CN104477373B - A kind of half-rotating mechanism lift wing dopey - Google Patents
A kind of half-rotating mechanism lift wing dopey Download PDFInfo
- Publication number
- CN104477373B CN104477373B CN201410769779.3A CN201410769779A CN104477373B CN 104477373 B CN104477373 B CN 104477373B CN 201410769779 A CN201410769779 A CN 201410769779A CN 104477373 B CN104477373 B CN 104477373B
- Authority
- CN
- China
- Prior art keywords
- hand rotation
- wing
- leaf device
- axle
- rotation leaf
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Landscapes
- Toys (AREA)
Abstract
A kind of half-rotating mechanism lift wing dopey, belongs to technical field of aerospace, including fuselage, empennage, port wing, starboard wing, left-hand rotation leaf device, right-hand rotation leaf device, left motor, right motor, propeller and undercarriage.The port wing left and right sides that be symmetrically arranged in fuselage identical with starboard wing structure.Left-hand rotation leaf device is arranged in left groove.The main shaft of left-hand rotation leaf device is connected with left motor.Right-hand rotation leaf device is identical with left-hand rotation leaf device structure and operation principle, and both are arranged symmetrically with.Left motor is identical with right motor, and they are symmetrically installed.Left-hand rotation leaf device includes main shaft, central gear and three or the identical rotating vane of four structures.Central gear is 2: 1 with the gear ratio of leaf-teeth wheel.When arm axle is in vertical position directly over main shaft, the blade of this rotating vane and this arm axle are in same horizontal vertical guide.Left-hand rotation leaf device and right-hand rotation Ye Qineng make the air-flow of port wing and starboard wing upper surface accelerate, and are conducive to producing lift.This aircraft energy STOL and aerial Ultra-Low Speed flight, mobility is high and safety is good.
Description
Technical field
A kind of half-rotating mechanism lift wing dopey, belongs to technical field of aerospace, particularly relates to a kind of dopey.
Background technology
The surface of traditional wing is smooth, aerofoil profile has symmetric form and asymmetric, symmetric form is substantially convex under epirelief, and asymmetric have flat pattern or epirelief concave shape under epirelief, and in the range of effective angle of attack, they can produce lift, but the lift produced is limited, and effective angle of attack scope is little, when the angle of attack increases to a certain degree, the air-flow of its upper surface can produce separation, i.e. produces stall event, resistance rises suddenly, and lift declines suddenly.Traditional aircraft wing flap to be leaned on lift-rising carrys out landing, and the runway needed during landing is the longest, and is difficult to when speed is relatively low take off.
Summary of the invention
It is an object of the invention to overcome the above-mentioned deficiency of existing aircraft, invent the half-rotating mechanism lift wing dopey that the big landing runway of the lift of a kind of low speed is short.
A kind of half-rotating mechanism lift wing dopey, including fuselage, empennage, port wing, starboard wing, the left-hand rotation leaf device being installed on port wing, the right-hand rotation leaf device being installed on starboard wing, drives the left motor of left-hand rotation leaf device, right motor, propeller and the undercarriage of driving right-hand rotation leaf device.Steerable system, energy supplyystem, airborne equipment and various flight instrumentation instrument it is furnished with in fuselage.Angle of rake thrust size, left motor and the rotating speed of right motor, the deflection of rudder, elevator, port aileron and starboard aileron, all controlled by steerable system.Propeller uses electromotor to add ducted fan propeller or electromotor adds screw propeller.Left motor and right motor use lithium battery power supply.Empennage includes tailplane and vertical tail, and tailplane is made up of the standing part of leading portion i.e. horizontal stabilizer and back segment movable part i.e. elevator, and vertical tail is made up of the standing part of leading portion i.e. fixed fin and back segment movable part i.e. rudder.The port wing left and right sides that be symmetrically arranged in fuselage identical with starboard wing structure；It is provided with port aileron at the wing tip trailing edge of port wing, at the wing tip trailing edge of starboard wing, is provided with starboard aileron；The aerofoil profile of port wing and starboard wing all uses thick wing type, and their leading edge is more perfectly round, and trailing edge is more tapering.Port wing upper surface has a cross section like fan-shaped left groove, and left groove inner wall is made up of the arc-shaped curved surface inwall of left end planar wall, right-hand member planar wall and middle part.Left-hand rotation leaf device is arranged on left groove and is built between the left end planar wall of left groove and right-hand member planar wall.The latter half of left-hand rotation leaf device is substantially surrounded by left groove, and the top half of left-hand rotation leaf device substantially exposes to above port wing.The main shaft right-hand member of left-hand rotation leaf device stretches into fuselage interior and is connected with left motor.Right-hand rotation leaf device is identical with left-hand rotation leaf device structure, and both are arranged symmetrically with.Right-hand rotation leaf device is installed in the right groove of starboard wing upper surface.The main shaft left end of right-hand rotation leaf device stretches into fuselage interior and is connected with right motor.Left motor is the most identical with parameter with right electric machine structure, and they are symmetrically arranged on the right and left of fuselage interior.Undercarriage uses wheel undercarriage.
The concrete structure of left-hand rotation leaf device is: the rotating vane that the left-hand rotation leaf device structure that to include main shaft, central gear different with the setting angle of three be evenly distributed on around central gear or four only blade is identical.From the trailing edge of port wing toward in terms of leading edge, main shaft transverse horizontal is arranged vertical with the left end planar wall of left groove and right-hand member planar wall, and the left end of main shaft passes through bearing and is connected with left end planar wall.Central gear is fixedly mounted on the left of right-hand member planar wall.The end portion of keeping right of main shaft is connected in the centre bore of central gear by bearing and central gear, and main shaft can flexible rotating in the centre bore of central gear.The right-hand member of main shaft stretches into fuselage interior by the hole of fuselage left wall and is connected with left motor.Each rotating vane includes arm axle, lobus dexter axle, nearly heart gear, arm axle sleeve pipe, telecentricity gear, leaf-teeth wheel, blade, lobus sinister axle and pivoted arm.Blade is Rectangular Rigid plate blade.Structural relation between each component of same rotating vane is: lobus sinister axle transverse horizontal is arranged, the right-hand member of lobus sinister axle is connected in the left side center position of blade by bearing and blade, lobus sinister axle and blade are in same plane, and the left end of lobus sinister axle is vertical with one end of pivoted arm to be connected.The lobus dexter axle right-hand member that be fixed on lobus dexter axle vertical with arm axle, lobus dexter axle is arranged with lobus sinister axle transverse horizontal coaxially.Lobus sinister axle, pivoted arm, lobus dexter axle and arm axle are in same plane.The left end of lobus dexter axle is connected with leaf-teeth wheel by bearing, and leaf-teeth wheel can be around lobus dexter axle flexible rotating.Leaf-teeth wheel is fixed on the center position on the right of blade with blade.Lobus dexter axle is with blade in the same plane.Arm axle sleeve pipe is contained in around arm axle by bearing holder (housing, cover), arm axle can in arm axle sleeve pipe flexible rotating.Nearly heart gear and telecentricity gear are respectively fixedly connected with in the two ends of arm axle sleeve pipe.Telecentricity gear engages with leaf-teeth wheel, and telecentricity gear is 4: 1 with the gear ratio of leaf-teeth wheel.The part of the close left end of main shaft is vertical with the pivoted arm of all rotating vanes to be connected.All pivoted arms are all in same longitudinal vertical guide.The part of the close central gear of right section of main shaft is vertical with the arm axle of all rotating vanes to be connected.All arm axles are all in same longitudinal vertical guide.The nearly heart gear of all rotating vanes all engages with central gear, and central gear is 1: 2 with the gear ratio of nearly heart gear.Central gear, nearly heart gear, telecentricity gear and leaf-teeth wheel all use bevel gear.Assembling left-hand rotation Ye Qishi, guarantee that when the arm axle of its arbitrary rotating vane is in vertical position directly over main shaft, the blade of this rotating vane and this arm axle are in same horizontal vertical guide, so, owing to central gear maintains static, and the gear ratio of central gear and leaf-teeth wheel is 2: 1, this rotating vane goes to the blade of this rotating vane when arm axle is in vertical position immediately below main shaft and is in level.
The port wing of this invention a kind of half-rotating mechanism lift wing dopey is so to produce lift under the cooperation of left-hand rotation leaf device and left motor: turn right from the left side of this aircraft, left motor drives left-hand rotation leaf device rotationally clockwise, the blade of rotating vane angle of attack when the lower section of main shaft moves ahead is less, and resistance is less；Blade above main shaft after row time the angle of attack more greatly be conducive to accelerate port wing upper surface air-flow.When this aircraft moves ahead under the push of the pusher, when port wing travels forward with the certain angle of attack in the range of effective angle of attack, front flow close to leading edge punish two plumes move, main air is the lower section air-flow of port wing, this air-flow velocity is basically unchanged, suitable with front speed of incoming flow；Secondary air flow is the overhead stream of port wing, and this air-flow is flowing upward to acceleration flowing underneath backward under the agitating that left-hand rotation leaf device is in left-hand rotation leaf device near the turning of port wing edge.Equation of continuity and Bernoulli equation according to fluid are learnt, the top pressure of port wing is less than lower section pressure, thus produces bigger lift.The left-hand rotation Ye Qineng of port wing upper surface makes air accelerate and relatively be close to upper surface to flow to rear, is difficult to separate with the postmedian of port wing upper surface, can postpone the generation of tail.
The operation principle that starboard wing produces lift under right-hand rotation leaf device with the cooperation of right motor is identical with port wing.
Elevator can deflect under the manipulation of steerable system up and down, upward deflects and this aircraft can be made to come back, it is achieved face upward；The change of team of elevator downward bias makes this aircraft bow, it is achieved nutation.Rudder is deflection under the manipulation of steerable system, and this aircraft can be made to go off course to the left or to the right.Manipulate port aileron and the upper and lower differential deflection of starboard aileron or change left-hand rotation leaf device and the rotating speed of right-hand rotation leaf device, horizontal rolling about this aircraft can be made；Manipulation port aileron and starboard aileron deflect down simultaneously, and this airplane ascensional force can be made to increase, favourable landing or climb.Improve lift by accelerating the rotating speed of left-hand rotation leaf device and right-hand rotation leaf device, be also beneficial to the short take-off and landing of this aircraft and aerial Ultra-Low Speed flight.When propeller does not works or exerts oneself inadequate, left-hand rotation leaf device and right-hand rotation leaf device can serve as auxiliary propulsion power, make this aircraft can slide farther, greatly increase safety.
Owing to this left-hand rotation leaf device and right-hand rotation leaf device are operated alone, therefore the mobility of this aircraft is high.
Accompanying drawing explanation
Fig. 1 is the schematic rear view of the present invention a kind of half-rotating mechanism lift wing dopey；Fig. 2 is the schematic top plan view of Fig. 1；Fig. 3 is the left view schematic diagram of Fig. 1；Fig. 4 is the left view simplified schematic diagram of the port wing being installed with the left-hand rotation leaf device with four rotating vanes being exaggerated；Fig. 5 is the left view schematic diagram of the left-hand rotation leaf device being exaggerated；Fig. 6 is the schematic rear view of engage with central gear the rotating vane being connected with main shaft of the left-hand rotation leaf device being exaggerated, and in figure, arm axle is in the surface vertical position of main shaft.
In figure, the rotating vane quantity of left-hand rotation leaf device and right-hand rotation leaf device is four.
In figure, 1-fuselage, 2-empennage, 21-tailplane, 22-vertical tail；3-port wing, 31-port aileron, 32-port wing leading edge, 33-port wing trailing edge, the left groove of 34-, the left end planar wall of the left groove of 341-, the right-hand member planar wall of the left groove of 342-；4-starboard wing, 41-starboard aileron；5-left-hand rotation leaf device, 51-main shaft, 52-central gear, 53-rotating vane, 531-arm axle, 532-lobus dexter axle, 533-nearly heart gear, 534-arm axle sleeve pipe, 535-telecentricity gear, 536-leaf-teeth wheel, 537-blade, 538-lobus sinister axle, 539-pivoted arm；53a, 53b, 53c and 53d represent the rotating vane being in diverse location；The rotation direction of 54-left-hand rotation leaf device 5；6-right-hand rotation leaf device；The left motor of 7-；The right motor of 8-；9-propeller；10-undercarriage.
Detailed description of the invention
Below in conjunction with accompanying drawing, 1 ~ 6 couple of present invention is illustrated.
A kind of half-rotating mechanism lift wing dopey, including fuselage 1, empennage 2, port wing 3, starboard wing 4, the left-hand rotation leaf device 5 being installed on port wing 3, the right-hand rotation leaf device 6 being installed on starboard wing 4, drives the left motor 7 of left-hand rotation leaf device 5, the driving right motor 8 of right-hand rotation leaf device 6, propeller 9 and undercarriage 10.Steerable system, energy supplyystem, airborne equipment and various flight instrumentation instrument it is furnished with in fuselage 1.The thrust size of propeller 10, left motor 7 and the rotating speed of right motor 8, rudder, elevator, port aileron 31 and the deflection of starboard aileron 41, all controlled by steerable system.Propeller 9 uses electromotor to add ducted fan propeller or electromotor adds screw propeller.Left motor 7 and right motor 8 use lithium battery power supply.Empennage 2 includes tailplane 21 and vertical tail 22, tailplane 21 is made up of the standing part of leading portion i.e. horizontal stabilizer and back segment movable part i.e. elevator, and vertical tail 22 is made up of the standing part of leading portion i.e. fixed fin and back segment movable part i.e. rudder.Port wing 3 left and right sides that be symmetrically arranged in fuselage 1 identical with starboard wing 4 structure；It is provided with port aileron 31 at the wing tip trailing edge of port wing 3, at the wing tip trailing edge of starboard wing 4, is provided with starboard aileron 41；The aerofoil profile of port wing 3 and starboard wing 4 all uses thick wing type, and their leading edge is more perfectly round, and trailing edge is more tapering.Port wing 3 upper surface has a cross section like fan-shaped left groove 34, and left groove 34 inwall is made up of the arc-shaped curved surface inwall of left end planar wall 341, right-hand member planar wall 342 and middle part.Left-hand rotation leaf device 5 is arranged between left end planar wall 341 and the right-hand member planar wall 342 that left groove 34 is built in left groove 34.The latter half of left-hand rotation leaf device 5 is substantially surrounded by left groove 34, and the top half of left-hand rotation leaf device 5 substantially exposes to above port wing 3.Main shaft 51 right-hand member of left-hand rotation leaf device 5 stretches into fuselage 1 inside and is connected with left motor 7.Right-hand rotation leaf device 6 is identical with left-hand rotation leaf device 5 structure, and both are arranged symmetrically with.Right-hand rotation leaf device 6 is installed in the right groove of starboard wing 4 upper surface.The main shaft left end of right-hand rotation leaf device 6 stretches into fuselage 1 inside and is connected with right motor 8.Left motor 7 is the most identical with right motor 8 structure and parameter, and they are symmetrically arranged on the right and left within fuselage 1.Undercarriage 10 uses wheel undercarriage.
The concrete structure of left-hand rotation leaf device 5 is: the rotating vane 53 that left-hand rotation leaf device 5 structure that to include main shaft 51, central gear 52 different with the setting angle of four be evenly distributed on around central gear 52 only blade 537 is identical.From the trailing edge of port wing 3 toward in terms of leading edge, main shaft 51 transverse horizontal is arranged vertical with the left end planar wall 341 of left groove 34 and right-hand member planar wall 342, and the left end of main shaft 51 passes through bearing and is connected with left end planar wall 341.Central gear 52 is fixedly mounted on the left of right-hand member planar wall 342.The end portion of keeping right of main shaft 51 is connected in the centre bore of central gear 52 by bearing and central gear 52, and main shaft 51 can flexible rotating in the centre bore of central gear 52.The right-hand member of main shaft 51 stretches into fuselage 1 inside by the hole of fuselage 1 left wall and is connected with left motor 7.Each rotating vane 53 includes arm axle 531, lobus dexter axle 532, nearly heart gear 533, arm axle sleeve pipe 534, telecentricity gear 535, leaf-teeth wheel 536, blade 537, lobus sinister axle 538 and pivoted arm 539.Blade 537 is Rectangular Rigid plate blade.Structural relation between each component of same rotating vane 53 is: lobus sinister axle 538 transverse horizontal is arranged, the right-hand member of lobus sinister axle 538 is connected in the left side center position of blade 537 by bearing and blade 537, lobus sinister axle 538 and blade 537 are in same plane, and the left end of lobus sinister axle 538 is vertical with one end of pivoted arm 539 to be connected.Lobus dexter axle 532 right-hand member that be fixed on lobus dexter axle 532 vertical with arm axle 531, lobus dexter axle 532 is arranged with lobus sinister axle 538 transverse horizontal coaxially.Lobus sinister axle 538, pivoted arm 539, lobus dexter axle 532 and arm axle 531 are in same plane.The left end of lobus dexter axle 532 is connected with leaf-teeth wheel 536 by bearing, and leaf-teeth wheel 536 can be around lobus dexter axle 532 flexible rotating.Leaf-teeth wheel 536 and blade 537 are fixed on the center position on the right of blade 537.Lobus dexter axle 532 is with blade 537 in the same plane.Arm axle sleeve pipe 534 is contained in around arm axle 531 by bearing holder (housing, cover), arm axle 531 can in arm axle sleeve pipe 534 flexible rotating.Nearly heart gear 533 and telecentricity gear 535 are respectively fixedly connected with in the two ends of arm axle sleeve pipe 534.Telecentricity gear 535 engages with leaf-teeth wheel 536, and telecentricity gear 535 is 4: 1 with the gear ratio of leaf-teeth wheel 536.The part of the close left end of main shaft 51 is vertical with the pivoted arm of all rotating vane 53a, 53b, 53c and 53d to be connected.All pivoted arms are all in same longitudinal vertical guide.The part of the close central gear 52 of right section of main shaft 51 is vertical with the arm axle of all rotating vane 53a, 53b, 53c and 53d to be connected.All arm axles are all in same longitudinal vertical guide.The nearly heart gear of all rotating vane 53a, 53b, 53c and 53d all engages with central gear 52, and central gear 52 is 1: 2 with the gear ratio of nearly heart gear 533.Central gear 52, nearly heart gear 533, telecentricity gear 535 and leaf-teeth wheel 536 all use bevel gear.During assembling left-hand rotation leaf device 5, guarantee that when the arm axle of its arbitrary rotating vane is in vertical position directly over main shaft, the blade of this rotating vane and this arm axle are in same horizontal vertical guide, so, owing to central gear 52 maintains static, and the gear ratio of central gear 52 and leaf-teeth wheel 536 is 2: 1, this rotating vane goes to the blade of this rotating vane when arm axle is in vertical position immediately below main shaft and is in level.
The port wing 3 of this invention a kind of half-rotating mechanism lift wing dopey is so to produce lift under the cooperation of left-hand rotation leaf device 5 and left motor 7: turn right from the left side of this aircraft, left motor 7 drives left-hand rotation leaf device 5 rotationally clockwise, the blade of rotating vane angle of attack when the lower section of main shaft 51 moves ahead is less, and resistance is less；Blade above main shaft 51 after row time the angle of attack more greatly be conducive to accelerate port wing 3 upper surface air-flow.When this aircraft moves ahead under the promotion of propeller 9, when port wing 3 travels forward with the certain angle of attack in the range of effective angle of attack, front flow close to port wing leading edge 32 punish two plumes move, main air is the lower section air-flow of port wing 3, this air-flow velocity is basically unchanged, suitable with front speed of incoming flow；Secondary air flow is the overhead stream of port wing 3, and this air-flow flows upward to acceleration flowing underneath backward under the agitating that left-hand rotation leaf device 5 is in left-hand rotation leaf device 5 in turning at port wing leading edge 32.Equation of continuity and Bernoulli equation according to fluid are learnt, the top pressure of port wing 3 is less than lower section pressure, thus produces bigger lift.The left-hand rotation leaf device 5 of port wing 3 upper surface can make air accelerate and relatively be close to upper surface to flow to rear, is difficult to separate with the postmedian on 3 surfaces on port wing, can postpone the generation of tail.
The operation principle that starboard wing 4 produces lift under right-hand rotation leaf device 6 with the cooperation of right motor 8 is identical with port wing 3.
Elevator can deflect under the manipulation of steerable system up and down, upward deflects and this aircraft can be made to come back, it is achieved face upward；The change of team of elevator downward bias makes this aircraft bow, it is achieved nutation.Rudder is deflection under the manipulation of steerable system, and this aircraft can be made to go off course to the left or to the right.Manipulate port aileron 31 and the differential deflection of starboard aileron about 41 or control left-hand rotation leaf device 5 and the rotating speed of right-hand rotation leaf device 6, horizontal rolling about this aircraft can be made；Manipulation port aileron 31 and starboard aileron 41 deflect down simultaneously, and this airplane ascensional force can be made to increase, favourable landing or climb.Improve lift by accelerating the rotating speed of left-hand rotation leaf device 5 and right-hand rotation leaf device 6, be conducive to the short take-off and landing of this aircraft and aerial Ultra-Low Speed flight.When propeller 9 does not works or exerts oneself inadequate, left-hand rotation leaf device 5 and right-hand rotation leaf device 6 can serve as auxiliary propulsion power, make this aircraft can slide farther, greatly increase safety.
Owing to this left-hand rotation leaf device 5 and right-hand rotation leaf device 6 are operated alone, therefore the mobility of this aircraft is high.
Claims (5)
1. a half-rotating mechanism lift wing dopey, it is characterised in that: include fuselage (1), empennage (2), port wing (3), starboard wing (4), left-hand rotation leaf device (5) being installed on port wing (3), right-hand rotation leaf device (6) being installed on starboard wing (4), drive the left motor (7) of left-hand rotation leaf device (5), right motor (8), propeller (9) and the undercarriage (10) of driving right-hand rotation leaf device (6)；Steerable system, energy supplyystem, airborne equipment and flight instrumentation instrument it is furnished with in fuselage (1)；Empennage (2) includes tailplane (21) and vertical tail (22), tailplane (21) is made up of the standing part of leading portion i.e. horizontal stabilizer and back segment movable part i.e. elevator, and vertical tail (22) is made up of the standing part of leading portion i.e. fixed fin and back segment movable part i.e. rudder；Port wing (3) left and right sides that be symmetrically arranged in fuselage (1) identical with starboard wing (4) structure；It is provided with port aileron (31) at the wing tip trailing edge of port wing (3), at the wing tip trailing edge of starboard wing (4), is provided with starboard aileron (41)；The aerofoil profile of port wing (3) and starboard wing (4) all uses thick wing type, and their leading edge is more perfectly round, and trailing edge is more tapering；Port wing (3) upper surface has a cross section like fan-shaped left groove (34), and left groove (34) inwall is made up of the arc-shaped curved surface inwall of left end planar wall (341), right-hand member planar wall (342) and middle part；Left-hand rotation leaf device (5) is arranged on left groove (34) and is built between the left end planar wall (341) of left groove (34) and right-hand member planar wall (342)；The latter half of left-hand rotation leaf device (5) is substantially surrounded by left groove (34), and the top half of left-hand rotation leaf device (5) substantially exposes to port wing (3) top；Main shaft (51) right-hand member of left-hand rotation leaf device (5) stretches into fuselage (1) inside and is connected with left motor (7)；Right-hand rotation leaf device (6) is the most identical with left-hand rotation leaf device (5) structure and operation principle, and both are arranged symmetrically with；Right-hand rotation leaf device (6) is installed in the right groove of starboard wing (4) upper surface；The main shaft left end of right-hand rotation leaf device (6) stretches into fuselage (1) inside and is connected with right motor (8)；Left motor (7) is the most identical with right motor (8) structure and parameter, and they are symmetrically arranged on the right and left that fuselage (1) is internal；Undercarriage (10) uses wheel undercarriage；
The concrete structure of left-hand rotation leaf device (5) is: the rotating vane (53) that left-hand rotation leaf device (5) structure that to include main shaft (51), central gear (52) different with the setting angle of be evenly distributed on central gear (52) around three or four only blade (537) is identical；From the trailing edge of port wing (3) toward in terms of leading edge, main shaft (51) transverse horizontal is arranged vertical with the left end planar wall (341) of left groove (34) and right-hand member planar wall (342), and the left end of main shaft (51) passes through bearing and is connected with left end planar wall (341)；Central gear (52) is fixedly mounted on right-hand member planar wall (342) left side；The end portion of keeping right of main shaft (51) is connected in the centre bore of central gear (52) by bearing and central gear (52), and main shaft (51) can flexible rotating in the centre bore of central gear (52)；The right-hand member of main shaft (51) stretches into fuselage (1) inside by the hole of fuselage (1) left wall and is connected with left motor (7)；Each rotating vane (53) includes arm axle (531), lobus dexter axle (532), nearly heart gear (533), arm axle sleeve pipe (534), telecentricity gear (535), leaf-teeth wheel (536), blade (537), lobus sinister axle (538) and pivoted arm (539)；Blade (537) is Rectangular Rigid plate blade；Structural relation between each component of same rotating vane (53) is: lobus sinister axle (538) transverse horizontal is arranged, the right-hand member of lobus sinister axle (538) is connected in the left side center position of blade (537) by bearing and blade (537), lobus sinister axle (538) and blade (537) are in same plane, and the left end of lobus sinister axle (538) is vertical with one end of pivoted arm (539) to be connected；Lobus dexter axle (532) right-hand member that be fixed on lobus dexter axle (532) vertical with arm axle (531), lobus dexter axle (532) is arranged with lobus sinister axle (538) transverse horizontal coaxially；Lobus sinister axle (538), pivoted arm (539), lobus dexter axle (532) and arm axle (531) are in same plane；The left end of lobus dexter axle (532) is connected with leaf-teeth wheel (536) by bearing, and leaf-teeth wheel (536) can be around lobus dexter axle (532) flexible rotating；Leaf-teeth wheel (536) and blade (537) are fixed on the center position on the right of blade (537)；Lobus dexter axle (532) is with blade (537) in the same plane；Arm axle sleeve pipe (534) is contained in arm axle (531) around by bearing holder (housing, cover), arm axle (531) can in arm axle sleeve pipe (534) flexible rotating；Nearly heart gear (533) and telecentricity gear (535) are respectively fixedly connected with in the two ends of arm axle sleeve pipe (534)；Telecentricity gear (535) engages with leaf-teeth wheel (536)；The part of the close left end of main shaft (51) is vertical with the pivoted arm of all rotating vanes to be connected；All pivoted arms are all in same longitudinal vertical guide；The part of the close central gear (52) of right section of main shaft (51) is vertical with the arm axle of all rotating vanes to be connected；All arm axles are all in same longitudinal vertical guide；The nearly heart gear of all rotating vanes all engages with central gear (52)；Central gear (52) is 2: 1 with the gear ratio of leaf-teeth wheel (536)；When the arm axle of rotating vane is in vertical position directly over main shaft, the blade of this rotating vane and this arm axle are in same horizontal vertical guide；
From fuselage (1) left side turn right, left-hand rotation leaf device (5) under the driving of left motor (7) rotationally clockwise；Right-hand rotation leaf device (6) under the driving of right motor (8) rotationally clockwise；Left-hand rotation leaf device (5) and right-hand rotation leaf device (6) are operated alone.
A kind of half-rotating mechanism lift wing dopey the most according to claim 1, it is characterised in that: propeller (9) uses electromotor to add ducted fan propeller or electromotor adds screw propeller.
A kind of half-rotating mechanism lift wing dopey the most according to claim 1, it is characterised in that: left motor (7) and right motor (8) use lithium battery power supply.
A kind of half-rotating mechanism lift wing dopey the most according to claim 1, it is characterised in that: the gear ratio that telecentricity gear (535) engages with leaf-teeth wheel (536) is 4: 1；The gear ratio that central gear (52) engages with nearly heart gear (533) is 1: 2.
5. according to a kind of half-rotating mechanism lift wing dopey described in claim 1 or 4, it is characterised in that: central gear (52), nearly heart gear (533), telecentricity gear (535) and leaf-teeth wheel (536) all use bevel gear.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410769779.3A CN104477373B (en) | 2014-12-15 | 2014-12-15 | A kind of half-rotating mechanism lift wing dopey |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410769779.3A CN104477373B (en) | 2014-12-15 | 2014-12-15 | A kind of half-rotating mechanism lift wing dopey |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104477373A CN104477373A (en) | 2015-04-01 |
| CN104477373B true CN104477373B (en) | 2016-08-31 |
Family
ID=52752030
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410769779.3A Expired - Fee Related CN104477373B (en) | 2014-12-15 | 2014-12-15 | A kind of half-rotating mechanism lift wing dopey |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104477373B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106275421B (en) * | 2015-06-04 | 2018-06-01 | 陈志石 | A kind of unmanned transporter |
| CN105035319A (en) * | 2015-07-27 | 2015-11-11 | 江阴市翔诺电子科技有限公司 | Novel vertical take-off and landing air vehicle and control method thereof |
| CN105882942B (en) * | 2016-05-27 | 2018-11-09 | 南京航空航天大学 | A kind of high-efficient low-speed aircraft |
| CN110450938A (en) * | 2019-08-16 | 2019-11-15 | 刘忠革 | A kind of whole rotatable aircraft of wing |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2007285289A (en) * | 2006-04-19 | 2007-11-01 | Masaru Yuasa | Reverse direction-half rotation blade perpendicular shaft type windmill |
| CN101405182A (en) * | 2006-03-31 | 2009-04-08 | 范文有限公司 | Aircraft with aerodynamic lift generating device |
| CN204297057U (en) * | 2014-12-15 | 2015-04-29 | 佛山市神风航空科技有限公司 | A kind of half-rotating mechanism lift wing dopey |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7607606B2 (en) * | 2002-09-11 | 2009-10-27 | Milde Jr Karl F | VTOL personal aircraft |
-
2014
- 2014-12-15 CN CN201410769779.3A patent/CN104477373B/en not_active Expired - Fee Related
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101405182A (en) * | 2006-03-31 | 2009-04-08 | 范文有限公司 | Aircraft with aerodynamic lift generating device |
| JP2007285289A (en) * | 2006-04-19 | 2007-11-01 | Masaru Yuasa | Reverse direction-half rotation blade perpendicular shaft type windmill |
| CN204297057U (en) * | 2014-12-15 | 2015-04-29 | 佛山市神风航空科技有限公司 | A kind of half-rotating mechanism lift wing dopey |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104477373A (en) | 2015-04-01 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105083550A (en) | Fixed-wing aircraft realizing vertical take-off and landing | |
| CN104108464B (en) | A kind of double-deck rotor aircraft | |
| CN205022862U (en) | Power device and fixed wing aircraft with mechanism of verting | |
| CN205022861U (en) | VTOL fixed wing aircraft | |
| CN104477373B (en) | A kind of half-rotating mechanism lift wing dopey | |
| CN206243479U (en) | Flapping wing aircraft | |
| CN204297058U (en) | A kind of high lift hardware aircraft | |
| CN104443353B (en) | A kind of variable wing plane | |
| CN106494618B (en) | Plumage formula flapping-wing aircraft | |
| CN203845012U (en) | Rotary flapping wing type driving airplane | |
| CN205131630U (en) | Double -oar vertical lift aircraft | |
| CN204297057U (en) | A kind of half-rotating mechanism lift wing dopey | |
| CN210416978U (en) | Novel vertical take-off and landing aircraft | |
| CN105173060B (en) | A kind of pair of oar Convertiplane | |
| CN103909796A (en) | Vertical lifting hovercar | |
| CN101121441A (en) | Aircraft with multi-wing and multi-thruster | |
| CN104477374B (en) | A kind of high lift hardware aircraft | |
| CN206734609U (en) | A kind of tail sitting posture VUAV using duct | |
| CN204642148U (en) | A kind of leading edge of a wing is equipped with the aircraft that wind ball drives wind wheel | |
| CN103991542B (en) | A kind of rotary flapping wing drives aircraft | |
| CN104787305B (en) | A kind of aircraft of the leading edge of a wing with wind ball driving wind wheel | |
| CN104590547B (en) | A kind of half way around blade aircraft | |
| RU36347U1 (en) | Aircraft "Tramp LA-01" | |
| CN204297059U (en) | A kind of variable wing plane | |
| CN105270623A (en) | High lift aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CB03 | Change of inventor or designer information |
Inventor after: Li Xiuli Inventor before: Wang Zhicheng |
|
| CB03 | Change of inventor or designer information | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20170908 Address after: 075000, No. 2, unit 75, 501 East Street, Qiaodong District, Hebei, Zhangjiakou Patentee after: Li Xiuli Address before: Foshan City, Guangdong province 528500 city streets Gaoming District No. 78 Jiangwan Road, room 402 Fu Wan Patentee before: Shenfeng science and technology of aviation Co., Ltd of Foshan City |
|
| TR01 | Transfer of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160831 Termination date: 20171215 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |