CN203864996U - Tapered rotating flapping wing air vehicle - Google Patents
Tapered rotating flapping wing air vehicle Download PDFInfo
- Publication number
- CN203864996U CN203864996U CN201420282627.6U CN201420282627U CN203864996U CN 203864996 U CN203864996 U CN 203864996U CN 201420282627 U CN201420282627 U CN 201420282627U CN 203864996 U CN203864996 U CN 203864996U
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Abstract
The utility model discloses a tapered rotating flapping wing air vehicle, and belongs to the technical field of air vehicles. The tapered rotating flapping wing air vehicle comprises a body, a landing gear, an energy system, a control system, a left tapered rotating flapping wing, a right tapered rotating flapping wing, a tail rod, an empennage and a counterweight balancing rod, wherein the energy system comprises a left motor, a left speed-reduction gear set, a right motor, a right speed-reduction gear set, a lithium battery convenient to charge, and a motor speed regulation control device; parameters of the left motor and the right motor are the same; parameters of the left speed-reduction gear set and the right speed-reduction gear set are also the same; the control system comprises a radio navigation device and a steering engine; the empennage has balancing and pitch flying attitude control effects; the left tapered rotating flapping wing and the right tapered rotating flapping wing have the same structures, are respectively and symmetrically distributed on left and right sides of the body and provide thrust under the driving of the left motor and the right motor respectively. The air vehicle can be vertically lifted and hovered, is high in efficiency and flexible,and can be used for various tasks, such as aerial photography, geographic survey, traffic duty, military reconnaissance, rescue and relief work and the like when a user carries shooting equipment.
Description
Technical field
A taper rotary flapping wing aircraft, belongs to vehicle technology field, relates in particular to the aircraft that a kind of fin rotates.
Background technology
Traditional flapping wing aircraft is to drive flapping wing by crankshaft-connecting rod mechanism, and flapping wing is fluttered up and down and produced thrust, and its efficiency is lower, is inconvenient to adjust thrust direction, more difficult vertical lift, and the strength at repeated alternation of flapping wing material is had relatively high expectations.
Summary of the invention
The object of the invention is to overcome the above-mentioned defect of traditional flapping wing aircraft, invent the taper rotary flapping wing aircraft of the higher and maneuverability of a kind of efficiency.
The present invention adopts following technical scheme: a kind of taper rotary flapping wing aircraft comprises fuselage, alighting gear, energy resource system, control system, left taper rotary flapping wing, right taper rotary flapping wing, foot piece, empennage and counterweight balance bar.Energy resource system comprises lithium cell and the speed regulation controller for motor of left motor, left train of reduction gears, right motor, right train of reduction gears, convenient charging, and left motor is identical with the right parameter of electric machine, and the parameter of left train of reduction gears and right train of reduction gears is also identical; Control system comprises radio navigational device and steering wheel; Fuselage is framed structure, with carbon fiber composite material, makes; Alighting gear is rear bikini; Foot piece horizontal arrangement, the front end of foot piece is connected with afterbody, the rear end that a steering wheel and the foot piece of empennage by control system is connected in foot piece, empennage plays balance and pitching flying attitude control action; Left taper rotary flapping wing is identical with right taper rotary flapping wing structure, and they are symmetrically arranged in respectively the left and right sides of fuselage and under the driving of left motor and right motor, provide thrust respectively.This aircraft can vertical lift and hovering, the higher and maneuverability of efficiency.
Left taper rotary flapping wing is comprised of left main shaft, left-hand rotation arm, left wing's axis positioner, left wing's axle, left wing's sheet, left pilot bar and left guides; Right taper rotary flapping wing is comprised of right main shaft, right-hand rotation arm, right flank axis positioner, right flank axle, right flank sheet, right pilot bar and right guides; Left main shaft and right main shaft are on same straight line, left main shaft is connected with left motor by left train of reduction gears, right main shaft is connected with right motor by right train of reduction gears, left motor and right motor drive separately respectively left taper rotary flapping wing and right taper rotary flapping wing to rotate, this is simple in structure, lightweight, the higher and maneuverability of efficiency.
The concrete structure of left taper rotary flapping wing is: left main shaft one end is connected with fuselage by bearing, one end of left-hand rotation arm is connected with the other end of left main shaft is vertical, one end of the other end of left-hand rotation arm and left wing's axle is connected, the angle of left wing's axle and left-hand rotation arm is acute angle, between 30 ° ~ 45 °, left wing's axle, left-hand rotation arm and left main shaft are in same plane; The other end of left wing's axle is connected in left wing's sheet leading edge place by bearing and left wing's sheet, and Zhou Yu left wing of left wing sheet leading edge is parallel, Pian Nengrao left wing of left wing axle flexible rotating; The end face of the close left-hand rotation arm of left wing's sheet is that the root end face of left wing's sheet and the leading edge of left wing sheet are vertical.Left wing's axis positioner is between left wing's sheet and left-hand rotation arm, and left wing's axle entangles through axis positioner Bing Bei left wing of left wing axis positioner, left wing's Zhou Nengrao left wing axis positioner center switch, but can not move axially.Left wing's axis positioner adopts rotary joint bearing.Left pilot bar is comprised of left round bar, left U-shaped fork and left bearing pin; The closed end of one end of left round bar and left U-shaped fork is connected, left round bar and left U-shaped fork draw a straight line, the root that the left bearing pin vertical with left round bar that left pilot bar is installed by the open end of its left U-shaped fork and left wing's sheet work are connected in left wing's sheet close left wing's axle place, the plane of left bearing pin vertically passing left wing's sheet leading edge and trailing edge, the clearance of left U-shaped fork thickness direction guarantees that the left wing's sheet clipping can do neatly the swing of left wing's plate plane direction in left U-shaped fork.Left guides is fixedly bumped in left universal bearing by left linear bearing and forms; Left guides is connected with fuselage by the shell of its left universal bearing.The other end of left round bar is through the left linear bearing of left guides, and left round bar can do reciprocating linear motion neatly in left linear bearing, left round bar can be around the center of left guides flexible switch.The left U-shaped fork that forms left pilot bar has enough length, to guarantee that the whole rotation process of left wing's sheet can not be stuck; Left round bar has enough length to guarantee that left round bar is not deviate from left guides in the whole rotation process of left wing's sheet; Left guides is installed near left wing's axis positioner as far as possible, but should guarantee can not touch left guides at left wing's sheet whole rotation process left-wing sheet and left U-shaped fork; Left main shaft and left wing's axis positioner are respectively in the both sides of left-hand rotation arm plane of rotation, and left wing's axis positioner is on the extended line of left main shaft, and left guides and left wing's axis positioner are in the same side of left-hand rotation arm plane of rotation; Left guides to the distance of left-hand rotation arm plane of rotation in left wing's axis positioner between 1.8 times ~ 2.5 times of the distance of left-hand rotation arm plane of rotation.
The principle of work of left taper rotary flapping wing is: left motor is given left main shaft by transmission of power after left train of reduction gears is slowed down, left main shaft rotates and drives the rotation of left-hand rotation arm, left-hand rotation arm drives left wing's axle to rotate, traction bottom left fin at left wing's axle rotates, restriction due to left pilot bar and left guides, left guides all the time in the plane in crossing left wing's sheet leading edge and trailing edge or near, when left wing's sheet rotates, its angle of attack revolves at a cycle of operations the interior meeting of turning around regular variation occurs, meet flapping wing, be conducive to produce thrust.Because left guides approaches left wing axis positioner, install, in one-period, the effect of flutterring generation under left wing's sheet much larger than on flutter, the efficiency that produces lift is higher.Change the size that rotating speed can change thrust, the direction of thrust is by changing the relative azimuth of left guides and left main shaft and highly realizing.Because the angle of left wing's axle and left-hand rotation arm is acute angle, the restriction of Qie Shou left wing axis positioner, in the left and right sides of left wing's axis positioner, the rotational trajectory of left wing's axle is taper, only needs shorter left-hand rotation arm, and the scope of fluttering of left wing's sheet is larger, efficiency is high, and this is simple and compact for structure, lightweight construction; Because left wing's sheet is done tapered circumference rotation, rotating speed can be higher, can produce larger thrust, and less demanding to the strength at repeated alternation of material.
The concrete structure of right taper rotary flapping wing and principle of work are identical with left taper rotary flapping wing.Left main shaft is connected with the flower wheel of left train of reduction gears, and the driving wheel of left train of reduction gears is connected with left motor output shaft; Right main shaft is connected with the flower wheel of right train of reduction gears, and the driving wheel of right train of reduction gears is connected with right motor output shaft.Left motor and right motor drive separately respectively left taper rotary flapping wing and right taper rotary flapping wing to rotate.
Accompanying drawing explanation
Fig. 1 is the schematic top plan view of a kind of taper rotary flapping wing of the present invention aircraft.
In figure, 1-fuselage, 2-alighting gear, 3-energy resource system, the left motor of 31-, the left train of reduction gears of 32-, the right motor of 33-, the right train of reduction gears of 34-, 4-control system, the left taper rotary flapping wing of 5-, the left main shaft of 51-, 52-left-hand rotation arm, 53-left wing axis positioner, 54-left wing axle, 55-left wing sheet, the left pilot bar of 56-, the left round bar of 561-, the left U-shaped fork of 562-, the left bearing pin of 563-, the left guides of 57-, the left linear bearing of 571-, the left universal bearing of 572-, the right taper rotary flapping wing of 6-, 7-foot piece, 8-empennage, 9-counterweight balance bar; The elliptic arc of left main shaft 51 place's band arrows represents the rotation direction of left main shaft 51 under the driving of power.
The specific embodiment
Now 1 for example the present invention is illustrated by reference to the accompanying drawings: a kind of taper rotary flapping wing aircraft comprises fuselage 1, alighting gear 2, energy resource system 3, control system 4, left taper rotary flapping wing 5, right taper rotary flapping wing 6, foot piece 7, empennage 8 and counterweight balance bar 9.Energy resource system 3 comprises lithium cell and the speed regulation controller for motor of left motor 31, left train of reduction gears 32, right motor 33, right train of reduction gears 34, convenient charging; Control system 4 comprises radio navigational device and steering wheel; Fuselage 1 is framed structure, with carbon fiber composite material, makes; Alighting gear 2 is rear bikini; Foot piece 7 horizontal arrangement, the front end of foot piece 7 is connected with fuselage 1 afterbody, the rear end that a steering wheel and the foot piece 7 of empennage 8 by control system 4 is connected in foot piece 7,8 balances of empennage and pitching flying attitude control action, counterweight balance bar 9 plays counterweight and balance; Left taper rotary flapping wing 5 is identical with right taper rotary flapping wing 6 structures, and they are symmetrically arranged in respectively the left and right sides of fuselage 1 and under the driving of left motor 31 and right motor 33, provide thrust respectively.This aircraft can vertical lift and hovering, the higher and maneuverability of efficiency.
Left taper rotary flapping wing 5 is comprised of left main shaft 51, left-hand rotation arm 52, left wing's axis positioner 53, left wing's axle 54, left wing's sheet 55, left pilot bar 56 and left guides 57; Right taper rotary flapping wing 6 is comprised of right main shaft, right-hand rotation arm, right flank axis positioner, right flank axle, right flank sheet, right pilot bar and right guides; Left main shaft 51 and right main shaft are on same straight line, left main shaft 51 is connected with left motor 31 by left train of reduction gears 32, right main shaft is connected with right motor 33 by right train of reduction gears 34, left motor 31 and right motor 33 drive separately respectively left taper rotary flapping wing 5 and right taper rotary flapping wing 6 to rotate, this is simple in structure, lightweight, the higher and maneuverability of efficiency.
The concrete structure of left taper rotary flapping wing 5 is: left main shaft 51 one end are connected with fuselage 1 by bearing, vertical being connected of the other end of one end of left-hand rotation arm 52 and left main shaft 51, one end of the other end of left-hand rotation arm 52 and left wing's axle 54 is connected, the angle α of left wing's axle 54 and left-hand rotation arm 52 is between 30 ° ~ 45 °, and left wing's axle 54, left-hand rotation arm 52 and left main shaft 51 are in same plane; The other end of left wing's axle 54 is connected in left wing's sheet 55 leading edge places by bearing and left wing's sheet 55, and Zhou54Yu left wing of left wing sheet 55 leading edges are parallel, Pian55Neng Rao left wing of left wing axle 54 flexible rotatings, but left wing's sheet 55 can not be made axial linear movement on left wing's axle 54; The end face of the close left-hand rotation arm 52 of left wing's sheet 55 is that the root end face of left wing's sheet 55 is vertical with the leading edge of left wing sheet 55.Between axis positioner 53 left wing of left wing sheet 55 and left-hand rotation arm 52, left wing's axle 54 entangles through axis positioner 53Bing Bei left wing of left wing axis positioner 53, Zhou54Neng Rao left wing of left wing axis positioner 53 center switches, the maximum taper of switch is greater than 120 °, but can not move axially.Left wing's axis positioner 53 adopts rotary joint bearing.Left pilot bar 56 is comprised of left round bar 561, left U-shaped fork 562 and left bearing pin 563; The closed end of one end of left round bar 561 and left U-shaped fork 562 is connected, left round bar 561 draws a straight line with left U-shaped fork 562, the left bearing pin 563Yu left wing sheet 55 alive root close left wing axle 54 places that are connected in left wing sheet 55 vertical with left round bar 561 that left pilot bar 56 is installed by the open end of its left U-shaped fork 562, the plane of left bearing pin 563 vertically passing left wing sheet 55 leading edges and trailing edge, the clearance that left U-shaped is pitched 562 thickness directions guarantees that the left wing's sheet 55 clipping can do neatly the swing of left wing's sheet 55 in-planes in left U-shaped fork 562.Left guides 57 is fixedly bumped in left universal bearing 572 by left linear bearing 571 and forms; Left guides 57 is connected with fuselage 1 by the shell of its left universal bearing 572.The other end of left round bar 561 is through the left linear bearing 571 of left guides 57, and left round bar 561 can do reciprocating linear motion neatly in left linear bearing 571, and left round bar 561 can be around the flexible switch in left guides 57 center.The left U-shaped fork 562 that forms left pilot bar 56 has enough length, to guarantee that the whole rotation process of left wing's sheet 55 can not be stuck; Left round bar 561 has enough length to guarantee that left round bar 561 is not deviate from left guides 57 in the whole rotation process of left wing's sheet 55; Left guides 57 is installed near left wing's axis positioner 53 as far as possible, but should guarantee can not touch left guides 57 at the whole rotation process left-wing of left wing's sheet 55 sheet 55 and left U-shaped fork 562; Left main shaft 51He left wing axis positioner 53 is respectively in the both sides of left-hand rotation arm 52 plane of rotations, left wing's axis positioner 53 on the extended line of left main shaft 51, left guides 57Yu left wing's axis positioner 53 the same sides at left-hand rotation arm 52 plane of rotations; Left guides 57 to the distance of left-hand rotation arm 52 plane of rotations in left wing's axis positioner 53 between 1.8 times ~ 2.5 times of the distance of left-hand rotation arm 52 plane of rotations.
For reducing the resistance of air, improve 1ift-drag ratio, improve the efficiency of fluttering, the aerofoil profile of left wing's sheet 55 and right flank sheet all adopts flat pattern or epirelief concave shape under epirelief.
The principle of work of left taper rotary flapping wing is: left motor 31 is given left main shaft 51 by transmission of power after left train of reduction gears 32 decelerations, left main shaft 51 rotates and drives 52 rotations of left-hand rotation arm, left-hand rotation arm 52 drives left wing's axle 54 to rotate, traction bottom left fin 55 at left wing's axle 54 rotates, restriction due to left pilot bar 56 and left guides 57, left guides 57 all the time in the plane in crossing left wing's sheet 55 leading edges and trailing edge or near, during 55 rotation of left wing's sheet, its angle of attack revolves at a cycle of operations the interior meeting of turning around regular variation occurs, meet flapping wing, be conducive to produce thrust.When left wing's sheet 55 rotates a circle, the concrete change procedure of its angle of attack is: suppose that left guides 57 and left main shaft 51 are in same level, now left guides 57 is zero with the relative height of left main shaft 51, the reference position of supposing 55 rotations of left wing's sheet is the position of left wing's sheet 55 the most close left guidess 57, now the angle of attack of left wing's sheet 55 is negative 90 °, rotation traction along with left wing's axle 54, left wing's sheet 55 upward movements, the absolute value of the angle of attack is reduced to rapidly 0 °, now left pilot bar 56 cross left main shaft 51 horizontal surface above tangent with the rotating cone of left wing axle 54, then left wing's axle 54 continues rotation, the angle of attack of left wing's sheet 55 becomes 90 ° more slowly from 0 °, left pilot bar 56 levels now, left wing's sheet 55 is away from left guides 57, continuation traction along with left wing's axle 54, left wing's sheet 55 moves downward, the angle of attack becomes 0 ° more slowly from 90 °, now left pilot bar 56 cross left main shaft 51 horizontal surface below tangent with the rotating cone of left wing axle 54, continuation rotation along with left wing's axle 54, the angle of attack of left wing's sheet 55 becomes rapidly negative 90 ° by 0 °, now get back to reference position, complete a swing circle.Because left guides 57 approaches left wing's axle 54 steady arms, install, in one-period, the effect that left wing's sheet is flutterred generation for 55 times much larger than on flutter, the efficiency that produces lift is higher.Change the size that rotating speed can change thrust, the direction of thrust is by changing the relative azimuth of left guides 57 and left main shaft 51 and highly realizing.Because left wing's axle 54 is acute angle with the angle of left-hand rotation arm 52, the restriction of Qie Shou left wing axis positioner 53, the left and right sides in left wing's axis positioner 53, the rotational trajectory of left wing's axle 54 is taper, only need shorter left-hand rotation arm 52, the scope of fluttering of left wing's sheet 55 is larger, and efficiency is high, this is simple and compact for structure, lightweight construction; Because left wing's sheet 55 is done tapered circumference rotation, rotating speed can be higher, can produce larger thrust, and less demanding to the strength at repeated alternation of material.
The concrete structure of right taper rotary flapping wing 6 and principle of work are identical with left taper rotary flapping wing 5.Left main shaft 51 is connected with the flower wheel of left train of reduction gears 32, and the driving wheel of left train of reduction gears 32 is connected with left motor 31 output shafts; Right main shaft is connected with the flower wheel of right train of reduction gears 34, and the driving wheel of right train of reduction gears 34 is connected with right motor 33 output shafts.Left motor 31 and right motor 33 drive separately respectively left taper rotary flapping wing 5 and right taper rotary flapping wing 6 to rotate.From the left side of this aircraft, turn right, left wing's sheet 55 is identical with the rotation direction of right flank sheet, is all to make left-hand revolution.
The flight attitude that should invent a kind of taper rotary flapping wing aircraft is below described further this invention.
Take off: start left motor 31 and right motor 33 simultaneously, drive left taper rotary flapping wing 5 and right taper rotary flapping wing 6 to flutter simultaneously, utilize control system 4 to adjust the height of left guides 57 and right guides simultaneously, make making a concerted effort upwards of left taper rotary flapping wing 5 and 6 generations of right taper rotary flapping wing, when motor speed reaches certain value, lift is greater than body weight, and this taper rotary flapping wing aircraft vertically goes up to the air.
Before fly: after taking off, left guides 57 and right guides are moved to front upper place simultaneously, thrust direction will improve motor speed simultaneously and make the component of the direction vertically upward of thrust equal body weight to front upper place, and this aircraft is flat flying forward.
After fly: aloft during aircraft, left guides 57 and right guides are moved downwards simultaneously, make thrust direction to back upper place, adjust motor speed simultaneously and make the component of the direction vertically upward of thrust equal body weight, realize flat flying backward.
Turning flight: when front flying, separately right guides is moved to this aircraft of little Xu toward front upper place and will turn left; Separately left guides 57 being moved to this aircraft of little Xu toward front upper place will bend to right.
Hovering: while aloft flying, left guides 57 and right guides are adjusted to suitable same height and position, adjust the rotating speed of motor, make making a concerted effort vertically upward and equaling body weight of left taper rotary flapping wing 5 and 6 generations of right taper rotary flapping wing, after elimination flight inertia, this aircraft will be in hovering position.
Landing: this aircraft is adjusted to behind hovering position, slowly reduces the rotating speed of motor, this aircraft is by slowly vertical landing.
More than explanation is what do not have to make under the operating mode of interference in air flow, if there is the existence of interference in air flow, should repair partially according to the direction of air-flow and flow velocity.
The multiple-tasks such as a kind of taper rotary flapping wing of the present invention aircraft band photographs equipment can be used for taking photo by plane, geographical measurement, traffic duty, military investigation and rescue and relief work.
Claims (3)
1. a taper rotary flapping wing aircraft, comprise fuselage (1), alighting gear (2), energy resource system (3), control system (4), left taper rotary flapping wing (5), right taper rotary flapping wing (6), foot piece (7), empennage (8) and counterweight balance bar (9), it is characterized in that: energy resource system (3) comprises lithium cell and the speed regulation controller for motor of left motor (31), left train of reduction gears (32), right motor (33), right train of reduction gears (34), convenient charging, control system (4) comprises radio navigational device and steering wheel, fuselage (1) is framed structure, with carbon fiber composite material, makes, alighting gear (2) is rear bikini, foot piece (7) horizontal arrangement, the front end of foot piece (7) is connected with fuselage (1) afterbody, the rear end that a steering wheel and the foot piece (7) of empennage (8) by control system (4) is connected in foot piece (7), left taper rotary flapping wing (5) is all identical with principle of work with right taper rotary flapping wing (6) structure, and they are symmetrically arranged in respectively the left and right sides of fuselage (1), left taper rotary flapping wing (5) is comprised of left main shaft (51), left-hand rotation arm (52), left wing's axis positioner (53), left wing's axle (54), left wing's sheet (55), left pilot bar (56) and left guides (57), right taper rotary flapping wing (6) is comprised of right main shaft, right-hand rotation arm, right flank axis positioner, right flank axle, right flank sheet, right pilot bar and right guides, left main shaft (51) is with right main shaft on same straight line, and left main shaft (51) is connected with left motor (31) by left train of reduction gears (32), and right main shaft is connected with right motor (33) by right train of reduction gears (34), left main shaft (51) one end is connected with fuselage (1) by bearing, vertical being connected of the other end of one end of left-hand rotation arm (52) and left main shaft (51), one end of the other end of left-hand rotation arm (52) and left wing's axle (54) is connected, the angle (α) of left wing's axle (54) and left-hand rotation arm (52) is between 30 ° ~ 45 °, and left wing's axle (54), left-hand rotation arm (52) and left main shaft (51) are in same plane, the other end of left wing's axle (54) is connected in left wing's sheet (55) leading edge place by bearing and left wing's sheet (55), and left wing's axle (54) is parallel with left wing's sheet (55) leading edge, the end face of the close left-hand rotation arm (52) of left wing's sheet (55) is that the root end face of left wing's sheet (55) is vertical with the leading edge of left wing's sheet (55), left wing's axis positioner (53) is between left wing's sheet (55) and left-hand rotation arm (52), left wing's axle (54) entangles through left wing's axis positioner (53) Bing Bei left wing axis positioner (53), left wing's axle (54) Neng Rao left wing axis positioner (53) center switch, the maximum taper of switch is greater than 120 °, but can not move axially, left pilot bar (56) is comprised of left round bar (561), left U-shaped fork (562) and left bearing pin (563), the closed end of one end of left round bar (561) and left U-shaped fork (562) is connected, left round bar (561) draws a straight line with left U-shaped fork (562), the left bearing pin (563) vertical with left round bar (561) that left pilot bar (56) is installed by the open end of its left U-shaped fork (562) lived and is connected in the root of left wing's sheet (55) and locates near left wing's axle (54) with left wing's sheet (55), the plane of left bearing pin (563) vertically passing left wing sheet (55) leading edge and trailing edge, the clearance of left U-shaped fork (562) thickness direction guarantees that the left wing's sheet (55) clipping can do neatly the swing of left wing's sheet (55) in-plane in left U-shaped fork (562), left guides (57) is fixedly bumped in left universal bearing (572) by left linear bearing (571) and forms, left guides (57) is connected with fuselage (1) by the shell of its left universal bearing (572), the other end of left round bar (561) is through the left linear bearing (571) of left guides (57), left round bar (561) can do reciprocating linear motion neatly in left linear bearing (571), and left round bar (561) can be around the flexible switch in the center of left guides (57), the left U-shaped fork (562) that forms left pilot bar (56) has enough length, to guarantee that the whole rotation process of left wing's sheet (55) can not be stuck, left round bar (561) has enough length to guarantee that left round bar (561) is not deviate from left guides (57) in the whole rotation process of left wing's sheet (55), left guides (57) is installed near left wing's axis positioner (53) as far as possible, but should guarantee can not touch left guides (57) at left wing's sheet (55) whole rotation process left-wing sheet (55) and left U-shaped fork (562), left main shaft (51) and left wing's axis positioner (53) are respectively in the both sides of left-hand rotation arm (52) plane of rotation, left wing's axis positioner (53) is on the extended line of left main shaft (51), and left guides (57) and left wing's axis positioner (53) are in the same side of left-hand rotation arm (52) plane of rotation, left guides (57) to the distance of left-hand rotation arm (52) plane of rotation in left wing's axis positioner (53) between 1.8 times ~ 2.5 times of the distance of left-hand rotation arm (52) plane of rotation.
2. a kind of taper rotary flapping wing aircraft according to claim 1, is characterized in that: the aerofoil profile of left wing's sheet (55) and right flank sheet all adopts flat pattern or epirelief concave shape under epirelief.
3. a kind of taper rotary flapping wing aircraft according to claim 1, is characterized in that: left wing's axis positioner (53) adopts rotary joint bearing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420282627.6U CN203864996U (en) | 2014-05-30 | 2014-05-30 | Tapered rotating flapping wing air vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420282627.6U CN203864996U (en) | 2014-05-30 | 2014-05-30 | Tapered rotating flapping wing air vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203864996U true CN203864996U (en) | 2014-10-08 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420282627.6U Withdrawn - After Issue CN203864996U (en) | 2014-05-30 | 2014-05-30 | Tapered rotating flapping wing air vehicle |
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| Country | Link |
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| CN (1) | CN203864996U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103991540A (en) * | 2014-05-30 | 2014-08-20 | 佛山市神风航空科技有限公司 | Conical rotary flapping wing aircraft |
| CN104494825A (en) * | 2014-12-15 | 2015-04-08 | 佛山市神风航空科技有限公司 | Panel type flapping wing aircraft with stepping motor |
| CN104590547A (en) * | 2014-12-15 | 2015-05-06 | 王志成 | Aircraft with half-rotating blades |
-
2014
- 2014-05-30 CN CN201420282627.6U patent/CN203864996U/en not_active Withdrawn - After Issue
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103991540A (en) * | 2014-05-30 | 2014-08-20 | 佛山市神风航空科技有限公司 | Conical rotary flapping wing aircraft |
| CN103991540B (en) * | 2014-05-30 | 2015-12-02 | 佛山市神风航空科技有限公司 | A kind of taper rotary flapping wing aircraft |
| CN104494825A (en) * | 2014-12-15 | 2015-04-08 | 佛山市神风航空科技有限公司 | Panel type flapping wing aircraft with stepping motor |
| CN104590547A (en) * | 2014-12-15 | 2015-05-06 | 王志成 | Aircraft with half-rotating blades |
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