CN107108026B - Multi-rotor aerocraft and its expansion of propeller protective cover and/or folding method - Google Patents
Multi-rotor aerocraft and its expansion of propeller protective cover and/or folding method Download PDFInfo
- Publication number
- CN107108026B CN107108026B CN201680004165.3A CN201680004165A CN107108026B CN 107108026 B CN107108026 B CN 107108026B CN 201680004165 A CN201680004165 A CN 201680004165A CN 107108026 B CN107108026 B CN 107108026B
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- China
- Prior art keywords
- protective cover
- fuselage
- propeller
- fold
- propeller protective
- Prior art date
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- 230000001681 protective effect Effects 0.000 title claims abstract description 286
- 238000000034 method Methods 0.000 title claims abstract description 37
- 230000004224 protection Effects 0.000 claims description 16
- 230000009187 flying Effects 0.000 claims description 3
- 230000005611 electricity Effects 0.000 description 3
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 239000013013 elastic material Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- -1 polypropylene Polymers 0.000 description 2
- 239000011241 protective layer Substances 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 239000004698 Polyethylene Substances 0.000 description 1
- 239000004743 Polypropylene Substances 0.000 description 1
- 239000004793 Polystyrene Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 238000005187 foaming Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 239000010410 layer Substances 0.000 description 1
- 239000004033 plastic Substances 0.000 description 1
- 229920003023 plastic Polymers 0.000 description 1
- 229920000573 polyethylene Polymers 0.000 description 1
- 229920001155 polypropylene Polymers 0.000 description 1
- 229920002223 polystyrene Polymers 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
- B64U30/26—Ducted or shrouded rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C19/00—Aircraft control not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
- B64U10/13—Flying platforms
- B64U10/14—Flying platforms with four distinct rotor axes, e.g. quadcopters
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
- B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
- B64U30/293—Foldable or collapsible rotors or rotor supports
Abstract
A kind of multi-rotor aerocraft and its expansion of propeller protective cover and/or folding method; multiple propeller protective covers that the aircraft includes fuselage and connect with the fuselage; at least one in the multiple propeller protective cover is that can fold protective cover; each protective cover that can fold is with a collapse state and a unfolded state; protective cover can be folded described under collapse state to be folded on above or below the fuselage, the protective cover that can fold is stretched out from the side of the fuselage in the deployed state.According to the solutions of the embodiments of the present invention, facilitate user to carry and aircraft cruise duration can be extended.
Description
Copyright notice
This patent document disclosure includes material protected by copyright.The copyright is all for copyright holder.Copyright
Owner does not oppose the patent document in the presence of anyone replicates the proce's-verbal of Patent&Trademark Office and archives or should
Patent discloses.
Technical field
The present invention relates to the methods that multi-rotor aerocraft and its propeller protective cover are unfolded and/or fold.
Background technique
Multiple rotor structures that multi-rotor aerocraft generally comprises fuselage and circumferentially stretched out by fuselage, each rotor structure
It is made of horn with the Power Component supported via horn.To be easy to carry, horn is foldable to fuselage two sides.To ensure peace
Entirely, the high aircraft of some pairs of security requirements, such as aircraft for self-timer usually can also install protective cover, the prior art additional
In, protective cover is usually superimposed on horn, in addition can shorten the cruise duration of aircraft after protective cover, in addition also tends to make
The folding mode of horn fails, and causes aircraft inconvenient to carry.On the other hand, some protective covers are detachable protective cover,
User can first unload protective cover before carrying aircraft, then horn is folded to fuselage side.So, such mode carries every time
Before be both needed to disassembly protective cover, still bring inconvenience to user, and horn is folded to the mode of fuselage two sides, will limit fuselage
Width prevents fuselage from loading bigger battery, influences aircraft cruise duration.
Summary of the invention
In order to solve the above-mentioned of the prior art and other potential problems, it is necessary to propose a kind of multi-rotor aerocraft and one
The propeller protective cover expansion of kind multi-rotor aerocraft and/or folding method.
In a first aspect, providing a kind of multi-rotor aerocraft, the aircraft includes fuselage, and is connected to the multiple of fuselage
Propeller protective cover, which is characterized in that at least one in the multiple propeller protective cover is that can fold protective cover, each described
Protective cover can be folded with a collapse state and a unfolded state, under collapse state described in can fold protective cover and be folded on institute
It states above or below fuselage, the protective cover that can fold is stretched out from the side of the fuselage in the deployed state.
Further, each propeller protective cover includes an interconnecting piece, and the propeller protective cover passes through the interconnecting piece
It is connected to the fuselage.
Further, each interconnecting piece that can fold protective cover is rotatablely connected to the fuselage, so that described receive
Closing protective cover can convert between unfolded state and collapse state.
Further, the protective cover that folds is at least a pair, and two to partner can fold protective cover and split institute
State the opposite two sides of fuselage and in wrong high distribution.
Further, each interconnecting piece of protective cover that can fold is around the course axis of the parallel aircraft or roll
The rotatable mode of the rotary shaft of axis is connected to the fuselage, so that the protective cover that folds unfolded state and can fold shape
It is converted between state.
Further, under collapse state, two to partner can fold protective cover perpendicular to aircraft course axis
Direction have overlapping.
Further, two to partner 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 it can be folded on the interconnecting piece of protective cover described in being set to, movable is connect between the fuselage, and being used for can described in fixation
Position of the protective cover relative to the fuselage is folded, and for unlocking the propeller protective cover from fixed position, so that
The interconnecting piece is able to drive the propeller protective cover and rotates 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 and motor base, and the cover is fixedly connected with and supports the motor base, the motor
Pedestal is for loading an at least motor, and the motor is for driving the propeller of the aircraft to rotate.
Further, the cover further includes a guard ring, and the guard ring is fixedly connected and is 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.
It further, is in angularly to be distributed between the fastening member；And/or the fastening member is rib.
Further, protective cover can be folded described in all or part while being the one-piece type protective cover of hood.
Further, all or part of one-piece type protective cover of hood is simultaneously that can fold protective cover.
Further, the multiple propeller protective cover is the one-piece type protective cover of hood and can fold protective cover.
Further, the multiple propeller protective cover is divided into two pairs or multipair, and each pair of two can fold protective cover point
It is placed in the opposite two sides of the fuselage and in wrong high distribution.
Further, the multi-rotor aerocraft is the quadrotor for including four propeller protective covers.
Further, one pair of them propeller protective cover close to fuselage head, be set to fuselage two sides, another pair propeller
Protective cover close to afterbody, be set to fuselage two sides.
Further, close to fuselage head a pair of of propeller protective cover be placed under collapse state fuselage top with
Lower section and perpendicular to course axis direction overlapping；Close to afterbody a pair of of propeller protective cover under collapse state also
Be placed in fuselage top it is with lower section and Chong Die in the direction perpendicular to course axis.
Further, be set to fuselage side the same side two propeller protective covers be placed in fuselage top under
Side.
Second aspect provides the expansion of propeller protective cover and/or folding method of a kind of multi-rotor aerocraft, more rotations
Rotor aircraft includes fuselage and multiple propeller protective covers, which comprises
One propeller protective cover is unlocked in first position, makes the propeller protective cover can be around being parallel to more rotors
The rotary shaft rotation of the course axis or roll axis of aircraft；
The propeller protective cover is rotated to the second position around the rotary shaft；And
The propeller protection is locked in the second position to cover on fuselage, makes the propeller protective cover can not be around institute
State rotary shaft rotation；
Wherein, when the propeller protective cover is located at one of them in first position and the second position, the propeller
Protective cover is located at the side of fuselage, described when the propeller protective cover is located at another in first position and the second position
Propeller protective cover is located above or below fuselage.
Further, the method also includes: a pair of of propeller protective cover is separately folded to the top of fuselage and lower section.
Further, the method also includes: a pair of of propeller protective cover of fuselage side opposite sides will be located at
It is separately folded to the top of fuselage and lower section and is locked on fuselage.
Further, the method also includes: a pair of of propeller protective cover of fuselage side opposite sides will be located at
It is separately folded and continues to rotate the pair of propeller protective cover to the top of fuselage and lower section and make it in the side perpendicular to course axis
It is covered on fuselage to overlapping, and the pair of propeller protection of locking.
Further, the method also includes: will be close to fuselage head and be located at the one of fuselage side opposite sides
To propeller protective cover, it is separately folded to the top of fuselage and lower section and is locked on fuselage.
Further, the method also includes: will be close to afterbody and be located at the one of fuselage side opposite sides
To propeller protective cover, it is separately folded to the top of fuselage and lower section and is locked on fuselage.
Further, the method also includes: will be close to waist and be located at the one of fuselage side opposite sides
To propeller protective cover, it is separately folded to the top of fuselage and lower section and is locked on fuselage.
Further, the method also includes: will be located at fuselage side the same side two adjacent propeller protective covers,
It is separately folded to the top of fuselage and lower section.
Further, the method also includes: unlock the propeller protective cover in the second position, make the spiral
Paddle protective cover can be rotated around the rotary shaft；The propeller protective cover is rotated to the first position around the rotary shaft；
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 rotary shaft rotation.
The embodiment of the present invention provide multi-rotor unmanned aerial vehicle and multi-rotor aerocraft propeller protective cover expansion and/or
Propeller protective cover is folded to fuselage upper and lower by folding method, has both facilitated user's carrying, and will not influence fuselage width,
Make that more big battery can be installed in fuselage, to extend aircraft cruise duration.
Detailed description of the invention
In order to illustrate the technical solution of the embodiments of the present invention more clearly, will make below to required in the embodiment of the present invention
Attached drawing is briefly described, it should be apparent that, drawings in the following description are only some embodiments of the invention, for
For those of ordinary skill in the art, without creative efforts, it can also be obtained according to these attached drawings other
Attached drawing.
Fig. 1 is the schematic top plan view that a quadrotor in an embodiment of the present invention is in unfolded state.
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 unfolded state.
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 unfolded state.
Fig. 6 is the schematic side view that quadrotor shown in Fig. 1 is in collapse state.
Fig. 7 is the schematic top plan view that three rotor crafts in an embodiment of the present invention are in unfolded state.
Fig. 8 is the schematic top plan view that three rotor crafts shown in Fig. 7 are in collapse state.
Fig. 9 is the schematic top plan view that six rotorcraft in an embodiment of the present invention is in unfolded state.
Figure 10 is the schematic top plan view that three rotor crafts shown in Fig. 9 are in collapse state.
Figure 11 is the expansion of propeller protective cover and/or folding method of the multi-rotor aerocraft in an embodiment of the present invention
Flow chart.
Main element symbol description
Aircraft 10,20,30
Fuselage 110,210,310
Rotor structure 120,220,320
Propeller protective cover 121,221,321
Cover 122
Motor base 123
Fastening member 124
Guard ring 125
Interconnecting piece 126,227,327
Course axis Y, Ya, Yb
Roll axis X, Xb
Head 111,211,311
Tail portion 112,212,312
Middle part 313
Step 41-43
The present invention that the following detailed description will be further explained with reference to the above drawings.
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts every other
Embodiment shall fall within the protection scope of the present invention.
It should be noted that it can be directly another when component is referred to as " being fixed on ", " being installed on " another component
On a component or there may also be components placed in the middle.When a component is considered as " being set to " another component, it can be with
It is to be set up directly on another component or may be simultaneously present component placed in the middle.Term " and or " used herein includes
All arbitrary and combinations of one or more relevant listed items.
It is illustrated by taking quadrotor and its propeller protective cover used as an example below.
It please refers to shown in Fig. 1-Fig. 6, the quadrotor 10 includes fuselage 110 and be connected to four of fuselage 110
Rotor structure 120, each rotor structure 120 include a propeller protective cover 121.In following specific descriptions, for convenience of describing,
The word that will use the expression such as " top of fuselage ", " lower section of fuselage " and " side of fuselage " orientation, wherein " fuselage
Top " refer to spatial position along aircraft course axis direction, on fuselage, " lower section of fuselage " refers to along flying
Row device course axis direction, the spatial position under fuselage, " side of fuselage " refer to six space of planes around fuselage
Behind the top and lower section that remove fuselage, any one or more spatial positions 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 122 and the motor base 123 for being connected with cover 122 and being supported by cover 122.The motor base
Seat 123 is located at the center of the cover 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 the motor (not shown) for driving propeller set rotation.Specifically, motor
It is installed on the motor base 123, propeller set is installed on again on the motor shaft of motor.In one embodiment, institute
It states motor base 123 and loads a motor, the motor shaft of the motor extends downwardly, and drives and is located under the motor base 123
The propeller set rotation of side.In another embodiment, the motor shaft of the motor stretches out upwards, drives and is located at the electricity
The propeller set rotation of 123 top of machine pedestal.In another embodiment, the motor base 123 loads two motors,
Wherein the motor shaft of a motor extends downwardly, and drives the propeller set rotation for being located at 123 lower section of motor base, Ling Yi electricity
The motor shaft of machine stretches out upwards, the propeller set rotation for being located at 123 top of motor base is driven, in this way, making aircraft
Spare 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 122 and motor base 123 by fastening member 124, with support motor base 123 with
And the Power Component that motor base 123 loads.The cover 122 includes a guard ring 125, and the guard ring 125 is located at motor
Protective layer (not indicating) is wrapped up on the guard ring 125 in one embodiment in the outer circumferential of pedestal 123.The protection
Layer is made of elastic material, for example, the protective layer can be by highly elastic material such as polypropylene plastics foamed material or foaming
Polystyrene polyethylene hybrid scheme at.
It is fixedly connected between the guard ring 125 and motor base 123 by fastening member 124.Further, the protection
It can be made by being integrally formed between circle 125, fastening member 124 and motor base 123.The quantity of the fastening member 124 can
Think it is multiple, below for four.Wherein at least one fastening member 124 be it is hollow, for from the control of 110 inside of fuselage
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 are in the same plane, in angularly dividing
Cloth extends the cruise duration of aircraft 10 to reduce the influence to rotor air-flow.In other embodiments, consolidate for described four
Even part 124 can be located in Different Plane, such as each fastening member 124 is fixedly connected with endpoint and the company of fixation of motor base 121
Slightly difference in height is taken over control between the endpoint of guard ring 125, angle is identical or substantially identical between every two adjacent fastening member 124, makes solid
It is even in angularly to be distributed between part 124.In other embodiments, it can also be other quantity and be connected in what is be angularly distributed
Part 124 is fixedly connected with motor base 123 and guard ring 125, such as 5,6 etc. of 2,3 or more.The fastening member
124 be rib in one embodiment.
Each propeller protective cover 120 further includes an interconnecting piece 126, and the interconnecting piece 126 is located at outside the guard ring 125
Side, the propeller protective cover are connected to fuselage 110 by the interconnecting piece 126.
In the present embodiment, the propeller protective cover 120 is that can fold protective cover, including as shown in Fig. 1,3,5
Unfolded state and Fig. 2,4,6 shown in collapse state.The interconnecting piece 126 is rotary type interconnecting piece, is set to fuselage 110
Top edges or lower edge can be rotated around the rotary shaft for being parallel to 10 course axis Y of aircraft, to allow to protect on propeller
Shield 120 switches between unfolded state and collapse state.
In one embodiment, each corresponding propeller protective cover 120,110 top edges of fuselage or under
The direction that method, edge is parallel to 10 course axis Y of aircraft is correspondingly arranged a shaft (not shown), and the shaft can be sitting at machine
In 110 top edges of body or lower edge, or the position positioned at 110 top edges of fuselage or lower edge among fuselage
It sets.The interconnecting piece 126 of the propeller protective cover 120 includes a hole location (not shown), is sheathed on the shaft by the hole location
Above and around the shaft rotate.One locking-unlocking structure (not shown), the locking-unlock are also set up on each interconnecting piece 126
Structure can fold on the interconnecting piece of protective cover described in being fixedly installed on, and connect between the fuselage for movable, described
Propeller protective cover is locked in the position, Yi Ji when propeller protective cover 120 is located at specific position by locking-unlocking structure
Propeller protective cover 120 is unlocked from fixed position, it can be (i.e. described around the rotary shaft for being parallel to 10 course axis Y of aircraft
Shaft) rotation.In one embodiment, the locking-unlocking structure can be on interconnecting piece 126 one towards fuselage 110
Pillar (not shown) and the fastener for being sheathed on pillar end, the pillar and the limiting slot (not shown) phase on fuselage 110
Cooperation, the both ends of limiting slot respectively correspond two states of propeller protective cover 120: unfolded state and collapse state.It is being unfolded
Under state, propeller protective cover 120 is fixed on the unfolded state by tightening fastener parts；It is switched to by propeller protective cover 120
When collapse state, fastener is loosened, propeller protective cover 120 is rotated along limiting slot to collapse state, then tightening fastener parts will
Propeller protective cover 120 is fixed on the collapse state.In another embodiment, the locking-unlocking structure can be setting
In the hole location on interconnecting piece 126 and the pin with the hole location close-fitting, the interconnecting piece 126 is located on the fuselage 110
Method, edge or lower edge are located at shaft two sides on the position at center, the fuselage 110 and are respectively provided with a hole location, the hole
Position also can be with pin close-fitting, wherein the expansion shape of the propeller protective cover 120 is corresponded to apart from the closer hole location of fuselage edge
The rotation of propeller protective cover 120 to the hole location on interconnecting piece 126 is directed at the hole location, recycles the hole of pin insertion alignment by state
Propeller protective case 120 is fixed on this position by position.The receipts of propeller protective cover 120 are corresponded to apart from the farther away hole location of fuselage edge
Conjunction state unclamps pin when propeller protective cover 120 is switched to collapse state, by the rotation of propeller protective cover 120 to even
Hole location in socket part 126 is directed at this apart from the farther away hole location of fuselage edge, and pin is recycled to fix.
It please refers to shown in Fig. 2,4,6, under collapse state, the propeller protective cover 120 is folded on 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.Still further, the propeller protective cover 120 is divided into two pairs, two pairs of left and right for being all set in fuselage 110
Two sides, first pair of tail portion 112 close to 111, the second pairs of close fuselages 110 in the head of fuselage 110.First pair of propeller protective cover
120 in wrong high setting, if the plane perpendicular to 10 course axis Y of aircraft 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
When state, energy is overlapped or partly overlaps.In the present embodiment, first pair of one of propeller protective cover 120 connection
In the lower right-hand side edge of fuselage 110, it is rotated the lower section for collapsing in fuselage 110；Another propeller protective cover 120 is connected to
The top edges in 110 left side of fuselage, are rotated the top for collapsing in fuselage 110, fold the latter two in the direction of parallel course axis Y
It is upper that there is overlapping.Second pair of propeller protective cover 120 is equally in wrong high setting, and two propeller protective covers 120 of second pair
In on the horizontal plane of different height, one of them is connected to the top edges on 110 right side of fuselage, another is connected to fuselage 110
The lower edge in left side folds the latter two and is located above and below fuselage 110, and on the direction of parallel course axis Y
With overlapping.Further, using 110 roll axis of fuselage as 110 left side of center line cutting fuselage and right side, it is located 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 110 left side of fuselage
Paddle protective cover 120 is in wrong high setting, such as in Fig. 1-6 illustrated embodiment, and two propellers positioned at 110 left side of fuselage are protected
In shield 120, wherein being connected to the top edges of fuselage 110 close to the propeller protective cover 120 on head 111, it is located at after folding
The top of fuselage 110 is located at after folding by the lower edge of propeller protective cover 120 connection and fuselage 110 of caudad 112
The lower section of fuselage 110；Another two propeller protective cover 120 positioned at 110 right side of fuselage is equally also in wrong high setting, in this way, appointing
One propeller protective cover 120 corresponding thereto and adjacent two propeller protective covers 120 in wrong high setting, so not only
10 lateral dimension of aircraft can be reduced to the greatest extent when folding, can also balance aircraft center of gravity in 10 flight course of aircraft.
The structure, principle of propeller protective cover in the embodiment of the present invention are illustrated by taking quadrotor as an example above.So,
As can be seen that the propeller protective cover in the embodiment of the present invention can be applied equally on other multi-rotor aerocrafts, such as three
On the aircraft such as rotor, six rotors, eight rotors.
Refering to shown in Fig. 7 and Fig. 8, being one or three rotor crafts 20, three rotor craft 20 is including fuselage 210 and even
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 tail portion 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, being located 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, being located at the propeller protective cover 221 on 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 fold
Protective cover.Each propeller protective cover 221 is turnably connected to fuselage 210 by an interconnecting piece 227, passes through the interconnecting piece
227 can will switch between the unfolded state shown in Fig. 7 of propeller protective cover 221 and collapse state shown in Fig. 8.Interconnecting piece
227 further include one locking-unlocking structure (not shown) simultaneously, the corresponding knot on the locking-unlocking structure cooperation fuselage 210
Propeller protective cover 221 is fixed on unfolded state or collapse state by structure.
In the present embodiment, the interconnecting piece 227 positioned at the propeller protective cover 221 on head 211 is set to fuselage 210
Top edge, therefore, the propeller protective cover 221 collapses in above fuselage 211 under collapse state, certainly, in other implementations
In mode, the lower edge in fuselage 210 can be set for the interconnecting piece 227 of the propeller protective cover 221 so that the propeller
Protective cover 221 collapses in the lower section of fuselage 210.Positioned at interconnecting piece 227 1 of a pair of of propeller protective cover 221 of tail portion 212
It is set to the top edge of fuselage 210, one is set to the lower edge of fuselage 210, so makes two propeller protective covers 221 in machine
210 two sides of body are in wrong high arrangement, and when folding, one collapses in the top of fuselage 210, and one collapses in the lower section of fuselage 210,
The two has overlapping in the direction perpendicular to 20 course axis Ya of aircraft.
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 tail portion 312 of fuselage 310 to rotor structure 320, third is located at the middle part 313 of fuselage 310 to rotor structure 320.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, being located at the propeller protective cover of head 311 and/or tail portion 312
321 can be other kinds of protective cover.The propeller protective cover 321 can fold protective cover, can not also be complete
It is all that can fold protective cover, although the side of fuselage 310, example can be collapsed according to the actual situation alternatively, can fold
Such as, 310 side of fuselage can otherwise be collapsed in positioned at the propeller protective cover 321 of head 311 and/or tail portion 312.?
In present embodiment, six propeller protective covers 321 are the one-piece type protective cover of hood and can fold protective cover, each spiral
Paddle protective cover 321 is turnably connected to fuselage 310 by an interconnecting piece 327, can be protected propeller by the interconnecting piece 327
Switch between the unfolded state shown in Fig. 7 of shield 321 and collapse state shown in Fig. 8.Interconnecting piece 327 further includes simultaneously a lock
Gu-unlocking structure (not shown), the locking-unlocking structure cooperates the corresponding construction on fuselage 310, by propeller protective cover
321 are fixed on unfolded state or collapse state.
In the present embodiment, interconnecting piece 327 1 of a pair of of propeller protective cover 321 positioned at head 311 are set to
The top edge of fuselage 310, one is set to the lower edge of fuselage 310, so makes two propeller protective covers 321 in fuselage 310
Two sides are in wrong high arrangement, and when folding, one collapses in the top of fuselage 310, and one collapses in the lower section of fuselage 310, the two
There is overlapping in the direction perpendicular to 30 course axis Yb of aircraft.Positioned at the connection of a pair of of propeller protective cover 321 of tail portion 312
327 1, portion is set to the top edge of fuselage 310, and one is set to the lower edge of fuselage 310, so makes two propeller protections
Cover 321 is in 310 two sides of fuselage in wrong high arrangement, and when folding, one collapses in the top of fuselage 310, and one collapses in fuselage
310 lower section, the two have overlapping in the direction perpendicular to 30 course axis Yb of aircraft.Likewise, being located at a pair at middle part 313
Interconnecting piece 327 1 of propeller protective cover 321 are set to the top edge of fuselage 310, and one is set to the following of fuselage 310
Edge so makes two propeller protective covers 321 in 310 two sides of fuselage in wrong high arrangement, and when folding, one collapses in fuselage
310 top, one collapses in the lower section of fuselage 310, and the two has overlapping in the direction perpendicular to 30 course axis Yb of aircraft.
In the present embodiment, using 310 roll axis Xb of fuselage as 310 left side of center line cutting fuselage and right side, it is same to be located at fuselage 310
Three propeller protective covers 321 of side are in previous-next-up or down-previous-next mistake by from head 311 to tail portion 312 sequence respectively
High setting, for example, being located at three propeller protective covers 321 in left side from head 311 to tail portion 312 respectively in the mistake in previous-next-
High setting, positioned at right side three propeller protective covers 321 from head 311 to tail portion 312 be in respectively under-the wrong height of previous-next sets
It sets, in this way, making to avoid adjoining spiral paddle also in wrong high arrangement between any two adjoining spiral paddle protective covers 321 of either side
The problem of protective cover 321 interferes 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, not need to be in above-described embodiment simultaneously
What is illustrated fold protective cover, alternatively, propeller protective cover can fold, but fold mode can with introduced in above-described embodiment
Difference, such as collapse in front of and after fuselage two sides or fuselage.In addition, according to actual needs may be used in multiple rotors of aircraft
To be the one-piece type protective cover of hood that part rotor uses introduction of the embodiment of the present invention, another part rotor still continued to use in the prior art
Horn and the mode that is provided separately of protective cover, such as motor base is supported by horn, protective cover is supported on motor base again；
Furthermore it is also possible to part rotor according to actual needs and protective cover is folded using introduction of the embodiment of the present invention, another part is revolved
The wing use other modes fold or rotor and fuselage between to be fixedly connected, can not fold.In part, rotor uses hood one
Figure protective cover and part or all of rotor can also be segmented are as follows: the one-piece type guarantor of hood using that can fold in the scheme of protective cover
Shield is applied on same rotor with that can fold protective cover, such as is applied on rotor A, B, C of three rotor crafts simultaneously；
The one-piece type protective cover of hood is applied on different rotors from that can fold protective cover, such as the one-piece type protective cover of hood is applied to three
On the rotor A of rotor craft, protective cover can be folded applied on rotor B, C；The one-piece type protective cover of hood and protection can be folded
The rotor of cover application partly overlaps, such as the one-piece type protective cover of hood is applied on rotor A, B, C of quadrotor, can receive
It closes protective cover to be applied on rotor B, C, D, furthermore the one-piece type protective cover of such as hood is applied to the rotor A of quadrotor
On, it is upper etc. applied to rotor A, B, C, D that protective cover can be folded.
It, according to the actual situation, can also be in it will can fold the scheme that protective cover rotates above or below stacked fuselage
Using will can fold protective cover around be parallel to aircraft roll axis rotary shaft rotate by the way of.
It is that the propeller protective cover of multi-rotor aerocraft in an embodiment is unfolded and/or folds refering to fig. 1 shown in 1
Method, comprising:
S41: unlocking a propeller protective cover in first position, revolve the propeller protective cover can around a rotary shaft
Turn, the course axis or roll axis of the parallel multi-rotor aerocraft of the rotary shaft；
S42: the rotary shaft around the multi-rotor aerocraft rotates the propeller protective cover to the second position；And
S43: the propeller protection is locked in the second position and is covered 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 position, the propeller
Protective cover is located at the side of fuselage, described when the propeller protective cover is located at another in first position and the second position
Propeller protective cover is located above or below fuselage.
In another embodiment, the method can with comprising steps of by a pair of of propeller protective cover be separately folded to
The top and lower section of fuselage.
In another embodiment, the method can be comprising steps of fuselage periphery opposite sides will be located at
A pair of of propeller protective cover is separately folded to the top of fuselage and lower section and is locked on fuselage.
In another embodiment, the method can be comprising steps of fuselage periphery opposite sides will be located at
A pair of of propeller protective cover is separately folded to the top of fuselage and lower section, continue to rotate the pair of propeller protective cover make its
It is covered on fuselage perpendicular to the direction overlapping of course axis, and the pair of propeller protection of locking.
In another embodiment, the method can be comprising steps of will be close to fuselage head and be located at fuselage
A pair of of propeller protective cover 121 of side opposite sides is separately folded to the top of fuselage and lower section and is locked on fuselage.
In another embodiment, the method can also include: that will be close to afterbody and be located at fuselage side
A pair of of propeller protective cover of opposite sides is separately folded to the top of fuselage and lower section and is locked on fuselage.
In another embodiment, the method also includes: will be close to waist and to be located at fuselage side opposite
A pair of of propeller protective cover of two sides is separately folded to the top of fuselage and lower section and is locked on fuselage.
In another embodiment, the method can also include: that will be located at the two adjacent of fuselage side the same side
Propeller protective cover is separately folded to the top of fuselage and lower section.
In another embodiment, the method can be comprising steps of unlock the propeller in the second position
Protective cover rotate the propeller protective cover can 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 conclusion the embodiment of the present invention multi-rotor aerocraft and multi-rotor aerocraft propeller protective cover expansion and/
Or method for folding, motor base is supported due to directly replacing traditional horn using protective cover, and then support the dynamic of aircraft
Power component not only solves the certain aircraft bring security risks highly sensitive to safety, and due to saving horn,
Compared to the unmanned plane that traditional existing horn has protective cover again, weight can be lighter and will not generate superposition shadow to rotor air-flow
It rings, thus will not influence the cruise duration of aircraft, set in addition, propeller protective cover is carried out wrong height by embodiment of the present invention
It sets, is separately folded in fuselage upper and lower, both facilitated user's carrying, and will not influence fuselage width, and made to install in fuselage
More big battery, to extend aircraft cruise duration.
Finally it should be noted that the above examples are only used to illustrate the technical scheme of the present invention and are not limiting, although reference
Preferred embodiment describes the invention in detail, those skilled in the art should understand that, it can be to of the invention
Technical solution is modified or equivalent replacement, without departing from the spirit and scope of the technical solution of the present invention.
Claims (25)
1. a kind of multi-rotor aerocraft, the aircraft includes fuselage, and 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, and each protective cover that can fold has
Have a collapse state and a unfolded state, under collapse state it is described can fold protective cover be folded on the fuselage top or
Lower section, the protective cover that can fold is stretched out from the side of the fuselage in the deployed state；
Wherein, each propeller protective cover includes an interconnecting piece, and the propeller protective cover is connected to institute by the interconnecting piece
State fuselage；
Each interconnecting piece that can fold protective cover is rotatablely connected to the fuselage, so that the protective cover that folds can opened up
It is converted between open state and collapse state；
The protective cover that folds is at least a pair, and two to partner can fold protective cover and split opposite two of the fuselage
Side and in wrong high distribution；
It is each described to fold the interconnecting piece of protective cover with can around the course axis of the parallel aircraft or the rotary shaft of roll axis
The mode of rotation is connected to the fuselage, so that the protective cover that folds can convert between unfolded state and collapse state.
2. multi-rotor aerocraft as described in claim 1, which is characterized in that under collapse state, two to partner can
Folding protective cover has overlapping in the direction perpendicular to aircraft course axis.
3. multi-rotor aerocraft as claimed in claim 2, which is characterized in that two to partner can fold protective cover and receive
Be placed in the top and lower section of the fuselage under conjunction state.
4. multi-rotor aerocraft as claimed in claim 3, which is characterized in that the protective cover that folds is at least two pairs, and 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.
5. multi-rotor aerocraft as claimed in claim 4, which is characterized 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 interconnecting piece of protective cover, with the fuselage
Between movable connection, for can fold position of the protective cover relative to the fuselage described in fixation, and for will be described
Propeller protective cover is unlocked from fixed position, so that the interconnecting piece is able to drive the propeller protective cover around the rotary shaft
Rotation.
6. multi-rotor aerocraft as described in claim 1, which is characterized in that at least one in the multiple propeller protective cover
For the one-piece type protective cover of hood, each one-piece type protective cover of hood includes cover and motor base, and the cover is fixed to be connected
The motor base is connect and supports, the motor base is for loading an at least motor, and the motor is for driving the flight
The propeller of device rotates.
7. multi-rotor aerocraft as claimed in claim 6, which is characterized in that the cover further includes a guard ring, described anti-
Guard ring is fixedly connected by multiple fastening members and supports the motor base.
8. multi-rotor aerocraft as claimed in claim 7, which is characterized in that at least fastening member in the multiple fastening member
For hollow structure, for passing through for the controlling cable for controlling the motor.
9. multi-rotor aerocraft as claimed in claim 8, which is characterized in that fuselage described in distance is most in the multiple fastening member
Close fastening member is hollow structure.
10. multi-rotor aerocraft as claimed in claim 7, which is characterized in that be in angularly to be distributed between the fastening member；
And/or the fastening member is rib.
11. such as the described in any item multi-rotor aerocrafts of claim 6-10, which is characterized in that can be folded described in all or part
Protective cover is the one-piece type protective cover of hood simultaneously.
12. such as the described in any item multi-rotor aerocrafts of claim 6-10, which is characterized in that all or part of hood one
Figure protective cover is simultaneously that can fold protective cover.
13. multi-rotor aerocraft as described in claim 1, which is characterized in that the multiple propeller protective cover is hood
One-piece type protective cover and protective cover can be folded.
14. multi-rotor aerocraft as claimed in claim 13, which is characterized in that the multiple propeller protective cover is divided into two pairs
Or it is multipair, each pair of two can fold protective cover and be placed in opposite two sides of the fuselage and in wrong high distribution.
15. multi-rotor aerocraft as claimed in claim 14, which is characterized in that the multi-rotor aerocraft be include four spiral shells
Revolve the quadrotor of paddle protective cover.
16. multi-rotor aerocraft as claimed in claim 15, which is characterized in that one pair of them propeller protective cover is close to fuselage
Head is set to fuselage two sides, another pair propeller protective cover close to afterbody, be set to fuselage two sides.
17. multi-rotor aerocraft as claimed in claim 16, which is characterized in that a pair of of propeller close to fuselage head is protected
The top for covering under collapse state the fuselage that is placed in is with lower section and Chong Die in the direction perpendicular to course axis；Close to afterbody
A pair of of propeller protective cover be also placed under collapse state the top and lower section and in the direction perpendicular to course axis of fuselage
Overlapping.
18. multi-rotor aerocraft as claimed in claim 17, which is characterized in that be set to two spiral shells of fuselage side the same side
Rotation paddle protective cover is placed in the top and lower section of fuselage.
19. a kind of expansion of propeller protective cover and/or receipts to 18 described in any item multi-rotor aerocrafts according to claim 1
Conjunction method, which is characterized in that the described method includes:
One propeller protective cover is unlocked in first position, makes the propeller protective cover can be around being parallel to more rotor flyings
The rotary shaft rotation of the course axis or roll axis of device；
The propeller protective cover is rotated to the second position around the rotary shaft；And
The propeller protection is locked in the second position to cover on fuselage, makes the propeller protective cover can not be around the rotation
Shaft rotation；
Wherein, when the propeller protective cover is located at one of them in first position and the second position, the propeller protection
Cover is located at the side of fuselage, when the propeller protective cover is located at another in first position and the second position, the spiral
Paddle protective cover is located above or below fuselage so that a pair of of propeller protective cover be separately folded to the top of fuselage and lower section and
In wrong high distribution.
20. method as claimed in claim 19, which is characterized in that further include: fuselage side opposite sides will be located at
A pair of of propeller protective cover is separately folded to the top of fuselage and lower section and is locked on fuselage.
21. method as claimed in claim 19, which is characterized in that further include: fuselage side opposite sides will be located at
A pair of of propeller protective cover is separately folded to the top of fuselage and lower section, continue to rotate the pair of propeller protective cover make its
It is covered on fuselage perpendicular to the direction overlapping of course axis, and the pair of propeller protection of locking.
22. method as claimed in claim 19, which is characterized in that further include: it will be close to fuselage head and be located at fuselage
A pair of of propeller protective cover of side opposite sides is separately folded to the top of fuselage and lower section and is locked on fuselage.
23. the method as described in claim 19 or 22, which is characterized in that further include: it will be close to afterbody and be located at
A pair of of propeller protective cover of fuselage side opposite sides is separately folded to the top of fuselage and lower section and is locked on fuselage.
24. method as claimed in claim 19, which is characterized in that further include: two phases of fuselage side the same side will be located at
Adjacent propeller protective cover, is separately folded to the top of fuselage and lower section.
25. method as claimed in claim 19, which is characterized in that further include: the propeller is unlocked in the second position
Protective cover rotate the propeller protective cover can 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 the rotation
Shaft rotation.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| PCT/CN2016/113831 WO2018120163A1 (en) | 2016-12-30 | 2016-12-30 | Multi-rotor aircraft and spreading and/or folding method of propeller protective cover thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107108026A CN107108026A (en) | 2017-08-29 |
| CN107108026B true CN107108026B (en) | 2019-05-31 |
Family
ID=59676497
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201680004165.3A Expired - Fee Related CN107108026B (en) | 2016-12-30 | 2016-12-30 | Multi-rotor aerocraft and its expansion of propeller protective cover and/or folding method |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN107108026B (en) |
| WO (1) | WO2018120163A1 (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109677600A (en) * | 2018-08-16 | 2019-04-26 | 深圳市格上格创新科技有限公司 | A kind of shrinkable unmanned plane rotor protective device and unmanned plane |
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| CN105235891A (en) * | 2015-01-04 | 2016-01-13 | 北京零零无限科技有限公司 | Foldable unmanned aerial vehicle |
| CN205221092U (en) * | 2015-11-06 | 2016-05-11 | 珠海华迈航空科技有限公司 | Four -rotor aircraft |
| CN105667777A (en) * | 2016-03-29 | 2016-06-15 | 普宙飞行器科技（深圳）有限公司 | Four-way-extensible paddle protecting cover, power system and unmanned aerial vehicle |
| CN105947202A (en) * | 2016-04-28 | 2016-09-21 | 乐视控股（北京）有限公司 | Foldable unmanned aerial vehicle and application method thereof |
| CN106081084A (en) * | 2016-07-11 | 2016-11-09 | 南京航空航天大学 | A kind of spherical unmanned plane of portable and collapsible |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB201411293D0 (en) * | 2014-06-25 | 2014-08-06 | Pearson Eng Ltd | Improvements in or relating to inspection systems |
| WO2016112124A2 (en) * | 2015-01-08 | 2016-07-14 | Vantage Robotics, Llc | Unmanned aerial vehicle with propeller protection and high impact survivability |
| CN206358357U (en) * | 2016-12-30 | 2017-07-28 | 深圳市大疆创新科技有限公司 | Multi-rotor aerocraft |
-
2016
- 2016-12-30 WO PCT/CN2016/113831 patent/WO2018120163A1/en active Application Filing
- 2016-12-30 CN CN201680004165.3A patent/CN107108026B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105235891A (en) * | 2015-01-04 | 2016-01-13 | 北京零零无限科技有限公司 | Foldable unmanned aerial vehicle |
| CN204998752U (en) * | 2015-01-04 | 2016-01-27 | 北京零零无限科技有限公司 | Folding unmanned aerial vehicle |
| CN205221092U (en) * | 2015-11-06 | 2016-05-11 | 珠海华迈航空科技有限公司 | Four -rotor aircraft |
| CN105667777A (en) * | 2016-03-29 | 2016-06-15 | 普宙飞行器科技（深圳）有限公司 | Four-way-extensible paddle protecting cover, power system and unmanned aerial vehicle |
| CN105947202A (en) * | 2016-04-28 | 2016-09-21 | 乐视控股（北京）有限公司 | Foldable unmanned aerial vehicle and application method thereof |
| CN106081084A (en) * | 2016-07-11 | 2016-11-09 | 南京航空航天大学 | A kind of spherical unmanned plane of portable and collapsible |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2018120163A1 (en) | 2018-07-05 |
| CN107108026A (en) | 2017-08-29 |
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