CN206050051U - A kind of multi-rotor aerocraft rotor arm fold mechanism - Google Patents
A kind of multi-rotor aerocraft rotor arm fold mechanism Download PDFInfo
- Publication number
- CN206050051U CN206050051U CN201620886781.3U CN201620886781U CN206050051U CN 206050051 U CN206050051 U CN 206050051U CN 201620886781 U CN201620886781 U CN 201620886781U CN 206050051 U CN206050051 U CN 206050051U
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- CN
- China
- Prior art keywords
- fuselage
- hole
- limiting plate
- shell
- rotor arm
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- 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.)
- Withdrawn - After Issue
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Abstract
The utility model discloses a kind of multi-rotor aerocraft rotor arm fold mechanism, including convex ratchet rotary shaft, pressing limiting plate, spring, fuselage connection shell, fuselage connection locating part and rotor arm.Wherein, convex ratchet is connected with rotor arm, and stage casing is provided with cam structure and ratchet structure.Pressing limiting plate is arranged on fuselage and connects in the chute of locating part, and bottom sets blind hole, and upper end connects the hole on shell, middle fluting through fuselage.Spring is arranged on fuselage connection shell, in the blind hole of insertion pressing limiting plate.Fuselage is connected shell and is connected with fuselage, and side sets through hole with top, and bottom sets blind hole.Fuselage is connected locating part and is connected with fuselage, which is provided with through hole and chute.This utility model mixes rotary shaft using convex ratchet, can carry out accurate circumferential spacing, and position-limit mechanism is contacted using face and wedge-like engagement, can be tolerated foozle and be strengthened limit effect.Fast folding is carried out by key pressing formula design, mechanism is simple to manufacture, simple operation, with high reliability and improves fatigue life.
Description
Technical field
The present invention relates to multi-rotor aerocraft field, more particularly to a kind of multi-rotor aerocraft rotor arm fold mechanism.
Background technology
Multi-rotor aerocraft is increasingly received publicity with its remarkable stability and excellent controllability, Aerial photography,
Consequence is occupied increasingly in various applications such as air surveillance.
Although multi-rotor aerocraft has lot of advantages, existing multi-rotor aerocraft is more due to rotor quantity, with
Centered on fuselage outside spoke shape install, it is large number of for the support arm of flight support, cause multi-rotor aerocraft volume compared with
Greatly, to aircraft manufacture, transport, carrying and storage etc. bring inconvenience.
Adopting folding mode that transformation is carried out to multi-rotor aerocraft can have in prior art with its capacity issue of effectively solving
Carry out folding spacing scheme using C-shaped or U-shaped draw-in groove, which carries out spacing, use using the quiet deformation of notch when folding
Shi Rongyi produces fatigue failure, affects service life；Having carries out spacing scheme using knockout screw or plug-in structure, folds
Complex operation and reliability is poor.
The content of the invention
The invention aims to overcome the problems referred to above, there is provided a kind of multi-rotor aerocraft rotor arm fold mechanism, use
In the rotor arm folding operation of multi-rotor aerocraft.
To reach above-mentioned purpose, the method that the present invention is adopted is：Including convex ratchet rotary shaft, pressing limiting plate, spring, machine
Body connection shell, fuselage connection locating part and rotor arm.
The hole that described convex ratchet rotating shaft terminal is connected locating part one end with fuselage is hinged and passes through fuselage connection shell-side
Hole on side, is fixedly connected with described rotor arm.At its middle section position circumferentially by certain angle be disposed with one it is convex
Wheeled construction and a ratchet-type structure.
Described pressing limiting plate is the bending plate structure of approximate L-shaped, and its upper side edge is installed in described fuselage connection limit
In the chute of position part one end, bottom is provided with the blind hole for being connected with described spring one end, and upper end connects through described fuselage
The hole on body contact top, centre are provided with groove, and the slot structure is extended on lower horizontal plate by the Upper vertical plate of L-shaped bending plate.
Described spring is arranged on the support bar that fuselage connects in shell internal holes, and the described pressing of other end insertion is spacing
In the blind hole of plate bottom.Described spring is constantly in compressive state before and after the folding of rotor arm and in folding process.
Described fuselage connection shell is shell structure, is fixedly connected with aircraft fuselage, and its side is provided with described in permission
The through hole that convex ratchet rotary shaft end is passed through, shell top are provided with the through hole for allowing described pressing limiting plate upper end to pass through, its shell
Inner bottom part is additionally provided with blind hole, is conformed with support bar in the blind hole, for installing described spring.
Described fuselage connection locating part one end is fixedly connected with aircraft fuselage, and the other end is provided with and described convex ratchet
The sliding groove structure that rotary shaft is hinged the through hole of cooperation and is coordinated with pressing limiting plate.
Press with described respectively afterwards before being folded the side of left and right two of the cam-type structure of described convex ratchet rotary shaft
Press the end contact of the lower end surface and horizontal plate of spacing board slot to coordinate, a side of its ratchet-type structure before being folded with institute
The upper surface of the fuselage connection locating part stated coordinates.
As the preferred of the present invention, the cam-type structure side introversion of described convex ratchet rotary shaft, with outer arc locality method
, in 5 ° to 30 ° of little acute angle, the end face bottom introversion upwards of the horizontal plate of described pressing limiting plate is described after folding for line
The right edge of the cam-type structure of convex ratchet rotary shaft forms face with the horizontal plate end face of described pressing limiting plate and contacts or wedge
Shape compression fit.
Beneficial effect：
Technical solution of the present invention compares traditional scheme, on the rotary shaft using the mixing of cam-type structure and ratchet-type structure
Design, can be carried out accurate circumferential spacing.Additionally, position-limit mechanism can be held using face contact and the friction tight mode of wedge pressure
Bear the error of processing and manufacturing and strengthen limit effect.This programme designs the rotor arm to multi-rotor aerocraft by a key pressing formula
Quickly folded, integrated model is simple to manufacture, simple operation, with good reliability and improve fatigue life.
Description of the drawings
Fig. 1 is the front schematic view under multi-rotor aerocraft rotor arm fold mechanism unfolded state；
Fig. 2 is the structural representation for pressing limiting plate；
Fig. 3 is the structural representation that fuselage connects shell；
Fig. 4 is the structural representation that fuselage connects locating part；
Fig. 5 is the schematic rear view in multi-rotor aerocraft rotor arm fold mechanism folding process；
Fig. 6 is the front schematic view in multi-rotor aerocraft rotor arm fold mechanism folding process；
Fig. 7 is the front schematic view after the folding of multi-rotor aerocraft rotor arm fold mechanism；
Fig. 8 is the contact structures schematic diagram of convex ratchet rotary shaft and pressing limiting plate after the folding of rotor arm.
Shown in Fig. 1 to Fig. 8,1, convex ratchet rotary shaft, 2, pressing limiting plate, 21, pressing limiting plate bottom blind hole, 22,
Pressing limiting plate medial launder, 3, spring, 4, fuselage connection shell, 41, fuselage connection shell-side side through hole, 42, fuselage connection shell top
Through hole, 43, fuselage connection shell bottom blind hole, 44, fuselage connection shell nipple support bar, 5, fuselage connection locating part, 51, fuselage connects
Connect locating part through hole, 52, fuselage connection locating part chute, 6, rotor arm.
Specific embodiment
Below in conjunction with the accompanying drawings and specific embodiment, the present invention is further elucidated, the present embodiment is with technical solution of the present invention
Premised under implemented, it should be understood that these embodiments are only illustrative of the invention and is not intended to limit the scope of the invention.
Embodiment 1：
Front and the folding being respectively under multi-rotor aerocraft rotor arm fold mechanism unfolded state as shown in Figure 1 and Figure 5
Schematic rear view during folded.Multi-rotor aerocraft rotor arm fold mechanism disclosed in the present embodiment is mainly revolved including convex ratchet
Rotating shaft 1, pressing limiting plate 2, spring 3, fuselage connection shell 4, fuselage connection locating part 5 and rotor arm 6.Divide as shown in Figures 2 to 4
Limiting plate 2, fuselage connection shell 4 Wei not be pressed and fuselage connects the structural representation of locating part 5.
The hole 51 that described convex 1 two ends of ratchet rotary shaft are connected 5 one end of locating part with fuselage is hinged and connects through fuselage
Hole 41 on 4 side of shell, is fixedly connected with described rotor arm 6.Circumferentially set gradually by certain angle at its middle section position
There are a cam-type structure and a ratchet-type structure.
Bending plate structure of the described pressing limiting plate 2 for approximate L-shaped, its upper side edge are arranged on described fuselage connection limit
In the chute 52 of position 5 one end of part, bottom is provided with the blind hole 21 for being connected with described 3 one end of spring, and upper end passes through described
The hole 42 on 4 top of fuselage connection shell, centre is provided with groove 22, and the slot structure is extended to down by the Upper vertical plate of L-shaped bending plate
On portion's horizontal plate.
Described spring 3 is arranged on the support bar 44 that fuselage connects in 4 internal holes 43 of shell, and other end insertion is described to press
In the blind hole 21 of 2 bottom of pressure limiting plate.Described spring 3 is constantly in pressure before and after the folding of rotor arm 6 and in folding process
Contracting state.
Described fuselage connection shell 4 is shell structure, is fixedly connected with aircraft fuselage, and its side is provided with described in permission
The through hole 41 that convex 1 end of ratchet rotary shaft passes through, shell top are provided with the through hole for allowing described 2 upper end of pressing limiting plate to pass through
42, its shell inner bottom part is additionally provided with blind hole 43, and support bar 44 is conformed with the blind hole, for installing described spring 3.
Described 5 one end of fuselage connection locating part is fixedly connected with aircraft fuselage, and the other end is provided with and described convex spine
52 structure of chute that wheel rotary shaft 1 is hinged the through hole 51 of cooperation and is coordinated with pressing limiting plate 2.
Press with described respectively afterwards before being folded the side of left and right two of the cam-type structure of described convex ratchet rotary shaft 1
Press the end contact of the lower end surface and horizontal plate of spacing board slot 2 to coordinate, a side of its ratchet-type structure before being folded with
The upper surface of described fuselage connection locating part 5 coordinates.
The front being illustrated in figure 6 in multi-rotor aerocraft rotor arm fold mechanism folding process disclosed in the present embodiment shows
It is intended to, it is characterised in that：Described pressing limiting plate 2 moves downward a thin tail sheep under the pressing effect of external force, makes described
Spring 3 further compress from initial compressed state, described convex ratchet rotary shaft 1 is rotated in a clockwise direction, its cam-type
The extrados of structure and the described horizontal plate upper surface for pressing limiting plate 2, described rotor arm 6 is in convex ratchet rotary shaft
Rotate under 1 drive, carry out folding movement.
It is illustrated in figure 7 the front after multi-rotor aerocraft rotor arm fold mechanism disclosed in the present embodiment is folded to illustrate
Figure, it is characterised in that：Described pressing limiting plate 2 is pressed into contact with convex ratchet rotary shaft 1 in the presence of spring 3, described
Rotor arm 6 reaches default folding position under the drive of described convex ratchet rotary shaft 1.
After being illustrated in figure 8 the rotor arm folding of this enforcement, the contact structures of convex ratchet rotary shaft and pressing limiting plate are illustrated
Figure, the cam-type structure side introversion of described convex ratchet rotary shaft 1, with outer arc locality normal in 5 ° to 30 ° of little sharp angle α,
The end face bottom introversion upwards of the horizontal plate of described pressing limiting plate 2, the cam-type structure of described convex ratchet rotary shaft 1
Right edge forms face with the horizontal plate end face of described pressing limiting plate 2 and contacts or wedge shape compression fit.
Technological means disclosed in the present invention program are not limited only to the technological means disclosed in above-mentioned technological means, also include
The technical scheme being made up of above technical characteristic combination in any.The above is the specific embodiment of the present invention, should be referred to
Go out, for those skilled in the art, under the premise without departing from the principles of the invention, can also make some
Improvements and modifications, these improvements and modifications are also considered as protection scope of the present invention.
Claims (2)
1. a kind of multi-rotor aerocraft rotor arm fold mechanism, including convex ratchet rotary shaft, pressing limiting plate, spring, fuselage connect
Body contact, fuselage connection locating part and rotor arm；It is characterized in that：
Described convex ratchet rotating shaft terminal is hinged with the hole that described fuselage is connected locating part one end and through described fuselage
Hole on connection shell-side side, is fixedly connected with described rotor arm, axially disposed at its middle section position to have a cam-type knot
Structure and a ratchet-type structure；
Bending plate structure of the described pressing limiting plate for L-shaped, its upper side edge are arranged on described fuselage connection locating part one end
Chute in, bottom is provided with the blind hole for being connected with described spring one end, and upper end is through described fuselage connection shell top
Hole, centre is provided with groove, and the slot structure is extended on lower horizontal plate by vertical plate；
Described spring is arranged on the support bar that fuselage connects in shell internal holes, the described pressing limiting plate bottom of other end insertion
In the blind hole in portion；Described spring is constantly in compressive state before and after the folding of rotor arm and in folding process；
Described fuselage connection shell is shell structure, is fixedly connected with aircraft fuselage, and its side is provided with allows described convex spine
The through hole that wheel rotary shaft end is passed through, shell top are provided with the through hole for allowing described pressing limiting plate upper end to pass through, its shell inner bottom
Portion is additionally provided with blind hole, is conformed with support bar in the blind hole, for installing described spring；
Described fuselage connection locating part one end is fixedly connected with aircraft fuselage, and the other end is provided with and described convex ratchet rotation
The sliding groove structure that axle is hinged the through hole of cooperation and is coordinated with pressing limiting plate；
The side of left and right two of the cam-type structure of described convex ratchet rotary shaft is limited with described pressing before being folded afterwards respectively
The end contact of the lower end surface and horizontal plate of position board slot coordinates, a side of its ratchet-type structure before being folded with it is described
The upper surface of fuselage connection locating part coordinates.
2. a kind of multi-rotor aerocraft rotor arm fold mechanism according to claim 1, it is characterised in that：Described convex spine
The cam-type structure side introversion of wheel rotary shaft, with outer arc locality normal in 5 ° to 30 ° of little acute angle, described pressing limiting plate
Horizontal plate the introversion upwards of end face bottom, the right edge of the cam-type structure of described convex ratchet rotary shaft and institute after folding
The horizontal plate end face of the pressing limiting plate stated forms face contact or wedge shape compression fit.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620886781.3U CN206050051U (en) | 2016-08-16 | 2016-08-16 | A kind of multi-rotor aerocraft rotor arm fold mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620886781.3U CN206050051U (en) | 2016-08-16 | 2016-08-16 | A kind of multi-rotor aerocraft rotor arm fold mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206050051U true CN206050051U (en) | 2017-03-29 |
Family
ID=58380543
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620886781.3U Withdrawn - After Issue CN206050051U (en) | 2016-08-16 | 2016-08-16 | A kind of multi-rotor aerocraft rotor arm fold mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206050051U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106240793A (en) * | 2016-08-16 | 2016-12-21 | 葛讯 | A kind of multi-rotor aerocraft rotor arm fold mechanism |
-
2016
- 2016-08-16 CN CN201620886781.3U patent/CN206050051U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106240793A (en) * | 2016-08-16 | 2016-12-21 | 葛讯 | A kind of multi-rotor aerocraft rotor arm fold mechanism |
| CN106240793B (en) * | 2016-08-16 | 2019-04-26 | 葛讯 | A kind of multi-rotor aerocraft rotor arm fold mechanism |
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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: 20180319 Address after: Nanjing Baixia High-tech Industrial Park in Jiangsu province 210000 Building No. 4 Room 305 Patentee after: Nanjing Tao - Aviation Technology Co. Ltd. Address before: Nanjing Baixia High-tech Industrial Park in Jiangsu province 210000 Building No. 4 Room 305 Patentee before: Ge Xun |
|
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20170329 Effective date of abandoning: 20190426 |