WO2019023899A1

WO2019023899A1 - Vibration reduction mechanism and unmanned aerial vehicle

Info

Publication number: WO2019023899A1
Application number: PCT/CN2017/095319
Authority: WO
Inventors: 张松; 张永生; 梁贵彬
Original assignee: 深圳市大疆创新科技有限公司
Priority date: 2017-07-31
Filing date: 2017-07-31
Publication date: 2019-02-07
Also published as: CN108513602B; CN108513602A

Abstract

Disclosed are a vibration reduction mechanism and an unmanned aerial vehicle (10) using the vibration reduction mechanism. The vibration reduction mechanism is installed on the unmanned aerial vehicle, the unmanned aerial vehicle comprises a fuselage (6), and the vibration reduction mechanism comprises connecting columns (3) penetrating through the fuselage (6), and first vibration reduction structures (2) arranged at upper and lower ends of the connecting columns, wherein the connecting columns (3) are removably connected to the fuselage (6), and the first vibration reduction structures (2) are connected to a mounting structure (5) for carrying mounted devices so as to realize vibration reduction for the mounted devices. The vibration reduction mechanism can effectively realize, by means of the first vibration reduction structures arranged at the upper and lower ends of the connecting columns, a vibration reduction effect for the mounted devices, has a simple structure, and is convenient to install/remove. When the vibration reduction mechanism is installed on the unmanned aerial vehicle, the influence of the vibration environment of the unmanned aerial vehicle on precise instruments, such as a pan-tilt camera and a video camera, can be effectively reduced, so that the photographing precision and effect of a photographing mechanism is ensured and user requirements can be met, thereby improving the practicality of the vibration reduction mechanism.

Description

Shock absorption mechanism and drone

Technical field

The invention relates to the technical field of drones, in particular to a shock absorbing mechanism and a drone.

Background technique

With the rapid development of science and technology, the equipment used in the field of photography is more and more diversified. Under normal circumstances, when performing aerial photography, it is often necessary for the drone to perform auxiliary shooting, and the shooting device is set in the drone. On the gimbal, at this time, the drone can be used as an auxiliary device for shooting, which can effectively ensure the accuracy and quality of the captured picture. However, during the operation, the vibration environment of the drone will have a great influence on the precision instruments such as the PTZ camera and the camera, which may easily fail to meet the actual application requirements.

In order to meet the needs of practical applications, a shock absorbing mechanism can be installed on the drone. In the prior art, the device for absorbing the vibration of the aircraft pan/tilt mainly uses a combination of a damping rubber ball and a damping oil; however, a shock absorber using a rubber ball is used. Due to the poor rigidity of the rubber itself, it is greatly affected by the ambient temperature. It is necessary to use multiple rubber balls in combination. Generally, the volume is relatively large, which is suitable for instruments with relatively small weight. Therefore, it is not suitable for use on drones.

Summary of the invention

The invention provides a shock absorbing mechanism and a drone for solving the vibration environment of the drone existing in the prior art, which has a great influence on a precision instrument such as a pan-tilt camera or a camera, which is easy to cause unsatisfactory The problem of actual application needs.

A first aspect of the present invention is to provide a damper mechanism for mounting on a drone, the drone including a fuselage body, and the damper mechanism including a connecting post that is disposed through the body of the fuselage And a first damper structure disposed at the upper and lower ends of the connecting column, the connecting column is detachably connected to the body body, and the first damper structure is connected with a mounting structure for carrying the mounting device, A shock absorption of the mounting device is achieved.

A second aspect of the present invention is to provide a drone comprising:

Body body

In the above-described damper mechanism, the damper mechanism is coupled to the body body.

The shock absorbing mechanism and the drone provided by the present invention can effectively realize the mounting device by the connecting column disposed through the fuselage main body and the first shock absorbing structure disposed at the upper and lower ends of the connecting column The shock absorption effect is simple, and the installation/disassembly is convenient. When the shock absorbing mechanism is mounted on the drone, the impact of the vibration environment of the drone on the precision instruments such as the pan/tilt camera and the camera can be effectively reduced. It ensures the shooting accuracy and shooting effect of the shooting mechanism, and can meet the user's application requirements, thereby improving the practicality of the shock absorbing mechanism and facilitating the promotion and application of the market.

DRAWINGS

In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings used in the description of the embodiments will be briefly described below. It is obvious that the drawings in the following description are some embodiments of the present invention. Other drawings may also be obtained from those of ordinary skill in the art in view of the drawings.

1 is a schematic exploded view of a shock absorbing mechanism according to an embodiment of the present invention;

2 is a schematic structural view showing an assembly structure of a shock absorbing mechanism according to an embodiment of the present invention;

3 is a schematic diagram of a split structure of a second shock absorbing structure according to an embodiment of the present invention;

4 is a schematic exploded view of a second shock absorbing structure according to an embodiment of the present invention;

FIG. 5 is a schematic structural diagram of an unmanned aerial vehicle according to an embodiment of the present invention; FIG.

FIG. 6 is a schematic structural diagram of an arm of an unmanned aerial vehicle in an unfolded state according to an embodiment of the present invention; FIG.

FIG. 7 is a schematic structural diagram of an arm of a drone in a folded state according to an embodiment of the present invention.

In the picture:

1. The second shock absorbing structure; 101, the horizontal shock absorbing unit;

102, fuselage connector; 103, sliding bearing;

104, a damping connecting member; 2, a first shock absorbing structure;

201, a vertical shock absorbing unit; 202, a second connecting member;

3. Connecting column; 4. First connecting piece;

5, the mounting structure; 6, the fuselage body;

601, upper fuselage body; 602, front fuselage body;

603, the rear fuselage body; 604, the lower fuselage body;

605, the lower cover of the fuselage; 7, the shock absorber spring;

8. Fixed pipe; 9. Third connecting piece;

10, drone; 1001, foldable arm;

1002, straight arm; 1003, power combination;

1004, propeller.

Detailed ways

The technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the drawings in the embodiments of the present invention. It is a partial embodiment of the invention, and not all of the embodiments. All other embodiments obtained by a person of ordinary skill in the art based on the embodiments of the present invention without creative efforts are within the scope of the present invention.

All technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs, unless otherwise defined. The terminology used in the description of the present invention is for the purpose of describing particular embodiments and is not intended to limit the invention. The term "and/or" used herein includes any and all combinations of one or more of the associated listed items.

In the present invention, the terms "installation", "connection", "fixation" and the like are to be understood broadly. For example, "connection" may be a fixed connection, a detachable connection, or an integral connection. For those skilled in the art, the specific meanings of the above terms in the present invention can be understood on a case-by-case basis.

In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", " After, "Left", "Right", "Vertical", "Horizontal", "Top", "Bottom", "Inside", "Outside" The orientation or positional relationship of the indications is based on the orientation or positional relationship shown in the drawings, and is merely for the convenience of describing the present invention and the simplified description, and does not indicate or imply that the device or component referred to has a specific orientation, Azimuth construction and operation are therefore not to be construed as limiting the invention.

Some embodiments of the present invention are described in detail below with reference to the accompanying drawings. The characteristics of the embodiments and examples described below can be combined with each other without conflict.

1 is a schematic exploded view of a shock absorbing mechanism according to an embodiment of the present invention; FIG. 2 is a schematic view showing an assembled structure of a shock absorbing mechanism according to an embodiment of the present invention; The example provides a shock absorbing mechanism for mounting on a drone, the drone includes a fuselage main body 6, and the damper mechanism includes a connecting post 3 that is disposed through the fuselage main body 6 and is disposed on the connecting post. 3, the first shock absorbing structure 2 at the upper and lower ends, the connecting column 3 and the fuselage body 6 are detachably connected, and the first damper structure 2 is connected with a mounting structure 5 for carrying the mounting device to realize the reduction of the mounting device shock.

The first damper structure 2 may be disposed at the upper and lower ends of the connecting column 3, and at this time, the first damping structure 2 may include a damper unit or a plurality of damper units, when the first damper structure 2 includes one In the damper unit, one damper unit can be symmetrically disposed on the upper and lower ends of the connecting column 3; when the first damper structure 2 includes a plurality of damper units, the plurality of damper units can be symmetrically disposed on the connecting column 3 respectively. The upper and lower ends. In addition, the first shock absorbing structure 2 in this embodiment can be used to achieve the shock absorption of the mounting device in the vertical direction, or can also be used to achieve the horizontal damping of the mounting device, or It can also be used to achieve shock absorption in the horizontal and vertical directions of the mounting device. The mounting device may be a shooting mechanism, such as a camera, a video camera, a video recorder, and other devices having a shooting function.

In addition, the specific implementation manner of the detachable connection between the connecting post 3 and the fuselage main body 6 is not limited in this embodiment, and those skilled in the art can set according to specific design requirements. Preferably, the lower end of the connecting post 3 can pass. The fixed pipe 8 is connected to the body main body 6. Specifically, the fixed pipe 8 may be provided with internal or external threads, so that the lower end of the connecting post 3 is screwed with the fuselage main body 6; or the fixing pipe 8 may be provided with a fixing hole corresponding to the connecting post 3 The same fixing hole is provided at the position, and the detachable connection of the connecting post 3 to the fuselage main body 6 is realized by the connecting member passing through the fixing hole, wherein the connecting member may include at least one of the following: a screw, a bolt, a stud and many more.

The shock absorbing mechanism provided in this embodiment is provided through the connecting post 3 of the fuselage main body 6 And the first shock absorbing structure 2 disposed at the upper and lower ends of the connecting column 3 can effectively achieve the shock absorbing effect on the mounting device, and has a simple structure and convenient installation/disassembly, when the shock absorbing mechanism is installed on the drone It can effectively reduce the impact of the vibration environment of the drone on the precision instruments such as the PTZ camera and camera, ensure the shooting accuracy and shooting effect of the shooting mechanism, and at the same time meet the application needs of the user, thereby improving the shock absorption. The practicality of the organization is conducive to the promotion and application of the market.

On the basis of the above-mentioned embodiments, referring to FIG. 1-2, the specific shape and structure of the first shock absorbing structure 2 are not limited in this embodiment, and those skilled in the art can set according to specific application requirements. During the man-machine flight, in the vertical direction, the flight state of the drone has a great influence on the photographing mechanism. Therefore, the first shock absorbing structure 2 may include a plurality of vertical damper units 201 arranged in the vertical direction. The vertical damper unit 201 is disposed between the mounting structure 5 and the body 6 .

The vertical damper unit 201 in this embodiment may include at least one of the following: a damper, a wire rope; wherein, for the wire rope, the wire rope is set to a spring-like structure, and the shock absorbing effect can also be achieved. In addition, the number of the vertical damper units 201 included in the first damper structure 2 is not limited in this embodiment, and can be set by a person skilled in the art according to specific design requirements. For example, the vertical damper unit 201 can be The number is set to 2, 3, 4, or 5, etc.; when a plurality of vertical damper units 201 are connected between the mounting structure 5 and the body 6 for easy implementation and control in the vertical In the direction of the shock absorbing effect of the mounting structure 5, the plurality of vertical damper units 201 can be evenly distributed between the mounting structure 5 and the body 6; further, when the vertical damper unit 201 is an even number, The plurality of vertical damper units 201 can be symmetrically disposed along the central axis of the mounting structure 5, which facilitates accurate and effective control of the first damper structure 2.

In addition, in this embodiment, the connection manner between the vertical damper unit 201 and the mounting structure 5 and the fuselage main body 6 is not limited, and those skilled in the art can set according to specific design requirements, for example, vertical shock absorption can be performed. The unit 201 is fixedly connected or detachably connected to the mounting structure 5 and the body 6; in particular, both ends of the vertical damper unit 201 can pass through the second connecting member 202 and the mounting structure 5 and the body. 6 phase connection. The second connecting member 202 may have a concave structure. Specifically, the second connecting member 202 may include: a vertical portion on both sides of the concave shape and a horizontal portion disposed between the two vertical portions, in the vertical direction. When the damper unit 201 is connected to the mounting structure 5, the upper end of the vertical damper unit 201 may be disposed between the two vertical portions, and may be connected by a connecting member, and further, a positioning hole is provided on the horizontal portion. The horizontal part can be accessed by positioning parts The positioning hole is connected to the mounting structure 5, and the upper end of the vertical damper unit 201 is stably and effectively connected to the mounting structure 5 through the second connecting member 202. Similarly, the lower end of the vertical damper unit 201 can also be connected to the body 6 through the second connecting member 202.

In addition, the present embodiment is not limited to the specific number of the connecting post 3, those skilled in the art can arbitrarily set according to the function of the connecting post 3, wherein the connecting post 3 is used to support and connect the mounting structure 5; Since the connecting post 3 is disposed between the fuselage main body 6 and the mounting structure 5, in particular, the upper end of the connecting post 3 can be connected to the mounting structure 5 through the first connecting member 4. Wherein, the first connecting member 4 may have a cylindrical structure, and the lower end of the first connecting member 4 may be engaged with the upper end of the connecting post 3, and the upper end of the first connecting post 3 may be provided with an external thread, so that A threaded connection is made between the first connecting piece 4 and the mounting structure 5.

Further, when the connecting post 3 is disposed in plurality, for example, 2, 3, 4, or 5, etc., the plurality of connecting posts 3 may be symmetrically disposed on the mounting structure along the central axis of the mounting structure 5 5 is between the body 6 and the body. The vertical damper unit 201 is also disposed between the mounting structure 5 and the body 6 . At this time, the connecting post 3 can be spaced apart from the vertical damper unit 201 between the mounting structure 5 and the body 6 . In this way, not only the support effect of the connecting post 3 on the mounting structure 5 but also the damping effect of the vertical damper unit 201 on the mounting device can be achieved.

In the embodiment, by arranging the first damper structure 2 to include a plurality of vertical damper units 201 arranged in the vertical direction, the vertical damper unit 201 is disposed between the mounting structure 5 and the body 6 , thereby The shock absorbing effect of the first shock absorbing structure 2 on the mounting device in the vertical direction is effectively realized, the accuracy of the working of the mounting device is ensured, and the stable reliability of the shock absorbing mechanism is further improved.

3 is a schematic diagram of a split structure of a second shock absorbing structure 1 according to an embodiment of the present invention; FIG. 4 is a schematic exploded view of a second shock absorbing structure 1 according to an embodiment of the present invention; Based on the following, it can be seen that when the first shock absorbing structure 2 can achieve the shock absorbing effect on the mounting device in the vertical direction, however, in the aerial environment of the drone, the vibration originates from the space. In various directions, at this time, in order to satisfy the shock absorbing effect on the photographing apparatus, the shock absorbing mechanism may further include a second shock absorbing structure 1 for damping in the horizontal direction, the second shock absorbing structure 1 and the connecting column 3 is connected to the fuselage main body 6.

The second damper structure 1 can be connected to the mounting structure 5 through the connecting post 3 , that is, the second damping structure 1 is disposed between the mounting structure 5 and the fuselage body 6 to achieve horizontal orientation. Damping effect on the mounting device. In addition, in this embodiment, the specific shape and structure of the second damper structure 1 is not limited, and those skilled in the art may set according to specific design requirements. Preferably, the second damper structure 1 may include: multiple along The horizontal damper unit 101, which is disposed in the horizontal direction, is connected to the body main body 6 through the body connector 102. The horizontal damper unit 101 may include at least one of the following: a damper and a wire rope, and for the wire rope, the wire rope is arranged in a spring-like structure, and the shock absorbing effect can also be achieved.

It should be noted that the number of the horizontal damper units 101 included in the second damper structure 1 is not limited in this embodiment, and those skilled in the art may set according to specific design requirements, for example, the level may be reduced. The number of the earthquake cells 101 is set to 2, 4, 6, 8, or 10, etc.; wherein, when the number of the horizontal damper units 101 is four, the four horizontal damper units 101 may be The parallelogram structure is arranged as shown in FIG. 3; when a plurality of horizontal damper units 101 are connected between the mounting structure 5 and the fuselage main body 6, the mounting structure 5 is horizontally oriented for convenience. The plurality of horizontal damper units 101 can be evenly distributed between the mounting structure 5 and the body 6; further, the plurality of horizontal damper units 101 are symmetrically disposed along the central axis of the mounting structure 5, This facilitates accurate and effective control of the second shock absorbing structure 1.

Further, in this embodiment, the specific connection manner of the second shock absorbing structure 1 and the connecting post 3 is not limited, and those skilled in the art may set according to specific design requirements. Preferably, the second shock absorbing structure 1 may also be The sliding bearing 103 is disposed between the plurality of horizontal damper units 101. The upper end of the sliding bearing 103 is mounted with a damper connecting member 104. The horizontal damper unit 101 is connected to the connecting post 3 through the sliding bearing 103 and the damper connecting member 104. In addition, the sliding bearing 103 can realize not only stable and effective connection between the plurality of horizontal damper units 101 but also a stable and effective connection between the horizontal damper unit 101 and the connecting post 3, and further, due to the connecting post 3 The sliding bearing 103 and the damper connecting member 104 are connected to the horizontal damper unit 101, so that the action between the connecting post 3 and the horizontal damper unit 101 is isolated and independent from each other, further ensuring that the second damper structure 1 is hanged. The horizontal damping effect of the loaded equipment.

When the first shock absorbing structure 2 can realize the shock absorbing effect on the mounting device in the vertical direction, the shock absorbing effect on the mounting device in the horizontal direction can be effectively realized by the second shock absorbing structure 1 provided. In addition, in the aerial photography environment of the drone, no matter which direction the vibration originates from, the vibration damping effect on the shooting device can be satisfied, and the mounting device can effectively ensure stable and reliable work, and the monitoring is improved. Shooting quality and efficiency.

Based on any of the above embodiments, with reference to FIGS. 1-4, in order to further improve the shock absorbing effect of the damper mechanism on the mounting device, the damper mechanism may further include a plurality of damper springs 7 The shock spring 7 is disposed between the body main body 6 and the second shock absorbing structure 1. The damping spring 7 can be sleeved on the connecting post 3.

Specifically, the body main body 6 may include an upper body main body 601 at an upper end, a middle body main body 6 detachably coupled to the upper body main body 601, and a lower body main body 604 detachably coupled to the middle body main body 6. Wherein, the middle fuselage body 6 includes a front fuselage main body 602 and a rear fuselage main body 603 that are detachably connected, wherein the lower fuselage main body 604 is also provided with an appropriate fit in order to prevent the lower fuselage main body 604 from being damaged. The lower cover 605 of the fuselage, and the lower cover 605 of the fuselage can be connected to the mounting structure 5 through the third connecting member 9. The mounting structure 5 is a mounting structure 5 disposed under the main body 6. The mounting device is disposed below the body 6 .

Further, the damper spring 7 may include: a first spring portion disposed between the middle body main body 6 and the lower body main body 604, and a second spring disposed between the upper body main body 601 and the middle body main body 6 The first spring portion may be disposed between the front fuselage main body 602 and the rear fuselage main body 603. In addition, when the connecting post 3 passes through the fuselage main body 6, the damper spring 7 can be sleeved on the connecting post 3, and the fixing pipe 8 of the lower end of the connecting post 3 can be in contact with the damper spring 7, at this time, Both ends of the damper spring 7 are in contact with the lower body main body 604 and the fixed pipe 8, respectively, so that the shock absorbing effect on the mounting device in the vertical direction can be effectively achieved.

In this embodiment, the shock absorbing spring 7 is provided, so that the damper spring 7 can cooperate with the first damper structure 2 to achieve the shock absorbing effect on the mounting device in the vertical direction, and the second damper structure 1 can be realized in The damping effect of the mounting device in the horizontal direction, so that the damping mechanism can provide damping and rigidity in the horizontal direction and the vertical direction, further ensuring the stable reliability of the working of the mounting device, and improving the damping The practicality of the institution.

FIG. 5 is a schematic structural diagram of a drone 10 according to an embodiment of the present invention; FIG. 6 is a schematic structural diagram of an arm of an unmanned aerial vehicle 10 in an unfolded state according to an embodiment of the present invention; A schematic structural view of the arm of the UAV 10 in a folded state is provided in an embodiment. Referring to Figures 5-7, the present embodiment provides a drone 10 that can include:

Body body 6;

In the damper mechanism of any of the above embodiments, the damper mechanism is coupled to the body main body 6.

Among them, the specific shape structure and function of the shock absorbing mechanism can refer to the above statement, This will not be repeated here.

The drone 10 provided in this embodiment is provided with the above-mentioned damper mechanism on the drone 10, and the damper mechanism can be disposed on the connecting post 3 of the fuselage main body 6 and disposed on the connecting post 3 The first shock absorbing structure 2 of the end can effectively realize the shock absorption effect on the mounting device, and has the advantages of simple structure, convenient installation/disassembly, and can effectively reduce the vibration environment of the drone 10 to the precision instruments such as the pan/tilt camera and the camera. The effect produced ensures the shooting accuracy and shooting effect of the shooting mechanism, and can meet the application requirements of the user, thereby improving the practicality of the drone 10 and facilitating the promotion and application of the market.

On the basis of the above embodiments, referring to FIG. 5-7, the UAV 10 in this embodiment may further include a photographing mechanism, which may be a camera, a mobile phone, a camera, a video recorder, and the like having a photographing function. The photographing mechanism can be connected above or below the body main body 6 by the damper mechanism. Specifically, when the photographing mechanism is connected above the fuselage main body 6 through the shock absorbing mechanism, the photographing mechanism is connected to the mounting structure 5 located at the upper end of the fuselage main body 6; when the photographing mechanism is connected to the fuselage main body through the shock absorbing mechanism When the lower portion is 6 , the photographing mechanism is connected to the mounting structure 5 located at the lower end of the main body 6 . At this time, the photographing mechanism can be disposed at different positions of the drone 10, which can meet the shooting requirements of the user, and further improves the convenience and reliability of the use of the drone 10 .

Based on the above embodiments, with continued reference to FIGS. 5-7, in order to further improve the convenience and reliability of the use of the drone 10, the drone 10 may further include: a foldable machine coupled to the body 6 The arm 1001 and the straight arm 1002 connected to the foldable arm 1001, the straight arm 1002 is connected with the propeller 1004 through the power combination 1003; one end of the foldable arm 1001 is movably connected with the fuselage main body 6, and the other end is connected with the straight arm 1002 active connection.

Wherein, when the drone 10 is in the working state, the foldable arm 1001 is in the unfolded state, as shown in FIG. 5-6. At this time, the drone 10 can be provided with a photographing mechanism, and the drone 10 and the photographing are performed. The mechanism performs an aerial photography operation; when the drone 10 is in the standby state, in order to reduce the occupied space of the drone 10, the foldable mechanism can be in a contracted state, and the fuselage main body 6 of the drone 10 can be folded, such as As shown in FIG. 7, at this time, the occupied space of the drone 10 can be effectively reduced, thereby facilitating the placement and movement of the drone 10.

By arranging the drone 10 to include the foldable arm 1001 and the straight arm 1002, the drone 10 can be made to have different structural states when in the working state and the standby state, facilitating the use of the drone 10, and When the drone 10 is in the standby state, to effectively reduce the drone 10 The space is occupied, which further facilitates the user to place and move the drone 10, thereby effectively improving the utility of the drone 10, and is beneficial to the promotion and application of the market.

Finally, it should be noted that the above embodiments are merely illustrative of the technical solutions of the present invention, and are not intended to be limiting; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art will understand that The technical solutions described in the foregoing embodiments may be modified, or some or all of the technical features may be equivalently replaced; and the modifications or substitutions do not deviate from the technical solutions of the embodiments of the present invention. range.

Claims

a shock absorbing mechanism, characterized in that it is mounted on a drone, the drone includes a fuselage body, the shock absorbing mechanism includes a connecting post that is disposed through the fuselage body, and is disposed in the a first damper structure connecting the upper and lower ends of the column, the connecting column is detachably connected to the body of the fuselage, and the first damper structure is connected with a mounting structure for carrying the mounting device to implement the hanging Shock absorption of the load carrying equipment.
The damper mechanism according to claim 1, wherein the first damper structure comprises a plurality of vertical damper units arranged in a vertical direction, and the vertical damper unit is disposed on the mounting structure and Between the fuselage bodies.
The damper mechanism according to claim 2, wherein the vertical damper unit comprises at least one of the following: a damper, a wire rope.
The damper mechanism according to claim 2, wherein a plurality of said vertical damper units are symmetrically disposed along a central axis of said mounting structure.
The damper mechanism according to claim 2, wherein both ends of the vertical damper unit are respectively connected to the mounting structure and the body body through a second connecting member.
A damper mechanism according to claim 1, wherein said damper mechanism further comprises a second damper structure for damping in a horizontal direction, said second damper structure and said connecting post and The main body of the fuselage is connected.
The damper mechanism according to claim 6, wherein said second damper structure is coupled to said mounting structure via said connecting post.
The damper mechanism according to claim 6, wherein the second damper structure comprises: a plurality of horizontal damper units arranged in a horizontal direction, the horizontal damper unit being connected to the machine through a body connecting member On the body.
The damper mechanism according to claim 8, wherein the horizontal damper unit comprises at least one of the following: a damper, a wire rope.
The damper mechanism according to claim 8, wherein a plurality of said horizontal damper units are symmetrically disposed along a central axis of said mounting structure.
The damper mechanism according to claim 8, wherein the second damper structure further comprises: a sliding bearing disposed between the plurality of horizontal damper units, the damper connecting member is mounted on the upper end of the sliding bearing, The horizontal damper unit passes through the sliding bearing and the damper connecting member The posts are connected.
The damper mechanism according to claim 2, wherein the connecting post is symmetrically disposed between the mounting structure and the body body along a central axis of the mounting structure.
The damper mechanism according to claim 12, wherein said connecting post is spaced apart from said vertical damper unit between said mounting structure and said body.
The damper mechanism according to any one of claims 1 to 13, characterized in that the damper mechanism further comprises a plurality of damper springs, the damper springs being disposed on the body body and the second reduction Between the earthquake structures.
The damper mechanism according to claim 14, wherein the damper spring is sleeved on the connecting post.
The damper mechanism according to any one of claims 1 to 13, characterized in that the lower end of the connecting post is connected to the body of the body by a fixed pipe.
The damper mechanism according to any one of claims 1 to 13, characterized in that the upper end of the connecting post is connected to the mounting structure by a first connecting member.
A drone, characterized in that it comprises:

Body body

The damper mechanism according to any one of claims 1 to 17, wherein the damper mechanism is coupled to the body body.
The drone according to claim 18, further comprising a photographing mechanism connected to the body main body by the damper mechanism.
The drone according to claim 18, further comprising a photographing mechanism connected to the lower side of the body main body by the damper mechanism.
The drone according to claim 18, wherein said drone further comprises: a foldable arm attached to the body of the body; and a straight arm connected to the foldable arm, The straight arm is connected to the propeller by a power combination; one end of the foldable arm is movably connected to the fuselage body, and the other end is movably connected to the straight arm.