CN213262924U - Carry thing aircraft - Google Patents
Carry thing aircraft Download PDFInfo
- Publication number
- CN213262924U CN213262924U CN202021382627.5U CN202021382627U CN213262924U CN 213262924 U CN213262924 U CN 213262924U CN 202021382627 U CN202021382627 U CN 202021382627U CN 213262924 U CN213262924 U CN 213262924U
- Authority
- CN
- China
- Prior art keywords
- clamping part
- clamping
- strap
- guide rail
- article
- 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.)
- Active
Links
Images
Abstract
The utility model discloses an object carrying aircraft, which comprises an aircraft main body with a guide rail and an object carrying device, wherein the object carrying device is arranged on the aircraft main body to load or unload loaded articles; the carrying device comprises a first clamping part, a second clamping part and a clamping device; the first clamping part and the second clamping part are movably connected to the guide rail; the clamping device is connected with the movable first clamping part and/or the movable second clamping part, so that the first clamping part and/or the second clamping part clamp or release the article to load and unload the article. The article is clamped through the clamping of the first clamping part and the second clamping part, the loading application range of the article with different specifications is improved, extra carriers such as special express boxes do not need to be manufactured, and the technical problem that in the prior art, the logistics cost is increased sharply due to the fact that the loading application range is improved through the special express boxes is solved.
Description
Technical Field
The utility model relates to a commodity circulation field especially indicates a carry thing aircraft.
Background
At present, with the vigorous development of the logistics industry, the adoption of an aircraft for express delivery of articles becomes a popular research direction. Especially, the delivery mode of unmanned aerial vehicle is more receiving much attention, but the parcel of express delivery is because specification size diverse, consequently makes unmanned aerial vehicle commodity circulation receive very big degree's restriction.
Through designing dedicated express delivery box among the prior art to realize transporting the article parcel of different specifications through the aircraft, all pack the parcel into dedicated express delivery box, because the external dimension of dedicated express delivery box is unanimous, so the aircraft just can load, but dedicated express delivery box must make the cost of commodity circulation improve by a wide margin.
Technical personnel in the field are searching for a cargo aircraft to satisfy the demand of different specification express delivery article, help solving the technical problem that adopts special express delivery box among the prior art, lead to aircraft logistics cost to improve by a wide margin.
SUMMERY OF THE UTILITY MODEL
The application provides a carry thing aircraft, its aim at improves the application scope to different specification article loads through the mode of first clamping part and second clamping part centre gripping, as long as article can place between first clamping part and second clamping part, just can realize loading article, and no longer need use special express delivery box, make the external dimension of article unanimous, thereby help solving prior art and improve the application scope of loading through special express delivery box, lead to the technical problem that logistics cost sharply increases.
The carrier aircraft comprises an aircraft body with a guide rail and a carrier device mounted on the aircraft body for loading or unloading carrier items;
the carrying device comprises a first clamping part, a second clamping part and a clamping device;
the first clamping part and/or the second clamping part are movably connected to the guide rail;
the clamping device is connected with the movable first clamping part and/or the movable second clamping part, so that the first clamping part and the second clamping part clamp or release the article to load and unload the article.
In an embodiment, the clamping device is an elastic bandage, and two ends of the elastic bandage are detachably bound on the first clamping part and the second clamping part to provide pre-tightening force between the first clamping part and the second clamping part to realize clamping.
In one embodiment, the clamping device comprises a connection lock and a first strap set, and a second strap set;
the connecting lock is arranged on the aircraft body between the first clamping part and the second clamping part;
the first binding belt group comprises a first connecting belt and a second connecting belt, one end of the first connecting belt is connected with the connecting lock in a matched mode so as to be connected with or disconnected from the first connecting belt through controlling the connecting lock, the other end of the first connecting belt is connected to the first clamping part, one end of the second connecting belt is connected with the first clamping part, and the other end of the second connecting belt is connected to the aircraft main body;
the second bandage group includes third connecting band and fourth connecting band, the one end of third connecting band with connect the lock cooperation and connect in order to realize through control connect the lock with the third connecting band is connected or is broken off, the other end of third connecting band is connected on the second clamping part, the one end of fourth connecting band with the second clamping part is connected, the other end of fourth connecting band is connected in the aircraft main part.
In one embodiment, the aircraft body comprises at least one of the guide rails and a power system, and a first connecting beam and a second connecting beam;
the two ends of the guide rail are respectively connected to the middle parts of the first connecting beam and the second connecting beam, and the power system is arranged on the guide rail and/or the first connecting beam and/or the second connecting beam;
the first connecting beam and the first clamping part are arranged on one side of the guide rail;
the second connecting beam and the second clamping part are arranged on the other side of the guide rail;
the other end of the second connecting belt is connected with the first connecting beam;
the other end of the fourth connecting band is connected with the second connecting beam.
In one embodiment, the power system comprises four rotors, and the four rotors are respectively arranged at two ends of the first connecting beam and the second connecting beam.
In one embodiment, the other end of the second connecting band is connected to the first connecting beam through a rolling device;
the winding device comprises a winding wheel, a pin seat and a plug pin;
the winding wheel is rotatably connected to the first connecting beam, and the other end of the second connecting belt is fixed to the winding wheel, so that the second connecting belt is driven to wind the winding wheel to adjust the length of the second connecting belt when the winding wheel rotates;
a plurality of positioning holes are circumferentially arranged on the end face of one end of the winding wheel around the rotating direction;
the pin seat is connected to the first connecting beam, and a pin hole is formed in the pin seat, so that the pin hole is connected with one of the positioning holes in a butt joint mode, then the pin is inserted into the positioning hole to achieve rotating positioning of the winding wheel, and then the telescopic length of the second connecting belt is fixed.
In one embodiment, one end of each of the first clamping part and the second clamping part is movably connected to the guide rail;
the other ends of the first clamping part and the second clamping part are respectively turned towards the space direction between the first clamping part and the second clamping part to form a hook-shaped structure.
In an embodiment, the at least one guide rail is two and arranged in the same direction, and two ends of each guide rail are respectively connected with the middle parts of the first connecting beam and the second connecting beam.
In one embodiment, the first clamping portion comprises two hook-shaped beams and two moving blocks, and a connecting plate and at least one connecting beam;
one end of each hook-shaped beam is of the hook-shaped structure, and the other end of each hook-shaped beam is connected with one moving block, so that the first clamping part is movably connected to the guide rail through the moving block;
the two hook-shaped beams are arranged side by side, and the connecting plate is respectively connected with the two moving blocks;
and two ends of each connecting beam are respectively connected to the two hook-shaped beams.
In an embodiment, the aircraft body further comprises a landing gear connected to the guide rail such that the article is suspended when the first and second clamping portions clamp the article.
As can be seen from the above, based on the above embodiment, the cargo aircraft of this application provides one kind and improves the technical scheme to the application scope that different specification article loaded through first clamping part and second clamping part centre gripping mode, replaces the mode that uses special express delivery box to help solving prior art and improve and load application scope through special express delivery box, finally lead to the technical problem that the commodity circulation cost sharply increases.
Drawings
Fig. 1 is a schematic external structural view of an embodiment of the present invention;
fig. 2 is a schematic external structural view of another embodiment of the present invention;
fig. 3 is an enlarged schematic view of a portion a of fig. 2 according to the present invention;
fig. 4 is a schematic structural view of the first clamping portion of the present invention.
Description of the labeling:
1 aircraft body
11 guide rail
12 power system
121 rotor
13 first connecting beam
14 second connecting beam
15 winding device
151 winding wheel
1511 locating hole
152 pin base
1521 Pin hole
153 bolt
16 undercarriage
2 carry thing device
21 first clamping part
211 hook beam
212 moving block
213 connecting plate
214 connecting beam
22 second clamping part
23 clamping device
231 connecting lock
232 first strap set
2321 first connecting band
2322 second connecting band
233 second strap set
2331 third connecting band
2332 fourth connecting band
Detailed Description
The applicant has found that it is difficult to load all sizes of said articles on the cargo of said aircraft during logistics of current cargo aircraft, due to the different sizes and volumes of said articles. The express box is often designed in the prior art, and the application range of the loaded goods of the cargo aircraft can be widened because the special express box has the consistent size. However, although the special express box can expand the loading application range of the carrier aircraft, obviously, the special express box has certain cost, and the use of the special express box can cause the final logistics cost to be increased sharply.
Fig. 1 is a schematic diagram of an external structure according to an embodiment of the present invention. In an embodiment, shown in fig. 1, there is provided a carrier aircraft comprising an aircraft body 1 with a rail 11 and a carrier device 2, the carrier device 2 being mounted on the aircraft body 1 for loading or unloading a load-bearing article 10;
the carrying device 2 comprises a first clamping part 21, a second clamping part 22 and a clamping device 23;
the first clamping part 21 and/or the second clamping part 22 are movably connected on the guide rail 11;
the clamping device 23 is connected with the movable first clamping part 21 and/or the movable second clamping part 22, so that the first clamping part 21 and the second clamping part 22 clamp or release the article 10 to load and unload the article.
In the present embodiment, a specific structure of a cargo aircraft is provided, on which an article 10 is loaded by a cargo device 2, since the article 10 is loaded by adopting a manner in which a first clamping portion 21 and a second clamping portion 22 of the cargo device 2 are clamped, so that no matter how external contours of the article 10 are, as long as the article 10 can be placed between the first clamping portion 21 and the second clamping portion 22, loading can be theoretically achieved by clamping the first clamping portion 21 and the second clamping portion 22, and therefore, a size range of the article 10 loaded by the cargo aircraft is increased, and the special express box is not used in the present embodiment, thereby helping to solve the technical problem in the prior art that the logistics cost is increased due to the fact that the size application range of the article 10 loaded by the cargo aircraft is increased by adopting the special express box.
In addition, the clamping device 23 is used for controlling the first clamping part 21 and/or the second clamping part 22 to be in a clamping or releasing state, so that the clamping device 23 only needs to control the first clamping part 21 and/or the second clamping part 22 which can move in the clamping or releasing state.
In one embodiment, the clamping device 23 is an elastic band, and two ends of the elastic band are detachably tied to the first clamping portion 21 and the second clamping portion 22 to provide a pre-tightening force between the first clamping portion 21 and the second clamping portion 22 to realize clamping.
In the present embodiment, a specific embodiment of clamping the first clamping portion 21 and the second clamping portion 22 by using the elastic band is provided. In this case, both the first clamping portion 21 and the second clamping portion 22 may be movable, and only one of them may be movable. When the article 10 is loaded, the two ends of the elastic bandage are connected between the first clamping part 21 and the second clamping part 22, and the article 10 is clamped by the pretightening force between the first clamping part 21 and the second clamping part 22 provided by the elasticity of the elastic bandage. When unloading the article 10, at least one end of the elastic band is detached from the first grip 21 or the second grip 22, and the article 10 can be unloaded from the carrier vehicle by releasing the grip of the article 10 from the first grip 21 or the second grip 22. The elastic band may also have one end tied to the movable first clamping portion 21 and the second clamping portion 22 in a fixed state, and the other end of the elastic band may be connected to the aircraft body 1, as long as it can provide a pre-tightening force to clamp the first clamping portion 21 and the second clamping portion 22.
Fig. 2 is a schematic external structural diagram of another embodiment of the present invention. As shown in fig. 2, in one embodiment, the clamping device 23 includes a connection lock 231 and a first strap set 232, and a second strap set 233;
the connecting lock 231 is provided on the aircraft body 1 between the first clamping portion 21 and the second clamping portion 22;
the first strap group 232 comprises a first connecting strap 2321 and a second connecting strap 2322, one end of the first connecting strap 2321 is connected with the connecting lock 231 in a matching manner so as to realize connection or disconnection with the first connecting strap 2321 by controlling the connecting lock 231, the other end of the first connecting strap 2321 is connected to the first clamping part 21, one end of the second connecting strap 2322 is connected with the first clamping part 21, and the other end of the second connecting strap 2322 is connected to the aircraft body 1;
In the present embodiment, a specific structure of the nip apparatus 23 is provided. The connection lock 231 may be in an automatic mode or a manual mode, the connection lock 231 may be connected to the first connection strap 2321 and the third connection strap 2331 by a safety belt buckle, or the like, or the connection lock 231 may be connected to the first connection strap 2321 and the third connection strap 2331 by an automatic buckle, and the connection lock 231 may be connected to or disconnected from the first connection strap 2321 and the third connection strap 2331 by an external control. One end of the second connecting band 2322 and one end of the fourth connecting band 2332 are respectively connected to the first clamping portion 21 and the second clamping portion 22, and the other end is connected to the aircraft body 1, so that the first clamping portion 21 and the second clamping portion 22 do not slide on the guide rail 11, and the distance between the first clamping portion 21 and the second clamping portion 22 is fixed, thereby achieving the purpose of clamping the carried article 10. The first connecting band 2321 and the second connecting band 2322, and the third connecting band 2331 and the fourth connecting band 2332 may be elastic connecting bands, in this embodiment, the lengths of the first connecting band 2321 and the second connecting band 2322, and the third connecting band 2331 and the fourth connecting band 2332 may be changed to clamp the articles 10 with different specifications, for example, the length of the second connecting band 2322 and/or the fourth connecting band 2332 may be shortened by winding the second connecting band 2322 and/or the fourth connecting band 2332 around the aircraft body 1, and of course, other mechanisms may be used to adjust the length of the connecting band, and a specific manner of adjusting will not be described herein again. Preferably, the elasticity of the first connecting band 2321 is greater than the elasticity of the second connecting band 2322 to provide better gripping of the article 10.
In an embodiment, the aircraft body 1 comprises at least one guide rail 11 and a power system 12, as well as a first connecting beam 13 and a second connecting beam 14;
the two ends of the guide rail 11 are respectively connected to the middle parts of the first connecting beam 13 and the second connecting beam 14, and the power system 12 is installed on the guide rail 11 and/or the first connecting beam 13 and/or the second connecting beam 14;
the first connecting beam 13 and the first clamping part 21 are arranged on one side of the guide rail 11;
the second connecting beam 14 and the second clamping part 22 are arranged on the other side of the guide rail 11;
the other end of the second connecting strap 2322 is connected with the first connecting beam 13;
the other end of the fourth connecting band 2332 is connected to the second connecting beam 14.
In the present embodiment, a specific structure of the aircraft body 1 is provided, and it is further disclosed how to attach the second connection strap 2322 and the fourth connection strap 2332 to the aircraft body 1.
In one embodiment, the power system 12 includes four rotors 121, and the four rotors 121 are respectively disposed at two ends of the first connecting beam 13 and the second connecting beam 14.
The specific configuration and mounting location of power system 12 is provided in this embodiment.
Fig. 3 is an enlarged schematic view of a portion a of fig. 2 according to the present invention. As shown in fig. 3, in an embodiment, the other end of the second connection strap 2322 is connected to the first connection beam 13 by the rolling device 15;
the winding device 15 comprises a winding wheel 151, a pin seat 152 and a plug 153;
the winding wheel 151 is rotatably connected to the first connecting beam 13, and the other end of the second connecting band 2322 is fixed to the winding wheel 151, so that the winding wheel 151 rotates to drive the second connecting band 2322 to wind around the winding wheel 151 to adjust the length of the second connecting band 2322;
a plurality of positioning holes 1511 are circumferentially arranged on the end face of one end of the winding wheel 151 in the direction around the rotating shaft;
the pin seat 152 is connected to the first connecting beam 13, and a pin hole 1521 is formed in the pin seat 152, so that the pin hole 1521 is in butt joint with one of the positioning holes 1511, and then the plug pin 153 is inserted to realize the rotating positioning of the winding wheel 151, thereby fixing the telescopic length of the second connecting band 2322.
In this embodiment, a specific structure of the winding device 15 is provided, the winding device 15 can adjust the length of the second connection belt 2322, the second connection belt 2322 is wound on the winding wheel 151 by rotating the winding wheel 151 to adjust the length of the second connection belt 2322, then when the second connection belt 2322 is adjusted to an appropriate length, the pin 153 is inserted into the pin hole 1521 of the pin seat 152 at this time, and the positioning hole 1511 on the end face of the winding wheel 151 aligned with the pin hole 1521 at this time, and finally the positioning of the rotation of the winding wheel 151 is completed, and the telescopic length of the second connection belt 2322 is further fixed. It should be noted that the length of the fourth connecting band 2332 can be adjusted by the same rolling device 15, and the length of the second connecting band 2322 and the fourth connecting band 2332 can be adjusted to make the first clamping portion 21 and the second clamping portion 22 at a proper distance, so as to be applied to loading of the articles 10 with different sizes.
In one embodiment, one end of each of the first clamping portion 21 and the second clamping portion 22 is movably connected to the guide rail 11;
the other ends of the first clamping part 21 and the second clamping part 22 are respectively folded towards the space direction between the first clamping part 21 and the second clamping part 22 to form a hook-shaped structure.
In the present embodiment, a specific connection manner of the first clamping portion 21 and the second clamping portion 22 with the guide rail 11 and a specific structure of the first clamping portion 21 and the second clamping portion 22 are provided. It should be noted that the hook structure is to hook an end surface of the article 10, the bending angle of the hook structure is 90 degrees, and the hook structure is located at the bottom of the first clamping portion 21 and the second clamping portion 22 and is used for dragging the bottom surface of the article 10.
In one embodiment, the at least one guide rail 11 is provided in two and same directions, and both ends of each guide rail 11 are respectively connected to the middle portions of the first connecting beam 13 and the second connecting beam 14.
In the present embodiment a specific said carrier vehicle structure is provided with two guide rails 11. The two guide rails 11 are used as cross beams, so that the mechanical properties of the cargo aircraft can be improved. In the embodiment, the connection mode between the guide rail 11 and the first connecting beam 13 and the second connecting beam 14 is also disclosed, and the first connecting beam 13 and the second connecting beam 14 can be arranged perpendicular to the guide rail 11 and form a rectangular frame with the two guide rails 11, obviously, the structure is more stable.
Fig. 4 is a schematic structural view of the first clamping portion of the present invention. As shown in fig. 4, in one embodiment, the first clamping portion 21 includes two hook beams 211 and two moving blocks 212, and a connecting plate 213 and at least one connecting beam 214;
one end of each hook-shaped beam 211 is of the hook-shaped structure, and the other end of each hook-shaped beam 211 is connected with one moving block 212, so that the first clamping part 21 is movably connected to the two guide rails 11 through the two moving blocks 212;
the two hook beams 211 are arranged side by side, and the connecting plate 213 is respectively connected with the two moving blocks 212;
two ends of each connecting beam 214 are respectively connected with the two hook beams 211.
A specific structure of the first clamping portion 21 is provided in the present embodiment. Correspondingly, the second clamping portion 22 may have the same structure as the first clamping portion 21, and may be installed to face each other. The first clamping portion 21 in this embodiment has a structure that the depth of the article 10 can be increased in the fore-and-aft direction of the carrier vehicle, so that the clamping is more stable.
In an embodiment, the aircraft body 1 further comprises a landing gear 16, the landing gear 16 being connected to the rail 11 such that the first and second clip portions 21, 22 effect suspension of the article 10 when the article is gripped.
In the present embodiment, the subject aircraft structure is provided with a landing gear 16. The landing gear 16 not only helps the carrier aircraft to land, but also suspends the article 10 for easy handling.
The above description is only a preferred embodiment of the present invention, and should not be taken as limiting the invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. An cargo aircraft, characterized in that it comprises an aircraft body (1) with a guide rail (11) and a cargo device (2), which cargo device (2) is mounted on the aircraft body (1) for loading or unloading a load-bearing article (10);
the carrying device (2) comprises a first clamping part (21), a second clamping part (22) and a clamping device (23);
the first clamping part (21) and/or the second clamping part (22) is movably connected to the guide rail (11);
the clamping device (23) is connected with the movable first clamping part (21) and/or the movable second clamping part (22) so that the first clamping part (21) and the second clamping part (22) clamp or release the article (10) to load and unload the article.
2. The cargo aircraft according to claim 1, wherein the clamping device (23) is an elastic strap, both ends of which are detachably bound to the first clamping portion (21) and the second clamping portion (22) to provide a pre-tensioning force between the first clamping portion (21) and the second clamping portion (22) for clamping.
3. The cargo aircraft according to claim 1, characterized in that the clamping device (23) comprises a connecting lock (231) and a first strap set (232), and a second strap set (233);
the connection lock (231) is arranged on the aircraft body (1) between the first clamping portion (21) and the second clamping portion (22);
the first strap group (232) comprises a first connecting strap (2321) and a second connecting strap (2322), one end of the first connecting strap (2321) is matched and connected with the connecting lock (231) to achieve connection or disconnection of the connecting lock (231) and the first connecting strap (2321) through control, the other end of the first connecting strap (2321) is connected to the first clamping portion (21), one end of the second connecting strap (2322) is connected with the first clamping portion (21), and the other end of the second connecting strap (2322) is connected to the aircraft body (1);
the second strap group (233) comprises a third connecting strap (2331) and a fourth connecting strap (2332), one end of the third connecting strap (2331) is matched with the connecting lock (231) to be connected so as to realize the connection or disconnection of the connecting lock (231) and the third connecting strap (2331) through control, the other end of the third connecting strap (2331) is connected onto the second clamping portion (22), one end of the fourth connecting strap (2332) is connected with the second clamping portion (22), and the other end of the fourth connecting strap (2332) is connected onto the aircraft body (1).
4. The cargo aircraft according to claim 3, characterized in that the aircraft body (1) comprises at least one of the guide rails (11) and a power system (12), and a first connecting beam (13) and a second connecting beam (14);
the two ends of the guide rail (11) are respectively connected to the middle parts of the first connecting beam (13) and the second connecting beam (14), and the power system (12) is installed on the guide rail (11) and/or the first connecting beam (13) and/or the second connecting beam (14);
the first connecting beam (13) and the first clamping part (21) are arranged on one side of the guide rail (11);
the second connecting beam (14) and the second clamping part (22) are arranged on the other side of the guide rail (11);
the other end of the second connecting belt (2322) is connected with the first connecting beam (13);
the other end of the fourth connecting band (2332) is connected to the second connecting beam (14).
5. The cargo aircraft according to claim 4, characterized in that the power system (12) comprises four rotors (121), the four rotors (121) being respectively arranged at the two ends of the first and second connecting beams (13, 14).
6. The cargo aircraft according to claim 4, characterized in that the other end of the second connecting strap (2322) is connected to the first connecting beam (13) by a take-up (15);
the winding device (15) comprises a winding wheel (151), a pin seat (152) and a plug pin (153);
the winding wheel (151) is rotatably connected to the first connecting beam (13), and the other end of the second connecting belt (2322) is fixed to the winding wheel (151), so that the second connecting belt (2322) is driven to wind the winding wheel (151) when the winding wheel (151) rotates to adjust the length of the second connecting belt (2322);
a plurality of positioning holes (1511) are circumferentially arranged on the end face of one end of the winding wheel (151) around the rotating direction;
the pin seat (152) is connected to the first connecting beam (13), a pin hole (1521) is formed in the pin seat (152), so that the pin hole (1521) is connected with one of the positioning holes (1511) in a butt joint mode and then is inserted into the pin (153) to achieve rotating positioning of the winding wheel (151), and further the telescopic length of the second connecting band (2322) is fixed.
7. The cargo aircraft according to any one of claims 4-6, characterized in that one end of the first clip part (21) and one end of the second clip part (22) are each movably connected to the rail (11);
the other ends of the first clamping part (21) and the second clamping part (22) are respectively folded towards the space direction between the first clamping part (21) and the second clamping part (22) to form a hook-shaped structure.
8. The cargo aircraft according to claim 7, characterized in that said at least one guide rail (11) is provided in two and co-directional arrangements, and each of said guide rails (11) has two ends connected to the middle of said first connecting beam (13) and said second connecting beam (14), respectively.
9. The cargo aircraft according to claim 8, characterized in that the first grip (21) comprises two hook-shaped beams (211) and two moving masses (212), as well as a connecting plate (213) and at least one connecting beam (214);
one end of each hook-shaped beam (211) is of the hook-shaped structure, and the other end of each hook-shaped beam is connected with one moving block (212) so that the first clamping part (21) is movably connected to the guide rail (11) through the moving block (212);
the two hook-shaped beams (211) are arranged side by side, and the connecting plate (213) is respectively connected with the two moving blocks (212); two ends of each connecting beam (214) are respectively connected to the two hook-shaped beams (211).
10. The cargo aircraft according to claim 1, characterized in that the aircraft body (1) further comprises a landing gear (16), the landing gear (16) being connected to the guide rail (11) so that the article (10) is suspended when the first and second grip portions (21, 22) grip the article.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021382627.5U CN213262924U (en) | 2020-07-14 | 2020-07-14 | Carry thing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021382627.5U CN213262924U (en) | 2020-07-14 | 2020-07-14 | Carry thing aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213262924U true CN213262924U (en) | 2021-05-25 |
Family
ID=75960055
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202021382627.5U Active CN213262924U (en) | 2020-07-14 | 2020-07-14 | Carry thing aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN213262924U (en) |
-
2020
- 2020-07-14 CN CN202021382627.5U patent/CN213262924U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102037237B (en) | Tip end bracket | |
| US10024299B2 (en) | Method and apparatus for transporting wind turbine blades | |
| KR20140053902A (en) | A container handling and flow system, use thereof and method of handling containers | |
| CN213262924U (en) | Carry thing aircraft | |
| CN112173353A (en) | Self-clamping type logistics tray | |
| US20130087430A1 (en) | Material handling station | |
| US6799933B1 (en) | Freight load pallet carrier and method for distributing freight load pallets | |
| CN210214192U (en) | Commodity circulation discharge devices | |
| US10245998B2 (en) | Load restraining apparatus and method | |
| CN210149786U (en) | Transport frame of mobile robot | |
| CN215515451U (en) | Self-locking traction device for tooling trolley | |
| CN109455463A (en) | Extendable conveyor | |
| CN207258411U (en) | A kind of container | |
| CN214112610U (en) | Stable component transport vehicle | |
| CN109455462A (en) | Extendable conveyor | |
| CN212074461U (en) | Trailer | |
| CN219790006U (en) | Container is transferred and is used cargo airplane | |
| CN210126722U (en) | Packaging and transporting device of mobile robot | |
| CN219859551U (en) | Full-automatic transfer loading line | |
| CN216374357U (en) | Express delivery transport vechicle goods fixing device | |
| CN117088157B (en) | Railway transportation connects and unloads device | |
| CN217867673U (en) | Spare part overhead hoist that fork truck used | |
| CN213569107U (en) | Cabin transportation handling device | |
| CN109956164B (en) | Logistics cargo carrying device based on Internet of things | |
| CN218708517U (en) | Long part bundle loading and transporting structure of automobile |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |