CN113833803A - Shock attenuation platform and unmanned aerial vehicle - Google Patents
Shock attenuation platform and unmanned aerial vehicle Download PDFInfo
- Publication number
- CN113833803A CN113833803A CN202111102961.XA CN202111102961A CN113833803A CN 113833803 A CN113833803 A CN 113833803A CN 202111102961 A CN202111102961 A CN 202111102961A CN 113833803 A CN113833803 A CN 113833803A
- Authority
- CN
- China
- Prior art keywords
- valve body
- mounting platform
- platform
- connecting cylinder
- shock absorbing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 230000035939 shock Effects 0.000 title claims description 43
- 238000013016 damping Methods 0.000 claims abstract description 26
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 15
- 230000000903 blocking effect Effects 0.000 claims description 2
- 230000000694 effects Effects 0.000 abstract description 7
- 238000007789 sealing Methods 0.000 description 10
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 7
- 239000000741 silica gel Substances 0.000 description 7
- 229910002027 silica gel Inorganic materials 0.000 description 7
- 238000010521 absorption reaction Methods 0.000 description 5
- 210000005069 ears Anatomy 0.000 description 5
- 238000005086 pumping Methods 0.000 description 4
- 239000000243 solution Substances 0.000 description 4
- 230000032683 aging Effects 0.000 description 3
- 238000009434 installation Methods 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 230000007613 environmental effect Effects 0.000 description 2
- 238000001746 injection moulding Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000000116 mitigating effect Effects 0.000 description 2
- 239000011347 resin Substances 0.000 description 2
- 229920005989 resin Polymers 0.000 description 2
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 239000002775 capsule Substances 0.000 description 1
- 230000008094 contradictory effect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Images
Classifications
-
- 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
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
- F16F15/022—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using dampers and springs in combination
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
-
- 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
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
- F16F15/023—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using fluid means
- F16F15/0232—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using fluid means with at least one gas spring
-
- 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
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
- F16F15/04—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means
- F16F15/046—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means using combinations of springs of different kinds
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Acoustics & Sound (AREA)
- Mechanical Engineering (AREA)
- Vibration Prevention Devices (AREA)
Abstract
The invention discloses a damping platform and an unmanned aerial vehicle, wherein a damping component is arranged between a first mounting platform and a second mounting platform to play a damping role; the damping assembly comprises a first valve body and a second valve body, wherein a first mounting platform is connected with the first valve body, a second mounting platform is connected with the second valve body, and the second valve body is hollow; the first valve body is movably arranged in the second valve body, the first valve body and the second valve body are sealed to form a cavity, and the first mounting platform is connected with the second mounting platform through the first valve body and the second valve body. Carry out evacuation processing to the cavity, the resistance of the air in the cavity produces damping effect, and air resistance forms the opposite pressure of effort that a direction and second mounting platform transmitted to come to prevent first mounting platform swing, vibrations, improve first mounting platform's stability, and then play the cushioning effect to the flight control main part of installing at first mounting platform.
Description
Technical Field
The invention relates to the technical field of aircraft accessories, in particular to a damping platform and an unmanned aerial vehicle.
Background
Unmanned aerial vehicle is at the air flight in-process, and engine, paddle motion often appear or receive the air current impact influence, can constantly sway vibrations, and apply the flight controller in the unmanned aerial vehicle and electronic equipment such as sensor easily, to the stronger impact vibrations of electronic equipment's production, this normal work when just being difficult to guarantee electronic equipment at unmanned aerial vehicle flight. Therefore, need provide reliable shock attenuation protection or install electronic equipment on shock attenuation platform for the last electronic equipment of unmanned aerial vehicle, avoid electronic equipment to receive vibrations harm when unmanned aerial vehicle meets with the air current or takes off and land, guarantee unmanned aerial vehicle flight control and sensing equipment's normal work.
Traditional flight control shock attenuation platform all relies on the silica gel shock attenuation to link together two shock attenuation boards on the damper assembly, and the gasbag adopts materials such as soft silica gel, and the material is inconsistent.
But because unmanned aerial vehicle is used outdoors, receives the influence of environmental factor, soft silica gel gasbag takes place the condition such as deformation, ageing easily for shock mitigation system's performance worsens, even inefficacy.
Disclosure of Invention
The invention mainly aims to provide a damping platform and aims to solve the problems of short service life, easy aging and consistent material performance of a traditional silica gel capsule.
In order to achieve the above object, the present invention provides a damping platform, comprising:
a first mounting platform;
a second mounting platform; and
the damping assembly comprises a first valve body and a second valve body, the first mounting platform is connected with the first valve body, the second mounting platform is connected with the second valve body, and the second valve body is hollow;
the first valve body is movably arranged in the second valve body, a cavity is formed in the first valve body and the second valve body in a sealed mode, the cavity is vacuumized, and the first mounting platform is connected with the second mounting platform through the first valve body and the second valve body.
Optionally, the first valve body includes a first limiting portion and a first connecting cylinder, the first limiting portion is fixedly connected with the first connecting cylinder, the first limiting portion is connected with the first mounting platform, and the first connecting cylinder is movably mounted in the second valve body.
Optionally, the first valve body comprises a sealing sheet, the sealing sheet is arranged on the first limiting part or the first connecting cylinder, and the sealing sheet seals the cavity.
Optionally, the second valve body includes a second limiting portion and a second connecting cylinder, the second limiting portion is fixedly connected with the second connecting cylinder, and the second limiting portion is connected with the second mounting platform.
Optionally, the second valve body further comprises a fastener, the fastener being mounted to the second connector barrel and blocking the cavity.
Optionally, the second position-limiting part is provided with a position-limiting hole, and the diameter of the fastener is consistent with that of the position-limiting hole.
Optionally, the first mounting platform and the second mounting platform are provided with mounting holes, the first connecting cylinder is connected with the first mounting platform through the mounting holes, and the second connecting cylinder is connected with the second mounting platform through the mounting holes.
Optionally, the diameter of the first connecting cylinder is smaller than the diameter of the second connecting cylinder, and the first connecting cylinder is accommodated in the second connecting cylinder.
Optionally, the first connecting cylinder and the second connecting cylinder are both provided with a cylindrical structure.
Optionally, the damping assembly further comprises a flight control main body portion, the flight control main body portion is mounted to the damping assembly, the flight control main body portion includes a housing, and the housing is mounted to the first mounting platform.
The invention provides an unmanned aerial vehicle which comprises a damping platform.
According to the technical scheme, the shock absorption assembly is arranged between the first mounting platform and the second mounting platform to play a shock absorption role; the damping assembly comprises a first valve body and a second valve body, wherein a first mounting platform is connected with the first valve body, a second mounting platform is connected with the second valve body, and the second valve body is hollow; the first valve body is movably arranged in the second valve body, the first valve body and the second valve body are sealed to form a cavity, and the first mounting platform is connected with the second mounting platform through the first valve body and the second valve body. Carry out evacuation processing to the cavity, the resistance of the air in the cavity produces damping effect, and air resistance forms the opposite pressure of effort that a direction and second mounting platform transmitted to come to prevent first mounting platform swing, vibrations, improve first mounting platform's stability, and then play the cushioning effect to the flight control main part of installing at first mounting platform.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.
FIG. 1 is a schematic perspective view of a shock absorbing platform according to an embodiment of the present invention;
FIG. 2 is an exploded view of a shock platform according to an embodiment of the present invention;
FIG. 3 is a cross-sectional view of one embodiment of a shock platform according to the present invention;
the reference numbers illustrate:
| reference numerals | Name (R) | Reference numerals | Name (R) |
| 100 | Shock-absorbing platform | 312 | A |
| 10 | |
313 | First connecting |
| 101 | |
32 | |
| 20 | |
321 | |
| 21 | |
322 | Limiting |
| 210 | |
323 | Second connecting |
| 22 | Positioning |
324 | Fastening piece |
| 30 | Shock-absorbing |
40 | Flight control |
| 31 | |
401 | |
| 311 | |
402 | Circuit board |
The implementation, functional features and advantages of the objects of the present invention will be further explained with reference to the accompanying drawings.
Detailed Description
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 only a part of the embodiments of the present invention, and not all of the embodiments. 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.
It should be noted that all the directional indicators (such as up, down, left, right, front, and rear … …) in the embodiment of the present invention are only used to explain the relative position relationship between the components, the movement situation, etc. in a specific posture (as shown in the drawing), and if the specific posture is changed, the directional indicator is changed accordingly.
In the present invention, unless otherwise expressly stated or limited, the terms "connected," "secured," and the like are to be construed broadly, and for example, "secured" may be a fixed connection, a removable connection, or an integral part; can be mechanically or electrically connected; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. 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 addition, the descriptions related to "first", "second", etc. in the present invention are only for descriptive purposes and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In addition, the meaning of "and/or" appearing throughout is to include three juxtapositions, exemplified by "A and/or B," including either the A or B arrangement, or both A and B satisfied arrangement. In addition, technical solutions between various embodiments may be combined with each other, but must be realized by a person skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination should not be considered to exist, and is not within the protection scope of the present invention.
The present invention provides a shock absorbing platform 100. Referring to fig. 1 to 3, fig. 1 is a schematic perspective view of a shock absorbing platform 100 according to an embodiment of the present invention; FIG. 2 is an exploded view of the damping platform 100 according to an embodiment of the present invention; FIG. 3 is a cross-sectional view of one embodiment of the shock platform 100 of the present invention;
in an embodiment of the present invention, as shown in fig. 1, to achieve the above object, a damping platform 100 according to the present invention includes:
a first mounting platform 10;
a second mounting platform 20; and
a shock absorbing assembly 30, wherein the shock absorbing assembly 30 comprises a first valve body 31 and a second valve body 32, the first mounting platform 10 is connected with the first valve body 31, the second mounting platform 20 is connected with the second valve body 32, and the second valve body 32 is hollow;
the first valve body 31 is movably mounted on the second valve body 32, the first valve body 31 and the second valve body 32 are sealed to form a cavity 33, and the first mounting platform 10 and the second mounting platform 20 are connected through the first valve body 31 and the second valve body 32.
According to the technical scheme, the shock absorption assembly 30 is arranged between the first installation platform 10 and the second installation platform 20 to play a shock absorption role; the shock absorption assembly 30 of the present invention comprises a first valve body 31 and a second valve body 32, wherein the first mounting platform 10 is connected with the first valve body 31, the second mounting platform 20 is connected with the second valve body 32, and the second valve body 32 is hollow; the first valve body 31 is movably mounted on the second valve body 32, the first valve body 31 and the second valve body 32 are sealed to form a cavity 33, and the first mounting platform 10 and the second mounting platform 20 are connected through the first valve body 31 and the second valve body 32.
Because unmanned aerial vehicle is used outdoors, receives environmental factor's influence, the soft silica gel gasbag that current shock attenuation platform 100 used takes place the condition such as deformation, ageing easily for shock mitigation system's performance worsens, even became invalid.
Compared with the prior art, the damping platform 100 provided by the invention has the advantages that the silica gel air bag is replaced by the damping component 30 which is manufactured and molded by adopting a mold and has high stable performance, so that the problems that the traditional silica gel air bag is short in service life, easy to age and incapable of ensuring consistency are solved.
Wherein, a spring or the like can be installed in the cavity 33 to enhance the cushioning and shock-absorbing functions of the shock-absorbing assembly 30.
In order to better distinguish the location where the shock absorbing assembly 30 needs to be installed, the first mounting platform 10 and the second mounting platform 20 are provided with protruding ears 21, and the protruding ears 21 are protruded from the outer edge of the first mounting platform 10 or the second mounting platform 20.
The first valve body 31 and the second valve body 32 correspond to the protruding ear 21 on the first mounting platform 10 and the protruding ear 21 on the second mounting platform 20, respectively, so that an assembler can recognize the mounting positions of the first valve body 31 and the second valve body 32 on the first mounting platform 10 or the second mounting platform 20 conveniently.
In one embodiment, the shock absorbing platform 100 is provided with six shock absorbing assemblies 30 to ensure the stability of the first mounting platform 10.
The cavity 33 is vacuumized, the resistance of air in the cavity 33 generates a damping effect, and the air resistance forms a pressure with a direction opposite to the acting force transmitted by the second mounting platform 20, so that the first mounting platform 10 is prevented from swinging and vibrating, the stability of the first mounting platform 10 is improved, and the flight control main body part 40 mounted on the first mounting platform 10 is further damped.
The joints of the shock absorbing assembly 30 and the first and second mounting platforms 10 and 20 may be provided with a limiting structure, a waterproof structure, and the like.
In one embodiment, the first valve body 31 and the second valve body 32 may be sleeves, and the first valve body 31 is sleeved in the second valve body 32 or the second valve body 32 is sleeved in the first valve body 31. The first valve body 31 and the second valve body 32 are sleeved to enclose a cavity 33, and the cavity 33 is vacuumized, so that air damping can play a role in damping the first mounting platform 10.
The connection between the first valve body 31 and the second valve body 32 may also be performed by matching the diameters of the first valve body 31 and the second valve body 32, splicing the first valve body 31 and the second valve body 32, sealing the connection between the first valve body 31 and the second valve body 32, and then evacuating the cavity 33 enclosed inside the first valve body 31 and the second valve body 32.
In order to more conveniently connect the first valve body 31 and the first mounting platform 10 together, the first valve body 31 includes a first limiting portion 312 and a first connecting cylinder 313, the first limiting portion 312 is fixedly connected with the first connecting cylinder 313, the first limiting portion 312 is connected with the first mounting platform 10, and the first connecting cylinder 313 is movably mounted on the second valve body 32.
In one embodiment, the first position-limiting portion 312 is a disk structure, the first connecting cylinder 313 is a cylinder structure, and the first mounting platform 10 is connected to the first valve body 31 by connecting with the first position-limiting portion 312. The first limiting portion 312 and the first connecting cylinder 313 are integrally formed, the first valve body 31 may be made of resin, and the first valve body 31 is formed by injection molding in a mold during the production of the first valve body 31.
The first mounting platform 10 and the first position-limiting portion 312 may be fixedly connected or movably connected, and the connection manner of the first mounting platform 10 and the first position-limiting portion 312 includes but is not limited to snap connection, welding, snap connection or splicing.
In order to seal the first valve body 31 and the second valve body 32, the first valve body 31 includes a sealing piece 311, the sealing piece 311 is disposed on the first stopper 312 or the first connecting cylinder 313, and the sealing piece 311 seals the cavity 33. When the sealing piece 311 is disposed at the first position-limiting portion 312, the volume of the first valve body 31 is relatively larger than that of the cavity 33 enclosed inside the second valve body 32, but the bottom of the first connecting cylinder 313 is easily contacted with the inner top surface of the second valve body 32, the acting force applied to the second mounting platform 20 is easily transmitted to the first valve body 31 through the contact place, and the damping effect of the damping assembly 30 is reduced.
If the closing piece 311 set up in first connecting cylinder 313, first valve body 31 with the cavity 33 that the second valve body 32 inner wall was sealed and is formed is small in volume, first connecting cylinder 313 of first valve body 31 be difficult with the interior top surface of second valve body 32 contacts, first valve body 31 connecting cylinder with the space between the interior top surface of second valve body 32, it is exactly the volume of inner chamber, the air damping effect of inner chamber directly reaches the interior top surface of second valve body 32 with the closing piece 311 of first mounting platform 10. And because the cavity 33 is small in volume, the vacuum-pumping treatment in a short time is convenient.
In order to more conveniently connect the second valve body 32 and the second mounting platform 20 together, the second valve body 32 includes a second limiting portion 321 and a second connecting cylinder 323, the second limiting portion 321 is fixedly connected with the second connecting cylinder 323, and the second limiting portion 321 is connected with the second mounting platform 20.
In one embodiment, the second limiting portion 321 is a disk structure, the second connecting tube 323 is a cylinder structure, and the second mounting platform 20 is connected to the second valve body 32 by being connected to the second limiting portion 321. The second limiting portion 321 and the second connecting cylinder 323 are integrally formed, the second valve body 32 may be made of resin, and the second valve body 32 is formed by injection molding in a mold during the production of the second valve body 32.
To close the cavity 33, the second valve body 32 further comprises a fastener 324, and the fastener 324 is mounted to the second connector barrel 323 and blocks the cavity 33. The first valve body 31 forms a semi-closed structure through the sealing sheet 311, the second valve body 32 forms a semi-closed structure through the fastening piece 324, and the first valve body 31 and the second valve body 32 are installed together, and the first valve body 31 and the interior of the second valve body 32 enclose a closed cavity 33.
The fastening member 324 may be disposed on the sealing sheet 311 of the first valve body 31, and the bottom of the second valve body 32 is sealed, so that the cavity 33 may be vacuumized by a vacuum pump by pulling out the fastening member 324 of the first valve body 31.
In order to facilitate the vacuum-pumping process of the cavity 33, the second position-limiting portion 321 has a position-limiting hole 322, and the diameter of the fastening member 324 is identical to the position-limiting hole 322. Removing the fastening piece 324 from the limiting hole 322, and performing vacuum-pumping treatment on the cavity 33 by using a vacuum pump; after the vacuum pumping is finished, the fastening piece 324 blocks the limiting hole 322, so that the cavity 33 is sealed.
The fastener 324 can be extended to a sensor for electronic automatic compensation control, so that the environment of flight control is always in an optimal state.
The fastening member 324 and the limiting hole 322 are disposed in a matching manner, and the fastening member 324 is disposed on the second valve body 32, so that the limiting hole 322 is disposed on the second valve body 32; the fastening member 324 is disposed on the first valve body 31, and the limiting hole 322 is disposed on the first valve body 31. Wherein, the number of the protruding ears 21 is correspondingly set according to the requirement of the shock absorbing assembly 30.
The protruding ear 21 is provided with a positioning cylinder 22 to mount the first mounting platform 10 or the second mounting platform 20 into the unmanned aerial vehicle.
In an embodiment, a gap 210 is disposed between two adjacent protruding ears 21, and the shape of the gap 210 may be a semi-circle, an arc, or the like. The notch 210 and the protruding ear 21 are arranged, so that the first mounting platform 10 and the second mounting platform 20 are easier to identify and have more aesthetic appearance.
Specifically, the first mounting platform 10 and the second mounting platform 20 are provided with mounting holes 101, the first connecting cylinder 313 is connected with the first mounting platform 10 through the mounting holes 101, and the second connecting cylinder 323 is connected with the second mounting platform 20 through the mounting holes 101. The first connecting cylinder 313 penetrates through the mounting hole 101 of the first mounting platform 10, and the first limiting part 312 blocks the first valve body 31 from falling from the mounting hole 101; similarly, the second connecting cylinder 323 penetrates through the mounting hole 101 of the second mounting platform 20, and the second limiting portion 321 blocks the second valve body 32 from falling from the mounting hole 101.
The mounting holes 101 are provided on the projecting ears 21 to facilitate the mounting of the first valve body 31 to the first mounting platform 10 or the mounting of the second valve body 32 to the second mounting platform 20.
In one embodiment, the diameter of the first connecting cylinder 313 is smaller than the diameter of the second connecting cylinder 323, and the first connecting cylinder 313 is accommodated in the second connecting cylinder 323.
Alternatively, the first connecting cylinder 313 and the second connecting cylinder 323 are both cylindrical. The first connecting cylinder 313 and the second connecting cylinder 323 are arranged in a circular structure, so that the first connecting cylinder 313 is conveniently sleeved in the second connecting cylinder 323.
Specifically, the shock absorbing platform 100 further includes a flight control main body portion 40, the flight control main body portion 40 is mounted to the shock absorbing assembly 30, the flight control main body portion 40 includes a housing 401, and the housing 401 is mounted to the first mounting platform 10.
The housing 401 is mounted to the first mounting platform 10, and a circuit board 402 is mounted within the housing 401.
The present invention is not limited to the shape of the first mounting platform 10 and the second mounting platform 20.
The invention provides an unmanned aerial vehicle, which comprises a damping platform 100. Install in the unmanned aerial vehicle protective housing shock attenuation platform 100, because of cavity 33 evacuation back, shock attenuation platform 100 is right circuit board 402 of installation in the casing 401 protects, in order to ensure circuit board 402 is not shaken badly.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention, and all modifications and equivalents of the present invention, which are made by the contents of the present specification and the accompanying drawings, or directly/indirectly applied to other related technical fields, are included in the scope of the present invention.
Claims (10)
1. A shock absorbing platform, comprising:
a first mounting platform;
a second mounting platform; and
the damping assembly comprises a first valve body and a second valve body, the first mounting platform is connected with the first valve body, the second mounting platform is connected with the second valve body, and the second valve body is hollow;
the first valve body is movably arranged in the second valve body, a cavity is formed in the first valve body and the second valve body in a sealed mode, the cavity is vacuumized, and the first mounting platform is connected with the second mounting platform through the first valve body and the second valve body.
2. The shock absorbing platform of claim 1, wherein the first valve body comprises a first position limiting portion and a first connecting cylinder, the first position limiting portion is fixedly connected with the first connecting cylinder, the first position limiting portion is connected with the first mounting platform, and the first connecting cylinder is movably mounted on the second valve body.
3. The shock absorbing platform as set forth in claim 2, wherein said first valve body includes a closing piece, said closing piece is disposed on said first position-limiting portion or said first connecting cylinder, said closing piece closes said cavity.
4. The shock absorbing platform of claim 3, wherein said second valve body includes a second position limiting portion and a second connecting cylinder, said second position limiting portion being fixedly connected to said second connecting cylinder, said second position limiting portion being connected to said second mounting platform.
5. The shock absorbing platform of claim 4, wherein said second valve body further comprises a fastener mounted to said second connector barrel and blocking said cavity.
6. The shock absorbing platform of claim 5, wherein the second position-limiting portion defines a position-limiting hole, and the fastener has a diameter corresponding to the position-limiting hole.
7. The shock absorbing platform of claim 4, wherein said first mounting platform and said second mounting platform are provided with mounting holes through which said first connector barrel is connected to said first mounting platform and through which said second connector barrel is connected to said second mounting platform.
8. A shock absorbing platform as claimed in any one of claims 4 to 7, wherein the diameter of said first connector barrel is smaller than the diameter of said second connector barrel in which said first connector barrel is received.
9. The shock absorbing platform of any one of claims 1 to 7 further comprising an flight control body portion mounted to the shock absorbing assembly, the flight control body portion comprising a housing mounted to the first mounting platform.
10. An unmanned aerial vehicle comprising the shock absorbing platform of any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111102961.XA CN113833803A (en) | 2021-09-18 | 2021-09-18 | Shock attenuation platform and unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111102961.XA CN113833803A (en) | 2021-09-18 | 2021-09-18 | Shock attenuation platform and unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113833803A true CN113833803A (en) | 2021-12-24 |
Family
ID=78960114
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111102961.XA Pending CN113833803A (en) | 2021-09-18 | 2021-09-18 | Shock attenuation platform and unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113833803A (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203463542U (en) * | 2013-09-12 | 2014-03-05 | 深圳市铭昊五金模具有限公司 | Nitrogen spring with rod type sealing mode |
| CN204985475U (en) * | 2015-07-17 | 2016-01-20 | 吴大华 | Novel air damping shock absorber of doing all can for model |
| CN106352012A (en) * | 2016-11-29 | 2017-01-25 | 浙江华飞智能科技有限公司 | Shock-absorbing device and unmanned aerial vehicle |
| CN206571877U (en) * | 2017-01-23 | 2017-10-20 | 山东哈迪斯机车配件有限公司 | A kind of air spring damper |
| CN210215920U (en) * | 2019-07-05 | 2020-03-31 | 山东小鸭集团家电有限公司 | Domestic appliance footing |
| CN112594325A (en) * | 2020-12-08 | 2021-04-02 | 重庆工程职业技术学院 | Damper with efficient shock absorption function for aerial photography equipment |
| CN216078110U (en) * | 2021-09-18 | 2022-03-18 | 四川一电航空技术有限公司 | Shock attenuation platform and unmanned aerial vehicle |
-
2021
- 2021-09-18 CN CN202111102961.XA patent/CN113833803A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203463542U (en) * | 2013-09-12 | 2014-03-05 | 深圳市铭昊五金模具有限公司 | Nitrogen spring with rod type sealing mode |
| CN204985475U (en) * | 2015-07-17 | 2016-01-20 | 吴大华 | Novel air damping shock absorber of doing all can for model |
| CN106352012A (en) * | 2016-11-29 | 2017-01-25 | 浙江华飞智能科技有限公司 | Shock-absorbing device and unmanned aerial vehicle |
| CN206571877U (en) * | 2017-01-23 | 2017-10-20 | 山东哈迪斯机车配件有限公司 | A kind of air spring damper |
| CN210215920U (en) * | 2019-07-05 | 2020-03-31 | 山东小鸭集团家电有限公司 | Domestic appliance footing |
| CN112594325A (en) * | 2020-12-08 | 2021-04-02 | 重庆工程职业技术学院 | Damper with efficient shock absorption function for aerial photography equipment |
| CN216078110U (en) * | 2021-09-18 | 2022-03-18 | 四川一电航空技术有限公司 | Shock attenuation platform and unmanned aerial vehicle |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US11272290B2 (en) | Speaker module and electronic device | |
| KR101906097B1 (en) | Ventilation element for a housing containing an electrical, mechanical or electromechanical member | |
| CN216078110U (en) | Shock attenuation platform and unmanned aerial vehicle | |
| EP2642152A1 (en) | Vibration isolation device, and bracket for vibration isolation device | |
| US20100264569A1 (en) | Liquid sealed-in type vibration damper | |
| US8973704B2 (en) | Vibration absorbing mounting device | |
| JP2018082090A (en) | Electronic device | |
| CN113833803A (en) | Shock attenuation platform and unmanned aerial vehicle | |
| CN105813003B (en) | Installation shell, manufacturing method and the mounting structure of loudspeaker and microphone | |
| CN108973643B (en) | Torsion bar | |
| JP6745228B2 (en) | Electronic control unit | |
| WO2021018723A1 (en) | Sensor | |
| CN111787144A (en) | Microphone sealing structure and terminal equipment | |
| WO2018090300A1 (en) | A damping assembly | |
| CN110658302A (en) | Nitrogen oxygen sensor and shell with waterproof and breathable structure | |
| CN214507368U (en) | Sound production device and electronic equipment | |
| CN111935619B (en) | Loudspeaker module and sound generating device | |
| JP2000208948A (en) | Structure of instrument housing | |
| CN207252092U (en) | Gum cover, housing, seal assembly and mobile terminal | |
| CN209266019U (en) | Hard-disk cartridge, hard disk unit and electronic equipment | |
| CN212573204U (en) | Protection device of electronic product and electronic equipment for agricultural machinery | |
| CN212890969U (en) | Flight control assembly and mobile device | |
| CN216218215U (en) | Automobile controller shell and automobile controller | |
| CN221304264U (en) | Combined hard disk box with good safety protection | |
| CN209787642U (en) | Electronic control unit |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |