CN207985223U - A kind of unmanned plane internal protection mechanism - Google Patents
A kind of unmanned plane internal protection mechanism Download PDFInfo
- Publication number
- CN207985223U CN207985223U CN201820347739.3U CN201820347739U CN207985223U CN 207985223 U CN207985223 U CN 207985223U CN 201820347739 U CN201820347739 U CN 201820347739U CN 207985223 U CN207985223 U CN 207985223U
- Authority
- CN
- China
- Prior art keywords
- fuselage
- rotating bar
- protection mechanism
- rubber sleeve
- unmanned plane
- 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.)
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Abstract
The utility model discloses a kind of unmanned plane internal protection mechanisms,Including fuselage,Wing,Electric cabinet,Control panel,Protection mechanism,Circuit board and accumulator,The correspondence both sides of the fuselage are mounted on wing,The bottom interior wall of the fuselage is equipped with circuit board,The inside of the fuselage is equipped with protection mechanism,The protection mechanism is by sliding slot,Fixed link,Resetting spring,Connecting rod,Sliding block,Rotating bar,Rubber sleeve,Cushion hole,Damping spring,Fixture block,Shaft and through-hole composition,The correspondence both sides of the fuselage offer sliding slot,It is welded with fixed link at the bottom centre of the sliding slot,The top of the fixed link is connected with rotating bar by articulate,One end of the rotating bar is bonded with fixture block by seccotine,The bottom end of the rotating bar is connect by rubber sleeve with fuselage bottom inner wall,Several cushion holes are offered on the outside of the rubber sleeve,The mechanism,Be conducive to protection circuit plates.
Description
Technical field
The utility model is related to unmanned plane safeguard technical field, specially a kind of unmanned plane internal protection mechanism.
Background technology
Referred to as " unmanned plane ", english abbreviation is " UAV " to UAV, using radio robot and is provided for oneself
The not manned aircraft that presetting apparatus manipulates, or fully or intermittently automatically operated by car-mounted computer.But one
As unmanned aerial vehicle body inside be not provided with protection mechanism, since circuit board is mounted on the inside of fuselage, if be not provided with pair
The mechanism of circuit board protection, when unmanned plane is repeatedly landed, it is easy to it causes inner body to fall and smashes circuit board, for
This defect, so we design a kind of unmanned plane internal protection mechanism, to improve the safety of circuit board.
Utility model content
The purpose of this utility model is to provide a kind of unmanned plane internal protection mechanisms, to solve in above-mentioned background technology
The problem of proposition.
In order to solve the above-mentioned technical problem, the utility model provides the following technical solutions：A kind of unmanned plane internal protection
The correspondence both sides of mechanism, including fuselage, wing, electric cabinet, control panel, protection mechanism, circuit board and accumulator, the fuselage are equal
Wing is installed, the bottom interior wall of the fuselage is equipped with circuit board, and the inside of the fuselage is equipped with protection mechanism, the guarantor
Protect mechanism by sliding slot, fixed link, resetting spring, connecting rod, sliding block, rotating bar, rubber sleeve, cushion hole, damping spring, fixture block,
Shaft and through-hole composition, the correspondence both sides of the fuselage offer sliding slot, are welded at the bottom centre of the sliding slot
The top of fixed link, the fixed link is connected with rotating bar by articulate, and one end of the rotating bar passes through strength gluing
It is connected to fixture block, the bottom end of the rotating bar is connect with fuselage bottom inner wall by rubber sleeve, opened on the outside of the rubber sleeve
Equipped with several cushion holes, the inside of the rubber sleeve is socketed with damping spring, and the outside of the rotating bar is socketed sliding block, described
The side of sliding block offers through-hole, and the correspondence both sides of the sliding slot are connected by shaft, and connection is socketed on the outside of the shaft
One end of bar, the connecting rod is connect by welding with sliding block side, and the side of the connecting rod passes through resetting spring and sliding slot
Side connects.
Further, electric cabinet has been screwed at the top of the fuselage, the side of the electric cabinet passes through screw
It is fixed with control panel, the inside of the electric cabinet is equipped with accumulator.
Further, the rubber sleeve is connect by seccotine with rotating bar.
Further, the shaft is connect by bearing with fuselage.
Further, the resetting spring is connect by welding with connecting rod.
Further, the connecting rod is connect by welding with shaft.
Compared with prior art, the advantageous effect that the utility model is reached is：The protection mechanism, when the zero of fuselage interior
It when part falls, pounds in rotating bar, rotating bar compresses rubber sleeve, due to the setting of cushion hole and damping spring, offsets
The power that partial rubber set is received, while when rotating bar rotates down, band movable slider moves downward, and connecting rod is made to rotate, to resetting bullet
Spring is compressed, and due to the resiliency characteristics of resetting spring, plays cushioning effect, is offset to the power that rotating bar moves downward,
Play the role of damping, is conducive to protect circuit board.
Description of the drawings
Attached drawing is used to provide a further understanding of the present invention, and a part for constitution instruction, with this practicality
Novel embodiment for explaining the utility model, does not constitute limitations of the present invention together.In the accompanying drawings：
Fig. 1 is the overall structure diagram of the utility model；
Fig. 2 is the fuselage interior structural schematic diagram of the utility model；
Fig. 3 is the rubber sleeve internal structure schematic diagram of the utility model；
Fig. 4 is the sliding block internal structure schematic diagram of the utility model；
Fig. 5 is the electric cabinet internal structure schematic diagram of the utility model；
In figure：1- fuselages；2- wings；3- electric cabinets；4- control panels；5- sliding slots；6- fixed links；7- resetting springs；8- connects
Extension bar；9- sliding blocks；10- rotating bars；11- rubber sleeves；12- cushion holes；13- damping springs；14- fixture blocks；15- shafts；16- is logical
Hole；17- protection mechanisms；18- circuit boards；19- accumulators.
Specific implementation mode
The following will be combined with the drawings in the embodiments of the present invention, carries out the technical scheme in the embodiment of the utility model
Clearly and completely describe, it is clear that the described embodiments are only a part of the embodiments of the utility model, rather than whole
Embodiment.Based on the embodiments of the present invention, those of ordinary skill in the art are without making creative work
The every other embodiment obtained, shall fall within the protection scope of the present invention.
- 5 are please referred to Fig.1, the utility model provides a kind of technical solution：A kind of unmanned plane internal protection mechanism, including
Pacify the correspondence both sides of fuselage 1, wing 2, electric cabinet 3, control panel 4, protection mechanism 17, circuit board 18 and accumulator 19, fuselage 1
Equipped with wing 2, the bottom interior wall of fuselage 1 is equipped with circuit board 18, and the inside of fuselage 1 is equipped with protection mechanism 17, protection mechanism
17 by sliding slot 5, fixed link 6, resetting spring 7, connecting rod 8, sliding block 9, rotating bar 10, rubber sleeve 11, cushion hole 12, damping spring
13, fixture block 14, shaft 15 and through-hole 16 form, and the correspondence both sides of fuselage 1 offer sliding slot 5, are welded at the bottom centre of sliding slot 5
It connects and is fixed with fixed link 6, the top of fixed link 6 is connected with rotating bar 10 by articulate, and one end of rotating bar 10 passes through strong
Power gluing is connected to fixture block 14, and the bottom end of rotating bar 10 is connect by rubber sleeve 11 with 1 bottom interior wall of fuselage, rubber sleeve 11
Outside offers several cushion holes 12, and the inside of rubber sleeve 11 is socketed with damping spring 13, and the outside socket of rotating bar 10 is slided
The side of block 9, sliding block 9 offers through-hole 16, and the correspondence both sides of sliding slot 5 are connected by shaft 15, and the outside of shaft 15 is socketed with
One end of connecting rod 8, connecting rod 8 is connect by welding with 9 side of sliding block, and the side of connecting rod 8 passes through resetting spring 7 and sliding slot
5 sides connect, and are conducive to protection circuit plates 18.
Further, the top of fuselage 1 has been screwed electric cabinet 3, and the side of electric cabinet 3 has been screwed
The inside of control panel 4, electric cabinet 3 is equipped with accumulator 19.
Further, rubber sleeve 11 is connect by seccotine with rotating bar 10, is conducive to connect.
Further, shaft 15 is connect by bearing with fuselage 1, is conducive to the rotation of shaft 15.
Further, resetting spring 7 is connect by welding with connecting rod 8, keeps connection more firm.
Further, connecting rod 8 is connect by welding with shaft 15, keeps connection more firm.
Operation principle：The correspondence both sides of fuselage 1 offer sliding slot 5, and fixation is welded at the bottom centre of sliding slot 5
The top of bar 6, fixed link 6 is connected with rotating bar 10 by articulate, and one end of rotating bar 10 is bonded with card by seccotine
The bottom end of block 14, rotating bar 10 is connect by rubber sleeve 11 with 1 bottom interior wall of fuselage, if the outside of rubber sleeve 11 offers
A dry cushion hole 12, the inside of rubber sleeve 11 are socketed with damping spring 13, and the outside of rotating bar 10 is socketed sliding block 9, and the one of sliding block 9
Side offers through-hole 16, and the correspondence both sides of sliding slot 5 are connected by shaft 15, and the outside of shaft 15 is socketed with connecting rod 8, connecting rod
8 one end is connect by welding with 9 side of sliding block, and the side of connecting rod 8 is connect by resetting spring 7 with 5 side of sliding slot, and machine is worked as
It when part inside body 1 falls, pounds in rotating bar 10, rotating bar 10 compresses rubber sleeve 11, due to 12 He of cushion hole
11 power received of partial rubber set are offset in the setting of damping spring 13, while when rotating bar 10 rotates down, and band movable slider 9 is downward
Movement makes connecting rod 8 rotate, is compressed to resetting spring 7, due to the resiliency characteristics of resetting spring 7, play cushioning effect,
The power moved downward to rotating bar 10 is offset, and damping is played the role of, and is conducive to protect circuit board 18.
Finally it should be noted that：The above descriptions are merely preferred embodiments of the present invention, is not limited to this
Utility model, although the utility model is described in detail with reference to the foregoing embodiments, for those skilled in the art
For, it still can be with technical scheme described in the above embodiments is modified, or to which part technical characteristic
Carry out equivalent replacement.Within the spirit and principle of the utility model, any modification, equivalent replacement, improvement and so on,
It should be included within the scope of protection of this utility model.
Claims (6)
1. a kind of unmanned plane internal protection mechanism, including fuselage (1), wing (2), electric cabinet (3), control panel (4), protection machine
Structure (17), circuit board (18) and accumulator (19), it is characterised in that：The correspondence both sides of the fuselage (1) are mounted on wing
(2), the bottom interior wall of the fuselage (1) is equipped with circuit board (18), and the inside of the fuselage (1) is equipped with protection mechanism
(17), the protection mechanism (17) is by sliding slot (5), fixed link (6), resetting spring (7), connecting rod (8), sliding block (9), rotating bar
(10), rubber sleeve (11), cushion hole (12), damping spring (13), fixture block (14), shaft (15) and through-hole (16) composition, it is described
The correspondence both sides of fuselage (1) offer sliding slot (5), and fixed link (6) is welded at the bottom centre of the sliding slot (5),
The top of the fixed link (6) is connected with rotating bar (10) by articulate, and one end of the rotating bar (10) passes through strength
Gluing is connected to fixture block (14), and the bottom end of the rotating bar (10) is connect by rubber sleeve (11) with fuselage (1) bottom interior wall,
Several cushion holes (12) are offered on the outside of the rubber sleeve (11), the inside of the rubber sleeve (11) is socketed with damping spring
(13), the outside socket sliding block (9) of the rotating bar (10), the side of the sliding block (9) offers through-hole (16), the sliding slot
(5) correspondence both sides are connected by shaft (15), and connecting rod (8), the connecting rod (8) are socketed on the outside of the shaft (15)
One end connect with sliding block (9) side by welding, the side of the connecting rod (8) passes through resetting spring (7) and sliding slot (5) one
Side connects.
2. a kind of unmanned plane internal protection mechanism according to claim 1, it is characterised in that：The top of the fuselage (1)
Portion has been screwed electric cabinet (3), and the side of the electric cabinet (3) has been screwed control panel (4), described automatically controlled
The inside of case (3) is equipped with accumulator (19).
3. a kind of unmanned plane internal protection mechanism according to claim 1, it is characterised in that：The rubber sleeve (11) is logical
Seccotine is crossed to connect with rotating bar (10).
4. a kind of unmanned plane internal protection mechanism according to claim 1, it is characterised in that：The shaft (15) passes through
Bearing is connect with fuselage (1).
5. a kind of unmanned plane internal protection mechanism according to claim 1, it is characterised in that：The resetting spring (7)
It is connect with connecting rod (8) by welding.
6. a kind of unmanned plane internal protection mechanism according to claim 1, it is characterised in that：The connecting rod (8) is logical
Welding is crossed to connect with shaft (15).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820347739.3U CN207985223U (en) | 2018-03-14 | 2018-03-14 | A kind of unmanned plane internal protection mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820347739.3U CN207985223U (en) | 2018-03-14 | 2018-03-14 | A kind of unmanned plane internal protection mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207985223U true CN207985223U (en) | 2018-10-19 |
Family
ID=63827968
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820347739.3U Expired - Fee Related CN207985223U (en) | 2018-03-14 | 2018-03-14 | A kind of unmanned plane internal protection mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207985223U (en) |
-
2018
- 2018-03-14 CN CN201820347739.3U patent/CN207985223U/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20181019 Termination date: 20190314 |