CN107031828A - A kind of unmanned plane - Google Patents
A kind of unmanned plane Download PDFInfo
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- CN107031828A CN107031828A CN201611054657.1A CN201611054657A CN107031828A CN 107031828 A CN107031828 A CN 107031828A CN 201611054657 A CN201611054657 A CN 201611054657A CN 107031828 A CN107031828 A CN 107031828A
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- Prior art keywords
- unmanned plane
- wing
- elementary cell
- connector
- mentioned
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
- B64C39/024—Aircraft not otherwise provided for characterised by special use of the remote controlled vehicle type, i.e. RPV
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/46—Arrangements of, or constructional features peculiar to, multiple propellers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
- B64D47/08—Arrangements of cameras
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/13—Propulsion using external fans or propellers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
- B64U2101/30—UAVs specially adapted for particular uses or applications for imaging, photography or videography
Abstract
The invention discloses a kind of unmanned plane, the unmanned plane, which is provided with, allows stable wing structure, at the same time, be additionally provided with the landing gear that the things such as the filming apparatus loaded by way of parenthesis can be expeditiously provided in unmanned plane.For this, unmanned plane according to embodiments of the present invention is provided with more than one wing components centered on body, above-mentioned body includes fastening the fastening part of above-mentioned wing components, connector that above-mentioned wing components include being used for and above-mentioned fastening part is fastened, with reference in above-mentioned connector and generating the more than one wing part of propulsive force, above-mentioned connector is fastened or separated with above-mentioned fastening part by connecting portion formation predetermined angle, and above-mentioned predetermined angle is then changed by user.Whereby, it can stably be run due to having used new wing structure, be able to realize miniaturization in the handling process of unmanned plane provided with new wing structure and landing gear, therefore, it is possible to improve the overall operation efficiency of unmanned plane.
Description
Technical field
The present invention relates to a kind of unmanned plane as unmanned airborne vehicle, in more detail, the unmanned plane, which has, allows operation more
Stable wing structure and be equipped with can more effectively carry filming apparatus landing mechanism.
Background technology
Unmanned plane from military supplies industry refers to the aircraft for not carrying personnel and the induction flight according to radio wave
Or the flying body of helicopter apperance.
Recent people widely carry out military and business application using unmanned plane, and people also carry out ardent research to it.
But, the volume of traffic increase that the trend for the increase in demand of unmanned plane will cause unmanned plane to fly on high, and
And cause that unmanned plane is awing collided or the possibility of overtaking collision can also increase.And for unmanned plane operate be unfamiliar with, electricity
The reason for tank discharge, failure etc, caused unmanned plane falling accident can also increase.During using unmanned plane it is incident on
The phenomenon for stating dangerous raising may result in loss on human life or property.
Recently, unmanned plane is used due to that can provide many interests of simplicity, swiftness and economy etc in military affairs
The various fields such as logistics distribution, the disaster relief, broadcast, outdoor activity are also widely used in beyond way.
Although unmanned plane possesses lot of advantages, but the external environment condition change and operation operation blown etc are unfamiliar with and caused
The possibility fallen is also higher.And unmanned plane and its parts price that is included are very high, therefore unmanned plane is damaged
When economic loss also than more serious.
Still more, not only can be because multi-rotor aerocraft unmanned plane is damaged in itself and brings very serious when unmanned plane falls
Economic loss, can also cause serious secondary injury to people and article.
Cause the operation stability of unmanned plane is received to attract attention in view of the foregoing, in order to maintain the stability, nobody
The wing components of machine and the structure design of landing mechanism turn into very important problem.
That is, when designing the wing components structure of unmanned plane, it is necessary to during in view of landing unmanned plane it is stable rise or under
The problem of drop, take off after the operation problem that is moved towards a certain specific direction, therefore need to develop and can solve the problem that this two at present
The unmanned air vehicle technique of problem.
Moreover, the wing components of existing unmanned plane largely take the form integral with body, but a bodily form
State has the danger of breakage etc at any time in the handling process of unmanned plane, it is therefore desirable to develops and can solve the problem that the danger
Wing components structure.
Moreover, the landing mechanism of unmanned plane plays the role for allowing unmanned plane body to keep stable in unmanned plane landing,
Especially the unmanned plane of recent development possesses the filming apparatus of variform in order to carry out Aerial photography, it is therefore desirable to develop
Go out the landing mechanism structure that effectively filming apparatus can be loaded into limited unmanned plane space.
As one, " the unmanned airborne vehicle of the rotating multi wing " of KR published patent the 10-2014-0102584th need not
Adjust the spacing of unmanned airborne vehicle rotary wings with regard to can control its posture and direction and the simplification for being achieved housing construction, due to
Eliminate large-scale main rotor (main rotor) and fatal security incident can be prevented, moreover it is possible to solve the rising around rotary wings
The problem of air-flow may cause.
But, the rotary wings that above-mentioned prior art disclosed the main rotor for excluding larger structure and be stabilized operation
(rotor blade) structure, but not propose can solve the problem that unmanned airborne vehicle (unmanned plane) mentioned above overall problem and and its
The alternative solution of compatibility issue between its device (filming apparatus etc.).
Therefore, in the urgent need to developing a kind of unmanned plane for the overall problem that can effectively solve the problem that unmanned plane mentioned above.
The content of the invention
Present invention seek to address that above mentioned problem, it is an object of the invention to provide a kind of unmanned plane, it is provided with stable operation
Wing structure, it is to avoid unmanned plane is damaged dangerous present in handling process, is additionally provided with and allows the thing such as filming apparatus of subsidiary loading
The landing gear in unmanned plane can be expeditiously provided in.
To reach above-mentioned purpose, the present invention is adopted the following technical scheme that：
A kind of unmanned plane, including body and the more than one wing components centered on body, described body include
The fastening part of the described wing components of fastening；Described wing components include being used for the connector fastened with described fastening part and
The more than one wing part of motive force is connected and generated with connector；Described connector forms predetermined angle by connecting portion
Ground and the fastening of above-mentioned fastening part are separated, and described predetermined angle is changed by user.
Further, in addition to described body the landing mechanism being connected, described landing mechanism is in landing from ground
Support described body in face；Described landing mechanism is two be oppositely arranged, and include being connected with described body the
One elementary cell, the second elementary cell connected with the first elementary cell, with the second elementary cell connection and contacting with ground
3rd elementary cell.
Further, folded by the second described elementary cell relative to described the first elementary cell and allow described the
Three elementary cells are towards ground direction or described body direction.
Further, the first described elementary cell is allowed to be in direction by the jackknife action of the second described elementary cell
Ground direction or the state of bottom surfaces parallel to described body.
Further, described body includes the collecting part for being used to store default device in bottom surfaces；Described collecting part
Including fastener and fixture, described fixture is used to connect body, and it is default that described fixture is stored for fixing
Device.
Further, described wing part includes propeller, described wing part with different combination angles with it is described
Connector connection, so as to each propeller radius of turn it is a part of overlapping.
Further, the wing part and the combination angle of respective connector being oppositely arranged centered on body are identical.
Technical solutions according to the invention are relative to prior art, the beneficial effect of acquirement：
According to the unmanned plane of above-mentioned solution, can stably it be run due to having used new wing structure.
In addition, the new wing structure and landing gear of the present invention can make unmanned plane realize miniaturization in handling process,
The breakage avoided in handling process is dangerous, so as to improve the overall operation efficiency of unmanned plane.
In addition, the auxiliary device (filming apparatus etc.) installed in unmanned plane body can be in limited space expeditiously
Install and improve the utilization degree of auxiliary device.
Brief description of the drawings
Accompanying drawing described herein is used for providing further understanding invention, constitutes the part of the present invention, the present invention
Schematic description and description be used for explain the present invention, do not constitute inappropriate limitation of the present invention.In the accompanying drawings：
Fig. 1 is the unmanned plane external structure stereogram of the embodiment of the present invention 1；
Fig. 2 for the embodiment of the present invention 1 unmanned plane wing components and the fastening part fastened with it a part stereogram；
Fig. 3 for the embodiment of the present invention 1 unmanned plane wing components and the fastening part fastened with it a part exploded view；
Fig. 4 is the stereogram of a part for the collecting part of the unmanned plane of the embodiment of the present invention 1；
Fig. 5 is the stereogram of the unmanned plane for possessing landing mechanism of the embodiment of the present invention 2；
Fig. 6 is the UAV Landing structural scheme of mechanism of the embodiment of the present invention 2；
Fig. 7 is stereogram of the unmanned plane of the embodiment of the present invention 2 in landing mechanism folded state；
Fig. 8 is the folded state schematic diagram of the UAV Landing mechanism of the embodiment of the present invention 2；
Fig. 9 is the wing components schematic diagram of the unmanned plane of the embodiment of the present invention 3.
Embodiment
The objects, features and advantages of the invention described above will further be explained by the following example.
Explanation below for specific structure or even function is simply to illustrate that the embodiment based on concept of the present invention and example
Show, the embodiment based on concept of the present invention can be implemented by a variety of forms, must not limit the present invention to this specification
Or accompanying drawing embodiment described.
Embodiment based on concept of the present invention can realize a variety of modifications, can also have various forms, the present invention will be
Specification or accompanying drawing describe specific embodiment in detail.The present invention can realize diversified modification, can also have various embodiments,
However, particular implementation form therefore can not be confined to the embodiment based on concept of the present invention, it is understood that the present invention's
All displacements, deformation and the modification carried out in technology and thought category is included.
A certain inscape is recited as " connecting " or during " access " other inscapes, although be construed as directly
Other inscapes are connected or accessed, can also be understood to that centre has other inscapes.On the contrary,
When a certain inscape is recited as " being directly connected to " or " being directly accessed " other inscapes, it should be understood that do not deposit centre
In other inscapes.Also should so it be explained for other terms for showing the relation between inscape.
Term used herein is only explanation specific embodiment and used, and must not therefore limit to the present invention.Unless
Can significantly it be distinguish between in the arteries and veins reason of sentence, otherwise odd number manifestation mode also includes the situation of plural number.
It is feature that the term such as the " comprising " of the application or " having " is only referred to determine to be implemented on specification, numeral, step, dynamic
Work, inscape, the presence of part or combinations thereof, are not construed as eliminating one or more other spies in advance
Levy, numeral, step, action, inscape, the presence or the presence of additional possibility of part or combinations thereof.
Unless given different definition in addition, otherwise all arts as used herein including technology or scientific terminology
Meaning represented by language is identical with the meaning that in the technical field of the invention there are the people of general knowledge generally to understand.One
As have defined term in dictionary meaning should be interpreted with managing had meaning according to the article arteries and veins of correlation technique
Unanimously, define, otherwise singularly or excessively must not make an explanation to formalism unless clearly given in this application.
Illustrate the preferred embodiments of the present invention below in conjunction with the accompanying drawings and describe effect of the invention in detail to obtain.Each accompanying drawing
In same graphical symbol represent same component.
First, the overall structure of according to embodiments of the present invention 1 unmanned plane is described based on Fig. 1 in detail below.
Fig. 1 shows the unmanned plane external structure stereogram of the embodiment of the present invention 1.Specifically, Fig. 1 is from the embodiment of the present invention
The stereogram that 1 unmanned plane 1 is watched from bottom.
As shown in figure 1, the unmanned plane 1 of the embodiment of the present invention 1 includes body 100, wing components 200 and collecting part 300.
Body 100 supports whole unmanned plane 1, and each side of body 100 is connected to wing components 200.Fig. 1 shows connection
Wing components 200 to body 100 are the situation of 4.As shown in figure 1, body 100 respectively side is connected when being shaped as cuboid
Wing components 200 and each wing components 200 can then be configured relative to one another.But, body 100 can not also take above-mentioned length
Cube and take other shapes, the quantity of the wing components 200 connected is then different according to the shape.
Moreover, the various mission relatives for being used for running unmanned plane 1 can be provided with inside body 100.That is, inside body 100
The means of communication communicated for the manipulation instrument with external control person, the control for controlling the operation of unmanned plane 1 can be provided with
Instrument processed etc..
As shown in figure 1, the fastener 120 for being used for stably fastening wing components 200 can be provided with body 100.Here,
Fastening part 120 is the instrument for allowing body 100 and wing components 200 stably to fasten, it is preferable that it is perpendicular to body 100
Formed one side.
As shown in figure 1, wing components 200 can set more than one, the wing components 200 include connector 210 and machine
Wing member 230.Connector 210 is used for fastening with body 100 and fastening part 120, and wing part 230 is connected to connector 210 and raw
Into the propulsive force for driving unmanned plane 1 to move.
Connector 210 can be provided with connecting portion and be fastened on fastening part 120 with connecting portion, later in association with Fig. 2 to Fig. 3
It is described in detail.
More than one wing part 230 can be provided with a wing components 200.Also i.e., it is possible in a connector
One or more wing parts 230 are connected on 210.The quantity of the wing part 230 can be to the translational speed performance required for unmanned plane 1
Or direction conversion performance is impacted.
Moreover, the end of wing part 230 can the propeller 250 provided with generation propulsive force.Propeller 250 can be with many kinds
Form is formed at wing part 230.In general, perpendicular to the bearing of trend of wing part 230, (wing part 230 is connected to rotary shaft
The direction extended after connector 210) preferably.
Moreover, collecting part 300 can combine the bottom surfaces in body 100, collecting part 300, which possesses, can store camera etc.
The space of the default device of filming apparatus etc.Preferably, collecting part 300 can possess same shape (in figure with body 100
It is in 1 and the identical rectangular shape of body 100) and the form that extends downward.
Moreover, collecting part 300 can be combined in body 100 or separated by fastener 350.Collecting part 300 may be used also
Internally or to be externally formed with the default device of storage to be subject to fixed fixture., can be in collecting part 300 as one
An internal side formed allow camera etc filming apparatus be stably installed on inside collecting part 300 fixture (not to
Go out diagram).
Describe the wing components 200 of the unmanned plane 1 of the embodiment of the present invention 1 in detail with reference to Fig. 2 and Fig. 3 and fastened with it
Body 100 fastening part 120.
Fig. 2 shows the solid of the unmanned plane wing components of the embodiment of the present invention 1 and a part for the fastening part fastened with it
Figure, Fig. 3 shows the exploded view of the unmanned plane wing components of the embodiment of the present invention 1 and a part for the fastening part fastened with it.
As shown in Fig. 2 the wing components 200 of the unmanned plane 1 of the embodiment of the present invention 1 are except including connector 210, wing part
230 and propeller 250 outside, in addition to connecting portion 205.
Connecting portion 205 is used for the fastening part 120 for allowing wing components 200 to be fastened to body 100, as shown in Figures 2 and 3, its
Connector 210 can be protruded from, and the space inserted for prominent connecting portion 205 is then formed on fastening part 120.This can lead to
The mode for the groove crossed in the insertion of connecting portion 205 fastening part 120 for protruding from connector 210 is by wing components 200 and fastening part 120
Fastening.The connecting portion 205 for protruding from connector 210 is each formed so that being connected with the groove on fastening part 120 in male and female form
It can be fastened between part 210 and fastening part 120.
Moreover, according to the shape of connecting portion 205 or the groove being formed in fastening part 120, wing components 200 being capable of shape
Fastening part 120 is fastened on into predetermined angle or is separated with fastening part 120.That is, connecting portion 204 or being formed at fastening part
The shape of groove in 120 can adjust formation with reference to angle to preferable.Therefore, the groove in fastening part 120 can also be opened up
Into multiple, and connecting portion 205 can select one of groove to insert, to realize adjustment combination angle.
More than one wing part 250 and connecting portion 205 are connected as shown in figure 3, can be provided with inside connector 230
The concrete mechanism connect.But, the internal structure of connector 230 shown in Fig. 3 be only one, internal structure it is not necessary to composition
Key element.
Then the collecting part 350 of the embodiment of the present invention 1 is illustrated based on Fig. 4.
Fig. 4 shows the stereogram of a part for the collecting part of the unmanned plane of the embodiment of the present invention 1.
As shown in figure 4, collecting part 300 can combine the bottom surfaces in body 100, specifically, collecting part 300 can have
There is the bottom surfaces identical area with body 100 and the bottom surfaces in body 100 can be combined by fastener 350.Pass through
The pothook of the side of body 100 is blocked or separated with the pothook of the side of collecting part 300, fastener 350 can be attached to
Body 100 or separation.
Collecting part 300 advantageously can be loaded into unmanned plane by the user of unmanned plane 1 by the fastener 350 of the form
1 or both are separated, therefore can effectively improve the shortcoming of the more difficult carrying of unmanned plane 1.
Next the unmanned plane 1 for possessing landing mechanism 400 in the embodiment of the present invention 2 is illustrated based on Fig. 5 to Fig. 8.
Fig. 5 shows the stereogram of the unmanned plane for possessing landing mechanism of the embodiment of the present invention 2, and Fig. 6 shows implementation of the present invention
The UAV Landing structural scheme of mechanism of example 2, Fig. 7 shows standing during the UAV Landing mechanism folded state of the embodiment of the present invention 2
Body figure, Fig. 8 shows the folded state schematic diagram of the UAV Landing mechanism of the embodiment of the present invention 2.
First, as shown in figure 5, the unmanned plane 1 of the embodiment of the present invention 2 is provided with landing mechanism 400.Landing mechanism 400 is in nothing
Man-machine 1 stably supports body 100 from ground when taking off and landing.Although more than a pair can be equipped with, just in view of unmanned plane 1
Operation characteristic (lightness and reduce may constitute the works of obstacle) as far as possible and formed a pair it is preferable.The landing machine that a pair of composition
Structure can be oppositely arranged.
Landing mechanism 400 can be connected to a side of body 100 as illustrated in fig. 5, and form pre- with ground direction
If angle is extended downwardly.
Landing mechanism 400 include be connected with body 100 the first elementary cell 410, be connected to the first elementary cell 410
Second elementary cell 420 and the 3rd elementary cell 430 for being connected to the second elementary cell and being contacted with ground.
Especially, the second elementary cell 420 can be folded by relative first elementary cell 410 allow the 3rd elementary cell
430 towards ground direction or body direction.Such as Fig. 6 to Fig. 8, the second elementary cell 420 can be by jackknife action and by two
The first elementary cell 410 formation straight line that pedestal is constituted, and allow a part for the second elementary cell 420 to insert the first elementary cell
Between 410 two pedestals.
By the jackknife action, the second elementary cell 420 can allow the 3rd elementary cell 430 in directly contact face to move
To the annex of body 100 or be re-directed towards ground land.
Although the Portability of foregoing unmanned plane 1 is preferably, the convenience that it is carried is weaker.But it is of the invention then pass through
The folding of landing mechanism 400 is effectively improved the movement of unmanned plane 1 and carries convenience.
Moreover, the jackknife action of above-mentioned second elementary cell 420 can be realized after unmanned plane takes off, in this situation
Under, driving part can be further equipped with landing mechanism 400.Now, operationally to reduce wind cloudy and significantly for unmanned plane
Reduce the possibility of collision obstacle in operation.
Moreover, as the jackknife action of above-mentioned second elementary cell 420, the first elementary cell 410 can also and body
100 coupling part, which is realized, to be folded.If that is, the jackknife action for depending merely on the second elementary cell 420 still can not be with optimal
When mode realizes the folding of landing mechanism 400, the first elementary cell 410 can be allowed by way of parenthesis also in the joint portion with body 100
Point folded, whereby, can as shown in Figure 7 allow landing mechanism 400 to realize the rugosity for being best suitable for flying in the best way
State.
Moreover, the jackknife action of the first elementary cell 410 can also attach the jackknife action of the second elementary cell 420 and reality
It is existing.That is, first base can proportionally be realized with the jackknife action (changes of folding angles) of the second elementary cell 420
The jackknife action of this unit 410, and optimal folding effect is realized by the jackknife action.
Finally, the wing components of the unmanned plane 1 of embodiments of the invention 3 are described in detail based on Fig. 9.
Fig. 9 shows the schematic diagram of the wing part of the unmanned plane of the embodiment of the present invention 3.
As shown in figure 9, the wing components of the unmanned plane 1 of the embodiment of the present invention 3 can allow located at more than one wing part 230-
1st, propeller 250-1,250-2,250-3 of 230-2,230-3 end each radius of turn is a part of overlapping.That is allowing
Formed a wing components multiple wing part 230-1,230-2,230-3 it is upper set by multiple propeller 250-1,250-2,
250-3 radius of turn is overlapped and multiple propellers are equipped with the confined space, and thus produces stronger motive force.
That is, just can be in the confined space to the combination angle of connector 210 only according to multiple wing part 230-1,230-2,230-3 are adjusted
It is interior as far as possible be equipped with more propeller 250-1,250-2,250-3, can so allow unmanned plane 1 up and down or left and right propulsive force more
By force.
Certainly, in order to be equipped with multiple propeller 250-1,250-2,250-3, it can adjust many according to the characteristic of unmanned plane 1
Combination angles of individual wing part 230-1,230-2, the 230-3 to connector 210.That is, although we can be by being equipped with
Multiple propeller 250-1,250-2,250-3 and adjust above-mentioned combination angle, but we can according to advance, retreat or on move down
Dynamic requirement determines wing part 230-1,230-2,230-3 optimal number.
So, be equipped with multiple wing part 230-1,230-2,230-3 and cause each propeller 250-1,250-2,
250-3 radius of turn is overlapping, can be designed by the overlapping phenomenon in the case where not hindering the flight of unmanned plane 1.And
And, multiple wing part 230-1,230-2,230-3 quantity can be equipped with a wing components 200 as shown in Figure 9 with odd number
To be preferable.Such as, as shown in Figure 9, it is preferable that allow and be located at middle wing part in three wing parts 230-1,230-2,230-3
230-2 position (the combination angle with connector 210) is different with wing the part 230-1 or 230-3 positioned at both sides.
The preferred embodiments of the present invention are description above described, it is to be understood that the present invention is not limited to above-mentioned implementation
Example, and the exclusion to other embodiment should not be regarded as.By the enlightenment of the present invention, those skilled in the art combine known or existing
The change that technology, knowledge are carried out also should be regarded as within the scope of the present invention.
Claims (7)
1. a kind of unmanned plane, including body and the more than one wing components centered on body, it is characterised in that：
Described body includes the fastening part of the wing components described in fastening；
Described wing components include the connector for being fastened with described fastening part and are connected with connector and generate promotion
The more than one wing part of power；
Described connector is fastened with above-mentioned fastening part or separated, described predetermined angle by connecting portion formation predetermined angle
Changed by user.
2. a kind of unmanned plane according to claim 1, it is characterised in that：
Also include the landing mechanism being connected with described body, described landing mechanism supports described sheet in landing from ground
Body；
Described landing mechanism is two be oppositely arranged, and include be connected with described body the first elementary cell, and
Second elementary cell of the first elementary cell connection, the 3rd elementary cell for connecting and being contacted with ground with the second elementary cell.
3. a kind of unmanned plane according to claim 2, it is characterised in that：
Folded by the second described elementary cell described the first elementary cell relatively and allow the 3rd described elementary cell direction
Ground direction or described body direction.
4. a kind of unmanned plane according to claim 3, it is characterised in that：
The first described elementary cell is allowed to be in towards ground direction or flat by the jackknife action of the second described elementary cell
Row is in the state of the bottom surfaces of described body.
5. a kind of unmanned plane according to claim 1, it is characterised in that：
Described body includes the collecting part for being used to store default device in bottom surfaces；
Described collecting part includes fastener and fixture, and described fixture is used to connect body, and described fixture is used for
The fixed default device stored.
6. a kind of unmanned plane according to claim 1, it is characterised in that：
Described wing part includes propeller, and described wing part is connected with different combination angles with described connector,
So as to each propeller radius of turn it is a part of overlapping.
7. a kind of unmanned plane according to claim 6, it is characterised in that：
The wing part and the combination angle of respective connector being oppositely arranged centered on body are identical.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| KR10-2016-0079938 | 2016-06-27 | ||
| KR1020160079938A KR101731054B1 (en) | 2016-06-27 | 2016-06-27 | Drone |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107031828A true CN107031828A (en) | 2017-08-11 |
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| CN201611054657.1A Pending CN107031828A (en) | 2016-06-27 | 2016-11-25 | A kind of unmanned plane |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107972854A (en) * | 2017-10-27 | 2018-05-01 | 成都睿翼无人机科技有限公司 | A kind of power patrol unmanned machine |
| JP2019172259A (en) * | 2017-11-06 | 2019-10-10 | 株式会社エアロネクスト | Flying body and method for controlling flying body |
| WO2020125523A1 (en) * | 2018-12-18 | 2020-06-25 | 深圳市格上格创新科技有限公司 | Foldable multi-rotor unmanned aerial vehicle |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR102381007B1 (en) * | 2017-06-26 | 2022-03-31 | (주)비씨디이엔씨 | Double folding landing gear and Vibration-free gimbal device having it |
| KR101967802B1 (en) * | 2017-07-07 | 2019-08-13 | 전남대학교산학협력단 | A hybrid shooting system utilizing the cable robot and the drone |
| KR102199908B1 (en) * | 2019-10-21 | 2021-01-08 | 한국항공우주연구원 | Multi-copter |
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| KR101366208B1 (en) * | 2013-05-02 | 2014-02-25 | 주식회사 네스앤텍 | Multi-rotor type small aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| JP2019172259A (en) * | 2017-11-06 | 2019-10-10 | 株式会社エアロネクスト | Flying body and method for controlling flying body |
| WO2020125523A1 (en) * | 2018-12-18 | 2020-06-25 | 深圳市格上格创新科技有限公司 | Foldable multi-rotor unmanned aerial vehicle |
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| Publication number | Publication date |
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| KR101731054B1 (en) | 2017-04-27 |
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