CN105217032A - Bionic aircraft - Google Patents
Bionic aircraft Download PDFInfo
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- CN105217032A CN105217032A CN201510720439.6A CN201510720439A CN105217032A CN 105217032 A CN105217032 A CN 105217032A CN 201510720439 A CN201510720439 A CN 201510720439A CN 105217032 A CN105217032 A CN 105217032A
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- bent axle
- bar
- rotary connection
- relative rotary
- multidirectional device
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Abstract
A kind of bionic Aircraft, two ends, motor left and right are all with transmission shaft, cabin frame is fixedly connected with deflector, deflector comprises steering gear frame, in steering gear frame, relative rotary connection has rotating shaft in horizontally disposed deflector, in deflector, in rotating shaft, relative rotary connection has vertical bar again, vertical bar lower end is fixedly connected with bar handle, upper end is fixedly connected with the transverse bar of horizontal motion all the time, transverse bar is symmetrical relative to vertical bar, flapping wing control mechanism is respectively equipped with between the transverse bar of the same side and the transmission shaft of motor, flapping wing control mechanism comprises bent axle, wherein one end of bent axle is connected with transmission shaft driven, the crank portion at bent axle other end place divides relative rotary connection to have bent axle sleeve, bent axle sleeve is fixedly connected with wing and inner edge bar, inner edge bar is positioned at inboard, inner edge bar free end is connected with multidirectional device, multidirectional device comprises rotating shaft in the outside frame of relative rotary connection and multidirectional device, inner edge bar and the relative rotary connection of rotating shaft in multidirectional device.
Description
Technical field
The present invention relates to a kind of aircraft, particularly relate to a kind of bionic Aircraft.
Background technology
Although had various aircraft now, their function has all gone back imperfection, such as: helicopter can not glide, and causes excessive fuel consumption; Fighter plane needs airfield runway, can not hovering, and speed is low will fall, and the two is once meet accident, dangerous large.
Summary of the invention
The object of this invention is to provide a kind of fuel saving, low speed elevation, bionic Aircraft without the need to airfield runway, safe in operation.
For achieving the above object, the technical solution used in the present invention is:
A kind of bionic Aircraft, comprise the cabin frame and motor that are fixedly linked, two ends, motor left and right are all with transmission shaft, it is characterized in that, cabin frame is fixedly connected with deflector, deflector comprises steering gear frame, in steering gear frame, relative rotary connection has rotating shaft in horizontally disposed deflector, in deflector, in rotating shaft, relative rotary connection has vertical bar again, vertical bar lower end is fixedly connected with bar handle, upper end is fixedly connected with the transverse bar of horizontal motion all the time, transverse bar is symmetrical relative to vertical bar, flapping wing control mechanism is respectively equipped with between the transverse bar of the same side and the transmission shaft of motor, flapping wing control mechanism comprises bent axle, wherein one end of bent axle is connected with transmission shaft driven, the crank portion at bent axle other end place divides relative rotary connection to have bent axle sleeve, bent axle sleeve is fixedly connected with wing and inner edge bar, inner edge bar is positioned at inboard, inner edge bar free end is connected with multidirectional device, multidirectional device comprises rotating shaft in the outside frame of relative rotary connection and multidirectional device, inner edge bar and the relative rotary connection of rotating shaft in multidirectional device, this outside frame in addition relative rotary connection has multidirectional device pipe link, the other end of multidirectional device pipe link is connected with the multidirectional device of another one, outside frame and the relative rotary connection of multidirectional device pipe link of this multidirectional device, rotating shaft rotary connection relative to described transverse bar in the multidirectional device of this multidirectional device.
According to described bionic Aircraft, it is characterized in that, described bent axle sleeve is fixedly connected with wing card, and described wing is fixed on bent axle sleeve and wing card by fin silk pressing.
According to described bionic Aircraft, it is characterized in that, the outer end of described bent axle is connected with the bent axle card cap that the described bent axle sleeve of restriction and bent axle depart from.
Driven by motor bent axle in the present invention constantly rotates, by the control of deflector and multidirectional device, wing can carry out rotation and flutters by the mimic biology wing, rotating at wing flutters in process, the angle of inclination of wing can be controlled, this aircraft is made to complete flight, glide and other action, just can low speed elevation, therefore fuel saving, safe in operation without the need to airfield runway.
Accompanying drawing explanation
Fig. 1 is main TV structure schematic diagram of the present invention;
Fig. 2 is right TV structure schematic diagram of the present invention.
In accompanying drawing:
1, motor; 2, bar handle; 3, transmission shaft; 4, bent axle; 5, outside frame; 6, rotating shaft in multidirectional device; 7, inner edge bar; 8, wing; 9, bent axle card cap; 10, fin silk pressing; 11, bent axle sleeve; 12, wing card; 13, multidirectional device pipe link; 14, cabin frame; 15, steering gear frame; 16, rotating shaft in deflector; 17, vertical bar; 18, transverse bar.
Detailed description of the invention
Below in conjunction with the drawings and specific embodiments, the invention will be further described:
A kind of bionic Aircraft, as depicted in figs. 1 and 2, comprise the cabin frame 14 and motor 1 that are fixedly linked, motor about 1 two ends are all with transmission shaft 3, cabin frame 14 is fixedly connected with deflector, deflector comprises steering gear frame 15, in steering gear frame 15, relative rotary connection has rotating shaft 16 in horizontally disposed deflector, in deflector, in rotating shaft 16, relative rotary connection has vertical bar 17 again, vertical bar 17 lower end is fixedly connected with bar handle 2, upper end is fixedly connected with the transverse bar 18 of horizontal motion all the time, transverse bar 18 is symmetrical relative to vertical bar 17, flapping wing control mechanism is respectively equipped with between the transverse bar 18 of the same side and the transmission shaft 3 of motor 1, flapping wing control mechanism comprises bent axle 4, wherein one end of bent axle 4 is connected with transmission shaft 3 transmission, the crank portion at bent axle 4 other end place divides relative rotary connection to have bent axle sleeve 11, bent axle sleeve 11 is fixedly connected with wing 8 and inner edge bar 7, inner edge bar 7 is positioned at inside wing 8, inner edge bar 7 free end is connected with multidirectional device, multidirectional device comprises rotating shaft 6 in the outside frame 5 of relative rotary connection and multidirectional device, inner edge bar 7 and the relative rotary connection of rotating shaft 6 in multidirectional device, this outside frame 5 in addition relative rotary connection has multidirectional device pipe link 13, the other end of multidirectional device pipe link 13 is connected with the multidirectional device of another one, outside frame 5 and the relative rotary connection of multidirectional device pipe link 13 of this multidirectional device, rotating shaft 6 and the relative rotary connection of described transverse bar 18 in the multidirectional device of this multidirectional device.
Described bent axle sleeve 11 is fixedly connected with wing card 12, and described wing 8 is fixed on bent axle sleeve 11 and wing card 12 by fin silk pressing 10.The outer end of described bent axle 4 is connected with the bent axle card cap 9 limiting described bent axle sleeve 11 and depart from bent axle 4.
Claims (3)
1. a bionic Aircraft, comprise the cabin frame (14) and motor (1) that are fixedly linked, motor (1) two ends, left and right are all with transmission shaft (3), it is characterized in that, (14) are fixedly connected with deflector with cabin frame, deflector comprises steering gear frame (15), the upper relative rotary connection of steering gear frame (15) has rotating shaft in horizontally disposed deflector (16), in rotating shaft in deflector (16), rotary connection has vertical bar (17) relatively again, vertical bar (17) lower end is fixedly connected with bar handle (2), upper end is fixedly connected with the transverse bar (18) of horizontal motion all the time, transverse bar (18) is symmetrical relative to vertical bar (17), flapping wing control mechanism is respectively equipped with between the transverse bar (18) of the same side and the transmission shaft (3) of motor (1), flapping wing control mechanism comprises bent axle (4), wherein one end of bent axle (4) is connected with transmission shaft (3) transmission, the crank portion at bent axle (4) other end place divides relative rotary connection to have bent axle sleeve (11), bent axle sleeve (11) is fixedly connected with wing (8) and inner edge bar (7), inner edge bar (7) is positioned at wing (8) inner side, inner edge bar (7) free end is connected with multidirectional device, multidirectional device comprises rotating shaft (6) in the outside frame (5) of relative rotary connection and multidirectional device, inner edge bar (7) and rotating shaft (6) relative rotary connection in multidirectional device, this outside frame (5) in addition relative rotary connection has multidirectional device pipe link (13), the other end of multidirectional device pipe link (13) is connected with the multidirectional device of another one, outside frame (5) and the relative rotary connection of multidirectional device pipe link (13) of this multidirectional device, rotating shaft (6) and described transverse bar (18) relative rotary connection in the multidirectional device of this multidirectional device.
2. bionic Aircraft according to claim 1, is characterized in that, described bent axle sleeve (11) is fixedly connected with wing card (12), and described wing (8) is fixed on bent axle sleeve (11) and wing card (12) by fin silk pressing (10).
3. bionic Aircraft according to claim 2, is characterized in that, the outer end of described bent axle (4) is connected with the bent axle card cap (9) limiting described bent axle sleeve (11) and depart from bent axle (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510720439.6A CN105217032B (en) | 2015-10-30 | 2015-10-30 | Bionic aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510720439.6A CN105217032B (en) | 2015-10-30 | 2015-10-30 | Bionic aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105217032A true CN105217032A (en) | 2016-01-06 |
| CN105217032B CN105217032B (en) | 2017-08-11 |
Family
ID=54986413
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510720439.6A Active CN105217032B (en) | 2015-10-30 | 2015-10-30 | Bionic aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105217032B (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050269447A1 (en) * | 2004-06-08 | 2005-12-08 | Chronister Nathan J | Ornithopter with independently controlled wings |
| KR20110057414A (en) * | 2009-11-24 | 2011-06-01 | 우병화 | Ornithopter |
| CN202414161U (en) * | 2011-11-16 | 2012-09-05 | 杨玉凯 | Aircraft |
| CN202491921U (en) * | 2011-10-17 | 2012-10-17 | 湖南工学院 | Bionic ornithopter |
| CN205098476U (en) * | 2015-10-30 | 2016-03-23 | 陈德生 | Bionic aircraft |
-
2015
- 2015-10-30 CN CN201510720439.6A patent/CN105217032B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050269447A1 (en) * | 2004-06-08 | 2005-12-08 | Chronister Nathan J | Ornithopter with independently controlled wings |
| KR20110057414A (en) * | 2009-11-24 | 2011-06-01 | 우병화 | Ornithopter |
| CN202491921U (en) * | 2011-10-17 | 2012-10-17 | 湖南工学院 | Bionic ornithopter |
| CN202414161U (en) * | 2011-11-16 | 2012-09-05 | 杨玉凯 | Aircraft |
| CN205098476U (en) * | 2015-10-30 | 2016-03-23 | 陈德生 | Bionic aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105217032B (en) | 2017-08-11 |
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