CN201678041U - Circulating flapping-wing flying vehicle - Google Patents
Circulating flapping-wing flying vehicle Download PDFInfo
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- CN201678041U CN201678041U CN2010201289942U CN201020128994U CN201678041U CN 201678041 U CN201678041 U CN 201678041U CN 2010201289942 U CN2010201289942 U CN 2010201289942U CN 201020128994 U CN201020128994 U CN 201020128994U CN 201678041 U CN201678041 U CN 201678041U
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Abstract
A circulating flapping-wing flying vehicle belongs to the technical field of mechanical manufacturing, and consists of a machine body, control mechanisms, a power unit, an output shaft and wing plates, wherein the wing plates are connected with the control mechanisms through wing shafts, and the power unit is mounted on the machine body; the flying vehicle is characterized in that a propeller is mounted on the machine body, 2 to 8 symmetrical control mechanisms are mounted on the machine body, and the intersecting angles between the wing shafts of the control mechanisms and the output shaft range from 0 DEG to 65 DEG. The utility model has the advantages of high aerodynamic quality, safety, stability, flexibility, low noise, energy consumption and environmental protection.
Description
Technical field:
The invention belongs to machinery manufacturing technology field, a kind of aircraft that specific description the present invention relates to.
Background technology:
Former carrying on as before such as the mankind have passed through very long course to the research of flapping wing aircraft, up to the present still do not have considerable progress, and the prototype of flapping wing comes out though have up and down, and, power consumption low because of its efficient is big rest on the toy stage.For many years, the inventor is engaged in flapping wing aircraft Study on Technology and exploration always, and has obtained outstanding progress.The inventor had once applied for the wheel wing of lifting flight " a kind of can " patent (patent No.: 200720094807.1), and authorized by State Patent Office in invention in 2007 and to State Patent Office; I invented and had applied for " circulating flapping wing aerial vehicle " patent (application number: 200910066667.0), now announced and enter the substantive examination stage again in 2009.
Summary of the invention:
The technical problems to be solved in the utility model is to disclose a kind of circulating flapping wing aerial vehicle.
The utility model is made of body, control mechanism, engine installation, output shaft and wing plate, wing plate connects control mechanism by wing axle, engine installation is contained on the body, it is characterized in that: screw propeller is housed on the body, the control mechanism of 2 to 8 symmetries is housed on the body, and the angle that the wing axle of control mechanism and output shaft intersect is between 0 degree is spent to 65.The angle that wing axle and output shaft intersect is between 15 degree are spent to 55.The angle that wing axle and output shaft intersect is 30 degree.
The circulating flapping wing aerial vehicle (as shown in Figure 1) of screw propeller is housed.At the front end of body one group of (2) control mechanism is installed, and one double helix oar is installed at the tail end of body.1, the vertical lift-off of aircraft and hovering: adjust rudder stock, make maximum 90 degree of control mechanism be located at the position parallel of rotation forward in angle (being maximum flapping wing face) down with the wind with horizontal surface, starting engine installation rotatablely moves control mechanism forward, drive screw propeller simultaneously tail lift is provided, (must keep organism balance) when the rotation of control mechanism and screw propeller reaches certain speed, aircraft promptly breaks away from ground and vertically goes up to the air.As locking control mechanism and propeller speed, aircraft gets final product hovering.2, aircraft flies forward: adjust head control mechanism rudder stock, maximum 90 is spent under angle (being maximum flapping wing face) the tuning horizontal surface that facings the wind, (palpus adjusting control mechanism and propeller speed keep organism balance) aircraft can fly forward.Also can adjust head control mechanism rudder stock, and direct adjusting control mechanism and propeller speed make tail be higher than head, aircraft also can fly forward.3, aircraft flies backward: adjust head control mechanism rudder stock, maximum 90 is spent on angle (being maximum flapping wing face) the tuning horizontal surface that facings the wind, (palpus adjusting control mechanism and propeller speed keep organism balance) aircraft can fly backward.Also can adjust head control mechanism rudder stock, and direct adjusting control mechanism and propeller speed make tail be lower than head, aircraft also can fly backward.4, aircraft about turn to flight: adjust right side control mechanism rudder stock, maximum 90 is spent on angle (being maximum flapping wing face) the tuning horizontal surface that facings the wind, also can adjust left side control mechanism rudder stock simultaneously, maximum 90 is spent under angle (being maximum flapping wing face) the tuning horizontal surface that facings the wind, (palpus adjusting control mechanism and propeller speed keep organism balance) aircraft gets final product left-handed turning to flight.Otherwise, adjust left side control mechanism rudder stock, maximum 90 is spent on angle (being maximum flapping wing face) the tuning horizontal surface that facings the wind, also can adjust right side control mechanism rudder stock simultaneously, maximum 90 is spent under angle (being maximum flapping wing face) the tuning horizontal surface that facings the wind, (palpus adjusting control mechanism and propeller speed keep organism balance) aircraft gets final product right-hand turning to flight.When aircraft flies forward, adjust the vertical tail flap and can realize that also aircraft turns to flight.The circulating flapping wing aerial vehicle advantage that screw propeller is housed is safe and reliable, maneuverability, convenient and swift.Field of application: traffic, rescue, model plane.
The circulating flapping wing aerial vehicle of two groups of (promptly 4) control mechanisms is housed.As shown in Figure 2, two groups of (promptly 4) control mechanisms are installed respectively before and after the aircraft body, adjust rudder stock and spend the outside that the angle (being maximum flapping wing face) that facings the wind is located at the rear and front end control mechanism maximum 90, the hand of rotation of two groups of control mechanisms is set to respectively rotate from inside to outside, head control mechanism left-hand revolution, tail control mechanism clickwise can be realized the flight of circulating flapping wing aerial vehicle by concrete operations and corresponding configuration.1, the vertical lift-off of circulating flapping wing aerial vehicle: rudder stock before and after adjusting, maximum 90 degree of two groups of control mechanisms are located at the position parallel with horizontal surface in angle (being maximum flapping wing face) down with the wind before and after making, two groups of control mechanisms were outwards done the contrarotation campaign respectively before and after driving power device made, swat air downwards, (must keep organism balance) when the control mechanism rotation reaches certain speed, aircraft promptly breaks away from ground and vertically goes up to the air.As lock control mechanism rotating speed aircraft and get final product hovering.2, circulating flapping wing aerial vehicle flies forward: adjust head control mechanism rudder stock, maximum 90 is spent under angle (being maximum flapping wing face) the tuning horizontal surface that facings the wind, also can adjust tail control mechanism rudder stock simultaneously, maximum 90 is spent on angle (being maximum flapping wing face) the tuning horizontal surface that facings the wind, and (control mechanism rotating speed maintenance organism balance before and after must adjusting) aircraft can fly forward.3, circulating flapping wing aerial vehicle flies backward: adjust head control mechanism rudder stock, maximum 90 is spent on angle (being maximum flapping wing face) the tuning horizontal surface that facings the wind, also can adjust tail control mechanism rudder stock simultaneously, maximum 90 is spent under angle (being maximum flapping wing face) the tuning horizontal surface that facings the wind, and (control mechanism rotating speed maintenance organism balance before and after must adjusting) aircraft can fly backward.4, turn to flight about circulating flapping wing aerial vehicle: adjust right side control mechanism rudder stock, maximum 90 is spent on angle (being maximum flapping wing face) the tuning horizontal surface that facings the wind, also can adjust left side control mechanism rudder stock simultaneously, maximum 90 degree is facingd the wind under the tuning horizontal surface of angle (being maximum flapping wing face), (the control mechanism rotating speed keeps organism balance before and after must adjusting) aircraft can left-handed turning to flight.Otherwise, adjust left side control mechanism rudder stock, maximum 90 is spent on angle (being maximum flapping wing face) the tuning horizontal surface that facings the wind, also can adjust right side control mechanism rudder stock simultaneously, maximum 90 degree is facingd the wind under the tuning horizontal surface of angle (being maximum flapping wing face), (the control mechanism rotating speed keeps organism balance before and after must adjusting) aircraft can right-hand turning to flight.When aircraft flies forward, adjust the vertical tail flap and can realize that also aircraft turns to flight.5, circulating flapping wing aerial vehicle landing: adjust rudder stock, maximum 90 degree of the two groups of control mechanisms angle (being maximum flapping wing face) that facings the wind is located at the position parallel with horizontal surface before and after making, the landing of can landing of rev down, aircraft.Also can be by the fixed-wing dead-stick landing.6, the horizontality by adjusting control mechanism rotating speed controlling aircraft rear and front end realizes that it flies forward and flight backward.Aircraft flies forward when head is lower than tail, and aircraft flies backward when head is higher than tail.7, air is swatted in two of circulating flapping wing aerial vehicle groups of also ecto-entad rotations simultaneously of control mechanism downwards.The circulating flapping wing aerial vehicle of two groups of control mechanisms is housed, pneumatic efficiency height, safety and steady, low, the energy-conserving and environment-protective of noise.Field of application: traffic, rescue, model plane etc.
Circulating flapping wing aerial vehicle is equipped with fixed-wing (hang gliding) and solar panels on body, in order to forced landing.。
Circulating flapping wing aerial vehicle is equipped with floating drum or ship storehouse under body, can be at surface navigation.
Circulating flapping wing aerial vehicle is equipped with wheel or sled under body, can and slide lift-off at ground run.
The circulating flapping wing aerial vehicle control mechanism is applied to aerogenerator.The existing propeller wind power machine area of collecting folk songs is little, and pneumatic efficiency is poor, and generating efficiency is low, quits work under the gentle breeze state.The characteristic of circulating flapping wing aerial vehicle control mechanism is that it is by rotating the asymmetric air-flow that can produce single direction, according to this characteristic, maximum 90 degree of control mechanism are facingd the wind angle (being maximum windward side) towards the windward side, wind-force promotes wing plate and control mechanism begins rotation, transfers mechanical energy to electric energy.Make a pylon or vertical rod, the bottom vertical fixing is in ground, bearing seat is equipped with on the top of pylon or vertical rod, control mechanism is installed on the top bearing seat of pylon or vertical rod, the control mechanism imput shaft is equipped with generator amature, rotor is with generator unit stator outward and is fixed in frame, and the electrical generator output line is connected with inverter with storage battery.Maximum 90 degree of control mechanism are facingd the wind angle (being maximum windward side) towards the windward side (vertical with horizontal surface), generating that wind-force promotion wing plate and control mechanism rotate and the driving electrical generator is started working.In the control mechanism frame tail plate is housed, to follow the tracks of wind direction.Also can drive electrical generator indirectly, electrical generator and control mechanism are separated, by change speed gear box or the work of belt drive electrical generator.The advantage that the aerogenerator of circulating flapping wing aerial vehicle control mechanism is housed is, the area of collecting folk songs is big, the pneumatic efficiency height, and the generating efficiency height still can be worked under the gentle breeze state as usual.The circulating flapping wing aerial vehicle control mechanism also can be applicable to hydroelectric generator.Water and air belong to fluid, density of medium difference just, and the structure (reducing area of foil) with the aerogenerator of application cycle flapping wing aircraft control mechanism is installed in rivers, the water channel and also can realizes hydropower.
The circulating flapping wing control mechanism is applied to the underwater scooter of boats and ships, Submarine.The underwater scooter of existing ship, submarine is to utilize propeller thrust, and its weak point is that the plane of action of blade and water is little, and efficient is low.The circulating flapping wing control mechanism also can produce asymmetric unimodal current in water, realize power efficiently.Specific embodiments: in boats and ships submarine site installation and control mechanism, adjusting control mechanism rudder stock, angle (being maximum flapping wing face) tuning is vertical with horizontal surface down with the wind with maximum 90 degree, promptly advances boats and ships to move ahead when control mechanism rotates forward, promptly retreats when control mechanism rotates boats and ships backward.When boats and ships move ahead, maximum 90 degree is facingd the wind angle (being maximum flapping wing face) tuning when spending less than 90 with horizontal surface, can produce buoyancy, make hull partly break away from the water surface, reduce water resistance, the raising route speed.Know-why according to circulating flapping wing aerial vehicle, in Submarine fuselage installation and control mechanism (suitably reducing area of foil), can realize that Submarine advances, retreats, turning, dive, come-up, minimizing is to the dependence of water inlet and draining, greatly improve the efficient and the alerting ability of Submarine, had very high practical value.
Description of drawings:
Fig. 1 is the circulating flapping wing aerial vehicle that screw propeller is housed;
Fig. 2 is the circulating flapping wing aerial vehicle that two groups of control mechanisms are housed.
The specific embodiment:
Example 1: the circulating flapping wing aerial vehicle that screw propeller is housed.As shown in Figure 1, the utility model is made of body 1, control mechanism 2, engine installation 3, output shaft 4 and wing plate 5, wing plate 5 connects control mechanism 2 by wing axle 6, engine installation 3 is contained on the body 1, the body afterbody is equipped with the control mechanism 2 that screw propeller 7, body 1 head are equipped with two symmetries, and the wing axle 6 of control mechanism 2 is 30 degree with the angle that output shaft 4 intersects.
Example 2: the circulating flapping wing aerial vehicle that two groups of (promptly 4) control mechanisms are housed.As shown in Figure 2, constitute by body 1, control mechanism 2, engine installation 3, output shaft 4 and wing plate 5, wing plate 5 connects control mechanism 2 by wing axle 6, engine installation 3 is contained on the body 1, the control mechanism 2 of two groups (4) symmetry is equipped with in body 1 front and back, and the wing axle 6 of control mechanism 2 is 30 degree with the angle that output shaft 4 intersects.
Example 3: make a pylon, the bottom vertical fixing is in ground, bearing seat is equipped with on the top of pylon, control mechanism is installed on the top bearing seat of pylon, the control mechanism imput shaft is equipped with generator amature, rotor is with generator unit stator outward and is fixed in frame, and the electrical generator output line is connected with inverter with storage battery.Maximum 90 degree of control mechanism are facingd the wind angle (being maximum windward side) towards the windward side (vertical with horizontal surface).Wind direction rudder tail plate is housed on the control mechanism frame.
Claims (3)
1. circulating flapping wing aerial vehicle, constitute by body, control mechanism, engine installation, output shaft and wing plate, wing plate connects control mechanism by wing axle, engine installation is contained on the body, it is characterized in that: screw propeller is housed on the body, the control mechanism of 2 to 8 symmetries is housed on the body, and the angle that the wing axle of control mechanism and output shaft intersect is between 0 degree is spent to 65.
2. aircraft according to claim 1 is characterized in that: the angle that wing axle and engine installation output shaft intersect is between 15 degree are spent to 55.
3. aircraft according to claim 2 is characterized in that: the angle that wing axle and engine installation output shaft intersect is 30 degree.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010201289942U CN201678041U (en) | 2010-03-12 | 2010-03-12 | Circulating flapping-wing flying vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010201289942U CN201678041U (en) | 2010-03-12 | 2010-03-12 | Circulating flapping-wing flying vehicle |
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| Publication Number | Publication Date |
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| CN201678041U true CN201678041U (en) | 2010-12-22 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN2010201289942U Expired - Fee Related CN201678041U (en) | 2010-03-12 | 2010-03-12 | Circulating flapping-wing flying vehicle |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN104176252A (en) * | 2014-09-05 | 2014-12-03 | 上海理工大学 | Flapping wing utilizing wind energy or water flow energy to charge for continuous voyage |
| CN113460296A (en) * | 2021-07-22 | 2021-10-01 | 南京航空航天大学 | Flapping wing-double rotor wing hybrid aircraft |
-
2010
- 2010-03-12 CN CN2010201289942U patent/CN201678041U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN103991549B (en) * | 2014-05-30 | 2015-12-02 | 佛山市神风航空科技有限公司 | A kind of high strength rotary flapping wing aircraft |
| CN104176252A (en) * | 2014-09-05 | 2014-12-03 | 上海理工大学 | Flapping wing utilizing wind energy or water flow energy to charge for continuous voyage |
| CN113460296A (en) * | 2021-07-22 | 2021-10-01 | 南京航空航天大学 | Flapping wing-double rotor wing hybrid aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20101222 Termination date: 20140312 |