CN104477391A - Flat-flapping-wing flapping-wing aircraft - Google Patents
Flat-flapping-wing flapping-wing aircraft Download PDFInfo
- Publication number
- CN104477391A CN104477391A CN201410769999.6A CN201410769999A CN104477391A CN 104477391 A CN104477391 A CN 104477391A CN 201410769999 A CN201410769999 A CN 201410769999A CN 104477391 A CN104477391 A CN 104477391A
- Authority
- CN
- China
- Prior art keywords
- synchronizing wheel
- wing
- main shaft
- sheet
- fuselage
- 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 relates to a flat-flapping-wing flapping-wing aircraft, belonging to the technical field of aviation. The flat-flapping-wing flapping-wing aircraft comprises a fuselage, an empennage, a left flapping wing device, a right flapping wing device and an undercarriage. The left flapping wing device and the right flapping wing device are the same in structure and parameter and are symmetrically arranged at the left and right sides of the fuselage. The empennage is used for controlling pitching and turning flight attitudes. The left flapping wing device comprises a left motor, a left main shaft, a left swinging arm, a left wing shaft, a left wing sheet, a left fixed synchronizing wheel, a left synchronizing belt and a left movable synchronizing wheel. The left fixed synchronizing wheel is fixedly connected with the fuselage, one end of the left swinging arm is vertically and fixedly connected with the left main shaft, and the other end of the left swinging arm is vertically connected with the left wing shaft through a bearing. The left movable synchronizing wheel is fixedly connected to the front end of the wing shaft, and the transmission ratio of the left fixed synchronizing wheel to the left movable synchronizing wheel is 1:1. The left wing sheet and a right wing sheet cannot generate horizontal components in the transverse direction during vertical flapping, so that the efficiency is higher. The aircraft can be applied to a variety of tasks, such as aerial photography, geographic survey, traffic duty, agriculture and forestry operation, military reconnaissance and emergency rescue and disaster relief.
Description
Technical field
A kind of flat bat fin flapping wing aircraft, belongs to technical field of aerospace, particularly relates to a kind of flapping wing aircraft.
Background technology
The wing of tradition flapping wing aircraft is fluttered by arc track, portion of air powertrain components is created in the horizontal direction of transverse direction during wing flapping motion, the component of this horizontal direction does not all have positive effect to moving ahead and going up to the air of aircraft, is a kind of loss of power.
Summary of the invention
The object of the invention is the above-mentioned deficiency overcoming existing flapping wing aircraft, invent the flat bat fin flapping wing aircraft that a kind of efficiency is higher.
A kind of flat bat fin flapping wing aircraft, comprises fuselage, empennage, left bat swing device, right bat swing device and alighting gear.Control system, airborne equipment and mains connection set is furnished with in fuselage, this aircraft flight attitude is handled by control system, airborne equipment comprises various flight instrumentation instrument and capture apparatus, and employing lithium cell is left motor, right motor, control system and airborne equipment are powered.Be configured with automatic navigation autonomous driving device or telecommand equipment, adopt automatic navigation autonomous driving mode or remote control mode flight.Left bat swing device and the right identical left and right sides being symmetrically arranged in fuselage of bat swing device structure and parameter.Empennage comprises tailplane and vertical tail, and tailplane is made up of the fixed part of leading portion and the moving part of horizontal stabilizer and back segment and elevating rudder, and vertical tail is made up of the fixed part of leading portion and the moving part of fixed fin and back segment and yaw rudder.Elevating rudder can deflect up and down under the manipulation of control system, upward deflects and this aircraft can be made to come back, realize facing upward; The downward bias change of team makes this aircraft bow, and realizes nutation.Yaw rudder is deflection under the manipulation of control system, and this aircraft can be made to go off course to the left or to the right.Bikini wheel undercarriage after alighting gear adopts.Facilitate left bat swing device and right bat swing device to flutter up and down flexibly in order to compact conformation, be provided with left side breach and right side breach in the left and right sides of fuselage respectively.
Left bat swing device comprises left motor, left main shaft, left swing arm, left wing's axle, left wing's sheet, left determine synchronizing wheel, left Timing Belt and a left side and move synchronizing wheel.Left wing's sheet is nonrigid, and left wing's sheet leading edge is perfectly round abundant, and trailing edge is tapering, and the part near leading edge is comparatively hard, and the part near trailing edge is softer.Left wing's plate plane shape is rectangular, and the aerofoil profile of left wing's sheet adopts flat pattern under epirelief concave shape or epirelief.Left wing sheet level is installed, and the rear end of left wing's axle is vertically fixed on the leading edge medium position of left wing's sheet, left wing's axle horizontal arrangement and with left main axis parallel.Left main shaft vertical equity is arranged, the leading portion of left main shaft is passed after the centre hole of synchronizing wheel is determined on a left side and is connected with fuselage by bearing, and the front end of left main shaft is connected with the output shaft of left motor, and the rear end of left main shaft is connected with fuselage by bearing.Left determine termination that synchronizing wheel determine synchronizing wheel by left and fuselage is fixed in the left side breach of fuselage, it is coaxial with the same height of left main shaft that synchronizing wheel is determined on a left side.One end of left swing arm is vertical with the stage casing of left main shaft to be fixed in the left side breach of fuselage, and the other end of left swing arm is by bearing and the vertical stage casing being connected in left wing's axle of left wing's axle.Left dynamic synchronizing wheel is connected in the front end of left wing's axle, and left dynamic synchronizing wheel determine synchronizing wheel with a left side and is connected by left Timing Belt, and the transmitting ratio that a left side determines synchronizing wheel and a left side to move synchronizing wheel is 1: 1.Left Timing Belt plane of movement is vertical with left main shaft.Left motor is fixedly mounted in the frame of fuselage, control system can to the rotating speed of left motor, to turn to and angle range controls.
Right bat swing device comprises right motor, right main shaft, right swing arm, right flank axle, right flank sheet, right determine synchronizing wheel, right Timing Belt and the right side and move synchronizing wheel.Right flank sheet is nonrigid, and the thick trailing edge of right flank sheet leading edge is thin, and the part near leading edge is comparatively hard, and the part near trailing edge is softer.Right flank plate plane shape is rectangular, and the aerofoil profile of right flank sheet adopts flat pattern under epirelief concave shape or epirelief.Right flank sheet level install, the rear end of right flank axle is vertically fixed on the leading edge medium position of right flank sheet, right flank axle horizontal arrangement and with right main axis parallel.Right main shaft vertical equity is arranged, the leading portion of right main shaft is passed after the centre hole of synchronizing wheel is determined on the right side and is connected with fuselage by bearing, and the front end of right main shaft is connected with the output shaft of right motor, and the rear end of right main shaft is connected with fuselage by bearing.Right determine termination that synchronizing wheel determine synchronizing wheel by right and fuselage is fixed in the right side breach of fuselage, it is coaxial with the same height of right main shaft that synchronizing wheel is determined on the right side.One end of right swing arm is vertical with the stage casing of right main shaft to be fixed in the right side breach of fuselage, and the other end of right swing arm is by the bearing stage casing that be connected in right flank axle vertical with right flank axle.Right dynamic synchronizing wheel is connected in the front end of right flank axle, and right dynamic synchronizing wheel determine synchronizing wheel with the right side and is connected by right Timing Belt, and the transmitting ratio that the right side determines synchronizing wheel and the right side to move synchronizing wheel is 1: 1.Right Timing Belt plane of movement is vertical with right main shaft.Right motor is fixedly mounted in the frame of fuselage, control system can to the rotating speed of right motor, to turn to and angle range controls.
From the tail end of this invention aircraft toward front end, the principle of work of right bat swing device is: under flutter process: suppose that reference position is that right flank sheet is in higher position, under the control of control system, start right motor to rotate clockwise, under the driving of right motor, right main shaft rotates clockwise, drive right swing arm rotates clockwise, the right side is determined synchronizing wheel and is maintained static, the transmitting ratio determining synchronizing wheel and the right side to move synchronizing wheel due to the right side is 1: 1, right Timing Belt drives right dynamic synchronizing wheel conter clockwise rotation, the leading edge of right flank sheet is kept to be horizontal lower bat, the displacement of clapping under the identical chord positions of spanwise right flank sheet is identical, realize flat bat downwards.Because right flank sheet is nonrigid, have certain flexibility and elasticity, when clapping under right flank sheet right flank sheet trailing edge want delayed right flank sheet leading edge some.Because the aerofoil profile of right flank sheet is flat pattern under epirelief concave shape or epirelief, claps under right flank sheet and produce larger lift upwards and less thrust forward.On the process of flutterring be: from right flank sheet is in lower position, control system controls right motor reversal, under the driving of right motor, right spindle axis counterclockwise rotation, drives right swing arm to rotate counterclockwise, the right side is determined synchronizing wheel and is maintained static, the transmitting ratio determining synchronizing wheel and the right side to move synchronizing wheel due to the right side is 1: 1, and right Timing Belt drives right dynamic synchronizing wheel to rotate clockwise, and keeps the leading edge of right flank sheet to be horizontal arsis, displacement along spanwise right flank sheet identical chord positions arsis is identical, realizes upwards flat bat.Because right flank sheet is nonrigid, have certain flexibility and elasticity, during right flank sheet arsis, the trailing edge of right flank sheet also can the leading edge of delayed right flank sheet.Because the aerofoil profile of right flank sheet is flat pattern under epirelief concave shape or epirelief, compared with lower bat, the degree of the leading edge of the trailing edge delayed right flank sheet of right flank sheet is larger.Arsis right flank sheet produces larger thrust forward and less lift upwards or does not produce lift, and the size that arsis process produces lift is relevant with the speed flown before this aircraft, and the lift that the front speed flown produces sooner is larger.The speed that right flank sheet is flapped and angular range being rotating speeds by controlling right motor, turning to and carrying out regulating with corner, and the scope of flapping is between 0 ° to 180 °.If on flutter and right swing arm gone to directly over right main shaft be in vertical position, under flutter and right swing arm gone to immediately below right main shaft be in vertical position, then the scope of fluttering is 180 °.
The principle of work of left bat swing device is identical with the principle of work of right bat swing device.The direction of flapping is symmetrical, and from the tail end of this invention aircraft toward front end, left spindle axis counterclockwise rotation, claps under left wing's sheet; Left main shaft rotates clockwise, left wing's sheet arsis.
Namely left wing's sheet and right flank sheet laterally can not produce horizontal component of force in spanwise in the process of flapping motion, and efficiency is higher.
The replaceable chaining type of drive of toothed belt transmission mode.Left bat swing device and right bat swing device independently separately control, left motor and right motor adopt servomotor, control ratio is more convenient, especially convenient flutter angular range and the speed of fluttering controlling left bat swing device and right bat swing device, makes this aircraft flight safety more flexibly.
Accompanying drawing explanation
Fig. 1 is the schematic rear view of a kind of flat bat fin flapping wing aircraft of the present invention, and in this figure, left bat swing device and right bat swing device are in down in the process of flutterring, and left wing's sheet and right flank sheet are in lower bat, and down, trailing edge upward for their leading edge; Fig. 2 is the schematic top plan view of Fig. 1; Fig. 3 is that schematic diagram is looked on a left side of Fig. 1; Fig. 4 is the schematic rear view that the left bat swing device of a kind of flat bat fin flapping wing aircraft of the present invention and right bat swing device are in when flutterring process, and in figure, left wing's sheet and right flank sheet are in arsis process, and upward, trailing edge down for their leading edge.
In figure, 1-fuselage, breach on the left of 11-, breach on the right side of 12-; 2-empennage, 21-tailplane, 22-vertical tail; The left bat swing device of 3-, the left motor of 31-, the left main shaft of 32-, 33-left swing arm, 34-left wing axle, 35-left wing sheet, the leading edge of 351-left wing sheet, the trailing edge of 352-left wing sheet, 36-determines synchronizing wheel in a left side, and 361-determines on a left side termination of synchronizing wheel, the left Timing Belt of 37-, the dynamic synchronizing wheel in a 38-left side; The right bat swing device of 4-, the right motor of 41-, the right main shaft of 42-, 43-right swing arm, 44-right flank axle, 45-right flank sheet, the leading edge of 451-right flank sheet, the trailing edge of 452-right flank sheet, 46-determines synchronizing wheel in the right side, and 461-determines on the right side termination of synchronizing wheel, the right Timing Belt of 47-, the dynamic synchronizing wheel in the 48-right side; 5-alighting gear.The longest path of motion that when the left bat swing device 3 of 341 expression is fluttered, left wing's axle 34 is possible; The longest path of motion that when the right bat swing device 4 of 441 expression is fluttered, right flank axle 44 is possible.
Detailed description of the invention
Now 1 ~ 4 couple of the present invention is illustrated by reference to the accompanying drawings: a kind of flat bat fin flapping wing aircraft, comprises fuselage 1, empennage 2, left bat swing device 3, right bat swing device 4 and alighting gear 5.Control system, airborne equipment and mains connection set is furnished with in fuselage 1, this aircraft flight attitude is handled by control system, airborne equipment comprises various flight instrumentation instrument and capture apparatus, adopts lithium cell to be that left motor 31, right motor 41 and other consumer are powered.Be configured with automatic navigation autonomous driving device in fuselage, adopt automatic navigation autonomous driving mode flight.Left bat swing device 3 and the right identical left and right sides being symmetrically arranged in fuselage 1 of bat swing device 4 structure and parameter.Empennage 2 comprises tailplane 21 and vertical tail 22, tailplane 21 is made up of the fixed part of leading portion and the moving part of horizontal stabilizer and back segment and elevating rudder, and vertical tail 22 is made up of the fixed part of leading portion and the moving part of fixed fin and back segment and yaw rudder.Elevating rudder can deflect up and down under the manipulation of control system, upward deflects and this aircraft can be made to come back, realize facing upward; The downward bias change of team makes this aircraft bow, and realizes nutation.Yaw rudder is deflection under the manipulation of control system, and this aircraft can be made to go off course to the left or to the right.Alighting gear 5 adopts rear bikini wheel undercarriage.Facilitate left bat swing device 3 and right bat swing device 4 to flutter up and down flexibly in order to compact conformation, be provided with left side breach 11 and right side breach 12 in the left and right sides of fuselage 1 respectively.
Left bat swing device 3 comprises left motor 31, left main shaft 32, left swing arm 33, left wing's axle 34, left wing's sheet 35, left determine synchronizing wheel 36, left Timing Belt 37 and a left side and move synchronizing wheel 38.Left wing's sheet 35 is nonrigid, and the leading edge 351 of left wing's sheet is perfectly round abundant, and trailing edge is tapering, and the trailing edge 352 of left wing's sheet is thinner, and the part near the leading edge 351 of left wing's sheet is comparatively hard, and the part near the trailing edge 352 of left wing's sheet is softer.Left wing's sheet 35 aspect is rectangular, and the aerofoil profile of left wing's sheet 35 adopts flat pattern under epirelief concave shape or epirelief.Left wing's sheet 35 level is installed, and the rear end of left wing's axle 34 is vertically fixed on leading edge 351 medium position of left wing's sheet, left wing's axle 34 horizontal arrangement and parallel with left main shaft 32.Left main shaft 32 vertical equity is arranged, the leading portion of left main shaft 32 is passed after the centre hole of synchronizing wheel 36 is determined on a left side and is connected with fuselage 1 by bearing, and the front end of left main shaft 32 is connected with the output shaft of left motor 31, and the rear end of left main shaft 32 is connected with fuselage 1 by bearing.A left side is determined synchronizing wheel 36 and is fixed in the left side breach 11 of fuselage 1 by left termination 361 of determining synchronizing wheel with fuselage 1, and it is same high coaxial with left main shaft 32 that synchronizing wheel 36 is determined on a left side.One end of left swing arm 33 is vertical with the stage casing of left main shaft 32 to be fixed in the left side breach 11 of fuselage 1, and the other end of left swing arm 33 is by bearing and the vertical stage casing being connected in left wing's axle 34 of left wing's axle 34.Left dynamic synchronizing wheel 38 is connected in the front end of left wing's axle 34, and left dynamic synchronizing wheel 38 and a left side determine synchronizing wheel 36 and are connected by left Timing Belt 37, and the transmitting ratio that a left side determines synchronizing wheel 36 and a left side to move synchronizing wheel 38 is 1: 1.Left Timing Belt 37 plane of movement is vertical with left main shaft 32.Left motor 31 is fixedly mounted in the frame of fuselage 1, control system can to the rotating speed of left motor 31, to turn to and angle range controls.
Right bat swing device 4 comprises right motor 41, right main shaft 42, right swing arm 43, right flank axle 44, right flank sheet 45, right determine synchronizing wheel 46, right Timing Belt 47 and the right side and move synchronizing wheel 48.Right flank sheet 45 is nonrigid, and the leading edge 451 of right flank sheet is thicker, and the trailing edge 452 of right flank sheet is thinner, and the part near the leading edge 451 of right flank sheet is comparatively hard, and the part near the trailing edge 452 of right flank sheet is softer.Right flank sheet 45 aspect is rectangular, and the aerofoil profile of right flank sheet 45 adopts flat pattern under epirelief concave shape or epirelief.Right flank sheet 45 level is installed, and the rear end of right flank axle 44 is vertically fixed on the leading edge medium position of right flank sheet 45, right flank axle 44 horizontal arrangement and parallel with right main shaft 42.Right main shaft 42 vertical equity is arranged, the leading portion of right main shaft 42 is passed after the centre hole of synchronizing wheel 46 is determined on the right side and is connected with fuselage 1 by bearing, and the front end of right main shaft 42 is connected with the output shaft of right motor 41, and the rear end of right main shaft 42 is connected with fuselage 1 by bearing.The right side is determined synchronizing wheel 46 and is fixed in the right side breach 12 of fuselage 1 by right termination 461 of determining synchronizing wheel with fuselage 1, and it is same high coaxial with right main shaft 42 that synchronizing wheel 46 is determined on the right side.One end of right swing arm 43 is vertical with the stage casing of right main shaft 42 to be fixed in the right side breach 12 of fuselage 1, and the other end of right swing arm 43 is by the bearing stage casing that be connected in right flank axle 44 vertical with right flank axle 44.Right dynamic synchronizing wheel 48 is connected in the front end of right flank axle 44, and right dynamic synchronizing wheel 48 and the right side determine synchronizing wheel 46 and are connected by right Timing Belt 47, and the transmitting ratio that the right side determines synchronizing wheel 46 and the right side to move synchronizing wheel 48 is 1: 1.Right Timing Belt 47 plane of movement is vertical with right main shaft 42.Right motor 41 is fixedly mounted in the frame of fuselage 1, control system can to the rotating speed of right motor 41, to turn to and angle range controls.
From the tail end of this invention aircraft toward front end, the principle of work of left bat swing device 3 is: under flutter process: suppose that reference position is the higher position of level attitude that left wing's sheet 35 is in higher than crossing left main shaft 32, under the control of control system, start left motor 31 to rotate counterclockwise, under the driving of left motor 31, left main shaft 32 rotates counterclockwise, left swing arm 33 is driven to rotate counterclockwise, a left side is determined synchronizing wheel 36 and is maintained static, the transmitting ratio determining synchronizing wheel 36 and a left side to move synchronizing wheel 38 due to a left side is 1: 1, left Timing Belt 37 drives left dynamic synchronizing wheel 38 to rotate clockwise, the leading edge of left wing's sheet 35 is kept to be horizontal lower bat, the displacement of clapping under the identical chord positions of spanwise left wing sheet 35 is identical, realize flat bat downwards.Because left wing's sheet 35 is nonrigid, have certain flexibility and elasticity, during left wing sheet 35 Xia Pai the trailing edge 452 of left wing's sheet 35 want delayed left wing sheet 35 leading edge 451 some.Because the aerofoil profile of left wing's sheet 35 is flat patterns under epirelief concave shape or epirelief, left wing's sheet is clapped for 35 times and is produced larger lift upwards and less thrust forward.On the process of flutterring be: from left wing's sheet 35 be in lower than cross left main shaft 32 level attitude lower position, control system controls left motor 31 and reverses, under the driving of left motor 31, left main shaft 32 rotates clockwise, left swing arm 33 is driven to rotate clockwise, a left side is determined synchronizing wheel 36 and is maintained static, the transmitting ratio determining synchronizing wheel 36 and a left side to move synchronizing wheel 38 due to a left side is 1: 1, left Timing Belt 37 drives left dynamic synchronizing wheel 38 conter clockwise rotation, the leading edge of left wing's sheet 35 is kept to be horizontal arsis, displacement along the identical chord positions arsis of spanwise left wing sheet 35 is identical, realize upwards flat bat.Because left wing's sheet 35 is nonrigid, have certain flexibility and elasticity, during left wing's sheet 35 arsis, the trailing edge of left wing's sheet 35 also can the leading edge of delayed left wing sheet 35.Because the aerofoil profile of left wing's sheet 35 is flat patterns under epirelief concave shape or epirelief, compared with lower bat, the degree of the leading edge 351 of the trailing edge 352 delayed left wing sheet of left wing's sheet is larger.Arsis left wing sheet 35 produces larger thrust forward and less lift upwards or does not produce lift, and the size that arsis process produces lift is relevant with the speed flown before this aircraft, and the lift that the front speed flown produces sooner is larger.The speed that left wing's sheet 35 is flapped and angular range being rotating speeds by controlling left motor 31, turning to and carrying out regulating with corner, and the scope of fluttering is between 0 ° to 180 °.If on flutter and left swing arm 33 gone to directly over left main shaft 32 be in vertical position, under flutter and left swing arm 33 gone to immediately below left main shaft 32 be in vertical position, then the scope of fluttering is 180 °.
The principle of work of right bat swing device 4 is identical with the principle of work of left bat swing device 3.The direction of flapping is symmetrical, and from the tail end of this invention aircraft toward front end, right main shaft 42 rotates clockwise, and right flank sheet is clapped for 45 times; Right main shaft 42 rotates counterclockwise, right flank sheet 45 arsis.
Namely left wing's sheet 35 and right flank sheet 45 laterally can not produce horizontal component of force in spanwise in the process of flapping motion, and efficiency is higher.
When load is heavier, the replaceable chaining type of drive of described toothed belt transmission mode, specifically be changed to: a left side is determined synchronizing wheel 36, left Timing Belt 37 and a left side and move corresponding being replaced with of synchronizing wheel 38 and left determine sprocket wheel, left chain and left movable sprocket, the transmitting ratio that sprocket wheel and left movable sprocket are determined in a left side is 1: 1; The right side is determined synchronizing wheel 46, right Timing Belt 47 and the right side to move corresponding being replaced with of synchronizing wheel 48 and right determine sprocket wheel, right chain and right movable sprocket, the transmitting ratio that sprocket wheel and right movable sprocket are determined in the right side is 1: 1.
Be furnished with pick up camera and information handling system in fuselage 1, can take photo by plane, the image information of shooting can be sent to wayside equipment.Machine can realize remote control distributor with this aircraft of telecommand equipment of ground configurations match.
This aircraft adopts hand mode of throwing take off or adopt the runway mode of sliding to take off; Left wing's sheet 35 and right flank sheet 45 are locked in the level attitude of the left main shaft of high mistake 32 or higher than the level attitude crossing left main shaft 32, facilitate this aircraft to glide or landing.
The present invention's one is flat claps that fin flapping wing aircraft can be used for taking photo by plane, geographical measurements, traffic duty, agrisilviculture, militaryly to investigate and the multiple-task such as rescue and relief work.
Claims (10)
1. a flat bat fin flapping wing aircraft, comprise fuselage (1), empennage (2), left bat swing device (3), right bat swing device (4) and alighting gear (5), it is characterized in that: fuselage is furnished with control system, airborne equipment and mains connection set in (1), is furnished with automatic navigation autonomous driving device or telecommand equipment; Left bat swing device (3) and the identical left and right sides being symmetrically arranged in fuselage (1) of right bat swing device (4) structure and parameter; Empennage (2) comprises tailplane (21) and vertical tail (22); The left and right sides of fuselage (1) is provided with left side breach (11) and right side breach (22) respectively; Left bat swing device (3) comprises left motor (31), left main shaft (32), left swing arm (33), left wing's axle (34), left wing's sheet (35), left determine synchronizing wheel (36), left Timing Belt (37) and a left side and move synchronizing wheel (38); Left wing's sheet (35) is nonrigid, and left wing's sheet (35) leading edge is perfectly round abundant, and trailing edge is tapering, and the part near leading edge is comparatively hard, and the part near trailing edge is softer; Left wing's sheet (35) aspect is rectangular, and the aerofoil profile of left wing's sheet (35) adopts flat pattern under epirelief concave shape or epirelief; Left wing's sheet (35) level is installed, and the rear end of left wing's axle (34) is vertically fixed on the leading edge medium position of left wing's sheet (35), left wing's axle (34) horizontal arrangement and parallel with left main shaft (32); Left main shaft (32) vertical equity is arranged, the leading portion of left main shaft (32) is passed after the centre hole of synchronizing wheel (36) is determined on a left side and is connected with fuselage (1) by bearing, the front end of left main shaft (32) is connected with the output shaft of left motor (31), and the rear end of left main shaft (32) is connected with fuselage (1) by bearing; A left side is determined synchronizing wheel (36) and is fixed in the left side breach (11) of fuselage (1) by left termination (361) of determining synchronizing wheel with fuselage (1), and it is same high coaxial with left main shaft (32) that synchronizing wheel (36) is determined on a left side; One end of left swing arm (33) is vertical with the stage casing of left main shaft (32) to be fixed in the left side breach (11) of fuselage (1), and the other end of left swing arm (33) is by the bearing stage casing that be connected in left wing axle (34) vertical with left wing's axle (34); Left dynamic synchronizing wheel (38) is connected in the front end of left wing's axle (34), and left dynamic synchronizing wheel (38) determine synchronizing wheel (36) with a left side and is connected by left Timing Belt (37), and the transmitting ratio that a left side determines synchronizing wheel (36) and a left side to move synchronizing wheel (38) is 1: 1; Left Timing Belt (37) plane of movement is vertical with left main shaft (32); Left motor (31) is fixedly mounted in the frame of fuselage (1), control system can to the rotating speed of left motor (31), turn to and control with angle range; Right bat swing device (4) comprises right motor (41), right main shaft (42), right swing arm (43), right flank axle (44), right flank sheet (45), right determine synchronizing wheel (46), right Timing Belt (47) and the right side and move synchronizing wheel (48); Right flank sheet (45) is nonrigid, and the thick trailing edge of right flank sheet (45) leading edge is thin, and the part near leading edge is comparatively hard, and the part near trailing edge is softer; Right flank sheet (45) aspect is rectangular, and the aerofoil profile of right flank sheet (45) adopts flat pattern under epirelief concave shape or epirelief; Right flank sheet (45) level is installed, and the rear end of right flank axle (44) is vertically fixed on the leading edge medium position of right flank sheet (45), right flank axle (44) horizontal arrangement and parallel with right main shaft (42); Right main shaft (42) vertical equity is arranged, the leading portion of right main shaft (42) is passed after the centre hole of synchronizing wheel (46) is determined on the right side and is connected with fuselage (1) by bearing, the front end of right main shaft (42) is connected with the output shaft of right motor (41), and the rear end of right main shaft (42) is connected with fuselage (1) by bearing; The right side is determined synchronizing wheel (46) and is fixed in the right side breach (12) of fuselage (1) by right termination (461) of determining synchronizing wheel with fuselage (1), and it is same high coaxial with right main shaft (42) that synchronizing wheel (46) is determined on the right side; One end of right swing arm (43) is vertical with the stage casing of right main shaft (42) to be fixed in the right side breach (12) of fuselage (1), and the other end of right swing arm (43) is by the bearing stage casing that be connected in right flank axle (44) vertical with right flank axle (42); Right dynamic synchronizing wheel (48) is connected in the front end of right flank axle (44), and right dynamic synchronizing wheel (48) determine synchronizing wheel (46) with the right side and is connected by right Timing Belt (47), and the transmitting ratio that the right side determines synchronizing wheel (46) and the right side to move synchronizing wheel (48) is 1: 1; Right Timing Belt (47) plane of movement is vertical with right main shaft (42); Right motor (41) is fixedly mounted in the frame of fuselage (1), control system can to the rotating speed of right motor (41), turn to and control with angle range; The speed that right flank sheet (45) is flapped and angular range being rotating speeds by controlling right motor (41), turning to and carrying out regulating with corner, and the scope of flapping is between 0 ° to 180 °; The principle of work of left bat swing device (3) is identical with the principle of work of right bat swing device (4), and the direction of flapping is symmetrical.
2. one according to claim 1 is flat claps fin flapping wing aircraft, it is characterized in that: employing lithium cell is left motor (31), right motor (32), control system and airborne equipment are powered.
3. one according to claim 1 is flat claps fin flapping wing aircraft, it is characterized in that: fuselage is furnished with pick up camera and information handling system in (1), the image information of shooting can be sent to wayside equipment.
4. one according to claim 1 is flat claps fin flapping wing aircraft, it is characterized in that: with the telecommand equipment of ground configurations match on machine.
5. one according to claim 1 is flat claps fin flapping wing aircraft, it is characterized in that: left wing's sheet (35) and right flank sheet (45) can be locked in the level attitude of the left main shaft of high mistake (32) or higher than the level attitude crossing left main shaft (32).
6. one according to claim 1 is flat claps fin flapping wing aircraft, it is characterized in that: bikini wheel undercarriage after alighting gear (5) adopts.
7. one according to claim 1 is flat claps fin flapping wing aircraft, it is characterized in that: left bat swing device (3) and the independent separately control of right bat swing device (4).
8. one according to claim 1 is flat claps fin flapping wing aircraft, it is characterized in that: left motor (31) and right motor (41) adopt servomotor.
9. one according to claim 1 is flat claps fin flapping wing aircraft, it is characterized in that: when toothed belt transmission mode is replaced with Chain conveyer mode, left determine synchronizing wheel (36), left Timing Belt (37) and a left side and move the corresponding left side that is replaced with of synchronizing wheel (38) and determine sprocket wheel, left chain and left movable sprocket, the transmitting ratio that sprocket wheel and left movable sprocket are determined in a left side is 1: 1; Right determine synchronizing wheel (46), right Timing Belt (47) and the right side and move the corresponding right side that is replaced with of synchronizing wheel (48) and determine sprocket wheel, right chain and right movable sprocket, the transmitting ratio that sprocket wheel and right movable sprocket are determined in the right side is 1: 1.
10. the one according to claim 1 or 9 is flat claps fin flapping wing aircraft, it is characterized in that: this aircraft adopts hand mode of throwing take off or adopt the runway mode of sliding to take off.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410769999.6A CN104477391B (en) | 2014-12-15 | 2014-12-15 | A kind of flat bat fin flapping wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410769999.6A CN104477391B (en) | 2014-12-15 | 2014-12-15 | A kind of flat bat fin flapping wing aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104477391A true CN104477391A (en) | 2015-04-01 |
| CN104477391B CN104477391B (en) | 2016-07-06 |
Family
ID=52752047
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410769999.6A Active CN104477391B (en) | 2014-12-15 | 2014-12-15 | A kind of flat bat fin flapping wing aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104477391B (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2008081094A (en) * | 2006-09-26 | 2008-04-10 | Bunri Gakuen | Ornithopter |
| FR2885116B1 (en) * | 2005-05-02 | 2009-01-02 | Daniel Abouassi | DEVICE FOR EQUIPPING A USER TO ENABLE IT TO MOVE INTO THE AIR |
| DE102007050427A1 (en) * | 2007-10-22 | 2009-04-23 | Sergei Afanassev | Swing airplane i.e. karura, has blade valves opened during rising of vane and closed during lowering of vane, where openings of valves realize engagement of large part of vane surface, and mechanism of drive of vane reduces lowering of vane |
| CN102874409A (en) * | 2012-10-30 | 2013-01-16 | 东南大学 | Flapping wing and turning device of micro aerial vehicle |
| CN103991549A (en) * | 2014-05-30 | 2014-08-20 | 佛山市神风航空科技有限公司 | High-intensity rotary ornithopter |
| CN204297087U (en) * | 2014-12-15 | 2015-04-29 | 佛山市神风航空科技有限公司 | A kind of flat bat fin flapping wing aircraft |
-
2014
- 2014-12-15 CN CN201410769999.6A patent/CN104477391B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2885116B1 (en) * | 2005-05-02 | 2009-01-02 | Daniel Abouassi | DEVICE FOR EQUIPPING A USER TO ENABLE IT TO MOVE INTO THE AIR |
| JP2008081094A (en) * | 2006-09-26 | 2008-04-10 | Bunri Gakuen | Ornithopter |
| DE102007050427A1 (en) * | 2007-10-22 | 2009-04-23 | Sergei Afanassev | Swing airplane i.e. karura, has blade valves opened during rising of vane and closed during lowering of vane, where openings of valves realize engagement of large part of vane surface, and mechanism of drive of vane reduces lowering of vane |
| CN102874409A (en) * | 2012-10-30 | 2013-01-16 | 东南大学 | Flapping wing and turning device of micro aerial vehicle |
| CN103991549A (en) * | 2014-05-30 | 2014-08-20 | 佛山市神风航空科技有限公司 | High-intensity rotary ornithopter |
| CN204297087U (en) * | 2014-12-15 | 2015-04-29 | 佛山市神风航空科技有限公司 | A kind of flat bat fin flapping wing aircraft |
Non-Patent Citations (1)
| Title |
|---|
| 颜幸尧等: "仿蝉翅膀气动力及扭矩特性的分析", 《浙江大学学报》 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104477391B (en) | 2016-07-06 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN205076045U (en) | Combined type aircraft of varistructure | |
| CN104443381B (en) | A kind of small-sized four wing flutter aircraft | |
| CN105129097A (en) | Unmanned aerial vehicle capable of taking off and landing vertically | |
| CN104477385B (en) | A kind of unmanned flapping wing aircraft | |
| Hayama et al. | Trial production of kite wing attached multicopter for power saving and long flight | |
| CN103991540A (en) | Conical rotary flapping wing aircraft | |
| CN102085911A (en) | Novel flight and aircraft | |
| CN106628115A (en) | Four-duct flying-wing type unmanned aerial vehicle | |
| CN204297088U (en) | A kind of single-shot double rocking lever is flat claps class flapping wing aircraft | |
| CN204310045U (en) | A kind of flat-type flapping wing aircraft with stepping motor | |
| CN103991549A (en) | High-intensity rotary ornithopter | |
| CN104477386A (en) | Single-engine, double-rocking-lever and flat-flapping flapping-wing aircraft | |
| CN203865000U (en) | Flying platform provided with four rotary flapping wings | |
| CN104002968B (en) | A kind of small taper rotary flapping wing aircraft | |
| CN204310049U (en) | A kind of dull and stereotyped fin flapping wing aircraft | |
| CN204297083U (en) | A kind of four fins are flat claps flapping wing aircraft | |
| CN204310048U (en) | A kind of unmanned flapping wing aircraft | |
| CN204297096U (en) | A kind of small-sized four wing flutter aircraft | |
| CN104494826B (en) | A kind of single-shot rotary flat claps class flapping wing aircraft | |
| CN104477389B (en) | A kind of miniature flutter aircraft | |
| CN204297087U (en) | A kind of flat bat fin flapping wing aircraft | |
| CN203864997U (en) | High-strength rotary flapping wing air vehicle | |
| CN204297084U (en) | A kind of single-shot rotary flat claps class flapping wing aircraft | |
| CN204297081U (en) | A kind of Minitype flat claps the unmanned flapping-wing aircraft of the wing | |
| CN104477388B (en) | A kind of four fins are flat claps flapping wing 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 | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20191225 Address after: 300000 No. 357, free trade road, Airport Economic Zone, Dongli District, Tianjin Patentee after: TIANJIN JINHANG INSTITUTE OF COMPUTING TECHNOLOGY 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 |