CN204055910U - Can the multi-rotor aerocraft of fast folding - Google Patents
Can the multi-rotor aerocraft of fast folding Download PDFInfo
- Publication number
- CN204055910U CN204055910U CN201420573886.4U CN201420573886U CN204055910U CN 204055910 U CN204055910 U CN 204055910U CN 201420573886 U CN201420573886 U CN 201420573886U CN 204055910 U CN204055910 U CN 204055910U
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- China
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- strut bar
- wing
- seat
- snap fastener
- rotor aerocraft
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- 238000010586 diagram Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
Abstract
A kind of can the multi-rotor aerocraft of fast folding, it is characterized in that, include and be with the main body of multiple wing seat, one end swings the wing being connected to strut bar on each wing seat end, being arranged on the wing mount pad on the strut bar other end and being arranged on wing mount pad by oscillating axle; Arc planing surface and strut bar expansion locating notch is provided with in described post upper portion; Expansion positioning snap fastener is provided with in the chute of described wing seat; The elastic reset part making expansion locating button release reset to contact with this arc planing surface is provided with in described wing mount pad, locating button is launched as long as back pull when folding strut bar, and launch locating button when launching without the need to operation, as long as pull strut bar, this is compared with current needs manual manipulation button, the multi-rotor aerocraft that another manual manipulation strut bar could launch, more reasonable structure of the present utility model, folding are faster and more convenient.
Description
Technical field
The utility model relates to a kind of aircraft, refers in particular to the aircraft of multiple rotor.
Background technology
Aloft photograph, on the field such as agricultural aerial spraying or model airplane, all may use multi-rotor aerocraft.Multi-rotor aerocraft needs to launch whole rotor in use, then wants folding when not using or collecting.Current, multi-rotor aerocraft operates more loaded down with trivial details, time-consuming when folding, and still wants operation push-button just can carry out when using upon deployment, and directly can not pull wing strut bar, therefore current multi-rotor aerocraft folding structure more complicated, inconvenient operation.
Summary of the invention
The purpose of this utility model is to overcome the deficiencies in the prior art, provides the more convenient and multi-rotor aerocraft efficiently of a kind of more reasonable structure, folding.
In order to solve the technical matters of above-mentioned existence, the utility model adopts following technical proposals:
A kind of can the multi-rotor aerocraft of fast folding, it is characterized in that, include and be with the main body of multiple wing seat, one end swings the wing being connected to strut bar on each wing seat end, being arranged on the wing mount pad on the strut bar other end and being arranged on wing mount pad by oscillating axle; Arc planing surface and strut bar expansion locating notch is provided with in described post upper portion; Expansion positioning snap fastener is provided with in the chute of described wing seat; The elastic reset part making expansion locating button release reset to contact with this arc planing surface is provided with in described wing mount pad.
To above-mentioned can fast folding multi-rotor aerocraft improvement project in, described main body includes the upper and lower fixing plate being with multiple fin, and the supporting seat between the corresponding fin being clipped in upper and lower fixing plate; Described supporting seat is made up of left and right supporting seat; The oscillating axle two ends of described strut bar are inserted into the axis hole of U-shaped breach both sides of strut bar respectively after the axis hole of left and right supporting seat stretches out; Described expansion positioning snap fastener two ends are exposed respectively from the chute of this left and right supporting seat; Described elastic reset part is enclosed within and launches after on the vertical pin be fixedly connected with of positioning snap fastener, and its other end leans on right support seat.
To above-mentioned can fast folding multi-rotor aerocraft improvement project in, described oscillating axle and launch positioning snap fastener be parallel to each other, described pin be connected to launch positioning snap fastener center line on.
Compared with prior art, the beneficial effects of the utility model are: as long as launch locating button because it back pulls when folding strut bar, and launch locating button when launching without the need to operation, as long as pull strut bar, this is compared with current needs manual manipulation button, the multi-rotor aerocraft that another manual manipulation strut bar could launch, more reasonable structure of the present utility model, folding are faster and more convenient.
Below in conjunction with accompanying drawing and detailed description of the invention, the utility model is described in further detail:
[accompanying drawing explanation]
Fig. 1 is the schematic diagram that the entirety of the utility model embodiment launches when using;
Fig. 2 is the folding structure schematic perspective view (during deployed condition) of one of them rotor of the utility model embodiment;
Fig. 3 is the folding structure schematic perspective view (during folding state) of one of them rotor of the utility model embodiment;
Fig. 4 is the assembling schematic diagram of the folding structure of one of them rotor of the utility model embodiment;
Fig. 5 is the partial enlarged drawing of Fig. 4 at I place.
[detailed description of the invention]
The utility model be a kind of can the multi-rotor aerocraft of fast folding, as shown in Fig. 1 to 5, the wing 5 that it includes and is with the main body 1 of multiple wing seat 11, one end swings by oscillating axle 2 strut bar 3 be connected on each wing seat 11 end, is arranged on the wing mount pad 4 on strut bar 3 other end and is arranged on wing mount pad 4, is provided with arc planing surface 31 in described strut bar 3 upper end and strut bar launches locating notch 32; Be provided with in the chute 111 of described wing seat 11 and launch positioning snap fastener 6; The elastic reset part 7 making expansion locating button 6 release reset to contact with this arc planing surface 31 is provided with in described wing mount pad 4.Multi-rotor aerocraft, when flying, launches locating button 6 and is slipped in the strut expansion locating notch 32 of strut bar 3 under the effect of elastic reset part 7, as shown in Figure 2; When wanting folding multi-rotor aerocraft to collect or carry, pinch with hand and launching positioning snap fastener 6 also draws toward the direction of the expansion locating notch 32 deviating from strut bar, when launching positioning snap fastener 6 and leaving expansion locating notch 32, just can carry out folding by swinging support bar downwards, be the state after strut bar folding completes as shown in Figure 3, at this moment launch positioning snap fastener 6 and be resisted against on the arc planing surface 31 of strut bar; And when wanting expansion supporting rod, as long as pull it to make it up to swing, at this moment arc planing surface 31 relative sliding of positioning snap fastener 6 along strut bar is launched, until launch positioning snap fastener 6 to be slipped to the expansion completing strut bar when launching in locating notch 32, as shown in Figure 2.
As can be seen from above, locating button is launched as long as back pull when folding strut bar, and launch locating button when launching without the need to operation, as long as pull strut bar, this is compared with current needs manual manipulation button, the multi-rotor aerocraft that another manual manipulation strut bar could launch, more reasonable structure of the present utility model, folding are faster and more convenient.
In the present embodiment, as shown in Figure 4,5, described main body 1 includes the upper and lower fixing plate 12,13 being with multiple fin, and the supporting seat 14 between the corresponding fin being clipped in upper and lower fixing plate 12,13, these two fins and supporting seat constitute the wing seat of main body, and this can alleviate the weight of main body and reduce costs; Described supporting seat 14 is made up of left and right supporting seat 141,142; Oscillating axle 2 two ends of described strut bar 3 are inserted into the axis hole 33 of U-shaped breach both sides of strut bar 3 respectively after the axis hole 1411,1421 of left and right supporting seat 141,142 stretches out, and are fixed by screw 8; Described expansion positioning snap fastener 6 two ends are exposed respectively from the chute 111 of this left and right supporting seat 141,142; Described elastic reset part 7 is enclosed within and launches after on the vertical pin 9 be fixedly connected with of positioning snap fastener 6, and its other end leans on right support seat 142.Elastic reset part 7 can be spring, Elastic flexible glue cover etc.
Preferably, as shown in Figure 4,5, described oscillating axle 2 and launch positioning snap fastener 6 and be parallel to each other, described pin 9 be connected to launch positioning snap fastener 6 center line on, the stressed of expansion positioning snap fastener 6 can be made like this evenly, slide more steady.
Although reference above embodiment describes the utility model in detail, but be it will be apparent to one skilled in the art that by the disclosure, when not departing from principle of the present utility model and the scope of claim restriction, can make a variety of changes the utility model or revise.Therefore, the detailed description of disclosure embodiment is only used for explaining, instead of is used for limiting the utility model, but is defined by the subject-matter of the claims the scope of protection.
Claims (3)
1. one kind can the multi-rotor aerocraft of fast folding, it is characterized in that, include and be with the main body of multiple wing seat, one end swings the wing being connected to strut bar on each wing seat end, being arranged on the wing mount pad on the strut bar other end and being arranged on wing mount pad by oscillating axle; Arc planing surface and strut bar expansion locating notch is provided with in described post upper portion; Expansion positioning snap fastener is provided with in the chute of described wing seat; The elastic reset part making expansion locating button release reset to contact with this arc planing surface is provided with in described wing mount pad.
2. according to claim 1 can the multi-rotor aerocraft of fast folding, it is characterized in that, described main body includes the upper and lower fixing plate being with multiple fin, and the supporting seat between the corresponding fin being clipped in upper and lower fixing plate; Described supporting seat is made up of left and right supporting seat; The oscillating axle two ends of described strut bar are inserted into the axis hole of U-shaped breach both sides of strut bar respectively after the axis hole of left and right supporting seat stretches out; Described expansion positioning snap fastener two ends are exposed respectively from the chute of this left and right supporting seat; Described elastic reset part is enclosed within and launches after on the vertical pin be fixedly connected with of positioning snap fastener, and its other end leans on right support seat.
3. according to claim 2 can the multi-rotor aerocraft of fast folding, it is characterized in that, described oscillating axle and launch positioning snap fastener and be parallel to each other, described pin be connected to launch positioning snap fastener center line on.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420573886.4U CN204055910U (en) | 2014-10-08 | 2014-10-08 | Can the multi-rotor aerocraft of fast folding |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420573886.4U CN204055910U (en) | 2014-10-08 | 2014-10-08 | Can the multi-rotor aerocraft of fast folding |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204055910U true CN204055910U (en) | 2014-12-31 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420573886.4U Active CN204055910U (en) | 2014-10-08 | 2014-10-08 | Can the multi-rotor aerocraft of fast folding |
Country Status (1)
| Country | Link |
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| CN (1) | CN204055910U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105292442A (en) * | 2015-10-28 | 2016-02-03 | 亳州市智航航空植保科技有限公司 | Rapid wing folding piece |
-
2014
- 2014-10-08 CN CN201420573886.4U patent/CN204055910U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105292442A (en) * | 2015-10-28 | 2016-02-03 | 亳州市智航航空植保科技有限公司 | Rapid wing folding piece |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |