CN109808877A - A kind of unmanned plane variable wing and its method - Google Patents
A kind of unmanned plane variable wing and its method Download PDFInfo
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- CN109808877A CN109808877A CN201811634598.4A CN201811634598A CN109808877A CN 109808877 A CN109808877 A CN 109808877A CN 201811634598 A CN201811634598 A CN 201811634598A CN 109808877 A CN109808877 A CN 109808877A
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Abstract
The present invention provides a kind of unmanned plane variable wing and its method, wherein the unmanned plane variable wing includes a fuselage；Two ailerons；Two wings；One empennage and at least three propellers, the setting of two ailerons is symmetrically disposed on the front of the fuselage, two wings are symmetrically disposed on the fuselage afterbody, the empennage is set on the upside of the afterbody, wherein a propeller is fuselage propeller, is arranged at the fore-body, the two aileron corresponding positions, propeller described in two of them is wing propeller, is arranged at the wing respectively, each wing propeller is rotatablely arranged at each wing respectively.
Description
Technical field
The present invention relates to a kind of unmanned plane, in particular to a kind of unmanned plane variable wing and its method, wherein described variable wing
Unmanned plane can be needed based on different flight, to adjust state of flight.
Background technique
With the continuous development of e-commerce, express transportation is become more and more important.
It is well known that vital two factors are exactly time and safety in express transportation.
When user has purchased a commodity, may be eager to take commodity very much.Even if without especially eager demand, if
See that the commodity being sent in time are also the something being in a cheerful frame of mind.Still further aspect, the safety of transportational process are also to closing
It is important, if the user sees that there is breakage in the thing sent, it will be appreciated that the mood of user should be less pleasant.
Another situation, requirement meeting of the user when posting some smallclothes things or some vital documents, for the time
It is higher, it may be necessary to be sent to other side place in a very short period of time.It may be based on posting the configuration of the basic procedure, human resources of part
And various factors such as traffic conditions, either conveying purchase commodity still be eager mailing object, the time is always
It has no idea to accomplish immediately.
For such status, each large size express company is dedicated to the research of unmanned plane transport.Existing various multiaxises fly
Row device is the trial in terms of unmanned plane transport.In general, the structure of Multi-axis aircraft is, by multiple interconnections
Axis constitutes flight wing.A propeller is arranged in the end of each wing, as power mechanism.Wing interconnection position
It is exactly position of centre of gravity as carrying cargo position.But this Multi-axis aircraft, due to the design feature of its own, there are many
Problem.
Due to the approximate circle structure of Multi-axis aircraft, aerodynamic Streamline Design is not met, it is made to fly
Cheng Zhong, the resistance being subject to is larger, and the power that take-off process needs is also larger, therefore the electric energy consumed is more, and there are cruise duration
Distinct disadvantage short, voyage is short.
Accordingly for such problems, also there are the three axis unmanned planes for imitating large aircraft and designing.Existing three
Axis unmanned plane, general structure use canard configuration, including a main wing and two groups of canards, two groups of canards to be vertically connected at side by side
Main wing.Such unmanned plane relative to Multi-axis aircraft, in structure for, two kinds of new shapes of identical scale, canard cloth
The resistance that office is subject to relative to Multi-axis aircraft is smaller, more meets air and takes offence and learn principle, therefore with identical power source
Under the conditions of, the cruising ability and voyage of three axis unmanned planes of canard configuration have and are relatively improved.The three of existing canard configuration
But axis unmanned plane improves in some terms, still there are many problems.
Although firstly, Multi-axis aircraft structure do not have it is streamlined, but due to its multiaxis feature, at the end of each axis
As soon as portion is fitted with a propeller as power source, therefore multiaxis also has more power sources, therefore uses canard configuration
Three axis unmanned planes, due to the change of its structure, on the basis of meeting aerodynamics, can install the position of propeller compared with
Few, the size of lift is related by the size of speed during aircraft taxi, it is therefore necessary to have it is certain slide place, reach
Certain speed can take off.On the other hand, the air drag in flight course reduced in structure, can be to provide
Power source is reduced, therefore still there is place to be improved in terms of cruise duration and voyage.
On the other hand, the unmanned plane of existing a kind of canard configuration, in canard two sides, installation propeller is as power source, such as
Upper described, such unmanned plane, the power source provided is less, take off and flight course in all have it is more highly difficult.
In addition, in the prior art, there are a kind of unmanned plane variable wing, propeller is mounted on canard two for fast braking
The two sides of side, canard can rotate within a certain angle.It is taking off, is flying, and canard is different during landing
State so that changing propeller provides the direction of power, therefore improves the property of the unmanned plane of canard configuration to a certain extent
Energy.But this unmanned plane variable wing, the problem of equally existing several aspects.
Firstly, helicopter and Multi-axis aircraft be since the power source of its installation is generally all right above fuselage, it can
VTOL may be implemented in other words to take off in lesser distance, but the unmanned plane of this canard configuration, due to its offer
Power source position and elongation fuselage shape, make it that must there is certain coasting distance, make its reach certain speed,
There is provided lift by wing can just take off, therefore can not achieve VTOL, be unsuitable for small place flight.
Secondly, the aircraft of this canard configuration is insensitive for course control.That is, passing through the spiral shell for changing wing two sides
The speed of paddle is revolved to change course, and the speed of adjusting is slower, influences the accuracy of the line of flight.
The aircraft of third, this canard configuration can not achieve the pitch control of end.That is, in vertical flying height
Change in terms of adjustable range very little, may reach after a certain flying height carries out, need the flight of sudden change aircraft
Height or heading, such case are then difficult to realize.
Advantage and disadvantage existing for comprehensive various small aircrafts existing in the prior art, the present invention exist from above-mentioned various aspects
The problem of start with, it is expected that obtaining a kind of being more suitable for the unmanned plane applied in small freight transport.
Summary of the invention
It is an object of the present invention to provide a kind of unmanned plane variable wing and its methods, wherein the unmanned plane variable wing
It can be needed based on different flight, to adjust state of flight.
It is an object of the present invention to provide a kind of unmanned plane variable wing and its methods, wherein the unmanned plane variable wing
Landing can be carried out in any place suitable for landing, to expand the use scope of the unmanned plane variable wing.
It is an object of the present invention to provide a kind of unmanned plane variable wing and its methods, wherein the unmanned plane variable wing
With longer cruising ability, so that the unmanned plane variable wing is suitable for the flight of long range.
It is an object of the present invention to provide a kind of unmanned plane variable wing and its methods, flight compared with the existing technology
For device, the unmanned plane variable wing can have the flight characteristic of the distinctive stability of Multi-axis aircraft, it is possible to have long
The flight characteristic of the Fixed Wing AirVehicles such as endurance, long-distance flight and high pneumatic efficiency, thus, the unmanned plane variable wing exists
It does not need under the premise of increasing self weight, there is good state of flight.
It is an object of the present invention to provide a kind of unmanned plane variable wing and its methods, wherein the unmanned plane variable wing
State of flight can be rapidly adjusted, the especially described unmanned plane variable wing can be realized rapidly from level flight condition to outstanding
Stop the adjustment between state of flight.
It is an object of the present invention to provide a kind of unmanned plane variable wing and its methods, wherein the unmanned plane variable wing
Multiple propellers are provided, by the cooperation of every propeller, the unmanned plane variable wing can be realized such as turn, dive,
The state of flights such as new line, and the flight flexibility of the unmanned plane variable wing can be ensured effectively.For example, the change
The turning of wing formula unmanned plane can pass through the differential (rotational speed difference, i.e., per the propeller with different turns of every propeller
Speed) Lai Shixian.
It is an object of the present invention to provide a kind of unmanned plane variable wing and its methods, wherein being installed on described variable wing
The propeller of one fuselage of unmanned plane can be a contrarotating propeller, in this way, the flight of the unmanned plane variable wing
Stationary performance accesses guarantee, to ensure the flight safety of the unmanned plane variable wing.
It is an object of the present invention to provide a kind of unmanned plane variable wing and its methods, wherein the unmanned plane variable wing
Layout be similar to traditional canard vehicle spatial layout feature, performance of having a smooth flight, which accesses, effectively to be ensured.
It is an object of the present invention to provide a kind of unmanned plane variable wing and its methods, wherein the unmanned plane variable wing
Under high-incidence condition, anti-stall ability with higher.
It is an object of the present invention to provide a kind of unmanned plane variable wing and its methods, wherein the unmanned plane variable wing
Air transportion particularly suitable for shipping parcels.
It is an object of the present invention to provide a kind of unmanned plane variable wing and its methods, and wherein load may act on described
The lower position of drone center of unmanned aerial vehicle variable wing, hovering stability with higher, in this way, it is described it is variable wing nobody
The flight safety of machine is ensured.
It is an object of the present invention to provide a kind of unmanned plane variable wing and its methods, wherein more than two framves or two framves
The unmanned plane variable wing can cooperate, to realize the transport of the cargo of the big scale of construction.In other words, nothing variable wing described in multi rack
It is man-machine to can have good cooperative ability.
In order to achieve the above object, the present invention provides a kind of unmanned plane variable wing comprising:
One fuselage；
Two wings are symmetrically disposed on the fuselage per the wing；And
At least three propellers are respectively arranged at the fuselage per the propeller and per the wing, are provided in every
The propeller of the wing is able to do the axial movement relative to the fuselage.
A preferred embodiment according to the present invention, the unmanned plane variable wing further include a power device, described dynamic
Power device is set to the fuselage, and is respectively coupled to the power device per the propeller.
A preferred embodiment according to the present invention, the unmanned plane variable wing further include a toter, the fortune
It carries to install and is placed in the fuselage, and the toter acts at the position of the fuselage and the center of the fuselage
In same vertical direction.
A preferred embodiment according to the present invention, the unmanned plane variable wing further include a lifting gear, and described
Falling unit is set to the lower section of the fuselage.
A preferred embodiment according to the present invention is selectively arranged at the middle part of the wing per the propeller
Or end.
A preferred embodiment according to the present invention respectively includes a connection wing and an adjustment wing per the wing, often
The connection wing is set to the fuselage, is rotatablely arranged at per the adjustment wing per the connection wing, and per the spiral shell
Rotation paddle is respectively arranged at per the connection wing.
A preferred embodiment according to the present invention respectively includes a connection wing and an adjustment wing per the wing, often
The connection wing is set to the fuselage, is rotatablely arranged at per the adjustment wing per the connection wing, and per the spiral shell
Rotation paddle is respectively arranged at per the adjustment wing.
A preferred embodiment according to the present invention is able to per the propeller with rotational speed difference.
A preferred embodiment according to the present invention, the propeller for being set to the fuselage is a contrarotation spiral shell
Revolve paddle.
A preferred embodiment according to the present invention respectively includes an at least blade per the propeller, per the paddle
Leaf is respectively provided with a bow oar face and a face of blade, and the curvature in the bow oar face is greater than the curvature of the face of blade.
According to an aspect of the present invention, a kind of unmanned plane variable wing is also provided comprising:
One fuselage；
At least two propellers；And
Two wings respectively include a connection wing and an adjustment wing per the wing, wherein symmetrically per the connection wing
It is set to the fuselage, is rotatablely arranged at respectively per the adjustment wing per the connection wing, and is selected per the propeller
It is set to selecting property per the connection wing or per the adjustment wing.
A preferred embodiment according to the present invention, a propeller are set to the fuselage, and the spiral shell
Rotation paddle is a contrarotating propeller.
A preferred embodiment according to the present invention is able to per the propeller with rotational speed difference.
A preferred embodiment according to the present invention respectively includes an at least blade per the propeller, per the paddle
Leaf is respectively provided with a bow oar face and a face of blade, and the curvature in the bow oar face is greater than the curvature of the face of blade.
A preferred embodiment according to the present invention, the unmanned plane variable wing further include a power device, described dynamic
Power device is set to the fuselage, and is respectively coupled to the power device per the propeller.
A preferred embodiment according to the present invention, the unmanned plane variable wing further include a toter, the fortune
It carries to install and is placed in the fuselage, and the toter acts at the position of the fuselage and the center of the fuselage
In same vertical direction.
A preferred embodiment according to the present invention, the unmanned plane variable wing further include a lifting gear, and described
Falling unit is set to the lower section of the fuselage.
According to an aspect of the present invention, a kind of flying method of unmanned plane variable wing, the nothing variable wing are also provided
Man-machine includes a fuselage and the wing for being symmetrically disposed on the fuselage, wherein every the method includes making to be respectively arranged at
One propeller of the wing both horizontally and vertically between adjust, to change the flight shape of the unmanned plane variable wing
State.
A preferred embodiment according to the present invention further comprises the steps of: in the above-mentioned methods
(a) the connection wing for being symmetrically disposed on the fuselage is provided；
(b) the adjustment wing being rotatablely arranged at per the connection wing is provided, per the connection wing and per the adjustment
The wing is respectively formed per the wing, and is selectively arranged at per the propeller per the connection wing or per the adjustment
The wing；And
(c) make to adjust per the adjustment wing in the horizontal direction and the vertical direction.
A propeller is arranged in the machine in the above-mentioned methods in a preferred embodiment according to the present invention
Body, and the propeller is a contrarotating propeller.
A preferred embodiment according to the present invention makes to generate rotational speed difference per the propeller in the above-mentioned methods.
A preferred embodiment according to the present invention makes to generate rotational speed difference per the propeller in the above-mentioned methods.
A preferred embodiment according to the present invention respectively includes an at least blade per the propeller, per the paddle
Leaf is respectively provided with a bow oar face and a face of blade, and the curvature in the bow oar face is greater than the curvature of the face of blade.
Detailed description of the invention
Fig. 1 is stereoscopic schematic diagram according to a preferred embodiment of the present invention.
Fig. 2 is the stereoscopic schematic diagram of one variant embodiment of above preferred embodiment according to the present invention.
Fig. 3 is the stereoscopic schematic diagram at a visual angle of another preferred embodiment according to the present invention.
Fig. 4 is the stereoscopic schematic diagram at the another visual angle of above preferred embodiment according to the present invention.
Fig. 5 is the landing status diagram of the unmanned plane variable wing of above preferred embodiment according to the present invention.
Fig. 6 is the floating state schematic diagram of the unmanned plane variable wing of above preferred embodiment according to the present invention.
Fig. 7 is shape of the unmanned plane variable wing of above preferred embodiment according to the present invention from hovering flight to horizontal flight
The adjustment process schematic of state.
Fig. 8 is the level flight condition schematic diagram of the unmanned plane variable wing of above preferred embodiment according to the present invention.
Fig. 9 A and Fig. 9 B are that the unmanned plane variable wing of above preferred embodiment according to the present invention is bowing, facing upward state respectively
Schematic diagram.
Figure 10 is schematic diagram of the unmanned plane variable wing in side steering state of above preferred embodiment according to the present invention.
Figure 11 is a kind of schematic diagram of operational mode of the unmanned plane variable wing of above preferred embodiment according to the present invention.
Figure 12 is a kind of schematic diagram of control mode of the unmanned plane variable wing of above preferred embodiment according to the present invention.
Specific embodiment
It is described below for disclosing the present invention so that those skilled in the art can be realized the present invention.It is excellent in being described below
Embodiment is selected to be only used as illustrating, it may occur to persons skilled in the art that other obvious modifications.It defines in the following description
Basic principle of the invention can be applied to other embodiments, deformation scheme, improvement project, equivalent program and do not carry on the back
Other technologies scheme from the spirit and scope of the present invention.
It is unmanned plane variable wing according to a preferred embodiment of the present invention as shown in Figure 1, can be applied to all
The a variety of different industries of such as logistics transportation because the unmanned plane variable wing can based on flight need different states it
Between be adjusted, so that the unmanned plane variable wing can be improved the efficiency and safety of goods transportation.The skill of the art
Art personnel should be appreciated that according to actual needs the unmanned plane variable wing may be applied to other industries and field, because
This, can not be considered as the limitation to the contents of the present invention and range in above-mentioned lifted example.
Specifically, the unmanned plane variable wing includes a fuselage 10, two wings 20, at least two propellers 30, Yi Jiqi
He is respectively arranged at wherein being symmetrically disposed on the fuselage 10 per the wing 20 per the propeller 30 necessary component
The fuselage 10 and every wing 20.For example, in this embodiment in accordance with the invention, the quantity of the propeller 30 can be by
Three are embodied as, wherein the fuselage 10 can be respectively set at per the propeller 30 and per the wing 20, passes through this
The mode of sample, balance quality of the unmanned plane variable wing under state of flight, which accesses, effectively to be guaranteed, thus, it is ensured that it is described
The flight safety of unmanned plane variable wing.
It is noted that the unmanned plane variable wing can also include two ailerons 210 and a tail in other examples
The wing 220, wherein being symmetrically disposed on the front of the fuselage 10 per the aileron 210, the empennage 220 is set to the fuselage
10 rear portion, and per the aileron 210 and per the wing 20 extending direction having the same, so that per the aileron 210,
The main structure for constituting the unmanned plane variable wing with the fuselage 10 per the wing 20, in this way, in this hair
In bright some embodiments, the unmanned plane variable wing can have the structure of traditional aircraft, for example, the nothing variable wing
It is man-machine to can have canard configuration structure, to ensure that the unmanned plane variable wing has good balance and stabilization in flight
Property, to guarantee the safety of flight.Preferably, the empennage 220 is set on the upside of the tail portion of the fuselage 10, described in balance
The momentum of unmanned plane variable wing.
It is noted that being set to the front of the fuselage 10 per the aileron 210, institute is set to per the wing 20
The rear portion of fuselage 10 is stated, and the size per the aileron 210 is less than the size per the wing 20, thus, in the change wing
When formula unmanned plane is in state of flight, per the aileron 210 can be used in cooperate with per the wing 20 to it is described it is variable wing nobody
Machine provides lift.
Further, in some embodiments of the invention, there is a upper side 201 and a downside per the wing 20
202, wherein the curvature of the upper side 201 is preferably greater than the curvature of the downside 202, in other words, the upper side
201 degree of convexity is greater than the degree of convexity of the downside 202, in this way, on the one hand, can reduce air pair
In the resistance of the unmanned plane variable wing under state of flight, thus, make the unmanned plane variable wing that there is boat faster
Fast and farther flying distance, on the other hand, additionally it is possible to make that there is better lift per the wing 20.It is noted that
Also can have the structure per the wing 20 per the aileron 210, thus, make the unmanned plane during flying variable wing it is safer,
Reliably.
Under normal circumstances, the formalness of aircraft and its state of flight have close relevance, for example, aircraft
Configuration and layout can be related to the flight characteristic and flying quality of aircraft, traditionally, need when in order to meet different
It wants, the formalness of different types of aircraft will be different, for example, in this embodiment in accordance with the invention, the change wing
Formula unmanned plane can form traditional canard configuration structure, in this way, the unmanned plane variable wing can be made to do
When the movements of mobility such as the facing upward of big intensity, tight spiral, the unmanned plane variable wing per 210 He of aileron
Can all generate per the wing 20 makes the air around the unmanned plane variable wing form powerful vortex, the vortex of varying strength
Between intercouple can enhance its generation lift.Especially in the state that the unmanned plane variable wing is in High Angle of Attack,
Reducing generation lift per 210 needs of the aileron can make the aircraft variable wing generate nose-down pitching moment, thus, effectively
The unmanned plane variable wing being guaranteed under High Angle of Attack state is suppressed the controllability excessively to come back.Therefore, of the invention
In specific embodiment, better controllability can be made it have using the unmanned plane variable wing of canard configuration.
Nevertheless, it should be understood by those skilled in the art that in other embodiments of the invention, the change
Wing formula unmanned plane can also have other kinds of layout, to meet different flight needs.Therefore, using the institute of canard configuration
Unmanned plane variable wing is stated only as an example to be not intended as to of the invention the advantages of describing the unmanned plane variable wing
The limitation of content and range.
As shown in Figure 1, being the unmanned plane variable wing according to a preferred embodiment of the present invention, it is provided in institute
The propeller 30 for stating fuselage 10 is defined as a fuselage propeller 31, correspondingly, being set to every institute per the wing 20
It states propeller 30 and is defined as a wing propeller 32, it is to be understood that in various embodiments, the fuselage propeller
31 can be consistent with the type per the wing propeller 32, can also be inconsistent.For example, in this embodiment, per described
Wing propeller 32 can have the structure of traditional propeller, and the fuselage propeller 31 is implemented as a contrarotation spiral
Paddle 31, to enhance the flying quality of the unmanned plane variable wing.
It is wherein rotatablely arranged at respectively per the wing propeller 32 per the wing 20, so that per the wing spiral shell
Rotation paddle 32 can do the axial movement relative to the fuselage 10.Specifically, set 10 direction of fuselage as horizontal direction,
Setting height direction is vertical direction, in this embodiment in accordance with the invention, can be in the water per the wing propeller 32
It square is adjusted between the vertical direction, to change the state of flight of the unmanned plane variable wing, thus, realize the change
Wing formula unmanned plane adjusts between horizontal flight and the state of hovering flight.That is, in the present invention, being set to per described
Wing 20 is able to do the axial movement relative to the fuselage 10 per the propeller 30, so as to be in per the propeller 30
When the horizontal direction, the unmanned plane variable wing can rapidly be flown with level flight condition, at every propeller 30
When the vertical direction, the unmanned plane variable wing can be flown with hovering flight state.Flight compared with the existing technology
For device, the unmanned plane variable wing has significant progress.
It is noted that can be set per the wing propeller 32 in every in this embodiment as described in Figure 1
The end of the wing 20；In this embodiment as described in Figure 2, every institute can also be set to per the wing propeller 32
State the middle part of wing 20.In other words, the end per the wing 20 is set to per 32 property of can choose of wing propeller
Portion or middle part, in this way, the topology layout of the unmanned plane variable wing can be enabled to be based on needing to be selected.It should be understood that
It is that in other examples per the wing propeller 32, other any positions that can be carried out can also be arranged at,
And ensure to be adjusted in the horizontal direction and the vertical direction per the wing propeller 32.
It is noted that by the fuselage propeller 31 and per the wing propeller 32 differential (rotational speed difference, i.e.,
Can have different revolving speeds per the propeller 30), it so that the unmanned plane realization variable wing is such as turned to
Etc. state of flights adjustment, to improve flexibility of the unmanned plane variable wing under state of flight.
It is unmanned plane variable wing according to another preferred embodiment of the invention as shown in Figure 3 and Figure 4, relative to above-mentioned excellent
It selects for embodiment, the unmanned plane variable wing can rapidly realize the state from the state of horizontal flight to hovering flight
Adjustment.
Specifically, a connection wing 21 and an adjustment wing 22 are respectively included per the wing 20, wherein per the connection wing
21 are set to the fuselage 10, are rotatably connected at respectively per the adjustment wing 22 per the connection wing 21, for example, at this
In embodiment, it is per the wing 20 close to the part of the fuselage 10 per the connection wing 21, is every per the adjustment wing 22
Part of the wing 20 far from the fuselage 10.By adjusting the direction of every adjustment wing 22, can make described variable wing
Unmanned plane can be realized the quick adjustment of the state from the state of horizontal flight to hovering flight, can also make described variable wing
Unmanned plane can be realized the adjustment of the state from the state of hovering flight to horizontal flight.In some embodiments of the invention,
Can be arranged at per the wing propeller 32 per the connection wing 21, by respectively driving per the wing propeller 32 and
It is adjusted to the vertical direction from the horizontal direction per the adjustment wing 22, the unmanned plane variable wing can be made to can be realized
The quick adjustment of state from the state of horizontal flight to hovering flight.In other embodiments of the invention, per described
Wing propeller 32 can also be arranged at per the adjustment wing 22, in this way, can synchronously drive per the wing propeller
32 are adjusted to the vertical direction from the horizontal direction with per the adjustment wing 22, so that the flight of the unmanned plane variable wing
State can faster and more easily be adjusted to improve the controllability and flexibility of the unmanned plane variable wing.
Preferably, parallel per the adjustment wing 22 with corresponding position respectively per the wing propeller 32, specifically,
When every wing propeller 32 is in the horizontal direction, the horizontal direction also is located at per the adjustment wing 22；Accordingly
Ground also is located at the vertical direction per the adjustment wing 22 when every wing propeller 32 is in the vertical direction, because
It is arranged at for every wing propeller 32 per the adjustment wing 22, when driving the rotation per the adjustment wing 22, per described
Wing propeller 32 can be rotated automatically, in other words, same with the movement per the adjustment wing 22 per the wing propeller 32
Step.
It further, further include an at least blade 33 per the propeller 30, the every spiral shell formed per the blade 33
Rotation paddle 30 can be formed simultaneously an axis, so as to can make rotating motion using the axis as axis per the blade 33, be worth mentioning
, the propeller 30 of different location can have identical quantity and the combination of identical structure per the blade 33,
Also it can have every blade 33 of different number or different structure combination.For example, in this example shown in Fig. 3 and Fig. 4
In, the quantity of the blade 33 of the fuselage propeller 31 can be six, and wherein blade 33 described in every two is overlappingly set
Set, with formed the fuselage propeller 31 starching and lower slurry, the quantity of the blade 33 per the wing propeller 32 can
To be two, thus, make the fuselage propeller 31 and can have different functions per the wing propeller 32.This technology
Field it will be appreciated by the skilled person that the fuselage propeller 31 cited by above-mentioned example with per the wing propeller 32
Type is only as illustrative explanation, in other examples, the fuselage propeller 31 and every wing propeller 32
There can also be other structures, therefore, the limitation to the contents of the present invention and range can not be considered as.
The unmanned plane variable wing further includes a power device 40, and the power device 40 is set to the fuselage 10, with
For providing power source for the unmanned plane variable wing, wherein it can be coupled to the power device 40 per the propeller 30,
During the unmanned plane during flying variable wing, rotation of the power device 40 by driving per the propeller 33, with
Realize the different state of flight of the unmanned plane variable wing, it is to be understood that the power device 40 is similarly the change wing
The flight of formula unmanned plane provides power source.Particularly, the power device 40 can make to have not per the propeller 33 respectively
With revolving speed make per speed difference is generated between the propeller 32, with the differential formed between per the propeller 30, for example,
By changing the revolving speed of the fuselage propeller 31, it can make that the unmanned plane variable wing makes new line or the flight of underriding is dynamic
Make, by making that there is different revolving speeds per the wing propeller 32, the unmanned plane variable wing can be assisted to execute turning etc.
Corresponding movement, in this way, the different state of flight of the adjustable unmanned plane variable wing, thus, improve institute
State the flexibility of unmanned plane variable wing.
In this embodiment of the invention, the fuselage propeller 31 equally may be implemented as the contrarotation spiral
Paddle 31, wherein the contrarotating propeller 31 is coupled to the power device 40, the power device 40 can drive described
Contrarotating propeller 31 makes rotating motion, and the power device 40 can control turning for the contrarotating propeller 31
Speed.In other words, by the power device 40, the fuselage spiral for being implemented as the contrarotating propeller 31 can be made
Paddle 31 and every wing propeller 32 have identical or different revolving speed, synergistically to adjust flying for the unmanned plane variable wing
Row state, thus, the performances such as the flight flexibility for enhancing the unmanned plane variable wing, having a smooth flight property, flight safety.
It is noted that can make described by adjusting every propeller 30 and per the position of the adjustment wing 22
Unmanned plane variable wing has different state of flights, and in such as Fig. 5 into example shown in Fig. 10, the present invention is with every wing spiral shell
Rotation paddle 32 is set to this specific embodiment per the adjustment wing 22, to describe per the wing propeller 32 and per described
Concrete condition of the wing 22 in the state of difference is adjusted, so that those skilled in the art are to the contents of the present invention and advantage
Understand with further.
In the present invention, it will be adjusted to per the adjustment wing 22 and per the wing propeller 32 from the horizontal direction
The vertical direction and when being adjusted to the horizontal direction from the vertical direction, the unmanned plane variable wing has difference
State.For example, in one embodiment of the invention, when the unmanned plane variable wing is per the adjustment wing 22 and per described
When wing propeller 32 is to start flight course as inceptive direction in the horizontal direction, the unmanned plane variable wing is undergone
Process can be but not limited to " ground-takes off-horizontal flight-comes back or bows-lateral turning-hovering-horizontal flight-landing-
Ground "；Correspondingly, when the unmanned plane variable wing is in described per the adjustment wing 22 and per the wing propeller 32
When vertical direction is that inceptive direction starts flight course, the unmanned plane process experienced variable wing can be but not limited to "
Face-takes off-hovers-and horizontal flight-bows or comes back-lateral turning-hovering-landing-ground ".It is understood that no matter institute
Which kind of state unmanned plane variable wing to start to fly with state, the unmanned plane variable wing can fly during flight in level
It is adjusted between the capable and state of hovering flight, to meet different flight needs.Those skilled in the art should
Understand, different requirements has place with the unmanned plane variable wing that different original states are flown, for example, working as institute
State unmanned plane variable wing carried out using the adjustment wing 22 and the wing propeller 32 using the vertical direction as original state it is winged
When row, the unmanned plane variable wing may be implemented it is vertical take off, certainly, the unmanned plane variable wing also may be implemented vertical
Landing allows in this way, the landing movement of the unmanned plane variable wing can be limited by flying field as few as possible small
The movement of takeoff and landing is completed on place.
It, will be with every adjustment wing 22 of the unmanned plane variable wing and per the wing in the following description of the present invention
Propeller 32 is to carry out detailed retouch as flight course of the inceptive direction to the unmanned plane variable wing in the vertical direction
It states and discloses.
As shown in figure 5, when the unmanned plane needs variable wing are taken off vertically by stopping at ground, that is, the change wing
When formula unmanned plane starts to execute flare maneuver using the vertical direction as inceptive direction, per the adjustment wing 22 and per the wing
Propeller 32 can be adjusted to the vertical direction from the horizontal direction first, at this point, can be vertical per the adjustment wing 22
In every connection wing 21, the power device 40 can respectively drive the fuselage propeller 31 and per the wing propeller
32 rotation per the blade 33.
For example, defining space locating for the unmanned plane variable wing is XYZ axial, wherein defining X axis and Y-axis as institute
It states horizontal direction, defines Z axis to for the vertical direction.When the unmanned plane variable wing needs to generate upward flare maneuver
When, the adjustment wing 22 and every wing propeller 32 are all in the vertical direction, correspondingly, the fuselage propeller 31
It can be rotated using the axis as axis in the horizontal direction with every wing propeller 32 per the blade 33.In the fuselage
During every 33 high-speed rotation of blade of propeller 31 and every wing propeller 32, the preceding slurry per the blade 33
Face and rear pulp noodle can be respectively by the reaction forces from air, in the present invention, and the preceding pulp noodle per the blade 33 are starched with rear
The curvature of pulp noodle after face has different curvature, such as often the curvature of the preceding pulp noodle of the blade 33 is preferably greater than, at this point, often
The air velocity of the preceding pulp noodle of the blade 33 can be greater than the air velocity of the rear pulp noodle of the corresponding blade 33, thus, often
The air pressure that the preceding pulp noodle of the blade 33 are subject to is greater than the air pressure that the rear pulp noodle of the corresponding blade 33 are subject to,
Preceding pulp noodle and rear pulp noodle per the blade 33 will form pressure difference forward and up, and the pressure difference can based on upwards,
To provide lift forward and upwards to the unmanned plane variable wing, hung down with driving the unmanned plane variable wing to realize substantially
Straight take-off process.And in this process, the starching of the fuselage propeller 31 and lower slurry are in the power device 40
It is rotated in a reverse direction under driving, provides upward liter to the unmanned plane variable wing per the wing propeller 32 to cooperate with
Power.
In addition, in this process, will receive the horizontal direction per the adjustment wing 22 in the vertical direction
Air drag, it is to be understood that because of the increase of forced area, be subject to per the adjustment wing 22 in the vertical direction
Air drag can be greater than its air drag being subject in the horizontal direction.
Specifically, after analyzing the stress condition of the unmanned plane variable wing in the whole process, the art
Technical staff should be known that when every adjustment wing 22 is in the vertical direction, the unmanned plane variable wing mainly by
To the fuselage propeller 31 and the lift obliquely provided per the wing propeller 31 while the unmanned plane variable wing
By the horizontal direction air drag and because the unmanned plane variable wing self weight and have gravity.In adjustment institute
State fuselage propeller 31 and when the revolving speed per the wing propeller 32 changes lift obliquely, the unmanned plane variable wing by
To the air drag of the horizontal direction can also change accordingly.In this process, after lift obliquely decomposes,
The power of the horizontal direction and the unmanned plane variable wing be subject to the air drag of the horizontal direction balance each other and
When the power of the vertical direction is greater than the gravity of the unmanned plane variable wing, the unmanned plane variable wing can be transported vertically upward
It is dynamic, thus, the unmanned plane variable wing, which can be realized, to take off vertically.
As shown in fig. 7, in the unmanned plane variable wing in the state of flight, when the unmanned plane variable wing is per described
When the adjustment wing 22 and every wing propeller 32 are adjusted to the horizontal direction from the vertical direction of original state, this
When, it can be consistent with every connection direction of the wing 21 per the adjustment wing 22, equally, the power device 40 still can drive
The fuselage propeller 31 and the rotation per the wing propeller 32.
Specifically, in this process, the every adjustment wing 22 and every wing spiral shell of the unmanned plane variable wing
Rotation paddle 32 is adjusted to the horizontal direction from the vertical direction, at this point, every blade 33 of the wing propeller 32
It can be in the vertical direction high-speed rotation.More specifically, turn at a high speed in every wing propeller 32 per the blade 33
In dynamic process, preceding pulp noodle and rear pulp noodle per the blade 33 all can be by the pressure of the air of corresponding position.It is same because
Often the curvature of the preceding pulp noodle of the blade 33 is greater than the curvature of the rear pulp noodle of the corresponding blade 33, often before the blade 33
The air velocity of pulp noodle is greater than the air velocity of the rear pulp noodle of the corresponding blade 33, thus, the preceding slurry per the blade 33
The air pressure being subject on face can be greater than the air pressure of the rear pulp noodle of the corresponding blade 33, at this point, can be in every paddle
Pressure difference downward backward is formed between the preceding pulp noodle and rear pulp noodle of leaf 33, and based on backward.In this process, described
Unmanned plane variable wing will receive air effect in the reaction force of every blade 33, to provide the unmanned plane variable wing forward
Power.And in this process, the starching of the fuselage propeller 31 and lower slurry are under the driving of the power device 40
It rotates in a reverse direction, provides upward lift to the unmanned plane variable wing per the wing propeller 32 to cooperate with.
It is noted that in this process, every tune per the connection wing 21 and in the horizontal direction
The main lift by the vertical direction of the whole wing 22.
Specifically, after analyzing the stress condition of the unmanned plane variable wing in the whole process, the art
Technical staff should be known that when every adjustment wing 22 is in the horizontal direction, the unmanned plane variable wing mainly by
Upward lift, the unmanned plane variable wing provided to every wing 20 will receive the horizontal direction air drag,
The unmanned plane variable wing will receive the reaction force of forward air and the unmanned plane variable wing will receive it is described vertical
The gravity in direction.The active force for mainly changing the horizontal direction per the wing propeller 32 is being adjusted, the fuselage is adjusted
After propeller 31 changes lift obliquely, the resistance for the horizontal direction that the unmanned plane variable wing is subject to also can be corresponding
Change.And in the dynamic balance of the horizontal direction and the vertical direction that the unmanned plane variable wing is subject to, the change
Wing formula unmanned plane can keep horizontal flight.
Those skilled in the art should be known that be in when per the adjustment wing 22 and per the wing propeller 32
When the horizontal position, the fuselage propeller 31 is capable of providing more power sources, and per the wing propeller 32
The power source of auxiliary can be provided, so that the unmanned plane variable wing can be realized longer time, more flight, and meeting at a distance
Make the unmanned plane variable wing that there is higher pneumatic efficiency.It is noted that in this state, the especially described change wing
Formula unmanned plane can be prior to every 20 stall of wing, at this point, the fuselage 10 in the flight of High Angle of Attack, per the aileron 210
Front can automatic nutation, for traditional Fixed Wing AirVehicle, the unmanned plane variable wing have it is higher
Anti- stall ability.
Correspondingly, the unmanned plane variable wing state of flight in the process adjusted from horizontal flight to hovering flight
In, it can be adjusted to the vertical direction from the horizontal direction per the adjustment wing 22 and per the wing propeller 32, this
When, the adjustment wing 22 can be perpendicular to the connection wing 21.The meeting per the blade 33 of the wing propeller 32 is in the water
Square to rotation, and during every 33 high-speed rotation of blade, preceding pulp noodle and rear pulp noodle per the blade 33 are all
It will receive the pressure of air.And since the curvature of the preceding pulp noodle of every blade 33 is greater than the curvature of rear pulp noodle, every institute
The air pressure that the preceding pulp noodle of blade 33 are subject to or the air pressure greater than the rear pulp noodle of the blade 33 accordingly are stated, thus,
Pressure difference forward and up is formed between the preceding pulp noodle and rear pulp noodle of the blade 33, and based on upwards, described in providing
The lift of unmanned plane variable wing forwardly and upwardly.
In addition, in this process, will receive the horizontal direction per the adjustment wing 22 in the vertical direction
Air drag, it is to be understood that can be greater than per the air drag that the adjustment wing 22 is subject in the vertical direction its
The air drag that the horizontal direction is subject to.
Specifically, after analyzing the stress condition of the unmanned plane variable wing in the whole process, the art
Technical staff should be known that when every adjustment wing 22 is in the vertical direction, the unmanned plane variable wing mainly by
It can be by the fuselage propeller 31 and the lift obliquely provided per the wing propeller 31, the unmanned plane variable wing
To the horizontal direction air drag and because the unmanned plane variable wing self weight and have gravity.Described in adjustment
The revolving speed of fuselage propeller 31 and every wing propeller 32 changes lift obliquely, what the unmanned plane variable wing was subject to
The air drag of the horizontal direction can also change accordingly.After lift obliquely decomposes, in the power of the horizontal direction
It balances each other in the air drag of the horizontal direction and with what the unmanned plane variable wing was subject in the power of the vertical direction
When balancing each other with the gravity of the unmanned plane variable wing, the unmanned plane variable wing will not be moved to any direction, thus, make institute
The state of flight that unmanned plane variable wing realizes hovering flight is stated, as shown in Figure 6.
It is noted that the process adjusted in every adjustment wing 22 from the horizontal direction to the vertical direction
In, per the air drag that is subject to of the adjustment wing 22 can due to forced area increase and increase, at this point, it is described it is variable wing nobody
The flying speed of machine will receive very big influence, so that keeping the unmanned plane variable wing quick from the state of flight of high speed
Ground is adjusted to the state of flight of low speed, and finally realizes hovering flight, thus, there is the unmanned plane variable wing stable
Flight characteristic.For Multi-axis aircraft compared with the existing technology, the unmanned plane variable wing has significant progress.
As shown in fig. 9 a and fig. 9b, when the state of flight of the unmanned plane variable wing from hovering flight be adjusted to new line or
When the state of flight bowed, at this point, the front of the fuselage 10 of the unmanned plane variable wing can make upward or downward dynamic
Make, when the unmanned plane variable wing is in hovering flight state, by adjusting the fuselage propeller 31 and per the wing
The revolving speed of propeller 32, so that the fuselage propeller 31 and every wing propeller 32 have different revolving speeds, thus
There is opposite differential between the fuselage propeller 31 and every wing propeller 32, make the unmanned plane variable wing in institute
The force unbalance of vertical direction is stated, so that resultant direction is upward or downward, thus, realize the unmanned plane variable wing low
Head and nose-up pitching moment, at this point, the unmanned plane variable wing can be realized flight up and down.
For example, making the fuselage by the power device 40 when the fuselage 10 needs to generate upward torque
Propeller 31 and every wing propeller 32 have different revolving speeds, its is made unbalanced rotor differential occur, e.g., increase institute
The revolving speed for stating fuselage propeller 31 keeps the revolving speed of the wing propeller 32 constant, can produce nose-up pitching moment；Or it keeps
The revolving speed of fuselage propeller 31 is constant, reduces the revolving speed of the wing propeller 32, equally generation nose-up pitching moment；Or it adjusts simultaneously
The revolving speed of whole the fuselage propeller 31 and the wing propeller 32, so that being located at the fuselage spiral shell of 10 front of fuselage
The relative velocity for revolving paddle 31 is greater than the relative velocity of every wing propeller 32 positioned at 10 rear portion of fuselage, so that
The fuselage 10 generates upward nose-up pitching moment.
Correspondingly, when the fuselage 10 needs to generate downward torque, the machine is adjusted by the power device 40
The revolving speed of body propeller 31 and the wing propeller 32 makes it unbalanced rotor differential occur and e.g. reduces the fuselage spiral shell
The revolving speed of paddle 31 is revolved, keeps the revolving speed per the wing propeller 32 constant, generates nose-down pitching moment；Or keep the fuselage spiral shell
The revolving speed for revolving paddle 31 is constant, increases the revolving speed per the wing propeller 32, equally generation nose-down pitching moment；Or institute is adjusted simultaneously
Fuselage propeller 31 and the revolving speed per the wing propeller 32 are stated, so that being located at the fuselage spiral of 10 front of fuselage
The relative velocity of paddle 31 is less than the relative velocity of the wing propeller 32 positioned at 10 rear portion of fuselage, so that described
Fuselage 10 generates downward nose-up pitching moment.
The unmanned plane variable wing state of flight by bowing or when new line state is adjusted to turning flight state, institute
The movement that fuselage propeller 31 cooperates with every wing propeller 32 is stated, to realize the turning flight of the unmanned plane variable wing.
Specifically, the fuselage propeller 31 and the relative velocity per the wing propeller 32 are adjusted, so that poor in lateral appearance
Speed, so that the front of the fuselage 10 be made to turn to side.For example, keep the velocity of rotation of the fuselage propeller 31 constant,
Change the speed of any one wing propeller 32 in per the wing propeller 32, the fuselage 10 will appear
Side torque is turned to realize to side.Those skilled in the art are appreciated that at the unmanned plane variable wing
When the state of flight bowed or come back, differential comes across the fuselage propeller 31 and per the wing propeller 32, at this point,
Revolving speed per the wing propeller 32 is consistent；When the unmanned plane variable wing is in lateral turn condition, differential is come across
Between the fuselage propeller 31 and every wing propeller 32, at this point, the revolving speed between per the wing propeller 32
It is inconsistent.
As shown in Figure 10, vertical decline is adjusted to from side to turn condition in the state of flight of the unmanned plane variable wing
When state, by adjusting the fuselage propeller 31 and per the relative velocity of the wing propeller 32, and adjust per the tune
The direction of the whole wing 22 makes to be adjusted to described hang down from the horizontal direction with per the wing propeller 32 per the adjustment wing 22
Histogram to, correspondingly, adjust the fuselage propeller 31 and change lift obliquely per the wing propeller 32, it is described
The air drag of horizontal direction can also change accordingly.After the lift obliquely decomposes the power of the horizontal direction with
The unmanned plane variable wing balances each other in the air drag that the horizontal direction is subject to and is less than in the power of the vertical direction
When the gravity, the unmanned plane variable wing can vertically do descending motion, thus, realize hanging down for the unmanned plane variable wing
It lands vertically and falls.
The unmanned plane variable wing can also include a toter 50, and the toter 50 can selectively be set
It is placed in inside or below the fuselage 10, wherein the toter 50 can be used to mounted in the article etc. transported, in institute
When stating state of the unmanned plane variable wing in flight, the toter 50 and the object being installed in inside the toter 50
The position that product act on the fuselage 10 is located at the center of gravity of the fuselage 10 or the lower section of center of gravity, in this way it can be ensured that described
The flight safety of unmanned plane variable wing.For example, the nothing variable wing in this example of such as Figure 11, more than two framves or two framves
It is man-machine to cooperate with to deliver article, specifically, unmanned plane variable wing described in multi rack is transported by the toter 50
When loading product, article can be in the center of gravity position of the fuselage 10 by the position that the toter 50 acts on the fuselage 10
The underface set, that is to say, that article acts on the position and the fuselage of the fuselage 10 by the toter 50
In the same vertical direction, (the i.e. described article passes through the position that the toter 50 acts on the fuselage 10 to 10 center of gravity
It is coaxial with the center of gravity of the fuselage 10), thus, it is ensured that the unmanned plane variable wing is during transporting article, with good
Good having a smooth flight property, to further ensure that the flight safety of the unmanned plane variable wing.
The unmanned plane variable wing can also include a lifting gear 60, wherein the lifting gear 60 is set to the machine
The lower part of body 10, to be used to assist the unmanned plane landing variable wing, as shown in figure 3, the lifting gear 60 is specific at one
Example in may be implemented as a landing frame, nevertheless, it should be understood by those skilled in the art that in the present invention
Other embodiments in, the lifting gear 60 also may be implemented as lifting wheel or similar in other examples
Device, therefore, the type of the lifting gear 60 can not be considered as the limitation to the contents of the present invention and range.
As shown in figure 12, the unmanned plane variable wing can also be controlled by a control device 70, specifically, by described dynamic
Power device 40 is communicably connected in the control device 70, and operator can use the control device 70 and pass through control institute
The energy output of power device 40 is stated to control revolving speed and state per the propeller 30, thus, make per the propeller 30
Between can realize switching of the unmanned plane variable wing under different state of flights by generating differential.For example, at this
In invention, operator can use the control device 70 to increase the spiral for being implemented as the fuselage propeller 31
The revolving speed of paddle 30, so that the unmanned plane variable wing has the flare maneuver to come back.Nevertheless, the technology people of the art
Member is it should be appreciated that the control device 70 can also be to the automation control of the unmanned plane variable wing, that is to say, that Ke Yi
Setting program in the control device 70 is operated with substituting operator to the state of flight of the unmanned plane variable wing.
Correspondingly, the present invention also provides a kind of flying methods of unmanned plane variable wing, wherein consolidating compared with the existing technology
Determine for rotor aircraft and Multi-axis aircraft, the flying method of the unmanned plane variable wing has significant progress.Specifically
Ground says, the method includes make to be respectively arranged at per the wing 20 per the propeller 30 in the horizontal direction and described
It is adjusted between vertical direction, to change the state of flight of the unmanned plane variable wing.
Preferably, the method also includes steps.
(a) the connection wing 21 for being symmetrically disposed on the fuselage 10 is provided.
(b) the adjustment wing 22 being rotatablely arranged at per the connection wing 21 is provided, it is per the connection wing 21 and every
The adjustment wing 22 is respectively formed per the wing 20, and is selectively arranged at per the propeller 30 per the connection wing
21 or per the adjustment wing 22.It is noted that being implemented as institute in this embodiment as shown in Figure 3 of the invention
That states wing propeller 32 is arranged at the adjustment wing 22 per the propeller 33, so that often the wing propeller 32 can be with
It is synchronous with every adjustment movement of the wing 22.Nevertheless, it should be understood by those skilled in the art that even described
Wing propeller 32 is set in this embodiment of the connection wing 21, by adjusting separately the wing propeller 32 and institute
The position for stating the adjustment wing 22, also can achieve same purpose.
(c) make to adjust between the horizontal direction and the vertical direction per the adjustment wing 22.Side in this way
Formula, in subsequent flight course, state of flight can neatly be changed the unmanned plane variable wing.
It is noted that in the above-mentioned methods, generating rotational speed difference between per the propeller 30 by making, institute can be made
It states unmanned plane variable wing to be adjusted between different state of flights, for example, the unmanned plane variable wing may be implemented such as
The flight courses such as come back, bow, turning, it is thus possible to increase the flexibility of the unmanned plane variable wing.
It should be understood by those skilled in the art that foregoing description and the embodiment of the present invention shown in the drawings are only used as illustrating
And it is not intended to limit the present invention.The purpose of the present invention has been fully and effectively achieved.Function and structural principle of the invention exists
It shows and illustrates in embodiment, under without departing from the principle, embodiments of the present invention can have any deformation or modification.
Claims (10)
1. a kind of unmanned plane variable wing characterized by comprising
One fuselage；
Two ailerons；
Two wings；
One empennage；With
At least three propellers, the setting of two ailerons are symmetrically disposed on the front of the fuselage, and two wings are symmetrically
It is set to the fuselage afterbody, the empennage is set on the upside of the afterbody, wherein a propeller is fuselage spiral
Paddle, is arranged at the fore-body, the two aileron corresponding positions, and propeller described in two of them is wing propeller, point
Be not arranged at the wing, each wing propeller is rotatablely arranged at each wing respectively, it is described nobody
Machine includes a power device, and the power device is set to the fuselage, and each propeller be respectively coupled to it is described
Power device.
2. unmanned plane variable wing according to claim 1, wherein the wing propeller is in the level where fuselage length
It is adjusted between vertical direction where direction and height.
3. unmanned plane variable wing according to claim 1, wherein the wing propeller is selectively set to per the machine
The end or middle part of the wing.
4. unmanned plane variable wing according to claim 1 is adjusted wherein each wing respectively includes a connection wing and one
The whole wing is set to the fuselage per the connection wing, is rotatablely arranged at per the wing and does not have the connection wing.
5. unmanned plane variable wing according to claim 4, wherein being selectively set to per the wing propeller described
Connect the wing or the adjustment wing.
6. unmanned plane variable wing according to claim 4, wherein the fortune per the wing propeller and per the adjustment wing
It is dynamic to synchronize.
7. unmanned plane variable wing according to claim 4, the propeller being provided in every wing is done
Relative to the axial movement of the fuselage, wherein the propeller is rotatablely arranged at the adjustment relative to the adjustment wing
The wing.
8. unmanned plane variable wing according to claim 1, wherein the unmanned plane variable wing further includes a toter, institute
It states toter and is set to the fuselage, and the toter acts in the position and the fuselage of the fuselage
The heart is in same vertical direction.
9. unmanned plane variable wing according to claim 1, wherein the unmanned plane variable wing includes a control device, it is described
Control device is communicatively coupled with the power device, and the control device is exported by controlling the energy of the power device
To control revolving speed and state per the propeller.
10. unmanned plane variable wing according to claim 1, wherein the propeller is a contrarotating propeller.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811634598.4A CN109808877A (en) | 2014-12-26 | 2014-12-26 | A kind of unmanned plane variable wing and its method |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811634598.4A CN109808877A (en) | 2014-12-26 | 2014-12-26 | A kind of unmanned plane variable wing and its method |
| CN201410828784.7A CN105775121A (en) | 2014-12-26 | 2014-12-26 | Wing-variable type unmanned aerial vehicle and method thereof |
Related Parent Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410828784.7A Division CN105775121A (en) | 2014-12-26 | 2014-12-26 | Wing-variable type unmanned aerial vehicle and method thereof |
Publications (1)
| Publication Number | Publication Date |
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| CN109808877A true CN109808877A (en) | 2019-05-28 |
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| CN201811634598.4A Pending CN109808877A (en) | 2014-12-26 | 2014-12-26 | A kind of unmanned plane variable wing and its method |
| CN201410828784.7A Pending CN105775121A (en) | 2014-12-26 | 2014-12-26 | Wing-variable type unmanned aerial vehicle and method thereof |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201410828784.7A Pending CN105775121A (en) | 2014-12-26 | 2014-12-26 | Wing-variable type unmanned aerial vehicle and method thereof |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106428550A (en) * | 2016-11-04 | 2017-02-22 | 山东萌萌哒航空科技有限公司 | Tilting type unmanned plane and flight control method thereof |
| US20190009899A1 (en) * | 2017-07-06 | 2019-01-10 | Autoflightx International Limited | Hybrid vtol fixed-wing drone having wing-tip propellers |
| FR3080605B1 (en) * | 2018-04-26 | 2020-05-29 | Airbus Helicopters | GIRAVION PROVIDED WITH A TURNING WING AND AT LEAST TWO PROPELLERS AND METHOD APPLIED BY THIS GIRAVION |
| CA3147197A1 (en) * | 2019-08-14 | 2021-02-18 | Gad Shaanan | Aerial vehicle |
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|---|---|---|---|---|
| US5096140A (en) * | 1989-09-08 | 1992-03-17 | Dornier Claudius Jr | Aircraft with engine pods tiltable about a transverse axis |
| CA2659499A1 (en) * | 2008-03-25 | 2009-09-25 | Eurocopter | Long-range, high-speed, hybrid helicopter |
| US20110114798A1 (en) * | 2009-11-17 | 2011-05-19 | Eurocopter | Long-range aircraft with high forward speed in cruising flight |
| CN103832585A (en) * | 2012-11-22 | 2014-06-04 | 上海市浦东新区知识产权保护协会 | Cruise aircraft |
| RU2527248C1 (en) * | 2013-04-17 | 2014-08-27 | Дмитрий Сергеевич Дуров | Drone with hybrid power plant (versions) |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3666209A (en) * | 1970-02-24 | 1972-05-30 | Boeing Co | V/stol aircraft with variable tilt wing |
| RU2012512C1 (en) * | 1993-09-07 | 1994-05-15 | Фирма "ВИСТ" | Hybrid flying vehicle |
| FR2798359B1 (en) * | 1999-09-14 | 2001-11-09 | Eurocopter France | IMPROVEMENTS ON TILTING ROTOR CONVERTIBLE AIRCRAFT |
| KR100822366B1 (en) * | 2007-05-15 | 2008-04-16 | 한국항공우주연구원 | Tiltrotor aircraft |
| FR2999150B1 (en) * | 2012-12-10 | 2015-10-09 | Bermond Gerome Maurice Paul | CONVERTIBLE AIRCRAFT COMPRISING TWO CAREN ROTORS AT THE END OF A WING AND A HORIZONTAL FAN IN FUSELAGE |
| CN104401480A (en) * | 2014-11-06 | 2015-03-11 | 南京航空航天大学 | Ducted tilt aircraft |
| CN204473135U (en) * | 2014-12-26 | 2015-07-15 | 金良 | A kind of change wing formula unmanned plane |
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- 2014-12-26 CN CN201811634598.4A patent/CN109808877A/en active Pending
- 2014-12-26 CN CN201410828784.7A patent/CN105775121A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5096140A (en) * | 1989-09-08 | 1992-03-17 | Dornier Claudius Jr | Aircraft with engine pods tiltable about a transverse axis |
| CA2659499A1 (en) * | 2008-03-25 | 2009-09-25 | Eurocopter | Long-range, high-speed, hybrid helicopter |
| US20110114798A1 (en) * | 2009-11-17 | 2011-05-19 | Eurocopter | Long-range aircraft with high forward speed in cruising flight |
| CN103832585A (en) * | 2012-11-22 | 2014-06-04 | 上海市浦东新区知识产权保护协会 | Cruise aircraft |
| RU2527248C1 (en) * | 2013-04-17 | 2014-08-27 | Дмитрий Сергеевич Дуров | Drone with hybrid power plant (versions) |
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| Publication number | Publication date |
|---|---|
| CN105775121A (en) | 2016-07-20 |
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Application publication date: 20190528 |
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