CN107097950A - A kind of plication rotor for airborne vehicle VTOL - Google Patents
A kind of plication rotor for airborne vehicle VTOL Download PDFInfo
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- CN107097950A CN107097950A CN201710354294.1A CN201710354294A CN107097950A CN 107097950 A CN107097950 A CN 107097950A CN 201710354294 A CN201710354294 A CN 201710354294A CN 107097950 A CN107097950 A CN 107097950A
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- blade
- axle sleeve
- rotary shaft
- rotor
- airborne vehicle
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/473—Constructional features
- B64C27/50—Blades foldable to facilitate stowage of aircraft
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- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The present invention provides a kind of plication rotor for airborne vehicle VTOL, belongs to airborne vehicle technical field.The multi-disc blade opened as folding fan and received and kept as folding fan during flight during with landing, including the opposite rotary shaft of one or more steering, the every multiple axle sleeves and multi-disc blade coordinated up and down of rotary shaft driving, each axle sleeve is connected with a piece of blade, every rotary shaft is connected with axle sleeve bottom and drives it to rotate, and following axle sleeve drives the axle sleeve of top successively；The upper and lower end face of each axle sleeve be provided with the fit structure with one-way and by its formed above and below two mating surfaces, the rotatable space between axle sleeve mating surface, which is formed, coordinates angle；Axle sleeve is rotated forward can locking driving, reversion reset free to rotate.Rotor aerodynamic configuration can be changed automatically by flight duty requirements and reduce resistance, improve lift, avoid vibration, realize VTOL and horizontal flight mode of operation smooth conversion and effectively compatible, have the advantages that mechanism is coordinated, simple in construction, cost is low, reliability is high, adaptability good.
Description
Technical field
The present invention relates to beaten during a kind of a kind of plication rotor, particularly VTOL for airborne vehicle VTOL
Open, horizontal flight when the plication rotor that folds, belong to airborne vehicle technical field.
Background technology
Man-carrying aircraft can be divided into fixed-wing and the major class of rotary wings two, and fixed-wing is common in Horizontal Take-off and Landing airborne vehicle（As sprayed
Gas formula passenger plane）, and rotary wings are common in VTOL airborne vehicle（Such as helicopter）.The technical merit just reached at present is come
Say, Fixed-Wing can be easy to operate with high-speed flight, but need to rely on runway landing.Rotary wing aircraft can vertically rise
Drop, is not required to rely on runway landing, strong adaptability, but mechanism is lacked of proper care, and manipulation is complicated, and flying speed is slow, and fuel efficiency is low.
At present, rotary wing aircraft is mainly shown as also in the presence of the inherent shortcoming that some can not overcome：（1）Flying speed
There is the limit.Velocity of sound is necessarily less than by wing tip absolute velocity to be limited, the theoretical velocity of rotary wing aircraft is public no more than 420
In/hour.（2）Reliability is low.Rotor blade waves generation mechanical oscillation, and adding the abrasion of hinge does not make reliability always not
Such as Fixed-Wing.（3）Roll stability is poor.Both sides rotor lift is uneven to cause rotary wing aircraft to occur roll,
It will topple in seconds out of control.（4）Manipulation is complicated.The rotor of helicopter had both provided the mobility of flight, while also making
Into the complexity of flight manipulation.So that manipulation load is far longer than fixed wing aircraft, the probability of human error is increased.（5）
It can not do big.Rotor diameter and rotating speed are limited by tip velocity no more than velocity of sound, and the general maximum of rotor diameter is exactly ten
Several meters, airborne vehicle is size-constrained, it is impossible to do more.（6）Flight mechanism is lacked of proper care.Although helicopter has developed nearly 70 years, still
In flight mechanism inaccurate coordination, be filled with geneogenous contradiction.Such as：Rotor torque is balanced using tail-rotor, using flapping hinge
With winged turning torque before lead lag hinge balance, require that rotor area is big during VTOL and wish that rotor area is small during horizontal flight,
The flight mechanism of VTOL state and level flight condition is conflicting, can not unify, and so on, directly result in flight shape
The control of state is complicated, stability is poor.
In a word, the drawbacks described above of rotary wing aircraft should take into account VTOL from rotor and meet horizontal flight again
Two kinds of offline mode and the contradiction produced.And plication rotor being capable of compatible two kinds of flight moulds of VTOL and horizontal flight very well
Formula, by as the new developing direction of rotary wing aircraft.
The content of the invention
The technical problem to be solved in the present invention is vertically risen to overcome the rotor of existing VTOL airborne vehicle to take into account
There is provided a kind of folding for airborne vehicle VTOL for the contradiction that drop meets the different offline mode of two kinds of horizontal flight and produced again
Fan formula rotor, changes aerodynamic configuration according to flight duty requirements and reduces flight resistance, avoids rotor vibration, improves characteristic of controlling oneself
And robustness, realize that intrinsic safety is anti-fall, accelerate richochet and flexible forced landing, concerted mechanism, simplify structure, reduce cost, improve reliable
Property and adaptability.
In order to solve the above technical problems, the present invention provides a kind of plication rotor for airborne vehicle VTOL, it is described
Plication rotor has during landing a multi-disc blade 3 opened and received and kept as folding fan during flight as folding fan, including one,
Two or many turn to opposite rotary shaft 1, every rotary shaft and drive the axle sleeve 2 and multi-disc blade 3 of multiple upper and lower cooperations, often
Individual axle sleeve is connected with a piece of blade, and every rotary shaft is connected with axle sleeve 2 bottom, the axle sleeve of rotary shaft driving bottom, under
The axle sleeve on side drives the axle sleeve of top successively, and thus every rotary shaft can drive one group of blade；The upper and lower end of each axle sleeve 2
Provided with fit structure 2-1 and by its formed between upper and lower two mating surfaces, the mating surface of the upper and lower axle sleeve of mutual cooperation can
Rotary moveable space, which is formed, coordinates angle α, and lower mating surface drives this axle sleeve, upper mating surface when Lower shaft sleeve turns to cooperation angle α
Upper shaft sleeve is driven when this axle sleeve turns to cooperation angle α；A leaf blade of bottom is active blade in every rotary shaft, often
The axle sleeve of root rotary shaft direct drive active blade drives the rotation of active blade, and the axle sleeve of active blade drives its top adjacent
The axle sleeve of driven blade, the axle sleeve of driven blade drives the axle sleeve of the adjacent driven blade in its top again so that same group of blade
Deploy successively according to the fit structure 2-1 cooperation angle α determined；Fit structure 2-1 on axle sleeve 2 has one-way, and positive direction turns
Can be according to the driving of angle locking be coordinated when dynamic, mating surface unlocks and upper and lower axle sleeve is freely rotated again when rotating backward
Position.
The fit structure 2-1 of the upper and lower end face of the axle sleeve 2 can be fan-shaped positive stop lug boss, the segment angle of fan-shaped positive stop lug boss
Degree, which is equal to, coordinates angle.The cooperation angle α divides equally 360 degree of determinations according to the blade number in same rotary shaft, it is ensured that a rotation
Each axle sleeve of rotating shaft drive rotates forward to after being mutually locked each blade thereon and divides equally 360o angles of circumference each other.Such as, a rotation
When there are 2 blades in rotating shaft, coordinate angle equal to 180 °, the lower surface positive stop lug boss of blade axle sleeve above and following paddle shaft
Mating surface between the upper surface positive stop lug boss of set can ensure that the two panels blade on two axle sleeves is opened in line or folded and receive
Close in line；When there are 4 blades in a rotary shaft, angle is coordinated to be equal to 90 °.
It can both be realized between the opposite rotary shaft of many steerings by way of inside and outside concentric shafts, rotation can also be passed through
Rotating shaft mode arranged apart is realized.Many turn to opposite rotary shaft modes arranged apart can be front-back staggered arrangement,
Can be dislocated arrangement, can also be the arrangement etc. that misplaces up and down.When being realized by the way of inside and outside concentric shafts, interior outward turning
It can be supported between rotating shaft by bearing, it is ensured that rotated freely between axle sleeve and rotary shaft.The rotary shaft 1 is rotated using even number
When axle is configured, two groups of blades of opposite direction rotation can cancel out each other reaction torque.
Fit structure 2-1 mating surface and blade 3 all has directionality on the axle sleeve 2, when the rotation direction of axle is opposite,
Their installation site is also opposite.The mounting sleeve 2 and during blade 3 i.e. in the opposite rotary shaft of rotation direction, should be by phase negative side
To installation, so as to ensure that the blade of mutually opposing rotation forms harmonious lift.
The blade 3 can increase when being arranged on axle sleeve 2 always away from hinge 4, so as to possess always away from regulatory function；Always can away from hinge 4
With locking with adjust blade 3 always away from can also discharge to allow blade 3 always away from free floating in adjustable range, accelerate rotation
The wing spins, and increases rotor accumulation of energy.Preferably, be always -15 ° to 45 ° away from adjustable range, specifically can be true according to actual needs
It is fixed.
The blade 3 be arranged on axle sleeve 2 on when with certain default negative angle of attack, preferably, the preset negative of blade is attacked
Angle is -5 ° to -15 °.By adjust blade 3 always away from hinge 4, increase negative angle of attack, actively form upper gas washing stream or side gas washing stream, can
To carry out super driving landing, gust disturbances are effective against, flight stability and security is improved.
The aerofoil profile of the blade 3 is existing ripe air-foil（I.e. with common wing identical streamlined）, can also carry out
Radian and thickness change, meet the air force demand of landing and flight, can specifically select to use according to actual needs.Blade 3
Profile be wide structure or axe shape structure wide outside and narrow inside, utilize rotor periphery high-speed region obtain maximum lift.Blade 3
The configurable widget for expanding rotor accumulation of energy in tip, further increases rotor rotational inertia, is conducive to increasing rotor accumulation of energy.
The rotary shaft 1 positive direction in airborne vehicle VTOL rotates, and active blade drives driven blade according to cooperation
Deploy successively at the cooperation angle of structure determination；Rotary shaft 1 is freely rotated in airborne vehicle horizontal flight, fit structure 2-1 mating surfaces
Locking discharges, and active blade brushes lower rear along folding with driven blade in windstream, reduces air drag and is simultaneously used as fixed-wing.
The blade 3 is arranged on predeterminable certain negative angle of attack when on axle sleeve 2, so as to possess spin forced landing function.In boat
In the case that pocket promptly falls, the active blade with negative angle of attack can blow lower positive direction spin rotation in air upflow, after
And drive whole group blade to deploy successively automatically, realize the unpowered spin forced landing of positive direction.
The quantity of the rotary shaft 1, axle sleeve 2 and blade 3 can increase according to real needs, quantity and the blade 3 of axle sleeve 2
Quantity is consistent, and particular number is actually needed determination according to airborne vehicle size, landing flight operating mode etc., to meet wanting for varying environment
Ask.
The present invention is deformed by the folding and retraction of rotor, changes the aerodynamic characteristics of rotor, so as to realize vertical rise
The smooth conversion and effective compatibility of drop and two kinds of mode of operations of horizontal flight.During aircraft vertical landing, plication rotor starts,
Rotary shaft 1 drives the driving axle housing and active blade thereon of bottom to rotate, then by fit structure driving axle housing and its
The adjacent driven shaft sleeve in top and driven blade servo rotary thereon；During aircraft horizontal flight, rotary shaft 1, which is in, freely to be turned
Dynamic state, the locking of the mating surface of axle sleeve 2 is released, and active blade is suitable after being brushed with driven blade by windstream to be folded, and is dropped
Low-drag, and at some extent as fixed-wing.The present invention is in working mode change, with self-reacting spy
Property, the i.e. working condition of extendible rotor can be according to flight condition automatic open-closes, reliable and stable, either in VTOL work
Under operation mode, at a high speed before either all have in the case of emergency landing under winged mode of operation it is self-maintaining, without manual intervention.Cause
This, can effectively reduce artificial operation intervention, improve the speed for flying control reaction and sensitivity, improve and fly control robustness（Fault-tolerant energy
Power）, mitigate manipulation intensity, reduce human error, the security of flight is improved, while being greatly reduced the driving of helicopter
Difficulty, reduces the manipulation load of pilot, improves lasting hours underway, improve applicability.
The present invention using float always away from design, collective pitch stick discharge after, blade can certain positive incidence
With in the range of negative angle of attack around always away from cutting with scissors 4 free floatings.In the case where airborne vehicle richochet is taken off or is promptly fallen, blade 3
Always away from hinge 4 always, away from free floating in adjustable range, to start rotor spin rapidly, rotor accumulation of energy can be increased, aviation is realized
The accumulation of energy richochet of device is taken off or the flexible forced landing of unpowered spin, preferably improves the job stability and adaptive ability of rotor.
In take-off and landing, by adjust blade 3 always away from hinge 4, increase negative angle of attack, actively form upper gas washing stream or side gas washing stream,
Super driving landing can be carried out, gust disturbances are effective against, flight stability and security is improved.At the same time it can also subtract significantly
Few downwash flow, so as to suppress dust from land surface, improves landing conditions, improves flight safety and robustness.
The blade of plication rotor of the present invention can be improved lift and be had affluence using wide string aerofoil profile, can be by rich liter
Power is used to improve flight stability, realizes super driving VTOL.And when using rigidity width string thickness rotor, rotor quality is larger,
Metal parts can also be configured in wing tip, rotor rotational inertia is further increased, is conducive to increasing rotor accumulation of energy, realizes dynamic
Ground when taking off accelerates flexible landing when richochet and unpowered rotation forced landing.
The plication rotor of the present invention is only responsible for providing lift, not responsible steering and gesture stability during VTOL, avoids
Various deflections that rotor occurs when flying before high speed, vibration, moment of torsion, eliminate flapping hinge, lead lag hinge and swash plate so that structure
Simplify, cost is reduced, reliability is improved.
The present invention provides very big flexibility to rotary shaft, the design of rotor and blade, can be designed that single shaft driving,
Two axle drive or even multiaxis driving.The blade number driven in each rotary shaft can be 1,2,3,4,5,6
It is individual even more many, different rotor demands can be met to adapt to different airborne vehicle machine configuration needs.
Compared with prior art, the present invention has steady turn that two kinds of mode of operations of VTOL and horizontal flight can be achieved
Change and effectively compatible, with self-reacting characteristic, be effectively reduced artificial operation intervention, improve the speed for flying control reaction, spirit
Sensitivity, fault-tolerant ability, security and lasting hours underway, can be achieved super driving VTOL, with mechanism coordination, structure letter
The advantages of single, with low cost, reliability is high, adaptability is good, can be widely applied to the fields such as man-carrying aircraft or unmanned plane.
Brief description of the drawings
Fig. 1 is the blade embodiment schematic front view of single shaft two of the present invention.
Fig. 2 is the blade embodiment left view schematic diagram of single shaft two of the present invention.
Fig. 3 is that the blade embodiment blade of single shaft two of the present invention is in deployed condition schematic top plan view.
Fig. 4 is schematic cross-sectional view when the axle sleeve of the embodiment of the present invention two cooperates.
Fig. 5 is A-A schematic cross-sectional views when the axle sleeve of the embodiment of the present invention two cooperates.
Fig. 6 is B-B schematic cross-sectional views when the axle sleeve of the embodiment of the present invention two cooperates.
Fig. 7 is the blade embodiment schematic front view of concentric double-shaft four of the present invention.
In figure：1- rotary shafts, 2- axle sleeves, 2-1- fit structures, 3- blades, 4- is always away from hinge, α-cooperation angle.
Embodiment
Below in conjunction with the accompanying drawings, the embodiment to the present invention is further described in detail.It is unreceipted in embodiment
Technology or product are prior art or can be by buying the conventional products obtained.
Embodiment 1：Single shaft drives two blade plication rotors.As shown in figures 1 to 6：The present invention is used for airborne vehicle VTOL
Plication rotor, the two panels blade 3 opened as folding fan and received and kept as folding fan during flight during with landing, using list
The paddle blade structure of axle two, including rotary shaft 1, the axle sleeve 2 and two panels blade 3 of two upper and lower cooperations, each axle sleeve and a piece of oar
Leaf is connected, and rotary shaft 1 is connected with following axle sleeve and drives it to rotate, and following axle sleeve drives the axle sleeve of top again；Each axle
The upper and lower end of set 2 is provided with fan-shaped boss fit structure 2-1, and forms upper and lower two mating surfaces by the fit structure；Phase interworking
Rotary movable space between the mating surface of the upper and lower axle sleeve closed forms 180 ° of cooperation angle α（The segment angle of i.e. fan-shaped boss
Degree is equal to 180 °）, lower mating surface drives this axle sleeve when Lower shaft sleeve turns to 180 °, and upper mating surface turns in this axle sleeve
Upper shaft sleeve is driven at 180 °.Leaf blade in rotary shaft 1 on the lower is active blade, rotary shaft direct drive active blade
Axle sleeve drives the rotation of active blade, and the axle sleeve of active blade drives axle sleeve and the rotation of driven blade of the driven blade above it again
Turn so that two panels blade deploys in line according to the fit structure 2-1 180 ° of cooperation angles determined.Fit structure on axle sleeve 2
2-1 has one-way, can be according to the driving of angle locking is coordinated when positive direction is rotated, and mating surface is unlocked and caused when rotating backward
Upper and lower axle sleeve can freely rotate reset.
Increase is always away from hinge 4 when blade 3 is arranged on axle sleeve 2, thus possess -15 ° to 45 ° adjustable ranges always away from adjusting work(
Energy；Always away from hinge 4 can be adjusted with locking blade 3 always away from, can also discharge with allow blade 3 always away from adjustable range freely
Float, increase rotor accumulation of energy.Blade 3 uses the thick blade of the rigidity of common air-foil, with -5 ° when on axle sleeve 2
Negative angle of attack.By adjust blade 3 always away from hinge 4, increase negative angle of attack, actively form upper gas washing stream or side gas washing stream, can carry out
Super driving landing, is effective against gust disturbances, improves flight stability and security.The profile of blade 3 is wide structure, wing tip
The metal widget of common increase rotor accumulation of energy is configured with, rotor rotational inertia is increased, increases rotor accumulation of energy.Rotary shaft 1 is in boat
Positive direction is rotated during pocket VTOL, and the cooperation angle that active blade drives driven blade to be determined according to fit structure is deployed；Rotation
Rotating shaft 1 is freely rotated in airborne vehicle horizontal flight, the release of fit structure 2-1 mating surfaces locking, active blade and driven blade
Brush lower rear along folding in windstream, reduce air drag and be simultaneously used as fixed-wing.Two panels blade 3 in rotary shaft 1 is in aviation
In the case that device promptly falls, active blade can blow lower positive direction spin rotation in air upflow, then drive driven blade
Automatic-expanding, realizes unpowered positive direction spin forced landing.
Embodiment 2：Twin-ax coaxial drives four blade plication rotors.As shown in figs. 4-7：It is vertical that the present invention is used for airborne vehicle
The plication rotor of landing, four blades 3 opened as folding fan and received and kept as folding fan during flight during with landing, bag
Include two coaxial and opposite rotary shafts 1 of steering（Outer shaft rotate counterclockwise, interior axle turns clockwise）, every rotary shaft driving two
The individual axle sleeve 2 and two panels blade 3 coordinated up and down, each axle sleeve is connected with a piece of blade, every rotary shaft and the following phase of axle sleeve 2
Even, rotary shaft drives following axle sleeve, and following axle sleeve drives the axle sleeve of top again, and thus every rotary shaft can drive two oars
Leaf；The upper and lower end of each axle sleeve 2 is provided with fan-shaped boss fit structure 2-1, and is formed from the fit structure with upper and lower two
Rotary movable space between face, the mating surface of the upper and lower axle sleeve of mutual cooperation forms 180 ° of cooperation angle α（I.e. fan-shaped limit
The fan angle of position boss is equal to 180 °）, lower mating surface Lower shaft sleeve turn to 180 ° coordinate angle when i.e. drive this axle sleeve, above match somebody with somebody
Conjunction face drives Upper shaft sleeve when this axle sleeve turns to 180 ° of cooperation angles；A leaf blade in every rotary shaft on the lower is actively
Blade, the axle sleeve of every rotary shaft direct drive active blade drives the rotation of active blade, and the axle sleeve of active blade drives thereon
The axle sleeve of Fang Xianglin driven blade and the rotation of driven blade so that determined according to fit structure 2-1 180 ° of same group of blade
Coordinate angle expansion in line；Fit structure 2-1 on axle sleeve 2 has one-way, can be according to cooperation angle when positive direction is rotated
Locking drives, and mating surface unlocks and allows upper and lower axle sleeve freely to rotate reset when rotating backward.Two turn to opposite rotation
Supported between rotating shaft by bearing, it is ensured that rotated freely between axle sleeve and rotary shaft.Fit structure 2-1 mating surface on axle sleeve 2
All there is directionality with blade 3, when the rotation direction of axle is opposite, their installation site is also opposite.Two rotary shafts are synchronously anti-
To rotation, two groups of blade synchronous backwards rotate above and below drive, balance.
Increase is always away from hinge 4 when blade 3 is arranged on axle sleeve 2, thus possess -15 ° to 45 ° adjustable ranges always away from adjusting work(
Can, satisfaction is taken off the need for operating mode, improves flight stability and security.The total of blade 3 always can be adjusted with locking away from hinge 4
Away from can also discharge to allow blade 3 always away from free floating in adjustable range, increase rotor accumulation of energy.Blade 3 uses common machine
The thick blade of rigidity of thriving type, with -15 ° of negative angle of attack when on axle sleeve 2.By adjust blade 3 always away from hinge 4, plus
Big negative angle of attack, actively forms upper gas washing stream or side gas washing stream, can carry out super driving landing, be effective against gust disturbances, improve
Flight stability and security.The profile of blade 3 is axe shape structure wide outside and narrow inside, is obtained using the high-speed region of rotor periphery
Maximum lift.The wing tip of blade 3 is configured with the metal widget of common increase rotor accumulation of energy, increases rotor rotational inertia, increase
Rotor accumulation of energy.The positive direction in airborne vehicle VTOL of rotary shaft 1 rotates, and active blade drives driven blade according to fit structure
The cooperation angle expansion of determination；Rotary shaft 1 is freely rotated in airborne vehicle horizontal flight, the release of fit structure 2-1 mating surfaces locking,
Active blade brushes lower rear along folding with driven blade in windstream, reduces air drag and is simultaneously used as fixed-wing.In rotary shaft 1
Two panels blade 3 in the case where airborne vehicle promptly falls, active blade can blow the spin rotation of lower positive direction in air upflow,
Then driven blade Automatic-expanding is driven, unpowered positive direction spin forced landing is realized.
Embodiment 3：Twin-ax coaxial drives six blade plication rotors.With reference to Fig. 1-3, as Figure 4-Figure 6：The present invention is used for
The plication rotor of airborne vehicle VTOL, six for opening as folding fan and being received and kept as folding fan during flight during with landing
Piece blade 3, including two coaxial and opposite rotary shafts 1 of steering（Outer shaft rotate counterclockwise, interior axle turns clockwise）, every rotation
Rotating shaft drives the axle sleeve 2 and three blades 3 of about three cooperations, and each axle sleeve is connected with a piece of blade, and every rotary shaft is with
The axle sleeve 2 on side is connected, and the axle sleeve of rotary shaft driving bottom, following axle sleeve drives the axle sleeve of top again, thus every rotation
Axle can drive three blades successively；The upper and lower end of each axle sleeve 2 is provided with fan-shaped boss fit structure 2-1, and is tied with this
The rotary movable space being configured between upper and lower two mating surfaces, the mating surface of the upper and lower axle sleeve of mutual cooperation forms 120 °
Cooperation angle α（The fan angle of i.e. fan-shaped positive stop lug boss is equal to 120 °）, lower mating surface turns in Lower shaft sleeve
120 ° drive this axle sleeve when coordinating angle, upper mating surface drives Upper shaft sleeve when this axle sleeve turns to 120 ° of cooperation angles；
A leaf blade of bottom is active blade in every rotary shaft, and the axle sleeve of every rotary shaft direct drive active blade drives master
Dynamic blade rotation, the axle sleeve of active blade drives axle sleeve and the rotation of driven blade of the adjacent driven blade in its top so that same
One group of blade is opened up successively according to the fit structure 2-1 120 ° of cooperation angles determined；Fit structure 2-1 on axle sleeve 2 has one-way,
Positive direction can be according to the driving of angle locking be coordinated when rotating, and mating surface unlocks and allows upper and lower axle sleeve certainly when rotating backward
Resetted by rotating.Supported between the opposite rotary shaft of two steerings by bearing, it is ensured that rotated freely between axle sleeve and rotary shaft.
Fit structure 2-1 mating surface and blade 3 all have directionality, when the rotation direction of axle is opposite, their installation position on axle sleeve 2
Put also opposite.Two groups of blade synchronous backward rotations, balance above and below two rotary shaft synchronous backward rotations, drive.
Increase is always away from hinge 4 when blade 3 is arranged on axle sleeve 2, thus possess -15 ° to 45 ° adjustable ranges always away from adjusting work(
Can, satisfaction is taken off the need for operating mode, improves flight stability and security.The total of blade 3 always can be adjusted with locking away from hinge 4
Away from can also discharge to allow blade 3 always away from free floating in adjustable range, increase rotor accumulation of energy.Blade 3 uses common machine
The thick blade of rigidity of thriving type, with -10 ° of negative angle of attack when on axle sleeve 2.By adjust blade 3 always away from hinge 4, plus
Big negative angle of attack, actively forms upper gas washing stream or side gas washing stream, can carry out super driving landing, be effective against gust disturbances, improve
Flight stability and security.The profile of blade 3 is axe shape structure wide outside and narrow inside, is obtained using the high-speed region of rotor periphery
Maximum lift.The wing tip of blade 3 is configured with common increase rotor accumulation of energy metal widget, increases rotor rotational inertia.Every rotation
The positive direction in airborne vehicle VTOL of rotating shaft 1 rotates, and active blade drives 120 ° that driven blade is determined according to fit structure
Coordinate angle expansion, produce maximum lift.Rotary shaft 1 is stalled in airborne vehicle horizontal flight, and fit structure 2-1 mating surface lockings are released
Put, active blade is folded with driven blade suitable after reverse rotation by axle center of rotary shaft under windstream brushes, rotor deformation
For the fixation wing-like of a windage very little, reduce air drag and as fixed-wing, realize high-speed flight.Every rotary shaft 1
On one group of blade 3 in the case where airborne vehicle promptly falls, active blade blows the spin rotation of lower positive direction in air upflow,
Then drive whole group blade to deploy successively automatically, realize the unpowered spin forced landing of positive direction.
Embodiment 4：The front and rear blade plication rotor of arrangement formula Two axle drive four.As shown in figs. 4-7：The present invention is used for aviation
The plication rotor of device VTOL, four oars opened as folding fan and received and kept as folding fan during flight during with landing
Leaf 3, including two forward and backward arrangements and turn to opposite rotary shaft 1（Front axle rotate counterclockwise, rear axle turns clockwise）, every
Rotary shaft drives the axle sleeves 2 and two panels blade 3 of about two cooperations, and each axle sleeve is connected with a piece of blade, every rotary shaft and
Following axle sleeve 2 is connected, and rotary shaft drives following axle sleeve, and following axle sleeve drives the axle sleeve of top again, thus every rotation
Axle can drive two blades；The upper and lower end of each axle sleeve 2 is provided with fan-shaped boss fit structure 2-1, and is formed by the fit structure
Rotary movable space between upper and lower two mating surfaces, the mating surface of the upper and lower axle sleeve of mutual cooperation forms 180 ° of cooperation
Angle α（The fan angle of i.e. fan-shaped positive stop lug boss is equal to 180 °）, the i.e. drive when Lower shaft sleeve turns to 180 ° of cooperation angles of lower mating surface
This axle sleeve is moved, upper mating surface drives Upper shaft sleeve when this axle sleeve turns to 180 ° of cooperation angles；In every rotary shaft on the lower
One leaf blade is active blade, and the axle sleeve of every rotary shaft direct drive active blade drives the rotation of active blade, active blade
Axle sleeve drive axle sleeve and the rotation of driven blade of its adjacent driven blade in top so that same group of blade is according to fit structure
180 ° of cooperation angle expansion that 2-1 is determined are in line；Fit structure 2-1 on axle sleeve 2 has one-way, and positive direction can when rotating
So that according to the driving of angle locking is coordinated, mating surface unlocks and allows upper and lower axle sleeve freely to rotate reset when rotating backward.Axle sleeve
Fit structure 2-1 mating surface and blade 3 all have directionality on 2, and when the rotation direction of axle is opposite, their installation site is also
Conversely.Two rotary shaft synchronous backward rotations, drive forward and backward two groups of blade synchronous backwards rotation, balance.
Increase is always away from hinge 4 when blade 3 is arranged on axle sleeve 2, thus possess -8 ° to 35 ° adjustable ranges always away from adjusting work(
Can, satisfaction is taken off the need for operating mode, improves flight stability and security.The total of blade 3 always can be adjusted with locking away from hinge 4
Away from can also discharge to allow blade 3 always away from free floating in adjustable range, increase rotor accumulation of energy.Blade 3 uses common machine
The thick blade of rigidity of thriving type, with -8 ° of negative angle of attack when on axle sleeve 2.By adjust blade 3 always away from hinge 4, increase
Negative angle of attack, actively forms upper gas washing stream or side gas washing stream, can carry out super driving landing, be effective against gust disturbances, improve and fly
Row stability and security.The profile of blade 3 is wide structure, and maximum lift is obtained using the high-speed region of rotor periphery.Often
The positive direction in airborne vehicle VTOL of root rotary shaft 1 rotates, and active blade drives what driven blade was determined according to fit structure
Coordinate angle expansion, produce maximum lift.Rotary shaft 1 is stalled in airborne vehicle horizontal flight, and fit structure 2-1 mating surface lockings are released
Put, active blade is folded with driven blade suitable after reverse rotation by axle center of rotary shaft under windstream brushes, rotor deformation
For the fixation wing-like of a windage very little, reduce air drag and as fixed-wing, realize high-speed flight.Every rotary shaft 1
On one group of blade 3 in the case where airborne vehicle promptly falls, active blade blows the spin rotation of lower positive direction in air upflow,
Then drive whole group blade to deploy successively automatically, realize the unpowered spin forced landing of positive direction.
The technology contents of the present invention are described above in conjunction with accompanying drawing, but protection scope of the present invention be not limited to it is described
In content, the knowledge that one skilled in the relevant art possesses, the premise of present inventive concept can also not departed from
Under the technology contents of the present invention are made a variety of changes, within the spirit and principles of the invention, any modification for being made, etc.
With replacement, improvement etc., it should be included in the scope of the protection.
Claims (10)
1. a kind of plication rotor for airborne vehicle VTOL, it is characterised in that：When the plication rotor has landing
The multi-disc blade opened and received and kept as folding fan during flight as folding fan（3）, including one, two or many steering is conversely
Rotary shaft（1）, the multiple pairings up and down of every rotary shaft driving axle sleeves（2）With multi-disc blade（3）, each axle sleeve and a piece of oar
Leaf is connected, and every rotary shaft is connected with axle sleeve bottom, and the axle sleeve of rotary shaft driving bottom, following axle sleeve drives successively
The axle sleeve of top, thus every rotary shaft can drive one group of blade；Each axle sleeve（2）Upper and lower end be provided with fit structure（2-
1）And the rotary movable space shape formed by it between upper and lower two mating surfaces, the mating surface of the upper and lower axle sleeve of mutual cooperation
Into cooperation angle（α）, lower mating surface is turned in Lower shaft sleeve coordinates angle（α）When drive this axle sleeve, upper mating surface this axle sleeve turn
Move cooperation angle（α）When drive Upper shaft sleeve；A leaf blade of bottom is active blade, every rotary shaft in every rotary shaft
The axle sleeve for directly driving active blade drives the rotation of active blade, and the axle sleeve of active blade drives the adjacent driven blade in its top
Axle sleeve, the axle sleeve of driven blade drives the axle sleeve of the adjacent driven blade in its top again so that same group of blade can according to
Close structure（2-1）Deploy successively at the cooperation angle of determination；Axle sleeve（2）On fit structure（2-1）With one-way, positive direction is rotated
When can according to coordinate angle locking driving, when rotating backward mating surface unlock and allow upper and lower axle sleeve freely to rotate reset.
2. the plication rotor according to claim 1 for airborne vehicle VTOL, it is characterised in that：The axle sleeve
（2）The fit structure of upper and lower end face（2-1）Can be fan-shaped positive stop lug boss, the fan angle of fan-shaped positive stop lug boss, which is equal to, coordinates angle
（α）.
3. the plication rotor according to claim 1 or 2 for airborne vehicle VTOL, it is characterised in that：It is described to match somebody with somebody
Close angle（α）According to same rotary shaft（1）On blade number divide equally 360 degree of determinations, it is ensured that rotary shaft drives each axle sleeve
Rotate forward to after being mutually locked each blade thereon and divide equally 360o angles of circumference each other.
4. the plication rotor according to claim 1 for airborne vehicle VTOL, it is characterised in that：Described many turn
To can both be realized between opposite rotary shaft by way of inside and outside concentric shafts, rotary shaft mode arranged apart can also be passed through
Realize；Rotary shaft（1）When being configured using even number rotary shaft, two groups of blades of opposite direction rotation can cancel out each other reaction torque.
5. the plication rotor according to claim 1 for airborne vehicle VTOL, it is characterised in that：The axle sleeve
（2）The axle sleeve of middle top drives by following axle sleeve, the axle sleeve（2）Axle sleeve bottom is connected with rotary shaft, synchronous to turn
It is dynamic, the axle sleeve of top, the axle sleeve are driven successively（2）Upper fit structure（2-1）Mating surface and blade（3）All there is direction
Property, when the rotation direction of axle is opposite, their peace position is also opposite.
6. the plication rotor according to claim 1 for airborne vehicle VTOL, it is characterised in that：The blade
（3）Installed in axle sleeve（2）It can increase always away from hinge when upper（4）, so as to possess always away from regulatory function；Always away from hinge（4）Can with locking with
Adjust blade（3）Always away from can also discharge to allow blade（3）Stored always away from free floating in adjustable range, increasing rotor
Energy.
7. the plication rotor according to claim 6 being vertically moved up or down for airborne vehicle, it is characterised in that：The blade
（3）Installed in axle sleeve（2）With certain default negative angle of attack when upper.
8. the plication rotor according to claim 1 for airborne vehicle VTOL, it is characterised in that：The blade
（3）Aerofoil profile be ripe air-foil, blade（3）Profile be wide structure or axe shape structure wide outside and narrow inside, utilize rotor
The high-speed region of periphery obtains maximum lift, blade（3）The configurable widget for expanding rotor accumulation of energy in tip.
9. the plication rotor according to claim 1 for airborne vehicle VTOL, it is characterised in that：The rotary shaft
（1）In airborne vehicle VTOL, positive direction rotates, and active blade drives the cooperation angle that driven blade is determined according to fit structure
Deploy successively；Rotary shaft（1）Freely rotated in airborne vehicle horizontal flight, fit structure（2-1）Mating surface locking discharges, actively
Blade brushes lower rear along folding with driven blade in windstream, reduces air drag and is simultaneously used as fixed-wing.
10. the plication rotor according to claim 1 being vertically moved up or down for airborne vehicle, it is characterised in that：The rotation
Axle（1）On one group of blade（3）In the case where airborne vehicle promptly falls, active blade can blow lower positive direction in air upflow
Spin rotation, then drives whole group blade to deploy successively automatically, realizes the unpowered spin forced landing of positive direction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710354294.1A CN107097950A (en) | 2017-05-18 | 2017-05-18 | A kind of plication rotor for airborne vehicle VTOL |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710354294.1A CN107097950A (en) | 2017-05-18 | 2017-05-18 | A kind of plication rotor for airborne vehicle VTOL |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107097950A true CN107097950A (en) | 2017-08-29 |
Family
ID=59670405
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710354294.1A Pending CN107097950A (en) | 2017-05-18 | 2017-05-18 | A kind of plication rotor for airborne vehicle VTOL |
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| Country | Link |
|---|---|
| CN (1) | CN107097950A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018224033A1 (en) * | 2017-06-09 | 2018-12-13 | 昆明鞘翼科技有限公司 | Aircraft with imitation beetle elytron wings |
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| DE545053C (en) * | 1929-11-20 | 1932-02-26 | Siemens & Halske Akt Ges | Braking device, especially for propellers at Flugmetoren |
| CN102905972A (en) * | 2010-06-15 | 2013-01-30 | 贝尔直升机泰克斯特龙公司 | Method and apparatus for in-flight blade folding |
| CN204688415U (en) * | 2015-05-22 | 2015-10-07 | 上海俏动智能化科技有限公司 | A kind of collapsible screw propeller for unmanned plane |
| CN205469772U (en) * | 2016-04-06 | 2016-08-17 | 成都普蓝特科技有限公司 | It is preceding to little volume unmanned aerial vehicle of folded form |
| CN207242036U (en) * | 2017-05-18 | 2018-04-17 | 昆明鞘翼科技有限公司 | A kind of plication rotor for aircraft VTOL |
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2017
- 2017-05-18 CN CN201710354294.1A patent/CN107097950A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE545053C (en) * | 1929-11-20 | 1932-02-26 | Siemens & Halske Akt Ges | Braking device, especially for propellers at Flugmetoren |
| CN102905972A (en) * | 2010-06-15 | 2013-01-30 | 贝尔直升机泰克斯特龙公司 | Method and apparatus for in-flight blade folding |
| CN204688415U (en) * | 2015-05-22 | 2015-10-07 | 上海俏动智能化科技有限公司 | A kind of collapsible screw propeller for unmanned plane |
| CN205469772U (en) * | 2016-04-06 | 2016-08-17 | 成都普蓝特科技有限公司 | It is preceding to little volume unmanned aerial vehicle of folded form |
| CN207242036U (en) * | 2017-05-18 | 2018-04-17 | 昆明鞘翼科技有限公司 | A kind of plication rotor for aircraft VTOL |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018224033A1 (en) * | 2017-06-09 | 2018-12-13 | 昆明鞘翼科技有限公司 | Aircraft with imitation beetle elytron wings |
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Application publication date: 20170829 |
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