CN201442653U - Guyed flapping-wing air vehicle steering driving mechanism - Google Patents
Guyed flapping-wing air vehicle steering driving mechanism Download PDFInfo
- Publication number
- CN201442653U CN201442653U CN2009200138942U CN200920013894U CN201442653U CN 201442653 U CN201442653 U CN 201442653U CN 2009200138942 U CN2009200138942 U CN 2009200138942U CN 200920013894 U CN200920013894 U CN 200920013894U CN 201442653 U CN201442653 U CN 201442653U
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- wing
- flapping
- folding
- wing aircraft
- air vehicle
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Abstract
Disclosed is a guyed flapping-wing air vehicle steering driving mechanism which relates to the technical field of flapping-wing air vehicles. The driving mechanism comprises a servo motor, a signal receiving device, folding wing guys and steering hinges, wherein the servo motor fixed onto a machine body of a flapping-wing air vehicle is connected with the signal receiving device via a conducting wire, the signal receiving device is placed inside an engine room of the flapping-wing air vehicle, two steering hinges are respectively arranged on two sides of the machine body of the flapping-wing air vehicle, a servo motor shaft is connected to a center of a connecting rod, two folding wing guys are respectively connected to two ends of the connecting rod, and each folding wing guy is connected with a rotary portion of a foldable wing of the flapping-wing air vehicle through one steering hinge on the side of the folding wing guy. The driving mechanism is capable of folding the foldable wing without increasing weight of vehicle wings, basically unaffecting aerodynamics characteristics of the vehicle wings, respectively realizing folding a left wing and a right wing and being convenient for the flapping-wing air vehicle to turn left or right.
Description
Technical field
The utility model relates to the flapping wing aircraft technical field, and particularly a kind of stay-supported flapping wing aircraft turns to driver train.
Background technology
Mini-sized flap wings aircraft (Flapping-Wing Micro Air Vehicle, be called for short FMAV) be a kind of course of new aircraft of imitating birds or insect flying, compare with rotor craft with fixed-wing, its principal feature is with lifting, hovers and propulsion functions is integrated in one, need not screw propeller or air jet system, have very strong manoevreability and alerting ability.And to realize these functions, actuating unit---the flapping wing wing plays a part comparatively crucial.
At present, the driver train of flexible wing folded part mostly is made of geared linkage mechanism, and be used on the flapping wing aircraft wing and can gain in weight and volume, so the folding wing steering hardware that is used as of no use, but control turns to by empennage.
The utility model content
Be difficult for realizing the folding and difficult problem that realizes dogled of flexible wing in order to solve existing wing-folding actuating device, the utility model provides a kind of later-model stay-supported flapping wing aircraft to turn to driver train, and this mechanism can realize the folding of flexible wing by the mode of backguy.
The technical solution adopted in the utility model is: comprise servomotor torque constant, signal receiving device, folding wings backguy and turn to hinge, wherein servomotor torque constant is fixed on the flapping wing aircraft fuselage, servomotor torque constant is connected with signal receiving device by lead, signal receiving device is placed in the cabin of flapping wing aircraft, flapping wing aircraft fuselage both sides respectively are provided with one and turn to hinge, the servo-electric arbor links to each other with the center of connecting rod, the two ends of connecting rod respectively are connected with a folding wings backguy, and every folding wings backguy links to each other with the rotating element of flapping wing aircraft flexible wing by the hinge that turns to of this side.
In remote control process, by the remote controller remote control, signal receiving device is accepted remote signal, servomotor torque constant is done corresponding rotation by the given signal of signal receiving device, drive folding wings backguy campaign, the pivotable parts of pulling flexible wing rotates, and realizes the folding of flexible wing.
A kind of optimal way of the present utility model: turn to hinge to be positioned on the fuselage of wing front end, servomotor torque constant adopts the DC motor of steering wheel or band coder, and servomotor torque constant is fixed on the center-of-gravity position of flapping wing aircraft fuselage.
The utility model driven object is a kind of flapping wing aircraft, and this aircraft has flexible wing, flexible wing realization rotation.
The beneficial effects of the utility model are: can realize the folding of flexible wing, can not increase the weight of wing, and not influence the moving phoronomics characteristic of air of wing substantially, and two wings folding about realizing respectively, so that flapping wing aircraft can be turned left or turn right.
Description of drawings
Fig. 1 is a structural representation of the present utility model;
The structural representation of Fig. 2 a kind of embodiment of the present utility model;
Among the figure: 1. first rod member, 2. turning joint, 3 second rod members, 4 turn to hinge, 5 folding wings backguys, 6 servomotor torque constants, 7 connecting rods.
The specific embodiment
In conjunction with the accompanying drawings the utility model is described further:
As shown in Figure 1, the utility model structural representation, comprise servomotor torque constant 6, signal receiving device, folding wings backguy 5 and turn to hinge 4, wherein servomotor torque constant 6 is fixed on the flapping wing aircraft fuselage, servomotor torque constant 6 is connected with signal receiving device by lead, signal receiving device is placed in the cabin of flapping wing aircraft, flapping wing aircraft fuselage both sides respectively are provided with one and turn to hinge 4, servomotor torque constant 6 arbors link to each other with the center of connecting rod, the two ends of connecting rod respectively are connected with a folding wings backguy 5, and every folding wings backguy 5 links to each other with the rotating element of flapping wing aircraft flexible wing by the hinge 4 that turns to of this side.The fine folding wings backguy that is difficult for breaking is adopted in the folding wings backguy, and servomotor torque constant adopts steering wheel.First rod member 1, turning joint 2. and second rod member 3 are formed the framework component part of flapping wing aircraft wing.First rod member 1 is connected by turning joint 2 with second rod member 3, and the mechanism that this three forms forms the rotating element of flapping wing aircraft flexible wing.
It is the BLUE ARROW ultramicro minitype servo (being steering wheel) of S0251 that servomotor torque constant 6 can be selected model for use, so signal receiving device can be selected the BLUE ARROW micro-receiver of R3PX V3 series for use, the optional FUTABA four-channel remote control device commonly used of remote controller.This driver train can be used for realizing the horizontal or longitudinal folding of flapping wing aircraft folding wing, also can be used for other folded form of flapping wing aircraft folding wing.As shown in Figure 2, the structural representation of a kind of embodiment of the present utility model, on its principle as hereinbefore.
Send control signal by remote controller, signal receiving device is passed to servomotor torque constant after receiving this signal, servomotor torque constant is by the corresponding rotation of given signal, fine folding wings backguy just follows by action, and the pivotable parts of pulling flexible wing rotates, and promptly realizes the folding of flexible wing.This driver train is installed on the flat type folding wing flapping wing aircraft, under the flat situation about flying of aircraft, controls this driver train by remote controller, aircraft is turned, and has proved that promptly it turns to function.
Claims (4)
1. a stay-supported flapping wing aircraft turns to driver train, it is characterized in that comprising servomotor torque constant, signal receiving device, folding wings backguy and turn to hinge, wherein servomotor torque constant is fixed on the flapping wing aircraft fuselage, servomotor torque constant is connected with signal receiving device by lead, signal receiving device is placed in the cabin of flapping wing aircraft, flapping wing aircraft fuselage both sides respectively are provided with one and turn to hinge, the servo-electric arbor links to each other with the center of connecting rod, the two ends of connecting rod respectively are connected with a folding wings backguy, and every folding wings backguy links to each other with the rotating element of flapping wing aircraft flexible wing by the hinge that turns to of this side.
2. stay-supported flapping wing aircraft according to claim 1 turns to driver train, it is characterized in that described servomotor torque constant adopts the DC motor of steering wheel or band coder.
3. stay-supported flapping wing aircraft according to claim 1 turns to driver train, it is characterized in that the described hinge that turns to is to be positioned on the fuselage of wing front end.
4. stay-supported flapping wing aircraft according to claim 1 turns to driver train, it is characterized in that described servomotor torque constant is fixed on the center-of-gravity position of flapping wing aircraft fuselage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009200138942U CN201442653U (en) | 2009-05-22 | 2009-05-22 | Guyed flapping-wing air vehicle steering driving mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009200138942U CN201442653U (en) | 2009-05-22 | 2009-05-22 | Guyed flapping-wing air vehicle steering driving mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201442653U true CN201442653U (en) | 2010-04-28 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009200138942U Expired - Fee Related CN201442653U (en) | 2009-05-22 | 2009-05-22 | Guyed flapping-wing air vehicle steering driving mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201442653U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102267566A (en) * | 2011-06-09 | 2011-12-07 | 西北工业大学 | Stepless speed-changing flapping wing driving mechanism |
| CN104354861A (en) * | 2014-12-15 | 2015-02-18 | 佛山市神风航空科技有限公司 | Flat-plate ornithopter with servo motor |
| CN109835481A (en) * | 2017-11-29 | 2019-06-04 | 中国科学院沈阳自动化研究所 | A kind of flapping wing aircraft to be flown by aerofoil Deformation control |
| CN113148144B (en) * | 2021-04-07 | 2022-07-19 | 吉林大学 | Foldable bionic flapping wing and aircraft |
-
2009
- 2009-05-22 CN CN2009200138942U patent/CN201442653U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102267566A (en) * | 2011-06-09 | 2011-12-07 | 西北工业大学 | Stepless speed-changing flapping wing driving mechanism |
| CN104354861A (en) * | 2014-12-15 | 2015-02-18 | 佛山市神风航空科技有限公司 | Flat-plate ornithopter with servo motor |
| CN109835481A (en) * | 2017-11-29 | 2019-06-04 | 中国科学院沈阳自动化研究所 | A kind of flapping wing aircraft to be flown by aerofoil Deformation control |
| CN109835481B (en) * | 2017-11-29 | 2021-09-28 | 中国科学院沈阳自动化研究所 | Flapping wing aircraft capable of controlling flight through wing surface deformation |
| CN113148144B (en) * | 2021-04-07 | 2022-07-19 | 吉林大学 | Foldable bionic flapping wing and 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: 20100428 Termination date: 20100522 |