CN2213118Y - Mixed ornithopter - Google Patents
Mixed ornithopter Download PDFInfo
- Publication number
- CN2213118Y CN2213118Y CN 94221317 CN94221317U CN2213118Y CN 2213118 Y CN2213118 Y CN 2213118Y CN 94221317 CN94221317 CN 94221317 CN 94221317 U CN94221317 U CN 94221317U CN 2213118 Y CN2213118 Y CN 2213118Y
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- Prior art keywords
- wing
- axle
- sleeve pipe
- movable
- fuselage
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- Expired - Fee Related
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Abstract
The utility model relates to a mixed ornithopter, belonging to a light aircraft. The utility model is provided with fixed wings and movable wings. The utility model has the proposal that plane turning angle and amplitude of fluctuation of the movable wings are equally controlled by transmission mechanisms; when a motor works, the movable wings are driven to swing up and down by a crankshaft connecting rod; wing planes can be turned simultaneously by controlling the turning angle of a wing root shaft in an annular groove, and the amplitude of fluctuation and the turning angle can be equally adjusted. The utility model solves the problem that the air resistance is large and the turning is inflexible when the existing aircraft is driven to turn the wing planes by airflow, so the running distance of taking off and landing is less than 10 meters. The utility model is particularly suitable for patrol, travel, traffic, fireproof, reconnaissance, agriculture, photographic flight, etc.
Description
The utility model belongs to the light aircraft device, particularly a kind of flapping wings type blimp.
The upset of existing flapping-wing aircraft wing is the passive upset of effect of air-flow when utilizing the pendulum on the wing or the bottom, can not carry out manual shift to adapt to the requirement of flying, especially its safety performance is very poor under wind direction variation or high wind situation, the both sides, front and back of its wing adopt different materials (the place ahead is a rigid material, and the back is a flexible material) also to cause its aerodynamic performance undesirable.The wing machine of more pattern relies on yaw rudder to turn to when turning, and the Yang Yi amplitude of fluctuation of both sides is identical simultaneously, and fuselage is inclined in opposite directions very easily, also influences safety.
To provide a kind of in the purpose of this utility model and turn flexibly, its propulsive force and lift ratio rationally and can improve the flapping-wing aircraft of its safety.
Realize that the technical scheme that above-mentioned purpose adopted is:
Flapping-wing aircraft is designed to hybrid whole wing, promptly has a pair of movable wing and a pair of fixed-wing, and this movable wing rear on fixed-wing has the transmission device of its planar inverted angle of control and controls its amplitude of fluctuation to realize the transmission device of turning action.
The mechanism of control movable wing planar inverted angle be included in that the fuselage bilateral symmetry installs respectively with both sides before and after triangle crossbeam two umbrella stulls that link, its underpart links to each other with connecting rod, the umbrella stull top has the bearing that the wing root axle is installed, its opening end and ring looping groove, one circle ebonite roller is housed in the groove, the wing root of movable wing also links with rotating disk, this rotating disk is installed in the circular groove and by above-mentioned rubber roll and is adjacent to, rotating disk has internally toothed annulus, this internally toothed annulus is meshed with gear, gear and gear are with being contained on the axle, and its bearing seat is fixed on the triangle crossbeam, and gear is by the rack segments driven rotary of the sleeve pipe that can slide on triangle crossbeam axle.The crank motion of sleeve pipe utilizes electromagnetic actuator device to realize;
The transmission device of control movable wing amplitude of fluctuation is included in the compound type power bent axle of fuselage both sides, imput shaft, be installed on the imput shaft gear and by the driven shaft of bearing block support, be with outer central siphon on the interior shaft part of this driven shaft, finishing bevel gear cuter is equipped with in its nearly bent axle lower end, should on the outer central siphon brake disc and the brake facing that is subjected to solenoid control be housed, and by the four paws movable chuck of solenoid control, should finishing bevel gear cuter be housed outer central siphon end, the shaft part rear portion is with finishing bevel gear cuter in driven shaft, the two all with support on compound planet gear at right angles mesh, the finishing bevel gear cuter rear portion is the friction wheel that fuses with it, and by key connecting, this two friction wheels transmission of motion is realized by push rod and pressure roller control by electromagnetic valve between another friction wheel of its coupling and the driven shaft shaft part.
Adopt said mechanism, can guarantee movable wing when lower swing, its nose of wing upset downwards at once (trailing edge is upwards upset simultaneously); Otherwise when movable wing was upwards swung, its nose of wing is upwards upset at once, and can regulate flip angle within the specific limits, can reduce resistance effectively, made to promote power and lift ratio reaches the most rational state.Owing to adopt the structure of compound crankshaft, can change the amplitude of fluctuation of movable wing, during turning flight, the inboard one side of fuselage amplitude of fluctuation is reduced, fuselage tilts thereupon, rotates flexibly, and it is less to consume energy.In addition owing to have a pair of fixed-wing, when driving engine breaks down, can gliding flight, and can regulate movable wing simultaneously and keep the flat state that flies, thus guarantee flapping-wing aircraft safety glide flight and landing, improved safety.In addition, the utility model also has advantages such as dash road landing (10 meters), governing speed scope be big, of many uses.
Accompanying drawing 1 is the utility model profile birds-eye view;
Accompanying drawing 2 is the utility model profile front elevations;
Accompanying drawing 3 is rotating disk and circular trough cutaway view;
Accompanying drawing 4 is sleeve pipe and rack structure figure;
Accompanying drawing 5 is guide rod, sleeve pipe and actuating device birds-eye view thereof;
Accompanying drawing 7 is AA-BB cross-sectional view of accompanying drawing 6;
Accompanying drawing 8 is C-C cross-sectional view of accompanying drawing 6;
Accompanying drawing 9 is the vertical mechanism assembly block diagrams of outer central siphon drilling.
Further specify embodiment in conjunction with the accompanying drawings:
In the utility model when flight, flutter downwards by the movable wing of both sides and produce lift and propulsive force.Fixed-wing also produces certain lift, plays stabilization simultaneously.
As shown in Figure 1 and Figure 2, flapping-wing aircraft has fixed-wing 1 and movable wing 5, and wing is the globality structure.Engine spindle connects the bent axle 2 and the connecting rod 6 of fuselage both sides by speed change system, the other end of connecting rod 6 links to each other with annulus 4, front and back triangle crossbeam 3 is connected with fuselage by crossbeam 7, pass through the crankshaft-link rod of fuselage both sides during engine operation, to rotatablely move becomes reciprocating, and drives annulus 4 and movable wing 5 swings up and down.Realize by regulating movable wing amplitude of fluctuation and flip angle during turning flight.
As Fig. 3, Fig. 4, Figure 5 shows that the mechanism of the utility model control movable wing planar inverted angle, be included in that the fuselage bilateral symmetry installs respectively with both sides before and after triangle crossbeams (3) two umbrella stulls (15) that link, its underpart links to each other with connecting rod (6), umbrella stull (15) top has the bearing (14) that wing root axle (8) is installed, its opening end and ring (4) looping groove (11), one circle ebonite roller (10) is housed in the groove, the wing root of movable wing (8) also links with rotating disk (9), this rotating disk (9) is installed in the circular groove and by above-mentioned rubber roll (10) and is adjacent to, rotating disk (9) has internally toothed annulus (12), this internally toothed annulus is meshed with gear (13), gear (20) is contained on the axle (16) together with gear (13), its bearing seat is fixed on the triangle crossbeam (3), and gear (20) is by rack segments (19B) driven rotary that can go up the sleeve pipe (19) that slides at triangle crossbeam axle (7).
Triangle crossbeam axle (7) two ends are cylindrical, are connected with fuselage by bearing, and the remainder of axle is a hexagon.
Sleeve pipe (19) is enclosed within on the triangle crossbeam axle (7), have the six prismatic endoporus that are complementary of six prisms with axle (7), its periphery is cylindrical, second half section is rack segments (19B) simultaneously upwards, the end joins by thrust baring and sleeve pipe (18), and this sleeve pipe (18) bottom is a rectangle feather key structure.
Have the cover array ceoncentrically wound coil parallel in drive sleeve (18 and 19) the reciprocating electromagnetic actuator devices (22) with sleeve pipe (18), and one passed the cylinder guide (21) that above-mentioned coil winding can be slided along roller (17), this guide rod is made by insulating material, there is a cylindrical soft iron in its stage casing, and guide rod (21) length is consistent with sleeve pipe (18).
When guide rod 21 moves, slip band moving gear 20 and 1 angle of gear 13 rotations by the rack segments 19B on sleeve pipe 18 and the sleeve pipe 19, and drive rotating disk 9 rotation thereupon, thereby making the wing root axle that links with it rotate and drive movable wing overturns, when lower swing, its leading edge 0-40 degree that can overturn downwards, on then can in 0-70 degree scope, regulate when putting.
As Fig. 6, Fig. 7 and Figure 8 shows that the transmission device of the utility model control movable wing amplitude of fluctuation.The transmission device of control movable wing amplitude of fluctuation is included in the compound type power bent axle (24 of fuselage both sides, 25), imput shaft (23), the driven shaft (31) that is installed in the gear (32) on the imput shaft (23) and supports by bearing seat (30), be with outer central siphon (34) on the interior shaft part (31B) of this driven shaft, finishing bevel gear cuter (29) is equipped with in its nearly bent axle lower end, be somebody's turn to do the brake facing (35) that on the outer central siphon (34) brake disc (36) is housed and is subjected to electromagnetic valve (51) control, and by the four paws movable chuck (39) of electromagnetic valve (48) control, should finishing bevel gear cuter (40) be housed outer central siphon end, shaft part in driven shaft (31B) rear portion is with finishing bevel gear cuter (46), the two all with support on compound planet gear (41,47) at right angles engagement, finishing bevel gear cuter (46) rear portion is the friction wheel (42) that fuses with it, and by key connecting, this two friction wheels transmission of motion is realized by push rod (43) and pressure roller (44) control by electromagnetic valve (45) between the interior shaft part (31B) of another friction wheel (52) of its coupling and driven shaft.
Compound type power bent axle (24,2,25) is formed by three sections, comprising:
A, power arm (24) with imput shaft of guide rail shape,
B, driven armshaft (25) with guide groove shape, its nut (26) and finishing bevel gear cuter (28) that one side is equipped with and screw rod (27) is nested outwardly,
C, the movable double crank (2) that is connected with connecting rod (6), one arm are enclosed within on the active armshaft (24), and another arm is clipped in the guide rail of driven armshaft (25), and pommel one side outwardly is equipped with the nut (26) that matches with drive screw (27).
Electromagnetic valve (48) is handled claw (37) to the control of four paws movable chuck (39) by driving lever (49), roller (50) and spring (38) and is realized.
The mechanism of above-mentioned control movable wing amplitude of fluctuation has three kinds of mode of operations:
1, when the equal no power of electromagnetic valve 51,48,45, outer central siphon 34 becomes one with interior axle 31B and rotates synchronously, and this moment, finishing bevel gear cuter 28, screw rod 27 did not rotate, and crank position is constant, and the swing degree of the movable wing of its homonymy is also constant.
2, when electromagnetic valve 51,48 energising, when valve 45 was obstructed, outer central siphon 34 was thrown off and the brake stall with interior axle 31B, at this moment, slave arm 25 drives finishing bevel gear cuter 28 and rotates on finishing bevel gear cuter 29, and drive screw 27 rotates, crank 2 is outwards moved, thereby increase the crank up radius, the movable wing amplitude of oscillation increases.
3, when electromagnetic valve 48,45 energisings, when valve 51 is obstructed, interior axle 31B throws off with outer central siphon 34, finishing bevel gear cuter 29 rotates synchronously with interior axle 31B simultaneously, and by 40 rotations of planetary wheel 41,47 drive finishing bevel gear cuters, this moment outer central siphon 34 with interior axle 31B in the same way but asynchronous rotation, outer central siphon rotating speed is higher than interior (ratio of revolution reaches more than the 2:1).And by finishing bevel gear cuter 29 drive finishing bevel gear cuters 28 and screw rod 27 rotations, its rotation direction is opposite with last a kind of direction, and crank is inwardly shortened, and the movable wing amplitude of fluctuation reduces.
The utility model can be made single-place plane, two-seater aircraft.Mix appropriate device and also can realize remote control.
Basic technical data: 7 meters of fuselage length, 11.8 meters of the spanes (3.6 meters of the activity chord of every side), gross wing area 14 sq ms, tailplane 3.9 sq ms (no vertical tail), 30 horsepowers of engine powers, 220 kilograms of flapping-wing aircraft bare weights, maximum take-off weight is 320 kilograms, 120 kilometers/hour of max level speeds.
The utility model can be used for patrol, tourism, traffic, fire prevention, scouting, agricultural and photo flight etc.
Claims (10)
1, a kind of hybrid flapping-wing aircraft, form by fuselage, wing, driving engine and drive disk assembly thereof, it is characterized in that: described wing is an integral type, comprise a pair of movable wing (5) and a pair of fixed-wing (1), this movable wing (5) has the transmission device of its planar inverted angle of control and controls its amplitude of fluctuation to realize the transmission device of turning action at the last rear of fixed-wing (1).
2, according to the described flapping-wing aircraft of claim 1, it is characterized in that: the mechanism of control movable wing planar inverted angle be included in that the fuselage bilateral symmetry installs respectively with both sides before and after triangle crossbeams (3) two umbrella stulls (15) that link, its underpart links to each other with connecting rod (6), umbrella stull (15) top has the bearing (14) that wing root axle (8) is installed, its opening end and ring (4) looping groove (11), one circle ebonite roller (10) is housed in the groove, the wing root of movable wing (8) also links with rotating disk (9), this rotating disk (9) is installed in the circular groove and by above-mentioned rubber roll (10) and is adjacent to, rotating disk (9) has internally toothed annulus (12), this internally toothed annulus is meshed with gear (13), gear (20) is contained on the axle (16) together with gear (13), its bearing seat is fixed on the triangle crossbeam (3), and gear (20) is by rack segments (19B) driven rotary that can go up the sleeve pipe (19) that slides at triangle crossbeam axle (7).The crank motion of sleeve pipe (19) utilizes electromagnetic actuator device (22) to realize.
3, according to claim 1 or 2 described flapping-wing aircrafts, it is characterized in that: described triangle crossbeam axle (7) two ends are cylindrical, are connected with fuselage by bearing, and the remainder of axle is a hexagon.
4, according to claim 1 or 2 described flapping-wing aircrafts, it is characterized in that: described sleeve pipe (19) is enclosed within on the triangle crossbeam axle (7), have the six prismatic endoporus that are complementary of six prisms with axle (7), its periphery is cylindrical, second half section is rack segments (19B) simultaneously upwards, the end joins by thrust baring and sleeve pipe (18), and this sleeve pipe (18) bottom is a rectangle feather key structure.
5, according to claim 1 or 2 described flapping-wing aircrafts, it is characterized in that: have the cover array ceoncentrically wound coil parallel in sleeve pipe (18 and 19) the reciprocating electromagnetic actuator devices (22) with sleeve pipe (18), and one passed the cylinder guide (21) that above-mentioned coil winding can be slided along roller (17), this guide rod is made by insulating material, there is a cylindrical soft iron in its stage casing, and guide rod (21) length is consistent with sleeve pipe (18).
6, according to the described flapping-wing aircraft of claim 1, it is characterized in that: the transmission device of control movable wing amplitude of fluctuation is included in the compound type power bent axle (24 of fuselage both sides, 25), imput shaft (23), the driven shaft (31) that is installed in the gear (32) on the imput shaft (23) and supports by bearing seat (30), be with outer central siphon (34) on the interior shaft part (31B) of this driven shaft, finishing bevel gear cuter (29) is equipped with in its nearly bent axle lower end, be somebody's turn to do the brake facing (35) that on the outer central siphon (34) brake disc (36) is housed and is subjected to electromagnetic valve (51) control, and by the four paws movable chuck (39) of electromagnetic valve (48) control, should finishing bevel gear cuter (40) be housed outer central siphon end, shaft part in driven shaft (31B) rear portion is with finishing bevel gear cuter (46), the two all with support on compound planet gear (41,47) at right angles engagement, finishing bevel gear cuter (46) rear portion is the friction wheel (42) that fuses with it, and by key connecting, this two friction wheels transmission of motion is realized by push rod (43) and pressure roller (44) control by electromagnetic valve (45) between the interior shaft part (31B) of another friction wheel (52) of its coupling and driven shaft.
7, according to claim 1 or 6 described flapping-wing aircrafts, it is characterized in that: compound type power bent axle (24,2,25) is formed by three sections, comprising:
A, power arm (24) with imput shaft of guide rail shape,
B, driven armshaft (25) with guide groove shape, its nut (26) and finishing bevel gear cuter (28) that one side is equipped with and screw rod (27) is nested outwardly,
C, the movable double crank (2) that is connected with connecting rod (6), one arm are enclosed within on the active armshaft (24), and another arm is clipped in the guide rail of driven armshaft (25), and pommel one side outwardly is equipped with the nut (26) that matches with drive screw (27).
8, according to claim 1 or 6 described flapping-wing aircrafts, it is characterized in that: electromagnetic valve (48) is handled claw (37) to the control of four paws movable chuck (39) by driving lever (49), roller (50) and spring (38) and is realized.
9, according to the described flapping-wing aircraft of claim 1, it is characterized in that: its fuselage is a single seated.
10, according to the described flapping-wing aircraft of claim 1, it is characterized in that: its fuselage is a double seat.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 94221317 CN2213118Y (en) | 1994-09-14 | 1994-09-14 | Mixed ornithopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 94221317 CN2213118Y (en) | 1994-09-14 | 1994-09-14 | Mixed ornithopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2213118Y true CN2213118Y (en) | 1995-11-22 |
Family
ID=33835648
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 94221317 Expired - Fee Related CN2213118Y (en) | 1994-09-14 | 1994-09-14 | Mixed ornithopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN2213118Y (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1999065767A1 (en) * | 1998-06-12 | 1999-12-23 | Tao Fan | The ornithopter |
| CN100413757C (en) * | 2006-03-20 | 2008-08-27 | 西北工业大学 | Rolling control mechanism for minitype ornithopter |
| CN100430297C (en) * | 2006-04-06 | 2008-11-05 | 西北工业大学 | Driving mechanism for wings of minitype ornithopter |
| CN102673785A (en) * | 2011-03-11 | 2012-09-19 | 张家港市九鼎机械有限公司 | Flapping-wing aircraft |
| CN104802990A (en) * | 2015-04-28 | 2015-07-29 | 北京航空航天大学 | Foldable flapping wings and fixed wings coupling-structured aircraft design |
| CN105416575A (en) * | 2015-12-14 | 2016-03-23 | 西北工业大学 | Bionic undercarriage system for flapping wing air vehicle and takeoff and landing control method |
| CN105620748A (en) * | 2016-03-08 | 2016-06-01 | 吴锜 | Flapping type double-wing flying device |
| CN106585982A (en) * | 2016-12-20 | 2017-04-26 | 西北工业大学 | Combined type micro air vehicle driven by flapping wings |
-
1994
- 1994-09-14 CN CN 94221317 patent/CN2213118Y/en not_active Expired - Fee Related
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1999065767A1 (en) * | 1998-06-12 | 1999-12-23 | Tao Fan | The ornithopter |
| CN1081155C (en) * | 1998-06-12 | 2002-03-20 | 樊涛 | The ornithopter |
| CN100413757C (en) * | 2006-03-20 | 2008-08-27 | 西北工业大学 | Rolling control mechanism for minitype ornithopter |
| CN100430297C (en) * | 2006-04-06 | 2008-11-05 | 西北工业大学 | Driving mechanism for wings of minitype ornithopter |
| CN102673785A (en) * | 2011-03-11 | 2012-09-19 | 张家港市九鼎机械有限公司 | Flapping-wing aircraft |
| CN102673785B (en) * | 2011-03-11 | 2015-02-25 | 张家港市九鼎机械有限公司 | Flapping-wing aircraft |
| CN104802990A (en) * | 2015-04-28 | 2015-07-29 | 北京航空航天大学 | Foldable flapping wings and fixed wings coupling-structured aircraft design |
| CN104802990B (en) * | 2015-04-28 | 2017-01-18 | 北京航空航天大学 | Foldable flapping wings and fixed wings coupling-structured aircraft design |
| CN105416575A (en) * | 2015-12-14 | 2016-03-23 | 西北工业大学 | Bionic undercarriage system for flapping wing air vehicle and takeoff and landing control method |
| CN105620748A (en) * | 2016-03-08 | 2016-06-01 | 吴锜 | Flapping type double-wing flying device |
| CN106585982A (en) * | 2016-12-20 | 2017-04-26 | 西北工业大学 | Combined type micro air vehicle driven by flapping wings |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C19 | Lapse of patent right due to non-payment of the annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |