CN108045576A - Deformable bionical rotor flapping wing fixed-wing one aircraft - Google Patents
Deformable bionical rotor flapping wing fixed-wing one aircraft Download PDFInfo
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- CN108045576A CN108045576A CN201810035791.XA CN201810035791A CN108045576A CN 108045576 A CN108045576 A CN 108045576A CN 201810035791 A CN201810035791 A CN 201810035791A CN 108045576 A CN108045576 A CN 108045576A
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- 238000010586 diagram Methods 0.000 description 4
- 238000005183 dynamical system Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000005265 energy consumption Methods 0.000 description 3
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C37/00—Convertible aircraft
- B64C37/02—Flying units formed by separate aircraft
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Abstract
The present invention provides a kind of deformable bionical rotor flapping wing fixed-wing one aircraft, are related to vehicle technology field, solve the technical issues of existing Flight Vehicle Structure is complicated, security is low.The deformable bionical rotor flapping wing fixed-wing one aircraft includes fuselage, rotor, fixed-wing and deformation driving device, and deformation driving device is located at below rotor and/or side, and there are gaps between deformation driving device and rotor；Deformation driving device is arranged on fixed-wing and/or is arranged between fixed-wing and fuselage, and fixed-wing can be driven to deform and resetted to form flapping wing；Or deformation driving device is arranged on fuselage and fuselage can be driven to deform and resetted；The working condition of aircraft includes the winged state of jacking condition peace, and fixed-wing and/or fuselage can switch aircraft working condition by way of deforming or resetting and can control aircraft level speed.The present invention is used to simplify gyroplane airframe structure and increases its security.
Description
Technical field
The present invention relates to vehicle technology fields, integrally fly more particularly, to a kind of deformable bionical rotor flapping wing fixed-wing
Row device.
Background technology
Gyroplane be it is a kind of using it is preceding winged when relative wind blow autorotation to generate the rotary wing aircraft of lift.It
Thrust directly provided by driven by engine propeller, gyroplane is a kind of aircraft between helicopter and aircraft,
Equipped with rotor and fixed aerofoil.Gyroplane have landing apart from it is short, low speed low-latitude flying can be made, it is simple light and handy, convenient for hidden etc.
Feature, available for take photo in the sky, arm discharge, battlefield scout etc..
Whether gyroplane with power set is divided into active gyroplane and driven gyroplane according to itself；Also between going straight up to
Tilting wing machine between machine and fixed-wing can be flown with VTOL fixed-wing, but no matter tilting rotor or tilting wing,
Fixed-wing will not fold.This gyroplane fuselage size is big, more demanding when flying to switch with having hung down putting down；In addition it is also compound
Wing aircraft, the rotor of existing vertical lift, and have fixed-wing.But it is neither foldable, fuselage size is big, and dynamical system is again multiple
It is miscellaneous.
Applicants have discovered that at least there are following technical problems for the prior art：The fixed-wing of common gyroplane cannot deform or
Also rotor verting and twist to realize that lifting peace is winged, it is necessary to be installed additional on propeller set in itself can only be utilized after person's deformation
It verts or wrench device, the structure of such aircraft is more complicated, and complete machine security is relatively low, and installation and maintenance are inconvenient.
The content of the invention
It is existing to solve it is an object of the invention to provide a kind of deformable bionical rotor flapping wing fixed-wing one aircraft
The technical issues of Flight Vehicle Structure present in technology is complicated, security is low.It is excellent in many technical solutions provided by the invention
Many technique effects elaboration as detailed below that selecting technology scheme can be generated.
To achieve the above object, the present invention provides following technical schemes：
Deformable bionical rotor flapping wing fixed-wing one aircraft provided by the invention, including fuselage, rotor, fixed-wing with
And deformation driving device, wherein：
The deformation driving device is located at the lower section and/or side of the rotor, and it is described deform driving device with it is described
There are gaps between rotor；
The deformation driving device be arranged on the fixed-wing and/or be arranged on the fixed-wing and the fuselage it
Between, and the fixed-wing can be driven to deform and reset to form flapping wing；Alternatively, the deformation driving device be arranged on it is described
On fuselage and the fuselage can be driven to deform and resetted；
The working condition of the aircraft includes the winged state of jacking condition peace, the fixed-wing and/or the fuselage energy
Switch the working condition of the aircraft by way of deforming or resetting and the aircraft can be controlled to equal winged speed.
Further, the fixed-wing includes the first fixed-wing and the second fixed-wing, first fixed-wing and described second
Fixed-wing each includes the motionless wing and movable wing, and the motionless wing is fixedly connected with fuselage, the movable wing and it is described not
Dynamic wing flexible connection；
It is respectively provided between first fixed-wing and the respective movable wing of second fixed-wing and the motionless wing
There is a deformation driving device, the deformation driving device is by changing the side of angle between the movable wing and the motionless wing
Formula forms flapping wing the fixed-wing to be driven to deform and is resetted.
Further, first fixed-wing and second fixed-wing are located at the both sides of the fuselage respectively.
Further, the fixed-wing is equipped at least one downward lifting support protrusion；
The fixed-wing can be deformed into unfolded state and be reset to folded state, and the deformable bionical rotor flapping wing is fixed
The bottom and ground of wing one aircraft lifting support protrusion when the fixed-wing drop to ground in a folded configuration
It contacts and by the deformable bionical rotor flapping wing fixed-wing one aircraft support on ground.
Further, the bottom surface of the lifting support protrusion is plane or straight rib.
Further, the fixed-wing includes the first fixed-wing and the second fixed-wing, and the first fixed-wing and the second fixed-wing are equal
Be flexibly connected with the fuselage, the deformation driving device by change between first fixed-wing and the fuselage angle with
And the mode of angle is formed the fixed-wing to be driven to deform and is resetted between second fixed-wing and the fuselage
Flapping wing.
Further, first fixed-wing and second fixed-wing are the ring-type that is folded up of outside, and described first
Fixed-wing and second fixed-wing are located at fuselage both sides and are hinged respectively with the fuselage.
Further, there are landing pit sections for the fixed-wing；The landing pit section is located on fixed-wing close to the position of fuselage,
And plane or straight rib is in the section bottom that lands.
Further, the deformable bionical rotor flapping wing fixed-wing one aircraft further includes power set, the power
Device is electrically connected respectively with the motor of the rotor and the deformation driving device, and the power set can be that the deformation is driven
The motor of dynamic device and the rotor.
Further, the rotor is coaxial double-rotary wing.
Beneficial effects of the present invention are：The wing of the deformable bionical rotor flapping wing fixed-wing one aircraft of the present invention
Or the fuselage can be deformed and resetted, and realized in the wing or the fuselage in its deformation or during resetting
The change of aircraft entirety position of centre of gravity so as to adjust the lifting of aircraft and flat winged state and equals winged speed, thus
It need not install additional and vert or wrench device on the propeller set of rotor, simplify airframe structure and its installation and maintenance process,
Add its security；The wing or the fuselage are in the flight course for deforming with flapping-wing aircraft being simulated in reseting procedure, profit
The interest of shown aircraft is added with bionical.
Description of the drawings
It in order to illustrate more clearly about the embodiment of the present invention or technical scheme of the prior art, below will be to embodiment or existing
There is attached drawing needed in technology description to be briefly described, it should be apparent that, the accompanying drawings in the following description is only this
Some embodiments of invention, for those of ordinary skill in the art, without creative efforts, can be with
Other attached drawings are obtained according to these attached drawings.
Fig. 1 is that deformable bionical 1 fixed-wing of rotor flapping wing fixed-wing one aircraft embodiment of the present invention is in rugosity
State schematic diagram；
Fig. 2 is that deformable bionical 1 fixed-wing of rotor flapping wing fixed-wing one aircraft embodiment of the present invention is in expansion shape
State schematic diagram；
Fig. 3 is that deformable bionical 2 fixed-wing of rotor flapping wing fixed-wing one aircraft embodiment of the present invention is in reset shape
State schematic diagram；
Fig. 4 is that deformable bionical 2 fixed-wing of rotor flapping wing fixed-wing one aircraft embodiment of the present invention is in change shape
State schematic diagram.
In figure：1st, fuselage；2nd, rotor；31st, the first fixed-wing；32nd, the second fixed-wing；33rd, the motionless wing；34th, movable wing；4、
Deform driving device；5th, lifting support protrusion；6th, land section.
Specific embodiment
To make the object, technical solutions and advantages of the present invention clearer, technical scheme will be carried out below
Detailed description.Obviously, described embodiment is only part of the embodiment of the present invention, instead of all the embodiments.Base
Embodiment in the present invention, those of ordinary skill in the art are obtained all on the premise of creative work is not made
Other embodiment belongs to the scope that the present invention is protected.
Deformable bionical rotor flapping wing fixed-wing one aircraft provided by the invention, including fuselage 1, rotor 2, fixed-wing
And deformation driving device 4, wherein：
Deformation driving device 4 is located at the lower section and/or side of rotor 2, and deforms and exist between driving device 4 and rotor 2
Gap；
Flapping-wing aircraft refers to the aircraft for overweighting air that wing can up and down flutter as bird and insect wing, also known as flutter
Machine, deformation driving device 4 is arranged on fixed-wing and/or is arranged between fixed-wing and fuselage 1, and can drive fixed-wing
It deforms and resets to form flapping wing；Alternatively, deformation driving device 4 sets on the fuselage 1 and fuselage 1 can be driven to deform and answer
Position；
The working condition of aircraft includes the winged state of jacking condition peace, and fixed-wing and/or fuselage 1 can be by deforming or answering
The mode of position switches the working condition of aircraft and aircraft can be controlled to equal winged speed.
The wing or the fuselage 1 of the deformable bionical rotor flapping wing fixed-wing one aircraft of the present invention can deform
And reset, and aircraft entirety center of gravity position is realized in its deformation or during resetting in the wing or the fuselage 1
The change put so as to adjust the lifting of aircraft and flat winged state and equals winged speed；
General gyroplane is verted by the installation of the propeller of rotor 2 or wrench device realizes flat chikung energy, energy consumption
Higher, level speed is slower；
And compared with fuselage 1 any displacement does not occur for the propeller of the present invention, without the propeller set in rotor 2
Upper installation is verted or wrench device, simplifies 1 structure of fuselage and its installation and maintenance process, adds its security, and reduce
Energy consumption improves level speed；
The wing or the fuselage 1 simulate the flight course of flapping-wing aircraft in deformation and reseting procedure, and utilization is bionical
The interest of shown aircraft and adaptability are added, the shape of aircraft and color matching be also designed to various animals or people
Object, bio-imitability is stronger, recreational higher；
Deformation driving device 4 in the present invention uses steering engine to provide power for wing or the deformation of fuselage 1.
Optionally embodiment, deformable bionical rotor flapping wing fixed-wing one aircraft further include power set,
Power set respectively with the motor of rotor 2 and deformation driving device 4 be electrically connected, power set can be deformation driving device 4 with
And the motor of rotor 2.
Since the switching of the flat winged state and jacking condition of aircraft is the side that deforms or reset by fixed-wing or fuselage 1
Formula is completed, and the flat power that flies relies only on the rotation of rotor 2 to provide with lift, so dynamical system need to be only the rotation of rotor 2
Turn to provide power, dynamical system relative simplicity improves the reliability of complete machine, while reduces 1 weight of fuselage, has safety height
The characteristics of effect is practical.
Optionally embodiment, rotor 2 are coaxial double-rotary wing.
The rotor 2 of the present invention is coaxial double-rotary wing, and coaxial double-rotary wing has around the rotation of same theory axis a positive and a negative
Upper and lower two secondary rotors due to steering on the contrary, the torque that two secondary rotors generate mutually balances under steady state of flight, lead to
Cross so-called rotor up and down always can realize directional control away from the differential imbalance torque that generates, and be provided with the aircraft of coaxial double-rotary wing
Tail-rotor need not be set, it is possible to reduce power consumption and energy consumption.The mode of more rotors can certainly be selected to be provided for aircraft dynamic
Power.
Embodiment 1：
Such as Fig. 1 and Fig. 2, deformable bionical rotor flapping wing fixed-wing one aircraft provided by the invention, fixed-wing includes
First fixed-wing 31 and the second fixed-wing 32, the first fixed-wing 31 and the second fixed-wing 32 each include the motionless wing 33 and live
The dynamic wing 34, the motionless wing 33 are fixedly connected with fuselage 1, and movable wing 34 is flexibly connected with the motionless wing 33；
Deformation is both provided between first fixed-wing 31 and 32 respective movable wing 34 of the second fixed-wing and the motionless wing 33 to drive
Dynamic device 4, deformation driving device 4 drive fixed-wing changing between movable wing 34 and the motionless wing 33 by way of angle
It deforms and resets to form flapping wing.Certainly, can also be set simultaneously between the motionless wing 33 and fuselage 1 deformation driving device 4 or
The motionless wing 33 is made folding resilient wing by person, and such first fixed-wing 31 can fold completely with the second fixed-wing 32,
Convenient for collecting and carrying；First fixed-wing 31 and 32 respective movable wing 34 of the second fixed-wing can also more than just one, activity
34 outside of the wing can set one and above additional movable wing 34, for more accurate complicated regulation and control flight parameter.
In the present embodiment, the rotation axis of rotor 2 be mounted on aircraft it is not deformed when whole center of gravity, when servos control the
When the deformation of 34 part of movable wing of one fixed-wing 31 and the second fixed-wing 32 is opened, the centre-of gravity shift of aircraft to 1 head of fuselage,
Aircraft is caused to deflect, after the gravity of aircraft and the lift of rotor 2 reach balance again, aircraft is switched to flat winged shape
State；
When aircraft is not deformed, the angle between the motionless wing 33 and movable wing 34 is minimum, when motionless 33 He of the wing of servos control
After angle between movable wing 34 gradually increases, the centre-of gravity shift degree of aircraft is higher, aircraft gravity itself and rotor 2
The lift of generation is made a concerted effort bigger so as to generate horizontal direction, and it is faster that aircraft equals winged speed, therefore, can pass through control
The mode of angle equals winged speed to control between movable wing 34 and the motionless wing 33 processed；It, can also be real when unilateral wing folding
The side chikung energy of existing aircraft, this control mode switching is simple, easy to operate；
The wing and fuselage 1 of the present embodiment can simulate the image of " dragon ", and because fixed-wing can be continuous in flight
Ground deformation resets, and and so on, folding is freely, bionical interesting high just as birds wing.
Optionally embodiment, the first fixed-wing 31 and the second fixed-wing 32 are located at the both sides of fuselage 1 respectively.First
31 and second fixed-wing 32 of fixed-wing is located at 1 both sides of fuselage and symmetrical, can so balance fuselage 1, it is handling to increase its.
Optionally embodiment, fixed-wing are equipped at least one downward lifting support protrusion 5；
Fixed-wing can be deformed into unfolded state and be reset to folded state, and deformable bionical rotor flapping wing fixed-wing integrally flies
Row device bottom of lifting support protrusion 5 when fixed-wing drop to ground in a folded configuration contacts with ground and will be deformable imitative
Raw rotor flapping wing fixed-wing one aircraft support is on ground.
Fixed-wing both can also can upon deployment increase complete machine as flat winged state and the switching part of jacking condition
Lift, and can be as undercarriage when lifting, advantage is to simplify fuselage 1 to design, and need not additionally add undercarriage,
Increase landing stability simultaneously.
Optionally embodiment, the bottom surface of lifting support protrusion 5 is plane or straight rib.The bottom of plane or straight rib
Face can be such that lifting support protrusion 5 is more firmly parked on landing face, further increase aircraft lands stability.
Embodiment 2：
Such as Fig. 3 and Fig. 4, the present embodiment 2 and the difference of embodiment 1 are：
Fixed-wing includes the first fixed-wing 31 and the second fixed-wing 32, and the first fixed-wing 31 and the second fixed-wing 32 are and machine
Body 1 is flexibly connected, and deformation driving device 4 is by changing angle and the second fixed-wing 32 between the first fixed-wing 31 and fuselage 1
The mode of angle forms flapping wing fixed-wing to be driven to deform and is resetted between fuselage 1.
In the present embodiment, the rotation axis of rotor 2 be mounted on aircraft it is not deformed when whole center of gravity, when servos control the
When one fixed-wing 31 and the second fixed-wing 32 deform, the centre-of gravity shift of aircraft to 1 head of fuselage causes aircraft to deflect,
After the gravity of aircraft and the lift of rotor 2 reach balance again, aircraft is switched to flat winged state；
When aircraft is not deformed, the angle between the head of the first fixed-wing 31, the front end of the second fixed-wing 32 and fuselage 1
Maximum, when the angle between the head of servos control the first fixed-wing 31, the front end of the second fixed-wing 32 and fuselage 1 is gradually reduced
Afterwards, the centre-of gravity shift degree of aircraft is higher --- and i.e. closer to 1 head of fuselage, aircraft gravity itself is generated with rotor 2
Lift make a concerted effort bigger so as to generate horizontal direction, it is faster that aircraft equals winged speed, therefore, can pass through control the
The mode of angle equals winged speed to control between the head of one fixed-wing 31, the front end of the second fixed-wing 32 and fuselage 1；It is this
Control mode switching is simple, easy to operate；
Optionally embodiment, the first fixed-wing 31 and the second fixed-wing 32 are the ring-type that outside is folded up,
First fixed-wing 31 and the second fixed-wing 32 are located at 1 both sides of fuselage and are hinged respectively with fuselage 1.
The wing and fuselage 1 of the present embodiment can simulate the image of " butterfly ", the first fixed-wing 31 and the second fixed-wing 32
Also the function of protection rotor 2 is had concurrently.
Optionally embodiment, there are landing pit sections 6 for fixed-wing；The section 6 that lands is located on fixed-wing close to fuselage 1
Position, and plane or straight rib is in 6 bottom of section that lands.
The section 6 that lands can increase the landing stability of aircraft, need not be that aircraft installs additional undercarriage, plane
Or the bottom surface of straight rib can be such that lifting support protrusion 5 is more firmly parked on landing face, further increase aircraft
Landing stability.
The above description is merely a specific embodiment, but protection scope of the present invention is not limited thereto, any
Those familiar with the art in the technical scope disclosed by the present invention, can readily occur in change or replacement, should all contain
Lid is within protection scope of the present invention.Therefore, protection scope of the present invention should be based on the protection scope of the described claims.
Claims (10)
1. a kind of deformable bionical rotor flapping wing fixed-wing one aircraft, which is characterized in that including fuselage, rotor, fixed-wing
And deformation driving device, wherein：
The deformation driving device is located at the lower section and/or side of the rotor, and the deformation driving device and the rotor
Between there are gaps；
The deformation driving device is arranged on the fixed-wing and/or is arranged between the fixed-wing and the fuselage, and
The fixed-wing can be driven to deform and reset to form flapping wing；Alternatively, the deformation driving device is arranged on the fuselage
Above and the fuselage can be driven to deform and resetted；
The working condition of the aircraft includes the winged state of jacking condition peace, and the fixed-wing and/or the fuselage can pass through
Deformation or the mode resetted switch the working condition of the aircraft and the aircraft can be controlled to equal winged speed.
2. deformable bionical rotor flapping wing fixed-wing one aircraft according to claim 1, which is characterized in that described solid
Determining the wing includes the first fixed-wing and the second fixed-wing, and first fixed-wing and second fixed-wing each include the motionless wing
And movable wing, the motionless wing are fixedly connected with fuselage, the movable wing is flexibly connected with the motionless wing；
It is respectively provided between first fixed-wing and the respective movable wing of second fixed-wing and the motionless wing
State deformation driving device, the deformation driving device change between the movable wing and the motionless wing by way of angle come
The fixed-wing is driven to deform and is resetted to form flapping wing.
3. deformable bionical rotor flapping wing fixed-wing one aircraft according to claim 2, which is characterized in that described
One fixed-wing and second fixed-wing are located at the both sides of the fuselage respectively.
4. deformable bionical rotor flapping wing fixed-wing one aircraft according to claim 1, which is characterized in that described solid
Determine the wing and be equipped at least one downward lifting support protrusion；
The fixed-wing can be deformed into unfolded state and be reset to folded state, the deformable bionical rotor flapping wing fixed-wing one
Body aircraft bottom of the lifting support protrusion when the fixed-wing drop to ground in a folded configuration is contacted with ground
And by the deformable bionical rotor flapping wing fixed-wing one aircraft support on ground.
5. deformable bionical rotor flapping wing fixed-wing one aircraft according to claim 4, which is characterized in that described
The bottom surface for falling support protrusion is plane or straight rib.
6. deformable bionical rotor flapping wing fixed-wing one aircraft according to claim 1, which is characterized in that described solid
Determining the wing includes the first fixed-wing and the second fixed-wing, and the first fixed-wing and the second fixed-wing are flexibly connected with the fuselage, institute
Deformation driving device is stated by changing angle and second fixed-wing and institute between first fixed-wing and the fuselage
The mode for stating angle between fuselage forms flapping wing the fixed-wing to be driven to deform and is resetted.
7. deformable bionical rotor flapping wing fixed-wing one aircraft according to claim 6, which is characterized in that described
One fixed-wing and second fixed-wing are the ring-type that outside is folded up, first fixed-wing and second fixed-wing
It is hinged respectively positioned at fuselage both sides and with the fuselage.
8. deformable bionical rotor flapping wing fixed-wing one aircraft according to claim 6, which is characterized in that described solid
Determining the wing, there are landing pit sections；The landing pit section is located on fixed-wing close to the position of fuselage, and the section bottom that lands is
Plane or straight rib.
9. deformable bionical rotor flapping wing fixed-wing one aircraft according to claim 1, which is characterized in that it is described can
It deforms bionical rotor flapping wing fixed-wing one aircraft and further includes power set, the power set electricity with the rotor respectively
Motivation and the deformation driving device electrical connection, the power set can be the electricity of the deformation driving device and the rotor
Motivation is powered.
10. according to any deformable bionical rotor flapping wing fixed-wing one aircraft of claim 1-9, feature exists
In the rotor is coaxial double-rotary wing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201810035791.XA CN108045576A (en) | 2018-01-15 | 2018-01-15 | Deformable bionical rotor flapping wing fixed-wing one aircraft |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201810035791.XA CN108045576A (en) | 2018-01-15 | 2018-01-15 | Deformable bionical rotor flapping wing fixed-wing one aircraft |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109263978A (en) * | 2018-11-12 | 2019-01-25 | 浙江大学 | Semi-active type imitates dandelion micro air vehicle and its control method |
| CN109533304A (en) * | 2018-10-19 | 2019-03-29 | 上海交通大学 | Have both rotor, fixed-wing offline mode single machine rotor aircraft and mode switching method |
| CN113212752A (en) * | 2021-06-21 | 2021-08-06 | 北京理工大学 | Multi-mode switching micro unmanned aerial vehicle |
| WO2024017419A1 (en) * | 2023-11-09 | 2024-01-25 | Su Wu | A bionic folding fixed wing household small manned aircraft |
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| CN109533304A (en) * | 2018-10-19 | 2019-03-29 | 上海交通大学 | Have both rotor, fixed-wing offline mode single machine rotor aircraft and mode switching method |
| CN109263978A (en) * | 2018-11-12 | 2019-01-25 | 浙江大学 | Semi-active type imitates dandelion micro air vehicle and its control method |
| CN109263978B (en) * | 2018-11-12 | 2023-05-23 | 浙江大学 | Semi-active dandelion-like microminiature aircraft and control method thereof |
| CN113212752A (en) * | 2021-06-21 | 2021-08-06 | 北京理工大学 | Multi-mode switching micro unmanned aerial vehicle |
| WO2024017419A1 (en) * | 2023-11-09 | 2024-01-25 | Su Wu | A bionic folding fixed wing household small manned aircraft |
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