CN206358357U - Multi-rotor aerocraft - Google Patents
Multi-rotor aerocraft Download PDFInfo
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- CN206358357U CN206358357U CN201621494164.5U CN201621494164U CN206358357U CN 206358357 U CN206358357 U CN 206358357U CN 201621494164 U CN201621494164 U CN 201621494164U CN 206358357 U CN206358357 U CN 206358357U
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- Prior art keywords
- protective cover
- fuselage
- propeller
- rotor aerocraft
- fold
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Abstract
The utility model provides a kind of multi-rotor aerocraft; the aircraft includes fuselage; and it is connected to multiple propeller protective covers of fuselage; it is characterized in that; at least one in the multiple propeller protective cover is that can fold protective cover; each protective cover that can fold is connected to the top edge or lower edge of fuselage and with a collapse state and a deployed condition; protective cover can be folded described under collapse state to be collapsed in above or below the fuselage, the protective cover that folds stretches out from the week side of boss of the fuselage in the deployed state.The propeller protective cover that the utility model embodiment is provided can reduce the potential safety hazard of aircraft, can extend aircraft cruising time, and be convenient for carrying.
Description
Copyright notice
This patent document disclosure includes material protected by copyright.The copyright is all for copyright holder.Copyright
Owner does not oppose that anyone replicates the patent document in the presence of the proce's-verbal of Patent＆Trademark Office and archives or should
Patent is disclosed.
Technical field
The utility model is related to multi-rotor aerocraft, more particularly to the multi-rotor aerocraft that propeller protective cover can be folded.
Background technology
Multi-rotor aerocraft generally comprises fuselage and the multiple rotor structures circumferentially stretched out by fuselage, each rotor structure
It is made up of horn and the Power Component that is supported via horn.For ease of carrying, horn is foldable to fuselage both sides.To ensure peace
Entirely, some aircraft high to security requirement, such as aircraft for auto heterodyne generally can also install protective cover, prior art additional
In, protective cover is generally superimposed on horn, is added after protective cover, can shorten the cruising time of aircraft, also tends to make in addition
The folding mode failure of horn, causes aircraft to be inconvenient to carry.On the other hand, some protective covers are detachable protective cover,
User first can unload protective cover before aircraft is carried, then horn is folded into fuselage side.So, such a mode is carried every time
Before be both needed to dismantle protective cover, still bring inconvenience to user, and horn is folded to the mode of fuselage both sides, can limit fuselage
Width, the battery for preventing fuselage bigger from loading influences aircraft cruising time.
Utility model content
In view of this, it is necessary to propose a kind of multi-rotor aerocraft, to solve above-mentioned and other potential problems.
A kind of multi-rotor aerocraft, the aircraft includes fuselage, and is connected to multiple propeller protective covers of fuselage,
It is each described to fold protective cover characterized in that, at least one in the multiple propeller protective cover is can fold protective cover
It is connected to the top edge or lower edge of fuselage and with a collapse state and a deployed condition, it is described under collapse state to fold
Protective cover is collapsed in above or below the fuselage, and the protective cover that folds is from the week of the fuselage in the deployed state
Side is stretched out.
Further, each propeller protective cover includes a connecting portion, and the propeller protective cover passes through the connecting portion
It is connected to the top edge or lower edge of the fuselage.
Further, each connecting portion that can fold protective cover rotates the top edge or following for being connected to the fuselage
Edge, so that the protective cover that folds can be converted between deployed condition and collapse state.
Further, the protective cover that folds is at least a pair, and two partnered can fold protective cover and split institute
State the relative both sides of fuselage and in wrong high distribution.
Further, it is each described to fold the connecting portion of protective cover with around the course axle of the parallel aircraft or roll
The rotatable mode of rotary shaft of axle is connected to the fuselage, so that the protective cover that folds can be in deployed condition with folding shape
Converted between state.
Further, under collapse state, two partnered can fold protective cover perpendicular to aircraft course axle
Direction have it is overlapping.
Further, two partnered can fold protective cover be placed under collapse state the fuselage top with
Lower section.
Further, the protective cover that folds is at least two pairs, and two centerings are located at fuselage the same side and adjacent two
Protective cover can be folded to be placed under collapse state the top and lower section of the fuselage.
Further, each protective cover that can fold includes one locking-unlocking structure, and the locking-unlocking structure is solid
Surely be arranged at it is described can fold on the connecting portion of protective cover, movable be connected between the fuselage, for can described in fixed
Position of the protective cover relative to the fuselage is folded, and for the propeller protective cover to be untied from fixed position, so that
The connecting portion can drive the propeller protective cover to be rotated around the rotary shaft.
Further, at least one in the multiple propeller protective cover is the one-piece type protective cover of hood, each machine
Covering one-piece type protective cover includes cover body and motor base, and the cover body is fixedly connected and supports the motor base, the motor
Pedestal is used to load an at least motor, and the motor is used to drive the propeller of the aircraft to rotate.
Further, the cover body also includes a guard ring, and the guard ring is fixedly connected and propped up by multiple fastening members
Support the motor base.
Further, at least fastening member in the multiple fastening member is hollow structure, for for controlling the motor
Controlling cable pass through.
Further, the nearest fastening member of fuselage described in distance is hollow structure in the multiple fastening member.
Further, it is in be angularly distributed between the fastening member；And/or, the fastening member is rib.
Further, the multiple propeller protective cover is that can fold protective cover and the one-piece type protective cover of hood.
Further, the multiple propeller protective cover is divided into two pairs or multipair, and two of each pair can fold protective cover point
It is placed in the relative both sides of the fuselage and in wrong high distribution.
Further, the multi-rotor aerocraft is to include the quadrotor of four propeller protective covers.
Further, one pair of which propeller protective cover close to fuselage head, be arranged at fuselage both sides, another pair propeller
Protective cover close to afterbody, be arranged at fuselage both sides.
Further, close to fuselage head a pair of propeller protective covers be placed under collapse state fuselage top with
Lower section and overlapping perpendicular to the direction of course axle；Close to afterbody a pair of propeller protective covers under collapse state also
Be placed in fuselage top with lower section and overlapping perpendicular to the direction of course axle.
Further, be arranged at two propeller protective covers of fuselage the week side of boss the same side be placed in fuselage top with
Side.
The multi-rotor unmanned aerial vehicle that the utility model embodiment is provided, is folded to fuselage upper and lower, both by propeller protective cover
User's carrying is facilitated, and does not interfere with fuselage width, makes more big battery can be installed in fuselage, so as to extend aircraft continuation of the journey
Time.
Brief description of the drawings
, below will be in the utility model embodiment in order to illustrate more clearly of the technical scheme of the utility model embodiment
The required accompanying drawing used is briefly described, it should be apparent that, drawings in the following description are only of the present utility model one
A little embodiments, for those of ordinary skill in the art, on the premise of not paying creative work, can also be according to these
Accompanying drawing obtains other accompanying drawings.
Fig. 1 is schematic top plan view of the quadrotor in deployed condition in the embodiment of the utility model one.
Fig. 2 is the schematic top plan view that quadrotor shown in Fig. 1 is in collapse state.
Fig. 3 is the front-view schematic diagram that quadrotor shown in Fig. 1 is in deployed condition.
Fig. 4 is the front-view schematic diagram that quadrotor shown in Fig. 1 is in collapse state.
Fig. 5 is the schematic side view that quadrotor shown in Fig. 1 is in deployed condition.
Fig. 6 is the schematic side view that quadrotor shown in Fig. 1 is in collapse state.
Fig. 7 is schematic top plan view of three rotor crafts in deployed condition in the embodiment of the utility model one.
Fig. 8 is the schematic top plan view that three rotor crafts shown in Fig. 7 are in collapse state.
Fig. 9 is schematic top plan view of the six rotorcraft in deployed condition in the embodiment of the utility model one.
Figure 10 is the schematic top plan view that three rotor crafts shown in Fig. 9 are in collapse state.
Figure 11 is the propeller protective cover expansion of the multi-rotor aerocraft in the embodiment of the utility model one and/or folded
The flow chart of method.
Main element symbol description
Aircraft 10,20,30
Fuselage 110,210,310
Rotor structure 120,220,320
Propeller protective cover 121,221,321
Cover body 122
Motor base 123
Fastening member 124
Guard ring 125
Connecting portion 126,227,327
Course axle Y, Ya, Yb
Roll axle X, Xb
Head 111,211,311
Afterbody 112,212,312
Middle part 313
Step 41-43
Following embodiment will further illustrate the utility model with reference to above-mentioned accompanying drawing.
Embodiment
Below in conjunction with the accompanying drawing in the utility model embodiment, the technical scheme in the utility model embodiment is carried out
Clearly and completely describe, it is clear that described embodiment is only a part of embodiment of the utility model, rather than whole
Embodiment.Based on the embodiment in the utility model, those of ordinary skill in the art are not under the premise of creative work is made
The every other embodiment obtained, belongs to the scope of the utility model protection.
It should be noted that when component is referred to as " being fixed on ", " being installed on " another component, it can be directly another
On individual component or there can also be a component placed in the middle.When a component is considered as " being arranged at " another component, it can be with
It is to be set directly on another component or may be simultaneously present component placed in the middle.Term as used herein " and/or " include
All arbitrary and combinations of one or more related Listed Items.
Illustrated below by taking quadrotor and its propeller protective cover used as an example.
Refer to shown in Fig. 1-Fig. 6, the quadrotor 10 includes fuselage 110 with being connected to four of fuselage 110
Rotor structure 120, each rotor structure 120 includes a propeller protective cover 121.In following specific descriptions, for convenience of description,
" top of fuselage ", " lower section of fuselage " and " the week side of boss of fuselage " etc. can be used to express the word in orientation, wherein " fuselage
Top " refer to along aircraft course axle direction, the locus on fuselage, " lower section of fuselage " refer to along fly
Row device course axle direction, the locus under fuselage, " the week side of boss of fuselage " refers to six space of planes for surrounding fuselage
Behind the top and lower section that remove fuselage, any one or more locus in remaining four space of planes all around.
In the present embodiment, each propeller protective cover 121 is machine (" motor base ") cover (" protective cover ") one
Type protective cover, including cover body 122 and the motor base 123 that is connected and is supported by cover body 122 with cover body 122.The motor base
Seat 123 is located at the center of the cover body 122, the Power Component (not shown) for installing the aircraft 10.It is described dynamic
Power component includes the propeller set of aircraft 10 and drives the motor (not shown) of propeller set rotation.Specifically, motor
It is installed on the motor base 123, propeller set is installed on the motor shaft of motor again.In one embodiment, institute
State motor base 123 and load a motor, the motor shaft of the motor is extended downwardly from, drive and be located under the motor base 123
The propeller set rotation of side.In another embodiment, the motor shaft of the motor is protruded upward, and is driven and is located at the electricity
The propeller set rotation of the top of machine pedestal 123.In another embodiment, the motor base 123 loads two motors,
The motor shaft of a wherein motor is extended downwardly from, and drives the propeller set rotation for being located at the lower section of motor base 123, Ling Yi electricity
The motor shaft of machine is protruded upward, and the propeller set rotation for being located at the top of motor base 123 is driven, in this way, making aircraft
Standby motor more than 10 and spare propeller device.In the 4th kind of embodiment, the motor base 123 loads two electricity
Machine, described two motor coaxles drive a propeller set rotation.
Be fixedly connected between the cover body 122 and motor base 123 by fastening member 124, with support motor base 123 with
And the Power Component that motor base 123 is loaded.The cover body 122 includes a guard ring 125, and the guard ring 125 is located at motor
The outer circumferential of pedestal 123, in one embodiment, wraps up overcoat (not indicating) on the guard ring 125.The protection
Layer is made up of elastomeric material, for example, the overcoat can be by highly elastic material such as polypropylene plastics expanded material or foaming
Polystyrene polyethylene hybrid scheme into.
It is fixedly connected between the guard ring 125 and motor base 123 by fastening member 124.Further, the protection
It can be made between circle 125, fastening member 124 and motor base 123 by being integrally formed.The quantity of the fastening member 124 can
Think multiple, below exemplified by four.Wherein at least one fastening member 124 is hollow, for from the control of the inside of fuselage 110
Cable (not shown) processed reaches the motor for being loaded into motor base 123 via the fastening member 124.In one embodiment, distance
A nearest fastening member 124 of fuselage 110 is hollow structure.Four fastening members 124 be generally aligned in the same plane in, in angularly dividing
Cloth, to reduce the influence to rotor air-flow, extends the cruising time of aircraft 10.In other embodiments, consolidate for described four
Even part 124 can be located in Different Plane, such as the end points that each fastening member 124 is fixedly connected with motor base 121 connects with fixed
Take over control between the end points of guard ring 125 between slightly difference in height, every two adjacent fastening member 124 that angle is identical or substantially identical, make solid
It is in even to be angularly distributed between part 124.In other embodiments, it can also be other quantity and in being connected for being angularly distributed
Part 124 is fixedly connected with motor base 123 and guard ring 125,5,6 such as 2,3 or more.The fastening member
124 be rib in one embodiment.
Each propeller protective cover 120 also includes a connecting portion 126, and the connecting portion 126 is located at outside the guard ring 125
Side, the propeller protective cover is connected to fuselage 110 by the connecting portion 126.
In the present embodiment, the propeller protective cover 120 is that can fold protective cover, including as shown in Fig. 1,3,5
Deployed condition and Fig. 2,4,6 shown in collapse state.The connecting portion 126 is rotary type connecting portion, is arranged at fuselage 110
Top edges or lower edge, can be around the rotary shaft rotation parallel to the course axle Y of aircraft 10, so as to allow to protect on propeller
Shield 120 switches between deployed condition and collapse state.
In one embodiment, correspond to each propeller protective cover 120, the top edges of fuselage 110 or under
Method, edge is correspondingly arranged a rotating shaft (not shown) parallel to the course axle Y of aircraft 10 direction, and the rotating shaft can be sitting at machine
In the top edges of body 110 or lower edge, or the position positioned at the top edges of fuselage 110 or lower edge in the middle of fuselage
Put.The connecting portion 126 of the propeller protective cover 120 includes a hole position (not shown), and the rotating shaft is sheathed on by the hole position
Above and around rotating shaft rotation.One locking-unlocking structure (not shown), the locking-unblock are also set up on each connecting portion 126
Structure can be folded on the connecting portion of protective cover described in being fixedly installed on, and be connected between the fuselage for movable, described
Propeller protective cover is locked in the position, Yi Ji by locking-unlocking structure when propeller protective cover 120 is located at ad-hoc location
Propeller protective cover 120 is untied from fixed position, can be (i.e. described around the rotary shaft parallel to the course axle Y of aircraft 10
Rotating shaft) rotate.In one embodiment, the locking-unlocking structure can be one towards fuselage 110 on connecting portion 126
Projection (not shown) and the fastener for being sheathed on projection end, the projection and the stopper slot (not shown) phase on fuselage 110
Coordinate, the two ends of stopper slot correspond to two states of propeller protective cover 120 respectively：Deployed condition and collapse state.In expansion
Under state, propeller protective cover 120 is fixed on the deployed condition by tightening fastener parts；Switched to by propeller protective cover 120
During collapse state, fastener is loosened, propeller protective cover 120 is rotated to collapse state along stopper slot, then tightening fastener parts will
Propeller protective cover 120 is fixed on the collapse state.In another embodiment, the locking-unlocking structure can be set
In the hole position on connecting portion 126 and the pin with the hole position close-fitting, the connecting portion 126 is located on the fuselage 110
Method, edge or lower edge are located at rotating shaft both sides on the position at center, the fuselage 110 has a hole position, the hole respectively
Position also can with pin close-fitting, wherein, the expansion shape of nearer apart from the fuselage edge hole position correspondence propeller protective cover 120
State, propeller protective cover 120 is rotated to the hole position on connecting portion 126 and is directed at the hole position, recycles the hole of pin insertion alignment
Propeller protective case 120 is fixed on this position by position.Apart from the receipts of the hole position correspondence propeller protective cover 120 of fuselage edge farther out
Conjunction state, when propeller protective cover 120 is switched into collapse state, unclamps pin, and propeller protective cover 120 is rotated to even
Hole position in socket part 126 is directed at the hole position apart from fuselage edge farther out, recycles pin to fix.
Refer to shown in Fig. 2,4,6, under collapse state, the propeller protective cover 120 is collapsed in the upper of fuselage 110
Side or lower section.Further, the top of fuselage 110 is partially disposed in the propeller protective cover 120, another part is placed in fuselage
110 lower section.Yet further, the propeller protective cover 120 is divided into two pairs, two pairs may be contained within fuselage 110 left and right
Both sides, first pair close to the head 111 of fuselage 110, second pair of afterbody 112 close to fuselage 110.First pair of propeller protective cover
120 in wrong high setting, if the plane perpendicular to the course axle Y of aircraft 10 is horizontal plane, first pair of two propeller protective covers
120 are located on the horizontal plane of different height, i.e., in wrong high setting, are so in first pair of propeller protective cover 120 and fold shape
During state, energy is overlapped or partly overlaps.In the present embodiment, first pair of one of propeller protective cover 120 is connected
In the lower right-hand side edge of fuselage 110, it is rotated collapsing in the lower section of fuselage 110；Another propeller protective cover 120 is connected to
The top edges in the left side of fuselage 110, are rotated collapsing in the top of fuselage 110, fold the latter two in parallel course axle Y direction
Above have overlapping.Second pair of propeller protective cover 120 is equally in wrong high setting, second pair of two propeller protective covers 120
In on the horizontal plane of different height, one of them is connected to the top edges on the right side of fuselage 110, and another is connected to fuselage 110
The lower edge in left side, folds the latter two and is located at respectively above and below fuselage 110, and on parallel course axle Y direction
With overlapping.Further, the left side of line cutting fuselage 110 and right side centered on the roll axle of fuselage 110, positioned at fuselage 110
Two propeller protective covers 120 of the same side are equally in wrong high setting, that is to say, that two spirals positioned at the left side of fuselage 110
Oar protective cover 120 is in wrong high setting, such as in Fig. 1-6 illustrated embodiments, and two propellers positioned at the left side of fuselage 110 are protected
In shield 120, wherein the propeller protective cover 120 close to head 111 is connected to the top edges of fuselage 110, it is located at after folding
The top of fuselage 110, close to the connection of propeller protective cover 120 and the lower edge of fuselage 110 of afterbody 112, is located at after folding
The lower section of fuselage 110；Another two propeller protective cover 120 positioned at the right side of fuselage 110 is equally also in wrong high setting, in this way, appointing
One propeller protective cover 120 corresponding thereto and two adjacent propeller protective covers 120 in wrong high setting, so not only
Can be tried one's best the reduction lateral dimension of aircraft 10 when folding, and aircraft center of gravity can be also balanced in the flight course of aircraft 10.
The structure of propeller protective cover, original in the utility model embodiment are illustrated by taking quadrotor as an example above
Reason.So, it can be seen that the propeller protective cover in the utility model embodiment can be applied equally to other multi-rotor aerocrafts
On, such as three rotors, six rotors, eight rotors on aircraft.
Refering to shown in Fig. 7 and Fig. 8, being one or three rotor crafts 20, three rotor craft 20 is including fuselage 210 with connecting
It is connected to three rotor structures 220 of fuselage 210.One of rotor structure 220 is located at the head 211 of fuselage 210, another pair rotation
Wing structure 220 is located at the afterbody 212 of fuselage 210.Each rotor structure 220 includes a propeller protective cover 221, the propeller
Protective cover 221 can be the one-piece type protective cover of hood, can not also be all the one-piece type protective cover of hood, for example, positioned at head
The propeller protective cover 221 in portion 211 can not be the one-piece type protective cover of hood.The propeller protective cover 221 can be can
Protective cover is folded, can also be not all can fold protective cover, for example, the propeller protective cover 221 positioned at head 211 can not be
Protective cover can be folded.In the present embodiment, three propeller protective covers 221 are the one-piece type protective cover of hood and can folded
Protective cover.Each propeller protective cover 221 is turnably connected to fuselage 210 by a connecting portion 227, passes through the connecting portion
227 can switch propeller protective cover 221 between the collapse state shown in the deployed condition and Fig. 8 shown in Fig. 7.Connecting portion
227 also include one locking-unlocking structure (not shown) simultaneously, and the locking-unlocking structure coordinates the corresponding knot on fuselage 210
Structure, deployed condition or collapse state are fixed on by propeller protective cover 221.
In the present embodiment, the connecting portion 227 positioned at the propeller protective cover 221 on head 211 is arranged at fuselage 210
Top edge, therefore, the propeller protective cover 221 collapses in the top of fuselage 211 under collapse state, certainly, in other implementations
In mode, the connecting portion 227 of the propeller protective cover 221 can be arranged at the lower edge of fuselage 210 so that the propeller
Protective cover 221 collapses in the lower section of fuselage 210.Positioned at the connecting portion 227 1 of a pair of propeller protective covers 221 of afterbody 212
Be arranged at the top edge of fuselage 210, one be arranged at fuselage 210 lower edge, so make two propeller protective covers 221 in machine
The both sides of body 210 are in wrong high arrangement, when folding, one collapse in fuselage 210 top, one collapse in fuselage 210 lower section,
The two has overlapping in the direction perpendicular to the course axle Ya of aircraft 20.
Refering to shown in Fig. 9 and Figure 10, being a six rotorcraft 30, the six rotorcraft 30 include fuselage 310 with
Six rotor structures 320 of fuselage 310 are connected to, wherein first pair of rotor structure 320 is located at the head 311 of fuselage 310, second
It is located at the afterbody 312 of fuselage 310 to rotor structure 320, the 3rd pair of rotor structure 320 is located at the middle part 313 of fuselage 310.Each
Rotor structure 320 includes a propeller protective cover 321, and the propeller protective cover 321 can be the one-piece type protection of hood
Cover, can not also be all the one-piece type protective cover of hood, for example, positioned at head 311 and/or the propeller protective cover of afterbody 312
321 can be other kinds of protective cover.The propeller protective cover 321 can fold protective cover, can not also be complete
All it is that can fold protective cover, or, although it can fold, but the week side of boss of fuselage 310, example can be collapsed according to actual conditions
Such as, the propeller protective cover 321 positioned at head 311 and/or afterbody 312 can otherwise collapse in the week side of boss of fuselage 310.
In present embodiment, six propeller protective covers 321 are the one-piece type protective cover of hood and can fold protective cover, each spiral
Oar protective cover 321 is turnably connected to fuselage 310 by a connecting portion 327, can be protected propeller by the connecting portion 327
Shield 321 switches between the collapse state shown in the deployed condition and Fig. 8 shown in Fig. 7.Connecting portion 327 also includes a lock simultaneously
Gu-unlocking structure (not shown), the locking-unlocking structure coordinates the corresponding construction on fuselage 310, by propeller protective cover
321 are fixed on deployed condition or collapse state.
In the present embodiment, the connecting portion 327 1 positioned at a pair of propeller protective covers 321 on head 311 is arranged at
The top edge of fuselage 310, one be arranged at fuselage 310 lower edge, so make two propeller protective covers 321 in fuselage 310
Both sides are in wrong high arrangement, when folding, one collapse in fuselage 310 top, one collapse in fuselage 310 lower section, the two
Have in the direction perpendicular to the course axle Yb of aircraft 30 overlapping.Positioned at the connection of a pair of propeller protective covers 321 of afterbody 312
The top edge that 327 1, portion is arranged at fuselage 310, one be arranged at fuselage 310 lower edge, so make the protection of two propellers
Cover 321 in the both sides of fuselage 310 in wrong high arrangement, when folding, one collapse in fuselage 310 top, one collapses in fuselage
310 lower section, the two has overlapping in the direction perpendicular to the course axle Yb of aircraft 30.Likewise, a pair positioned at middle part 313
The top edge that the connecting portion 327 1 of propeller protective cover 321 is arranged at fuselage 310, one is arranged at the following of fuselage 310
Edge, so makes two propeller protective covers 321 in the both sides of fuselage 310 in wrong high arrangement, when folding, one collapses in fuselage
310 top, one collapse in fuselage 310 lower section, the two has overlapping in the direction perpendicular to the course axle Yb of aircraft 30.
In the present embodiment, the left side of line cutting fuselage 310 and right side centered on the roll axle Xb of fuselage 310, same positioned at fuselage 310
Three propeller protective covers 321 of side are by the mistake for from head 311 to the order of afterbody 312 being in respectively previous-next-up or down-previous-next
High setting, for example, positioned at left side three propeller protective covers 321 from head 311 to afterbody 312 respectively in previous-next-on mistake
High setting, positioned at three propeller protective covers 321 on right side be in respectively to afterbody 312 from head 311 under-the wrong height of previous-next sets
Put, in this way, also in wrong high arrangement between making any two adjoining spiral oar protective covers 321 of either side, it is to avoid adjoining spiral oar
The problem of protective cover 321 is interfered after folding, while fuselage 310 can also be allowed smaller more compact.
In the embodiment of above-mentioned introduction, although quadrotor 10, three rotor crafts 20 and six rotor flyings
Each propeller protective cover of device 30 is the one-piece type protective cover of hood and can fold protective cover, however, in other embodiments,
Any propeller protective cover of aircraft can be only the one-piece type protective cover of hood, and need not be simultaneously above-described embodiment
What is illustrated fold protective cover, or, propeller protective cover can be folded, but fold mode can be with being introduced in above-described embodiment
Difference, for example, collapse in before and after fuselage both sides or fuselage.In addition, in multiple rotors of aircraft, also may be used according to actual needs
To be the one-piece type protective cover of hood that part rotor uses the utility model embodiment to introduce, another part rotor still continues to use existing skill
The mode that horn in art is provided separately with protective cover, for example, support motor base, protective cover is supported in motor base again by horn
On seat；Furthermore, can also be that part rotor folds protective cover using the utility model embodiment introduction according to actual needs,
Another part rotor use other modes fold or rotor and fuselage between to be fixedly connected, can not fold.In part, rotor is adopted
It can be folded in the scheme of protective cover, can also be subdivided into the one-piece type protective cover of hood and part or all of rotor use：Hood
One-piece type protective cover is for example applied to the rotor of three rotor crafts simultaneously with that can fold protective cover applied on same rotor
On A, B, C；The one-piece type protective cover of hood is applied on different rotors from that can fold protective cover, the one-piece type protective cover of such as hood
It is applied to applied to protective cover on the rotor A of three rotor crafts, can be folded on rotor B, C；The one-piece type protective cover of hood with can
The rotor for folding protective cover application partly overlaps, the one-piece type protective cover of such as hood be applied to the rotor A of quadrotor, B,
On C, protective cover can be folded and be applied on rotor B, C, D, furthermore the one-piece type protective cover of such as hood is applied to quadrotor
Rotor A on, can fold protective cover applied to rotor A, B, C, D it is first-class.
It is stacked protective cover rotation will can be folded in the scheme above or below fuselage, can also according to actual conditions
Using will can fold protective cover around parallel to aircraft roll axle rotary shaft rotation by the way of.
Refering to shown in Figure 11, be multi-rotor aerocraft in an embodiment propeller protective cover expansion and/or fold
Method, including：
S41：One propeller protective cover is unlocked in first position, the propeller protective cover is revolved around a rotary shaft
Turn, the course axle or roll axle of the parallel multi-rotor aerocraft of the rotary shaft；
S42：Rotary shaft around the multi-rotor aerocraft rotates the propeller protective cover to the second place；And
S43：The propeller protection is locked in the second place to cover on fuselage, makes the propeller protective cover can not
Rotary shaft around the multi-rotor aerocraft rotates；
Wherein, when the propeller protective cover is located at one of them in first position and the second place, the propeller
Protective cover is located at the week side of boss of fuselage, described when the propeller protective cover is located at another in first position and the second place
Propeller protective cover is located above or below fuselage.
In another embodiment, methods described can also include step：By a pair of propeller protective covers be separately folded to
The top and lower section of fuselage.
In another embodiment, methods described can also include step：Fuselage periphery opposite sides will be located at respectively
A pair of propeller protective covers are separately folded to the top of fuselage and lower section and are locked on fuselage.
In another embodiment, methods described can also include step：Fuselage periphery opposite sides will be located at respectively
A pair of propeller protective covers are separately folded to the top of fuselage and lower section, continue to rotate the pair of propeller protective cover make its
Direction perpendicular to course axle is overlapping, and the pair of propeller protection of locking is covered on fuselage.
In another embodiment, methods described can also include step：It will be close to fuselage head and be located at fuselage respectively
A pair of propeller protective covers 121 of the week side of boss opposite sides, are separately folded to the top of fuselage and lower section and are locked on fuselage.
In another embodiment, methods described can also include：It will be close to afterbody and be located at fuselage the week side of boss respectively
A pair of propeller protective covers of opposite sides, are separately folded to the top of fuselage and lower section and are locked on fuselage.
In another embodiment, methods described also includes：It will be close to waist and relative positioned at fuselage the week side of boss respectively
A pair of propeller protective covers of both sides, are separately folded to the top of fuselage and lower section and are locked on fuselage.
In another embodiment, methods described can also include：Will be adjacent positioned at two of fuselage the week side of boss the same side
Propeller protective cover, is separately folded to the top of fuselage and lower section.
In another embodiment, methods described can also include step：The propeller is unlocked in the second place
Protective cover, makes the propeller protective cover to be rotated around the rotary shaft；The propeller protective cover is revolved around the rotary shaft
Go to the first position；And
The propeller protection is locked in the first position to cover on fuselage, makes the propeller protective cover can not be around institute
State the rotary shaft rotation of multi-rotor aerocraft.
In summary, the multi-rotor aerocraft of the utility model embodiment, due to directly replacing traditional using protective cover
Horn supports motor base, and then supports the Power Component of aircraft, not only solves extremely sensitive to security some
The potential safety hazard that aircraft is brought, and due to saving horn, compared to the unmanned plane that traditional existing horn has protective cover, weight again
Amount can be lighter and overlaying influence will not be produced to rotor air-flow, thus does not interfere with the cruising time of aircraft, in addition, originally
Propeller protective cover is carried out wrong high setting by utility model embodiment, is separately folded in fuselage upper and lower, is both facilitated user
Carry, and do not interfere with fuselage width, make more big battery can be installed in fuselage, so as to extend aircraft cruising time.
Finally it should be noted that above example is only unrestricted to illustrate the technical solution of the utility model, although
The utility model is described in detail with reference to preferred embodiment, it will be understood by those within the art that, can be right
The technical solution of the utility model is modified or equivalent substitution, without departing from the spirit and model of technical solutions of the utility model
Enclose.
Claims (20)
1. a kind of multi-rotor aerocraft, it is characterised in that the aircraft includes fuselage, and is connected to multiple spirals of fuselage
Oar protective cover, it is characterised in that at least one in the multiple propeller protective cover is each described to receive for that can fold protective cover
Close protective cover and be connected to the top edge or lower edge of fuselage and with a collapse state and a deployed condition, the institute under collapse state
Protective cover can be folded and collapsed in above or below the fuselage by stating, and the protective cover that folds is from described in the deployed state
The week side of boss of fuselage is stretched out.
2. multi-rotor aerocraft as claimed in claim 1, it is characterised in that each propeller protective cover includes a connecting portion,
The propeller protective cover is connected to the top edge or lower edge of the fuselage by the connecting portion.
3. multi-rotor aerocraft as claimed in claim 2, it is characterised in that each connecting portion that can fold protective cover turns
The dynamic top edge or lower edge for being connected to the fuselage so that it is described fold protective cover can deployed condition and collapse state it
Between convert.
4. multi-rotor aerocraft as claimed in claim 3, it is characterised in that the protective cover that folds is at least a pair, group
Two in a pair can fold protective cover and split the relative both sides of the fuselage and in wrong high distribution.
5. multi-rotor aerocraft as claimed in claim 4, it is characterised in that each connecting portion that can fold protective cover with
The fuselage is connected to around the rotatable mode of the rotary shaft of course axle or roll axle of the parallel aircraft, so that described can
Folding protective cover can convert between deployed condition and collapse state.
6. multi-rotor aerocraft as claimed in claim 5, it is characterised in that under collapse state, two partnered can
Fold protective cover have in the direction perpendicular to aircraft course axle it is overlapping.
7. multi-rotor aerocraft as claimed in claim 6, it is characterised in that two partnered can fold protective cover in receipts
Be placed in the top and lower section of the fuselage under conjunction state.
8. multi-rotor aerocraft as claimed in claim 7, it is characterised in that the protective cover that folds is at least two pairs, two
Centering be located at fuselage the same side and adjacent two can fold protective cover be placed under collapse state the fuselage top with
Lower section.
9. multi-rotor aerocraft as claimed in claim 8, it is characterised in that each protective cover that can fold includes a lock
Gu-unlocking structure, the locking-unlocking structure be fixedly installed on it is described can fold on the connecting portion of protective cover, with the fuselage
Between movable connect, can fold position of the protective cover relative to the fuselage for fixed described, and for will described in
Propeller protective cover is untied from fixed position, so that the connecting portion can drive the propeller protective cover around the rotary shaft
Rotate.
10. multi-rotor aerocraft as claimed in claim 2, it is characterised in that at least one in the multiple propeller protective cover
Individual is the one-piece type protective cover of hood, and each one-piece type protective cover of hood includes cover body and motor base, and the cover body is fixed
Connect and support the motor base, the motor base is used to load an at least motor, and the motor is used to drive described fly
The propeller rotation of row device.
11. multi-rotor aerocraft as claimed in claim 10, it is characterised in that the cover body also includes a guard ring, described
Guard ring is fixedly connected with supporting the motor base by multiple fastening members.
12. multi-rotor aerocraft as claimed in claim 11, it is characterised in that at least one in the multiple fastening member is connected
Part is hollow structure, for for controlling the controlling cable of the motor to pass through.
13. multi-rotor aerocraft as claimed in claim 12, it is characterised in that fuselage described in distance in the multiple fastening member
Nearest fastening member is hollow structure.
14. multi-rotor aerocraft as claimed in claim 11, it is characterised in that be in angularly to be distributed between the fastening member；
And/or, the fastening member is rib.
15. multi-rotor aerocraft as claimed in claim 10, it is characterised in that the multiple propeller protective cover is to receive
Close protective cover and the one-piece type protective cover of hood.
16. multi-rotor aerocraft as claimed in claim 15, it is characterised in that the multiple propeller protective cover is divided into two pairs
Or it is multipair, two of each pair can fold protective cover and be placed in relative both sides of the fuselage and in wrong high distribution.
17. multi-rotor aerocraft as claimed in claim 16, it is characterised in that the multi-rotor aerocraft is to include four spiral shells
Revolve the quadrotor of oar protective cover.
18. multi-rotor aerocraft as claimed in claim 17, it is characterised in that one pair of which propeller protective cover is close to fuselage
Head, be arranged at fuselage both sides, another pair propeller protective cover close to afterbody, be arranged at fuselage both sides.
19. multi-rotor aerocraft as claimed in claim 18, it is characterised in that a pair of propellers close to fuselage head are protected
The top for the fuselage that is placed in is covered under collapse state with lower section and overlapping perpendicular to the direction of course axle；Close to afterbody
A pair of propeller protective covers be also placed under collapse state fuselage top and lower section and in the direction perpendicular to course axle
It is overlapping.
20. multi-rotor aerocraft as claimed in claim 19, it is characterised in that be arranged at two spiral shells of fuselage the week side of boss the same side
Rotation oar protective cover is placed in the top and lower section of fuselage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621494164.5U CN206358357U (en) | 2016-12-30 | 2016-12-30 | Multi-rotor aerocraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621494164.5U CN206358357U (en) | 2016-12-30 | 2016-12-30 | Multi-rotor aerocraft |
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| CN206358357U true CN206358357U (en) | 2017-07-28 |
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ID=59378578
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| Application Number | Title | Priority Date | Filing Date |
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| CN201621494164.5U Expired - Fee Related CN206358357U (en) | 2016-12-30 | 2016-12-30 | Multi-rotor aerocraft |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018120163A1 (en) * | 2016-12-30 | 2018-07-05 | 深圳市大疆创新科技有限公司 | Multi-rotor aircraft and spreading and/or folding method of propeller protective cover thereof |
| CN108382578A (en) * | 2018-04-09 | 2018-08-10 | 北京航空航天大学 | A kind of mixed at high speed layout vertically taking off and landing flyer |
| CN109863083A (en) * | 2017-05-22 | 2019-06-07 | 深圳市大疆创新科技有限公司 | Unmanned plane |
| RU2724006C1 (en) * | 2018-07-04 | 2020-06-18 | Др. Инг. Х.Ц.Ф. Порше Акциенгезелльшафт | Aircraft |
| CN111661327A (en) * | 2019-03-05 | 2020-09-15 | 上海科技大学 | Many rotors of flexible fuselage flight device |
-
2016
- 2016-12-30 CN CN201621494164.5U patent/CN206358357U/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018120163A1 (en) * | 2016-12-30 | 2018-07-05 | 深圳市大疆创新科技有限公司 | Multi-rotor aircraft and spreading and/or folding method of propeller protective cover thereof |
| CN109863083A (en) * | 2017-05-22 | 2019-06-07 | 深圳市大疆创新科技有限公司 | Unmanned plane |
| CN108382578A (en) * | 2018-04-09 | 2018-08-10 | 北京航空航天大学 | A kind of mixed at high speed layout vertically taking off and landing flyer |
| CN108382578B (en) * | 2018-04-09 | 2024-03-29 | 北京航空航天大学 | High-speed hybrid layout vertical take-off and landing aircraft |
| RU2724006C1 (en) * | 2018-07-04 | 2020-06-18 | Др. Инг. Х.Ц.Ф. Порше Акциенгезелльшафт | Aircraft |
| US11358714B2 (en) | 2018-07-04 | 2022-06-14 | Dr. Ing. H.C. F. Porsche Aktiengesellschaft | Aircraft |
| CN111661327A (en) * | 2019-03-05 | 2020-09-15 | 上海科技大学 | Many rotors of flexible fuselage flight device |
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