CN106240793B - 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
- CN106240793B CN106240793B CN201610673070.2A CN201610673070A CN106240793B CN 106240793 B CN106240793 B CN 106240793B CN 201610673070 A CN201610673070 A CN 201610673070A CN 106240793 B CN106240793 B CN 106240793B
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- Prior art keywords
- fuselage
- hole
- limit plate
- shell
- convex
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
Abstract
The invention discloses a kind of multi-rotor aerocraft rotor arm fold mechanisms, including convex ratchet rotary shaft, pressing limit plate, spring, fuselage connection shell, fuselage connection locating part and rotor arm.Wherein, convex ratchet and rotor arm are connected, and middle section is equipped with cam structure and ratchet structure.Pressing limit plate is mounted in the sliding slot of fuselage connection locating part, and bottom sets blind hole, and upper end passes through the hole on fuselage connection shell, centre fluting.Spring is mounted on fuselage connection shell, in the blind hole of insertion pressing limit plate.Fuselage connects shell and fuselage is connected, and side and top set through-hole, and bottom sets blind hole.Fuselage connects locating part and fuselage is connected, and which is provided with through-hole and sliding slot.The present invention mixes rotary shaft using convex ratchet, can carry out accurate circumferential limit, and position-limit mechanism uses face contact and wedge-like engagement, can tolerate foozle and enhance limit effect.It is designed by a key pressing formula and carries out fast folding, mechanism is simple to manufacture, it is convenient to operate, and has high reliability and improves fatigue life.
Description
Technical field
The present invention relates to multi-rotor aerocraft field, in particular to a kind of multi-rotor aerocraft rotor arm fold mechanism.
Background technique
Multi-rotor aerocraft with its brilliant stability and excellent controllability more and more attention has been paid to, Aerial photography,
Consequence is increasingly occupied in a variety of application fields such as air surveillance.
Although multi-rotor aerocraft have lot of advantages, existing multi-rotor aerocraft since rotor quantity is more, with
Centered on fuselage the installation of outside spoke shape, for flight support support arm it is large number of, cause multi-rotor aerocraft volume compared with
Greatly, inconvenience is brought to the manufacture of aircraft, transport, carrying and storage etc..
Its capacity issue can effectively be solved by being transformed using folding mode to multi-rotor aerocraft, be had in the prior art
The scheme for fold using C-shaped or U-shaped card slot limit, is limited when folding using the quiet deformation of notch, is used
When be easy to produce fatigue failure, influence service life；There is the scheme limited using knockout screw or plug-in structure, folds
Complicated for operation and reliability is poor.
Summary of the invention
The purpose of the invention is to overcome the above problem, a kind of multi-rotor aerocraft rotor arm fold mechanism is provided, is used
In the rotor arm folding operation of multi-rotor aerocraft.
In order to achieve the above objectives, the method that the present invention uses is: including convex ratchet rotary shaft, pressing limit plate, spring, machine
Body connects shell, fuselage connection locating part and rotor arm.
The convex ratchet rotating shaft terminal, which connect the hole of locating part one end with fuselage hingedly and passes through fuselage, connects shell-side
Hole on side is fixedly connected with the rotor arm.At its middle section position along axial direction by certain angle be disposed with one it is convex
Wheeled construction and a ratchet-type structure.
The pressing limit plate is approximate L-shaped bending plate structure, and upper side edge is mounted on the fuselage connection limit
In the sliding slot of position part one end, bottom is provided with the blind hole for connecting with the spring one end, and upper end passes through the fuselage and connects
The hole on body contact top, centre is provided with slot, and the slot structure is extended on lower horizontal plate by the Upper vertical plate of L shape bending plate.
The spring is mounted on the support rod in fuselage connection shell internal holes, the other end insertion pressing limit
In the blind hole in board bottom portion.The spring is constantly in compressive state before and after the folding of rotor arm and in folding process.
The fuselage connection shell is shell structure, is fixedly connected with aircraft fuselage, side is provided with described in permission
The through-hole that convex ratchet rotary shaft end passes through, shell top are provided with the through-hole for allowing the pressing limit plate upper end to pass through, shell
Interior bottom is additionally provided with blind hole, and nipple support bar is equipped in the blind hole, for installing the spring.
Described fuselage connection locating part one end is fixedly connected with aircraft fuselage, and the other end is equipped with and the convex ratchet
The through-hole that rotary shaft hingedly cooperates and the sliding groove structure with pressing limit plate cooperation.
It is pressed respectively with described afterwards before being folded the side of left and right two of the cam-type structure of the convex ratchet rotary shaft
The lower end surface and the end face of level board for pressing limit plate are engaged, a side of ratchet-type structure before being folded with it is described
Fuselage connection locating part upper surface be engaged.
As a preference of the present invention, the cam-type structure side introversion of the convex ratchet rotary shaft, with outer arc locality method
Line is in 5 ° to 30 ° of small acute angle, the upward introversion in end face bottom end of the level board of the pressing limit plate, described after folding
The right edge of the cam-type structure of convex ratchet rotary shaft is contacted with the horizontal plate end face forming face of the pressing limit plate or wedge
Shape compression fit.
The utility model has the advantages that
Technical solution of the present invention compares traditional scheme, uses the mixing of cam-type structure and ratchet-type structure on the rotary shaft
Design, is able to carry out accurate axial limiting.In addition, position-limit mechanism can be held by the way of face contact and wedge-shaped compression fit
Bear the error of processing and manufacturing and enhances limit effect.This programme designs the rotor arm to multi-rotor aerocraft by a key pressing formula
It is quickly folded, overall mechanism is simple to manufacture, it is convenient to operate, and has good reliability and improves fatigue life.
Detailed description of the invention
Fig. 1 is the front schematic view under multi-rotor aerocraft rotor arm fold mechanism unfolded state；
Fig. 2 is the structural schematic diagram for pressing limit plate；
Fig. 3 is the structural schematic diagram that fuselage connects shell；
Fig. 4 is the structural schematic diagram 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 folded front schematic view of multi-rotor aerocraft rotor arm fold mechanism；
Fig. 8 is the contact structures schematic diagram of convex ratchet rotary shaft and pressing limit plate after rotor arm folds.
Shown in Fig. 1 to Fig. 8,1, convex ratchet rotary shaft, 2, pressing limit plate, 21, pressing limit plate bottom blind hole, 22,
Press limit plate medial launder, 3, spring, 4, fuselage connection shell, 41, side through-hole, 42, top through-hole, 43, fuselage connection shell bottom
Portion's blind hole, 44, support rod, 5, fuselage connection locating part, 51, through-hole, 52, sliding slot, 6, rotor arm.
Specific embodiment
In the following with reference to the drawings and specific embodiments, the present invention is furture elucidated, and the present embodiment is with technical solution of the present invention
Premised under implemented, it should be understood that these examples are only for illustrating the present invention and are not intended to limit the scope of the present invention.
Embodiment 1:
It is as shown in Figure 1 and Figure 5 respectively front and the folding under multi-rotor aerocraft rotor arm fold mechanism unfolded state
Schematic rear view during folded.Multi-rotor aerocraft rotor arm fold mechanism disclosed in the present embodiment mainly includes convex ratchet rotation
Shaft 1, pressing limit 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
Limit plate 2 Wei not pressed, fuselage connection shell 4 connects the structural schematic diagram of locating part 5 with fuselage.
Convex 1 both ends of ratchet rotary shaft, which connect the through-hole 51 of 5 one end of locating part with fuselage hingedly and pass through fuselage, to be connected
Side through-hole 41 on 4 side of body contact is fixedly connected with the rotor arm 6.Certain angle is pressed along axial at its middle section position
It is disposed with a cam-type structure and a ratchet-type structure.
The pressing limit plate 2 is approximate L-shaped bending plate structure, and upper side edge is mounted on the fuselage connection limit
In the sliding slot 52 of position 5 one end of part, bottom is provided with the blind hole 21 for connecting with described 3 one end of spring, and upper end passes through described
Fuselage connects the top through-hole 42 on 4 top of shell, and centre is provided with slot 22, and the slot structure is prolonged by the Upper vertical plate of L shape bending plate
It reaches on lower horizontal plate.
The spring 3 is mounted on the support rod 44 in fuselage connection 4 interior bottom portion blind hole 43 of shell, and the other end is inserted into institute
In the blind hole 21 for pressing 2 bottom of limit plate stated.The spring 3 rotor arm 6 folding before and after and folding process in always
In compressive state.
The fuselage connection shell 4 is shell structure, is fixedly connected with aircraft fuselage, side is provided with described in permission
The side through-hole 41 that convex 1 end of ratchet rotary shaft passes through, shell top are provided with that allow 2 upper end of pressing limit plate to pass through upper
Side through-hole 42, bottom is additionally provided with bottom blind hole 43 in shell, and nipple support bar 44 is equipped in the blind hole, for installing the bullet
Spring 3.
Described fuselage connection 5 one end of locating part is fixedly connected with aircraft fuselage, and the other end is equipped with and the convex spine
The through-hole 51 and 52 structure of sliding slot cooperated with pressing limit plate 2 that wheel rotary shaft 1 hingedly cooperates.
It is pressed respectively with described afterwards before being folded the side of left and right two of the cam-type structure of the convex ratchet rotary shaft 1
The lower end surface and the end face of level board for pressing limit plate 2 are engaged, a side of ratchet-type structure before being folded with institute
The upper surface for the fuselage connection locating part 5 stated is engaged.
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: the pressing limit plate 2 moves downward a thin tail sheep under the pressing effect of external force, makes described
Spring 3 further compressed from initial compressed state, the convex ratchet rotary shaft 1 is rotated in a clockwise direction, cam-type
The extrados of structure is contacted with the level board upper surface of the pressing limit plate 2, and the rotor arm 6 is in convex ratchet rotary shaft
It is rotated under 1 drive, carries out folding movement.
It is illustrated in figure 7 the folded front signal of multi-rotor aerocraft rotor arm fold mechanism disclosed in the present embodiment
Figure, it is characterised in that: the pressing limit plate 2 is pressed into contact under the action of spring 3 with convex ratchet rotary shaft 1, described
Rotor arm 6 reaches preset folding position under the drive of the convex ratchet rotary shaft 1.
Convex ratchet rotary shaft is illustrated with the contact structures for pressing limit plate after being illustrated in figure 8 the rotor arm folding of this implementation
Figure, the cam-type structure side introversion of the convex ratchet rotary shaft 1 are in 5 ° to 30 ° of small sharp angle α with outer arc locality normal,
The upward introversion in end face bottom end of the level board of the pressing limit plate 2, the cam-type structure of the convex ratchet rotary shaft 1
Right edge is contacted with the horizontal plate end face forming face of the pressing limit plate 2 or wedge-shaped compression fit.
The technical means disclosed in the embodiments of the present invention is not limited to the technical means disclosed in the above technical means, and further includes
Technical solution consisting of any combination of the above technical features.The foregoing is a specific embodiment of the present invention, should refer to
Out, for those skilled in the art, without departing from the principle of the present invention, can also make several
Improvements and modifications, these modifications and embellishments are also considered to be within the scope of the present invention.
Claims (2)
1. a kind of multi-rotor aerocraft rotor arm fold mechanism, including convex ratchet rotary shaft, pressing limit plate, spring, fuselage connect
Body contact, fuselage connection locating part and rotor arm；It is characterized by:
The convex ratchet rotating shaft terminal connect the hole of locating part one end with the fuselage hingedly and passes through the fuselage
Connect shell-side side on side through-hole, be fixedly connected with the rotor arm, at middle section position it is axially disposed have one it is convex
Wheeled construction and a ratchet-type structure；
The pressing limit plate is L-shaped bending plate structure, and upper side edge is mounted on described fuselage connection locating part one end
Sliding slot in, bottom is provided with the blind hole for connecting with the spring one end, and upper end passes through the fuselage and connects shell top
Top through-hole, centre is provided with slot, and the slot structure is extended on lower horizontal plate by vertical plate；
The spring is mounted on the support rod in fuselage connection shell interior bottom portion hole, the other end insertion pressing
In the blind hole of limit plate bottom；The spring is constantly in compressive state before and after the folding of rotor arm and in folding process；
The fuselage connection shell is shell structure, is fixedly connected with aircraft fuselage, side, which is provided with, allows the convex spine
The side through-hole that wheel rotary shaft end passes through, shell top are provided with the top through-hole for allowing the pressing limit plate upper end to pass through,
Bottom is additionally provided with bottom blind hole in its shell, and nipple support bar is equipped in the blind hole, for installing the spring；
Described fuselage connection locating part one end is fixedly connected with aircraft fuselage, and the other end is equipped with to be rotated with the convex ratchet
The through-hole that axis hingedly cooperates and the sliding groove structure with pressing limit plate cooperation；
The side of left and right two of the cam-type structure of the convex ratchet rotary shaft is limited with the pressing respectively afterwards before being folded
The lower end surface of position plate and the end face of level board are engaged, a side of ratchet-type structure before being folded with the machine
The upper surface of body connection locating part is engaged.
2. a kind of multi-rotor aerocraft rotor arm fold mechanism according to claim 1, it is characterised in that: the convex spine
The cam-type structure side introversion for taking turns rotary shaft is in 5 ° to 30 ° of small acute angle, the pressing limit plate with outer arc locality normal
Level board the upward introversion in end face bottom end, the right edge of the cam-type structure of the convex ratchet rotary shaft and institute after folding
The contact of horizontal plate end face forming face or wedge-shaped compression fit for the pressing limit plate stated.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610673070.2A CN106240793B (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 |
|---|---|---|---|
| CN201610673070.2A CN106240793B (en) | 2016-08-16 | 2016-08-16 | A kind of multi-rotor aerocraft rotor arm fold mechanism |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106240793A CN106240793A (en) | 2016-12-21 |
| CN106240793B true CN106240793B (en) | 2019-04-26 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610673070.2A Active CN106240793B (en) | 2016-08-16 | 2016-08-16 | A kind of multi-rotor aerocraft rotor arm fold mechanism |
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| CN (1) | CN106240793B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN208498780U (en) * | 2018-06-28 | 2019-02-15 | 深圳市大疆创新科技有限公司 | Unmanned plane and its rack |
| CN111942576B (en) * | 2020-08-25 | 2024-04-05 | 长天智航(北京)科技有限公司 | Foldable unmanned aerial vehicle |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105000165A (en) * | 2015-07-23 | 2015-10-28 | 致导科技（北京）有限公司 | Locking device for folding type unmanned aerial vehicle arm |
| CN205186518U (en) * | 2015-10-27 | 2016-04-27 | 杭州海康威视数字技术股份有限公司 | Unmanned aerial vehicle |
| CN105539827A (en) * | 2016-01-26 | 2016-05-04 | 南京航空航天大学 | Arm folding device of multi-axial air vehicle |
| CN206050051U (en) * | 2016-08-16 | 2017-03-29 | 葛讯 | A kind of multi-rotor aerocraft rotor arm fold mechanism |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8052081B2 (en) * | 2008-08-22 | 2011-11-08 | Draganfly Innovations Inc. | Dual rotor helicopter with tilted rotational axes |
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2016
- 2016-08-16 CN CN201610673070.2A patent/CN106240793B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105000165A (en) * | 2015-07-23 | 2015-10-28 | 致导科技（北京）有限公司 | Locking device for folding type unmanned aerial vehicle arm |
| CN205186518U (en) * | 2015-10-27 | 2016-04-27 | 杭州海康威视数字技术股份有限公司 | Unmanned aerial vehicle |
| CN105539827A (en) * | 2016-01-26 | 2016-05-04 | 南京航空航天大学 | Arm folding device of multi-axial air vehicle |
| CN206050051U (en) * | 2016-08-16 | 2017-03-29 | 葛讯 | A kind of multi-rotor aerocraft rotor arm fold mechanism |
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| Publication number | Publication date |
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| CN106240793A (en) | 2016-12-21 |
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Effective date of registration: 20200107 Address after: 425000 Building 1, Youth Innovation and entrepreneurship Park, Xiaoxiang science and technology innovation center, economic development zone, Yongzhou City, Hunan Province Patentee after: Hunan taoxun 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 |
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