CN217100481U - Aircraft with a flight control device - Google Patents
Aircraft with a flight control device Download PDFInfo
- Publication number
- CN217100481U CN217100481U CN202220606343.2U CN202220606343U CN217100481U CN 217100481 U CN217100481 U CN 217100481U CN 202220606343 U CN202220606343 U CN 202220606343U CN 217100481 U CN217100481 U CN 217100481U
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- aircraft
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- support frame
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- connector
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Abstract
The utility model provides an aircraft. The aircraft comprises a supporting frame and a shell, wherein the shell comprises a fixed part and a movable part, the supporting frame is fixedly connected with the fixed part, the movable part comprises two opposite ends, one end of the movable part is pivoted with one of the supporting frame and the fixed part, and the other end of the movable part is correspondingly detachably connected with the fixed part or the supporting frame. Aircraft frame is convenient for the aircraft and is changed battery and not fragile aircraft casing.
Description
Technical Field
The utility model relates to an aircraft technical field, in particular to aircraft.
Background
The aircraft comprises a shell and a support frame, wherein the shell is fixedly connected with the support frame and covers at least part of the support frame. Therefore, the support frame can be protected, and the appearance of the aircraft can be beautified.
In the prior art, the aircraft casing is an overall structure, can not split, aircraft casing and aircraft support frame fixed connection, in the equipment mode of aircraft casing, when the installation or when taking out the aircraft battery, need with the aircraft casing with the aircraft support frame separates completely, and this mode makes the installation of aircraft battery is inconvenient, and because the aircraft battery needs frequent change, so the aircraft casing needs frequent dismantlement, makes the aircraft casing fragile.
SUMMERY OF THE UTILITY MODEL
The utility model discloses a solve the technical problem that above-mentioned exists, provide an aircraft convenient to battery and aircraft casing are not fragile is changed to the aircraft.
The utility model provides an aircraft, including support frame and casing, the casing includes fixed part and movable part, the support frame with fixed part fixed connection, the movable part includes two looks remote terminals, wherein one end with the support frame with one of the two pin joints in the fixed part, simultaneously the other end of movable part correspond with the connection can be dismantled to fixed part or support frame.
Preferably, the fixed part comprises a first connecting piece, the movable part comprises a second connecting piece, and the fixed part and the movable part are detachably connected through the cooperation of the first connecting piece and the second connecting piece.
Preferably, the support frame comprises a first connecting piece, the movable part comprises a second connecting piece, and the support frame and the movable part are matched through the first connecting piece and the second connecting piece to realize detachable connection.
Preferably, the movable part further comprises a key, and the key is fixedly assembled with the movable part and fixedly connected with the second connecting piece.
Preferably, the key includes a pressing body, an elastic body and a fixing member, the pressing body accommodates the elastic body, the elastic body is clamped between the pressing body and the fixing member, the fixing member is fixedly assembled with the movable portion, and the pressing body is fixedly connected with the second connecting member.
Preferably, the pressing body includes a pressing end and a pressing post, the pressing end accommodates the pressing post and the elastic body, the pressing end is connected to the pressing post, the elastic body is sleeved outside the pressing post, and the pressing post and the fixing member are arranged at an interval.
Preferably, the fixing member includes a base and a stopper which are perpendicular to each other, and the base and the movable portion are fixedly assembled by bolts.
Preferably, the movable portion further includes a first through hole, and the first through hole receives the key.
Preferably, the base includes a second through hole, the movable portion further includes a limiting member corresponding to the second through hole, and the bolt fixes the base and the movable portion through the second through hole and the limiting member.
Preferably, the fixed part comprises a shaft body, and the fixed part and the movable part are pivoted through the shaft body.
Compared with the prior art, the casing comprises a fixed part and a movable part, the support frame is fixedly connected with the fixed part, the movable part comprises two opposite ends, one end of the movable part is pivoted with the support frame and one of the two of the fixed parts, and the other end of the movable part corresponds to the fixed part or the support frame and is detachably connected with the movable part. The movable part is separated from or combined with the fixed part or the support frame through the first connecting piece and the second connecting piece, meanwhile, the movable part is pivoted with the fixed part or the support frame, so that the casing is not required to be detached from the support frame, the battery is convenient to install and replace, the battery is required to be replaced frequently, the casing is not required to be detached from the support frame, the first connecting piece is separated from or connected with the second connecting piece through operating the key, the movable part is in an open or closed state, and therefore the casing is not easy to damage even if the battery is replaced frequently.
Drawings
FIG. 1 is a schematic perspective view of an aircraft according to a first embodiment of the present invention;
FIG. 2 is a schematic perspective view of the housing of FIG. 1;
FIG. 3 is an exploded view and a partially enlarged view of the housing shown in FIG. 2;
FIG. 4 is an exploded perspective view of the second connecting member and the key shown in FIG. 3;
FIG. 5 is a schematic perspective view of the moveable member of FIG. 3;
FIGS. 6a and 6b are perspective views of the aircraft according to the first embodiment in two operating states;
FIG. 7 is a schematic perspective view and a partially enlarged view of an aircraft according to a second embodiment of the present invention;
fig. 8a and 8b are perspective views of the aircraft according to the second embodiment in two operating states.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely below, and it should be apparent that the described embodiments are only some embodiments of the present invention, but not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.
First embodiment
Please refer to fig. 1, which is a schematic perspective view of an aircraft according to a first embodiment of the present invention. The aircraft 100 comprises a shell 10, a support frame 20, a power system 30 and a propeller 40, wherein the shell 10 is connected with the support frame 20, the support frame 20 is fixedly assembled with the power system 30, and the power system 30 is fixedly assembled with the propeller 40.
Referring to fig. 1 and fig. 2, fig. 1 is a schematic perspective view of an aircraft according to a first embodiment of the present invention, and fig. 2 is a schematic perspective view of a housing shown in fig. 1. The casing 10 includes a fixed portion 11 and a movable portion 13, the fixed portion 11 is fixedly connected to the supporting frame 20, one end of the movable portion 13 is pivotally connected to the supporting frame 20, and the other end is detachably connected to the fixed portion 11.
Fig. 3 is a schematic exploded view and a partial enlarged view of the housing shown in fig. 2. The fixed part 11 comprises a fixed part 111 and a first connecting piece 113, and the fixed part 111 is fixedly connected with the first connecting piece 113; the movable portion 13 includes a second connecting member 131, a button 133 and a movable member 135, wherein the button 133 is fixedly assembled with the movable member 135 and fixedly connected with the second connecting member 131; the first connecting piece 113 and the second connecting piece 131 are correspondingly arranged, and the fixed part 11 and the movable part 13 are detachably connected through the cooperation of the first connecting piece 113 and the second connecting piece 131.
The first connecting member 113 includes a first connecting portion 1131 and a first hooking portion 1133, the first connecting portion 1131 and the first hooking portion 1133 are integrated, the first connecting portion 1131 is fixedly connected to the fixing member 111, and the first hooking portion 1133 is detachably connected to the second connecting member 131.
Please refer to fig. 4, which is a schematic exploded perspective view of the second connecting member and the key shown in fig. 3. The second connector 131 includes a second connection portion 1311 and a second hooking portion 1313, the second connection portion 1311 and the second hooking portion 1313 are integrated, the second connection portion 1311 and the key 133 are integrated or fixed, and the second hooking portion 1313 and the first hooking portion 1133 are hooked. First connecting piece 113 with second connecting piece 131 both can be the hook and connect, also can be through magnet, the setting is connected to the electro-magnet mode.
The key 133 includes a pressing body 1331, an elastic body 1333 and a fixing body 1335, the pressing body 1331 receives the elastic body 1333, the elastic body 1333 is sandwiched between the pressing body 1331 and the fixing body 1335, the second connecting portion 1311 is fixedly connected to the surface of the pressing body 1331, as an integral structure, the fixing body 1335 and the movable element 135 are fixedly assembled by the bolt, as shown in fig. 5, the movable element 135 includes a first through hole 1351, and the first through hole 1351 is disposed corresponding to the key 133 and receives the key 133.
The pressing body 1331 includes a pressing end portion 13311 and a pressing post 13313, the pressing end portion 13311 receives the pressing post 13313 and the elastic body 1333, the pressing end portion 13311 and the pressing post 13313 are integrated, the elastic body 1333 is sleeved outside the pressing post 13313, and the pressing post 13313 and the fixing body 1335 are spaced apart from each other.
The elastic body 1333 includes a first end 13331 and a second end 13333, the first end 13331 is fixedly connected to the pressing end 13311, and the second end 13333 is fixedly connected to the fixing body 1335.
The fixing body 1335 includes a base 13351 and a stop 13353 vertically disposed, the base 13351 is fixedly connected to the stop 13353, the base 13351 is fixedly assembled to the movable element 135 through bolts, the stop 13353 is fixedly connected to the second end 13333, and the pressing columns 13313 are disposed at intervals.
As shown in fig. 5, the base 13351 includes a second through hole 133511, and the movable member 135 includes a retaining member 1353 corresponding to the second through hole 133511, and the bolt fixes the base 13351 and the movable member 135 through the second through hole 133511 and the retaining member 1353.
Referring to fig. 6a and 6b, fig. 6a is a state diagram of the aircraft with the movable portion of the first embodiment in a closed state, and fig. 6b is a state diagram of the aircraft with the movable portion of the first embodiment in an open state.
Second embodiment
The second embodiment is different from the first embodiment in that, as shown in fig. 7, one end of the movable portion 23 is pivotally connected to the fixed portion 21, and the other end is detachably connected to the supporting frame 25.
The fixed portion 21 further includes a shaft body 211, and the fixed portion 21 and the movable portion 23 are pivotally connected through the shaft body 211.
Referring to fig. 8a and 8b, fig. 8a is a state diagram of the aircraft with the movable portion of the second embodiment in a closed state, and fig. 8b is a state diagram of the aircraft with the movable portion of the second embodiment in an open state.
Compared with the prior art, the casing 10 includes the fixed part 11 and the movable part 13, the support frame 20 with the fixed part 11 fixed connection, the movable part 13 includes two opposite ends, one of them end with the support frame 20 with one of the two pin joints in the fixed part 11, simultaneously the other end of the movable part 13 correspond with the fixed part 11 or the support frame 20 can be dismantled and be connected. The movable part 13 is separated from or combined with the fixed part 11 or the support frame 20 through the first connecting piece 113 and the second connecting piece 131, meanwhile, the movable part 13 is pivoted with the fixed part 11 or the support frame 20, so the casing 10 does not need to be detached from the support frame, the battery is convenient to install and replace, the battery needs to be replaced frequently, and the casing 10 does not need to be detached from the support frame 20, but the first connecting piece 113 is separated from or connected with the second connecting piece 131 through operating the key 133, so the movable part 13 is in an open state or a closed state, and therefore, even if the battery is replaced frequently, the casing 10 is not easy to damage.
The above only is some embodiments of the present invention, not so limiting the scope of the present invention, and all the equivalent structures or equivalent flow changes made by using the contents of the specification and drawings of the present invention or directly or indirectly applied to other related technical fields are included in the same way in the protection scope of the present invention.
Claims (10)
1. An aircraft, characterized in that, including support frame and casing, the casing includes fixed part and movable part, the support frame with fixed connection, the movable part includes two opposite ends, wherein one end with the pivot joint of the support frame with either one of the fixed part or the support frame, the other end of the movable part corresponds and can dismantle with fixed part or support frame and be connected.
2. The aircraft of claim 1, wherein the fixed portion comprises a first connector and the movable portion comprises a second connector, and the fixed portion and the movable portion are detachably connected by the first connector and the second connector.
3. The aircraft of claim 1, wherein the support frame comprises a first connector, the movable portion comprises a second connector, and the support frame and the movable portion are detachably connected by the first connector and the second connector in a matching manner.
4. The aircraft according to claim 2 or 3, characterized in that said mobile portion further comprises a key, said key being fixedly assembled with said mobile portion and fixedly connected with said second connection element.
5. The aircraft of claim 4, wherein the key comprises a pressing body, an elastic body and a fixing piece, the pressing body accommodates the elastic body, the elastic body is clamped between the pressing body and the fixing piece, the fixing piece is fixedly assembled with the movable part, and the pressing body is fixedly connected with the second connecting piece.
6. The aircraft of claim 5, wherein the pressing body comprises a pressing end and a pressing post, the pressing end receives the pressing post and the elastic body, the pressing end is connected to the pressing post, the elastic body is sleeved outside the pressing post, and the pressing post is spaced from the fixing member.
7. The aircraft of claim 6, wherein the fixed part comprises a base and a stop block which are arranged perpendicularly to each other, and the base and the movable part are fixedly assembled through bolts.
8. The aircraft of claim 7, wherein the movable portion further comprises a first through hole, the first through hole receiving the key.
9. The aircraft of claim 8, wherein the base comprises a second through hole, the movable portion further comprises a stopper corresponding to the second through hole, and the bolt fixes the base and the movable portion through the second through hole and the stopper.
10. The aircraft of claim 1, wherein the stationary portion comprises a shaft, and the stationary portion is pivotally connected to the movable portion via the shaft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220606343.2U CN217100481U (en) | 2022-03-18 | 2022-03-18 | Aircraft with a flight control device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220606343.2U CN217100481U (en) | 2022-03-18 | 2022-03-18 | Aircraft with a flight control device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217100481U true CN217100481U (en) | 2022-08-02 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202220606343.2U Active CN217100481U (en) | 2022-03-18 | 2022-03-18 | Aircraft with a flight control device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217100481U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115446706A (en) * | 2022-08-29 | 2022-12-09 | 浙江明磊锂能源科技股份有限公司 | Shell assembly of electric tool and electric tool |
-
2022
- 2022-03-18 CN CN202220606343.2U patent/CN217100481U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115446706A (en) * | 2022-08-29 | 2022-12-09 | 浙江明磊锂能源科技股份有限公司 | Shell assembly of electric tool and electric tool |
| CN115446706B (en) * | 2022-08-29 | 2024-04-23 | 浙江明磊锂能源科技股份有限公司 | Electric tool |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20230425 Address after: Room 532, 5th Floor, Block C, Zhongxing Industrial City, Chuangye Road, Nanshan Street, Nanshan District, Shenzhen City, Guangdong Province, 518054 Patentee after: Shenzhen Xiaopan Technology Co.,Ltd. Address before: Building 1-6, No. 25 South Industrial Avenue, Xiaolan Town, Zhongshan City, Guangdong Province, 528400 Patentee before: Zhongshan Gutian Technology Innovation Co.,Ltd. |