CN211417568U - Unmanned aerial vehicle frame and unmanned aerial vehicle - Google Patents
Unmanned aerial vehicle frame and unmanned aerial vehicle Download PDFInfo
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- CN211417568U CN211417568U CN201921885079.5U CN201921885079U CN211417568U CN 211417568 U CN211417568 U CN 211417568U CN 201921885079 U CN201921885079 U CN 201921885079U CN 211417568 U CN211417568 U CN 211417568U
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Abstract
The utility model belongs to the technical field of unmanned aerial vehicle, especially, relate to an unmanned aerial vehicle frame and unmanned aerial vehicle, this unmanned aerial vehicle frame includes the main frame body, a plurality of first rotor arm and a plurality of second rotor arm, the main frame body includes first main body frame, second main body frame and a plurality of purlin, first main body frame and the relative interval of second main body frame set up, the first end of each purlin all is connected with first main body frame and interval distribution is around first main body frame, the second end of each purlin all is connected with second main body frame and interval distribution is around second main body frame; each first rotor arm is mounted on the first main body frame, and each second rotor arm is mounted on the second main body frame. This unmanned aerial vehicle frame can bear bigger load for use the unmanned aerial vehicle fuselage bulk strength that has this unmanned aerial vehicle frame and effectively strengthened, can solve current unmanned aerial vehicle fuselage and have that intensity is weak, anti big overload capacity and the not enough problem of rigidity.
Description
Technical Field
The utility model belongs to the technical field of unmanned aerial vehicle, especially, relate to an unmanned aerial vehicle frame and unmanned aerial vehicle.
Background
The use of unmanned aerial vehicles in the industry is more and more popular at present, and the unmanned aerial vehicle has great application prospects in the fields of agriculture, security protection, electric power, petrifaction, aerial photography and the like; unmanned aerial vehicle in the industry of present need set up a plurality of cavities and a plurality of mounting groove isotructures in the design, in order to subtract heavy or lay angle considerations such as equipment, on the general unmanned aerial vehicle fuselage, this causes unmanned aerial vehicle fuselage intensity to be more weak, anti big overload capacity is poor and fuselage rigidity is not enough scheduling problem easily, influences unmanned aerial vehicle's flight stability, causes the potential safety hazard.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide an unmanned aerial vehicle frame and unmanned aerial vehicle aims at solving the technical problem that unmanned aerial vehicle fuselage intensity among the prior art is more weak, anti big overload capacity is poor and rigidity is not enough.
In order to achieve the above object, the utility model adopts the following technical scheme: an unmanned aerial vehicle frame comprises a main frame body, a plurality of first rotor arms and a plurality of second rotor arms, wherein the main frame body comprises a first main body frame, a second main body frame and a plurality of stringers, the first main body frame and the second main body frame are arranged at intervals, a first end of each stringer is connected with the first main body frame and distributed around the first main body frame at intervals, and a second end of each stringer is connected with the second main body frame and distributed around the second main body frame at intervals; each of the first rotor arms is mounted on the first body frame, and each of the second rotor arms is mounted on the second body frame.
Optionally, the first body frame and the second body frame are both annular, and the stringers are arranged in parallel at intervals.
Optionally, a plurality of first mounting grooves are formed in the side surface, facing the second main body frame, of the first main body frame, and a first end of each stringer is fixedly mounted in the first mounting groove; the side surface of the second main body frame facing the first main body frame is provided with a plurality of second mounting grooves, and the second end of each stringer is fixedly mounted in the second mounting groove.
Optionally, a first end of each of the stringers is connected to the first body frame by a first fastener, and a second end of each of the stringers is connected to the second body frame by a second fastener.
Optionally, a first end of each of the stringers is bonded to the first body frame, and a second end of each of the stringers is bonded to the second body frame.
Optionally, each of the first rotor arms is located on the same side portion of the first main body frame, each of the second rotor arms is located on the same side portion of the second main body frame, and the first rotor arm and the second rotor arm are located on opposite side portions of the main body frame.
Optionally, the unmanned aerial vehicle frame further includes a plurality of first connecting pieces and a plurality of second connecting pieces, each of the first connecting pieces is mounted on the first main body frame and arranged at intervals, and an end of each of the first rotor arms is connected to each of the first connecting pieces in a one-to-one correspondence manner; the second connecting pieces are arranged on the second main body frame at intervals, and the end parts of the second rotor arms are correspondingly connected with the second connecting pieces one by one.
Optionally, a plurality of first fixing protrusions are arranged on the side portion of the first main body frame, each first connecting piece comprises a first connecting cylinder section and a first fixing portion connected with the first connecting cylinder section, the end portion of the first rotor arm is fixedly inserted into the first connecting cylinder section, a first notch is arranged on the first fixing portion, and two adjacent side surfaces of the first notch are respectively and fixedly attached to two adjacent side surfaces of the first fixing protrusions; the lateral part of the second main body frame is provided with a plurality of second fixing bulges, each second connecting piece comprises a second connecting cylinder section and a second fixing part connected with the second connecting cylinder section, the end part of the second rotor arm is fixedly inserted into the second connecting cylinder section, a second notch is arranged on the second fixing part, and the adjacent two side faces of the second notch are respectively tightly attached to and fixedly connected with the adjacent two side faces of the second fixing bulges.
Optionally, the main frame body is an aircraft aluminum frame body or a composite material frame body.
The utility model provides an above-mentioned one or more technical scheme in the unmanned aerial vehicle frame have one of following technological effect at least: after the first main body frame and the second main body frame are arranged at intervals relatively, the first main body frame and the second main body frame are connected by utilizing the stringers, and the first end and the second end of each stringer are respectively distributed around the first main body frame and around the second main body frame at intervals, so that a closed stressed main frame body is formed, the bearing capacity of the first main body frame and the second main body frame conducted by the first rotor arm and the second rotor arm and the acting force of the main frame body conducted by the outside can be transmitted to the whole main frame body through the stringers, the bearing capacity and the external acting force are effectively decomposed, the whole unmanned aerial vehicle frame can bear larger load, the bearing capacity of the unmanned aerial vehicle frame is greatly improved, the overall strength of the unmanned aerial vehicle body with the unmanned aerial vehicle frame is effectively enhanced, and the problems that the existing unmanned aerial vehicle body is weak in strength and weak in strength, Large overload resistance and insufficient rigidity.
The utility model discloses another technical scheme be: an unmanned aerial vehicle, includes foretell unmanned aerial vehicle frame.
The utility model discloses an unmanned aerial vehicle owing to used foretell unmanned aerial vehicle frame for the unmanned aerial vehicle fuselage bulk strength of this unmanned aerial vehicle frame obtains effectively strengthening, can solve current unmanned aerial vehicle fuselage and have the problem that intensity is weak, anti big overload capacity and rigidity are not enough.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for the embodiments or the prior art descriptions will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without inventive labor.
Fig. 1 is the embodiment of the utility model provides a structural schematic of unmanned aerial vehicle frame.
Fig. 2 is an exploded view of the drone bay shown in fig. 1.
Wherein, in the figures, the respective reference numerals:
10-main frame body 11-first main body frame 12-second main body frame
13-stringer 21-first rotor arm 22-second rotor arm
31-first connecting piece 32-second connecting piece 111-first mounting groove
112-first fixing protrusion 121-second mounting groove 122-second fixing protrusion
131-lightening slot 311-first connecting cylinder section 312-first fixing part
321, second connecting cylinder section 322, second fixing part 3121, first gap
3221-second gap.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to fig. 1-2 are exemplary and intended to be used to illustrate the invention, but should not be construed as limiting the invention.
In the description of the present invention, it is to be understood that the terms "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are merely for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only 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 one or more of that feature. In the description of the present invention, "a plurality" means two or more unless specifically limited otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," and "fixed" are to be construed broadly and may, for example, be fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meaning of the above terms in the present invention can be understood according to specific situations by those skilled in the art.
As shown in fig. 1-2, in an embodiment of the present invention, an unmanned aerial vehicle frame is provided, which is suitable for various types of unmanned aerial vehicles, and is disposed inside the unmanned aerial vehicle frame to support the unmanned aerial vehicle frame, further, the unmanned aerial vehicle frame includes a main frame body 10, a plurality of first rotor arms 21 and a plurality of second rotor arms 22, the main frame body 10 includes a first main frame 11, a second main frame 12 and a plurality of stringers 13, the first main frame 11 and the second main frame 12 are disposed at intervals, a first end of each stringer 13 is connected to the first main frame 11 and is spaced around the first main frame 11, and a second end of each stringer 13 is connected to the second main frame 12 and is spaced around the second main frame 12; each first rotor arm 21 is mounted on the first main body frame 11, and each second rotor arm 22 is mounted on the second main body frame 12.
Specifically, in the unmanned aerial vehicle frame according to the embodiment of the present invention, after the first main body frame 11 and the second main body frame 12 are disposed at a relative interval, the first main body frame 11 and the second main body frame 12 are connected by using the stringers 13, and the first end and the second end of each stringer 13 are respectively disposed at the periphery of the first main body frame 11 and the periphery of the second main body frame 12 at an interval, so as to form a closed stressed main frame 10, and the bearing capacity transmitted to the first main body frame 11 and the second main body frame 12 by the first rotor arm 21 and the second rotor arm 22 and the acting force transmitted to the main frame 10 from the outside can be transmitted to the entire main frame 10 through the stringers 13, so as to effectively decompose the bearing capacity and the external acting force, so that the entire unmanned aerial vehicle frame can bear a larger load, thereby greatly improving the bearing capacity of the unmanned aerial vehicle frame, and effectively enhancing the overall strength of the unmanned aerial vehicle body to which is applied with the unmanned aerial vehicle frame, the problem that the existing unmanned aerial vehicle body is weak in strength, resistant to large overload capacity and insufficient in rigidity can be solved.
In another embodiment of the present invention, as shown in fig. 1-2, the first main body frame 11 and the second main body frame 12 of the unmanned aerial vehicle frame are both circular, and the stringers 13 are disposed in parallel at intervals. Specifically, the first main body frame 11 and the second main body frame 12 are annular, and the stringers 13 are arranged in parallel at intervals, so that a cylindrical main frame body 10 can be formed, the components of the whole main frame body 10 are uniformly distributed, and no stress concentration area exists, so that when the bearing capacity of the first main body frame 11 and the second main body frame 12 conducted by the first rotor arm 21 and the second rotor arm 22 and the acting force of the external part conducted to the main frame body 10 can be uniformly transmitted to the whole main frame body 10 through the stringers 13, the bearing capacity of the whole main frame body 10 is uniformly distributed, the stress concentration position is small, the bearing capacity of the main frame body 10 can be further increased, and the strength of the unmanned aerial vehicle frame is further improved.
In another embodiment of the present invention, as shown in fig. 1-2, a plurality of first mounting grooves 111 are provided on a side surface of the first main body frame 11 of the unmanned aerial vehicle frame facing the second main body frame 12, and a first end of each stringer 13 is fixedly mounted in the first mounting groove 111; the second body frame 12 is provided with a plurality of second mounting grooves 121 facing the side of the first body frame 11, and the second end of each stringer 13 is fixedly mounted in the second mounting groove 121. Specifically, as the first end of the stringer 13 is fixedly installed in the first installation groove 111, the first end of the stringer 13 is abutted against the wall surface of the first installation groove 111 to bear a large lateral acting force, so that the lateral acting force bearing capacity of the unmanned aerial vehicle frame is greatly improved; because the second end fixed mounting of stringer 13 is in second mounting groove 121, the second end of stringer 13 can bear great side effort with the wall looks butt of the groove of second mounting groove 121, improves this unmanned aerial vehicle frame greatly and bears side effort ability.
Further, the first mounting groove 111 and the second mounting groove 121 can play a role of fixing the stringer 13, and the mass of the first main body frame 11 and the second main body frame 12 can be greatly reduced, wherein the first mounting groove 111 extends along the circumferential direction of the first main body frame 11, the second mounting groove 121 extends along the circumferential direction of the second main body frame 12, meanwhile, the first mounting groove 111 is arranged on two opposite side faces of the first main body frame 11 and is symmetrically arranged, and the second mounting groove 121 is arranged on two opposite side faces of the second main body frame 12 and is symmetrically arranged, so that the mass of the unmanned aerial vehicle frame can be greatly reduced.
Further, the opposite two side faces of each stringer 13 are provided with weight reduction grooves 131 extending along the length defensive lines, so that the weight of the unmanned aerial vehicle frame can be reduced to the greatest extent, and the unmanned aerial vehicle is designed in a light weight mode.
In another embodiment of the present invention, as shown in fig. 1-2, a first end of each stringer 13 of the unmanned aerial vehicle frame is connected to the first main body frame 11 through a first fastener (not shown), and a second end of each stringer 13 is connected to the second main body frame 12 through a second fastener (not shown). Specifically, adopt first fastener to be connected between stringer 13 and the first main body frame 11, adopt the second fastener to be connected between stringer 13 and the second main body frame 12, the dismouting of fastener is simple to make easy dismounting between stringer 13, first main body frame 11 and the second main body frame 12 swift, this unmanned aerial vehicle frame's dismouting labour saving and time saving, convenient and fast also is convenient for realize the rapid production of this unmanned aerial vehicle frame.
Further, first main body frame 11 and second main body frame 12 adopt same structure, and the structure of each stringer 13 is also the same, is convenient for realize the modularization equipment of unmanned aerial vehicle frame like this, further improves this unmanned aerial vehicle frame production efficiency.
In another embodiment of the present invention, the first end of each stringer 13 of the provided unmanned aerial vehicle frame is all glued to the first main body frame 11, and the second end of each stringer 13 is all glued to the second main body frame 12. Specifically, all adopt glue to bond between first main body frame 11 and the stringer 13 and between second main body frame 12 and the stringer 13, adopt the mode easy operation that glue bonds, the quick preparation of this unmanned aerial vehicle frame of also being convenient for to, also need not with the help of other adapting unit, its structure is compacter, and the practicality is good.
In another embodiment of the present invention, as shown in fig. 1-2, each first rotor arm 21 of the provided unmanned aerial vehicle frame is located at the same side portion of the first main body frame 11, each second rotor arm 22 is located at the same side portion of the second main body frame 12, and the first rotor arm 21 and the second rotor arm 22 are respectively located at the opposite side portions of the main body frame 10. Specifically, first rotor arm 21 and second rotor arm 22 are located the relative two diagonal positions of main frame body 10 respectively, and first rotor arm 21 transmits the effort and the effort on second rotor arm 22 and the second main body frame 12 for first main body frame 11 like this, and opposite direction of both sets up, can offset each other, realizes the balance of effort self, and the bearing capacity who further increases this unmanned aerial vehicle frame.
In another embodiment of the present invention, as shown in fig. 1-2, the provided unmanned aerial vehicle frame further includes a plurality of first connecting members 31 and a plurality of second connecting members 32, each first connecting member 31 is installed on the first main body frame 11 and spaced apart from the first main body frame, and the end of each first rotor arm 21 is connected to each first connecting member 31 in a one-to-one correspondence; the second connecting members 32 are mounted on the second body frame 12 at intervals, and the end portions of the second rotor arms 22 are connected to the second connecting members 32 in a one-to-one correspondence. Specifically, be connected through first connecting piece 31 between first rotor arm 21 and the first main part frame 11, be connected through first connecting piece 31 between second rotor arm 22 and the second main part frame 12, its connection stability is good, make between main frame body 10 and the first rotor arm 21 and between main frame body 10 and the second rotor arm 22 firm in connection, whole unmanned aerial vehicle frame rigidity is firm, the whole atress of unmanned aerial vehicle frame is balanced, the front and back rotor arm rigidity that is applied with the unmanned aerial vehicle of this unmanned aerial vehicle frame is firm, power conduction is even between rotor arm and the unmanned aerial vehicle frame, whole structural strength is big, structural rigidity is firm.
In another embodiment of the present invention, as shown in fig. 1-2, a plurality of first fixing protrusions 112 are disposed on a side portion of the first main body frame 11 of the unmanned aerial vehicle frame, each first connecting member 31 includes a first fixing portion 312 where the first connecting cylinder 311 is connected to the first connecting cylinder 311, an end portion of the first rotor arm 21 is inserted into the first connecting cylinder 311, a first notch 3121 is disposed on the first fixing portion 312, and two adjacent side surfaces of the first notch 3121 are respectively tightly attached to two adjacent side surfaces of the first fixing protrusions 112; a plurality of second fixing protrusions 122 are disposed on the side of the second body frame 12, each second connecting member 32 includes a second connecting tube section 321 and a second fixing portion 322 connected to the second connecting tube section 321, the end of the second rotor arm 22 is inserted into the second connecting tube section 321, a second gap 3221 is disposed on the second fixing portion 322, and two adjacent side surfaces of the second gap 3221 are respectively and fixedly attached to two adjacent side surfaces of the second fixing protrusions 122.
Specifically, the end of the first rotor arm 21 and the end of the second rotor arm 22 are respectively inserted and fixed in the first connecting cylinder section 311 and the second connecting cylinder section 321, so that the connection between the first rotor arm 21 and the first connecting member 31 and the connection between the second rotor arm 22 and the second connecting member 32 are more stable and firm, meanwhile, two adjacent side surfaces of the notch on the first fixing portion 312 of the first connecting member 31 are respectively and tightly fixed on two adjacent side surfaces of the first fixing protrusion 112, and through the abutting action of the side surfaces, the connection between the first connecting member 31 and the first main body frame 11 is stable and firm, and the connection rigidity and the connection strength are good; adjacent both sides face of breach on the second fixed part 322 of second connecting piece 32 hugs closely respectively on being fixed in the adjacent both sides face of the fixed arch 122 of second, through the butt effect of side, it is firm and stable to be connected between second connecting piece 32 and the second main part frame 12 effectively, connection rigidity and joint strength are good, between main frame body 10 and the first rotor arm 21 and between main frame body 10 and the second rotor arm 22 more firm in connection and joint rigidity are good, make whole unmanned aerial vehicle frame rigidity more firm, the whole atress of unmanned aerial vehicle frame is balanced, the front and back rotor arm rigidity that has applied the unmanned aerial vehicle of this unmanned aerial vehicle frame is firm, power conduction is even between rotor arm and the unmanned aerial vehicle frame, complete machine structural strength is big, structural rigidity is firm.
In another embodiment of the present invention, the main frame body 10 of the unmanned aerial vehicle frame is an aviation aluminum frame body or a composite material frame body. Specifically, main framework 10 adopts aviation aluminium or combined material as the integrative main frame body of material preparation, and it has the advantage that intensity is high, light in weight, rigidity is good, the damage resistance can the reinforce, further increases the bulk strength of this unmanned aerial vehicle frame.
In another embodiment of the present invention, an unmanned aerial vehicle is provided, comprising the above-mentioned unmanned aerial vehicle frame.
The utility model discloses unmanned aerial vehicle owing to used foretell unmanned aerial vehicle frame for the unmanned aerial vehicle fuselage bulk strength of this unmanned aerial vehicle frame obtains effectively strengthening, can solve current unmanned aerial vehicle fuselage and have the problem that intensity is weak, anti big overload capacity and rigidity are not enough.
The above description is only exemplary of the present invention and should not be construed as limiting the present invention, and any modifications, equivalents and improvements made within the spirit and principles of the present invention are intended to be included within the scope of the present invention.
Claims (10)
1. An unmanned aerial vehicle frame, its characterized in that: the main frame body comprises a first main body frame, a second main body frame and a plurality of stringers, the first main body frame and the second main body frame are arranged oppositely at intervals, a first end of each stringer is connected with the first main body frame and distributed around the first main body frame at intervals, and a second end of each stringer is connected with the second main body frame and distributed around the second main body frame at intervals;
each of the first rotor arms is mounted on the first body frame, and each of the second rotor arms is mounted on the second body frame.
2. The unmanned aerial vehicle frame of claim 1, wherein: the first main body frame and the second main body frame are both in a circular ring shape, and the stringers are arranged in parallel at intervals.
3. The unmanned aerial vehicle frame of claim 1, wherein: a plurality of first mounting grooves are formed in the side face, facing the second main body frame, of the first main body frame, and the first end of each stringer is fixedly mounted in each first mounting groove; the side surface of the second main body frame facing the first main body frame is provided with a plurality of second mounting grooves, and the second end of each stringer is fixedly mounted in the second mounting groove.
4. The unmanned aerial vehicle frame of claim 1, wherein: the first end of each stringer is connected with the first body frame through a first fastener, and the second end of each stringer is connected with the second body frame through a second fastener.
5. The unmanned aerial vehicle frame of claim 1, wherein: the first end of each stringer is glued to the first body frame, and the second end of each stringer is glued to the second body frame.
6. The unmanned aerial vehicle frame of claim 1, wherein: each of the first rotor arms is located on the same side portion of the first main body frame, each of the second rotor arms is located on the same side portion of the second main body frame, and the first rotor arms and the second rotor arms are located on opposite side portions of the main frame body, respectively.
7. An unmanned aerial vehicle frame as claimed in any one of claims 1 ~ 6, characterized in that: the unmanned aerial vehicle frame further comprises a plurality of first connecting pieces and a plurality of second connecting pieces, each first connecting piece is mounted on the first main body frame and arranged at intervals, and the end part of each first rotor arm is connected with each first connecting piece in a one-to-one correspondence manner; the second connecting pieces are arranged on the second main body frame at intervals, and the end parts of the second rotor arms are correspondingly connected with the second connecting pieces one by one.
8. The unmanned aerial vehicle frame of claim 7, wherein: the side part of the first main body frame is provided with a plurality of first fixing bulges, each first connecting piece comprises a first connecting cylinder section and a first fixing part connected with the first connecting cylinder section, the end part of the first rotor arm is fixedly inserted into the first connecting cylinder section, the first fixing part is provided with a first notch, and two adjacent side surfaces of the first notch are respectively and fixedly connected with two adjacent side surfaces of the first fixing bulges in a clinging manner;
the lateral part of the second main body frame is provided with a plurality of second fixing bulges, each second connecting piece comprises a second connecting cylinder section and a second fixing part connected with the second connecting cylinder section, the end part of the second rotor arm is fixedly inserted into the second connecting cylinder section, a second notch is arranged on the second fixing part, and the adjacent two side faces of the second notch are respectively tightly attached to and fixedly connected with the adjacent two side faces of the second fixing bulges.
9. An unmanned aerial vehicle frame as claimed in any one of claims 1 ~ 6, characterized in that: the main frame body is an aviation aluminum frame body or a composite material frame body.
10. An unmanned aerial vehicle, its characterized in that: including the drone bay of any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921885079.5U CN211417568U (en) | 2019-11-04 | 2019-11-04 | Unmanned aerial vehicle frame and unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921885079.5U CN211417568U (en) | 2019-11-04 | 2019-11-04 | Unmanned aerial vehicle frame and unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211417568U true CN211417568U (en) | 2020-09-04 |
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ID=72253142
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921885079.5U Expired - Fee Related CN211417568U (en) | 2019-11-04 | 2019-11-04 | Unmanned aerial vehicle frame and unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN211417568U (en) |
-
2019
- 2019-11-04 CN CN201921885079.5U patent/CN211417568U/en not_active Expired - Fee Related
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Granted publication date: 20200904 Termination date: 20211104 |