CN102862679B - Movable guide rod type reciprocating wing lifting force generation device - Google Patents
Movable guide rod type reciprocating wing lifting force generation device Download PDFInfo
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- CN102862679B CN102862679B CN201210341819.5A CN201210341819A CN102862679B CN 102862679 B CN102862679 B CN 102862679B CN 201210341819 A CN201210341819 A CN 201210341819A CN 102862679 B CN102862679 B CN 102862679B
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Abstract
The invention discloses a movable guide rod type reciprocating wing lifting force generation device and belongs to the technical field of an aircraft and a model thereof. The lifting force generation device comprises a crankshaft, a crankshaft front bearing, a crankshaft rear bearing, a connecting rod, a movable guide rod, a guide rod linear bearing, a reciprocating wing and a reciprocating wing driving shaft; and the connecting rod is connected with the crankshaft, the movable guide rod is connected with the connecting rod, the movable guide rod penetrates through the movable rod linear bearing to be arranged in the left-right direction, a run-through hole along the wingspan direction is arranged on the reciprocating wing, the reciprocating wing driving shaft penetrates through the run-through hole of the reciprocating wing, and a gap is arranged at the front edge end of the middle position of the reciprocating wing in the wingspan direction. The crankshaft is driven by power to rotate, so as to drive the movable guide rod to carry out reciprocating motion, and the reciprocating wing driving shaft drives the reciprocating wing to carry out reciprocating motion, so that the upward lifting force is generated. The movable guide rod type reciprocating wing lifting force generation device is simple in structure, convenient to operate and control, higher in efficiency and is used as the lifting device for an aircraft or a model thereof.
Description
Technical field
The reciprocal wing lift generating device of a kind of moving leader formula, relates to aircraft and modelling technique field thereof, can be widely used in the fields such as transport, military affairs, agriculture and forestry, sports and amusement and toy.
Background technology
The mankind thirst for driving simple, the safe and reliable and easy-to-operate aircraft of a kind of structure aloft freely circles in the air.
Traditional determine wing aircraft and produce lift by fixed-wing when having when relative velocity with air, although handle simple, can not vertical takeoff and landing, hovering and after fly, require high to landing site, need longer and smooth runway; Although traditional helicopter can vertical takeoff and landing, but front when flying the blade one side of main rotor rotate one side and advance together with body, the synthesis of these two kinds motions, make the relative air speed of blade left and right sides in plane of rotation asymmetric, lean on main rotor flapping action to balance, handle and trim all more difficult, its complex structure, operation manoevreability and safety not high.
Summary of the invention
The object of the invention is for overcoming above-mentioned the deficiencies in the prior art, providing that a kind of structure is simple, control comfort and the reciprocal wing lift generating device of moving leader formula of safety flexibly.
The technical solution used in the present invention is: comprise bent axle, crankshaft front bearing, crankshaft rear bearing, connecting rod, moving leader, guide rod linear bearing, the back and forth wing and reciprocal wing axle drive shaft, bent axle is arranged on fuselage by crankshaft front bearing and crankshaft rear bearing, be arranged in same level before and after crankshaft front bearing and crankshaft rear bearing, the left end of connecting rod is connected with bent axle, the right-hand member of connecting rod is connected with the left end of moving leader, moving leader is arranged through the guide rod linear bearing left and right directions be fixedly mounted on fuselage side wall, the right-hand member of moving leader on the right side of guide rod linear bearing, moving leader can in guide rod linear bearing flexible left and right reciprocating translatory, the reciprocal wing is rigidity, adopts the aerofoil profile of symmetric figure, and have one along the through hole of spanwise near the leading edge place of the reciprocal wing, through hole is as far as possible near leading edge, reciprocal wing axle drive shaft is through the through hole of the reciprocal wing, the leading edge of the reciprocal wing is above reciprocal wing axle drive shaft, the trailing edge of the reciprocal wing is in the below of reciprocal wing axle drive shaft, reciprocal wing axle drive shaft intersects with moving leader " ten " word and is connected, reciprocal wing axle drive shaft is on the right side of guide rod linear bearing, reciprocal wing axle drive shaft and moving leader orthogonal, reciprocal wing axle drive shaft and moving leader were in the horizontal surface of crankshaft front bearing, before and after reciprocal wing spanwise relative movement guide rod, both sides are symmetrical, reciprocal wing acies before the midway location of spanwise has breach, similar " V " font of shape of breach, the effect of this breach is convenient to the reciprocal wing around the reciprocal wing axle drive shaft energy angle that switch is certain flexibly, breach is a bit larger tham the diameter of moving leader along the width of spanwise, the minimum angle of attack when degree of depth of breach chordwise determines that the reciprocal wing runs, under the restriction of the moving leader of the reciprocal wing axle drive shaft left and right sides, the reciprocal wing can obtain larger 1ift-drag ratio thus obtain larger lift and higher efficiency, the reciprocal wing can not move at the axis direction of reciprocal wing axle drive shaft.
In order to be limited in lift effect under moving leader K/UP, at the identical front rack of the front and back bilateral symmetry mounting structure of moving leader and tail-bracket, front rack is made up of front top rod, front trough of belt cross bar and front lower link, and tail-bracket is made up of rear top rod, rear trough of belt cross bar and rear lower link, backwards, the notch of rear trough of belt cross bar forward for the notch of front trough of belt cross bar, horizontal arrangement is in left and right directions on the front for front trough of belt cross bar, and left end and the fuselage outer side of front trough of belt cross bar are connected, and limit horizontal arrangement is in left and right directions rearward for rear trough of belt cross bar, and left end and the fuselage outer side of rear trough of belt cross bar are connected, front trough of belt cross bar and rear trough of belt cross bar are all vertical with reciprocal wing axle drive shaft, and three is in same level, in the rear and front end of reciprocal wing axle drive shaft, symmetry is installed with axle drive shaft front end slide block and axle drive shaft rear end slide block respectively, axle drive shaft front end slide block and axle drive shaft rear end slide block are placed in the smooth groove of front trough of belt cross bar and rear trough of belt cross bar respectively, and axle drive shaft front end slide block and axle drive shaft rear end slide block can along with reciprocal wing axle drive shaft horizontally slip in the groove of front trough of belt cross bar and rear trough of belt cross bar, the composition front top rod of front rack and front lower link and front trough of belt cross bar are in same perpendicular, front top rod and front lower link are arranged in the both sides up and down of front trough of belt cross bar respectively, front top rod is that upper left side is tiltedly arranged to lower right, the upper end of front top rod is connected with fuselage side wall above front trough of belt cross bar, the lower end of front top rod is connected with the right-hand member of front trough of belt cross bar, front lower link is that lower left is tiltedly arranged to upper right side, the lower end of front lower link is connected in the below of front trough of belt cross bar and fuselage side wall, and the upper end of front lower link is connected with the right-hand member of front trough of belt cross bar, the composition rear top rod of tail-bracket and rear lower link and rear trough of belt cross bar are also in same perpendicular, rear top rod and rear lower link are arranged in the both sides up and down of rear trough of belt cross bar respectively, rear top rod is that upper left side is tiltedly arranged to lower right, the upper end of rear top rod is connected with fuselage side wall above rear trough of belt cross bar, the lower end of rear top rod is connected with the right-hand member of rear trough of belt cross bar, rear lower link is that lower left is tiltedly arranged to upper right side, the lower end of rear lower link is connected in the below of rear trough of belt cross bar and fuselage side wall, the upper end of rear lower link is connected with the right-hand member of rear trough of belt cross bar.
For guaranteeing higher efficiency and larger lift, and consider scantling of structure and structural strength, the aspect ratio span of the reciprocal wing is between 4 to 14, when the aspect ratio of the reciprocal wing is x, the ratio of the chord length toward complex magnitude and the reciprocal wing of the rotating diameter of bent axle and the reciprocal wing is called for short width string ratio and controls between 4 to (x+1).
In order to reduce the friction of the reciprocal wing around the reciprocal switch of reciprocal wing axle drive shaft, be connected by bearing between the reciprocal wing with reciprocal wing axle drive shaft.
Crank rotation under the driving of power, moving leader is driven to do left and right reciprocating translatory by connecting rod, reciprocal wing axle drive shaft drives the reciprocal wing to do bilateral reciprocation, and in reciprocatory movement, the reciprocal wing is except drawing the effect of pushing away outer also by the restriction of the effects such as own gravity, inertia and air resistance and moving leader by reciprocal wing axle drive shaft.A reciprocation period can be divided into two processes, process one: back and forth wing axle drive shaft runs to the process of high order end from low order end, the speed of this process reciprocal wing axle drive shaft accelerates to maximum from zero and then decelerates to zero, because the through hole of the reciprocal wing is near leading edge, and trailing edge is in the below of reciprocal wing axle drive shaft, when the speed of reciprocal wing axle drive shaft translation is left enough fast, turn right switch in the bottom of the reciprocal wing relatively back and forth wing axle drive shaft, by the restriction of the moving leader on the right of reciprocal wing axle drive shaft, in this process except reciprocal wing axle drive shaft be in low order end and high order end and they near except, moving leader on the right of the reciprocal wing axle drive shaft of the tight note of the reciprocal wing, the reciprocal wing keeps the positive angle of attack relative to left incoming flow, the reciprocal wing produces lift upwards, process two: back and forth wing axle drive shaft runs to the process of low order end from high order end, the speed of this process reciprocal wing axle drive shaft accelerates to from zero and maximumly then decelerates to zero, because the through hole of the reciprocal wing is near leading edge, and trailing edge is in the below of reciprocal wing axle drive shaft, when the speed of reciprocal wing axle drive shaft translation is to the right enough fast, turn left switch in the bottom of the reciprocal wing relatively back and forth wing axle drive shaft, by the restriction of the moving leader on the reciprocal wing axle drive shaft left side, in this process except reciprocal wing axle drive shaft be in high order end and low order end and they near except, the moving leader on the tight note of the reciprocal wing reciprocal wing axle drive shaft left side, the reciprocal wing keeps the positive angle of attack relative to right incoming flow, the reciprocal wing also produces lift upwards.Reciprocal wing left and right like this faster reciprocal motion, this device can produce larger lift, and the size of lift becomes relationships of increase function with the quadratic power of crankshaft rotating speed.Due to the existence of front rack and tail-bracket, the axle drive shaft front end slide block of the rear and front end of reciprocal wing axle drive shaft and axle drive shaft rear end slide block slide in the groove of front trough of belt cross bar and rear trough of belt cross bar, and moving leader can not bend.This plant efficiency is higher, and structure is simple, safe and reliable.
Accompanying drawing explanation
Fig. 1: a kind of moving leader formula reciprocal wing lift generating device structural representation back view;
Fig. 2: a kind of moving leader formula reciprocal wing lift generating device structural representation birds-eye view;
Fig. 3: the moving leader on the right of the reciprocal wing axle drive shaft of the tight note of the reciprocal wing of a kind of moving leader formula reciprocal wing lift generating device is to the schematic rear view of left movement;
Fig. 4: the schematic rear view that the moving leader on the tight note of the reciprocal wing reciprocal wing axle drive shaft left side of a kind of moving leader formula reciprocal wing lift generating device moves right;
Fig. 5: schematic diagram is looked on a left side for the reciprocal wing after the amplification of a kind of moving leader formula reciprocal wing lift generating device;
The A-A section-drawing of Fig. 6: Fig. 5;
The B-B section-drawing of Fig. 7: Fig. 5.
Wherein, the rotation direction of the arc representation bent axle 1 of left side band arrow in Fig. 1, the straight line of the two band arrows on the right represents the vibration-direction of moving leader 3; In Fig. 2, the elliptic arc of the band arrow of lower left represents the rotation direction of bent axle 1, and the straight line of the two band arrows on the right represents the vibration-direction of moving leader 3; Straight line with arrow in Fig. 3 represents the sense of motion of moving leader 3; Straight line with arrow in Fig. 4 represents the sense of motion of moving leader 3.
Detailed description of the invention
Provide embodiments of the present invention example below, and 1 ~ 7 be illustrated by reference to the accompanying drawings.
As shown in the figure, the reciprocal wing lift generating device of a kind of moving leader formula of the present invention comprises bent axle 1, crankshaft front bearing 11, crankshaft rear bearing 12, connecting rod 2, moving leader 3, guide rod linear bearing 31, the back and forth wing 4 and reciprocal wing axle drive shaft 5, bent axle 1 is arranged on fuselage by crankshaft front bearing 11 and crankshaft rear bearing 12, be arranged in same level before and after crankshaft front bearing 11 and crankshaft rear bearing 12, the left end of connecting rod 2 is connected with bent axle 1, the right-hand member of connecting rod 2 is connected with the left end of moving leader 3, moving leader 3 is arranged through guide rod linear bearing 31 left and right directions be fixedly mounted on fuselage side wall, the right-hand member of moving leader 3 on the right side of guide rod linear bearing 31, moving leader 3 can in guide rod linear bearing 31 flexible left and right reciprocating translatory, the reciprocal wing 4 is rigidity, adopts the aerofoil profile of symmetric figure, and have one along the through hole of spanwise near the leading edge place of the reciprocal wing 4, through hole is as far as possible near leading edge, reciprocal wing axle drive shaft 5 is through the through hole of the reciprocal wing 4, the leading edge of the reciprocal wing 4 is above reciprocal wing axle drive shaft 5, the trailing edge of the reciprocal wing 4 is in the below of reciprocal wing axle drive shaft 5, reciprocal wing axle drive shaft 5 intersects with moving leader 3 " ten " word and is connected, reciprocal wing axle drive shaft 5 is on the right side of guide rod linear bearing 31, reciprocal wing axle drive shaft 5 is orthogonal with moving leader 3, and reciprocal wing axle drive shaft 5 and moving leader 3 were in the horizontal surface of crankshaft front bearing 31, before and after the reciprocal wing 4 spanwise relative movement guide rod 3, both sides are symmetrical, the reciprocal wing 4 acies before the midway location of spanwise has breach, similar " V " font of shape of breach, the effect of this breach is convenient to the reciprocal wing 4 around the reciprocal wing axle drive shaft 5 energy angle that switch is certain flexibly, breach is a bit larger tham the diameter of moving leader 3 along the width of spanwise, the minimum angle of attack when degree of depth of breach chordwise determines that the reciprocal wing 4 runs, under the restriction of the moving leader 3 of reciprocal wing axle drive shaft 5 left and right sides, the reciprocal wing 4 can obtain larger 1ift-drag ratio thus obtain larger lift and higher efficiency, the reciprocal wing 4 can not move at the axis direction of reciprocal wing axle drive shaft 5.
In order to be limited in lift effect under moving leader 3 K/UP, at the identical front rack 8 of the front and back bilateral symmetry mounting structure of moving leader 3 and tail-bracket 9, front rack 8 is made up of front top rod 81, front trough of belt cross bar 82 and front lower link, and tail-bracket 9 is made up of rear top rod 91, rear trough of belt cross bar 92 and rear lower link 93, backwards, the notch of rear trough of belt cross bar 92 forward for the notch of front trough of belt cross bar 82, horizontal arrangement is in left and right directions on the front for front trough of belt cross bar 82, and left end and the fuselage outer side of front trough of belt cross bar 82 are connected, and limit horizontal arrangement is in left and right directions rearward for rear trough of belt cross bar 92, and left end and the fuselage outer side of rear trough of belt cross bar 92 are connected, front trough of belt cross bar 82 and rear trough of belt cross bar 92 are all vertical with reciprocal wing axle drive shaft 5, and three is in same level, in the rear and front end of reciprocal wing axle drive shaft 5, symmetry is installed with axle drive shaft front end slide block 6 and axle drive shaft rear end slide block 7 respectively, axle drive shaft front end slide block 6 and axle drive shaft rear end slide block 7 are placed in the smooth groove of front trough of belt cross bar 82 and rear trough of belt cross bar 92 respectively, and axle drive shaft front end slide block 6 and axle drive shaft rear end slide block 7 can along with reciprocal wing axle drive shaft 5 horizontally slip in the groove of front trough of belt cross bar 82 and rear trough of belt cross bar 92, the composition front top rod 81 of front rack 8 and front lower link and front trough of belt cross bar 82 are in same perpendicular, front top rod 81 and front lower link are arranged in the both sides up and down of front trough of belt cross bar 82 respectively, front top rod 81 is that upper left side is tiltedly arranged to lower right, the upper end of front top rod 81 is connected with fuselage side wall above front trough of belt cross bar 82, the lower end of front top rod 81 is connected with the right-hand member of front trough of belt cross bar 82, front lower link is that lower left is tiltedly arranged to upper right side, the lower end of front lower link is connected in the below of front trough of belt cross bar 82 and fuselage side wall, the upper end of front lower link is connected with the right-hand member of front trough of belt cross bar 82, rear top rod 91 and the rear lower link 93 of composition tail-bracket 9 are also in same perpendicular with rear trough of belt cross bar 92, rear top rod 91 and rear lower link 93 are arranged in the both sides up and down of rear trough of belt cross bar 92 respectively, rear top rod is that upper left side is tiltedly arranged to lower right, the upper end of rear top rod is connected with fuselage side wall above rear trough of belt cross bar, the lower end of rear top rod 91 is connected with the right-hand member of rear trough of belt cross bar 92, rear lower link 93 is that lower left is tiltedly arranged to upper right side, the lower end of rear lower link 93 is connected in the below of rear trough of belt cross bar 92 and fuselage side wall, the upper end of rear lower link 93 is connected with the right-hand member of rear trough of belt cross bar 92.
For guaranteeing higher efficiency and larger lift, and consider scantling of structure and structural strength, the aspect ratio span of the reciprocal wing 4 is between 4 to 14, when the aspect ratio of the reciprocal wing 4 is x, the ratio of the chord length toward complex magnitude and the reciprocal wing 4 of the rotating diameter of bent axle 1 and the reciprocal wing 4 is called for short width string ratio and controls between 4 to (x+1).Such as: when back and forth the aspect ratio of the wing 4 is 4, width string ratio is got between 4 to 5; When the aspect ratio of the reciprocal wing 4 is 8, width string ratio is got between 4 to 9; When the aspect ratio of the reciprocal wing 4 is 14, width string ratio is got between 4 to 15.
In order to reduce the friction of the reciprocal wing 4 around the reciprocal switch of reciprocal wing axle drive shaft 5, be connected by bearing between the reciprocal wing 4 with reciprocal wing axle drive shaft 5.
The minimum angle of attack when degree of depth because of the reciprocal wing 4 breach chordwise determines that the reciprocal wing 4 runs, in order to obtain larger lift and higher efficiency, choose the reciprocal wing 4 1ift-drag ratio close to angle of attack during maximum and not stall as this minimum angle of attack, determine the degree of depth and the shape of the reciprocal wing 4 breach chordwise thus.When the aerofoil profile of the reciprocal wing 4 is determined, by wind tunnel test or consult available data document and can obtain the reciprocal wing 4 1ift-drag ratio with the relation of the angle of attack.
The principle of work of the reciprocal wing lift generating device of a kind of moving leader of the present invention formula is: under the driving of power, bent axle 1 rotates, moving leader 3 is driven to do left and right reciprocating translatory by connecting rod 2, reciprocal wing axle drive shaft 5 drives the reciprocal wing 4 to do bilateral reciprocation, and in reciprocatory movement, the reciprocal wing 4 is except drawing the effect of pushing away outer also by the restriction of the effects such as own gravity, inertia and air resistance and moving leader 3 by reciprocal wing axle drive shaft 5.A reciprocation period can be divided into two processes, process one: back and forth wing axle drive shaft 5 runs to the process of high order end from low order end, the speed of this process reciprocal wing axle drive shaft 5 accelerates to maximum from zero and then decelerates to zero, because the through hole of the reciprocal wing 4 is near leading edge, and trailing edge is in the below of reciprocal wing axle drive shaft 5, when the speed of reciprocal wing axle drive shaft 5 translation is left enough fast, turn right switch in the bottom of the reciprocal wing 4 relatively back and forth wing axle drive shaft 5, by the restriction of the moving leader 3 on the right of reciprocal wing axle drive shaft 5, in this process except reciprocal wing axle drive shaft 5 be in low order end and high order end and they near except, moving leader 3 on the right of the tight reciprocal wing axle drive shaft 5 of note of the reciprocal wing 4, the reciprocal wing 4 relatively left incoming flow keeps the positive angle of attack, the reciprocal wing 4 produces lift upwards, process two: back and forth wing axle drive shaft 5 runs to the process of low order end from high order end, the speed of this process reciprocal wing axle drive shaft 5 accelerates to from zero and maximumly then decelerates to zero, because the through hole of the reciprocal wing 4 is near leading edge, and trailing edge is in the below of reciprocal wing axle drive shaft 5, when the speed of reciprocal wing axle drive shaft 5 translation is to the right enough fast, turn left switch in the bottom of the reciprocal wing 4 relatively back and forth wing axle drive shaft 5, by the restriction of the moving leader 3 on reciprocal wing axle drive shaft 5 left side, in this process except reciprocal wing axle drive shaft 5 be in high order end and low order end and they near except, the moving leader 3 on tight note reciprocal wing axle drive shaft 5 left side of the reciprocal wing 4, the reciprocal wing 4 relatively right incoming flow keeps the positive angle of attack, the reciprocal wing 4 also produces lift upwards.The reciprocal wing 4 is left and right faster reciprocal motion so, and this device can produce larger lift, and the size of lift becomes relationships of increase function with the quadratic power of bent axle 1 rotating speed.Due to the existence of front rack 8 and tail-bracket 9, the axle drive shaft front end slide block 6 of the rear and front end of reciprocal wing axle drive shaft 5 and axle drive shaft rear end slide block 7 slide in the groove of front trough of belt cross bar 82 and rear trough of belt cross bar 92, and moving leader 3 can not bend.
This moving leader formula of simple declaration reciprocal wing lift generating device of illustrating below is used in the situation on reciprocal rotor aircraft:
Example 1, apparatus of the present invention that use two structures are identical, from reciprocal rotor aircraft dead aft toward dead ahead, two devices are symmetrically arranged in the fuselage left and right sides of reciprocal rotor aircraft, the bent axle of stream oriented device is inner, the reciprocal wing is outer, the reciprocal wing axle drive shaft of stream oriented device is in same level, and stream oriented device all produces lift upwards under the driving of power.Stream oriented device can drive in synchronous interaction, also can individual drive, and maneuvering performance is good.Because the reciprocal wing is arranged on the fuselage left and right sides, convenient at reciprocal rotor aircraft top installation parachute, improve safety, this is that traditional helicopter is not accomplished.
Example 2, apparatus of the present invention matrix that use four structures are identical are arranged in the surrounding of same reciprocal rotor aircraft, form a flying platform, four devices are symmetrical between two, the all inner geometric centre close to reciprocal rotor aircraft of bent axle of four devices, their all outer geometric centre away from reciprocal rotor aircraft of the reciprocal wing, the reciprocal wing axle drive shaft of four devices is in same level, four device individual drive, can by the flight attitude regulating the reciprocating frequence of four devices to handle this reciprocal rotor aircraft, maneuvering performance is good.
Claims (6)
1. the reciprocal wing lift generating device of moving leader formula, comprise bent axle (1), crankshaft front bearing (11), crankshaft rear bearing (12), connecting rod (2), moving leader (3), guide rod linear bearing (31), the reciprocal wing (4) and reciprocal wing axle drive shaft (5), it is characterized in that: bent axle (1) is arranged on fuselage by crankshaft front bearing (11) and crankshaft rear bearing (12), be arranged in same level before and after crankshaft front bearing (11) and crankshaft rear bearing (12), the left end of connecting rod (2) is connected with bent axle (1), the right-hand member of connecting rod (2) is connected with the left end of moving leader (3), moving leader (3) is arranged through guide rod linear bearing (31) left and right directions be fixedly mounted on fuselage side wall, the upper leading edge place near the reciprocal wing (4) of the reciprocal wing (4) has one along the through hole of spanwise, reciprocal wing axle drive shaft (5) is through this through hole, the leading edge of the reciprocal wing (4) is in the top of reciprocal wing axle drive shaft (5), the trailing edge of the reciprocal wing (4) is in the below of reciprocal wing axle drive shaft (5), reciprocal wing axle drive shaft (5) is intersected with moving leader (3) " ten " word and is connected, reciprocal wing axle drive shaft (5) is on the right side of guide rod linear bearing (31), reciprocal wing axle drive shaft (5) is orthogonal with moving leader (3), reciprocal wing axle drive shaft (5) and moving leader (3) were in the horizontal surface of crankshaft front bearing (31), the reciprocal wing (4) acies before the midway location of spanwise has breach, at the identical front rack (8) of the front and back bilateral symmetry mounting structure of moving leader (3) and tail-bracket (9), front rack (8) is made up of front top rod (81), front trough of belt cross bar (82) and front lower link, and tail-bracket (9) is made up of rear top rod (91), rear trough of belt cross bar (92) and rear lower link (93), backwards, the notch of rear trough of belt cross bar (92) forward for the notch of front trough of belt cross bar (82), front trough of belt cross bar (82) on the front horizontal arrangement in left and right directions, left end and the fuselage outer side of front trough of belt cross bar (82) are connected, limit horizontal arrangement is in left and right directions rearward for rear trough of belt cross bar (92), and left end and the fuselage outer side of rear trough of belt cross bar (92) are connected, front trough of belt cross bar (82) and rear trough of belt cross bar (92) are all vertical with reciprocal wing axle drive shaft (5), and three is in same level, in the rear and front end of reciprocal wing axle drive shaft (5), symmetry is installed with axle drive shaft front end slide block (6) and axle drive shaft rear end slide block (7) respectively, and axle drive shaft front end slide block (6) and axle drive shaft rear end slide block (7) are placed in the smooth groove of front trough of belt cross bar (82) and rear trough of belt cross bar (92) respectively, front top rod (81) and front lower link and the front trough of belt cross bar (82) of composition front rack (8) are in same perpendicular, the rear top rod (91) of composition tail-bracket (9) and rear lower link (93) are also in same perpendicular with rear trough of belt cross bar (92).
2. the reciprocal wing lift generating device of a kind of moving leader formula according to claim 1, is characterized in that: back and forth the degree of depth of the wing (4) breach chordwise and the shape minimum angle of attack met when the reciprocal wing (4) runs are the reciprocal wing (4) 1ift-drag ratio close to angle of attack during maximum and not stall.
3. the reciprocal wing lift generating device of a kind of moving leader formula according to claim 1, is characterized in that: its reciprocal wing (4) is connected by bearing with between reciprocal wing axle drive shaft (5).
4. the reciprocal wing lift generating device of a kind of moving leader formula according to claim 1 or 2 or 3, is characterized in that: its reciprocal wing (4) is rigidity, adopts the aerofoil profile of symmetric figure; The aspect ratio span of the reciprocal wing (4) is between 4 to 14, when the aspect ratio of the reciprocal wing (4) is x, the Ratio control of the chord length toward complex magnitude and the reciprocal wing (4) of the rotating diameter of bent axle (1) and the reciprocal wing (4) is between 4 to x+1.
5. the reciprocal wing lift generating device of a kind of moving leader formula according to claim 1 or 2 or 3, it is characterized in that: when using two these devices on same reciprocal rotor aircraft, the device that two structures are identical is symmetrically arranged in the fuselage left and right sides of reciprocal rotor aircraft, the bent axle (1) of stream oriented device is inner, the reciprocal wing (4) is outer, the reciprocal wing axle drive shaft (5) of stream oriented device is in same level, stream oriented device synchronous interaction driving or individual drive.
6. the reciprocal wing lift generating device of a kind of moving leader formula according to claim 1 or 2 or 3, it is characterized in that: when using four these devices on same reciprocal rotor aircraft, their matrixes are arranged in the surrounding of reciprocal rotor aircraft, form a flying platform, four devices are symmetrical between two, the all inner geometric centre close to reciprocal rotor aircraft of bent axle (1) of four devices, their all outer geometric centre away from reciprocal rotor aircraft of the reciprocal wing (4), the reciprocal wing axle drive shaft (5) of four devices is in same level, four device individual drive.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210341819.5A CN102862679B (en) | 2012-09-02 | 2012-09-02 | Movable guide rod type reciprocating wing lifting force generation device |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201210341819.5A CN102862679B (en) | 2012-09-02 | 2012-09-02 | Movable guide rod type reciprocating wing lifting force generation device |
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| CN102862679A CN102862679A (en) | 2013-01-09 |
| CN102862679B true CN102862679B (en) | 2015-03-11 |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB190901528A (en) * | 1908-02-10 | 1909-04-15 | Friedrich Kopsch | Improvements in Flying Machines. |
| CN2551303Y (en) * | 2002-04-30 | 2003-05-21 | 孙波 | Flutter mechanism for toy ornithopter |
| CN101249889A (en) * | 2008-03-29 | 2008-08-27 | 王志成 | Plate blade thrusting unit for flying vehicle |
| CN101537883A (en) * | 2008-03-17 | 2009-09-23 | 王志成 | High-efficiency flapping wing device |
| CN202765291U (en) * | 2012-08-30 | 2013-03-06 | 华南理工大学 | Insect aircraft imitating flapping wing mechanism |
-
2012
- 2012-09-02 CN CN201210341819.5A patent/CN102862679B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB190901528A (en) * | 1908-02-10 | 1909-04-15 | Friedrich Kopsch | Improvements in Flying Machines. |
| CN2551303Y (en) * | 2002-04-30 | 2003-05-21 | 孙波 | Flutter mechanism for toy ornithopter |
| CN101537883A (en) * | 2008-03-17 | 2009-09-23 | 王志成 | High-efficiency flapping wing device |
| CN101249889A (en) * | 2008-03-29 | 2008-08-27 | 王志成 | Plate blade thrusting unit for flying vehicle |
| CN202765291U (en) * | 2012-08-30 | 2013-03-06 | 华南理工大学 | Insect aircraft imitating flapping wing mechanism |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102862679A (en) | 2013-01-09 |
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