CN106927026A - Multi-rotor aerocraft - Google Patents
Multi-rotor aerocraft Download PDFInfo
- Publication number
- CN106927026A CN106927026A CN201511026583.6A CN201511026583A CN106927026A CN 106927026 A CN106927026 A CN 106927026A CN 201511026583 A CN201511026583 A CN 201511026583A CN 106927026 A CN106927026 A CN 106927026A
- Authority
- CN
- China
- Prior art keywords
- rotor
- supporting part
- rotor assemblies
- assemblies
- pivot
- 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.)
- Pending
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- 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
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
Abstract
This application discloses a kind of multi-rotor aerocraft.The multi-rotor aerocraft includes：First rotor assemblies, it includes the first supporting part, and first group of rotor for being installed on first supporting part；Second rotor assemblies, it includes the second supporting part, and second group of rotor for being installed on second supporting part；Revolving member, it is configured as being pivotally connected first rotor assemblies and second rotor assemblies, to enable that first rotor assemblies and the second rotor assemblies relatively rotate with respect to each other around a pivot center, wherein the pivot center is perpendicular to first supporting part and the principal plane of second supporting part；And locking component, it is configured as locking the relative rotation between first rotor assemblies and second rotor assemblies when first rotor assemblies turn to one or more predetermined expanded positions relative to second rotor assemblies.
Description
Technical field
The application is related to unmanned vehicle technology, more particularly, to a kind of multi-rotor aerocraft.
Background technology
Unmanned vehicle is the not manned vehicle of a kind of utilization radio robot and the manipulation of airborne control device.In recent years
Come, with the fast development of technology, the production and application of unmanned vehicle are flourished, and many companies are proposed very
Many unmanned vehicle products, these new unmanned vehicle products generally use multiple rotors, such as with four or six
Rotor.
However, existing multi-rotor aerocraft structural volume is larger, therefore its is not readily portable, which has limited unmanned vehicle
Use.
The content of the invention
The first purpose of the application is to provide a kind of portable unmanned vehicle.
In the one side of the application, there is provided a kind of multi-rotor aerocraft, including：First rotor assemblies, it includes
First supporting part, and it is installed on first group of rotor of first supporting part；Second rotor assemblies, it includes second
Supporting part, and it is installed on second group of rotor of second supporting part；Revolving member, it is configured as pivotally connecting
First rotor assemblies and second rotor assemblies are connect, to cause first rotor assemblies and the second rotor assemblies
Can be relatively rotated with respect to each other around a pivot center, wherein the pivot center is perpendicular to first supporting part and described
The principal plane of two supporting parts；And locking component, it is configured as first rotor assemblies relative to described second
Rotor assemblies lock first rotor assemblies and second rotor when turning to one or more predetermined expanded positions
Relative rotation between component.
In certain embodiments, the revolving member is further configured to allow first rotor assemblies relative to institute
State the second rotor assemblies and turn to predetermined closed position, compared in one or more of predetermined expanded positions, place
The overlapped region increase of first rotor assemblies and second rotor assemblies in the predetermined closed position.
In certain embodiments, first rotor assemblies and second rotor assemblies have identical circumferential profile.
In certain embodiments, the revolving member includes the pivot and axle sleeve that are mutually matched, wherein, the axle sleeve quilt
It is arranged on one among first supporting part and the second supporting part, and the pivot is arranged on described first
On another among supporting part and the second supporting part.
In certain embodiments, the pivot is arranged on first supporting part, and the axle sleeve is arranged on institute
State on the second supporting part.
In certain embodiments, the outside of the pivot has limit fastener, and it is configured as the pivot and is inserted into
The relative position of both is limited after the axle sleeve, to avoid it from being separated from each other.
In certain embodiments, first supporting part has cylindrical protrusions, and second supporting part limits cylinder
Shape cavity, the cylindrical cavity is configured as accommodating the cylindrical protrusions, and the cylindrical protrusions with it is described
The axis of cylindrical cavity overlaps with the pivot center.
In certain embodiments, the locking component includes：Keeper, its from the lateral wall of the cylindrical protrusions to
Outer extension；Pivot guide slot, its side wall for being arranged on the cylindrical cavity, and along the cylindrical cavity
Side wall circumferentially extending, the pivot guide slot can accommodate the keeper wherein along the side wall circumference of cylindrical cavity
It is mobile；Wherein, when first rotor assemblies turn to a predetermined expanded position relative to second rotor assemblies
When, its described keeper can contact the side wall of the cylindrical cavity, and offer can lock first rotor
The power of the relative rotation between component and the second rotor assemblies.
In certain embodiments, the pivot guide slot has insertion opening, and it is configured such that the keeper energy
Enough it is inserted into the pivot guide slot.
In certain embodiments, the keeper is made up of elastomeric material.
In certain embodiments, the pivot guide slot is not less than along the side wall circumferentially extending angle of the cylindrical cavity
90 degree.
In certain embodiments, the side wall of the cylindrical cavity has one or more locating recesses, and each is described fixed
Position depression is configured as first rotor assemblies and turns to a predetermined expansion relative to second rotor assemblies
During position, it can accommodate the end of the keeper, so as to lock first rotor assemblies and the second rotor assemblies
Between relative rotation.
In certain embodiments, one or more of locating recesses are described on the side-wall outer side edge of the cylindrical cavity
The circumferentially extending directional spreding of pivot guide slot.
In certain embodiments, one or more of locating recesses are arranged on the side of the pivot guide slot.
In certain embodiments, first supporting part and second supporting part include two ends, and institute respectively
Stating first group of rotor includes being separately positioned on first supporting part, two the two of end rotors, and second group of rotation
The wing includes being separately positioned on second supporting part, two the two of end rotors.
In certain embodiments, when first rotor assemblies turned to relative to second rotor assemblies it is one
Or during a predetermined expanded position in multiple predetermined expanded positions, two centers of rotor connect in first group of rotor
Line is mutually perpendicular to the line of centres of two rotors in second group of rotor.
In certain embodiments, first rotor assemblies and second rotor assemblies have identical circumferential profile,
The revolving member is further configured to allow first rotor assemblies to be rotated relative to second rotor assemblies
To predetermined closed position, in the predetermined closed position, first rotor assemblies and second rotor assemblies it is outer
All profiles are overlapped together.
In certain embodiments, also include：Power switch, it is arranged to control to first group of rotor and described
Second group of power supply supply of rotor.
In certain embodiments, the power switch is configured as first rotor assemblies relative to the described second rotation
Wing component allows the electronic system to the multi-rotor aerocraft when turning to one or more of predetermined expanded positions
Power supply；And forbid when first rotor assemblies do not turn to predetermined expanded position relative to second rotor assemblies
To the powering electronic systems of the multi-rotor aerocraft.
In certain embodiments, the power switch is arranged on the medial surface of second supporting part, and described
The medial surface of one supporting part includes one or more switch actuating components, when first rotor assemblies are relative to described the
When two rotor assemblies turn to a predetermined expanded position, one in one or more of switch actuating components can
The power switch is controlled to close.
In certain embodiments, the switch actuating component includes projection or magnet.
Above for the application general introduction, may have simplify, summarize and omissions of detail situation, therefore this area technology
Personnel are it should be appreciated that the part is only Illustrative, and is not intended to limit the application scope by any way.
This overview section is both not intended to determine the key feature or essential feature of claimed subject, is also not intended to be used as really
Determine the supplementary means of the scope of claimed subject.
Brief description of the drawings
Combined by following description and appending claims and with accompanying drawing, it will be more fully clearly understood that this
Apply for the above and other feature of content.It is appreciated that these accompanying drawings depict only some embodiment party of teachings herein
Formula, therefore it is not considered as the restriction to teachings herein scope.By using accompanying drawing, teachings herein will be obtained
Definitely and explain.
Fig. 1 is the schematic diagram being in the deployed according to the multi-rotor aerocraft 100 of the application one embodiment；
Fig. 2 is multi-rotor aerocraft 100 shown in Fig. 1 schematic diagram in the closed position；
Fig. 3 is the perspective view of the locking component of the multi-rotor aerocraft 100 shown in Fig. 1；
Fig. 4 is the fragmentary, perspective view of the locking component shown in Fig. 3；
Fig. 5 is the partial schematic diagram of the locking component shown in Fig. 3；
Fig. 6 is the generalized section of the revolving member of the multi-rotor aerocraft 100 shown in Fig. 1；
Fig. 7 is the schematic diagram of the medial surface of the first supporting part of the multi-rotor aerocraft 100 shown in Fig. 1；
Fig. 8 is the partial schematic diagram of the medial surface of the second supporting part of the multi-rotor aerocraft 100 shown in Fig. 1；
Fig. 9 is that the switch actuating component on the medial surface of the second supporting part of the multi-rotor aerocraft 100 shown in Fig. 1 connects
Partial schematic diagram during electric shock source switch.
Specific embodiment
In the following detailed description, with reference to constitute part thereof of accompanying drawing.In the accompanying drawings, similar symbol is usual
Similar part is represented, unless otherwise indicated by context.Described in detailed description, drawings and claims
Illustrated embodiment is not intended to limit.In the case of without departing from the spirit or scope of the theme of the application, can be with
Using other embodiment, and other changes can be made.It is appreciated that can be to general description in the application
, the various aspects of the teachings herein for illustrating in the accompanying drawings carry out various differently composed configurations, replacement, group
Close, design, and all these parts for all clearly constituting teachings herein.
Figures 1 and 2 show that the overall structure of the multi-rotor aerocraft 100 according to the application one embodiment.Wherein,
Fig. 1 is the schematic diagram that the multi-rotor aerocraft 100 is in the deployed, and Fig. 2 is at the multi-rotor aerocraft 100
In the schematic diagram of closed position.
As depicted in figs. 1 and 2, the multi-rotor aerocraft 100 includes the first rotor assemblies 102 and the second rotor group
Part 104.Wherein, the first rotor assemblies 102 include the first supporting part 106, and installed in the first supporting part 106
First group of rotor 108.First supporting part 106 is used to install first group of rotor 108, with so as to stabilization
Link together.In the embodiment shown in fig. 1, in the tabular for extending, it has end to the first supporting part 106
The 106a and end 106b relative with end 106a.Correspondingly, first group of rotor 108 includes two rotor 108a
And 108b, it is generally symmetrically arranged on end 106a and 106b.In some other embodiments, first
Group rotor can also include more rotors.For example, the first supporting part can be moved by being mutually in 120 degree 3 of angle
The arm of force is constituted, and a rotor is wherein provided with one end of each power arm, and the other end then interconnects.
Similarly, the second rotor assemblies 104 include the second supporting part 110, and installed in the second supporting part 110
Second group of rotor 112.Second supporting part 110 is used to install second group of rotor 112, and it is substantially in the tabular of elongation,
And with two ends.Correspondingly, second group of rotor 112 includes two rotors 112a and 112b, and it is by substantially
It is symmetrically disposed on two ends of the second supporting part 110.
Rotor 108a, 108b, 112a and 112b of multi-rotor aerocraft 100 generally can have identical structure and
Size.Specifically, by taking rotor 108a as an example, it includes a cantilever 114, and one end of the cantilever 114 is connected to
On first supporting part 106, and the other end is then used to install propeller 116 and drives the motor of the rotation of propeller 116
(not shown).Additionally, the periphery of propeller 116 is additionally provided with isolation frame 118, its can be used for avoiding or
Propeller 116 is at least reduced operationally to impact to exterior object.In the embodiment shown in fig. 1, the first supporting part
106 end 106a is connected to isolation frame 118, and similarly, the other end 106b of the first supporting part 106 also connects
It is connected to isolation frame 119.In certain embodiments, the two isolation frames 118 and 119 can be with the first supporting part 106
It is integrally formed, collectively forms the support frame of rotor 108a and 108b.It is appreciated that in some other implementation
In example, rotor 108a, 108b, 112a and 112b can also use different structure and/or size.For example, rotor
108a and 108b have larger size, and rotor 112a and 112b have relatively small size.Additionally, rotation
The diameter (such as diameter of propeller or isolation frame) of the wing 108a, 108b can be more than the width of the first supporting part 106
Degree, and/or the diameter of rotor 112a and 112b can be more than the width of the second supporting part 110.The increase of rotor size
It is favorably improved the power of multi-rotor aerocraft.
Multi-rotor aerocraft 100 also includes revolving member and locking component, and it is arranged on the first supporting part 106 and the
On two supporting parts 110.Revolving member and locking component structurally and functionally will be explained further below.
Specifically, the revolving member of multi-rotor aerocraft 100 is pivotally connected the first rotor assemblies 102 and the second rotor
Component 104.So, the first rotor assemblies 102 and the second rotor assemblies 104 can be around a pivot center ZZ ' (ginsengs
See Fig. 2) relatively rotate with respect to each other, so as to be rotated between the closed position shown in the expanded position and Fig. 2 shown in Fig. 1.
Wherein, pivot center ZZ ' is perpendicular to the first supporting part 106 and the principal plane of the second supporting part 110.Each supporting part
Principal plane refer to subject plane of the support zone between two end, the principal plane of the first supporting part 106 and
The principal plane of the second supporting part 110 is substantially parallel to one another.For being interconnected simultaneously in mode shown in Fig. 1 and 2
And for two rotor assemblies 102 and 104 that can be rotated relative to one another, when the first rotor assemblies 102 and second
When rotor assemblies 104 are in expanded position as shown in Figure 1 or closed position as shown in Figure 2, the first supporting part 106
Principal plane and the principal plane of the second supporting part 110 be basically perpendicular to pivot center ZZ '.When along pivot center ZZ '
Direction when seeing, the principal plane of the two rotor assemblies 102 and 104 is least partially overlapped.For example, shown in Fig. 1
Embodiment in, together with the principal plane of the first supporting part 106 and the second supporting part 110 is at least partly overlapped；
In the embodiment shown in Figure 2, the substantially all phase mutual respect of the principal plane of the first supporting part 106 and the second supporting part 110
Stack.
By means of revolving member, the first rotor assemblies 102 and the second rotor assemblies 104 can be rotated to shown in Fig. 2
Closed position.Compared to the multi-rotor aerocraft 100 in the expanded position shown in Fig. 1, when in closed position,
First rotor assemblies 102 and the overlapped region increase of the second rotor assemblies 104.For example, as shown in Fig. 2 removing
Outside two supporting parts overlap, first group of rotor 108 and second group of rotor 112 also overlap respectively,
So as to increase two areas of the overlapping region of rotor assemblies.In general, in closed position, the first rotor assemblies
108 and second rotor assemblies 112 there is maximum overlapping region.
Figure it is seen that the first rotor assemblies 102 can be with outer with what the second rotor assemblies 104 were substantially the same
All profiles.Wherein, the circumferential profile being substantially the same refers to the whole of the first rotor assemblies 102 and the second rotor assemblies 104
External body shape and size are essentially identical, and first group of rotor 108 and second group of rotor 112 are with essentially identical
Shape and size, position of first group of rotor 108 on the first supporting part 106 is with second group of rotor 112 at second
Position on support part 110 also corresponds to substantially.For example, as shown in Fig. 2 first group of rotor 108 and second group of rotor 112
Isolation frame be the circle of equal diameters, and first group of the two of rotor 108 isolation frame to pivot center ZZ's '
Distance is generally equalized with second group of the two of rotor 112 distance for isolating frame to pivot center ZZ '.So, when being in
During closed position, two rotor assemblies of multi-rotor aerocraft 100 generally it is completely overlapped together.As can be seen that
The compact conformation of multi-rotor aerocraft 100 after closing, is easy to user to carry；When flight is needed, user can be with
Multi-rotor aerocraft 100 is opened to expanded position, at this moment first group of rotor 108 be not mutual with second group of rotor 112
Overlap, so as to constitute the Flight Vehicle Structure of four rotors, six rotors or more rotor.
It should be noted that the circumferential profile of two rotor assemblies is identical to be not meant to the first rotor assemblies 102 and
Two rotor assemblies 108 cannot have some inapparent structures or profile differences；Conversely, such as the first rotor assemblies
There can be decorating structure on 102 and can not have decorating structure in the second rotor assemblies 108, people in the art
Member is not it is appreciated that these inapparent structures or profile differences interfere with the flight of multi-rotor aerocraft, thus it is still
Belong to the protection domain of the application.It is appreciated that in further embodiments, the first rotor assemblies 102 and second are revolved
Wing component 104 can also have different circumferential profiles.
In certain embodiments, when multi-rotor aerocraft 100 is in an expanded position, its first group of rotor 108
In in two lines of centres and second group of rotor 112 of rotor 108a and 108b in two rotors 112a and 112b
Heart line can be mutually perpendicular to, the overall shape in right-angled intersection of multi-rotor aerocraft 100.It is appreciated that many rotors
Aircraft 100 can also be in other expanded positions.For example, when in other expanded positions, rotor 108a
The line of centres and the angle of the line of centres of rotor 112a and 112b with 108b can also be other angles, for example
It is arbitrarily angled between 10 degree, 20 degree, 30 degree, 45 degree or 60 degree, or 10 degree to 90 degree.As a rule,
When in display position, two groups of downwash flows of rotor are not interfered with each other substantially, it will be appreciated that the application is simultaneously
Not limited to this.Even if for example, the downwash flow of two groups of rotors slightly has interference, as long as many rotors fly when being in the deployed
Row device 100 still is able to normal flight after being powered, and this implementation method still falls within scope of the present application.
In certain embodiments, the first supporting part 108 and the second supporting part 110 are substantially in tabular, and the two
At least part of region of supporting part 108 and 110 is close to each other.In order to reduce two groups of Plane of rotations of rotor 108 and 112
Between spacing, in certain embodiments, for fixing first group of cantilever of rotor 108 114 and 115 and for solid
Fixed second group of cantilever of rotor 112 120 and 121 can be set in which be located remotely from each other.In other words, cantilever 114 and 115
It is arranged on the lower of the first supporting part 106, and cantilever 120 and 121 are arranged on the second supporting part 110
Upper.So, the propeller of first group of rotor 114 and second group of Plane of rotation of the propeller of rotor 115 can be with
It is close to each other as much as possible, for example, its spacing is equal to or less than 1 centimetre, or preferably, equal to or less than 0.5
Centimetre, and between first group of cantilever of rotor 108 114 and 115 and second group of cantilever of rotor 112 120 and 121
Still can be with a certain distance apart from one another.
Fig. 3 to Fig. 6 shows the revolving member and locking component of the multi-rotor aerocraft 100 shown in Fig. 1.Wherein,
Fig. 3 is locked out the perspective view of component；Fig. 4 shows the fragmentary, perspective view of locking component and revolving member；Fig. 5 is lock
Determine the partial schematic diagram of component；Fig. 6 is locked out the sectional view of component and revolving member.
As shown in Figure 4 and Figure 6, the revolving member of multi-rotor aerocraft is arranged on the first supporting part and the second supporting part
Between.Wherein, revolving member 122 includes the pivot 124 and axle sleeve 126 that are mutually matched.Wherein, the quilt of pivot 124
It is arranged on the first supporting part, and axle sleeve 126 is arranged on the second supporting part.It is appreciated that in other implementations
In example, pivot can also be arranged on the second supporting part, and axle sleeve is then arranged on the first supporting part.
Specifically, pivot 124 is substantially in cylindrical, the internal diameter substantial match of its external diameter and axle sleeve 126.So, pivot
Axle 124 can be inserted into axle sleeve 126, so that two rotor assemblies can relatively rotate with respect to each other.At some
In embodiment, the outside of pivot 124 can also set limit fastener 128.After pivot 124 is inserted into axle sleeve 126,
Limit fastener 128 can limit the relative position of both, to avoid it from being separated from each other.For example, limit fastener 128
Can be the lateral projection or flange near the top of pivot 124, after pivot 124 is inserted into axle sleeve 126, pivot
The lateral projection or flange on the top of axle 124 can abut the port of axle sleeve 126.In further embodiments, limiting card
Button can also be the flange (such as pivot middle part) in the outside of pivot 124, and the madial wall of axle sleeve 126 can have it is right
The annular recess answered.After pivot 124 is inserted into axle sleeve 126, the flange on pivot 124 is embedded in axle sleeve 126
Annular recess in, so as to limit pivot 124 and axle sleeve 126 is separated from each other.Because flange is generally annular in shape, and
Its position is corresponding with annular recess, therefore flange can be moved under the guiding of annular recess, and its without limitation on
Rotation of the pivot relative to axle sleeve.As can be seen that this revolving member simple structure, and be easily installed.
The locking component of multi-rotor aerocraft is used to for two rotor assemblies to be locked in predetermined expanded position.Specifically, when
When first rotor assemblies turn to predetermined expanded position relative to the second rotor assemblies, locking component can lock this two
Individual rotor assemblies and between relative rotation.So, when flight is launched, by means of locking component, many rotor flyings
Device can keep the relative position between its each component constant.
With further reference to Fig. 3 to Fig. 6, with cylindrical protrusions 130 on the first supporting part 106, and the second supporting part
110 limit cylindrical cavity 132 corresponding with the cylindrical protrusions 130.Cylindrical protrusions 130 are accommodated in circle
In cylindrical cavity 132, and the axis of both with the first rotor assemblies and the pivot center weight of the second rotor assemblies
Close.In certain embodiments, the cylindrical protrusions 130 and cylindrical cavity 132 can also be used as revolving members.
In some embodiments, the center of cylindrical cavity 132 can be provided with pivot 124, and in cylindrical protrusions 130
The heart can then set axle sleeve 126, and the pivot 124 and axle sleeve 126 are mutually matched, used as revolving member.Can replace
Change ground, in some other embodiments, pivot can also be arranged in cylindrical protrusions 130, and axle sleeve then by
It is arranged on cylindrical cavity 132.
In certain embodiments, locking component is arranged in cylindrical protrusions 130 and cylindrical cavity 132.Specifically
Ground, as shown in figure 4, locking component includes keeper 134, it is outside from the lateral wall 136 of cylindrical protrusions 130
Extend.Keeper 134 is generally made up of elastomeric material, for example, be made up of plastics or metal material.The keeper 134
There can be the hooked end of bending, the end of the hooked end can move to towards cylindrical cavity 132
Substantially abut the position of the side wall 138 of cylindrical cavity 132.Additionally, locking component also includes pivot guide slot 140,
It is arranged on the side wall 138 of cylindrical cavity 132, and is circumferentially extended along the side wall 138.Pivot guide slot
140 can accommodate keeper 134 wherein along the circumferential movement of side wall 138 of cylindrical cavity 132.Keeper 134
Gathering sill 140 is rotated to clamp, therefore the first rotor assemblies and the second rotor assemblies must not limit and are separated from each other.
In some embodiments, when the hooked end of keeper 134 is connected on side wall 138, hooked end and side wall 138
Between contact sufficiently large pressure and frictional force can be provided, so as to limit two rotor assemblies of multi-rotor aerocraft
Relatively rotate with respect to each other.In certain embodiments, the end of keeper 134 can be designed as towards the face of side wall 138
It is curved, with about the same with the radian of side wall 138, this be conducive to increasing the end of keeper 134 and side wall 138 it
Between frictional force.So, the expanded position needed for multi-rotor aerocraft can be just locked in flight by locking component.Can
To understand, when needing to rotate two rotor assemblies, user can firmly relatively rotate two rotor assemblies, to change
Become the relative position of the two rotor assemblies.
In certain embodiments, locking component can also include one on the side wall 138 of cylindrical cavity 132
Or multiple locating recesses (not shown)s.Wherein, the shape of each locating recesses and height and keeper 134
End matches.So, it is fixed when the first rotor assemblies turn to an expanded position relative to the second rotor assemblies
Position depression can accommodate the end of keeper 134, so as to lock the phase between the first rotor assemblies and the second rotor assemblies
To rotating.It is appreciated that the circumferential position of each locating recesses corresponds to an expanded position of multi-rotor aerocraft.
Therefore, the need for according to concrete application, these locating recesses can be on the outside edge of side wall 138 of cylindrical cavity 132
The circumferentially extending directional spreding of pivot guide slot 140, so that obtain multi-rotor aerocraft can be every certain angle locking
In an expanded position.As can be seen that the cooperation of locating recesses and keeper can better lock onto multi-rotor aerocraft.
As shown in Figure 4 and Figure 5, pivot guide slot 140 can also have insertion opening 142, and it is located at rotation and is oriented to
The side of groove 140, for cause keeper 134 be inserted into pivot guide slot 140, for example along parallel to turn
The direction of shaft line is inserted into pivot guide slot 140.Insertion opening 142 is conducive to the assembling of multi-rotor aerocraft.
In certain embodiments, when multi-rotor aerocraft is assembled, can be close to each other by two rotor assemblies so that cylinder
Shape projection is mutually aligned with cylindrical cavity, and causes that keeper 134 and insertion opening 142 are mutually aligned.Right
After standard, continuation moves the two rotor assemblies along pivot center direction, so that cylindrical protrusions 130 are received into
In cylindrical cavity 132, while keeper 134 is entered into pivot guide slot 140 by insertion opening 142.It
Afterwards, can select to seal insertion opening 142, so as to avoid keeper 134 in opposite direction from pivot guide slot 140
Middle disengaging.So, keeper 134 is restricted to only can circumferentially move certain angle in pivot guide slot 140
Degree.
Pivot guide slot 140 can be along the circumferentially extending of cylindrical cavity 132, but circumferentially extending angle does not surpass typically
Cross 360 degree.In certain embodiments, pivot guide slot 140 circumferentially extends along the side wall 138 of cylindrical cavity 132
Angle is not less than 90 degree, for example, 90 degree, 120 degree, 135 degree, 150 degree, 170 degree or 180 degree.At some
In embodiment, pivot guide slot 140 can be equal to or more than 180 degree along the circumferentially extending of side wall 138 angle.At some
In embodiment, locking component can include along the axisymmetric two groups of pivot guide slots of pivot center and keeper, Yi Jike
Selection of land includes multiple locating recesses.This axisymmetric structure is more preferable in lock timing stability.
Pivot guide slot 140 can have two ends.As shown in figure 3, the position of insertion opening 142 can be set
An end 140a in pivot guide slot 140 is put, now, keeper 134 only can be towards the another of gathering sill 140
One end 140b directions are moved, or the movement from end 140b to end 140a again.In further embodiments,
Keeper 134 can also be arranged on the non-end position of pivot guide slot 140, such as centre position.Such case
Under, after such insertion, keeper 134 can be along the circumferentially extending direction of pivot guide slot 140 to end 140a or 140b
It is mobile.
The electronic system comprising electronic building bricks such as power supply, controller, motors is also mounted with multi-rotor aerocraft, is used for
Power is provided to multi-rotor aerocraft, and also can allow the user to manipulate the flight of multi-rotor aerocraft.Phase
Ying Di, multi-rotor aerocraft can have power switch, for controlling the electronic system to multi-rotor aerocraft to supply
Electricity.In certain embodiments, power switch can be come by user's manual manipulation, such as mode such as pressing, contact
So that the power switch is opened or closed.In further embodiments, power switch can also be by two rotor assemblies
Relative position change control.Specifically, power switch can be closed or disconnected by switch actuating component, when first
When rotor assemblies turn to a predetermined expanded position relative to the second rotor assemblies, the switch actuating component can be controlled
Power switch is closed, so as to powering electronic systems.
Fig. 7 to Fig. 9 shows the schematic diagram of the power switching operations of the multi-rotor aerocraft 100 shown in Fig. 1.Wherein,
Fig. 7 is the schematic diagram of the medial surface of the first supporting part；Fig. 8 is the partial schematic diagram of the medial surface of the second supporting part；Figure
9 is the partial schematic diagram of the second supporting part medial surface when power switch is closed.
As shown in fig. 7, being provided with electricity on the medial surface (i.e. towards the side of the second supporting part) of the first supporting part 106
Road plate 144, is provided with power switch 146.The power switch 146 can be push switch, when by object
After pressing, the power switch 146 can be closed；And when press its object leave after, the weight of power switch 146
It is new to disconnect.The surface that power switch 146 receives push action is set towards the second supporting part.In certain embodiments,
The surface of power switch 146 is slightly above the height in the medial surface of the first supporting part 106 major part region.
As shown in figure 8, being provided with the medial surface (i.e. towards the side of the first supporting part) of the second supporting part 110 convex
Block 148, it extends certain length from the medial surface towards the first supporting part.The projection 148 is for example in rib-like structure.
The circuit board 144 shown in Fig. 7 is also show in fig. 8, but for clarity of illustration, not shown in Fig. 8
First supporting part.Radial distance and power switch 146 to pivot center ZZ ' of the projection 148 to pivot center ZZ '
Radial distance is generally equalized.When required expanded position is not in, circuit board 144 and projection 148 are along first or the
There is angle in the rotation direction of two rotor assemblies, therefore projection 148 will not touch power switch 146.However, working as
When two rotor assemblies are rotated relatively to each other required expanded position (as shown in Figure 9), the top meeting of projection 148
Contact and pushing power switch 146, so that power switch 146 is closed.So, power switch 146 controls electricity
Source to powering electronic systems so that the rotor wing rotation of aircraft.This power switch sets and is very easy to make
The use of user.When needing to close multi-rotor aerocraft, user needs only to rotate it to closed position, this
When projection do not contact power switch, thus power supply is disconnected；When needing to open multi-rotor aerocraft, user can be with
The expanded position shown in Fig. 9 is rotated it to, to cause bump contact power switch, so that power switch is closed, and
And rotor rotational.It is appreciated that in certain embodiments, multi-rotor aerocraft can have multiple expanded positions, phase
Ying Di, a projection can be set corresponding to each expanded position, on the second supporting part, to enable power switch
Enough it is pressed closure.It is appreciated that circuit board 144 can also be arranged on the second supporting part, and projection 148 can
To be arranged on the first supporting part.
In some other embodiments, power switch can also use other structures, such as magnetic switch.Correspondingly,
Switch actuating component can also use corresponding trigger mechanism.For example, can correspondingly be set on the second supporting part 110
There is magnet.When expanded position is turned to, the magnetic field that magnet sends can drive magnetic switch to close, so that energy
Enough to powering electronic systems.
Although it should be noted that be referred to some modules or submodule of multi-rotor aerocraft in above-detailed,
It is that this division is merely exemplary rather than enforceable.In fact, according to embodiments herein, being described above
Two or more modules feature and function can be embodied in a module.Conversely, an above-described mould
The feature and function of block can be further divided into being embodied by multiple modules.
The those skilled in the art of those the art can be by studying specification, disclosure and accompanying drawing and appended
Claims, understand and implement to disclose implementation method other change.In the claims, word " bag
Include " other elements and step are not excluded for, and wording " one ", " one " are not excluded for plural number.Should in the reality of the application
In, the function of cited multiple technical characteristics in a possible perform claim requirement of part.Appointing in claim
What reference should not be construed as the limitation to scope.
Claims (21)
1. a kind of multi-rotor aerocraft, it is characterised in that including：
First rotor assemblies, it includes the first supporting part, and first group of rotor for being installed on first supporting part；
Second rotor assemblies, it includes the second supporting part, and second group of rotor for being installed on second supporting part；
Revolving member, it is configured as being pivotally connected first rotor assemblies and second rotor assemblies, so that
Obtaining first rotor assemblies and the second rotor assemblies can relatively rotate with respect to each other around a pivot center, wherein the rotation
Axis is perpendicular to first supporting part and the principal plane of second supporting part；And
Locking component, it is configured as first rotor assemblies and turns to one relative to second rotor assemblies
Or relative rotation between first rotor assemblies and second rotor assemblies is locked during multiple predetermined expanded positions.
2. multi-rotor aerocraft according to claim 1, it is characterised in that the revolving member is further configured
To allow first rotor assemblies to turn to predetermined closed position relative to second rotor assemblies, compared to being in
One or more of predetermined expanded positions, first rotor assemblies in the predetermined closed position and described
The overlapped region increase of two rotor assemblies.
3. multi-rotor aerocraft according to claim 2, it is characterised in that first rotor assemblies and described
Two rotor assemblies have identical circumferential profile.
4. multi-rotor aerocraft according to claim 1, it is characterised in that the revolving member includes being mutually matched
Pivot and axle sleeve, wherein, the axle sleeve be arranged on one among first supporting part and the second supporting part it
On, and the pivot be arranged on another among first supporting part and the second supporting part on.
5. multi-rotor aerocraft according to claim 4, it is characterised in that the pivot is arranged on described first
On supporting part, and the axle sleeve is arranged on second supporting part.
6. multi-rotor aerocraft according to claim 4, it is characterised in that the outside of the pivot has limiting card
Button, it is configured as limiting the relative position of both after the pivot is inserted into the axle sleeve, to avoid its mutual
Separate.
7. multi-rotor aerocraft according to claim 1, it is characterised in that first supporting part has cylinder
Projection, and second supporting part limits cylindrical cavity, the cylindrical cavity is configured as accommodating the cylinder
Projection, and the cylindrical protrusions overlap with the axis of the cylindrical cavity with the pivot center.
8. multi-rotor aerocraft according to claim 7, it is characterised in that the locking component includes：
Keeper, it stretches out from the lateral wall of the cylindrical protrusions；
Pivot guide slot, its side wall for being arranged on the cylindrical cavity, and along the side wall of the cylindrical cavity
Circumferentially extending, the pivot guide slot can accommodate the keeper and circumferentially be moved along the side wall of cylindrical cavity wherein
It is dynamic；
Wherein, when first rotor assemblies turn to a predetermined expanded position relative to second rotor assemblies,
Its described keeper can contact the side wall of the cylindrical cavity, and offer can lock first rotor assemblies
And the power of the second relative rotation between rotor assemblies.
9. multi-rotor aerocraft according to claim 8, it is characterised in that the pivot guide slot is opened with insertion
Mouthful, it is configured such that the keeper is inserted into the pivot guide slot.
10. multi-rotor aerocraft according to claim 8, it is characterised in that the keeper is by elastomeric material structure
Into.
11. multi-rotor aerocrafts according to claim 8, it is characterised in that the pivot guide slot is along the cylinder
The side wall circumferentially extending angle of shape cavity is not less than 90 degree.
12. multi-rotor aerocrafts according to claim 8, it is characterised in that the side wall of the cylindrical cavity has
One or more locating recesses, each described locating recesses are configured as first rotor assemblies relative to described
When two rotor assemblies turn to a predetermined expanded position, it can accommodate the end of the keeper, so as to lock institute
State the relative rotation between the first rotor assemblies and the second rotor assemblies.
13. multi-rotor aerocrafts according to claim 12, it is characterised in that one or more of locating recesses
The cylindrical cavity side-wall outer side along the pivot guide slot circumferentially extending directional spreding.
14. multi-rotor aerocrafts according to claim 12, it is characterised in that one or more of locating recesses
It is arranged on the side of the pivot guide slot.
15. multi-rotor aerocrafts according to claim 1, it is characterised in that first supporting part and described second
Supporting part includes two ends respectively, and first group of rotor includes being separately positioned on first supporting part two
Two rotors of end, and second group of rotor includes being separately positioned on second supporting part two the two of end
Rotor.
16. multi-rotor aerocrafts according to claim 15, it is characterised in that when first rotor assemblies are relative
When a predetermined expanded position during second rotor assemblies turn to one or more of predetermined expanded positions,
Two lines of centres of rotor and two line of centres phases of rotor in second group of rotor in first group of rotor
It is mutually vertical.
17. multi-rotor aerocrafts according to claim 16, it is characterised in that first rotor assemblies and described
Second rotor assemblies have identical circumferential profile, and the revolving member is further configured to allow first rotor
Component turns to predetermined closed position relative to second rotor assemblies, in the predetermined closed position, described first
Together with rotor assemblies are overlapped with the circumferential profile of second rotor assemblies.
18. multi-rotor aerocrafts according to claim 1, it is characterised in that also include：
Power switch, it is arranged to power supply supply of the control to first group of rotor and second group of rotor.
19. multi-rotor aerocrafts according to claim 18, it is characterised in that the power switch is configured as
When first rotor assemblies turn to one or more of predetermined expanded positions relative to second rotor assemblies
Allow the powering electronic systems to the multi-rotor aerocraft；And work as first rotor assemblies relative to the described second rotation
Wing component forbids the powering electronic systems to the multi-rotor aerocraft when not turning to predetermined expanded position.
20. multi-rotor aerocrafts according to claim 19, it is characterised in that the power switch is arranged on institute
State on the medial surface of the second supporting part, and the medial surface of first supporting part includes one or more switch actuating structures
Part, it is described when first rotor assemblies turn to a predetermined expanded position relative to second rotor assemblies
One in one or more switch actuating components can control the power switch to close.
21. multi-rotor aerocrafts according to claim 20, it is characterised in that the switch actuating component includes convex
Block or magnet.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201511026583.6A CN106927026A (en) | 2015-12-31 | 2015-12-31 | Multi-rotor aerocraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201511026583.6A CN106927026A (en) | 2015-12-31 | 2015-12-31 | Multi-rotor aerocraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106927026A true CN106927026A (en) | 2017-07-07 |
Family
ID=59441283
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201511026583.6A Pending CN106927026A (en) | 2015-12-31 | 2015-12-31 | Multi-rotor aerocraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106927026A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109896002A (en) * | 2019-02-14 | 2019-06-18 | 西安理工大学 | A kind of deformable quadrotor |
-
2015
- 2015-12-31 CN CN201511026583.6A patent/CN106927026A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109896002A (en) * | 2019-02-14 | 2019-06-18 | 西安理工大学 | A kind of deformable quadrotor |
| CN109896002B (en) * | 2019-02-14 | 2020-12-18 | 西安理工大学 | Deformable four-rotor aircraft |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN205366057U (en) | Multi -rotor aircraft | |
| CN205499336U (en) | Screw, motor, power suit and unmanned vehicles | |
| WO2022194141A1 (en) | Folding mechanism, support structure and electronic device | |
| CN103253383B (en) | Bilateral double-spring driving unfolding mechanism | |
| CN108609205A (en) | Homologous connects separator and system | |
| AU2016348095B2 (en) | Flying object | |
| CN106927026A (en) | Multi-rotor aerocraft | |
| CN105971962B (en) | A kind of motor-driven single spool rotary type hydraulic valve of list | |
| CN108756509A (en) | A kind of panel handle structure of the convenient commutation function of band | |
| CN104975765B (en) | Electromechanical connector construction and method with magnetic rotary switch | |
| CN110879643B (en) | Hinge structure and foldable electronic equipment | |
| CN206766325U (en) | Folding device and unmanned plane | |
| CN205906206U (en) | Wing connecting device , wing and aircraft | |
| CN105818974B (en) | Unmanned plane with detachable rotor structure | |
| CN109236709A (en) | Fan | |
| EP3741905B1 (en) | Door assembly of laundry treatment device and laundry treatment device | |
| CN205499354U (en) | Screw, motor, power suit and unmanned vehicles | |
| CN205602094U (en) | Foot rest structure and aircraft of aircraft | |
| CN105099098A (en) | Separating device for motor end covers and stators | |
| CN113098205B (en) | Rotary transformer and new energy automobile motor | |
| CN107237816A (en) | Hinge and the office machine for possessing the hinge | |
| JP2022521756A (en) | Connection assembly and mobile terminal | |
| CN106114816A (en) | A kind of wing attachment means, wing and aircraft | |
| KR102009515B1 (en) | Foldable Drone And Method for Working the Same | |
| WO2022206852A1 (en) | Tiltable wing and unmanned aerial vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170707 |
|
| WD01 | Invention patent application deemed withdrawn after publication |