CN108513602B - Damper and unmanned aerial vehicle - Google Patents
Damper and unmanned aerial vehicle Download PDFInfo
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- CN108513602B CN108513602B CN201780005166.4A CN201780005166A CN108513602B CN 108513602 B CN108513602 B CN 108513602B CN 201780005166 A CN201780005166 A CN 201780005166A CN 108513602 B CN108513602 B CN 108513602B
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- 238000013016 damping Methods 0.000 claims abstract description 103
- 230000007246 mechanism Effects 0.000 claims abstract description 65
- 230000035939 shock Effects 0.000 claims abstract description 55
- 229910000831 Steel Inorganic materials 0.000 claims description 5
- 239000010959 steel Substances 0.000 claims description 5
- 230000000149 penetrating effect Effects 0.000 claims description 3
- 230000000694 effects Effects 0.000 abstract description 26
- 238000009434 installation Methods 0.000 abstract description 3
- 238000010521 absorption reaction Methods 0.000 description 16
- 238000010586 diagram Methods 0.000 description 6
- 230000002349 favourable effect Effects 0.000 description 4
- 230000008093 supporting effect Effects 0.000 description 2
- 239000006096 absorbing agent Substances 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U20/00—Constructional aspects of UAVs
- B64U20/80—Arrangement of on-board electronics, e.g. avionics systems or wiring
- B64U20/87—Mounting of imaging devices, e.g. mounting of gimbals
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F7/00—Vibration-dampers; Shock-absorbers
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
- B64U2101/30—UAVs specially adapted for particular uses or applications for imaging, photography or videography
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- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Microelectronics & Electronic Packaging (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Buildings Adapted To Withstand Abnormal External Influences (AREA)
- Accessories Of Cameras (AREA)
- Vibration Prevention Devices (AREA)
Abstract
A damping mechanism and an unmanned aerial vehicle (10) using the same are provided. This damper is used for installing on unmanned aerial vehicle, and unmanned aerial vehicle includes fuselage main part (6), and damper is including wearing to locate spliced pole (3) of fuselage main part (6) and setting up first shock-absorbing structure (2) at both ends about the spliced pole, and spliced pole (3) can be dismantled with fuselage main part (6) and be connected, and first shock-absorbing structure (2) are connected with carry structure (5) that are used for bearing the weight of carry equipment to the realization is to the shock attenuation of carry equipment. This damper can realize the shock attenuation effect to the carry equipment effectively through setting up the first shock-absorbing structure at both ends about the spliced pole to simple structure, the installation/dismantlement is convenient, when installing this damper on unmanned aerial vehicle, can reduce unmanned aerial vehicle's the vibrations environment to the produced influence of precision instruments such as cloud platform camera, camera effectively, has guaranteed the shooting precision and the shooting effect of shooting mechanism, has improved this damper's practicality.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to a damping mechanism and an unmanned aerial vehicle.
Background
Along with scientific and technological rapid development, be applied to the equipment in the shooting field and more diversified, under the general condition, when carrying out big preparation aerial photography, often need unmanned aerial vehicle to assist and shoot, and shoot the device and set up on unmanned aerial vehicle's cloud platform, at this moment, unmanned aerial vehicle can guarantee effectively that the precision and the quality of shooting the picture as the auxiliary assembly who shoots. However, during operation, the vibration environment of the unmanned aerial vehicle can greatly affect the precise instruments such as the pan-tilt camera and the video camera, which easily results in that the requirements of practical application cannot be met.
In order to meet the requirements of practical application, a damping mechanism can be installed on the unmanned aerial vehicle, and in the prior art, the device for damping the cloud deck of the aircraft mainly combines damping rubber balls and damping oil; however, the shock absorber using the rubber balls is poor in rigidity of rubber, is greatly influenced by ambient temperature, needs a plurality of rubber balls to be used in a combined mode to achieve an effect, is large in size and suitable for instruments with small weight, and is not suitable for being applied to the unmanned aerial vehicle.
Disclosure of Invention
The invention provides a damping mechanism and an unmanned aerial vehicle, which are used for solving the problem that the vibration environment of the unmanned aerial vehicle in the prior art can generate great influence on precise instruments such as a pan-tilt camera, a video camera and the like, so that the actual application requirements can not be met easily.
The invention provides a damping mechanism for being installed on an unmanned aerial vehicle, the unmanned aerial vehicle comprises a main body, the damping mechanism comprises a connecting column penetrating through the main body and first damping structures arranged at the upper end and the lower end of the connecting column, the connecting column is detachably connected with the main body, and the first damping structures are connected with a mounting structure for bearing mounting equipment so as to realize damping of the mounting equipment.
A second aspect of the present invention is to provide an unmanned aerial vehicle, including:
a main body of the body;
the damping mechanism is connected with the machine body.
According to the damping mechanism and the unmanned aerial vehicle provided by the invention, the damping effect on the mounting equipment can be effectively realized through the connecting column arranged through the main body of the unmanned aerial vehicle and the first damping structures arranged at the upper end and the lower end of the connecting column, the damping mechanism is simple in structure and convenient to mount/dismount, when the damping mechanism is mounted on the unmanned aerial vehicle, the influence of the vibration environment of the unmanned aerial vehicle on precision instruments such as a pan-tilt camera, a video camera and the like can be effectively reduced, the shooting precision and the shooting effect of the shooting mechanism are ensured, meanwhile, the application requirements of users can be met, the practicability of the damping mechanism is further improved, and the damping mechanism is favorable for popularization and application in the market.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without inventive labor.
FIG. 1 is an exploded view of a shock absorbing mechanism according to an embodiment of the present invention;
FIG. 2 is a schematic view of an assembly structure of a damping mechanism according to an embodiment of the present invention;
fig. 3 is a schematic view of a split structure of a second damping structure according to an embodiment of the present invention;
FIG. 4 is an 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. 6 is a schematic structural diagram of an unmanned aerial vehicle according to an embodiment of the present invention, where a horn is in a deployed state;
fig. 7 is a schematic structural diagram of an unmanned aerial vehicle according to an embodiment of the present invention, where a horn is in a folded state.
In the figure:
1. a second shock-absorbing structure; 101. A horizontal damping unit;
102. a fuselage connection; 103. A sliding bearing;
104. a damping connection; 2. A first shock-absorbing structure;
201. a vertical damping unit; 202. A second connecting member;
3. connecting columns; 4. A first connecting member;
5. a mounting structure; 6. A main body of the body;
601. an upper body main body; 602. A front body main body;
603. a rear body main body; 604. A lower body main body;
605. a lower cover plate of the machine body; 7. A damping spring;
8. a fixed tube; 9. A third connecting member;
10. an unmanned aerial vehicle; 1001. A foldable horn;
1002. a straightening arm; 1003. Combining power;
1004. a propeller.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Unless defined otherwise, 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. The terminology used in the description of the invention herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used herein, the term "and/or" includes any and all combinations of one or more of the associated listed items.
In the present invention, the terms "mounted," "connected," "fixed," and the like are used in a broad sense, and for example, "connected" may be a fixed connection, a detachable connection, or an integral connection. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience of description and for simplicity of description, and do not indicate or imply that the device or element so referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and thus should not be considered as limiting the present invention.
Some embodiments of the invention are described in detail below with reference to the accompanying drawings. The features in the embodiments and examples described below may be combined with each other without conflict.
FIG. 1 is an exploded view of a shock absorbing mechanism according to an embodiment of the present invention; FIG. 2 is a schematic view of an assembly structure of a damping mechanism according to an embodiment of the present invention; referring to fig. 1-2, this embodiment provides a damper, this damper is used for installing on unmanned aerial vehicle, and unmanned aerial vehicle includes fuselage main part 6, and damper includes spliced pole 3 of wearing to locate fuselage main part 6 and sets up the first shock-absorbing structure 2 at spliced pole 3 upper and lower both ends, and spliced pole 3 can be dismantled with fuselage main part 6 and be connected, and first shock-absorbing structure 2 is connected with the carry structure 5 that is used for bearing carry equipment to the realization is to the shock attenuation of carry equipment.
The first damping structure 2 can be arranged at the upper end and the lower end of the connecting column 3, at the moment, the first damping structure 2 can comprise one damping unit or a plurality of damping units, and when the first damping structure 2 comprises one damping unit, one damping unit can be independently and symmetrically arranged at the upper end and the lower end of the connecting column 3; when first shock-absorbing structure 2 includes a plurality of shock attenuation units, a plurality of shock attenuation units can be symmetrical respectively in the upper and lower both ends of spliced pole 3. In addition, the first shock absorption structure 2 in this embodiment may be used to achieve shock absorption of the mounted device in the vertical direction, or may also be used to achieve shock absorption of the mounted device in the horizontal direction and the vertical direction. Wherein, the mounting device can be a shooting mechanism, for example: cameras, video recorders, and other devices having a shooting function, and the like.
In addition, this embodiment does not restrict the concrete implementation that spliced pole 3 and fuselage main part 6 can be dismantled and be connected, and the technical personnel in the field can set up according to specific design demand, and is comparatively preferred, and this spliced pole 3's lower extreme can be connected on fuselage main part 6 through fixed pipe 8. Specifically, the fixing pipe 8 can be provided with internal threads or external threads, so that the lower end of the connecting column 3 is in threaded connection with the machine body 6; or, the fixing pipe 8 can be further provided with a fixing hole, the same fixing hole is arranged at the position corresponding to the connecting column 3, the detachable connection of the connecting column 3 and the machine body main body 6 is realized through a connecting piece penetrating through the fixing hole, wherein the connecting piece can comprise at least one of the following components: screws, bolts, studs, etc.
The damper that this embodiment provided, through the spliced pole 3 of wearing to locate fuselage main part 6 and the first shock-absorbing structure 2 of setting both ends about spliced pole 3 that sets up, can realize the shock attenuation effect to the carry equipment effectively, and simple structure, the installation/dismantlement is convenient, when installing this damper on unmanned aerial vehicle, can reduce unmanned aerial vehicle's vibrations environment to cloud platform camera effectively, the produced influence of precision instruments such as camera, the shooting precision and the shooting effect of shooting mechanism have been guaranteed, can satisfy user's application demand simultaneously, and then improved this damper's practicality, be favorable to the popularization and the application in market.
On the basis of the above-mentioned embodiment, it can be known with reference to fig. 1-2 continuously, this embodiment does not limit to the specific shape structure of first shock-absorbing structure 2, and technical personnel in the art can set up according to specific application requirements, and in the unmanned aerial vehicle flight process, in the vertical direction, unmanned aerial vehicle's flight state can produce great influence to shooting mechanism, and consequently, this first shock-absorbing structure 2 can include a plurality of vertical shock-absorbing units 201 that set up along the vertical direction, and vertical shock-absorbing unit 201 sets up between mounting structure 5 and fuselage main part 6.
The vertical damping unit 201 in this embodiment may include at least one of: dampers, wire ropes; wherein, for wire rope, set up wire rope into spring-like structure, can realize absorbing effect equally. In addition, the number of the vertical shock absorption units 201 included in the first shock absorption structure 2 is not limited in this embodiment, and those skilled in the art may set the number according to specific design requirements, for example, the number of the vertical shock absorption units 201 may be set to 2, 3, 4, or 5, etc.; when the plurality of vertical shock absorption units 201 are connected between the mounting structure 5 and the main body 6 of the fuselage, in order to facilitate achieving and controlling the shock absorption effect on the mounting structure 5 in the vertical direction, the plurality of vertical shock absorption units 201 may be uniformly distributed between the mounting structure 5 and the main body 6 of the fuselage; further, when the number of the vertical damping units 201 is even, the plurality of vertical damping units 201 may be symmetrically disposed along the central axis of the mounting structure 5, which facilitates accurate and effective control of the first damping structure 2.
In addition, in the present embodiment, the connection manner between the vertical shock absorption unit 201 and the mounting structure 5 and the main body of the fuselage 6 is not limited, and those skilled in the art can set the connection manner according to specific design requirements, for example, the vertical shock absorption unit 201 can be fixedly connected or detachably connected with the mounting structure 5 and the main body of the fuselage 6; specifically, the two ends of the vertical damping unit 201 may be connected to the mounting structure 5 and the main body 6 through the second connection member 202. The second connecting member 202 may have a zigzag structure, and specifically, the second connecting member 202 may include: the vertical portion that is located the character cut in bas-relief both sides with set up the horizontal part between two vertical portions, when perpendicular shock attenuation unit 201 is connected with carry structure 5, the upper end of perpendicular shock attenuation unit 201 can set up between two vertical portions to can be connected through the connecting piece, it is further, be provided with the locating hole on the horizontal part, the horizontal part can be realized being connected with carry structure 5 through the configuration of setting element and locating hole, and then realized the upper end of perpendicular shock attenuation unit 201 through this second connecting piece 202 with carry structure 5's stability, effective connection. Similarly, the lower end of the vertical damping unit 201 may be connected to the body main body 6 by a second connection member 202.
In addition, the specific number of the connecting columns 3 is not limited in this embodiment, and those skilled in the art can arbitrarily set the connecting columns 3 according to the functional effects of the connecting columns 3, wherein the connecting columns 3 are used for supporting and connecting the mounting structures 5; because the connecting column 3 is arranged between the machine body main body 6 and the mounting structure 5, specifically, the upper end of the connecting column 3 can be connected with the mounting structure 5 through the first connecting piece 4. Wherein, first connecting piece 4 can be cylindric structure to, can with the upper end joint of spliced pole 3 at the lower extreme of first connecting piece 4, and can be provided with the external screw thread in the upper end of first spliced pole 3, make and realize threaded connection between first connecting piece 4 and the carry structure 5.
Further, when the connecting column 3 is provided in plural, for example, 2, 3, 4 or 5, etc., the plural connecting columns 3 may be symmetrically provided between the mounting structure 5 and the main body 6 along the central axis of the mounting structure 5. And the vertical damping unit 201 is also arranged between the mounting structure 5 and the body 6, and at this time, the connecting column 3 and the vertical damping unit 201 can be arranged between the mounting structure 5 and the body 6 at an interval. Therefore, the supporting effect of the connecting column 3 on the mounting structure 5 can be effectively guaranteed, and the damping effect of the vertical damping unit 201 on the mounting equipment can also be achieved.
In this embodiment, through setting up first shock-absorbing structure 2 to including a plurality of perpendicular shock attenuation units 201 that set up along vertical direction, perpendicular shock attenuation units 201 set up between mounting structure 5 and fuselage main part 6 to realized effectively that the accurate degree of mounting equipment work has been guaranteed to the shock attenuation effect of mounting equipment in vertical direction through first shock-absorbing structure 2 that sets up, further improved the reliable and stable nature that this shock-absorbing mechanism used.
Fig. 3 is a schematic view of a split structure of the second damping structure 1 according to an embodiment of the present invention; fig. 4 is an exploded view of a second shock absorbing structure 1 according to an embodiment of the present invention; on the basis of any one of the above embodiments, as can be seen with continued reference to fig. 1 to 4, when the first shock-absorbing structure 2 can achieve the shock-absorbing effect on the mounted device in the vertical direction, however, in the environment of aerial photography of the unmanned aerial vehicle, the shock is originated from all directions in the space, at this time, in order to satisfy the shock-absorbing effect on the shooting device, the shock-absorbing mechanism may further include a second shock-absorbing structure 1 for absorbing shock in the horizontal direction, and the second shock-absorbing structure 1 is connected with the connecting column 3 and the main body 6 of the main body of.
Wherein, second shock-absorbing structure 1 can be connected with mounting structure 5 through spliced pole 3, also promptly, second shock-absorbing structure 1 sets up between mounting structure 5 and fuselage main part 6 to realize the shock attenuation effect to mounting equipment in the horizontal direction. In addition, the specific shape and structure of the second shock absorbing structure 1 are not limited in this embodiment, and those skilled in the art can set the second shock absorbing structure according to specific design requirements, and preferably, the second shock absorbing structure 1 may include: a plurality of horizontal damping units 101 are arranged in a horizontal direction, and the horizontal damping units 101 are connected to the body 6 by body connectors 102. Wherein, the horizontal damping unit 101 may include at least one of: the damper is used for damping the vibration of the steel wire rope, and the steel wire rope is of a spring-shaped structure, so that the vibration of the steel wire rope can be reduced.
It should be noted that, in the present embodiment, the number of the horizontal shock absorbing units 101 included in the second shock absorbing structure 1 is not limited, and a person skilled in the art may set the number according to specific design requirements, for example, the number of the horizontal shock absorbing units 101 may be set to be 2, 4, 6, 8, or 10, etc.; when the number of the horizontal damping units 101 is 4, the 4 horizontal damping units 101 may be arranged in a parallelogram structure, which can be specifically referred to as shown in fig. 3; when the plurality of horizontal shock absorption units 101 are connected between the mounting structure 5 and the main body 6 of the machine body, in order to facilitate the shock absorption effect on the mounting structure 5 in the horizontal direction, the plurality of horizontal shock absorption units 101 may be uniformly distributed between the mounting structure 5 and the main body 6 of the machine body; further, a plurality of horizontal damping units 101 are symmetrically arranged along the central axis of the mounting structure 5, which facilitates accurate and effective control of the second damping structure 1.
Further, this embodiment does not limit the specific connection mode of the second shock-absorbing structure 1 and the connecting column 3, and those skilled in the art can set according to specific design requirements, and preferably, the second shock-absorbing structure 1 further includes: the slide bearings 103 are arranged among the horizontal shock absorption units 101, the damping connecting pieces 104 are installed at the upper ends of the slide bearings 103, and the horizontal shock absorption units 101 are connected with the connecting column 3 through the slide bearings 103 and the damping connecting pieces 104. Wherein, this slide bearing 103 not only can realize the stability between a plurality of horizontal shock attenuation unit 101, effective connection, and can also realize the stable effective connection between horizontal shock attenuation unit 101 and the spliced pole 3, in addition, because spliced pole 3 is connected with horizontal shock attenuation unit 101 through slide bearing 103 and damping connecting piece 104, consequently, make the action mutual isolation and the independence between spliced pole 3 and the horizontal shock attenuation unit 101, further guaranteed the horizontal shock attenuation effect of second shock-absorbing structure 1 to the equipment of hanging.
When first shock-absorbing structure 2 can realize the shock attenuation effect to the carry equipment in the vertical direction, through the second shock-absorbing structure 1 that sets up, can realize effectively that the shock attenuation effect to the carry equipment in the horizontal direction, and then make in unmanned aerial vehicle environment of taking photo by plane, no matter vibrations derive from which direction in the space, the shock attenuation effect to the equipment of shooing all can be satisfied, and still guaranteed effectively that the carry equipment can carry out stable, reliable work, improved shooting quality and efficiency.
On the basis of any one of the above embodiments, as can be seen with continued reference to fig. 1 to 4, in order to further improve the damping effect of the damping mechanism on the mounted device, the damping mechanism may further include a plurality of damping springs 7, and the damping springs 7 are disposed between the body main body 6 and the second damping structure 1. Wherein, the damping spring 7 can be sleeved on the connecting column 3.
Specifically, the body main body 6 may include an upper body main body 601 located at an upper end, a middle body main body 6 detachably connected to the upper body main body 601, and a lower body main body 604 detachably connected to the middle body main body 6, wherein the middle body main body 6 includes a front body main body 602 and a rear body main body 603 detachably connected to each other, wherein, in order to prevent the lower body main body 604 from being damaged, the lower body main body 604 is further provided with a lower body cover plate 605 adapted to the lower body main body, and the lower body cover plate 605 may be connected to the mounting structure 5 through a third connecting member 9, the mounting structure 5 is a mounting structure 5 disposed below the body main body 6, and the mounting device may be disposed below the body main 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 portion disposed between the upper body main body 601 and the middle body main body 6, wherein the first spring portion may be disposed between the front body main body 602 and the rear body main body 603. In addition, when the connecting column 3 passes through the body main body 6, the damping spring 7 can be sleeved on the connecting column 3, the fixing tube 8 at the lower end of the connecting column 3 can be in contact with the damping spring 7, and at the moment, two ends of the damping spring 7 are respectively in contact with the lower body main body 604 and the fixing tube 8, so that the damping effect on the hanging and carrying equipment in the vertical direction can be effectively realized.
In this embodiment, through the damping spring 7 who sets up for damping spring 7 can cooperate first shock-absorbing structure 2 to realize the shock attenuation effect to the carry equipment in the vertical direction, combines second shock-absorbing structure 1 can realize the shock attenuation effect to the carry equipment in the horizontal direction, thereby makes this damper can provide damping and rigidity on horizontal direction and vertical direction, has further guaranteed the reliable and stable nature of carry equipment work, has improved this damper's practicality.
Fig. 5 is a schematic structural diagram of an unmanned aerial vehicle 10 according to an embodiment of the present invention; fig. 6 is a schematic structural diagram of an unmanned aerial vehicle 10 according to an embodiment of the present invention, in which the arm is in a deployed state; fig. 7 is a schematic structural diagram of the unmanned aerial vehicle 10 according to an embodiment of the present invention, in which the arms are in a folded state. As can be appreciated with reference to fig. 5-7, the present embodiment provides a drone 10, the drone 10 may include:
a body main body 6;
in the damper mechanism according to any of the above embodiments, the damper mechanism is connected to the main body 6.
The specific shape, structure and function of the damping mechanism can refer to the above statements, and are not repeated herein.
The unmanned aerial vehicle 10 that this embodiment provided, through install above-mentioned damper on unmanned aerial vehicle 10, this damper can be through the spliced pole 3 of wearing to locate fuselage main part 6 and the first shock-absorbing structure 2 of setting both ends about spliced pole 3 that sets up, can realize the shock attenuation effect to the carry equipment effectively, and moreover, the steam generator is simple in structure, the installation/dismantlement is convenient, can reduce unmanned aerial vehicle 10's vibrations environment to cloud platform camera effectively, the produced influence of precision instruments such as camera, the shooting precision and the shooting effect of shooting mechanism have been guaranteed, can satisfy user's application demand simultaneously, and then the practicality of this unmanned aerial vehicle 10 has been improved, be favorable to the popularization and the application in market.
On the basis of the above embodiments, as can be seen with continued reference to fig. 5 to 7, the unmanned aerial vehicle 10 in this embodiment may further include a shooting mechanism, where the shooting mechanism may be a video camera, a mobile phone, a camera, a video recorder, or other devices with shooting functions, and the shooting mechanism may be connected above or below the main body 6 of the fuselage through the damping mechanism. Specifically, when the shooting mechanism is connected above the machine body 6 through the damping mechanism, the shooting mechanism is connected with the mounting structure 5 positioned at the upper end of the machine body 6; when the photographing mechanism is connected below the main body 6 through the damper mechanism, the photographing mechanism is connected to the mounting structure 5 located at the lower end of the main body 6. At this moment, shoot the mechanism and can set up in unmanned aerial vehicle 10's different positions department, can satisfy user's shooting demand, further improved the convenient and reliable degree that this unmanned aerial vehicle 10 used.
On the basis of the above embodiment, as can be seen with continued reference to fig. 5 to 7, in order to further improve the convenience and reliability of the use of the unmanned aerial vehicle 10, the unmanned aerial vehicle 10 may further include: a foldable horn 1001 connected to the body 6 and a straight horn 1002 connected to the foldable horn 1001, the straight horn 1002 being connected to a propeller 1004 through a power pack 1003; one end of the foldable horn 1001 is movably connected with the main body 6 of the machine body, and the other end is movably connected with the straight horn 1002.
When the unmanned aerial vehicle 10 is in a working state, the foldable arm 1001 is in an unfolded state, as shown in fig. 5-6, at this time, the unmanned aerial vehicle 10 may be provided with a shooting mechanism, and aerial photography is performed through the unmanned aerial vehicle 10 and the shooting mechanism; and when unmanned aerial vehicle 10 is in standby state, in order to reduce unmanned aerial vehicle 10's occupation space, but folding mechanism can be in the shrink state, and then can fold unmanned aerial vehicle 10's fuselage main part 6, as shown in fig. 7, this moment, can reduce unmanned aerial vehicle 10's occupation space effectively, and then conveniently place and remove unmanned aerial vehicle 10.
Through setting up unmanned aerial vehicle 10 to including collapsible horn 1001 and straight horn 1002, can make unmanned aerial vehicle 10 have different structural state when being in operating condition and standby state, make things convenient for unmanned aerial vehicle 10's use, and, when unmanned aerial vehicle 10 is in standby state, with reduce unmanned aerial vehicle 10's occupation space effectively, further made things convenient for the user to place and remove unmanned aerial vehicle 10, thereby improve this unmanned aerial vehicle 10's practicality effectively, be favorable to the popularization and the application in market.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.
Claims (18)
1. The damping mechanism is characterized by being used for being installed on an unmanned aerial vehicle, the unmanned aerial vehicle comprises a main body of the main body, the damping mechanism comprises a connecting column penetrating through the main body of the main body and first damping structures arranged at the upper end and the lower end of the connecting column, the connecting column is detachably connected with the main body of the main body, and the first damping structures are connected with a mounting structure used for bearing mounting equipment so as to realize damping of the mounting equipment;
the damping mechanism further comprises a second damping structure for damping in the horizontal direction, and the second damping structure is connected with the connecting column and the machine body main body; the second shock-absorbing structure includes: the horizontal damping units are arranged along the horizontal direction and connected to the machine body main body through a machine body connecting piece;
the second shock-absorbing structure further includes: the damping device comprises a plurality of horizontal damping units, a connecting column and a plurality of sliding bearings, wherein the sliding bearings are arranged among the plurality of horizontal damping units, and damping connecting pieces are arranged at the upper ends of the sliding bearings; the horizontal damping units are uniformly distributed between the mounting structure and the machine body main body.
2. The damping mechanism according to claim 1, characterized in that the first damping structure comprises a plurality of vertical damping units arranged in a vertical direction, the vertical damping units being arranged between the mounting structure and the fuselage body.
3. The damping mechanism of claim 2, wherein the vertical damping unit comprises at least one of: a damper and a steel wire rope.
4. The damper mechanism according to claim 2, wherein a plurality of the vertical damper units are arranged symmetrically along a central axis of the mounting structure.
5. The damping mechanism according to claim 2, wherein both ends of the vertical damping unit are connected to the mounting structure and the main body of the body respectively through second connecting members.
6. The damper mechanism of claim 1, wherein the second damper structure is connected to the mounting structure via the connecting post.
7. The damping mechanism according to claim 1, wherein the horizontal damping unit comprises at least one of: a damper and a steel wire rope.
8. The damping mechanism according to claim 1, wherein a plurality of the horizontal damping units are symmetrically disposed along a central axis of the mounting structure.
9. The damping mechanism according to claim 2, characterized in that the connecting column is symmetrically arranged between the mounting structure and the body along a central axis of the mounting structure.
10. The damping mechanism according to claim 9, wherein the connecting column and the vertical damping unit are disposed between the mounting structure and the main body at an interval.
11. The damper mechanism according to any one of claims 1 to 10, further comprising a plurality of damper springs disposed between the body and the second damper structure.
12. The damper mechanism of claim 11, wherein the damper spring is sleeved over the connecting post.
13. The damper mechanism according to any one of claims 1 to 10, wherein the lower end of the connecting column is connected to the body through a fixing pipe.
14. The damper mechanism according to any one of claims 1-10, wherein the upper end of the connecting column is connected to the mounting structure by a first connection member.
15. An unmanned aerial vehicle, comprising:
a main body of the body;
the damper mechanism of any one of claims 1-14, the damper mechanism being coupled to the fuselage body.
16. The unmanned aerial vehicle of claim 15, further comprising a camera mechanism connected above the fuselage body by the shock absorbing mechanism.
17. The unmanned aerial vehicle of claim 16, further comprising a camera mechanism connected below the fuselage body through the shock absorbing mechanism.
18. The drone of claim 16, further comprising: the aircraft comprises a foldable horn connected to an aircraft body and a straight horn connected with the foldable horn, wherein the straight horn is connected with a propeller through a power combination; one end of the foldable horn is movably connected with the machine body main body, and the other end of the foldable horn is movably connected with the straight horn.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| PCT/CN2017/095319 WO2019023899A1 (en) | 2017-07-31 | 2017-07-31 | Vibration reduction mechanism and unmanned aerial vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108513602A CN108513602A (en) | 2018-09-07 |
| CN108513602B true CN108513602B (en) | 2020-11-17 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201780005166.4A Active CN108513602B (en) | 2017-07-31 | 2017-07-31 | Damper and unmanned aerial vehicle |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN108513602B (en) |
| WO (1) | WO2019023899A1 (en) |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114152580A (en) * | 2021-11-18 | 2022-03-08 | 刘志权 | Hyperspectral remote sensing geological survey appearance |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20140145026A1 (en) * | 2012-11-28 | 2014-05-29 | Hans Skjersaa | Unmanned Aerial Device |
| CN203681878U (en) * | 2014-01-23 | 2014-07-02 | 徐鹏 | Damping device of multi-lens aerial photography stabilized platform |
| JP6061996B1 (en) * | 2015-07-07 | 2017-01-18 | 株式会社マルチコプターラボ | Multicopter |
| CN205559664U (en) * | 2016-04-15 | 2016-09-07 | 深圳市大疆创新科技有限公司 | Damper and use this damper's unmanned vehicles |
| CN205872501U (en) * | 2016-07-26 | 2017-01-11 | 四川建筑职业技术学院 | Adopt torsion bar spring absorbing cloud platform suspension |
| CN206358359U (en) * | 2017-01-03 | 2017-07-28 | 山东鹰翼航空科技有限公司 | A kind of foldable long endurance multi-rotor unmanned aerial vehicle |
| CN106892097B (en) * | 2017-03-08 | 2019-04-30 | 深圳榕亨实业集团有限公司 | A kind of vehicle-mounted unmanned aerial vehicle for road condition monitoring |
-
2017
- 2017-07-31 CN CN201780005166.4A patent/CN108513602B/en active Active
- 2017-07-31 WO PCT/CN2017/095319 patent/WO2019023899A1/en active Application Filing
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| Publication number | Publication date |
|---|---|
| CN108513602A (en) | 2018-09-07 |
| WO2019023899A1 (en) | 2019-02-07 |
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