intended to limit the present invention. The term "and / or" used in this specification includes any and all combinations of one or more of the related listed items.

[0032] See also Figure 1 An unmanned aerial vehicle 100 provided in one embodiment of the present invention may be a multi-rotor unmanned aerial vehicle, a fixed-wing unmanned aerial vehicle or a tilt-rotor unmanned aerial vehicle. In this embodiment, the unmanned aerial vehicle 100 is taken as an example of a tilt-rotor unmanned aerial vehicle for detailed description.

[0033] The unmanned aerial vehicle 100 is a symmetrical structure as a whole, having a symmetry plane M. The unmanned aerial vehicle 100 includes a fuselage 10, two wings 20, two sets of propeller assemblies 30, and a landing gear assembly 40. The two wings 20 are arranged on two opposite sides of the fuselage 10, the two sets of propeller assemblies 30 are respectively arranged on the two wings 20, and the landing gear assembly 40 is arranged on the fuselage 10.

[0034] The fuselage 10 is generally in a long shuttle shape and is symmetrical with respect to the symmetry plane M. The fuselage 10 is provided with a mounting plate 11 , which can be detachably connected to the fuselage 10 , for example, by a threaded connector, and the mounting plate 11 can also be integrally formed with the fuselage 10 .

[0035] The mounting plate 11 is in the shape of a flat plate as a whole, and has a mounting surface 110 . The mounting surface 110 is a side of the mounting plate 11 facing away from the body 10 .

[0036] The two wings 20 are symmetrically distributed relative to the symmetry plane M.

[0037] The two groups of propeller assemblies 30 are symmetrically distributed relative to the symmetry plane M. The two groups of propeller assemblies 30 can rotate relative to the two wings 20 respectively. For example, the two groups of propeller assemblies 30 rotate 90 degrees to provide vertically upward lift, so that the unmanned aerial vehicle 100 can take off and take off vertically.

[0038] There are two landing gear assemblies 40 , and the two landing gear assemblies 40 are symmetrically distributed relative to the symmetry plane M.

[0039] Please also read Figure 2 The landing gear assembly 40 includes a landing gear 42 and a clamping structure 43 . The landing gear 42 is mounted on the mounting plate 11 . The clamping structure 43 connects the mounting plate 11 and the landing gear 42 .

[0040] It is understandable that, according to actual conditions, the mounting plate 11 can be omitted, that is, the mounting surface 110 is directly disposed on the fuselage 10 .

[0041] The mounting surface 110 is provided with a mounting groove 111, and the mounting groove 111 is a circular groove. One end of the landing gear 42 is accommodated in the mounting groove 111, and the bottom of the mounting groove 111 is provided with a first contact surface 112. The shaft hole 113 and the at least two locking holes 114 are both provided on the landing gear 42, and the shaft hole 113 has a center line S, and the shaft hole is connected to the interior of the fuselage 10. The shaft hole 113 and the at least two locking holes 114 are formed correspondingly to the first contact surface 112, that is, the shaft hole 113 and the at least two locking holes 114 are both recessed from the first contact surface 112 along the direction of the center line S, and the opening of the shaft hole 113 and the opening of the at least two locking holes 114 are both opened on the first contact surface.

[0042] Please also read Figure 3 and Figure 4 , the center line S is arranged at a first angle a with the symmetry plane M, and the first angle a is an acute angle, so that when the landing gear 42 rotates around the center line S relative to the mounting plate 11, the opening and closing angle c between the landing gear 42 and the symmetry plane changes, so that the landing gear 42 can be deployed or folded relative to the fuselage 10. When the landing gear 42 is deployed relative to the fuselage 10, the opening and closing angle c is the maximum value; when the landing gear 42 is folded relative to the fuselage 10, the opening and closing angle c is the minimum value.

[0043] Specifically, the opening of the first angle between the center line S and the symmetry plane M is toward the tail of the fuselage 10, and when the unmanned aerial vehicle 100 flies horizontally, the center line S is set horizontally, so that the landing gear is subject to small air resistance during the flight of the unmanned aerial vehicle.

[0044] The at least two locking holes 114 are distributed circumferentially around the center line S. Preferably, the at least two locking holes 114 are distributed equidistantly. Any one of the at least two locking holes 114 can be a through hole or a blind hole, which is not limited in this embodiment.

[0045] In this embodiment, any one of the at least two locking holes 114 is cylindrical.

[0046] In some other embodiments, see Figure 5 Any one of the at least two locking holes 114 is hemispherical.

[0047] The at least two locking holes 114 include a first locking hole and a second locking hole, and the first locking hole and the second locking hole are symmetrically arranged relative to the center line S.

[0048] Please refer to Figure 2The landing gear 42 includes a supporting portion 420 and a connecting portion 421 extending from one end of the supporting portion 420 .

[0049] The support portion 420 is in a long column shape and is used to support the fuselage 10 when the landing gear 42 is deployed relative to the fuselage 10 .

[0050] The connecting portion 421 is in a long columnar shape, the axis of the connecting portion 421 coincides with the center line S, the connecting portion 421 and the supporting portion 420 form a second angle b, and the second angle b is an obtuse angle, so that when the landing gear 42 is deployed relative to the fuselage 10, the end of the supporting portion 420 close to the connecting portion 421 is closer to the symmetry plane M than the end far from the connecting portion 421, that is, the supporting portions 420 of the two supporting frames 42 are in an eight-shaped shape, so that the stability of the landing gear 42 supporting the fuselage 10 is improved.

[0051] Furthermore, the second angle b is greater than or equal to the supplementary angle of the first angle a, that is, the second angle b is greater than or equal to the difference between 180 degrees and the first angle a, so that when the landing gear 42 is folded relative to the fuselage 10, the end of the support portion 420 close to the connecting portion 421 is closer to the tail of the fuselage 10 than the end far from the connecting portion 421, so that the support portion 420 is parallel or tends to be parallel to the symmetry plane M.

[0052] A second contact surface 423 is disposed at one end of the connecting portion 421 away from the supporting portion 420 .

[0053] The second contact surface 423 faces the first contact surface 112, and a rotating shaft 424 and a locking pin 425 are disposed on the second contact surface 423. The rotating shaft 424 and the locking pin 425 both extend along the center line S toward the second contact surface 423.

[0054] The rotating shaft 424 is adapted to the shaft hole 113 , and the rotating shaft 424 is used to be inserted into the shaft hole 113 .

[0055] It can be understood that, according to actual conditions, the positions of the rotating shaft 424 and the axial hole 113 can be interchanged, that is, the rotating shaft 424 is arranged on the first contact surface 112, and the axial hole 113 is arranged on the second contact surface 423. As long as one of the first contact surface 112 and the second contact surface 423 is provided with the axial hole 113, the other one is provided with the rotating shaft 424.

[0056] The locking pin 425 is matched with any one of the at least two locking holes 114 , and the locking pin 425 is used to be inserted into any one of the at least two locking holes 113 .

[0057] It can be understood that, according to actual conditions, the positions of the locking pin 425 and the at least two locking holes 114 can be interchanged, that is, the locking pin 425 is arranged on the first contact surface 112, and the at least two locking holes 114 are arranged on the second contact surface 423. As long as one of the first contact surface 112 and the second contact surface 123 is provided with the locking pin 425, the other one is provided with the at least two locking holes 114.

[0058] The lock pin 425 includes a first lock pin and a second lock pin, wherein the first lock pin is used to be inserted into one of the first lock hole and the second lock hole, and the second lock pin is used to be inserted into the other of the first lock hole and the second lock hole. When the first lock pin is inserted into the first lock hole, the second lock pin is inserted into the second lock hole; when the second lock pin is inserted into the second lock hole, the second lock pin is inserted into the first lock hole.

[0059] Please also read Figures 6 to 9 , the rotating shaft 424 is inserted into the shaft hole 113, as Figure 6 and Figure 7 As shown, on the one hand, the rotating shaft 424 can move relative to the shaft hole 113 along the center line S, that is, the landing gear 42 can move relative to the mounting plate 11 along the center line S; Figure 8 and Fig. 9 As shown, on the other hand, when the locking pin 425 is not inserted into the locking hole 114, the rotating shaft 424 can rotate around the center line S relative to the shaft hole 113, that is, the landing gear 42 can rotate around the center line S relative to the mounting plate 11.

[0060] When the landing gear 42 rotates relative to the mounting plate 11 , the locking pin 425 can be aligned with any one of the at least two locking holes 114 , so that the locking pin 425 can be inserted into a locking hole 114 aligned therewith.

[0061] When the locking pin 425 is inserted into any one of the at least two locking holes 114, the landing gear 42 cannot rotate relative to the mounting plate 11 around the center line S, that is, the landing gear 42 is fixed relative to the mounting plate 11 in the direction around the center line S. By arranging the locking pin 425 and the locking hole 114 between the landing gear 42 and the mounting plate 11, the landing gear 42 will not rotate when the landing gear 42 is unfolded or folded relative to the fuselage 10, thereby improving the stability of the landing gear 42 supporting the fuselage 10.

[0062] When the landing gear 42 is folded relative to the fuselage 10, the locking pin 425 is inserted into one of the two locking holes 114, so that the landing gear 42 cannot rotate around the center line S relative to the mounting plate 11, that is, the landing gear 42 is fixed relative to the mounting plate 11 in the direction around the center line S; when the landing gear 42 is unfolded relative to the fuselage 10, the locking pin 425 is inserted into the other of the two locking holes 114, so that the landing gear 42 cannot rotate around the center line S relative to the mounting plate 11, that is, the landing gear 42 is fixed relative to the mounting plate 11 in the direction around the center line S.

[0063] When the landing gear 42 is unfolded or folded relative to the fuselage 10 , the landing gear 42 may move relative to the mounting plate 11 along the center line S, so that the locking pin 425 is separated from the locking hole 114 .

[0064] The clamping structure 43 is used to provide a clamping force to bring the mounting plate 11 and the landing gear 42 closer to each other along the center line S, so that the first contact surface 112 and the second contact surface 423 are in abutment with each other.

[0065] The clamping structure 43 includes a clamping plate 430 and an elastic member 431. The clamping plate 430 is connected to one end of the rotating shaft 424 passing through the shaft hole 113. Preferably, the clamping plate 430 and the rotating shaft 424 are connected by threads. The elastic member 431 is connected between the clamping plate 430 and the mounting plate 11. When the landing gear 42 moves along the center line S relative to the mounting plate 11 so that the locking pin 425 is separated from the pin hole 114, the elastic member 431 is compressed to provide a clamping force that abuts the first contact surface 112 and the second contact surface 423.

[0066] The elastic member 431 is a compression spring, which is sleeved on one end of the rotating shaft 424 passing through the shaft hole 113, and the compression spring abuts between the mounting plate 11 and the pressure plate 430. According to actual conditions, the compression spring can also be replaced by a spring sheet, an elastic rubber ball, etc.

[0067] It should be noted that, according to actual conditions, the elastic member 431 can also be replaced by two magnetic members. For example, magnetic members that attract each other are respectively embedded on the two opposite surfaces of the mounting plate 11 and the pressure plate 430, which can also provide a clamping force to abut the first contact surface 112 and the second contact surface 423. In addition, when the landing gear 42 moves along the center line S relative to the mounting plate 11, so that the locking pin 425 gradually separates from the locking hole 114, the clamping force gradually increases.

[0068] When the unmanned aerial vehicle 100 is in use, the landing gear 42 is unfolded or folded relative to the fuselage 10. When the landing gear 42 needs to switch states, for example, the landing gear 42 switches from the unfolded state to the folded state, the switching can be performed by the following steps:

[0069] First, the landing gear 42 moves relative to the mounting plate 11 along the center line S, so that the first contact surface 112 and the second contact surface 423 move away from each other, and at the same time, the locking pin 425 is separated from the locking hole 114;

[0070] Then, after the locking pin 424 is separated from the locking hole 114 , the landing gear 42 can be rotated relative to the mounting plate 11 around the center line S so that the locking pin 425 is aligned with a corresponding one of the at least two locking holes 114 .

[0071] Finally, after the locking pin 425 is aligned with a corresponding one of the at least two locking holes 114, the landing gear 42 moves along the center line S relative to the mounting plate 11, so that the first contact surface 112 contacts the second contact surface 423, and the locking pin 425 is inserted into the locking hole 114 aligned therewith, that is, the landing gear 42 completes the switch from the deployed state to the folded state.

[0072] Compared with the prior art, in the unmanned aerial vehicle 100 provided in the embodiment of the present invention, the unmanned aerial vehicle 100 is equipped with a landing gear assembly 40, and the landing gear 42 in the landing gear assembly 40 can be unfolded or folded relative to the fuselage 10, so as to achieve the convenience of carrying.

[0073] In addition, the landing gear assembly 40 is a non-electric landing gear assembly, and the landing gear 42 can be manually driven by the user to fold or unfold relative to the fuselage 10, so that the unmanned aerial vehicle 100 equipped with the landing gear assembly 40 consumes less power. Since there is no motor, the unmanned aerial vehicle 100 is lighter.

[0074] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit them. Under the concept of the present invention, the technical features in the above embodiments or different embodiments may also be combined, the steps may be implemented in any order, and there are many other changes in different aspects of the present invention as described above, which are not provided in detail for the sake of simplicity. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they may still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. An unmanned aerial vehicle (100), characterized in that: It comprises a fuselage (10) and a landing gear assembly (40) mounted on the fuselage (10), wherein the landing gear assembly (40) comprises: A landing gear (42), the landing gear (42) being rotatable relative to the fuselage (10) about a centerline (S); a clamping structure (43), one end of the clamping structure (43) being connected to the landing gear (42) and the other end being connected to the fuselage (10), the clamping structure (43) being used to provide a clamping force that causes the landing gear (42) to approach the fuselage (10) along the center line (S); One of the fuselage (10) and the landing gear (42) is provided with a lock hole (114), and the other of the fuselage (10) and the landing gear (42) is provided with a lock pin (425); The locking pin (425) cooperates with the locking hole (114) so ​​that the position of the landing gear (42) relative to the fuselage (10) is locked; The locking pin (425) can be separated from the locking hole (114) so ​​that the landing gear (42) can rotate relative to the fuselage (10) around the center line (S); The center line (S) is arranged at a first angle with the symmetry plane M, the first angle is an acute angle, and the opening of the first angle faces the tail of the fuselage; One of the landing gear (42) and the fuselage (10) is provided with a rotating shaft (424) arranged along the center line (S), and the other is provided with an axis hole (113), and the rotating shaft (424) is inserted into the axis hole (113); The rotating shaft (424) moves along the center line (S) relative to the shaft hole (113) corresponding thereto, so that the locking pin (425) is separated from the locking hole (114).

2. The unmanned aerial vehicle (100) according to claim 1, characterized in that: The fuselage (10) is further provided with a mounting plate (11), one of the mounting plate (11) and the landing gear (42) being provided with the locking hole (114), and the other of the mounting plate (11) and the landing gear (42) being provided with the locking pin (425).

3. The unmanned aerial vehicle (100) according to claim 2, characterized in that: The locking pin (425) is provided on the landing gear (42), and the locking hole (114) is provided on the mounting plate (11).

4. The unmanned aerial vehicle (100) according to claim 3, characterized in that: The mounting plate (11) has a first contact surface (112), and the landing gear (42) has a second contact surface (423) facing the first contact surface (112) and in contact with the first contact surface (112); The locking pin (425) is disposed on the first contact surface (112), and the locking pin (425) extends along the center line (S) toward the second contact surface (423), and the locking hole (114) is correspondingly formed on the second contact surface (423).

5. The unmanned aerial vehicle (100) according to claim 2, characterized in that: The locking hole (114) is provided on the landing gear (42), and the locking pin (425) is provided on the mounting plate (11).

6. The unmanned aerial vehicle (100) according to claim 5, characterized in that: The mounting plate (11) has a first contact surface (112), and the landing gear (42) has a second contact surface (423) facing the first contact surface (112) and in contact with the first contact surface (112); The locking pin (425) is disposed on the second contact surface (423), and the locking pin (425) extends along the center line (S) toward the first contact surface (112), and the locking hole (114) is correspondingly formed on the first contact surface (112).

7. The unmanned aerial vehicle (100) according to any one of claims 4 or 6, characterized in that: The mounting plate (11) is provided with a mounting groove (111), and the first contact surface (423) is the bottom of the mounting groove (111); One end of the landing gear (42) provided with the first contact surface (112) is received in the mounting groove (111).

8. The unmanned aerial vehicle (100) according to any one of claims 2 to 6, characterized in that: The rotating shaft (424) is arranged on the landing gear (42), the shaft hole (113) is arranged on the mounting plate (11), and the shaft hole (113) passes through the mounting plate (11) and is connected to the interior of the fuselage (10).

9. The unmanned aerial vehicle according to claim 8, characterized in that: The pressing structure (43) comprises a pressing plate (430) and an elastic member (431); The pressing plate (430) is arranged at one end of the rotating shaft (424) passing through the shaft hole (113), the elastic member (431) is sleeved on the rotating shaft (424), and the elastic member (431) is abutted between the pressing plate (430) and the mounting plate (11).

10. The unmanned aerial vehicle (100) according to claim 9, characterized in that: The elastic member (431) is a compression spring.

11. The unmanned aerial vehicle (100) according to claim 9 or 10, characterized in that: The pressing plate (430) is threadedly connected to the rotating shaft (424).

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