CN104443378A - Small flapping wing type ducted aircraft - Google Patents
Small flapping wing type ducted aircraft Download PDFInfo
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- CN104443378A CN104443378A CN201410646229.2A CN201410646229A CN104443378A CN 104443378 A CN104443378 A CN 104443378A CN 201410646229 A CN201410646229 A CN 201410646229A CN 104443378 A CN104443378 A CN 104443378A
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Abstract
The invention relates to a small flapping wing type ducted aircraft. A flapping wing mechanism and ducted engines are organically combined, and three ducted engines and the flapping wing mechanism provide power commonly, so that multi-pose and flexible flight can be achieved; the flapping wing mechanism adopts a crank rocker based deformation mechanism to realize bionic flapping wing motion; the three ducted engines are in triangular pneumatic layout, the ducted engine positioned in the middle is a main ducted engine and is immobilized; the other two ducted engines positioned at sides are small ducted engines and can rotate obliquely; the aircraft can realize vertical take-off and landing, and at the moment, the three ducted engines can provide power in a vertical direction; when the flapping wing is immobilized at a horizontal position, the two small ducted engines obliquely rotate to a horizontal position and provide pushing force in a horizontal direction to realize high-speed level flight or steering of the aircraft; and the aircraft can cruise slowly when in a flapping wing movement manner. The small flapping wing type ducted aircraft adopts combination driving and multi-pose flight, so that the flight efficiency and the motility of the aircraft can be greatly improved.
Description
Technical field
The present invention relates to a kind of small-sized bionic aircraft, particularly about by bionic flapping-wing structure with can a kind of course of new aircraft of combining of tilting type duct driving engine.
Background technology
Common Fixed Wing AirVehicle possesses high speed operation function, but it can not vertical takeoff and landing and hovering; Rotor craft energy vertical takeoff and landing, but can not high-speed flight.Can solve the problems referred to above by tilting duct aircraft, achieving aircraft vertical takeoff and landing can put down at a high speed again and fly.This type of duct aircraft has the advantages that thrust is large, the speed of a ship or plane is high, but its outstanding shortcoming is that noise is large, efficiency is low, cruise duration is short.Comparatively speaking, flapping-wing type aircraft has the advantages such as efficiency is high, noise is little, but the shortcoming that its speed of a ship or plane is low, thrust is little also limit its application.
Summary of the invention
For the problems referred to above, the object of the present invention is to provide the small aircraft of the flight attitude maneuverability that a kind of flight efficiency is high, cruise duration long, the speed of a ship or plane is higher, noise is lower.
For achieving the above object, the present invention takes following technical scheme: by the flapping wing mechanism of aircraft with can the ingenious combination of tilting type duct driving engine, take rational aerodynamic arrangement, thus realize the flexible flight of aircraft.It is characterized in that the organic assembling of a kind of deformation mechanism based on quadric linkage and three duct driving engines.
Described flapping wing mechanism is a kind of deformation mechanism based on quadric linkage.Diagram dual gear 3 is as crank, and main connecting rod 5, auxiliary connecting rod 4, this three of auxiliary connecting rod 6 form one " triangular structure ".Rocking bar comprises two-stage, and the first order is elementary rocking bar (elementary main bone 7, elementary secondary bone 8), and the second stage is secondary rocking bar (secondary main bone 9).
Described three duct driving engines are made up of a large duct driving engine 12 and two little duct driving engines (10,11).Large duct driving engine 12 maintains static, and provides the prevailing lift of aircraft; Two little duct driving engines (10,11) can be verted, and provide lift when vertical state, thrust when then providing aircraft advance and turn to when being tilted to horizontality.
Described aerodynamic configuration of aircraft rationally, efficiently, large duct driving engine 12 is positioned in the middle of two flapping wing mechanisms, and two little duct driving engines (10,11) that can vert then are positioned on rear side of flapping wing mechanism, three duct motor mechanism triangularity aerodynamic arrangements.
Accompanying drawing explanation
Fig. 1 is appearance schematic diagram of the present invention.
Fig. 2 is inner structure schematic diagram of the present invention.
Fig. 3 is flapping wing mechanism schematic diagram of the present invention
Detailed description of the invention
Describe the present invention below in conjunction with accompanying drawing.
Flapping wing mechanism main drive motor drives synchronous pulley 1 to rotate, synchronous pulley 1 drives dual gear 3 (with large synchronous pulley consubstantiality) to rotate by Timing Belt 2, dual gear 3 drives main connecting rod 5, auxiliary connecting rod 4, auxiliary connecting rod 6 to move, main connecting rod 5, auxiliary connecting rod 4, auxiliary connecting rod 6 three form " triangular structure ", and three is relatively motionless.Main connecting rod 5, auxiliary connecting rod 4, auxiliary connecting rod 6 three drive elementary rocking bar (elementary main bone 7, elementary secondary bone 8) to move, and elementary rocking bar drives secondary rocking bar (secondary main bone 9) to move again.Elementary rocking bar and secondary rocking bar jointly complete bionic flapping-wing and move.
Steering wheel 14 rotates, and driven gear axle 13 rotates, and realizes two the little duct driving engines 10,11 be arranged on gear wheel shaft and verts.
The working process of apparatus of the present invention, comprises the following steps:
In aircraft vertical landing process, flapping wing mechanism main drive motor drives synchronous pulley 1 to rotate, thus drives dual gear 3 to rotate by Timing Belt 2, forwards certain angle to and makes flapping wing mechanism be rugosity, and keep motionless.Meanwhile, three duct driving engines 10,11,12 provide aircraft lift upwards vertically downward, make aircraft be climbed to specified altitude assignment.
Aircraft arrives after specified altitude assignment, and now flapping wing mechanism main drive motor forwards certain angle to and makes flapping wing mechanism be deployed into level attitude and keep motionless, and steering wheel 14 driven gear axle 13 rotates and makes two little duct driving engines 10,11 be tilted to level attitude simultaneously.Now two little duct driving engines 10,11 thrust of providing aircraft to advance, realizes that the high speed of aircraft is flat to fly.
After aircraft arrives intended target place, flapping wing mechanism main drive motor drives synchronous pulley 1 Periodic Rotating, realizes the flapping motion of flapping wing mechanism, for aircraft provides main lift; For avoiding lift not enough, now large duct driving engine 12 also providing unit can divide lift.Duct driving engine 10,11 still remains on level attitude, provides the thrust varied in size, realize differential steering when aircraft needs to turn to, thus makes the slow cruising flight function of aircraft in desired target area.
Claims (4)
1. one kind by distortion quadric linkage and can the small-sized flapping wings type duct aircraft that forms of tilting type duct driving engine, primarily of frame, distortion quadric linkage, Timing Belt 2, flapping wing mechanism main drive motor, steering wheel 14, gear wheel shaft 13, miniature bearing, battery, three duct driving engines (10, 11, 12), outer covering and various retaining element composition, it is characterized in that, symmetrical distortion quadric linkage is as flapping wing structure, bionic flapping-wing action is adopted to provide the major impetus of aircraft when low-speed operations, there is provided the extra power for turning to by duct driving engine simultaneously, now two of aircraft rear portion little duct driving engines (10, 11) horizontal attitude is taked, there is provided the thrust varied in size to realize the differential steering of aircraft, when aircraft high-speed flight, flapping wing structure is deployed into level attitude and maintains static, now similar fixed-wing, two little duct driving engines (10, 11) level attitude is tilted to, horizontal thrust is provided.
2. small-sized flapping wings type duct aircraft according to claim 1, it is characterized in that, flapping wing mechanism main drive motor is fixed in frame, dual gear 3 is driven to rotate by Timing Belt 2, dual gear 3, as the crank of distortion quadric linkage, drives whole distortion quadric linkage to realize the flapping motion of imitative bird.
3. the distortion quadric linkage of small-sized flapping wings type duct aircraft according to claim 2, it is characterized in that, dual gear 3 center is connected with frame, edge protuberance is connected with main connecting rod 5 and two auxiliary connecting rods (4,6), auxiliary connecting rod 6 one end is connected with elementary main bone 7, the other end is connected with elementary secondary bone 8, and elementary main bone 7 is connected with secondary main bone 9 with the other end of elementary secondary bone 8, and all connections all require rotatable and non-interference.
4. small-sized flapping wings type duct aircraft according to claim 1, it is characterized in that, steering wheel, battery, Minisize axial bearing are all fixed on body plate, gear wheel shaft 13 is connected with bearing seat by miniature bearing, gear on gear wheel shaft and the gears meshing on steering wheel, the two ends of gear wheel shaft 13 and two little duct driving engines (10,11) that can vert are connected, for accurately controlling turning to of tilting duct driving engine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410646229.2A CN104443378A (en) | 2014-11-14 | 2014-11-14 | Small flapping wing type ducted aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410646229.2A CN104443378A (en) | 2014-11-14 | 2014-11-14 | Small flapping wing type ducted aircraft |
Publications (1)
| Publication Number | Publication Date |
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| CN104443378A true CN104443378A (en) | 2015-03-25 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
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| CN201410646229.2A Pending CN104443378A (en) | 2014-11-14 | 2014-11-14 | Small flapping wing type ducted aircraft |
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| CN (1) | CN104443378A (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105227119A (en) * | 2015-09-30 | 2016-01-06 | 黑龙江兴安新能源股份有限公司 | A kind of with crank and rocker mechanism pull expansion solar panels |
| CN105480404A (en) * | 2015-12-21 | 2016-04-13 | 哈尔滨工业大学 | Wing tip winglet structure with variable mounting angles |
| CN105620747A (en) * | 2016-03-03 | 2016-06-01 | 上海工程技术大学 | Flapping-wing mechanism capable of achieving motion trail shaped like horizontal Arabic number eight |
| CN106741918A (en) * | 2017-01-14 | 2017-05-31 | 陕西捷恒新材料有限责任公司 | The axle flying vehicles control structure of skew product vector two |
| CN107161334A (en) * | 2017-05-31 | 2017-09-15 | 佛山市神风航空科技有限公司 | A kind of flapping wing helicopter |
| CN108674651A (en) * | 2018-04-11 | 2018-10-19 | 南宁蜂虎科技有限公司 | Flapping wing device and flapping-wing aircraft |
| CN108891591A (en) * | 2018-07-02 | 2018-11-27 | 北京电子工程总体研究所 | A kind of aircraft |
| CN112977817A (en) * | 2021-04-26 | 2021-06-18 | 吉林大学 | Flapping wing aircraft |
| CN113428361A (en) * | 2021-07-06 | 2021-09-24 | 中国人民解放军总参谋部第六十研究所 | Intelligent separable variant vertical take-off and landing unmanned platform and control strategy thereof |
| CN116674747A (en) * | 2023-08-03 | 2023-09-01 | 西南石油大学 | Flexible flapping wing and ducted propeller hybrid-driven simulated baton floating aircraft |
| CN116853496A (en) * | 2022-02-21 | 2023-10-10 | 浙江万里学院 | Flying device and flying method |
-
2014
- 2014-11-14 CN CN201410646229.2A patent/CN104443378A/en active Pending
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105227119A (en) * | 2015-09-30 | 2016-01-06 | 黑龙江兴安新能源股份有限公司 | A kind of with crank and rocker mechanism pull expansion solar panels |
| CN105480404A (en) * | 2015-12-21 | 2016-04-13 | 哈尔滨工业大学 | Wing tip winglet structure with variable mounting angles |
| CN105480404B (en) * | 2015-12-21 | 2018-07-03 | 哈尔滨工业大学 | A kind of variable established angle winglet structure for being used to improve pneumatic efficiency |
| CN105620747A (en) * | 2016-03-03 | 2016-06-01 | 上海工程技术大学 | Flapping-wing mechanism capable of achieving motion trail shaped like horizontal Arabic number eight |
| CN106741918B (en) * | 2017-01-14 | 2022-01-18 | 陕西捷恒航空技术有限责任公司 | Oblique product vector diaxon aircraft control structure |
| CN106741918A (en) * | 2017-01-14 | 2017-05-31 | 陕西捷恒新材料有限责任公司 | The axle flying vehicles control structure of skew product vector two |
| CN107161334A (en) * | 2017-05-31 | 2017-09-15 | 佛山市神风航空科技有限公司 | A kind of flapping wing helicopter |
| CN108674651A (en) * | 2018-04-11 | 2018-10-19 | 南宁蜂虎科技有限公司 | Flapping wing device and flapping-wing aircraft |
| CN108674651B (en) * | 2018-04-11 | 2021-08-03 | 南宁蜂虎科技有限公司 | Flapping wing device and flapping wing machine |
| CN108891591A (en) * | 2018-07-02 | 2018-11-27 | 北京电子工程总体研究所 | A kind of aircraft |
| CN112977817A (en) * | 2021-04-26 | 2021-06-18 | 吉林大学 | Flapping wing aircraft |
| CN113428361A (en) * | 2021-07-06 | 2021-09-24 | 中国人民解放军总参谋部第六十研究所 | Intelligent separable variant vertical take-off and landing unmanned platform and control strategy thereof |
| CN113428361B (en) * | 2021-07-06 | 2022-11-25 | 中国人民解放军总参谋部第六十研究所 | Intelligent separable variant vertical take-off and landing unmanned platform and control strategy thereof |
| CN116853496A (en) * | 2022-02-21 | 2023-10-10 | 浙江万里学院 | Flying device and flying method |
| CN116674747A (en) * | 2023-08-03 | 2023-09-01 | 西南石油大学 | Flexible flapping wing and ducted propeller hybrid-driven simulated baton floating aircraft |
| CN116674747B (en) * | 2023-08-03 | 2023-10-20 | 西南石油大学 | Flexible flapping wing and ducted propeller hybrid-driven simulated baton floating aircraft |
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Application publication date: 20150325 |