CN104002968A - Small conical rotary flapping wing air vehicle - Google Patents
Small conical rotary flapping wing air vehicle Download PDFInfo
- Publication number
- CN104002968A CN104002968A CN201410234072.2A CN201410234072A CN104002968A CN 104002968 A CN104002968 A CN 104002968A CN 201410234072 A CN201410234072 A CN 201410234072A CN 104002968 A CN104002968 A CN 104002968A
- Authority
- CN
- China
- Prior art keywords
- wing
- sheet
- left wing
- main shaft
- rotary flapping
- 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.)
- Granted
Links
Landscapes
- Toys (AREA)
Abstract
The invention discloses a small conical rotary flapping wing air vehicle belonging to the technical field of air vehicles. The small conical rotary flapping wing air vehicle is composed of an airframe, an undercarriage, an energy system, a control system, a left conical rotary flapping wing, a right conical rotary flapping wing, a tail rod, a tail wing and a counter weight balancing pole. The energy system comprises a motor, a lithium battery, a reduction gear set and a speed regulating device; the control system comprises a wireless remote control transmitter, a receiver and a steering engine; the left conical rotary flapping wing is composed of a left main shaft, a left rotating arm, a left wing shaft locator, a left wing shaft, a left wing plate, a left guide rod and a left guider; the right conical rotary flapping wing is composed of a right main shaft, a right rotating arm, a right wing shaft locator, a right wing shaft, a right wing plate, a right guide rod and a right guider; and the left conical rotary flapping wing and the right conical rotary flapping wing are respectively and symmetrically arranged at the left and right sides of the airframe and are used for providing a thrust under the drive of power. The air vehicle is simple, light and convenient in structure, relatively high in efficiency and capable of vertically lifting and hovering. If being additionally provided with shooting equipment, the small conical rotary flapping wing air vehicle can be used for executing various tasks such as aerial photography, geographical measurement, traffic duty, military reconnaissance, rescue and relief work and the like.
Description
Technical field
A kind of small 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 small taper rotary flapping wing aircraft that a kind of efficiency is higher.
The present invention adopts following technical scheme: a kind of small 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, train of reduction gears and the speed regulation device of a motor, convenient charging; Control system comprises radio telecommand projector, receptor and steering wheel; Fuselage is framed structure; Alighting gear is rear bikini; Foot piece horizontal arrangement, the front end of foot piece is connected with afterbody, and the steering wheel of empennage by control system and foot piece are connected in the rear end of foot piece, and empennage plays balance and pitching flying attitude control action; Left taper rotary flapping wing is identical with right taper rotary flapping wing structure, and the left and right sides that they are symmetrically arranged in respectively fuselage provides thrust under the driving of power.This aircraft can vertical lift and hovering.
Left taper rotary flapping wing is made up 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 made up 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 fixed together coaxially, adopt single motor to be used as power, and pass to left main shaft and right main shaft by train of reduction gears, drive the synchronized motion in the same way of left taper rotary flapping wing and right taper rotary flapping wing simultaneously, and this is simple in structure, lightweight.
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 vertical with the other end of left main shaft to be connected, 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 45 ° ~ 60 °, 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 sheet leading edge place of left wing by bearing and left wing's sheet, and left wing's axle is parallel with left wing sheet leading edge, and left wing's sheet can be around left wing's 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 is through left wing's axis positioner being entangled by left wing's axis positioner, and left wing's axle can be around left wing's axis positioner center switch, but can not move axially.Left wing's axis positioner adopts rotary joint bearing.Left pilot bar is made up 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 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 root the axle place of close left wing of left wing's sheet, 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, and left round bar can be around the flexible switch in the center of left guides.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 is greater than the distance of left wing's axis positioner to left-hand rotation arm plane of rotation to the distance of left-hand rotation arm plane of rotation.
The principle of work of left taper rotary flapping wing is: the power of motor passes to left main shaft after slowing 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, due to the restriction of 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.Install because left guides approaches left wing axis positioner, 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 the relative azimuth by changing left guides and left main shaft and highly realizes.Because the angle of left wing's axle and left-hand rotation arm is acute angle, and be subject to the restriction of left wing's 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.Right main shaft and left main shaft are fixed together coaxially, and are connected with the flower wheel of train of reduction gears, and the driving wheel of train of reduction gears is connected with motor.
Brief description of the drawings
Fig. 1 is the schematic top plan view of a kind of small taper rotary flapping wing of the present invention aircraft.
In figure, 1-fuselage, 2-alighting gear, 3-energy resource system, 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.
Detailed description of the invention
Now 1 for example the present invention is illustrated by reference to the accompanying drawings: a kind of small 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, train of reduction gears and the speed regulation device of a motor, convenient charging; Control system 4 comprises radio telecommand projector, receptor and steering wheel; Fuselage 1 is framed structure; Alighting gear 2 is rear bikini; Foot piece 7 horizontal arrangement, the front end of foot piece 7 is connected with fuselage 1 afterbody, and the steering wheel of empennage 8 by control system 4 and foot piece 7 are connected in the rear end of 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 the left and right sides that they are symmetrically arranged in respectively fuselage 1 provides thrust under the driving of power.This aircraft can vertical lift and hovering.
Left taper rotary flapping wing 5 is made up 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 made up 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 fixed together coaxially, employing single motor is used as power, and passes to left main shaft 51 and right main shaft by train of reduction gears, drives the synchronized motion in the same way of left taper rotary flapping wing 5 and right taper rotary flapping wing 6 simultaneously, this is simple in structure, lightweight.
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 45 ° ~ 60 °, 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 left wing's axle 54 is parallel with left wing sheet 55 leading edges, 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.Left wing's axis positioner 53 is between left wing's sheet 55 and left-hand rotation arm 52, left wing's axle 54 passes left wing's axis positioner 53 and is entangled by left wing's 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 made up 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 vertical with left round bar 561 563 that left pilot bar 56 is installed by the open end of its left U-shaped fork 562 and left wing's sheet 55 root that is connected in left wing's sheet 55 alive is also near axle 54 places of left wing, 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 51 and left wing's axis positioner 53 are respectively in the both sides of left-hand rotation arm 52 plane of rotations, and 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 rotations; Left guides 57 to the distance of left-hand rotation arm 52 plane of rotations in left wing's axis positioner 53 between 1.3 times ~ 2 times of the distance of left-hand rotation arm 52 plane of rotations.
Left main shaft 51 and right main shaft are fixed together coaxially.Constant speed rotating in same direction, left wing's sheet 55 and right flank sheet arrive body foremost simultaneously, and now left wing's sheet 55 and right flank sheet all move downward and flutter down.
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: the power of motor passes to left main shaft 51 after slowing down, left main shaft 51 rotates and drives left-hand rotation arm 52 to rotate, 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, due to the restriction of 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, when left wing's sheet 55 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.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, suppose that the reference position that left wing's sheet 55 rotates 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 °, along with the rotation traction of 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 °, now left pilot bar 56 levels, left wing's sheet 55 is away from left guides 57, along with the continuation traction of 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, along with the continuation rotation of 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.Install because left guides 57 approaches left wing's axle 54 steady arms, 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 the relative azimuth by changing left guides 57 and left main shaft 51 and highly realizes.Because left wing's axle 54 is acute angle with the angle of left-hand rotation arm 52, and be subject to the restriction of left wing's axis positioner 53, in the left and right sides of 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.Right main shaft and left main shaft 51 are fixed together coaxially, and are connected with the flower wheel of train of reduction gears, and the driving wheel of train of reduction gears is connected with motor.Turn right from the left side of this aircraft, 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 small taper rotary flapping wing aircraft is below described further this invention.
Take off: actuating motor, 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, what make that left taper rotary flapping wing 5 and right taper rotary flapping wing 6 produce makes a concerted effort upwards, in the time that motor speed reaches certain value, lift is greater than body weight, and this small 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 be to front upper place, improves motor speed simultaneously and makes the component of the direction vertically upward of thrust equal body weight, and this aircraft is flat flying forward.
After fly: aloft when 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: in the time 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 flight, left guides 57 and right guides are adjusted to suitable same height and position, adjust the rotating speed of motor, what make that left taper rotary flapping wing 5 and right taper rotary flapping wing 6 produce makes a concerted effort vertically upward and equals body weight, eliminate flight inertia after 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 under the operating mode that there is no interference in air flow, to make, 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 small 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 small 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, train of reduction gears and the speed regulation device of a motor, convenient charging, control system (4) comprises radio telecommand projector, receptor and steering wheel, fuselage (1) is framed structure, alighting gear (2) is rear bikini, foot piece (7) horizontal arrangement, the front end of foot piece (7) is connected with fuselage (1) afterbody, and the steering wheel of empennage (8) by control system (4) and foot piece (7) are connected in the rear end of 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 made up 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 made up 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 fixed together coaxially, adopt single motor to be used as power, and pass to left main shaft (51) and right main shaft by train of reduction gears, 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 45 ° ~ 60 °, 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), left wing's axle (54) is parallel with left wing's sheet (55) leading edge, left wing's sheet (55) can be around left wing's axle (54) flexible rotating, 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'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) passes left wing's axis positioner (53) and is entangled by left wing's axis positioner (53), left wing's axle (54) can be around left wing's axis positioner (53) center switch, but can not move axially, left pilot bar (56) is made up 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 1.3 times ~ 2 times of the distance of left-hand rotation arm (52) plane of rotation.
2. a kind of small 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 small 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 |
|---|---|---|---|
| CN201410234072.2A CN104002968B (en) | 2014-05-30 | 2014-05-30 | A kind of small taper rotary flapping wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410234072.2A CN104002968B (en) | 2014-05-30 | 2014-05-30 | A kind of small taper rotary flapping wing aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104002968A true CN104002968A (en) | 2014-08-27 |
| CN104002968B CN104002968B (en) | 2016-02-17 |
Family
ID=51363932
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410234072.2A Expired - Fee Related CN104002968B (en) | 2014-05-30 | 2014-05-30 | A kind of small taper rotary flapping wing aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104002968B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN105329443A (en) * | 2015-11-20 | 2016-02-17 | 武汉科技大学 | Ornithopter capable of realizing flapping-reversing coupled motion |
| CN107458572A (en) * | 2017-07-17 | 2017-12-12 | 徐铭阳 | A kind of floating type bionic flapping-wing flying vehicle |
| CN108298075A (en) * | 2018-02-02 | 2018-07-20 | 南昌航空大学 | The flapping wing aircraft and its control mode that can be hovered |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2266238C2 (en) * | 2002-11-27 | 2005-12-20 | Васильев Анатолий Степанович | Flapping-wing vehicle |
| US20070262194A1 (en) * | 2005-11-08 | 2007-11-15 | Agrawal Sunil K | Mechanism for biaxial rotation of a wing and vehicle containing such mechanism |
| CN102862679A (en) * | 2012-09-02 | 2013-01-09 | 王志成 | Movable guide rod type reciprocating wing lifting force generation device |
| CN102862678A (en) * | 2012-09-02 | 2013-01-09 | 王志成 | Moving guide frame type reciprocating airfoil lift force generating device |
| CN203845006U (en) * | 2014-05-30 | 2014-09-24 | 佛山市神风航空科技有限公司 | Small tapered rotary ornithopter |
-
2014
- 2014-05-30 CN CN201410234072.2A patent/CN104002968B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2266238C2 (en) * | 2002-11-27 | 2005-12-20 | Васильев Анатолий Степанович | Flapping-wing vehicle |
| US20070262194A1 (en) * | 2005-11-08 | 2007-11-15 | Agrawal Sunil K | Mechanism for biaxial rotation of a wing and vehicle containing such mechanism |
| CN102862679A (en) * | 2012-09-02 | 2013-01-09 | 王志成 | Movable guide rod type reciprocating wing lifting force generation device |
| CN102862678A (en) * | 2012-09-02 | 2013-01-09 | 王志成 | Moving guide frame type reciprocating airfoil lift force generating device |
| CN203845006U (en) * | 2014-05-30 | 2014-09-24 | 佛山市神风航空科技有限公司 | Small tapered rotary ornithopter |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN105329443A (en) * | 2015-11-20 | 2016-02-17 | 武汉科技大学 | Ornithopter capable of realizing flapping-reversing coupled motion |
| CN105329443B (en) * | 2015-11-20 | 2017-05-31 | 武汉科技大学 | One kind flutter twisted coupling motion flapping wing aircraft |
| CN107458572A (en) * | 2017-07-17 | 2017-12-12 | 徐铭阳 | A kind of floating type bionic flapping-wing flying vehicle |
| CN108298075A (en) * | 2018-02-02 | 2018-07-20 | 南昌航空大学 | The flapping wing aircraft and its control mode that can be hovered |
| CN108298075B (en) * | 2018-02-02 | 2021-01-05 | 南昌航空大学 | Flapping wing aircraft capable of hovering and control method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104002968B (en) | 2016-02-17 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103991540B (en) | A kind of taper rotary flapping wing aircraft | |
| CN104002968B (en) | A kind of small taper rotary flapping wing aircraft | |
| CN103991549B (en) | A kind of high strength rotary flapping wing aircraft | |
| CN103991543B (en) | A kind of rotary flapping wing aircraft with spring | |
| CN203865000U (en) | Flying platform provided with four rotary flapping wings | |
| CN203864996U (en) | Tapered rotating flapping wing air vehicle | |
| CN204310045U (en) | A kind of flat-type flapping wing aircraft with stepping motor | |
| CN104443381A (en) | Small air vehicle with four oscillation wings | |
| CN203864998U (en) | Small-sized rotating flapping wing unmanned aerial vehicle | |
| CN203864997U (en) | High-strength rotary flapping wing air vehicle | |
| CN203845012U (en) | Rotary flapping wing type driving airplane | |
| CN103991541B (en) | A kind of rotary flapping wing aircraft of mini zone spring | |
| CN204310049U (en) | A kind of dull and stereotyped fin flapping wing aircraft | |
| CN204568062U (en) | One can be hovered flapping wing aircraft | |
| CN203845006U (en) | Small tapered rotary ornithopter | |
| CN203845010U (en) | Small ornithopter | |
| CN203845009U (en) | Rotary ornithopter | |
| CN203845008U (en) | Unmanned ornithopter | |
| CN103991548B (en) | A kind of rotary flapping wing aircraft | |
| CN103991547B (en) | A kind of small-sized class flapping wing aircraft | |
| CN104477389A (en) | Minitype fluttering-wing aircraft | |
| CN104494824B (en) | A kind of double; two rotary flat of sending out claps class flapping-wing aircraft | |
| CN203845011U (en) | Small rotary ornithopter with springs | |
| CN203865001U (en) | Rotary flapping wing aircraft with spring | |
| CN104443379B (en) | A kind of Minitype flat claps the unmanned flapping-wing aircraft of the wing |
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: Cui Shuangchang Inventor before: Wang Zhicheng |
|
| CB03 | Change of inventor or designer information | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20170908 Address after: 065200 Hebei Province, Sanhe Yanjiao Development Zone No. 2 and Cloud River Building 1 unit 302 room Patentee after: Cui Shuangchang 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: 20160217 Termination date: 20180530 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |