WO2020135448A1

WO2020135448A1 - Unmanned aerial vehicle

Info

Publication number: WO2020135448A1
Application number: PCT/CN2019/128059
Authority: WO
Inventors: 梁智颖
Original assignee: 深圳市道通智能航空技术有限公司
Priority date: 2018-12-24
Filing date: 2019-12-24
Publication date: 2020-07-02
Also published as: CN109552602A

Abstract

An unmanned aerial vehicle (100), comprising an unmanned aerial vehicle body (10) and an undercarriage assembly (40) mounted on the unmanned aerial vehicle body. The undercarriage assembly comprises a mounting plate, an undercarriage (42), and a pressing structure (43). The mounting plate is connected to the unmanned aerial vehicle body. The undercarriage is mounted on the mounting plate. The undercarriage can rotate around a central line with respect to the mounting plate. Locking holes (114) are formed in one of the mounting plate and the undercarriage, and locking pins (425) are arranged on the other one of the mounting plate and the undercarriage. The locking holes are distributed circumferentially around the central line. The pressing structure is connected to the mounting plate and the undercarriage and used for providing the pressing force to enable the mounting plate and the undercarriage to approach each other along the central line. The undercarriage assembly is provided on the unmanned aerial vehicle, and the undercarriage in the undercarriage assembly can be unfolded or folded with respect to the unmanned aerial vehicle body, and therefore, it is convenient to carry the unmanned aerial vehicle.

Description

An unmanned aerial vehicle

【Technical field】

The invention relates to the field of aircraft, and in particular to an unmanned aerial vehicle.

【Background technique】

The landing gear, as an attachment device for unmanned aerial vehicles with bearing and maneuverability, bears an extremely important mission during the safe takeoff and landing of the unmanned aerial vehicle, and is one of the important parts of the unmanned aerial vehicle.

At present, the landing gear is generally fixed.

However, in the process of implementing the present invention, the inventor found that the use of a fixed landing gear is not convenient to carry. Therefore, the existing technology needs improvement.

[Invention content]

In order to solve the above technical problems, embodiments of the present invention provide an unmanned aerial vehicle equipped with a landing gear, which is easy to carry.

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

An unmanned aerial vehicle is provided, which includes a fuselage and a landing gear assembly mounted on the fuselage, the landing gear assembly includes: a landing gear, the landing gear may be relative to the fuselage about a centerline Rotation; compression structure, one end of the compression structure is connected to the rotating shaft, and the other end is connected to the fuselage, the compression structure is used to provide the landing gear close to the fuselage along the centerline The pressing force of one of the fuselage and the landing gear is provided with a lock hole, and the other of the fuselage and the landing gear is provided with a lock pin; The lock hole cooperates so that the position of the landing gear relative to the fuselage is locked; the lock pin can be separated from the lock hole so that the landing gear can be rotated around the center relative to the fuselage The line turns.

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 lock hole, and the mounting plate and the landing gear are both The other is provided with the lock pin.

In some embodiments, the lock pin is provided on the landing gear, and the lock hole is provided on the mounting plate.

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 provided on the The first contact surface, and the lock pin extends along the center line toward the second contact surface, and the lock hole is formed on the second contact surface accordingly.

In some embodiments, the lock hole is provided on the landing gear, and the lock pin is provided on the mounting plate.

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 provided on the The second contact surface, and the lock pin extends along the center line toward the first contact surface, and the lock hole is formed on the first contact surface accordingly.

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

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

In some embodiments, the rotating shaft is provided on the landing gear, the shaft hole is provided on the mounting plate, and the shaft hole penetrates the mounting plate and communicates with the inside of the fuselage.

In some embodiments, the pressing structure includes a pressing plate and an elastic member; the pressing plate is disposed at an end of the rotating shaft passing through the shaft hole, the elastic member is sleeved on the rotating shaft, and the elastic member resists It is connected between the pressing plate and the mounting plate.

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

In some embodiments, the pressure plate is screwed to the rotating shaft.

Compared with the prior art, in an unmanned aerial vehicle according to an embodiment of the present invention, the unmanned aerial vehicle is configured with a landing gear assembly, and the landing gear in the landing gear assembly can be deployed relative to the fuselage or Folding can make the UAV easy to carry.

[Description of the drawings]

One or more embodiments are exemplified by the corresponding drawings. These exemplary descriptions do not constitute a limitation on the embodiments. Elements with the same reference numerals in the drawings are represented as similar elements unless there are special It is stated that the figures in the drawings do not constitute a scale limitation.

1 is a perspective view of an unmanned aerial vehicle according to one embodiment of the present invention;

2 is a cross-sectional view of the landing gear assembly of the UAV shown in FIG. 1, wherein the landing gear of the landing gear assembly is partially omitted;

FIG. 3 is a top view of the UAV shown in FIG. 1, in which parts of the UAV are omitted;

4 is a front view of the UAV shown in FIG. 1, in which the length of the two wings is omitted;

5 is a cross-sectional view of the landing gear assembly shown in FIG. 2 in another embodiment, in which the landing gear is partially omitted;

6 is a schematic cross-sectional view of the landing gear assembly shown in FIG. 2 in a first state;

7 is a schematic cross-sectional view of the landing gear assembly shown in FIG. 2 in a second state;

8 is a schematic cross-sectional view of the landing gear assembly shown in FIG. 2 in a third state;

9 is a schematic cross-sectional view of the landing gear assembly shown in FIG. 2 in a fourth state.

【detailed description】

In order to facilitate understanding of the present invention, the present invention will be described in more detail with reference to the accompanying drawings and specific embodiments. It should be noted that when an element is expressed as "fixed" to another element, it may be directly on the other element, or there may be one or more centered elements in between. When an element is expressed as "connecting" another element, it may be directly connected to the other element, or one or more centered elements may be present therebetween. The terms "vertical", "horizontal", "left", "right", "inner", "outer", and similar expressions used in this specification are for illustrative purposes only.

Unless otherwise defined, all technical and scientific terms used in this specification have the same meaning as commonly understood by those skilled in the technical field of the present invention. The terms used in the description 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 related listed items.

Referring to FIG. 1, an unmanned aerial vehicle 100 according to one embodiment of the present invention may be a multi-rotor drone, a fixed-wing drone, or a tilt-rotor drone. In this embodiment, the The unmanned aerial vehicle 100 is a tilt-rotor drone as an example for detailed description.

The UAV 100 has a symmetrical structure as a whole and has a plane of symmetry M. The UAV 100 includes a fuselage 10, two wings 20, two sets of propeller assemblies 30, and a landing gear assembly 40. Wherein the two wings 20 are disposed on opposite sides of the fuselage 10, the two sets of propeller assemblies 30 are respectively disposed on the two wings 20, and the landing gear assembly 40 is disposed on the On the fuselage 10.

The fuselage 10 has a generally long shuttle shape and is symmetrical with respect to the symmetry plane M. The body 10 is provided with a mounting plate 11 that can be detachably connected to the body 10, for example, by a threaded connection, the mounting plate 11 can also be connected to the body 10 One piece.

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

The two wings 20 are distributed symmetrically with respect to the symmetry plane M.

The two sets of propeller assemblies 30 are symmetrically distributed with respect to the plane of symmetry M. The two sets of propeller assemblies 30 can rotate relative to the two wings 20, for example, the two sets of propeller assemblies 30 rotate 90 degrees, In order to provide vertical upward lift, the UAV 100 can be lifted vertically.

The number of the landing gear assemblies 40 is two, and the two landing gear assemblies 40 are symmetrically distributed with respect to the symmetry plane M.

Please refer to FIG. 2 together. The landing gear assembly 40 includes a landing gear 42 and a pressing structure 43. The landing gear 42 is mounted on the mounting plate 11. The pressing structure 43 connects the mounting plate 11 and the starting structure.落架42。 42.

It can be understood that, according to the actual situation, the mounting plate 11 may be omitted, that is, the mounting surface 110 is directly disposed on the body 10.

The mounting surface 110 is provided with a mounting groove 111, the mounting groove 111 is a circular groove, one end of the landing gear 42 is received in the mounting groove 111, and a first contact surface 112 is provided on the bottom of the mounting groove 111 , The shaft hole 113 and the at least two lock holes 114 are both provided in the landing gear 42, the shaft hole 113 has a center line S, the shaft hole communicates with the inside of the body 10, the The shaft hole 113 and the at least two lock holes 114 are correspondingly formed with the first contact surface 112, that is, the shaft hole 113 and the at least two lock holes 114 are along the center line The direction of S is recessed from the first contact surface 112. The openings of the shaft hole 113 and the openings of the at least two lock holes 114 are both opened on the first contact surface.

3 and FIG. 4 together, the center line S and the symmetry plane M are set at a first angle a, the first angle a is an acute angle, so that the landing gear 42 is relative to the mounting plate 11 When rotating around the center line S, the opening and closing angle c of the landing gear 42 and the symmetry plane changes, so that the landing gear 42 can be unfolded 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.

Specifically, the opening at the first angle between the centerline S and the symmetry plane M is toward the tail of the fuselage 10, and when the UAV 100 is flying horizontally, the centerline The S level is set so that during the flight of the UAV, the air resistance to the landing gear is small.

The at least two lock holes 114 are distributed circumferentially around the center line S. Preferably, the at least two lock holes 114 are equally spaced. Any one of the at least two lock holes 114 may be a through hole or a blind hole, which is not limited in this embodiment.

In this embodiment, any one of the at least two lock holes 114 is cylindrical.

In some other embodiments, please refer to FIG. 5, any one of the at least two lock holes 114 is hemispherical.

The at least two lock holes 114 include a first lock hole and a second lock hole, and the first lock hole and the second lock hole are arranged symmetrically with respect to the center line S.

Please refer back to FIG. 2. The landing gear 42 includes a supporting portion 420 and a connecting portion 421 extending at one end of the supporting portion 420.

The support portion 420 has a long column shape, and the support portion 420 is used to support the fuselage 10 when the landing gear 42 is unfolded relative to the fuselage 10.

The connecting portion 421 has a long column 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 support portion 420 closer to the connecting portion 421 is closer to the symmetry plane M than the end farther away from the connecting portion 421, That is, the support portions 420 of the two support frames 42 are in a figure eight shape, so that the stability of the landing gear 42 to support the fuselage 10 is improved.

Further, 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 supporting portion 420 closer to the connecting portion 421 is closer to the tail portion of the fuselage 10 than the end farther away from the connecting portion 421, so that the support The portion 420 is parallel or tends to be parallel to the symmetry plane M.

An end of the connecting portion 421 facing away from the supporting portion 420 is provided with a second contact surface 423.

The second contact surface 423 faces the first contact surface 112, and a rotating shaft 424 and a locking pin 425 are provided 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.

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.

It can be understood that, according to the actual situation, the positions of the rotating shaft 424 and the shaft hole 113 can be interchanged, that is, the rotating shaft 424 is disposed on the first contact surface 112, and the shaft hole 113 is disposed on the first For the two contact surfaces 423, as long as one of the first contact surface 112 and the second contact surface 423 is provided with the shaft hole 113, the other is provided with the rotating shaft 424.

The lock pin 425 is adapted to any one of the at least two lock holes 114. The lock pin 425 is used to be inserted into any one of the at least two lock holes 113.

It can be understood that, according to the actual situation, the positions of the lock pin 425 and the at least two lock holes 114 can be interchanged, that is, the lock pin 425 is disposed on the first contact surface 112, and the at least two The lock hole 114 is provided 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 lock pin 425 and the other is provided with the at least two A keyhole 114 is sufficient.

The lock pin 425 includes a first lock pin and a second lock pin, the first lock pin is used to insert into one of the first lock hole and the second lock hole, and the second lock pin is used to Insert the other of the first lock hole and the second lock hole. When the first locking pin is inserted into the first locking hole, the second locking pin is inserted into the second locking hole; when the second locking pin is inserted into the second locking hole, the second The lock pin is inserted into the first lock hole.

Please refer to FIGS. 6-9 together, the rotating shaft 424 is inserted into the shaft hole 113, as shown in FIGS. 6 and 7, on the one hand, the rotating shaft 424 can be relative to the shaft hole 113 along the center The line S moves, that is, the landing gear 42 can move along the center line S relative to the mounting plate 11; as shown in FIGS. 8 and 9, on the other hand, the lock pin 425 is not inserted into the When the hole 114 is locked, the rotating shaft 424 can rotate about the center line S relative to the shaft hole 113, that is, the landing gear 42 can rotate about the center line S relative to the mounting plate 11.

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 one aligned with it Keyhole 114.

When the lock pin 425 is inserted into any one of the at least two lock holes 114, the landing gear 42 cannot rotate about the center line S relative to the mounting plate 11, that is, the landing gear 42 is winding The direction of the center line S is fixed relative to the mounting plate 11. By providing the lock pin 425 and the lock hole 114 between the landing gear 42 and the mounting plate 11, the landing gear 42 can be extended when the landing gear 42 is expanded or folded relative to the fuselage 10. 42 will not rotate, which improves the stability of the landing gear 42 to support the fuselage 10.

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 be wound around the mounting plate 11 The center line S rotates, that is, the landing gear 42 is fixed relative to the mounting plate 11 in a direction around the center line S; when the landing gear 42 is deployed relative to the fuselage 10, the lock The pin 425 is inserted into the other of the two lock holes 114, so that the landing gear 42 cannot rotate about the center line S relative to the mounting plate 11, that is, the landing gear 42 is around the center line The direction of S is fixed with respect to the mounting plate 11.

When the landing gear 42 is unfolded or folded relative to the fuselage 10, the landing gear 42 can move relative to the mounting plate 11 along the center line S, so that the locking pin 425 and the locking hole 114 separate.

The pressing structure 43 is used to provide a pressing force for bringing 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 Contact.

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

The elastic member 431 is a compression spring, which is sleeved on an end of the rotating shaft 424 passing through the shaft hole 113, and the compression spring abuts between the mounting plate 11 and the compression plate 430. According to the actual situation, the compression spring can also be replaced by a shrapnel, an elastic rubber ball, or the like.

It should be noted that, according to the actual situation, the elastic member 431 can also be replaced by two magnetic members, for example, magnetic members attracting magnetic attraction are embedded on the two surfaces of the mounting plate 11 and the pressing plate 430 opposite to each other , It is also possible to provide a pressing force that abuts the first contact surface 112 and the second contact surface 423, and the landing gear 42 moves relative to the mounting plate 11 along the center line S so that As the lock pin 425 gradually separates from the lock hole 114, the pressing force gradually increases.

When the UAV 100 is in use, the landing gear 42 is unfolded or folded relative to the fuselage 10, and when the landing gear 42 needs to switch states, for example, the landing gear 42 is switched from the deployed state To the folded state, you can switch through the following steps:

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 are away from each other, and at the same time, the lock pin 425 is The keyhole 114 is separated;

Then, after the locking pin 424 is separated from the locking hole 114, the landing gear 42 can rotate relative to the mounting plate 11 about the center line S, so that the locking pin 425 is aligned with the at least The corresponding one of the two keyholes 114.

Finally, after the locking pin 425 is aligned with the corresponding one of the at least two locking holes 114, the landing gear 42 moves relative to the mounting plate 11 along the center line S, so that the first The contact surface 112 is in contact with the second contact surface 423, and the lock pin 425 is inserted into the lock hole 114 aligned therewith, that is, the landing gear 42 is completely switched from the unfolded state to the folded state.

Compared with the prior art, in the UAV 100 provided by the embodiment of the present invention, the UAV 100 is configured with a landing gear assembly 40, and the landing gear 42 in the landing gear assembly 40 may be relative to the aircraft The body 10 can be unfolded or folded to achieve the convenience of carrying.

In addition, the landing gear assembly 40 is a non-electric landing gear assembly, which can be folded or unfolded relative to the fuselage 10 by the user manually driving the landing gear 42 to realize the unmanned aerial vehicle 100 equipped with the landing gear assembly 40 The power consumption is small, and because there is no motor, the UAV 100 is light in weight.

Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, not to limit them; under the idea of the present invention, the technical features in the above embodiments or different embodiments may also be combined, The steps can be implemented in any order, and there are many other variations of the different aspects of the present invention as described above. For simplicity, they are not provided in the details; although the present invention has been described in detail with reference to the foregoing embodiments, it is common in the art The skilled person should understand that they can still modify the technical solutions described in the foregoing embodiments, or equivalently replace some of the technical features; and these modifications or replacements do not deviate from the essence of the corresponding technical solutions from the implementation of the present invention. Examples of technical solutions.

Claims

An unmanned aerial vehicle (100), characterized by comprising a fuselage (10) and a landing gear assembly (40) mounted on the fuselage (10), the landing gear assembly (40) comprising:

Landing gear (42), the landing gear (42) can rotate relative to the fuselage (10) about a center line (S);

A pressing structure (43), one end of the pressing structure (43) is connected to the rotating shaft (424) and the other end is connected to the fuselage (10), and the pressing structure (43) is used to provide The pressing force of the landing gear (42) near the fuselage (10) along the center line (S);

One of the fuselage (10) and the landing gear (42) is provided with a keyhole (114), and the other of the fuselage (10) and the landing gear (42) is provided With locking 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 lock pin (425) can be separated from the lock hole (114) so that the landing gear (42) can rotate about the center line (S) relative to the fuselage (10).
The UAV (100) according to claim 1, characterized in that the fuselage (10) is further provided with a mounting plate (11), the mounting plate (11) and the landing gear (42) are both One of them is provided with the lock hole (114), and the other of the mounting plate (11) and the landing gear (42) is provided with the lock pin (425).
The UAV (100) according to claim 2, wherein the locking pin (425) is provided on the landing gear (42), and the locking hole (114) is provided on the mounting plate (100) 11) On.
The UAV (100) according to claim 3, wherein the mounting plate (11) has a first contact surface (112), and the landing gear (42) has a direction toward the first contact surface (100) 112) and a second contact surface (423) in contact with the first contact surface (112);

The locking pin (425) is provided on the first contact surface (112), and the locking pin (425) extends along the center line (S) toward the second contact surface (423), the A lock hole (114) is correspondingly formed on the second contact surface (423).
The UAV (100) according to claim 2, characterized in that the lock hole (114) is provided on the landing gear (42), and the lock pin (425) is provided on the mounting plate (100) 11) On.
The UAV (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 direction toward the first contact surface (100) 112) and a second contact surface (423) in contact with the first contact surface (112);

The lock pin (425) is provided on the second contact surface (423), and the lock pin (425) extends along the center line (S) toward the first contact surface (112), the A lock hole (114) is correspondingly formed on the first contact surface (112).
The unmanned aerial vehicle (100) according to any one of claims 2-6, characterized in that, the mounting plate (11) is provided with a mounting groove (111), and the second contact surface (112) is Describe the slot bottom of the mounting slot (111);

One end of the landing gear (42) provided with the first contact surface (112) is received in the mounting groove (111).
The UAV (100) according to any one of claims 1-7, wherein one of the landing gear (42) and the fuselage (10) is provided along the center The rotating shaft (424) provided by the line (S) is provided with a shaft hole (113), and the rotating shaft (424) is inserted into the shaft hole (113).
The UAV (100) according to claim 8, characterized in that the rotating shaft (424) is provided on the landing gear (42), and the shaft hole (113) is provided on the mounting plate (11) ), and the shaft hole (113) penetrates the mounting plate (11) and communicates with the inside of the body (10).
The unmanned aerial vehicle according to claim 9, characterized in that the pressing structure (43) includes a pressing plate (430) and an elastic member (431);

The pressing plate (430) is disposed at an 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) Abutting between the pressing plate (430) and the mounting plate (11).
The unmanned aerial vehicle (100) according to claim 10, wherein the elastic member (431) is a compression spring.
The unmanned aerial vehicle (100) according to claim 10 or 11, wherein the pressure plate (430) is screwed to the rotating shaft (424).